### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Number: 767-29A0115**  Original Issue: May 22, 2013 ATA System: 2911 5451 **SUBJECT:** HYDRAULIC POWER - Main Hydraulic Systems - Wire Bundle Inspection and Wire Support Bracket Replacement Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). 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 © 2013 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. 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, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries 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.

Original Issue: May 22, 2013 767-29A0115 1 of 37 4.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 2 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION ........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 15 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 16 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 16 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 18 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 19 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 FIGURE 1: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP REMOVAL. . . . . . . . . . . . . . . . 25 FIGURE 2: LEFT ENGINE STRUT - WIRE BUNDLES W290, W390, AND W398 - INSPECTION [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 FIGURE 3: LEFT ENGINE STRUT - WIRE BUNDLES W290, W406, W424, AND W440 - INSPECTION [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 FIGURE 4: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET REMOVAL. . . . . . . . . . . . . 31 FIGURE 5: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET INSTALLATION . . . . . . . . . . 33 FIGURE 6: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP INSTALLATION . . . . . . . . . . . . . 36

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 3 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 4 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**

BLANK PAGE

### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Summary**  **Number: 767-29A0115** Original Issue: May 22, 2013 ATA System: 2911 5451 **SUBJECT:** HYDRAULIC POWER - Main Hydraulic Systems - Wire Bundle Inspection and Wire Support Bracket Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **CONCURRENT REQUIREMENTS** Refer to Paragraph 1.B., Concurrent Requirements. **BACKGROUND** This service bulletin provides instructions to inspect the Alternating Current Motor Pump (ACMP) power feeder wire bundle and adjacent wire bundles in the left engine strut for chafing damage and to replace the wire support brackets with improved brackets. Chafing of the ACMP power feeder wire bundle can cause electrical arcing, loss of power to the left ACMP, and/or damage to a hydraulic line, which could cause low hydraulic pressure or the complete loss of the left hydraulic system. If this service bulletin is not done, electrical arcing could result in a possible ignition source for fuel vapor and/or hydraulic fluid, which could result in an uncontained engine strut fire. Several operators have reported low hydraulic pressure or loss of electrical power to the left ACMP. These failures were caused by a damaged power feeder wire bundle in the outboard aft fairing area of the left engine strut. In most cases, the wire bundle had chafed against the fuse pin washer at the midspar fitting, and evidence of arcing was noted. One operator reported that the wire bundle had chafed against a hydraulic elbow near the fuse pin, which completely severed the wire bundle and created a deep hole in the elbow. Although the hole in the elbow was not deep enough to cause the loss of hydraulic fluid, escape and ignition of hydraulic fluid was possible if the chafing condition had continued. The new wire support brackets increase the separation between the wire bundles and the fuse pin, which will help prevent the reported chafing conditions. The right engine strut has a different wire bundle routing which is not subject to these chafing conditions. Boeing Service Bulletin (SB) 767-29A0098 is related to this service bulletin. SB 767-29A0098 installs the new wire support brackets on 767 airplanes with General Electric (GE) CF6-80A or CF6-80C2 engines. Boeing Service Related Problem (SRP) 767-SRP-29-0090 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 767 FTD 29-12001 is related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 5 of 37This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected No Spares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes Yes Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected Yes Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts Yes Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator No Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required
**ACTION (PRR B12901-107S)** Open access to the left engine strut aft fairing area. Remove the wire bundle clamps. Do a detailed inspection of the wire bundles for damage. Repair the wire bundles if necessary. Remove the Engine Driven Pump (EDP) supply shutoff valve. Remove the wire support brackets and install new brackets. Install and do a test of the EDP supply shutoff valve. Install new wire bundle clamps. Close access to the left engine strut aft fairing area. **EFFECTIVITY** 767-200/-300 airplanes with Pratt and Whitney engines. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. **COMPLIANCE** Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-16-12 is related to this service bulletin. Paragraph (b) of AD 2004-16-12 requires the incorporation of Boeing Service Bulletin 767-29-0057, which installs the brackets that are replaced by this service bulletin. 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 change given in this service bulletin be done within 48 months after the original issue date of this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 6 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT INDUSTRY SUPPORT INFORMATION**  Boeing warranty remedies are not available for the configuration changes, inspection, and/or repair procedures given in this service bulletin. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  7.35 12.10 All
**MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 7 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 8 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**

### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Number: 767-29A0115**  Original Issue: May 22, 2013 ATA System: 2911 5451 **SUBJECT:** HYDRAULIC POWER - Main Hydraulic Systems - Wire Bundle Inspection and Wire Support Bracket Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent production airplanes. Refer to PRR B12901-107S for data about this change.
**DESCRIPTION CONFIGURATION**  **GROUP** 767 airplanes with Pratt and Whitney engines, line numbers 1-471.

