# Boeing Alert Service Bulletin 747-29A2114: Revision 1

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- Document: [Boeing Alert Service Bulletin 747-29A2114](https://openairdocs.org/service-documents/boeing/747-29a2114.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin
SB-747-29A2114-01
- Pages: 43
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## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
Number: 747-29A2114
Original Issue: October 01, 2009
Revision 1: July 15, 2010
ATA System: 2911
SUBJECT: HYDRAULIC POWER - Main Hydraulic Supply System - Wire Bundle Inspection and
Wire Routing Change
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2009 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 2
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 3
D. Description .............................................. 1 3
E. Compliance .............................................. 1 4
F. Approval ............................................... 1 4
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 6
I. Electrical Load Data ......................................... 1 6
J. References .............................................. 1 6
1. Existing Data .......................................... 1 6
2. Data supplied with this Service Bulletin ............................ 1 6
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 6
K. Publications Affected ........................................ 1 7
L. Interchangeability and Intermixability of Parts ........................... 1 7
2. MATERIAL INFORMATION ........................................ 1 9
A. Material - Price and Availability ................................... 1 9
B. Industry Support Information .................................... 1 9
C. Parts Necessary For Each Airplane ................................. 1 9
1. Kits/Parts ............................................ 1 9
2. Parts and Materials Supplied by the Operator ........................ 2 0
3. Parts Modified and Reidentified ................................ 2 0
4. Parts Removed and Not Replaced .............................. 2 0
D. Parts Necessary to Change Spares ................................. 2 0
E. Special Tooling - Price and Availability ............................... 2 0
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 1
A. GENERAL INFORMATION ..................................... 2 1
B. WORK INSTRUCTIONS ....................................... 2 2
FIGURE 1: LEFT WING - WIRE BUNDLE INSPECTION ......................... 2 6
FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE ........................... 2 9
FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK ......................... 3 2
FIGURE 4: RIGHT WING - WIRE BUNDLE INSPECTION ........................ 3 5
FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE .......................... 3 8
FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK ........................ 4 1
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Commercial 
Airplanes
747
Service Bulletin
Revision Transmittal SheetNumber: 747-29A2114Original Issue: October 01, 2009
Revision 1: July 15, 2010
ATA System: 2911
SUBJECT: HYDRAULIC POWER - Main Hydraulic Supply System - Wire Bundle Inspection and
Wire Routing Change
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on airplanes changed as shown in the Original Issue of this service bulletin.
Airplane RT043 was added to Group 1 of this service bulletin effectivity.
REASON FOR REVISION
As a part of a service bulletin validation program, this change was completed on RT436 by Service Bulletin
747-29A2114 Original Issue before the release of Revision 1 of this service bulletin. The change completed on
airplane RT436 by Service Bulletin 747-29A2114 Original Issue is equivalent to the release of Revision 1 of this
service bulletin. Airplane RT436 has the configuration of a Group 1 airplane.
This Revision is sent to incorporate findings of the validation of the service bulletin.
The following section of the service bulletin were changed:
1. In Summary, Background, Service Bulletin validation information has been added.
2. In Paragraph 1.A., Effectivity, airplane RT043 was added to Group 1.
3. In Paragraph 1.C., Reason, Service Bulletin validation information has been added.
4. In Paragraph 2.C., Parts Necessary For Each Airplane, Parts information was added.
5. In Figure 2, and Figure 5, Step 11, added note (a).
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
October 01, 2009Original Issue:
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July 15, 2010Revision 1:
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Commercial 
Airplanes
747
Service Bulletin
SummaryNumber: 747-29A2114Original Issue: October 01, 2009
Revision 1: July 15, 2010
ATA System: 2911
SUBJECT: HYDRAULIC POWER - Main Hydraulic Supply System - Wire Bundle Inspection and
Wire Routing Change
CONCURRENT REQUIREMENTS
Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND
This service bulletin is issued to do a General Visual Inspection of two wire bundles in the number two and
number three engine pylons near the leading edge and to change the wire routing if necessary. If the wire
bundles have an incorrect wire routing where they go across a fuel feed tube, damage from chaffing can occur
to the wire bundle or the fuel feed tube. If damage to the wire bundle or fuel feed tube occurs, it could cause
fuel leaks and arcing and could cause a fire in the number two or number three engine pylon.
PRR 82874 was issued in 1991 to give a design change to these areas to give better separation between several
wire bundles and the fuel tubes. As a part of this PRR, the routing of wire bundles for the Alternating Current
(AC) motor-driven pump was also changed to give better clearance from the fuel feed tubes. Service bulletin
747-24A2168 was issued to install support brackets to change the clearance between the fuel tube and the
power feeder cables in the number two and the number three engine pylons. In 2007, Boeing received a report
of a PW4056 powered 747-400 airplane that arrived at a gate with fuel leak from the drain line of the number
two engine pylon. An investigation found the AC motor-driven pump wire bundle touched the fuel feed tube
