### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Number: 777-25-0482**  Original Issue: February 24, 2011 Revision 1: February 21, 2012 ATA System: 2521 5313 **SUBJECT:** EQUIPMENT/FURNISHINGS - Passenger Compartment - Lowered Ceiling Panel - Section 41 - Overhead Space Utilization (OSU) Ceiling - Change To Strengthen Support Structure 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 1 of 61 3.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 2 of 61 **BOEING SERVICE BULLETIN 777-25-0482**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 16 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 24 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 25 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 FIGURE 1: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE REMOVAL. . . . . . . . . . 30 FIGURE 2: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION. . . . . . . 33 FIGURE 3: LEFT SIDE TIE ROD AND ATTACH FITTING INSTALLATION [Group 1]. . . . . . . . . 40 FIGURE 4: LEFT SIDE TIE ROD AND ATTACH FITTING INSTALLATION [Group 2]. . . . . . . . . 43 FIGURE 5: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE REMOVAL. . . . . . . . . 46 FIGURE 6: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION. . . . . . . 49 FIGURE 7: RIGHT SIDE TIE ROD AND ATTACH FITTING INSTALLATION [Group 1]. . . . . . . . . 56 FIGURE 8: RIGHT SIDE TIE ROD AND ATTACH FITTING INSTALLATION [Group 2]. . . . . . . . . 59

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 3 of 61 **BOEING SERVICE BULLETIN 777-25-0482**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 4 of 61 **BOEING SERVICE BULLETIN 777-25-0482**

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### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Revision Transmittal Sheet**  **Number: 777-25-0482** Original Issue: February 24, 2011 Revision 1: February 21, 2012 ATA System: 2521 5313 **SUBJECT:** EQUIPMENT/FURNISHINGS - Passenger Compartment - Lowered Ceiling Panel - Section 41 - Overhead Space Utilization (OSU) Ceiling - Change To Strengthen Support Structure This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. **REASON FOR REVISION** This revision is sent to incorporate changes found during the validation of this service bulletin. As a part of a service bulletin validation program, this change was completed on airplane WD796 by Service Bulletin 777-25-0482 Original Issue before the release of Revision 01 of this service bulletin. The change completed on airplane WD796 by Service Bulletin 777-25-0482 Original Issue is equivalent to the release of Revision 01of this service bulletin. Airplane WD796 has the configuration of a Group 2 airplane. These sections are changed: 1. Summary - Background - Validation statement added. 2. Summary - Manpower - Time for access and restoring access added. 3. Paragraph 1.C., Reason - Validation statement added. 4. Paragraph 1.G., Manpower - Time for access and restoring access added. 5. Paragraph 1.J.1, Existing Data - Standard Wiring Practices Manual (SWPM) and 777 Aircraft Maintenance Manual (AMM) references added. 6. Paragraph 2.C.1., Kits/Parts - Changed part number for 1 bolt. 7. Paragraph 3.A., General Information - Current general notes added. 8. Paragraph 3.B., Work Instructions - Instruction for Access and Restoring Access added.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 5 of 619. Figures 3, and 4: a. Changed part number for 1 bolt in Step Table. b. Added information to relocate ground if required. 10. Figure 6: a. Instruction is added to the Step Table regarding a possibly blocked ceiling panel insert. 11. Figures 7, and 8: a. Changed part number for 1 bolt in Step Table. b. Added information to relocate ground if required. c. In Step 1 and Step 3 of Step Tables, changed More Data for Bushing to Far Side from Near Side. 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** February 24, 2011 Original Issue: February 21, 2012 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 6 of 61 **BOEING SERVICE BULLETIN 777-25-0482**

### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Summary**  **Number: 777-25-0482** Original Issue: February 24, 2011 Revision 1: February 21, 2012 ATA System: 2521 5313 **SUBJECT:** EQUIPMENT/FURNISHINGS - Passenger Compartment - Lowered Ceiling Panel - Section 41 - Overhead Space Utilization (OSU) Ceiling - Change To Strengthen Support Structure BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** This service bulletin provides instructions and a kit of parts to strengthen the structure which supports the forward lowered ceiling panels for some 777 model airplanes. If you do not do this service bulletin and a 9G forward load condition occurs, the forward lowered ceiling panels and support structure could become dislodged and injure personnel or interfere with emergency evacuation. The possibility of a 9G forward load when landing is small. No operator has reported dislodged ceiling panels from such a load. The support structure was found to be under strength during the design review of a new section 41 lowered ceiling configuration. Only airplanes incorporating the Overhead Space Utilization (OSU) option would have under strength structure. The OSU option includes overhead stowage boxes in the ceiling inboard of left and right door 1. The under strength area supports lowered ceiling panels immediately aft of these overhead stowage boxes. This service bulletin provides for increasing strength by installing thicker structure and an additional load path on each side. Boeing Service Related Problem (SRP) 777-SRP-25-0289 is related to this service bulletin. This SRP is described in Fleet Team Digest Article 777 FTD 25-09010. As a part of a service bulletin validation program, this change was completed on airplane WD796 by Service Bulletin 777-25-0482 Original Issue before the release of Revision 01 of this service bulletin. The change completed on airplane WD796 by Service Bulletin 777-25-0482 Original Issue is equivalent to the release of Revision 01of this service bulletin. Airplane WD796 has the configuration of a Group 2 airplane.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 7 of 61**ACTION (PRR 62224)** In the forward lowered ceiling area, remove the forward overhead stowage bin modules and adjacent aft ceiling panel to expose the support structure for the lowered ceiling panels in section 41. Disconnect a tie rod and remove two C-channels and related brackets from both left and right side ceiling panel support structure. Install new support channel assemblies composed of C-channels having thicker cross sections. The new assemblies also include fittings for attaching two tie rods in place of fittings for attaching one tie rod. Add a new load path on each side by adding new fittings to the rails above the changed structure and adding new tie rods between the fittings on new support structure and the new fittings on the rails above. If a ground stud occupies a hole required for the new fitting, relocate the ground to an adjacent hole. Reconnect the existing tie rods. **EFFECTIVITY** 777-200, -200LR and -300ER airplanes incorporating Overhead Space Utilization (OSU) option. 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. Boeing recommends that the changes given in this service bulletin be done within 5 years after the original issue date of this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of January 16, 2008. Please refer to Paragraph 2.B., Industry Support Information. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  12.00 22.50 All
**MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 8 of 61 **BOEING SERVICE BULLETIN 777-25-0482**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 9 of 61 **BOEING SERVICE BULLETIN 777-25-0482**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 10 of 61 **BOEING SERVICE BULLETIN 777-25-0482**