- 1 767 airplanes with Pratt and Whitney engines, line numbers 472-561.

- 2 767 airplanes with Pratt and Whitney engines, line numbers 562-1021.

- 3

Airplane Models: 767-200, 767-300 **Group Variable Number**  1 VA001 - VA020 1 VA701 - VA719 1 VA801 - VA810

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 9 of 37**Group Variable Number**  1 VB001 - VB002 1 VB201 - VB202 1 VB281 - VB284 1 VB301 - VB302 1 VB371 - VB373 1 VE001 - VE003 1 VE021 - VE023 1 VE041 - VE043 1 VE061 - VE069 1 VE083 - VE086 1 VE171 - VE172 1 VF061 - VF062 1 VF071 - VF072 1 VF091 - VF093 1 VF101 - VF102 1 VF161 2 VF162 1 VK001 - VK011 1 VK021 - VK022 2 VK055 - VK056 1 VK161 2 VK162 - VK163 3 VK164 2 VK171 1 VL011 3 VL806 - VL807 3 VL931 - VL932 1 VN151 - VN158 1 VN163 - VN168 1 VN171 - VN173 3 VN174 1 VN211 - VN212 1 VN221 - VN224

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 10 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT Group**  **Variable Number** 3 VN225 1 VN241 - VN243 1 VN251 - VN262 2 VN263 - VN264 3 VN265 - VN276 1 VN371 - VN372 1 VN376 1 VN381 - VN383 2 VN384 - VN387 3 VN388 1 VN491 - VN505 2 VN506 - VN513 1 VN531 - VN532 1 VN536 - VN537 1 VN541 - VN542 1 VN551 1 VN556 - VN557 2 VN561 - VN562 1 VN631 - VN633 1 VN671 - VN672 1 VN681 - VN687 2 VN688 - VN690 3 VN691 2 VN931 3 VN932 - VN936 3 VN966 - VN967 3 VN971 - VN972 3 VR421 - VR423 3 VR471 - VR472 3 VS061 3 VS066 - VS070 3 VS091 - VS104 3 VS206 - VS208

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 11 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT Group**  **Variable Number** 3 VS211 3 VS301 - VS303 3 VS306 - VS311 3 VS426 - VS428 3 VS496 - VS497 3 VS506 - VS507 3 VS821 - VS825 3 VS841 - VS844 3 VS881 - VS883 3 VS896 3 VS911 - VS912 3 VS916 3 VS981 - VS982 2. Spares Affected None. **B. Concurrent Requirements Group 1:**  The service bulletin listed below must be done before or at the same time as this service bulletin: **Group 1: Description**  **Service Bulletin Company**  Changes wire bundle routing and improves wire bundle support in the left and right struts. 767-29-0057, Original Issue, Revision 1, Revision 2, or Revision 3 Boeing
**Group 2-3:** None. **C. Reason** This service bulletin provides instructions to inspect the Alternating Current Motor Pump (ACMP) power feeder wire bundle and adjacent wire bundles in the left engine strut for chafing damage and to install improved wire support brackets. Chafing of the ACMP power feeder wire bundle can cause electrical arcing, loss of power to the left ACMP, and/or damage to a hydraulic line, which could cause low hydraulic pressure or the complete loss of the left hydraulic system. If this service bulletin is not done, electrical arcing could result in a possible ignition source for fuel vapor and/or hydraulic fluid, which could result in an uncontained engine strut fire.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 12 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**Several operators have reported low hydraulic pressure or loss of electrical power to the left ACMP. These failures were caused by a damaged power feeder wire bundle in the outboard aft fairing area of the left engine strut. In most cases, the wire bundle had chafed against the fuse pin washer at the midspar fitting, and evidence of arcing was noted. One operator reported that the wire bundle had chafed against a hydraulic elbow near the fuse pin, which completely severed the wire bundle and created a deep hole in the elbow. Although the hole in the elbow was not deep enough to cause the loss of hydraulic fluid, escape and ignition of hydraulic fluid was possible if the chafing condition had continued. The new wire support brackets increase the separation between the wire bundles and the fuse pin, which will help prevent the reported chafing conditions. The right engine strut has a different wire bundle routing which is not subject to these chafing conditions. Boeing Service Bulletin (SB) 767-29A0098 is related to this service bulletin. SB 767-29A0098 installs the new wire support brackets on 767 airplanes with General Electric (GE) CF6-80A or CF6-80C2 engines. Boeing Service Related Problem (SRP) 767-SRP-29-0090 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 767 FTD 29-12001 is related to this service bulletin. **D. Description** Open access to the left engine strut aft fairing area. Remove the wire bundle clamps. Do a detailed inspection of the wire bundles for damage. Repair the wire bundles if necessary. Remove the Engine Driven Pump (EDP) supply shutoff valve. Remove the wire support brackets and install new brackets. Install and do a test of the EDP supply shutoff valve. Install new wire bundle clamps. Close access to the left engine strut aft fairing area. The changes in this service bulletin will not change the Engine Indication and Crew Alerting System (EICAS). The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1-2:**
**Affected Maintenance Zones Zone**  **Model** 437 767-200, 767-300 **Group 3:**
**Affected Maintenance Zones Zone**  **Model** 437 767-300