which caused chaffing and the leak.
This service bulletin gives operators instructions to do a General Visual Inspection of the wire routing near the
wing leading edge and the number two and the number three engine pylons. Instructions are given to change
the routing configuration for the wire bundles.
Boeing Service Related Problem (SRP) 747-SRP-28-0121 is related to this service bulletin.
As a part of a service bulletin validation program, this change was completed on airplane RT436 by Service
Bulletin 747-29A2114 Original Issue before the release of Revision 1 of this service bulletin. The change
completed on airplane RT436 by Service Bulletin 747-29A2114 Original Issue is equivalent to the release of
Revision 1 of this service bulletin. Airplane RT436 has the configuration of a Group 1 airplane.
ACTION (PRR 85901-97RS)
Work Package 1 - Get access to the fuel feed tube and wire bundle in the number two pylon area. Do a General
Visual Inspection for wire routing between the fuel feed tube and wire bundle. If routing is incorrect, do a General
Visual Inspection of the wire bundle and the fuel feed tube, and move the wire bundle above the support bracket
as given in Work Package 2. If wire bundle routing goes above the support bracket, no more work is necessary.
Close access and put the airplane back to the serviceable condition.
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Work Package 2 - Get access to the fuel feed tube and wire bundle in the number two pylon area. Move the
wire bundle above the support bracket. Close access and put the airplane back to the serviceable condition.
Work Package 3 - Get access to the fuel feed tube and wire bundle in the number three pylon area. Do a General
Visual Inspection for for wire routing between the fuel feed tube and wire bundle. If routing is incorrect, do a
General Visual Inspection of the wire bundle and the fuel feed tube, and move the wire bundle above the support
bracket as given in Work Package 4. If wire bundle routing goes above the support bracket, no more work is
necessary. Close access and put the airplane back to the serviceable condition.
Work Package 4 - Get access to the fuel feed tube and wire bundle in the number three pylon area. Move the
wire bundle above the support bracket. Close access and put the airplane back to the serviceable condition.
EFFECTIVITY
747-400/ -400D Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Boeing recommends that the inspection and if necessary, the changes given in this service bulletin be done
within 24 months after the original issue date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 747-29A2114
LEFT WING SHOWN
RIGHT WING OPPOSITE
- GET ACCESS TO THE LEFT FUEL
FEED TUBE AND WIRE BUNDLE.
DO A GENERAL VISUAL INSPECTION
FUEL FEED  FOR CORRECT WIRE ROUTING.
TUBE
IF NECESSASARY, CHANGE THE WIRE
ROUTING CONFIGURATION.
1814693
Original Issue: October 01, 2009
Revision 1: July 15, 2010  747-29A2114
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Commercial 
Airplanes
747
Service Bulletin
Number: 747-29A2114
Original Issue: October 01, 2009
Revision 1: July 15, 2010
ATA System: 2911
SUBJECT: HYDRAULIC POWER - Main Hydraulic Supply System - Wire Bundle Inspection and
Wire Routing Change
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D6-30300 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR 85901-97RS and PRR 82874 for data about this change.
DESCRIPTIONCONFIGURATIONGROUP
Some 747-400/-400D airplanes with AC motor-driven pumps at the
strut 2 and 3 location.
-1
Airplane Models:
747-400, 747-400D
GroupVariable Number
1RT001 - RT007
1RT021 - RT022
1RT031 - RT033
1RT041 - RT047
1RT071 - RT072
1RT101 - RT103
1RT121
1RT131
1RT401 - RT410
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GroupVariable Number
1RT431 - RT438
1RT471 - RT489
1RT501 - RT512
1RT531 - RT533
1RT551 - RT564
1RT591
1RT631 - RT633
1RT641 - RT654
1RT671 - RT672
1RT681 - RT682
1RT691 - RT693
1RT701 - RT703
1RT711 - RT712
1RT741 - RT742
1RT751 - RT753
1RT776 - RT777
1RU801 - RU802
2. Spares Affected
None.
B. Concurrent Requirements
The service bulletin listed below must be done before this service bulletin:
DescriptionService BulletinCompany
This service bulletin is issued to inspect the
clearance between the fuel tube and the
power feeder cable in number 2 and 3 strut,
and to install the power feeder support
bracket to separate the cable from the fuel
tube.
747-24A2168, Revision 1, Revision 2 or
Revision 3.
Boeing
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C. Reason
This service bulletin is issued to do a General Visual Inspection of two wire bundles in the number two
and number three engine pylons near the leading edge and to change the wire routing if necessary. If
the wire bundles have an incorrect wire routing where they go across a fuel feed tube, damage from
chaffing can occur to the wire bundle or the fuel feed tube. If damage to the wire bundle or fuel feed
tube occurs, it could cause fuel leaks and arcing and could cause a fire in the number two or number
three engine pylon.
PRR 82874 was issued in 1991 to give a design change to these areas to give better separation between
several wire bundles and the fuel tubes. As a part of this PRR, the routing of wire bundles for the
Alternating Current (AC) motor-driven pump was also changed to give better clearance from the fuel
feed tubes. Service bulletin 747-24A2168 was issued to install support brackets to change the clearance
between the fuel tube and the power feeder cables in the number two and the number three engine
pylons. In 2007, Boeing received a report of a PW4056 powered 747-400 airplane that arrived at a
gate with fuel leak from the drain line of the number two engine pylon. An investigation found the AC
motor-driven pump wire bundle touched the fuel feed tube which caused chaffing and the leak.
This service bulletin gives operators instructions to do a General Visual Inspection of the wire routing
near the wing leading edge and the number two and the number three engine pylons. Instructions are
given to change the routing configuration for the wire bundles.
Boeing Service Related Problem (SRP) 747-SRP-28-0121 is related to this service bulletin.