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### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Number: 777-25-0482**  Original Issue: February 24, 2011 Revision 1: February 21, 2012 ATA System: 2521 5313 **SUBJECT:** EQUIPMENT/FURNISHINGS - Passenger Compartment - Lowered Ceiling Panel - Section 41 - Overhead Space Utilization (OSU) Ceiling - Change To Strengthen Support Structure BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **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 airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 62224 for data about this change.
**DESCRIPTION CONFIGURATION**  **GROUP** 777-200 and 777-300ER Airplanes with Overhead Space Utilization (OSU) Option and line number from 423 through 494. - 1
777-200, 777-200LR, and 777-300ER Airplanes with Overhead Space Utilization (OSU) Option and line number from 497 through 751. - 2

Airplane Models: 777-200, 777-200LR, 777-300ER **Group Variable Number**  2 WC221 - WC222 1 WC301 - WC306 2 WC307 - WC308 1 WC381 - WC388

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 11 of 61**Group Variable Number**  2 WC389 - WC395 2 WC486 - WC493 2 WC506 - WC508 2 WC531 - WC536 2 WC546 - WC548 2 WC556 2 WC566 - WC567 2 WD001 - WD002 2 WD011 - WD015 2 WD031 - WD036 2 WD066 - WD067 1 WD501 - WD502 2 WD503 - WD510 1 WD521 - WD526 2 WD527 - WD539 2 WD546 - WD552 1 WD561 2 WD562 - WD573 2 WD581 - WD591 2 WD606 - WD609 2 WD621 - WD632 2 WD651 - WD661 2 WD671 - WD675 2 WD741 - WD750 2 WD761 - WD770 2 WD786 - WD788 2 WD796 - WD804 2 WD826 - WD830 2 WD871 - WD875 2 WD911 - WD912 2 WD936 - WD939 2 WD966

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 12 of 61 **BOEING SERVICE BULLETIN 777-25-0482**2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** This service bulletin provides instructions and a kit of parts to strengthen the structure which supports the forward lowered ceiling panels for some 777 model airplanes. If you do not do this service bulletin and a 9G forward load condition occurs, the forward lowered ceiling panels and support structure could become dislodged and injure personnel or interfere with emergency evacuation. The possibility of a 9G forward load when landing is small. No operator has reported dislodged ceiling panels from such a load. The support structure was found to be under strength during the design review of a new section 41 lowered ceiling configuration. Only airplanes incorporating the Overhead Space Utilization (OSU) option would have under strength structure. The OSU option includes overhead stowage boxes in the ceiling inboard of left and right door 1. The under strength area supports lowered ceiling panels immediately aft of these overhead stowage boxes. This service bulletin provides for increasing strength by installing thicker structure and an additional load path on each side. Boeing Service Related Problem (SRP) 777-SRP-25-0289 is related to this service bulletin. This SRP is described in Fleet Team Digest Article 777-FTD-25-09010. Revision 01 is sent to make changes found to be required during validation of the service bulletin. Changes include adding access instructions, reducing the grip length of a bolt, relocating a ground stud if required, and installing a bushing far side instead of near side. As a part of a service bulletin validation program, this change was completed on airplane WD796 by Service Bulletin 777-25-0482 Original Issue before the release of Revision 01 of this service bulletin. The change completed on airplane WD796 by Service Bulletin 777-25-0482 Original Issue is equivalent to the release of Revision 01of this service bulletin. Airplane WD796 has the configuration of a Group 2 airplane. The data given in Information Notice 777-25-0482 IN 01 is included in this revision. **D. Description** In the forward lowered ceiling area, remove the forward overhead stowage bin modules and adjacent aft ceiling panel to expose the support structure for the lowered ceiling panels in section 41. Disconnect a tie rod and remove two C-channels and related brackets from both left and right side ceiling panel support structure. Install new support channel assemblies composed of C-channels having thicker cross sections. The new assemblies also include fittings for attaching two tie rods in place of fittings for attaching one tie rod. Add a new load path on each side by adding new fittings to the rails above the changed structure and adding new tie rods between the fittings on new support structure and the new fittings on the rails above. If a ground stud occupies a hole required for the new fitting, relocate the ground stud to an adjacent hole. Reconnect the existing tie rods.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 13 of 61 **BOEING SERVICE BULLETIN 777-25-0482**Airplanes are divided into two groups because of a difference in the width of the new tie rod fitting and the lattice rail to which the fitting is attached. The work is the same for both groups. 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:**
**Affected Maintenance Zones Zone**  **Model** 221, 222, 223, 224 777-200, 777-300ER **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 221, 222, 223, 224 777-200, 777-200LR, 777- 300ER **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 recommends that the changes given in this service bulletin be done within 5 years after the original issue date of this service bulletin. **F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task hours necessary to do this change 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 14 of 61 **BOEING SERVICE BULLETIN 777-25-0482**• 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. **Group 1: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 1.00 2.00 2 Open Access 1.25 2.50 2 Figure 1 3.00 6.00 2 Figure 2 0.75 0.75 1 Figure 3 1.25 2.50 2 Figure 5 3.00 6.00 2 Figure 6 0.75 0.75 1 Figure 7 1.00 2.00 2 Close Access 12.00 22.50 TOTAL FOR EACH AIRPLANE **Group 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 1.00 2.00 2 Open Access 1.25 2.50 2 Figure 1 3.00 6.00 2 Figure 2 0.75 0.75 1 Figure 4 1.25 2.50 2 Figure 5 3.00 6.00 2 Figure 6 0.75 0.75 1 Figure 8 1.00 2.00 2 Close Access 12.00 22.50 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane**  +2053.3 +5.3 777-200 +940.2 +5.3 777-300

