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.

ECCN: 9E991

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Copyright © 2009 The Boeing Company

Unpublished Work - All Rights Reserved

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2.0
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BOEING SERVICE BULLETIN 747-29A2114

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 16

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 20

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 20

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

FIGURE 1: LEFT WING - WIRE BUNDLE INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . 26

FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK . . . . . . . . . . . . . . . . . . . . . . . . . 32

FIGURE 4: RIGHT WING - WIRE BUNDLE INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . 35

FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK . . . . . . . . . . . . . . . . . . . . . . . . 41

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BOEING SERVICE BULLETIN 747-29A2114

BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

Revision Transmittal Sheet Number: 747-29A2114

Original Issue: October 01, 2009

Revision 1: July 15, 2010

ATA System: 2911

SUBJECT: HYDRAULIC POWER - Main Hydraulic Supply System - Wire Bundle Inspection and

Wire Routing Change

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on airplanes changed as shown in the Original Issue of this service bulletin.

Airplane RT043 was added to Group 1 of this service bulletin effectivity.

REASON FOR REVISION

As a part of a service bulletin validation program, this change was completed on RT436 by Service Bulletin

747-29A2114 Original Issue before the release of Revision 1 of this service bulletin. The change completed on

airplane RT436 by Service Bulletin 747-29A2114 Original Issue is equivalent to the release of Revision 1 of this

service bulletin. Airplane RT436 has the configuration of a Group 1 airplane.

This Revision is sent to incorporate findings of the validation of the service bulletin.

The following section of the service bulletin were changed:

1. In Summary, Background, Service Bulletin validation information has been added.

2. In Paragraph 1.A., Effectivity, airplane RT043 was added to Group 1.

3. In Paragraph 1.C., Reason, Service Bulletin validation information has been added.

4. In Paragraph 2.C., Parts Necessary For Each Airplane, Parts information was added.

5. In Figure 2, and Figure 5, Step 11, added note (a).

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: October 01, 2009

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BOEING SERVICE BULLETIN 747-29A2114
Commercial 

Airplanes 747

Service Bulletin

Summary Number: 747-29A2114

Original Issue: October 01, 2009

Revision 1: July 15, 2010

ATA System: 2911

SUBJECT: HYDRAULIC POWER - Main Hydraulic Supply System - Wire Bundle Inspection and

Wire Routing Change

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

This service bulletin is issued to do a General Visual Inspection of two wire bundles in the number two and

number three engine pylons near the leading edge and to change the wire routing if necessary. If the wire

bundles have an incorrect wire routing where they go across a fuel feed tube, damage from chaffing can occur

to the wire bundle or the fuel feed tube. If damage to the wire bundle or fuel feed tube occurs, it could cause

fuel leaks and arcing and could cause a fire in the number two or number three engine pylon.

PRR 82874 was issued in 1991 to give a design change to these areas to give better separation between several

wire bundles and the fuel tubes. As a part of this PRR, the routing of wire bundles for the Alternating Current

(AC) motor-driven pump was also changed to give better clearance from the fuel feed tubes. Service bulletin

747-24A2168 was issued to install support brackets to change the clearance between the fuel tube and the

power feeder cables in the number two and the number three engine pylons. In 2007, Boeing received a report

of a PW4056 powered 747-400 airplane that arrived at a gate with fuel leak from the drain line of the number

two engine pylon. An investigation found the AC motor-driven pump wire bundle touched the fuel feed tube

which caused chaffing and the leak.

This service bulletin gives operators instructions to do a General Visual Inspection of the wire routing near the

wing leading edge and the number two and the number three engine pylons. Instructions are given to change

the routing configuration for the wire bundles.

Boeing Service Related Problem (SRP) 747-SRP-28-0121 is related to this service bulletin.

As a part of a service bulletin validation program, this change was completed on airplane RT436 by Service

Bulletin 747-29A2114 Original Issue before the release of Revision 1 of this service bulletin. The change

completed on airplane RT436 by Service Bulletin 747-29A2114 Original Issue is equivalent to the release of

Revision 1 of this service bulletin. Airplane RT436 has the configuration of a Group 1 airplane.

