### Commercial **Airplanes** 

# 747 Service Bulletin **Number: 747-29A2114** Original Issue: October 01, 2009 Revision 1: July 15, 2010 ATA System: 2911 **SUBJECT:** HYDRAULIC POWER - Main Hydraulic Supply System - Wire Bundle Inspection and Wire Routing Change 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 1 of 43 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 2 of 43 **BOEING SERVICE BULLETIN 747-29A2114**

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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 20 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 20 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 FIGURE 1: LEFT WING - WIRE BUNDLE INSPECTION. . . . . . . . . . . . . . . . . . . . . . . . . 26 FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK. . . . . . . . . . . . . . . . . . . . . . . . . 32 FIGURE 4: RIGHT WING - WIRE BUNDLE INSPECTION. . . . . . . . . . . . . . . . . . . . . . . . 35 FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . 38 FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK. . . . . . . . . . . . . . . . . . . . . . . . 41

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 3 of 43 **BOEING SERVICE BULLETIN 747-29A2114**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 4 of 43 **BOEING SERVICE BULLETIN 747-29A2114**

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### Commercial **Airplanes** 

# 747 Service Bulletin **Revision Transmittal Sheet Number: 747-29A2114**  Original Issue: October 01, 2009 Revision 1: July 15, 2010 ATA System: 2911 **SUBJECT:** HYDRAULIC POWER - Main Hydraulic Supply System - Wire Bundle Inspection and Wire Routing Change This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** No more work is necessary on airplanes changed as shown in the Original Issue of this service bulletin. Airplane RT043 was added to Group 1 of this service bulletin effectivity. **REASON FOR REVISION** As a part of a service bulletin validation program, this change was completed on RT436 by Service Bulletin 747-29A2114 Original Issue before the release of Revision 1 of this service bulletin. The change completed on airplane RT436 by Service Bulletin 747-29A2114 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane RT436 has the configuration of a Group 1 airplane. This Revision is sent to incorporate findings of the validation of the service bulletin. The following section of the service bulletin were changed: 1. In Summary, Background, Service Bulletin validation information has been added. 2. In Paragraph 1.A., Effectivity, airplane RT043 was added to Group 1. 3. In Paragraph 1.C., Reason, Service Bulletin validation information has been added. 4. In Paragraph 2.C., Parts Necessary For Each Airplane, Parts information was added. 5. In Figure 2, and Figure 5, Step 11, added note (a). 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** October 01, 2009 Original Issue:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 5 of 43July 15, 2010 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 6 of 43 **BOEING SERVICE BULLETIN 747-29A2114**

