# Boeing Alert Service Bulletin 767-29A0115: No revision named

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- Document: [Boeing Alert Service Bulletin 767-29A0115](https://openairdocs.org/service-documents/boeing/767-29a0115.md)
- Title as filed: U.S. DOT/FAA - SB-767-29A0115-00
- Pages: 37
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## Text

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### Page 1

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.
9E991ECCN:
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Unpublished Work.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.
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767-29A0115
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4.0

### Page 2

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### Page 3

Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 2
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 2
D. Description .............................................. 1 3
E. Compliance .............................................. 1 4
F. Approval ............................................... 1 4
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 5
I. Electrical Load Data ......................................... 1 5
J. References .............................................. 1 5
1. Existing Data: ......................................... 1 5
2. Data Supplied with this Service Bulletin: ........................... 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 6
K. Publications Affected ........................................ 1 6
L. Interchangeability and Intermixability of Parts ........................... 1 6
M. Software Accomplishment Summary ................................ 1 6
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary for Each Airplane ................................. 1 7
1. Kits/Parts ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 1 8
3. Parts Modified and Reidentified ................................ 1 8
4. Parts Removed and Not Replaced .............................. 1 9
D. Parts Necessary to Change Spares ................................. 1 9
E. Special Tooling - Price and Availability ............................... 1 9
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 9
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 1
A. GENERAL INFORMATION ..................................... 2 1
B. WORK INSTRUCTIONS ....................................... 2 2
FIGURE 1: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP REMOVAL ................ 2 5
FIGURE 2: LEFT ENGINE STRUT - WIRE BUNDLES W290, W390, AND W398 - INSPECTION [Group
1-2] ............................................... 2 7
FIGURE 3: LEFT ENGINE STRUT - WIRE BUNDLES W290, W406, W424, AND W440 - INSPECTION
[Group 3] ............................................ 2 9
FIGURE 4: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET REMOVAL ............. 3 1
FIGURE 5: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET INSTALLATION .......... 3 3
FIGURE 6: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP INSTALLATION ............. 3 6
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### Page 5

Commercial 
Airplanes
767
Service Bulletin
ALERT
SummaryNumber: 767-29A0115Original 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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### Page 6

This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
NoOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial 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.
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### Page 7

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 HoursTotal Task HoursAirplanes
7.3512.10All
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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### Page 8 (OCR)

BOEING SERVICE BULLETIN 767-29A0115
ALERT  ALERT
NAC
STA
238.65
LEFT STRUT ONLY
INSPECT WIRE BUNDLES FOR DAMAGE.  REPAIR IF NECESSARY
REMOVE AND REPLACE
WIRE SUPPORT BRACKETS
AND CLAMPS
2198205
Original Issue: May 22, 2013
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Work - See page 1 for details.  8 of 37

### Page 9

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.
DESCRIPTIONCONFIGURATIONGROUP
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
GroupVariable Number
1VA001 - VA020
1VA701 - VA719
1VA801 - VA810
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### Page 10

GroupVariable Number
1VB001 - VB002
1VB201 - VB202
1VB281 - VB284
1VB301 - VB302
1VB371 - VB373
1VE001 - VE003
1VE021 - VE023
1VE041 - VE043
1VE061 - VE069
1VE083 - VE086
1VE171 - VE172
1VF061 - VF062
1VF071 - VF072
1VF091 - VF093
1VF101 - VF102
1VF161
2VF162
1VK001 - VK011
1VK021 - VK022
2VK055 - VK056
1VK161
2VK162 - VK163
3VK164
2VK171
1VL011
3VL806 - VL807
3VL931 - VL932
1VN151 - VN158
1VN163 - VN168
1VN171 - VN173
3VN174
1VN211 - VN212
1VN221 - VN224
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GroupVariable Number
3VN225
1VN241 - VN243
1VN251 - VN262
2VN263 - VN264
3VN265 - VN276
1VN371 - VN372
1VN376
1VN381 - VN383
2VN384 - VN387
3VN388
1VN491 - VN505
2VN506 - VN513
1VN531 - VN532
1VN536 - VN537
1VN541 - VN542
1VN551
1VN556 - VN557
2VN561 - VN562
1VN631 - VN633
1VN671 - VN672
1VN681 - VN687
2VN688 - VN690
3VN691
2VN931
3VN932 - VN936
3VN966 - VN967
3VN971 - VN972
3VR421 - VR423
3VR471 - VR472
3VS061
3VS066 - VS070
3VS091 - VS104
3VS206 - VS208
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### Page 12