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 15 of 61 **BOEING SERVICE BULLETIN 777-25-0482 I. Electrical Load Data**  Not changed. **J. References** 1. Existing Data a. Engineering Change Memo PRR 62224 b. Standard Wiring Practices Manual (SWPM) 20-20-10 c. 777 Aircraft Maintenance Manual (AMM) 25-21-07, 25-28-07 d. 777 Fleet Team Digest (FTD) 25-09010 e. Service Related Problem (SRP) 777-SRP-25-0289 f. 777-200 Structural Repair Manual (SRM) 51-20-01, 51-20-10, 51-40-08 g. 777-300 Structural Repair Manual (SRM) 51-20-01, 51-20-10, 51-40-08 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin
**Title Drawing Number**  TIE ROD INSTL-LOWERED CEILING 413W1200 SUPPORT STRUCTURE INSTL - LOWERED CEILING, DOOR 1 413W1201 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications: **Chapter-Section**

**Publication** 53-13 777 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 does not affect FCS, therefore DTIs are not necessary.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 16 of 61 **BOEING SERVICE BULLETIN 777-25-0482 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: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 17 of 61 **BOEING SERVICE BULLETIN 777-25-0482**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 18 of 61 **BOEING SERVICE BULLETIN 777-25-0482**

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 **Group 1: 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** 

$13,329.00 514 1 October 13, 2011 TOP KIT - REWORKOF OSU TYPE SECTION 41 LOWERED CEILING SUPPORT STRUCTURE, GROUP 1 005W3441-1

$13,329.00 514 6 February 10, 2012 TOP KIT - REWORKOF OSU TYPE SECTION 41 LOWERED CEILING SUPPORT STRUCTURE, GROUP 1 005W3441-1

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 19 of 61 **BOEING SERVICE BULLETIN 777-25-0482 Group 2:**  **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** 

$13,329.00 514 25 October 13, 2011 TOP KIT - REWORKOF OSU TYPE SECTION 41 LOWERED CEILING SUPPORT STRUCTURE, GROUP 1 005W3441-2

**B. Industry Support Information** Boeing warranty remedies are available for 777 airplanes in warranty as of January 16, 2008. For task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin number and reference the airplane variable numbers in your purchase order. **C. Parts Necessary For Each Airplane** 1. Kits/Parts To get the kits 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. The Top Kit is divided into Figure kits for each installation figure shown in the table below. **Figure Kit 8**  **7 6**  **4 3**  **2 Top Kit** 

- 1 1
- 1 1 005W3441-1 1
- 1 1
- 1 005W3441-2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 20 of 61 **BOEING SERVICE BULLETIN 777-25-0482 Group 1:** 
**KIT 005W3441-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 7**  **6 3**  **2 QTY**  (a),(b) 413W1221-105B AND 413W1221- 113B AND 413W1221-35B AND 413W1221-7 SUPPORTSTRUCTURE ASSY - LOWERED CEILING, SECT 41 1 413W1210-105B

(a),(b) 413W1221-106B AND 413W1221- 113B AND 413W1221-35 AND 413W1221-7 SUPPORTSTRUCTURE ASSY - LOWERED CEILING, SECT 41 1 413W1210-106B

(a),(b) 413W1221-55B GUSSET 2 2 413W1221-246B (a),(b) 413W1221-31B GUSSET 1 1 413W1221-269B (a),(b) 413W1221-33B GUSSET 1 1 413W1221-270B (a),(b) 413W1221-35B ANGLE 1 1 413W1221-271B (a),(b) 413W1221-60B CORNER BRACK- ET 1 1 413W1221-272B (a),(b) 413W1221-60B CORNER BRACK- ET 1 1 413W1221-273B
MISCELLANEOUS - MACHINE PART 1 1 422W2165-111
TIE ROD ASSY 1 1 777081-178 BUSHING 2 2 BACB28AK04-024 BUSHING 1 1 BACB28AK04-038 (c) BOLT 2 2 BACB30NR4K15 (c) BOLT, HEX HEAD 1 1 BACB30NR4K17 (c) BOLT, PROTRUD- ING HD 8 8 BACB30NX5HK3 (c) BOLT 4 4 BACB30VF3K5 (c) BOLT, 100 DEG HEX DR 12 12 BACB30YP5K4 COLLAR, PRELOAD 10 10 BACC30BH5 COLLAR, SHEAR 12 12 BACC30BL5 NUT 3 3 BACN10YR4CD

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 21 of 61 **BOEING SERVICE BULLETIN 777-25-0482 Group 1:** 
**KIT 005W3441-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 7**  **6 3**  **2 QTY**  (c) RIVET 5 5 BACR15BB4D6C (c) RIVET, UNIVER- SAL HD 13 12 BACR15FT5D6C (c) RIVET, UNIVER- SAL HD 10 10 BACR15FT5D7C (c) RIVET 5 5 BACR15GF4D6 SHIM, LAMINATED 1 1 BACS40R009D024F
WASHER 3 3 BACW10BP4CD WASHER 3 3 BACW10BP4DP (a) Discard the existing part. (b) You cannot use the existing part to replace the new or changed part. (c) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. **Group 2:**
**KIT 005W3441-2**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **6 4**  **2 QTY**  (a), (b) 413W1221-105B AND 413W1221- 113B AND 413W1221-35 AND 413W1221-7 SUPPORTSTRUCTURE ASSY - LOWERED CEILING, SECT 41 1 413W1210-105B