### Commercial **Airplanes** 

# 747 Service Bulletin **Summary Number: 747-29A2114**  Original Issue: October 01, 2009 Revision 1: July 15, 2010 ATA System: 2911 **SUBJECT:** HYDRAULIC POWER - Main Hydraulic Supply System - Wire Bundle Inspection and Wire Routing Change **CONCURRENT REQUIREMENTS** Refer to Paragraph 1.B., Concurrent Requirements. **BACKGROUND** This service bulletin is issued to do a General Visual Inspection of two wire bundles in the number two and number three engine pylons near the leading edge and to change the wire routing if necessary. If the wire bundles have an incorrect wire routing where they go across a fuel feed tube, damage from chaffing can occur to the wire bundle or the fuel feed tube. If damage to the wire bundle or fuel feed tube occurs, it could cause fuel leaks and arcing and could cause a fire in the number two or number three engine pylon. PRR 82874 was issued in 1991 to give a design change to these areas to give better separation between several wire bundles and the fuel tubes. As a part of this PRR, the routing of wire bundles for the Alternating Current (AC) motor-driven pump was also changed to give better clearance from the fuel feed tubes. Service bulletin 747-24A2168 was issued to install support brackets to change the clearance between the fuel tube and the power feeder cables in the number two and the number three engine pylons. In 2007, Boeing received a report of a PW4056 powered 747-400 airplane that arrived at a gate with fuel leak from the drain line of the number two engine pylon. An investigation found the AC motor-driven pump wire bundle touched the fuel feed tube which caused chaffing and the leak. This service bulletin gives operators instructions to do a General Visual Inspection of the wire routing near the wing leading edge and the number two and the number three engine pylons. Instructions are given to change the routing configuration for the wire bundles. Boeing Service Related Problem (SRP) 747-SRP-28-0121 is related to this service bulletin. As a part of a service bulletin validation program, this change was completed on airplane RT436 by Service Bulletin 747-29A2114 Original Issue before the release of Revision 1 of this service bulletin. The change completed on airplane RT436 by Service Bulletin 747-29A2114 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane RT436 has the configuration of a Group 1 airplane. **ACTION (PRR 85901-97RS)** Work Package 1 - Get access to the fuel feed tube and wire bundle in the number two pylon area. Do a General Visual Inspection for wire routing between the fuel feed tube and wire bundle. If routing is incorrect, do a General Visual Inspection of the wire bundle and the fuel feed tube, and move the wire bundle above the support bracket as given in Work Package 2. If wire bundle routing goes above the support bracket, no more work is necessary. Close access and put the airplane back to the serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 7 of 43Work Package 2 - Get access to the fuel feed tube and wire bundle in the number two pylon area. Move the wire bundle above the support bracket. Close access and put the airplane back to the serviceable condition. Work Package 3 - Get access to the fuel feed tube and wire bundle in the number three pylon area. Do a General Visual Inspection for for wire routing between the fuel feed tube and wire bundle. If routing is incorrect, do a General Visual Inspection of the wire bundle and the fuel feed tube, and move the wire bundle above the support bracket as given in Work Package 4. If wire bundle routing goes above the support bracket, no more work is necessary. Close access and put the airplane back to the serviceable condition. Work Package 4 - Get access to the fuel feed tube and wire bundle in the number three pylon area. Move the wire bundle above the support bracket. Close access and put the airplane back to the serviceable condition. **EFFECTIVITY** 747-400/ -400D Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. **COMPLIANCE** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the inspection and if necessary, the changes given in this service bulletin be done within 24 months after the original issue date of this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration given in this service bulletin. **MANPOWER** Refer to Paragraph 1.G., Manpower. **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: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 8 of 43 **BOEING SERVICE BULLETIN 747-29A2114**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 9 of 43 **BOEING SERVICE BULLETIN 747-29A2114**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 10 of 43 **BOEING SERVICE BULLETIN 747-29A2114**

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### Commercial **Airplanes** 

# 747 Service Bulletin **Number: 747-29A2114** Original Issue: October 01, 2009 Revision 1: July 15, 2010 ATA System: 2911 **SUBJECT:** HYDRAULIC POWER - Main Hydraulic Supply System - Wire Bundle Inspection and Wire Routing Change **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index Document D6-30300 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 85901-97RS and PRR 82874 for data about this change.
**DESCRIPTION CONFIGURATION**  **GROUP** Some 747-400/-400D airplanes with AC motor-driven pumps at the strut 2 and 3 location. - 1

Airplane Models: 747-400, 747-400D **Group Variable Number**  1 RT001 - RT007 1 RT021 - RT022 1 RT031 - RT033 1 RT041 - RT047 1 RT071 - RT072 1 RT101 - RT103 1 RT121 1 RT131 1 RT401 - RT410

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 11 of 43**Group Variable Number**  1 RT431 - RT438 1 RT471 - RT489 1 RT501 - RT512 1 RT531 - RT533 1 RT551 - RT564 1 RT591 1 RT631 - RT633 1 RT641 - RT654 1 RT671 - RT672 1 RT681 - RT682 1 RT691 - RT693 1 RT701 - RT703 1 RT711 - RT712 1 RT741 - RT742 1 RT751 - RT753 1 RT776 - RT777 1 RU801 - RU802 2. Spares Affected None. **B. Concurrent Requirements** The service bulletin listed below must be done before this service bulletin: **Description Service Bulletin**  **Company** This service bulletin is issued to inspect the clearance between the fuel tube and the power feeder cable in number 2 and 3 strut, and to install the power feeder support bracket to separate the cable from the fuel tube. 747-24A2168, Revision 1, Revision 2 or Revision 3. Boeing