GroupVariable Number
3VS211
3VS301 - VS303
3VS306 - VS311
3VS426 - VS428
3VS496 - VS497
3VS506 - VS507
3VS821 - VS825
3VS841 - VS844
3VS881 - VS883
3VS896
3VS911 - VS912
3VS916
3VS981 - 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:
DescriptionService BulletinCompany
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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### Page 13

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
ZoneModel
437767-200, 767-300
Group 3:
Affected Maintenance Zones
ZoneModel
437767-300
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### Page 14

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 HoursTask HoursNumber of PersonsTask
2.254.502Open Access
0.250.251Figure 1
0.350.351Figure 2 or 3
0.750.751Figure 4
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### Page 15

Elapsed HoursTask HoursNumber of PersonsTask
0.750.751Figure 5
0.500.501Figure 6
0.250.502Test
2.254.502Close Access
7.3512.10TOTAL 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+0.4All
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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### Page 16

3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Wire Bundle Installation - Aft Strut Fairing LH, NAC STA 232.99
Thru 383.4
288T3185
Wire Provision Instl. - Aft Fairing, Engine Strut287T1110
Wire Provision Instl. - Aft Bulkhead Engine Strut287T1106
Module Instl. - Shutoff Valve, Supply, Aft Fairing Strut271T5260
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-SectionPublication
54-51767 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.
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### Page 17

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)
QTYDateNameKit Number
$349.00291117-Jun-2013Top Kit - ACMP Wiring
Support Bracket Change
015T1880-1
113-Aug-2013
10026-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
654Top Kit
111015T1880-1
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### Page 18

ALL
KIT 015T1880-1
Notes
Existing Part
NumberName
Figure
New Part Number
654
Qty
(a)287T1107-119FILLER.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)287T1107-31WIRE SUPPORT ASSY - SAIL BOAT,
STRUT
.1.287T1107-134
(c)BOLT.4.BACB30LM4-12
(c)BOLT, PROTRUDING HD..2BACB30NX6K3X
(c)BOLT, PROTRUDING HD..2BACB30NX6K3Y
CLAMP, WIRE BUNDLE5..BACC10GU108
COLLAR..2BACC30M6
COLLAR..2BACC30R6
NUT.3.BACN10JC3CD
NUT,SELF-LOCKING.4.BACN10JC4CD
BOLT.3.BACS12HN3-7
BOLT5..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 longer
than indicated. Also, if any fastener part numbers listed are not available or have been superseded, sub-
stitute 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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### Page 19

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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### Page 20

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### Page 21

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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### Page 22

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.
NomenclatureCircuit BreakerLocation
HYD L ENG PUMP DEPRESSC1095P11-2 Panel
ENG HYD PUMP L SUPPLYC1097P11-4 Panel
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### Page 23

NomenclatureCircuit BreakerLocation
HYD ELEC PUMP LC1084P11-5 Panel
HYD QTYC1101P11-5 Panel
RIGHT GENC903P32 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.
NomenclatureCircuit BreakerLocation
HYD L ENG PUMP DEPRESSC1095P11-2 Panel
ENG HYD PUMP L SUPPLYC1097P11-4 Panel
HYD ELEC PUMP LC1084P11-5 Panel
HYD QTYC1101P11-5 Panel
RIGHT GENC903P32 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.
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### Page 24

17. Put the airplane back to a serviceable condition.
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### Page 25 (OCR)

BOEING SERVICE BULLETIN 767-29A0115
ALERT  ALERT
NAC
STA
238.65
LEFT STRUT ONLY
2199384
FIGURE 1: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP REMOVAL
(SHEET 1 OF 2)
Original Issue: May 22, 2013
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Work - See page 1 for details.  25 of 37

### Page 26

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 DataQtyIdentificationNameTaskStep
3-FastenersRemove1
3-ClampsRemove
FIGURE 1: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP REMOVAL
(SHEET 2 OF 2)
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 767-29A0115
ALERT  ALERT
This Figure applies only to: Group 1-2.
NAC
STA
238.65
LEFT STRUT ONLY
FIGURE 2: LEFT ENGINE STRUT - WIRE BUNDLES W290, W390, AND W398 - INSPECTION
(SHEET 1 OF 2)
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### Page 28