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 13 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT E. Compliance**  Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-16-12 is related to this service bulletin. Paragraph (b) of AD 2004-16-12 requires the incorporation of Boeing Service Bulletin 767-29-0057, which installs the brackets that are replaced by this service bulletin. 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 change given in this service bulletin be done within 48 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. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (b) of AD 2004-16-12. All provisions of AD 2004-16-12 that are not specifically referenced in the above statement remain fully applicable and must be complied with. 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 inspection and 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. **Elapsed Hours Task Hours**  **Number of Persons Task**  2.25 4.50 2 Open Access 0.25 0.25 1 Figure 1 0.35 0.35 1 Figure 2 or 3 0.75 0.75 1 Figure 4

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 14 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.75 0.75 1 Figure 5 0.50 0.50 1 Figure 6 0.25 0.50 2 Test 2.25 4.50 2 Close Access 7.35 12.10 TOTAL FOR EACH AIRPLANE **Group 1:** This estimate does not include the task hour data given in the service bulletin(s) in Paragraph 1.B., Concurrent Requirements. **H. Weight and Balance Changes Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane**  +364.0 +0.4 All
**I. Electrical Load Data** Not changed. **J. References** 1. Existing Data: a. Engineering Change Memo PRR B12901-107S b. Boeing Service Bulletin 767-29-0057, 767-29A0098 c. Boeing Service Related Problem (SRP) 767-SRP-29-0090 d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2004-16-12 e. Service Bulletin Index D624T001 f. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-13, 20-10-19 g. 767 Aircraft Maintenance Manual (AMM) 06-43-00, 29-11-00, 29-11-06, 78-31-00 h. 767 Fleet Team Digest (FTD) 29-12001 i. 767-200 and 767-300 Structural Repair Manual (SRM) Chapter 51 j. 767 Wiring Diagram Manual (WDM) 91-01-21, 91-01-22 2. Data Supplied with this Service Bulletin: None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 15 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**3. Installation Drawings Used in the Preparation of this Service Bulletin:
**Title Drawing Number**  Wire Bundle Installation - Aft Strut Fairing LH, NAC STA 232.99 Thru 383.4 288T3185 Wire Provision Instl. - Aft Fairing, Engine Strut 287T1110 Wire Provision Instl. - Aft Bulkhead Engine Strut 287T1106 Module Instl. - Shutoff Valve, Supply, Aft Fairing Strut 271T5260 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  54-51 767 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. **L. Interchangeability and Intermixability of Parts** Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability information. **M. Software Accomplishment Summary** Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 16 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 **REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION** 
**Unit Price as of the original issue date** **of this Service Bul letin (US Dollars)**  **ROLT as of the original issue date** **of this Service Bul**

**letin (Calendar Days)**  **QTY Date**  **Name Kit Number** 

$349.00 291 1 17-Jun-2013 Top Kit - ACMP Wiring Support Bracket Change 015T1880-1 1 13-Aug-2013 100 26-Nov-2013 **B. Industry Support Information** Boeing warranty remedies are not available for the configuration changes, inspection, and/or repair procedures given in this service bulletin. **C. Parts Necessary for Each Airplane** 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. **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 6**  **5 4**  **Top Kit** 1 1 1 015T1880-1