(a), (b) 413W1221-106B AND 413W1221- 113B AND 413W1221-35 AND 413W1221-7 SUPPORTSTRUCTURE ASSY - LOWERED CEILING, SECT 41 1 413W1210-106B

(a), (b) 413W1221-55B GUSSET 2 2 413W1221-246B (a), (b) 413W1221-31B GUSSET 1 1 413W1221-269B (a), (b) 413W1221-33B GUSSET 1 1 413W1221-270B

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 22 of 61 **BOEING SERVICE BULLETIN 777-25-0482 Group 2:** 
**KIT 005W3441-2**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **6 4**  **2 QTY**  (a), (b) 413W1221-35B ANGLE 1 1 413W1221-271B (a), (b) 413W1221-60B CORNER BRACK- ET 1 1 413W1221-272B (a), (b) CORNER BRACK- ET 1 1 413W1221-273B
MISCELLANEOUS - MACHINE PART 1 1 422W2165-108
TIE ROD ASSY 1 1 777081-178 BUSHING 2 2 BACB28AK04-024 BUSHING 1 1 BACB28AK04-038 (c) BOLT 2 2 BACB30NR4K15 (c) BOLT, HEX HEAD 1 1 BACB30NR4K17 (c) BOLT, PROTRUD- ING HD 8 8 BACB30NX5HK3 (c) BOLT 4 4 BACB30VF3K5 (c) BOLT, 100 DEG HEX DR 12 12 BACB30YP5K4 (c) COLLAR, PRELOAD 10 10 BACC30BH5 COLLAR, SHEAR 12 12 BACC30BL5 NUT 3 3 BACN10YR4CD (c) RIVET 5 5 BACR15BB4D6C (c) RIVET, UNIVER- SAL HD 13 12 BACR15FT5D6C (c) RIVET, UNIVER- SAL HD 10 10 BACR15FT5D7C (c) RIVET 5 5 BACR15GF4D6 SHIM, LAMINATED 1 1 BACS40R009D024F
WASHER 3 3 BACW10BP4CD WASHER 3 3 BACW10BP4DP (a) Discard the existing part.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 23 of 61 **BOEING SERVICE BULLETIN 777-25-0482 Group 2:** 
**KIT 005W3441-2**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **6 4**  **2 QTY**  (b) You cannot use the existing part to replace the new or changed part. (c) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. 2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** (a) Primer 2 oz BMS 10-11, Type I (a) Paint 2 oz BMS 10-83, Type III Enamel, Boeing Color 8328 (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 **NOTE:**Parts below are not replaced individually but are replaced by a part of an assembly as explained in the Notes column.
**Notes QTY**  **Name Existing Part Number**  413W1221- 245B (a) 1 Member 413W1221-105B
413W1221- 267B (a) , (b) 2 Member 413W1221-113B
413W1221-33 (a) , (b) , 413W1221-270 (c) , (d) 4 Gusset 413W1221-33

413W1221-35 (a) , (b) , 413W1221-271 (c) , (d) 4 Angle 413W1221-35

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 24 of 61 **BOEING SERVICE BULLETIN 777-25-0482 Notes**  **QTY Name**  **Existing Part Number** 413W1221-269 (a) , (b) 2 Fitting Assy 413W1224-7
413W1221-269 (a) , (d) 2 Gusset 413W1221-31
413W1221-246 (c) , (d) 4 Gusset 413W1221-55 qty (2) 413W1221-273 and qty (2) 413W1221-272 (c) , (d) 4 Angle 413W1221-60

413W1221- 268B (b) 1 Member 413W1221-106B (a) Part of Support Structure Assy 413W1210-105B (b) Part of Support Structure Assy 413W1210-106B (c) Part in installation of Support Structure Assy 413W1210-105B (d) Part in installation of Support Structure Assy 413W1210-106B **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. Operators may choose to fabricate locating templates. Refer to FIGURE 2, Step 1, and to FIGURE 6, Step 1, for information.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 25 of 61 **BOEING SERVICE BULLETIN 777-25-0482**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 26 of 61 **BOEING SERVICE BULLETIN 777-25-0482**

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. 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. 6. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 27 of 61 **BOEING SERVICE BULLETIN 777-25-0482**8. 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. 9. 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. 10. 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. 11. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. **B. WORK INSTRUCTIONS** 1. Access: a. Remove overhead stowage box and module inboard of Door 1 left and right. Refer to 777 AMM 25-28-07 as an accepted procedure. b. Remove lowered ceiling panel(s) immediately aft of overhead stowage box opening. Refer to 777 AMM 25-21-07 as an accepted procedure. 2. Remove specific left side lowered ceiling support structure members in accordance with FIGURE 1. 3. Install new left side lowered ceiling support structure members in accordance with FIGURE 2. 4. Install new left side tie rod attach fitting and tie rods on:

a.**Group 1:** In accordance with FIGURE 3. b.**Group 2:** In accordance with FIGURE 4. 5. Remove specific right side lowered ceiling support structure members in accordance with FIGURE 5. 6. Install new right side lowered ceiling support structure members in accordance with FIGURE 6. 7. Install new right side tie rod attach fitting and tie rods on:

a.**Group 1:** In accordance with FIGURE 7. b.**Group 2:** In accordance with FIGURE 8.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 28 of 61 **BOEING SERVICE BULLETIN 777-25-0482**8. Restore Access: a. Install lowered ceiling panel(s) immediately aft of overhead stowage box opening. Refer to 777 AMM 25-21-07 as an accepted procedure. b. Install overhead stowage box and module inboard of Door 1 left and right. Refer to 777 AMM 25-28-07 as an accepted procedure. 9. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1: February 21, 2012 29 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 1: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE REMOVAL**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 30 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 1: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE REMOVAL**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 31 of 61 **BOEING SERVICE BULLETIN 777-25-0482**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 this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Disconnect at lower end. Leave upper end attached. Rotate tie rod up and out ofwork area and secure it temporarily. 1 777084-181 Tie Rod Disconnect 1