As a part of a service bulletin validation program, this change was completed on airplane RT436 by
Service Bulletin 747-29A2114 Original Issue before the release of Revision 1 of this service bulletin.
The change completed on airplane RT436 by Service Bulletin 747-29A2114 Original Issue is equivalent
to the release of Revision 1 of this service bulletin. Airplane RT436 has the configuration of a Group 1
airplane.
Revision 1 is sent to incorporate the findings of the validation.
D. Description
Work Package 1 - Get access to the fuel feed tube and wire bundle in the number two pylon area. Do
a General Visual Inspection for wire routing between the fuel feed tube and wire bundle. If routing is
incorrect, do a General Visual Inspection of the wire bundle and the fuel feed tube, and move the wire
bundle above the support bracket as given in Work Package 2. If wire bundle routing goes above the
support bracket, no more work is necessary. Close access and put the airplane back to the serviceable
condition.
Work Package 2 - Get access to the fuel feed tube and wire bundle in the number two pylon area.
Move the wire bundle above the support bracket. Close access and put the airplane back to the
serviceable condition.
Work Package 3 - Get access to the fuel feed tube and wire bundle in the number three pylon area.
Do a General Visual Inspection for for wire routing between the fuel feed tube and wire bundle. If routing
is incorrect, do a General Visual Inspection of the wire bundle and the fuel feed tube, and move the
wire bundle above the support bracket as given in Work Package 4. If wire bundle routing goes above
the support bracket, no more work is necessary. Close access and put the airplane back to the
serviceable condition.
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Work Package 4 - Get access to the fuel feed tube and wire bundle in the number three pylon area.
Move the wire bundle above the support bracket. Close access and put the airplane back to the
serviceable condition.
Revision 1 - No more work is necessary on airplanes changed as shown in the Original Issue of this
service bulletin.
Airplane RT043 was added to Group 1 of this service bulletin effectivity.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
461, 462, 463, 464, 471, 472, 473, 474747-400, 747-400D
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Boeing recommends that the inspection and if necessary, the changes given in this service bulletin be
done within 24 months after the original issue date of this service bulletin.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
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Work Package 1 - Left Wing - Wire Bundle Inspection
Elapsed HoursTask-HoursNumber of Per-
sons
Task
0.500.501Open Access
0.250.251Figure 1
0.500.501Close Access
1.251.25Total for Work Package 1
Work Package Number one can be done at the same time as Work Package three or four.
Work Package 2 - Left Wing - Wire Bundle Change
Elapsed HoursTask-HoursNumber of Per-
sons
Task
0.750.751Open Access
1.001.001Figure 2
1.001.001Figure 3
0.750.751Close Access
3.503.50Total for Work Package 2
Work Package Number two can be done at the same time as Work Package three or four.
Work Package 3 - Right Wing - Wire Bundle Inspection
Elapsed HoursTask-HoursNumber of Per-
sons
Task
0.500.501Open Access
0.250.251Figure 4
0.500.501Close Access
1.251.25Total for Work Package 3
Work Package number three can be done at the same time as Work Package one or two.
Work Package 4 - Right Wing - Wire Bundle Change
Elapsed HoursTask-HoursNumber of Per-
sons
Task
0.750.751Open Access
1.001.001Figure 5
1.001.001Figure 6
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Work Package 4 - Right Wing - Wire Bundle Change
Elapsed HoursTask-HoursNumber of Per-
sons
Task
0.750.751Close Access
3.503.50Total for Work Package 4
Work Package number four can be done at the same time as Work Package one or two.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Engineering Change Memo PRR 85901-97RS, PRR 82874
b. Service Related Problem (SRP) 747-SRP-28-0121
c. 747 Aircraft Maintenance Manual (AMM) Subject 747-400 AMM 06-09-09, 20-11-05, 24-22-00,
28-22-07, 29-11-19
d. Boeing Standard Wiring Practices Manual SWPM 20-10-11, 20-10-12, 20-10-13, 20-10-19,
20-10-20, 20-20-00, 20-60-06
e. Boeing Parts Standards Document D-590
f. 747-400 Structural Repair Manual (SRM), 51
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
WIRE BUNDLE INSTALLATION L.H. FRONT SPAR AND LEADING
EDGE.
288U1271
WIRE BUNDLE INSTALLATION RH FRONT SPAR AND LEADING
EDGE
288U1272
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These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications: None
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated this service bulletin for effects on Fatigue Critical Structure (FCS) and for
changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This
service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown below.
If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More
kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date
Boeing gets the purchase order.
Unit Price thru
March 06/10
ROLT
(Weeks)
QTYDateNameKit Number
$26.00602504/15/09Top Kit - Fuel Feed Tube
and Wire Bundle Separa-
tion
015U1875-1
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.
Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of the methods that follow:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Mail to:
Spares Customer Support - MC 36-65
Boeing Spares Department
P.O. Box 3707
Seattle, Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit is necessary for each airplane.
Figure Kit
6532Top Kit
1111015U1875-1
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ALL
KIT 015U1875-1
NOTES
Existing Part
NumberName
Figure
New Part Number
6532
QTY
CLAMP, WIRE
BUNDLE
1414BACC10GU104
SCREW22BACS12GU3K14
(BACS12GU3K16
optional)
SCREW, CAP22BACS12GU3K16
SCREW1313BACS12GU3K8
SEAL33BACS45B1
WASHER1313NAS1149D0332J
SPACERS FOR
BOLTS
22NAS43DD3-22FC
SPACER22NAS43DD3-32FC
(NAS43DD3-22FC
optional)
2. Parts and Materials Supplied by the Operator
None.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
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20 of 43
BOEING SERVICE BULLETIN 747-29A2114