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 17 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT ALL** 
**KIT 015T1880-1**

**Notes Existing Part**  **Number Name**  **Figure**

**New Part Number 6**  **5 4**  **Qty** (a) 287T1107-119 FILLER

. 2

. 287T1107-119 (a) WIRE SUPPORT ASSY - SAIL BOAT, STRUT . 2

. 287T1107-131 (a) (b) 287T1107- 117,287T1107-27 WIRE SUPPORT ASSY - SAIL BOAT, STRUT. . 1

. 287T1107-132 (a) (b) 287T1107-31 WIRE SUPPORT ASSY - SAIL BOAT, STRUT . 1

. 287T1107-134 (c) BOLT

. 4

. BACB30LM4-12 (c) BOLT, PROTRUDING HD

. . 2 BACB30NX6K3X (c) BOLT, PROTRUDING HD

. . 2 BACB30NX6K3Y CLAMP, WIRE BUNDLE 5

. . BACC10GU108 COLLAR

. . 2 BACC30M6 COLLAR

. . 2 BACC30R6 NUT

. 3

. BACN10JC3CD NUT,SELF-LOCKING

. 4

. BACN10JC4CD BOLT

. 3

. BACS12HN3-7 BOLT 5

. . BACS12HN3-8 WASHER, SPRING

. 3

. BACW10EC3S WASHER

. 3

. NAS1149D0332J WASHER

. 8

. NAS1149D0463J (a) This part is used in production. (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 longerthan indicated. Also, if any fastener part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. 2. Parts and Materials Supplied by the Operator None. 3. Parts Modified and Reidentified None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 18 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 19 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 20 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **CAUTION:** KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:** 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. 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. 6. The necessary conditions for selection of clamp type and size are included in SWPM 20-10-12. If any wire bundle support clamp 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 a clamp that fits correctly. 7. 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. 8. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 21 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**9. 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. 10. 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. 11. 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. 12. 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. 13. 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. 14. Shaded areas in Figures are to separate the non-critical and non-authoritative information from the critical and authoritative information. 15. Some steps in the Work Instructions are identified as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps identified as RC must be done to comply with the AD. Alternative procedures for steps not identified with RC can be used if the RC steps can still be done as specified, and the airplane can be put back in a serviceable condition. An Alternative Method of Compliance (AMOC) is not necessary for deviations to steps that are not identified as RC. **B. WORK INSTRUCTIONS** 1. Do the deactivation procedure for the thrust reverser. Refer to 767 AMM 78-31-00 as an accepted procedure. 2. Remove access panels 437BL and 437ELX. Refer to 767 AMM 06-43-00. 3. Remove pressure from the left hydraulic system and reservoir. Refer to 767 AMM 29-11-00 as an accepted procedure. 4. Open these circuit breakers and attach DO-NOT-CLOSE tags. Refer to 767 WDM 91-01-21 and 767 WDM 91-01-22.
**Nomenclature Circuit Breaker**  **Location** HYD L ENG PUMP DEPRESS C1095 P11-2 Panel ENG HYD PUMP L SUPPLY C1097 P11-4 Panel

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 22 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT Nomenclature**  **Circuit Breaker Location**  HYD ELEC PUMP L C1084 P11-5 Panel HYD QTY C1101 P11-5 Panel RIGHT GEN C903 P32 Panel 5. Remove the wire bundle clamps in accordance with FIGURE 1. 6. RC - Do a detailed inspection of the wire bundles in accordance with the figure below:

a. **Group 1-2:** Use FIGURE 2. b. **Group 3:** Use FIGURE 3. 7. RC - If any damaged wire bundle is found, repair the damaged wires. Refer to SWPM 20-10-13 as an accepted procedure. 8. To get access to the wire support brackets, remove the Engine Driven Pump (EDP) supply shutoff valve. Refer to 767 AMM 29-11-06 as an accepted procedure. 9. Remove the wire support brackets in accordance with FIGURE 4. 10. RC - Install new wire support brackets in accordance with FIGURE 5. 11. Install and do a test of the EDP supply shutoff valve. Refer to 767 AMM 29-11-06 as an accepted procedure. 12. RC - Install new wire bundle clamps in accordance with FIGURE 6. 13. Close these circuit breakers and remove the DO-NOT-CLOSE tags. Refer to 767 WDM 91-01-21 and 767 WDM 91-01-22.
**Nomenclature Circuit Breaker**  **Location** HYD L ENG PUMP DEPRESS C1095 P11-2 Panel ENG HYD PUMP L SUPPLY C1097 P11-4 Panel HYD ELEC PUMP L C1084 P11-5 Panel HYD QTY C1101 P11-5 Panel RIGHT GEN C903 P32 Panel 14. Pressurize the left hydraulic system. Refer to 767 AMM 29-11-00 as an accepted procedure. 15. Install access panels 437BL and 437ELX. Refer to 767 AMM 06-43-00. 16. Do the activation procedure for the thrust reverser. Refer to 767 AMM 78-31-00 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 23 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**17. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 24 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT FIGURE 1: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP REMOVAL**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 25 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  3
- Fasteners Remove 1 3
- Clamps Remove