1 BACB30NR4K14 Bolt Remove 2 NAS1149D0432J Washer Remove 1 BACB28Y4C024 Bushing Remove 1 BACN10YR4CD Nut Remove 13 BACR15FT5D*C Rivet Remove 2 2 BACR15GF4D* Rivet Remove 3 4 BACB30NX5HK3 Bolt Remove 4 4 BACC30BH5 Collar Remove Remove the following parts as an assembly: 1
- SUPPORT STRUC- TURE ASSY Remove 5

1 413W1221-105B Member Remove 1 413W1221-113B Member Remove 2 413W1221-33 Gusset Remove 2 413W1221-35 Angle Remove 1 413W1224-7 Fitting Assy Remove 1 413W1221-31 Gusset Remove 2 413W1221-55 Gusset Remove 2 413W1221-60 Angle Remove (a)

- - Structure Inspect 6 (a) Do a general visual inspection of the existing structure in the area of rework. Remove nicks, scratches,gouges and/or minor corrosion, and protect all exposed aluminum in and around the repair areas in accordance with 777-200 SRM 51-20-01 or 777-300 SRM 51-20-01 as applicable.

**FIGURE 1: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE REMOVAL (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 32 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 2: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION**  **(SHEET 1 OF 7)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 33 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 2: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION**  **(SHEET 2 OF 7)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 34 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 2: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION**  **(SHEET 3 OF 7)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 35 of 61 **BOEING SERVICE BULLETIN 777-25-0482**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 this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Use existing ceiling panel as locatingtemplate (or fabricate similar rigid template). Make sure that ceilingpanel can be installed and that tie rods align with new Support StructureAssy before attaching gussets and angles. 1 413W1210-105B SUPPORT STRUC-TURE ASSY - LOWERED CEILING, SECT 41 Install (New) 1

2 413W1221-246B GUSSET Install (New) 2 Use existing holes in rail. Drill new holes in gusset. 4 BACR15FT5D6C RIVET, UNIVERSAL HD Install (New)

Use pilot holes in Step 2 gusset. Drill new holes in Step 1 Support Structure Assy. 4 BACR15FT5D7C RIVET, UNIVERSAL HD Install (New) 3

1 413W1221-269B GUSSET Install (New) 4 Use existing holes in rail. Drill new holes in gusset. 3 BACR15FT5D6C RIVET, UNIVERSAL HD Install (New)

Use pilot holes in Step 4 gusset. Drill new holes in Step 1 Support Structure Assy. 2 BACR15FT5D6C RIVET, UNIVERSAL HD Install (New) 5

1
- Ceiling Panel or Tem- plate Remove 6

**FIGURE 2: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION (SHEET 4 OF 7)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 36 of 61 **BOEING SERVICE BULLETIN 777-25-0482 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 1 413W1221-270B GUSSET Install (New) 7 Use shim if required between new gussetand existing rail. Remove 0.003 thicklaminations as necessary. A gap of0.005 max is permitted between rail andgusset before fastener installation. 1 BACS40R009D024F SHIM, LAMINATED Install (New)

Use existing holes in rail. Drill new holes in gusset and shim.Install with countersunk head on ceiling panel side of rail. 2 BACR15GF4D6 RIVET Install (New)

Use pilot holes in Step 7 gusset. Drill new holes in Step 1 Support Structure Assy. Install with countersunk head on ceiling panel side of rail. 2 BACR15GF4D6 RIVET Install (New) 8

1 413W1221-271B ANGLE Install (New) 9 Use existing holes inrail. Drill holes in angle. 4 BACR15FT5D7C RIVET, UNIVERSAL HD Install (New)

Use pilot holes in Step 9 angle. Drillholes in Step 1 Support Structure Assy. 4 BACR15BB4D6C RIVET Install (New) 10

1 413W1221-272B CORNER BRACKET Install (New) 11 Use existing hole in rail. Drill new hole 0.161 - 0.164 in. dia. in bracket. Install with head on bracket side. (a) 1 BACB30NX5HK3 BOLT, PROTRUDING HD Install (New)

Collar on rail side. 1 BACC30BH5 COLLAR, PRELOAD Install (New)

**FIGURE 2: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION (SHEET 5 OF 7)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 37 of 61 **BOEING SERVICE BULLETIN 777-25-0482 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Use pilots in Step 11 bracket. Drill holes 0.161 - 0.164 in. dia. in rail. Install with head on bracket side. 3 BACB30NX5HK3 BOLT, PROTRUDING HD Install (New) 12

Collar on rail side. 3 BACC30BH5 COLLAR, PRELOAD Install (New) Use pilots in Step 11 bracket. Drill holes 0.161 - 0.164 in. dia.in rail or Step 1 Support Structure Assy.Install with countersunk head on rail or Support Structure Assy side. 6 BACB30YP5K4 BOLT, 100 DEG HEX DR Install (New) 13

Collar on bracket side. 6 BACC30BL5 COLLAR, SHEAR Install (New)

1 413W1221-273B CORNER BRACKET Install (New) 14 Use existing hole in rail. Drill new hole 0.161 - 0.164 in. dia. in bracket. Install with head on bracket side. (a) 1 BACB30NX5HK3 BOLT, PROTRUDING HD Install (New)

