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.

ECCN: 9E991

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Unpublished Work.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.

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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

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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.

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This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change Yes Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required Yes Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material No

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

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.

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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

Airplanes Total Task Hours Elapsed Hours

All 12.10 7.35

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

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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.

GROUP CONFIGURATION DESCRIPTION

1 - 767 airplanes with Pratt and Whitney engines, line numbers 1-471.

2 - 767 airplanes with Pratt and Whitney engines, line numbers 472-561.

3 - 767 airplanes with Pratt and Whitney engines, line numbers 562-1021.

Airplane Models:

767-200, 767-300

Variable Number Group

VA001 - VA020 1

VA701 - VA719 1

VA801 - VA810 1

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Variable Number Group

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 1

VF162 2

VK001 - VK011 1

VK021 - VK022 1

VK055 - VK056 2

VK161 1

VK162 - VK163 2

VK164 3

VK171 2

VL011 1

VL806 - VL807 3

VL931 - VL932 3

VN151 - VN158 1

VN163 - VN168 1

VN171 - VN173 1

VN174 3

VN211 - VN212 1

VN221 - VN224 1

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BOEING SERVICE BULLETIN 767-29A0115

ALERT ALERT
Variable Number Group

VN225 3

VN241 - VN243 1

VN251 - VN262 1

VN263 - VN264 2

VN265 - VN276 3

VN371 - VN372 1

VN376 1

VN381 - VN383 1

VN384 - VN387 2

VN388 3

VN491 - VN505 1

VN506 - VN513 2

VN531 - VN532 1

VN536 - VN537 1

VN541 - VN542 1

VN551 1

VN556 - VN557 1

VN561 - VN562 2

VN631 - VN633 1

VN671 - VN672 1

VN681 - VN687 1

VN688 - VN690 2

VN691 3

VN931 2

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 3

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BOEING SERVICE BULLETIN 767-29A0115

ALERT ALERT
Variable Number Group

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 3

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:

Company Service Bulletin Description

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

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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

Model Zone

767-200, 767-300 437

Group 3:

Affected Maintenance Zones

Model Zone

767-300 437

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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.

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 4.50 2.25

Figure 1 1 0.25 0.25

Figure 2 or 3 1 0.35 0.35

Figure 4 1 0.75 0.75

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BOEING SERVICE BULLETIN 767-29A0115

ALERT ALERT
Task Number of Persons Task Hours Elapsed Hours

Figure 5 1 0.75 0.75

Figure 6 1 0.50 0.50

Test 2 0.50 0.25

Close Access 2 4.50 2.25

TOTAL FOR EACH AIRPLANE 12.10 7.35

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

Airplane (Pounds)

All +0.4 +364.0

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.

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BOEING SERVICE BULLETIN 767-29A0115

ALERT ALERT
3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

Wire Bundle Installation - Aft Strut Fairing LH, NAC STA 232.99

Thru 383.4

288T3185

287T1110 Wire Provision Instl. - Aft Fairing, Engine Strut

287T1106 Wire Provision Instl. - Aft Bulkhead Engine Strut

271T5260 Module Instl. - Shutoff Valve, Supply, Aft Fairing Strut

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:

Publication Chapter-Section

767 Illustrated Parts Catalog 54-51

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.

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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 Bulletin (US Dollars)

ROLT as of the

original issue date

of this Service Bulletin (Calendar

Days)

Kit Number Name Date QTY

Top Kit - ACMP Wiring 17-Jun-2013 1 291 $349.00

Support Bracket Change

015T1880-1

13-Aug-2013 1

26-Nov-2013 100

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

Top Kit 4 5 6

015T1880-1 1 1 1

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ALL

KIT 015T1880-1

Notes

Existing Part

Name Number

Figure

New Part Number

4 5 6

Qty

287T1107-119 . 2 . FILLER 287T1107-119 (a)

WIRE SUPPORT ASSY - SAIL BOAT, (a)

STRUT

287T1107-131 . 2 .

287T1107- (a) (b)

117,287T1107-27

WIRE SUPPORT ASSY - SAIL BOAT,

STRUT.

287T1107-132 . 1 .

WIRE SUPPORT ASSY - SAIL BOAT, 287T1107-31 (a) (b)

STRUT

287T1107-134 . 1 .

BACB30LM4-12 . 4 . BOLT (c)

BACB30NX6K3X 2 . . BOLT, PROTRUDING HD (c)

BACB30NX6K3Y 2 . . BOLT, PROTRUDING HD (c)

BACC10GU108 . . 5 CLAMP, WIRE BUNDLE

BACC30M6 2 . . COLLAR

BACC30R6 2 . . COLLAR

BACN10JC3CD . 3 . NUT

BACN10JC4CD . 4 . NUT,SELF-LOCKING

BACS12HN3-7 . 3 . BOLT

BACS12HN3-8 . . 5 BOLT

BACW10EC3S . 3 . WASHER, SPRING

NAS1149D0332J . 3 . WASHER

NAS1149D0463J . 8 . WASHER

(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 longer

than 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.