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 12 of 43 **BOEING SERVICE BULLETIN 747-29A2114 C. Reason**  This service bulletin is issued to do a General Visual Inspection of two wire bundles in the number two and number three engine pylons near the leading edge and to change the wire routing if necessary. If the wire bundles have an incorrect wire routing where they go across a fuel feed tube, damage from chaffing can occur to the wire bundle or the fuel feed tube. If damage to the wire bundle or fuel feed tube occurs, it could cause fuel leaks and arcing and could cause a fire in the number two or number three engine pylon. PRR 82874 was issued in 1991 to give a design change to these areas to give better separation between several wire bundles and the fuel tubes. As a part of this PRR, the routing of wire bundles for the Alternating Current (AC) motor-driven pump was also changed to give better clearance from the fuel feed tubes. Service bulletin 747-24A2168 was issued to install support brackets to change the clearance between the fuel tube and the power feeder cables in the number two and the number three engine pylons. In 2007, Boeing received a report of a PW4056 powered 747-400 airplane that arrived at a gate with fuel leak from the drain line of the number two engine pylon. An investigation found the AC motor-driven pump wire bundle touched the fuel feed tube which caused chaffing and the leak. This service bulletin gives operators instructions to do a General Visual Inspection of the wire routing near the wing leading edge and the number two and the number three engine pylons. Instructions are given to change the routing configuration for the wire bundles. Boeing Service Related Problem (SRP) 747-SRP-28-0121 is related to this service bulletin. As a part of a service bulletin validation program, this change was completed on airplane RT436 by Service Bulletin 747-29A2114 Original Issue before the release of Revision 1 of this service bulletin. The change completed on airplane RT436 by Service Bulletin 747-29A2114 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane RT436 has the configuration of a Group 1 airplane. Revision 1 is sent to incorporate the findings of the validation. **D. Description** Work Package 1 - Get access to the fuel feed tube and wire bundle in the number two pylon area. Do a General Visual Inspection for wire routing between the fuel feed tube and wire bundle. If routing is incorrect, do a General Visual Inspection of the wire bundle and the fuel feed tube, and move the wire bundle above the support bracket as given in Work Package 2. If wire bundle routing goes above the support bracket, no more work is necessary. Close access and put the airplane back to the serviceable condition. Work Package 2 - Get access to the fuel feed tube and wire bundle in the number two pylon area. Move the wire bundle above the support bracket. Close access and put the airplane back to the serviceable condition. Work Package 3 - Get access to the fuel feed tube and wire bundle in the number three pylon area. Do a General Visual Inspection for for wire routing between the fuel feed tube and wire bundle. If routing is incorrect, do a General Visual Inspection of the wire bundle and the fuel feed tube, and move the wire bundle above the support bracket as given in Work Package 4. If wire bundle routing goes above the support bracket, no more work is necessary. Close access and put the airplane back to the serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 13 of 43 **BOEING SERVICE BULLETIN 747-29A2114**Work Package 4 - Get access to the fuel feed tube and wire bundle in the number three pylon area. Move the wire bundle above the support bracket. Close access and put the airplane back to the serviceable condition. Revision 1 - No more work is necessary on airplanes changed as shown in the Original Issue of this service bulletin. Airplane RT043 was added to Group 1 of this service bulletin effectivity. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 461, 462, 463, 464, 471, 472, 473, 474 747-400, 747-400D **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 inspection and if necessary, the changes given in this service bulletin be done within 24 months 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: • 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 14 of 43 **BOEING SERVICE BULLETIN 747-29A2114 Work Package 1 - Left Wing - Wire Bundle Inspection** **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task**
0.50 0.50 1 Open Access 0.25 0.25 1 Figure 1 0.50 0.50 1 Close Access 1.25 1.25 Total for Work Package 1 Work Package Number one can be done at the same time as Work Package three or four. **Work Package 2 - Left Wing - Wire Bundle Change Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 
0.75 0.75 1 Open Access 1.00 1.00 1 Figure 2 1.00 1.00 1 Figure 3 0.75 0.75 1 Close Access 3.50 3.50 Total for Work Package 2 Work Package Number two can be done at the same time as Work Package three or four. **Work Package 3 - Right Wing - Wire Bundle Inspection Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 
0.50 0.50 1 Open Access 0.25 0.25 1 Figure 4 0.50 0.50 1 Close Access 1.25 1.25 Total for Work Package 3 Work Package number three can be done at the same time as Work Package one or two. **Work Package 4 - Right Wing - Wire Bundle Change Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 
0.75 0.75 1 Open Access 1.00 1.00 1 Figure 5 1.00 1.00 1 Figure 6