Collar on rail side. 1 BACC30BH5 COLLAR, PRELOAD Install (New) Use pilots in Step 14 bracket. Drill holes 0.161 - 0.164 in. dia. in rail. Install with head on bracket side. 3 BACB30NX5HK3 BOLT, PROTRUDING HD Install (New) 15

Collar on rail side. 3 BACC30BH5 COLLAR, PRELOAD Install (New)

**FIGURE 2: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION (SHEET 6 OF 7)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 38 of 61 **BOEING SERVICE BULLETIN 777-25-0482 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Use pilots in Step 14 bracket. Drill holes 0.161 - 0.164 in. dia.in rail or Step 1 Support Structure Assy.Install with countersunk head on rail or Support Structure Assy side. 6 BACB30YP5K4 BOLT, 100 DEG HEX DR Install (New) 16

Collar on bracket side. 6 BACC30BL5 COLLAR, SHEAR Install (New) (a) Remaining open holes are acceptable. The parts shown in the table below are provided as extra parts for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  2 BACC30BH5 COLLAR, PRELOAD 1 BACR15BB4D6C RIVET 3 BACR15FT5D6C RIVET, UNIVERSAL HD 2 BACR15FT5D7C RIVET, UNIVERSAL HD 1 BACR15GF4D6 RIVET

**FIGURE 2: LEFT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION (SHEET 7 OF 7)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 39 of 61 **BOEING SERVICE BULLETIN 777-25-0482 This Figure applies only to: Group 1.** 

**FIGURE 3: LEFT SIDE TIE ROD AND ATTACH FITTING INSTALLATION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 40 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 3: LEFT SIDE TIE ROD AND ATTACH FITTING INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 41 of 61 **BOEING SERVICE BULLETIN 777-25-0482 More Data**  **Qty Identification**  **Name Task**  **Step** 1 777084-181 Tie Rod Install (Kept) 1 Near side. 1 BACB30NR4K15 BOLT Install (New) Near side. 1 BACW10BP4CD WASHER Install (New) Near side 1 BACB28AK04-024 BUSHING Install (New) Far side 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) (a) 1 422W2165-111 MISCELLANEOUS - MACHINE PART Install (New) 2
Install 2 near side, 2 far side. (b) , (c) 4 BACB30VF3K5 BOLT, 100 DEG HEAD Install (New)

1 777081-178 TIE ROD ASSY Install (New) 3 Near side. 1 BACB30NR4K15 BOLT Install (New) Near side. 1 BACW10BP4CD WASHER Install (New) Near side. 1 BACB28AK04-024 BUSHING Install (New) Far side. 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) Near side. 1 BACB30NR4K17 BOLT, HEX HEAD Install (New) 4 Near side. 1 BACW10BP4CD WASHER Install (New) Near side. 1 BACB28AK04-038 BUSHING Install (New) Far side. 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) (a) Maximum gap allowed between part and rail before fastener installation is .003 in. Install shim if required in accordance with 777-200 SRM 51-20-10 or 777-300 SRM 51-20-10. (b) For countersink information, refer to 777-200 SRM 51-40-08 or 777-300 SRM 51-40-08 as an accepted procedure. (c) If a required hole is used for a ground, relocate ground to nearest unused hole. Refer to SWPM 20-20- 10 as an accepted procedure.

**FIGURE 3: LEFT SIDE TIE ROD AND ATTACH FITTING INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 42 of 61 **BOEING SERVICE BULLETIN 777-25-0482 This Figure applies only to: Group 2.** 

**FIGURE 4: LEFT SIDE TIE ROD AND ATTACH FITTING INSTALLATION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 43 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 4: LEFT SIDE TIE ROD AND ATTACH FITTING INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 44 of 61 **BOEING SERVICE BULLETIN 777-25-0482 More Data**  **Qty Identification**  **Name Task**  **Step** 1 777084-181 Tie Rod Install (Kept) 1 Near side. 1 BACB30NR4K15 BOLT Install (New) Near side. 1 BACW10BP4CD WASHER Install (New) Near side 1 BACB28AK04-024 BUSHING Install (New) Far side 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) (a) 1 422W2165-108 MISCELLANEOUS - MACHINE PART Install (New) 2
Install 2 near side, 2 far side. (b), (c) 4 BACB30VF3K5 BOLT, 100 DEG HEAD Install (New)

1 777081-178 TIE ROD ASSY Install (New) 3 Near side. 1 BACB30NR4K15 BOLT Install (New) Near side. 1 BACW10BP4CD WASHER Install (New) Near side. 1 BACB28AK04-024 BUSHING Install (New) Far side. 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) Near side. 1 BACB30NR4K17 BOLT, HEX HEAD Install (New) 4 Near side. 1 BACW10BP4CD WASHER Install (New) Near side. 1 BACB28AK04-038 BUSHING Install (New) Far side. 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) (a) Maximum gap allowed between part and rail before fastener installation is .003 in. Install shim if required in accordance with 777-200 SRM 51-20-10 or 777-300 SRM 51-20-10. (b) For countersink information, refer to 777-200 SRM 51-40-08 or 777-300 SRM 51-40-08 as an accepted procedure. (c) If a required hole is used for a ground, relocate ground to nearest unused hole. Refer to SWPM 20-20- 10 as an accepted procedure.