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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.

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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.

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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.

Location Circuit Breaker Nomenclature

P11-2 Panel C1095 HYD L ENG PUMP DEPRESS

P11-4 Panel C1097 ENG HYD PUMP L SUPPLY

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Location Circuit Breaker Nomenclature

P11-5 Panel C1084 HYD ELEC PUMP L

P11-5 Panel C1101 HYD QTY

P32 Panel C903 RIGHT GEN

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.

Location Circuit Breaker Nomenclature

P11-2 Panel C1095 HYD L ENG PUMP DEPRESS

P11-4 Panel C1097 ENG HYD PUMP L SUPPLY

P11-5 Panel C1084 HYD ELEC PUMP L

P11-5 Panel C1101 HYD QTY

P32 Panel C903 RIGHT GEN

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.

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ALERT ALERT
17. Put the airplane back to a serviceable condition.

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ALERT ALERT
FIGURE 1: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP REMOVAL

(SHEET 1 OF 2)

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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.

Step Task Name Identification Qty More Data

1 Remove Fasteners - 3

Remove Clamps - 3

FIGURE 1: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP REMOVAL

(SHEET 2 OF 2)

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This Figure applies only to: Group 1-2.

FIGURE 2: LEFT ENGINE STRUT - WIRE BUNDLES W290, W390, AND W398 - INSPECTION

(SHEET 1 OF 2)

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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.

Step Task Name Identification Qty More Data

Do a detailed inspection for damage.

Damage includes broken or worn insulation or broken wires.

1 Inspect Wire Bundles W290, W390, W398 3

FIGURE 2: LEFT ENGINE STRUT - WIRE BUNDLES W290, W390, AND W398 - INSPECTION

(SHEET 2 OF 2)

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This Figure applies only to: Group 3.

FIGURE 3: LEFT ENGINE STRUT - WIRE BUNDLES W290, W406, W424, AND W440 - INSPECTION

(SHEET 1 OF 2)

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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.

Step Task Name Identification Qty More Data

Do a detailed inspection for damage.

Damage includes broken or worn insulation or broken wires.

W290, W406, W424, 4

W440

1 Inspect Wire Bundles

FIGURE 3: LEFT ENGINE STRUT - WIRE BUNDLES W290, W406, W424, AND W440 - INSPECTION

(SHEET 2 OF 2)

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FIGURE 4: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET REMOVAL

(SHEET 1 OF 2)

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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.

Step Task Name Identification Qty More Data

1 Remove Collar - 2

Remove Bolt - 2

Remove Wire Support Bracket 287T1107-31 1

2 Remove Nut - 2

Remove Washer - 4

Remove Bolt - 2

287T1107-117 1

(287T1107-27 optional)

Remove Bracket

Do not remove valve

mounting brackets.

3 Remove Nut - 2

Remove Washer - 4

Remove Bolt - 2

Remove Filler 287T1107-119 2 if installed.

4 Install (New) BOLT, PROTRUDING HD BACB30NX6K3X 2

Install (New) COLLAR BACC30M6 2

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

Use in step 4 if second oversize

bolts are necessary.

BOLT, PROTRUDING HD BACB30NX6K3Y 2

COLLAR BACC30R6 2 Use with BACB30NX6K3Y bolts.

FIGURE 4: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET REMOVAL

(SHEET 2 OF 2)

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FIGURE 5: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET INSTALLATION

(SHEET 1 OF 3)

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FIGURE 5: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET INSTALLATION

(SHEET 2 OF 3)

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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.

Step Task Name Identification Qty More Data

1 Install (New) FILLER 287T1107-119 2

WIRE SUPPORT ASSY - 287T1107-131 2

SAIL BOAT, STRUT

2 Install (New)

WIRE SUPPORT ASSY - 287T1107-132 1

SAIL BOAT, STRUT.

3 Install (New)

WIRE SUPPORT ASSY - 287T1107-134 1

SAIL BOAT, STRUT

4 Install (New)

5 Install (New) BOLT BACS12HN3-7 3

Install (New) WASHER NAS1149D0332J 3 under the bolt head

Install (New) WASHER, SPRING BACW10EC3S 3 under the nut

Install (New) NUT BACN10JC3CD 3

6 Install (New) BOLT BACB30LM4-12 4

Install (New) WASHER NAS1149D0463J 8

Install (New) NUT,SELF-LOCKING BACN10JC4CD 4

FIGURE 5: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET INSTALLATION

(SHEET 3 OF 3)

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FIGURE 6: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP INSTALLATION

(SHEET 1 OF 2)

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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.

Step Task Name Identification Qty More Data

1 Install (New) CLAMP, WIRE BUNDLE BACC10GU108 5

Install (New) BOLT BACS12HN3-8 5

FIGURE 6: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP INSTALLATION

(SHEET 2 OF 2)

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