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 15 of 43 **BOEING SERVICE BULLETIN 747-29A2114 Work Package 4 - Right Wing - Wire Bundle Change**  **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task**
0.75 0.75 1 Close Access 3.50 3.50 Total for Work Package 4 Work Package number four can be done at the same time as Work Package one or two. **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data a. Engineering Change Memo PRR 85901-97RS, PRR 82874 b. Service Related Problem (SRP) 747-SRP-28-0121 c. 747 Aircraft Maintenance Manual (AMM) Subject 747-400 AMM 06-09-09, 20-11-05, 24-22-00, 28-22-07, 29-11-19 d. Boeing Standard Wiring Practices Manual SWPM 20-10-11, 20-10-12, 20-10-13, 20-10-19, 20-10-20, 20-20-00, 20-60-06 e. Boeing Parts Standards Document D-590 f. 747-400 Structural Repair Manual (SRM), 51 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin
**Title Drawing Number**  WIRE BUNDLE INSTALLATION L.H. FRONT SPAR AND LEADING EDGE. 288U1271
WIRE BUNDLE INSTALLATION RH FRONT SPAR AND LEADING EDGE 288U1272

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 16 of 43 **BOEING SERVICE BULLETIN 747-29A2114**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: None 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated 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. **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: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 17 of 43 **BOEING SERVICE BULLETIN 747-29A2114**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 18 of 43 **BOEING SERVICE BULLETIN 747-29A2114**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.
**Unit Price thru March 06/10**  **ROLT (Weeks)**  **QTY Date**  **Name Kit Number**  $26.00 60 25 04/15/09 Top Kit - Fuel Feed Tubeand Wire Bundle Separation 015U1875-1

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Mail to: Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA **B. Industry Support Information** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **C. Parts Necessary For Each Airplane** 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. **NOTE:** One top kit is necessary for each airplane. **Figure Kit 6**  **5 3**  **2 Top Kit**  1 1 1 1 015U1875-1

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 19 of 43 **BOEING SERVICE BULLETIN 747-29A2114 ALL** 
**KIT 015U1875-1**

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

**New Part Number 6**  **5 3**  **2 QTY**  CLAMP, WIRE BUNDLE 1 4 1 4 BACC10GU104
SCREW 2 2 BACS12GU3K14 (BACS12GU3K16 optional) SCREW, CAP 2 2 BACS12GU3K16 SCREW 1 3 1 3 BACS12GU3K8 SEAL 3 3 BACS45B1 WASHER 1 3 1 3 NAS1149D0332J SPACERS FOR BOLTS 2 2 NAS43DD3-22FC
SPACER 2 2 NAS43DD3-32FC (NAS43DD3-22FC optional)