**FIGURE 1: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP REMOVAL (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 26 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT This Figure applies only to: Group 1-2.** 

**FIGURE 2: LEFT ENGINE STRUT - WIRE BUNDLES W290, W390, AND W398 - INSPECTION (SHEET 1 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 27 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  Do a detailed inspection for damage.Damage includes broken or worn insulation or broken wires. 3 W290, W390, W398 Wire Bundles Inspect 1

**FIGURE 2: LEFT ENGINE STRUT - WIRE BUNDLES W290, W390, AND W398 - INSPECTION (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 28 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT This Figure applies only to: Group 3.** 

**FIGURE 3: LEFT ENGINE STRUT - WIRE BUNDLES W290, W406, W424, AND W440 - INSPECTION (SHEET 1 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 29 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  Do a detailed inspection for damage.Damage includes broken or worn insulation or broken wires. 4 W290, W406, W424, W440 Wire Bundles Inspect 1

**FIGURE 3: LEFT ENGINE STRUT - WIRE BUNDLES W290, W406, W424, AND W440 - INSPECTION (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 30 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT FIGURE 4: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET REMOVAL**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 31 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  2
- Collar Remove 1 2
- Bolt Remove 1 287T1107-31 Wire Support Bracket Remove 2
- Nut Remove 2 4
- Washer Remove 2
- Bolt Remove 1 287T1107-117 (287T1107-27 optional) Bracket Remove
Do not remove valve mounting brackets. 2
- Nut Remove 3

4
- Washer Remove 2
- Bolt Remove if installed. 2 287T1107-119 Filler Remove 2 BACB30NX6K3X BOLT, PROTRUDING HD Install (New) 4 2 BACC30M6 COLLAR Install (New) The parts shown in the table below are provided as extra parts for this figure.
**More Data Qty**  **Identification Name**  Use in step 4 if second oversize bolts are necessary. 2 BACB30NX6K3Y BOLT, PROTRUDING HD
Use with BACB30NX6K3Y bolts. 2 BACC30R6 COLLAR

**FIGURE 4: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET REMOVAL (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 32 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT FIGURE 5: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET INSTALLATION**  **(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 33 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT FIGURE 5: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET INSTALLATION**  **(SHEET 2 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 34 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  2 287T1107-119 FILLER Install (New) 1 2 287T1107-131 WIRE SUPPORT ASSY - SAIL BOAT, STRUT Install (New) 2

1 287T1107-132 WIRE SUPPORT ASSY - SAIL BOAT, STRUT. Install (New) 3

1 287T1107-134 WIRE SUPPORT ASSY - SAIL BOAT, STRUT Install (New) 4
3 BACS12HN3-7 BOLT Install (New) 5 under the bolt head 3 NAS1149D0332J WASHER Install (New) under the nut 3 BACW10EC3S WASHER, SPRING Install (New) 3 BACN10JC3CD NUT Install (New) 4 BACB30LM4-12 BOLT Install (New) 6 8 NAS1149D0463J WASHER Install (New) 4 BACN10JC4CD NUT,SELF-LOCKING Install (New)

**FIGURE 5: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET INSTALLATION (SHEET 3 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 35 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT FIGURE 6: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP INSTALLATION**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 36 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  5 BACC10GU108 CLAMP, WIRE BUNDLE Install (New) 1 5 BACS12HN3-8 BOLT Install (New)

**FIGURE 6: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP INSTALLATION (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 22, 2013 767-29A0115 37 of 37 **BOEING SERVICE BULLETIN 767-29A0115 ALERT**  **ALERT**