**FIGURE 4: LEFT SIDE TIE ROD AND ATTACH FITTING INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 45 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 5: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE REMOVAL**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 46 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 5: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE REMOVAL**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 47 of 61 **BOEING SERVICE BULLETIN 777-25-0482 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Disconnect at lower end. Leave upper end attached. Rotate tie rod up and out ofwork area and secure it temporarily. 1 777084-181 Tie Rod Disconnect 1

1 BACB30NR4K14 Bolt Remove 2 NAS1149D0432J Washer Remove 1 BACB28Y4C024 Bushing Remove 1 BACN10YR4CD Nut Remove 13 BACR15FT5D*C Rivet Remove 2 2 BACR15GF4D* Rivet Remove 3 4 BACB30NX5HK3 Bolt Remove 4 4 BACC30BH5 Collar Remove Remove the following parts as an assembly: 1
- SUPPORT STRUC- TURE ASSY Remove 5

1 413W1221-106B Member Remove 1 413W1221-113B Member Remove 2 413W1221-33 Gusset Remove 2 413W1221-35 Angle Remove 1 413W1224-7 Fitting Assy Remove 1 413W1221-31 Gusset Remove 2 413W1221-55 Gusset Remove 2 413W1221-60 Angle Remove (a)

- - Structure Inspect 6 (a) Do a general visual inspection of the existing structure in the area of rework. Remove nicks, scratches,gouges and/or minor corrosion, and protect all exposed aluminum in and around the repair areas in accordance with 777-200 SRM 51-20-01 or 777-300 SRM 51-20-01 as applicable.

**FIGURE 5: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE REMOVAL (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 48 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 6: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION**  **(SHEET 1 OF 7)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 49 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 6: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION**  **(SHEET 2 OF 7)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 50 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 6: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION**  **(SHEET 3 OF 7)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 51 of 61 **BOEING SERVICE BULLETIN 777-25-0482 More Data**  **Qty Identification**  **Name Task**  **Step** Use existing ceiling panel as locatingtemplate (or fabricate similar rigid template). Make sure that ceilingpanel can be installed and that tie rods align with new Support StructureAssy before attaching gussets and angles. (b) 1 413W1210-106B SUPPORT STRUC-TURE ASSY - LOWERED CEILING, SECT 41 Install (New) 1

2 413W1221-246B GUSSET Install (New) 2 Use existing holes in rail. Drill new holes in gusset. 4 BACR15FT5D6C RIVET, UNIVERSAL HD Install (New)

Use pilot holes in Step 2 gusset. Drill new holes in Step 1 Support Structure Assy. 4 BACR15FT5D7C RIVET, UNIVERSAL HD Install (New) 3

1 413W1221-269B GUSSET Install (New) 4 Use existing holes in rail. Drill new holes in gusset. 3 BACR15FT5D6C RIVET, UNIVERSAL HD Install (New)

Use pilot holes in Step 4 gusset. Drill new holes in Step 1 Support Structure Assy. 2 BACR15FT5D6C RIVET, UNIVERSAL HD Install (New) 5

No longer required after upper gussets have been installed. 1
- Ceiling Panel or Tem- plate Remove 6

**FIGURE 6: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION (SHEET 4 OF 7)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 52 of 61 **BOEING SERVICE BULLETIN 777-25-0482 More Data**  **Qty Identification**  **Name Task**  **Step** 1 413W1221-270B GUSSET Install (New) 7 Use shim if required between new gussetand existing rail. Remove 0.003 thicklaminations as necessary. A gap of0.005 max is permitted between rail andgusset before fastener installation. 1 BACS40R009D024F SHIM, LAMINATED Install (New)

Use existing holes in rail. Drill new holes in gusset and shim.Install with countersunk head on ceiling panel side of rail. 2 BACR15GF4D6 RIVET Install (New)

Use pilot holes in Step 7 gusset. Drill new holes in Step 1 Support Structure Assy. Install with countersunk head on ceiling panel side of rail. 2 BACR15GF4D6 RIVET Install (New) 8

1 413W1221-271B ANGLE Install (New) 9 Use existing holes inrail. Drill holes in angle. 4 BACR15FT5D7C RIVET, UNIVERSAL HD Install (New)

Use pilot holes in Step 9 angle. Drillholes in Step 1 Support Structure Assy. 4 BACR15BB4D6C RIVET Install (New) 10

1 413W1221-272B CORNER BRACKET Install (New) 11 Use existing hole in rail. Drill new hole 0.161 - 0.164 in. dia. in bracket. Install with head on bracket side. (a) 1 BACB30NX5HK3 BOLT, PROTRUDING HD Install (New)

Collar on rail side. 1 BACC30BH5 COLLAR, PRELOAD Install (New)

**FIGURE 6: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION (SHEET 5 OF 7)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 53 of 61 **BOEING SERVICE BULLETIN 777-25-0482 More Data**  **Qty Identification**  **Name Task**  **Step** Use pilots in Step 11 bracket. Drill holes 0.161 - 0.164 in. dia. in rail. Install with head on bracket side. 3 BACB30NX5HK3 BOLT, PROTRUDING HD Install (New) 12

Collar on rail side. 3 BACC30BH5 COLLAR, PRELOAD Install (New) Use pilots in Step 11 bracket. Drill holes 0.161 - 0.164 in. dia.in rail or Step 1 Support Structure Assy.Install with countersunk head on rail or Support Structure Assy side. 6 BACB30YP5K4 BOLT, 100 DEG HEX DR Install (New) 13

Collar on bracket side. 6 BACC30BL5 COLLAR, SHEAR Install (New)

1 413W1221-273B CORNER BRACKET Install (New) 14 Use existing hole in rail. Drill new hole 0.161 - 0.164 in. dia. in bracket. Install with head on bracket side. (a) 1 BACB30NX5HK3 BOLT, PROTRUDING HD Install (New)

Collar on rail side. 1 BACC30BH5 COLLAR, PRELOAD Install (New) Use pilots in Step 14 bracket. Drill holes 0.161 - 0.164 in. dia. in rail. Install with head on bracket side. 3 BACB30NX5HK3 BOLT, PROTRUDING HD Install (New) 15

Collar on rail side. 3 BACC30BH5 COLLAR, PRELOAD Install (New)