### 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. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed, but the order of removing electrical power, gaining access
to the work area, inspection, repair of damaged wire bundle, repair or replace
damaged fuel feed tube, and closing access to the work area should not be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Obey all of the warnings and cautions given in the specified manual sections.
4. The work instructions are divided into work packages. Task Hours and Elapsed Hours
for each package are given in Paragraph 1.G., Manpower. You can do each work
package independently.
5. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Torque limits to tighten nuts and bolts are in 747-400 Structural Repair Manual
(SRM), Chapter 51
6. Use the approved fastener and process material substitutions in accordance with
747-400 Structural Repair Manual (SRM), Chapter 51. Alternate fasteners are listed
in 747-400 Structural Repair Manual (SRM) Chapter 51 and Boeing Drawing
012W6100.
7. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
8. The necessary conditions for selection of a clamp and clamp size are included in
SWPM 20-10-12. If the clamp size for the wire harness supports specified in this
service bulletin does not make a correct fit on the wire bundle, refer to SWPM
20-10-12 as an accepted procedure to select the correct clamp.
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Copyright © Unpublished Work - See page 1 for details.
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21 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 22

9. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure or irregularity.
This level of inspection is made from within touching distance unless otherwise
specified. A mirror may be necessary to enhance visual access to all exposed surfaces
in the inspection area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may
require removal or opening of access panels or doors. Stands, ladders or platforms
may be required to gain proximity to the area being checked.
10. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
11. Materials and supplies in the manuals given in Paragraph 1.J., References, can be
necessary. Examine the specified maintenance manual procedures to make sure all
necessary supplies are available.
B. WORK INSTRUCTIONS
WORK PACKAGE 1 - Left Wing - Wire Bundle Inspection
1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
2. Remove door 511CT located in the upper inboard nacelle if necessary for access. Refer to 747-400
AMM 06-09-08 as an accepted procedure.
3. Gain access to fuel feed tube and power feeder cable in the number two pylon area.
4. Find if the wire bundle W4300 has correct or incorrect routing in accordance with FIGURE 1.
a. Do a General Visual Inspection of the wire bundle.
(1) If the wire bundle routing goes above the support bracket no more action is required.
(2) If the wire bundle routing goes under the support bracket, do a General Visual Inspection
for damage between the wire bundle and the fuel feed tube.
(a) If damage is found, repair the wire bundle. Refer to SWPM 20-10-13 as an accepted
procedure.
(b) If damage is found, repair the fuel feed tube where wire bundles goes across the
tube. Refer to 747-400 AMM 28-22-07, for fuel system tubing damage check as an
accepted procedure.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1: July 15, 2010
22 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 23