2. Parts and Materials Supplied by the Operator None. 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: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 20 of 43 **BOEING SERVICE BULLETIN 747-29A2114 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, but the order of removing electrical power, gaining access to the work area, inspection, repair of damaged wire bundle, repair or replace damaged fuel feed tube, and closing access to the work area should not 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. The work instructions are divided into work packages. Task Hours and Elapsed Hours for each package are given in Paragraph 1.G., Manpower. You can do each work package independently. 5. 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 – Torque limits to tighten nuts and bolts are in 747-400 Structural Repair Manual (SRM), Chapter 51 6. Use the approved fastener and process material substitutions in accordance with 747-400 Structural Repair Manual (SRM), Chapter 51. Alternate fasteners are listed in 747-400 Structural Repair Manual (SRM) Chapter 51 and Boeing Drawing 012W6100. 7. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 8. The necessary conditions for selection of a clamp and clamp size are included in SWPM 20-10-12. If the clamp size for the wire harness supports specified in this service bulletin does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select the correct clamp.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 21 of 43 **BOEING SERVICE BULLETIN 747-29A2114**9. 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. 10. 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. 11. Materials and supplies in the manuals given in Paragraph 1.J., References, can be necessary. Examine the specified maintenance manual procedures to make sure all necessary supplies are available. **B. WORK INSTRUCTIONS WORK PACKAGE 1 - Left Wing - Wire Bundle Inspection**  1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted procedure. 2. Remove door 511CT located in the upper inboard nacelle if necessary for access. Refer to 747-400 AMM 06-09-08 as an accepted procedure. 3. Gain access to fuel feed tube and power feeder cable in the number two pylon area. 4. Find if the wire bundle W4300 has correct or incorrect routing in accordance with FIGURE 1. a. Do a General Visual Inspection of the wire bundle. (1) If the wire bundle routing goes above the support bracket no more action is required. (2) If the wire bundle routing goes under the support bracket, do a General Visual Inspection for damage between the wire bundle and the fuel feed tube. (a) If damage is found, repair the wire bundle. Refer to SWPM 20-10-13 as an accepted procedure. (b) If damage is found, repair the fuel feed tube where wire bundles goes across the tube. Refer to 747-400 AMM 28-22-07, for fuel system tubing damage check as an accepted procedure.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 22 of 43 **BOEING SERVICE BULLETIN 747-29A2114**1) If the fuel feed tube has damage that is not permitted, repair or replace the tube. Refer to 747-400 AMM 28-22-07 as an accepted procedure. 2) If the fuel feed tube does not have damage more than the permitted limits, go to step three. (3) Move the wire bundle above the support bracket in accordance with Work Package 2. 5. Install access door 511CT located in the upper inboard nacelle if removed for access. Refer to 747-400 AMM 06-09-08 as an accepted procedure. 6. Put the airplane back to the serviceable condition. **WORK PACKAGE 2 - Left Wing - Wire Bundle Change** 1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted procedure. 2. Remove the door 511CT located in the upper inboard nacelle if necessary for access. Refer to 747-400 AMM 06-09-08 as an accepted procedure. 