ACTION (PRR 85901-97RS)

Work Package 1 - Get access to the fuel feed tube and wire bundle in the number two pylon area. Do a General

Visual Inspection for wire routing between the fuel feed tube and wire bundle. If routing is incorrect, do a General

Visual Inspection of the wire bundle and the fuel feed tube, and move the wire bundle above the support bracket

as given in Work Package 2. If wire bundle routing goes above the support bracket, no more work is necessary.

Close access and put the airplane back to the serviceable condition.

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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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BLANK PAGE
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.

GROUP CONFIGURATION DESCRIPTION

Some 747-400/-400D airplanes with AC motor-driven pumps at the

strut 2 and 3 location.

1 -

Airplane Models:

747-400, 747-400D

Variable Number Group

RT001 - RT007 1

RT021 - RT022 1

RT031 - RT033 1

RT041 - RT047 1

RT071 - RT072 1

RT101 - RT103 1

RT121 1

RT131 1

RT401 - RT410 1

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Variable Number Group

RT431 - RT438 1

RT471 - RT489 1

RT501 - RT512 1

RT531 - RT533 1

RT551 - RT564 1

RT591 1

RT631 - RT633 1

RT641 - RT654 1

RT671 - RT672 1

RT681 - RT682 1

RT691 - RT693 1

RT701 - RT703 1

RT711 - RT712 1

RT741 - RT742 1

RT751 - RT753 1

RT776 - RT777 1

RU801 - RU802 1

2. Spares Affected

None.

B. Concurrent Requirements

The service bulletin listed below must be done before this service bulletin:

Company Service Bulletin Description

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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BOEING SERVICE BULLETIN 747-29A2114
C. Reason

This service bulletin is issued to do a General Visual Inspection of two wire bundles in the number two

and number three engine pylons near the leading edge and to change the wire routing if necessary. If

the wire bundles have an incorrect wire routing where they go across a fuel feed tube, damage from

chaffing can occur to the wire bundle or the fuel feed tube. If damage to the wire bundle or fuel feed

tube occurs, it could cause fuel leaks and arcing and could cause a fire in the number two or number

three engine pylon.

PRR 82874 was issued in 1991 to give a design change to these areas to give better separation between

several wire bundles and the fuel tubes. As a part of this PRR, the routing of wire bundles for the

Alternating Current (AC) motor-driven pump was also changed to give better clearance from the fuel

feed tubes. Service bulletin 747-24A2168 was issued to install support brackets to change the clearance

between the fuel tube and the power feeder cables in the number two and the number three engine

pylons. In 2007, Boeing received a report of a PW4056 powered 747-400 airplane that arrived at a

gate with fuel leak from the drain line of the number two engine pylon. An investigation found the AC

motor-driven pump wire bundle touched the fuel feed tube which caused chaffing and the leak.

This service bulletin gives operators instructions to do a General Visual Inspection of the wire routing

near the wing leading edge and the number two and the number three engine pylons. Instructions are

given to change the routing configuration for the wire bundles.

Boeing Service Related Problem (SRP) 747-SRP-28-0121 is related to this service bulletin.

As a part of a service bulletin validation program, this change was completed on airplane RT436 by

Service Bulletin 747-29A2114 Original Issue before the release of Revision 1 of this service bulletin.

The change completed on airplane RT436 by Service Bulletin 747-29A2114 Original Issue is equivalent

to the release of Revision 1 of this service bulletin. Airplane RT436 has the configuration of a Group 1

airplane.

Revision 1 is sent to incorporate the findings of the validation.

D. Description

Work Package 1 - Get access to the fuel feed tube and wire bundle in the number two pylon area. Do

a General Visual Inspection for wire routing between the fuel feed tube and wire bundle. If routing is

incorrect, do a General Visual Inspection of the wire bundle and the fuel feed tube, and move the wire

bundle above the support bracket as given in Work Package 2. If wire bundle routing goes above the

support bracket, no more work is necessary. Close access and put the airplane back to the serviceable

condition.