1) If the fuel feed tube has damage that is not permitted, repair or replace the tube.
Refer to 747-400 AMM 28-22-07 as an accepted procedure.
2) If the fuel feed tube does not have damage more than the permitted limits, go
to step three.
(3) Move the wire bundle above the support bracket in accordance with Work Package 2.
5. Install access door 511CT located in the upper inboard nacelle if removed for access. Refer to
747-400 AMM 06-09-08 as an accepted procedure.
6. Put the airplane back to the serviceable condition.
WORK PACKAGE 2 - Left Wing - Wire Bundle Change
1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
2. Remove the door 511CT located in the upper inboard nacelle if necessary for access. Refer to
747-400 AMM 06-09-08 as an accepted procedure.
3. Gain access to fuel feed tube and power feeder cable in the number two pylon area.
4. Move the wire bundle to the specified location in accordance with FIGURE 2.
5. If the wire bundle must have more slack to let it to be moved to the new routing, refer to this list
of steps:
a. Remove door 464AL and 464AR in the aft fairing if necessary for access. Refer to 747-400
AMM 29-11-19 as an accepted procedure.
b. Move the wire bundle to get more slack in accordance with FIGURE 3.
c. Install door 464AL and 464AR in the aft fairing if removed for access. Refer to 747-400 AMM
29-11-19 as an accepted procedure.
6. Install access door 511CT if removed for access. Refer to 747-400 AMM 06-09-08 as an accepted
procedure.
7. Put the airplane back to the serviceable condition.
WORK PACKAGE 3 - Right Wing - Wire Bundle Inspection
1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
2. Remove door 611CT located in the upper inboard nacelle if necessary for access. Refer to 747-400
AMM 06-09-08 as an accepted procedure.
3. Gain access to fuel feed tube and power feeder cable in the number three pylon area.
4. Find if the wire bundle W4302 has correct or incorrect routing in accordance with FIGURE 4.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1: July 15, 2010
23 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 24