3. Gain access to fuel feed tube and power feeder cable in the number two pylon area. 4. Move the wire bundle to the specified location in accordance with FIGURE 2. 5. If the wire bundle must have more slack to let it to be moved to the new routing, refer to this list of steps: a. Remove door 464AL and 464AR in the aft fairing if necessary for access. Refer to 747-400 AMM 29-11-19 as an accepted procedure. b. Move the wire bundle to get more slack in accordance with FIGURE 3. c. Install door 464AL and 464AR in the aft fairing if removed for access. Refer to 747-400 AMM 29-11-19 as an accepted procedure. 6. Install access door 511CT if removed for access. Refer to 747-400 AMM 06-09-08 as an accepted procedure. 7. Put the airplane back to the serviceable condition. **WORK PACKAGE 3 - Right Wing - Wire Bundle Inspection** 1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted procedure. 2. Remove door 611CT located in the upper inboard nacelle if necessary for access. Refer to 747-400 AMM 06-09-08 as an accepted procedure. 3. Gain access to fuel feed tube and power feeder cable in the number three pylon area. 4. Find if the wire bundle W4302 has correct or incorrect routing in accordance with FIGURE 4.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 23 of 43 **BOEING SERVICE BULLETIN 747-29A2114**a. Do a General Visual Inspection of the wire bundle. (1) If the wire bundle routing goes above the support bracket no more action is required. (2) If the wire bundle routing goes under the support bracket, do a General Visual Inspection for damage between the wire bundle and the fuel feed tube. (a) If damage is found, repair the wire bundle. Refer to SWPM 20-10-13 as an accepted procedure. (b) If damage is found, repair the fuel feed tube where wire bundles goes across the tube. Refer to 747-400 AMM 28-22-07, for fuel system tubing damage check as an accepted procedure. 1) If the fuel feed tube has damage that is not permitted, repair or replace the tube. Refer to 747-400 AMM 28-22-07 as an accepted procedure. 2) If the fuel feed tube does not have damage more than the permitted limits, go to step three. (3) Move the wire bundle above the support bracket in accordance with Work Package 4. 5. Install access door 611CT located in the upper inboard nacelle if removed for access. Refer to 747-400 AMM 06-09-08 as an accepted procedure. 6. Put the airplane back to the serviceable condition. **WORK PACKAGE 4 - Right Wing - Wire Bundle Change** 1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted procedure. 2. Remove the door 611CT located in the upper inboard nacelle if necessary for access. Refer to 747-400 AMM 06-09-08 as an accepted procedure. 3. Gain access to fuel feed tube and power feeder cable in the number three pylon area. 4. Move the wire bundle to the specified location in accordance with FIGURE 5. 5. If the wire bundle must have more slack to let it to be moved to the new routing, refer to this list of steps:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 24 of 43 **BOEING SERVICE BULLETIN 747-29A2114**a. Remove door 474AL and 474AR in the aft fairing if necessary for access. Refer to 747-400 AMM 29-11-19 as an accepted procedure. b. Move the wire bundle to get more slack in accordance with FIGURE 6. c. Install door 474AL and 474AR in the aft fairing if removed for access. Refer to 747-400 AMM 29-11-19 as an accepted procedure. 6. Install access door 611CT if removed for access. Refer to 747-400 AMM 06-09-08 as an accepted procedure. 7. Put the airplane back to the serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1: July 15, 2010 25 of 43 **BOEING SERVICE BULLETIN 747-29A2114 FIGURE 1: LEFT WING - WIRE BUNDLE INSPECTION**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 26 of 43 **BOEING SERVICE BULLETIN 747-29A2114**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.