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 DataQtyIdentificationNameTaskStep
Do a detailed inspection for damage.
Damage includes broken or worn insu-
lation or broken wires.
3W290, W390, W398Wire BundlesInspect1
FIGURE 2: LEFT ENGINE STRUT - WIRE BUNDLES W290, W390, AND W398 - INSPECTION
(SHEET 2 OF 2)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN 767-29A0115
ALERT  ALERT
This Figure applies only to: Group 3.
NAC
STA
238.65
LEFT STRUT ONLY
2198280
FIGURE 3: LEFT ENGINE STRUT - WIRE BUNDLES W290, W406, W424, AND W440 - INSPECTION
(SHEET 1 OF 2)
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### Page 30

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 DataQtyIdentificationNameTaskStep
Do a detailed inspection for damage.
Damage includes broken or worn insu-
lation or broken wires.
4W290, W406, W424,
W440
Wire BundlesInspect1
FIGURE 3: LEFT ENGINE STRUT - WIRE BUNDLES W290, W406, W424, AND W440 - INSPECTION
(SHEET 2 OF 2)
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### Page 31 (OCR)

BOEING SERVICE BULLETIN 767-29A0115
ALERT  ALERT
NAC
STA
238.65
BULKHEAD
LEFT STRUT ONLY
WIRE suppORT BRACKET 1
VALVE MOUNTING BRACKET
2199392
FIGURE 4: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET REMOVAL
(SHEET 1 OF 2)
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### Page 32

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 DataQtyIdentificationNameTaskStep
2-CollarRemove1
2-BoltRemove
1287T1107-31Wire Support BracketRemove
2-NutRemove2
4-WasherRemove
2-BoltRemove
1287T1107-117
(287T1107-27 optional)
BracketRemove
Do not remove valve
mounting brackets.
2-NutRemove3
4-WasherRemove
2-BoltRemove
if installed.2287T1107-119FillerRemove
2BACB30NX6K3XBOLT, PROTRUDING HDInstall (New)4
2BACC30M6COLLARInstall (New)
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
Use in step 4 if second oversize
bolts are necessary.
2BACB30NX6K3YBOLT, PROTRUDING HD
Use with BACB30NX6K3Y bolts.2BACC30R6COLLAR
FIGURE 4: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET REMOVAL
(SHEET 2 OF 2)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN 767-29A0115
ALERT  ALERT
NAC
STA
238.65
- BI
LEFT STRUT ONLY
NAC
STA
238.65
2199490
FIGURE 5: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET INSTALLATION
(SHEET 1 OF 3)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 767-29A0115
ALERT  ALERT
2 LOCATIONS €  EXISTING BRACKET
3 LOCATIONS  BULKHEAD
3 LOCATIONS 5
2 LOCATIONS €
2 LOCATIONS
VALVE
MOUNTING
BRACKET
6) 2 LOCATIONS
BULKHEAD
EXISTING BRACKET
TYPICAL
A-A  (4 LOCATIONS)  2199495
FIGURE 5: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET INSTALLATION
(SHEET 2 OF 3)
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### Page 35

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 DataQtyIdentificationNameTaskStep
2287T1107-119FILLERInstall (New)1
2287T1107-131WIRE SUPPORT ASSY -
SAIL BOAT, STRUT
Install (New)2
1287T1107-132WIRE SUPPORT ASSY -
SAIL BOAT, STRUT.
Install (New)3
1287T1107-134WIRE SUPPORT ASSY -
SAIL BOAT, STRUT
Install (New)4
3BACS12HN3-7BOLTInstall (New)5
under the bolt head3NAS1149D0332JWASHERInstall (New)
under the nut3BACW10EC3SWASHER, SPRINGInstall (New)
3BACN10JC3CDNUTInstall (New)
4BACB30LM4-12BOLTInstall (New)6
8NAS1149D0463JWASHERInstall (New)
4BACN10JC4CDNUT,SELF-LOCKINGInstall (New)
FIGURE 5: LEFT ENGINE STRUT - WIRE SUPPORT BRACKET INSTALLATION
(SHEET 3 OF 3)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 767-29A0115
ALERT  ALERT
NAC
STA
238.65
LEFT STRUT ONLY
2199574
FIGURE 6: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP INSTALLATION
(SHEET 1 OF 2)
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### Page 37

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 DataQtyIdentificationNameTaskStep
5BACC10GU108CLAMP, WIRE BUNDLEInstall (New)1
5BACS12HN3-8BOLTInstall (New)
FIGURE 6: LEFT ENGINE STRUT - WIRE BUNDLE CLAMP INSTALLATION
(SHEET 2 OF 2)
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