a. Do a General Visual Inspection of the wire bundle.
(1) If the wire bundle routing goes above the support bracket no more action is required.
(2) If the wire bundle routing goes under the support bracket, do a General Visual Inspection
for damage between the wire bundle and the fuel feed tube.
(a) If damage is found, repair the wire bundle. Refer to SWPM 20-10-13 as an accepted
procedure.
(b) If damage is found, repair the fuel feed tube where wire bundles goes across the
tube. Refer to 747-400 AMM 28-22-07, for fuel system tubing damage check as an
accepted procedure.
1) If the fuel feed tube has damage that is not permitted, repair or replace the tube.
Refer to 747-400 AMM 28-22-07 as an accepted procedure.
2) If the fuel feed tube does not have damage more than the permitted limits, go
to step three.
(3) Move the wire bundle above the support bracket in accordance with Work Package 4.
5. Install access door 611CT located in the upper inboard nacelle if removed for access. Refer to
747-400 AMM 06-09-08 as an accepted procedure.
6. Put the airplane back to the serviceable condition.
WORK PACKAGE 4 - Right Wing - Wire Bundle Change
1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
2. Remove the door 611CT located in the upper inboard nacelle if necessary for access. Refer to
747-400 AMM 06-09-08 as an accepted procedure.
3. Gain access to fuel feed tube and power feeder cable in the number three pylon area.
4. Move the wire bundle to the specified location in accordance with FIGURE 5.
5. If the wire bundle must have more slack to let it to be moved to the new routing, refer to this list
of steps:
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1: July 15, 2010
24 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 25

a. Remove door 474AL and 474AR in the aft fairing if necessary for access. Refer to 747-400
AMM 29-11-19 as an accepted procedure.
b. Move the wire bundle to get more slack in accordance with FIGURE 6.
c. Install door 474AL and 474AR in the aft fairing if removed for access. Refer to 747-400 AMM
29-11-19 as an accepted procedure.
6. Install access door 611CT if removed for access. Refer to 747-400 AMM 06-09-08 as an accepted
procedure.
7. Put the airplane back to the serviceable condition.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1: July 15, 2010
25 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 26 (OCR)

BOEING SERVICE BULLETIN 747-29A2114
AND
INCORRECT
WIRE ROUTE
FUEL FEED  WIRE
TUBE  FSSI  BUNDLE  W4300
684.18
FSSI
671.09  1815555
FIGURE 1: LEFT WING - WIRE BUNDLE INSPECTION
(SHEET 1 OF 3)
Original Issue: October 01, 2009
Revision 1 July 15, 2010  747-29A2114
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  26 of 43

### Page 27 (OCR)

BOEING SERVICE BULLETIN 747-29A2114
BRACKET
FUEL FEED
TUBE
CORRECT
WIRE ROUTE
WIRE
BUNDLE
FSSI  W4300
684.18
FSSI
671.09
1815574
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
FIGURE 1: LEFT WING - WIRE BUNDLE INSPECTION
(SHEET 2 OF 3)
Original Issue: October 01, 2009
Revision 1 July 15, 2010  BOEING PROPRIETARY -  747-29A2114
Copyright © Unpublished Work - See page 1 for details.  27 of 43

### Page 28

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)-W4300WIRE BUNDLEInspect1
(a) Do a General Visual Inspection of the wire bundle.
(b) Make sure the wire bundle routing goes above the bracket.
FIGURE 1: LEFT WING - WIRE BUNDLE INSPECTION
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1 July 15, 2010
28 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 29 (OCR)

BOEING SERVICE BULLETIN 747-29A2114
8) 15  SUPPORT  BRACKET
FSSI
684.18  WIRE
BUNDLE
WIRE  W4300
FSSI  BUNDLE
671.09  W212
TYPICAL
1823199
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE
(SHEET 1 OF 3)
Original Issue: October 01, 2009
Revision 1 July 15, 2010  BOEING PROPRIETARY -  747-29A2114
Copyright © Unpublished Work - See page 1 for details.  29 of 43

### Page 30

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
--SCREWRemove / Keep1
--WASHERRemove / Keep
--CLAMPRemove / Keep
--SCREWRemove / Keep2
--WASHERRemove / Keep
--CLAMPRemove / Keep
--SCREWRemove3
Remove washer be-
tween the head of
the screw and
clamp.
--WASHERRemove
--NUTRemove / Keep
Keep washer be-
tween the nut and
clamp.
--WASHERRemove / Keep
--SPACERRemove4
--CLAMPRemove5
--WASHERRemove
1-CLAMPRemove / Keep6
1-CLAMPRemove / Keep7
--BLOCKRemove / Keep8
1-CLAMPRemove / Keep9
(a)1BACS12GU3K14
(BACS12GU3K16 op-
tional)
SCREWInstall (New)10
1NAS1149D0332JWASHERInstall (New)
(a)1NAS43DD3-32FC
(NAS43DD3-22FC op-
tional)
SPACERInstall (New)11
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
1BACC10GU104CLAMP, WIRE BUN-
DLE
Install (New)12
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
1-CLAMPInstall (Kept)13
FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1 July 15, 2010
30 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 31