**FIGURE 1: LEFT WING - WIRE BUNDLE INSPECTION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 27 of 43 **BOEING SERVICE BULLETIN 747-29A2114 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (a) (b)

- W4300 WIRE BUNDLE Inspect 1 (a) Do a General Visual Inspection of the wire bundle. (b) Make sure the wire bundle routing goes above the bracket.

**FIGURE 1: LEFT WING - WIRE BUNDLE INSPECTION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 28 of 43 **BOEING SERVICE BULLETIN 747-29A2114**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.

**FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 29 of 43 **BOEING SERVICE BULLETIN 747-29A2114 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP**

- - SCREW Remove / Keep 1

- - WASHER Remove / Keep

- - CLAMP Remove / Keep

- - SCREW Remove / Keep 2

- - WASHER Remove / Keep

- - CLAMP Remove / Keep

- - SCREW Remove 3 Remove washer between the head of the screw and clamp. - - WASHER Remove

- - NUT Remove / Keep Keep washer between the nut and clamp. - - WASHER Remove / Keep

- - SPACER Remove 4

- - CLAMP Remove 5

- - WASHER Remove 1
- CLAMP Remove / Keep 6 1
- CLAMP Remove / Keep 7

- - BLOCK Remove / Keep 8 1
- CLAMP Remove / Keep 9 (a) 1 BACS12GU3K14(BACS12GU3K16 optional) SCREW Install (New) 10

1 NAS1149D0332J WASHER Install (New) (a) 1 NAS43DD3-32FC(NAS43DD3-22FC optional) SPACER Install (New) 11

Refer to SWPM 20-10-12 as an accepted procedure. 1 BACC10GU104 CLAMP, WIRE BUN- DLE Install (New) 12

Refer to SWPM 20-10-12 as an accepted procedure. 1
- CLAMP Install (Kept) 13

**FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 30 of 43 **BOEING SERVICE BULLETIN 747-29A2114 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Refer to SWPM 20-10-12 as an accepted procedure. 1
- CLAMP, WIRE BUN- DLE Install (Kept) 14

1
- BLOCK Install (Kept) 15 Refer to SWPM 20-10-12 as an accepted procedure. 1
- CLAMP Install (Kept) 16

1
- WASHER Install (Kept) 1
- NUT Install (Kept) Refer to SWPM 20-10-12 as an accepted procedure. - - CLAMP Install (Kept) 17

- - SCREW Install (Kept)

- - WASHER Install (Kept) Refer to SWPM 20-10-12 as an accepted procedure. - - CLAMP Install (Kept) 18

- - SCREW Install (Kept)

- - WASHER Install (Kept) (a) If the specified spacer and screw has insufficient length, use combination of spacers to get the necessary length, but not so much length that it interferes with structure or other components. Spacers and screws provided in extra parts table. The parts shown in the table below are given as extra parts for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  3 BACC10GU104 CLAMP, WIRE BUN- DLE 1 BACS12GU3K14 SCREW 3 BACS12GU3K8 SCREW 1 NAS43DD3-32FC SPACER 2 NAS1149D0332J WASHER 2 NAS43DD3-22FC SPACERS FOR BOLTS 2 BACS12GU3K16 SCREW, CAP

**FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 31 of 43 **BOEING SERVICE BULLETIN 747-29A2114 FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 32 of 43 **BOEING SERVICE BULLETIN 747-29A2114**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.

**FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 33 of 43 **BOEING SERVICE BULLETIN 747-29A2114 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP**

- - CLAMP Loosen 1 Refer to SWPM 20-10-20 as an accepted procedure for removal and installation of pressure seal. 1
- SEAL Remove / Keep 2

(a) 1 W4300 WIRE BUNDLE Move 3 Refer to SWPM 20-10-20 as an accepted procedure for removal and installation of pressure seal. 1
- SEAL Install (Kept) 4

Refer to SWPM 20-10-12 as an accepted procedure. 1 BACC10GU104 CLAMP, WIRE BUN- DLE Tighten 5

(a) Make sure to maintain drip loop at connector. Refer to SWPM 20-10-11 as an accepted procedure. The parts shown in the table below are given as extra parts for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  3 BACS45B1 SEAL 1 BACC10GU104 CLAMP, WIRE BUN- DLE 1 NAS1149D0332J WASHER 1 BACS12GU3K8 SCREW

**FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 34 of 43 **BOEING SERVICE BULLETIN 747-29A2114 FIGURE 4: RIGHT WING - WIRE BUNDLE INSPECTION**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 35 of 43 **BOEING SERVICE BULLETIN 747-29A2114 FIGURE 4: RIGHT WING - WIRE BUNDLE INSPECTION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 36 of 43 **BOEING SERVICE BULLETIN 747-29A2114 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (a) (b)

- W4302 WIRE BUNDLE Inspect 1 (a) Do a General Visual Inspection of the wire bundle. (b) Make sure the wire bundle routing goes above the bracket.

**FIGURE 4: RIGHT WING - WIRE BUNDLE INSPECTION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 37 of 43 **BOEING SERVICE BULLETIN 747-29A2114**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.

**FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 38 of 43 **BOEING SERVICE BULLETIN 747-29A2114 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP**

- - SCREW Remove / Keep 1

- - WASHER Remove / Keep

- - CLAMP Remove / Keep

- - SCREW Remove / Keep 2

- - WASHER Remove / Keep

- - CLAMP Remove / Keep

- - SCREW Remove 3 Remove washer between the head of the screw and clamp. - - WASHER Remove

- - NUT Remove / Keep Keep washer between the nut and clamp. - - WASHER Remove / Keep

- - SPACER Remove 4

- - CLAMP Remove 5

- - WASHER Remove 1
- CLAMP Remove / Keep 6 1
- CLAMP Remove / Keep 7

- - BLOCK Remove / Keep 8 1
- CLAMP Remove / Keep 9 (a) 1 BACS12GU3K14(BACS12GU3K16 optional) SCREW Install (New) 10

1 NAS1149D0332J WASHER Install (New) (a) 1 NAS43DD3-32FC(NAS43DD3-22FC optional) SPACER Install (New) 11

Refer to SWPM 20-10-12 as an accepted procedure. 1 BACC10GU104 CLAMP, WIRE BUN- DLE Install (New) 12

Refer to SWPM 20-10-12 as an accepted procedure. 1
- CLAMP Install (Kept) 13

**FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 39 of 43 **BOEING SERVICE BULLETIN 747-29A2114 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Refer to SWPM 20-10-12 as an accepted procedure. 1
- CLAMP Install (Kept) 14

1
- BLOCK Install (Kept) 15 Refer to SWPM 20-10-12 as an accepted procedure. 1
- CLAMP Install (Kept) 16

1
- WASHER Install (Kept) 1
- NUT Install (Kept) Refer to SWPM 20-10-12 as an accepted procedure. - - CLAMP Install (Kept) 17

- - SCREW Install (Kept)

- - WASHER Install (Kept) Refer to SWPM 20-10-12 as an accepted procedure. - - CLAMP Install (Kept) 18

- - SCREW Install (Kept)

- - WASHER Install (Kept) (a) If the specified spacer and screw has insufficient length, use combination of spacers to get the necessary length, but not so much length that it interferes with structure or other components. Spacers and screws provided in extra parts table. The parts shown in the table below are given as extra parts for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  3 BACC10GU104 CLAMP, WIRE BUN- DLE 1 BACS12GU3K14 SCREW 3 BACS12GU3K8 SCREW 1 NAS43DD3-32FC SPACER 2 NAS1149D0332J WASHER 2 NAS43DD3-22FC SPACERS FOR BOLTS 2 BACS12GU3K16 SCREW, CAP

**FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 40 of 43 **BOEING SERVICE BULLETIN 747-29A2114 FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 41 of 43 **BOEING SERVICE BULLETIN 747-29A2114**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.

**FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 42 of 43 **BOEING SERVICE BULLETIN 747-29A2114 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP**

- - CLAMP Loosen 1 Refer to SWPM 20-10-20 as an accepted procedure for removal and installation of pressure seal. 1
- SEAL Remove / Keep 2

(a) 1 W4302 WIRE BUNDLE Move 3 Refer to SWPM 20-10-20 as an accepted procedure for removal and installation of pressure seal. 1
- SEAL Install (Kept) 4

Refer to SWPM 20-10-12 as an accepted procedure. - BACC10GU104 CLAMP, WIRE BUN- DLE Tighten 5

(a) Make sure to maintain drip loop at connector. Refer to SWPM 20-10-11 as an accepted procedure. The parts shown in the table below are given as extra parts for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  3 BACS45B1 SEAL 1 BACC10GU104 CLAMP, WIRE BUN- DLE 1 NAS1149D0332J WASHER 1 BACS12GU3K8 SCREW

**FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 01, 2009 747-29A2114 Revision 1 July 15, 2010 43 of 43 **BOEING SERVICE BULLETIN 747-29A2114**