**FIGURE 6: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION (SHEET 6 OF 7)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 54 of 61 **BOEING SERVICE BULLETIN 777-25-0482 More Data**  **Qty Identification**  **Name Task**  **Step** Use pilots in Step 14 bracket. Drill holes 0.161 - 0.164 in. dia.in rail or Step 1 Support Structure Assy.Install with countersunk head on rail or Support Structure Assy side. 6 BACB30YP5K4 BOLT, 100 DEG HEX DR Install (New) 16

Collar on bracket side. 6 BACC30BL5 COLLAR, SHEAR Install (New) (a) Remaining open holes are acceptable. (b) On some airplanes, the ceiling panel assembly might contain one insert in a location where the support structure member (existing or new) does not have a hole for a fastener. If such a condition is encountered, the fastener at this hole location may be omitted. Alternatively, removing the blocked insert and installing an operator-furnished insert SL2334-3A1, fastener BACS12GU3K5, and washer NAS1149D0332J, in the panel at the hole location adjacent to the blocked insert is also acceptable. Refer to 777 AMM 25-00-00, Potted Inserts Repair, and BAC5583 Method B, Wet Potting of Inserts, as accepted procedures. The parts shown in the table below are provided as extra parts for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  2 BACC30BH5 COLLAR, PRELOAD 1 BACR15BB4D6C RIVET 4 BACR15FT5D6C RIVET, UNIVERSAL HD 2 BACR15FT5D7C RIVET, UNIVERSAL HD 1 BACR15GF4D6 RIVET

**FIGURE 6: RIGHT SIDE LOWERED CEILING SUPPORT STRUCTURE INSTALLATION (SHEET 7 OF 7)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 55 of 61 **BOEING SERVICE BULLETIN 777-25-0482 This Figure applies only to: Group 1.** 

**FIGURE 7: RIGHT SIDE TIE ROD AND ATTACH FITTING INSTALLATION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 56 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 7: RIGHT SIDE TIE ROD AND ATTACH FITTING INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 57 of 61 **BOEING SERVICE BULLETIN 777-25-0482 More Data**  **Qty Identification**  **Name Task**  **Step** 1 777084-181 Tie Rod Install (Kept) 1 Near side. 1 BACB30NR4K15 BOLT Install (New) Near side. 1 BACW10BP4CD WASHER Install (New) Far side 1 BACB28AK04-024 BUSHING Install (New) Far side 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) (a) 1 422W2165-111 MISCELLANEOUS - MACHINE PART Install (New) 2
Install 2 near side, 2 far side. (b) , (c) 4 BACB30VF3K5 BOLT, 100 DEG HEAD Install (New)

1 777081-178 TIE ROD ASSY Install (New) 3 Near side. 1 BACB30NR4K15 BOLT Install (New) Near side. 1 BACW10BP4CD WASHER Install (New) Far side 1 BACB28AK04-024 BUSHING Install (New) Far side. 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) Near side. 1 BACB30NR4K17 BOLT, HEX HEAD Install (New) 4 Near side. 1 BACW10BP4CD WASHER Install (New) Near side. 1 BACB28AK04-038 BUSHING Install (New) Far side. 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) (a) Maximum gap allowed between part and rail before fastener installation is .003 in. Install shim if required in accordance with 777-200 SRM 51-20-10 or 777-300 SRM 51-20-10. (b) For countersink information, refer to 777-200 SRM 51-40-08 or 777-300 SRM 51-40-08 as an accepted procedure. (c) If a required hole is used for a ground, relocate ground to nearest unused hole. Refer to SWPM 20-20- 10 as an accepted procedure.

**FIGURE 7: RIGHT SIDE TIE ROD AND ATTACH FITTING INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 58 of 61 **BOEING SERVICE BULLETIN 777-25-0482 This Figure applies only to: Group 2.** 

**FIGURE 8: RIGHT SIDE TIE ROD AND ATTACH FITTING INSTALLATION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 59 of 61 **BOEING SERVICE BULLETIN 777-25-0482 FIGURE 8: RIGHT SIDE TIE ROD AND ATTACH FITTING INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 60 of 61 **BOEING SERVICE BULLETIN 777-25-0482 More Data**  **Qty Identification**  **Name Task**  **Step** 1 777084-181 Tie Rod Install (Kept) 1 Near side. 1 BACB30NR4K15 BOLT Install (New) Near side. 1 BACW10BP4CD WASHER Install (New) Far side 1 BACB28AK04-024 BUSHING Install (New) Far side 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) (a) 1 422W2165-108 MISCELLANEOUS - MACHINE PART Install (New) 2
Install 2 near side, 2 far side. (b) , (c) 4 BACB30VF3K5 BOLT, 100 DEG HEAD Install (New)

1 777081-178 TIE ROD ASSY Install (New) 3 Near side. 1 BACB30NR4K15 BOLT Install (New) Near side. 1 BACW10BP4CD WASHER Install (New) Far side 1 BACB28AK04-024 BUSHING Install (New) Far side. 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) Near side. 1 BACB30NR4K17 BOLT, HEX HEAD Install (New) 4 Near side. 1 BACW10BP4CD WASHER Install (New) Near side. 1 BACB28AK04-038 BUSHING Install (New) Far side. 1 BACW10BP4DP WASHER Install (New) Far side. 1 BACN10YR4CD NUT Install (New) (a) Maximum gap allowed between part and rail before fastener installation is .003 in. Install shim if required in accordance with 777-200 SRM 51-20-10 or 777-300 SRM 51-20-10. (b) For countersink information, refer to 777-200 SRM 51-40-08 or 777-300 SRM 51-40-08 as an accepted procedure. (c) If a required hole is used for a ground, relocate ground to nearest unused hole. Refer to SWPM 20-20- 10 as an accepted procedure.

**FIGURE 8: RIGHT SIDE TIE ROD AND ATTACH FITTING INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: February 24, 2011 777-25-0482 Revision 1 February 21, 2012 61 of 61 **BOEING SERVICE BULLETIN 777-25-0482**