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
1-CLAMP, WIRE BUN-
DLE
Install (Kept)14
1-BLOCKInstall (Kept)15
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
1-CLAMPInstall (Kept)16
1-WASHERInstall (Kept)
1-NUTInstall (Kept)
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
--CLAMPInstall (Kept)17
--SCREWInstall (Kept)
--WASHERInstall (Kept)
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
--CLAMPInstall (Kept)18
--SCREWInstall (Kept)
--WASHERInstall (Kept)
(a) If the specified spacer and screw has insufficient length, use combination of spacers to get the necessary
length, but not so much length that it interferes with structure or other components. Spacers and screws
provided in extra parts table.
The parts shown in the table below are given as extra parts for this figure.
MORE DATAQTYIDENTIFICATIONNAME
3BACC10GU104CLAMP, WIRE BUN-
DLE
1BACS12GU3K14SCREW
3BACS12GU3K8SCREW
1NAS43DD3-32FCSPACER
2NAS1149D0332JWASHER
2NAS43DD3-22FCSPACERS FOR
BOLTS
2BACS12GU3K16SCREW, CAP
FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1 July 15, 2010
31 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 32

FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK
(SHEET 1 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1 July 15, 2010
32 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 33 (OCR)

BOEING SERVICE BULLETIN 747-29A2114
W4300
W4300 (3)
W4300
ELECTRICAI
3 W4300  CONNECTOF
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK
(SHEET 2 OF 3)
Original Issue: October 01, 2009
Revision 1 July 15, 2010  BOEING PROPRIETARY -  747-29A2114
Copyright © Unpublished Work - See page 1 for details.  33 of 43

### Page 34

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
--CLAMPLoosen1
Refer to SWPM 20-
10-20 as an accept-
ed procedure for re-
moval and installa-
tion of pressure seal.
1-SEALRemove / Keep2
(a)1W4300WIRE BUNDLEMove3
Refer to SWPM 20-
10-20 as an accept-
ed procedure for re-
moval and installa-
tion of pressure seal.
1-SEALInstall (Kept)4
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
1BACC10GU104CLAMP, WIRE BUN-
DLE
Tighten5
(a) Make sure to maintain drip loop at connector. Refer to SWPM 20-10-11 as an accepted procedure.
The parts shown in the table below are given as extra parts for this figure.
MORE DATAQTYIDENTIFICATIONNAME
3BACS45B1SEAL
1BACC10GU104CLAMP, WIRE BUN-
DLE
1NAS1149D0332JWASHER
1BACS12GU3K8SCREW
FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1 July 15, 2010
34 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 35 (OCR)

BOEING SERVICE BULLETIN 747-29A2114
AND
INCORRECT
WIRE ROUTE
WIRE
BUNDLE
W4302  FSSI
684.18
FSSI
671.09  FUEL FEED  1814721
TUBE
FIGURE 4: RIGHT WING - WIRE BUNDLE INSPECTION
(SHEET 1 OF 3)
Original Issue: October 01, 2009
Revision 1 July 15, 2010  BOEING PROPRIETARY -  747-29A2114
Copyright © Unpublished Work - See page 1 for details.  35 of 43

### Page 36 (OCR)

BOEING SERVICE BULLETIN 747-29A2114
- BRACKET
FUEL FEED
TUBE
CORRECT
WIRE ROUTE
WIRE
BUNDLE
W4302
FSSI
684.18
FSSI
671.09
1815478
FIGURE 4: RIGHT WING - WIRE BUNDLE INSPECTION
(SHEET 2 OF 3)
Original Issue: October 01, 2009
Revision 1 July 15, 2010  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  36 of 43

### Page 37

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)-W4302WIRE BUNDLEInspect1
(a) Do a General Visual Inspection of the wire bundle.
(b) Make sure the wire bundle routing goes above the bracket.
FIGURE 4: RIGHT WING - WIRE BUNDLE INSPECTION
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1 July 15, 2010
37 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 38 (OCR)

BOEING SERVICE BULLETIN 747-29A2114
W4302
TYPICAL
SUPPORT
BRACKET
1815701
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE
(SHEET 1 OF 3)
Original Issue: October 01, 2009
Revision 1 July 15, 2010  BOEING PROPRIETARY -  747-29A2114
Copyright © Unpublished Work - See page 1 for details.  38 of 43

### Page 39

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
--SCREWRemove / Keep1
--WASHERRemove / Keep
--CLAMPRemove / Keep
--SCREWRemove / Keep2
--WASHERRemove / Keep
--CLAMPRemove / Keep
--SCREWRemove3
Remove washer be-
tween the head of
the screw and
clamp.
--WASHERRemove
--NUTRemove / Keep
Keep washer be-
tween the nut and
clamp.
--WASHERRemove / Keep
--SPACERRemove4
--CLAMPRemove5
--WASHERRemove
1-CLAMPRemove / Keep6
1-CLAMPRemove / Keep7
--BLOCKRemove / Keep8
1-CLAMPRemove / Keep9
(a)1BACS12GU3K14
(BACS12GU3K16 op-
tional)
SCREWInstall (New)10
1NAS1149D0332JWASHERInstall (New)
(a)1NAS43DD3-32FC
(NAS43DD3-22FC op-
tional)
SPACERInstall (New)11
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
1BACC10GU104CLAMP, WIRE BUN-
DLE
Install (New)12
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
1-CLAMPInstall (Kept)13
FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1 July 15, 2010
39 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 40

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
1-CLAMPInstall (Kept)14
1-BLOCKInstall (Kept)15
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
1-CLAMPInstall (Kept)16
1-WASHERInstall (Kept)
1-NUTInstall (Kept)
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
--CLAMPInstall (Kept)17
--SCREWInstall (Kept)
--WASHERInstall (Kept)
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
--CLAMPInstall (Kept)18
--SCREWInstall (Kept)
--WASHERInstall (Kept)
(a) If the specified spacer and screw has insufficient length, use combination of spacers to get the necessary
length, but not so much length that it interferes with structure or other components. Spacers and screws
provided in extra parts table.
The parts shown in the table below are given as extra parts for this figure.
MORE DATAQTYIDENTIFICATIONNAME
3BACC10GU104CLAMP, WIRE BUN-
DLE
1BACS12GU3K14SCREW
3BACS12GU3K8SCREW
1NAS43DD3-32FCSPACER
2NAS1149D0332JWASHER
2NAS43DD3-22FCSPACERS FOR
BOLTS
2BACS12GU3K16SCREW, CAP
FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1 July 15, 2010
40 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 41

FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK
(SHEET 1 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1 July 15, 2010
41 of 43
BOEING SERVICE BULLETIN 747-29A2114

### Page 42 (OCR)

BOEING SERVICE BULLETIN 747-29A2114
W4302 3
WA302 A
W4302  2 4
ELECTRICAL
CONNECTOR
1823184
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK
(SHEET 2 OF 3)
Original Issue: October 01, 2009
Revision 1 July 15, 2010  BOEING PROPRIETARY -  747-29A2114
Copyright © Unpublished Work - See page 1 for details.  42 of 43

### Page 43

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
--CLAMPLoosen1
Refer to SWPM 20-
10-20 as an accept-
ed procedure for re-
moval and installa-
tion of pressure seal.
1-SEALRemove / Keep2
(a)1W4302WIRE BUNDLEMove3
Refer to SWPM 20-
10-20 as an accept-
ed procedure for re-
moval and installa-
tion of pressure seal.
1-SEALInstall (Kept)4
Refer to SWPM 20-
10-12 as an accept-
ed procedure.
-BACC10GU104CLAMP, WIRE BUN-
DLE
Tighten5
(a) Make sure to maintain drip loop at connector. Refer to SWPM 20-10-11 as an accepted procedure.
The parts shown in the table below are given as extra parts for this figure.
MORE DATAQTYIDENTIFICATIONNAME
3BACS45B1SEAL
1BACC10GU104CLAMP, WIRE BUN-
DLE
1NAS1149D0332JWASHER
1BACS12GU3K8SCREW
FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
747-29A2114Revision 1 July 15, 2010
43 of 43
BOEING SERVICE BULLETIN 747-29A2114

---
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