Work Package 2 - Get access to the fuel feed tube and wire bundle in the number two pylon area.

Move the wire bundle above the support bracket. Close access and put the airplane back to the

serviceable condition.

Work Package 3 - Get access to the fuel feed tube and wire bundle in the number three pylon area.

Do a General Visual Inspection for for wire routing between the fuel feed tube and wire bundle. If routing

is incorrect, do a General Visual Inspection of the wire bundle and the fuel feed tube, and move the

wire bundle above the support bracket as given in Work Package 4. If wire bundle routing goes above

the support bracket, no more work is necessary. Close access and put the airplane back to the

serviceable condition.

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BOEING SERVICE BULLETIN 747-29A2114
Work Package 4 - Get access to the fuel feed tube and wire bundle in the number three pylon area.

Move the wire bundle above the support bracket. Close access and put the airplane back to the

serviceable condition.

Revision 1 - No more work is necessary on airplanes changed as shown in the Original Issue of this

service bulletin.

Airplane RT043 was added to Group 1 of this service bulletin effectivity.

The work in this service bulletin is done in the maintenance zone(s) given below.

Affected Maintenance Zones

Model Zone

747-400, 747-400D 461, 462, 463, 464, 471, 472, 473, 474

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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BOEING SERVICE BULLETIN 747-29A2114
Work Package 1 - Left Wing - Wire Bundle Inspection

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 0.50 0.50

Figure 1 1 0.25 0.25

Close Access 1 0.50 0.50

Total for Work Package 1 1.25 1.25

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

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 0.75 0.75

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Close Access 1 0.75 0.75

Total for Work Package 2 3.50 3.50

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

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 0.50 0.50

Figure 4 1 0.25 0.25

Close Access 1 0.50 0.50

Total for Work Package 3 1.25 1.25

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

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 0.75 0.75

Figure 5 1 1.00 1.00

Figure 6 1 1.00 1.00

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BOEING SERVICE BULLETIN 747-29A2114
Work Package 4 - Right Wing - Wire Bundle Change

Number of Per- Task-Hours Elapsed Hours

sons

Task

Close Access 1 0.75 0.75

Total for Work Package 4 3.50 3.50

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

Drawing Number Title

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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BOEING SERVICE BULLETIN 747-29A2114
These drawings were used to prepare this service bulletin. These drawings are not necessary to

make the specified changes, and are not supplied with this service bulletin. These drawings may

not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications: None

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated this service bulletin for effects on Fatigue Critical Structure (FCS) and for

changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This

service bulletin does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

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BOEING SERVICE BULLETIN 747-29A2114

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown below.

If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More

kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date

Boeing gets the purchase order.

Unit Price thru

March 06/10

ROLT

(Weeks)

Kit Number Name Date QTY

Top Kit - Fuel Feed Tube 04/15/09 25 60 $26.00

and Wire Bundle Separation

015U1875-1

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.

Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of the methods that follow:

1. Order on-line via ATA Spec 2000 or Boeing Part Page

2. Fax to (206) 662-7145

3. Mail to:

Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

NOTE: One top kit is necessary for each airplane.

Figure Kit

Top Kit 2 3 5 6

015U1875-1 1 1 1 1

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BOEING SERVICE BULLETIN 747-29A2114
ALL

KIT 015U1875-1

NOTES

Existing Part

Name Number

Figure

New Part Number

2 3 5 6

QTY

CLAMP, WIRE

BUNDLE

BACC10GU104 4 1 4 1

BACS12GU3K14 2 2 SCREW

(BACS12GU3K16

optional)

BACS12GU3K16 2 2 SCREW, CAP

BACS12GU3K8 3 1 3 1 SCREW

BACS45B1 3 3 SEAL

NAS1149D0332J 3 1 3 1 WASHER

SPACERS FOR

BOLTS

NAS43DD3-22FC 2 2

NAS43DD3-32FC 2 2 SPACER

(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.

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BOEING SERVICE BULLETIN 747-29A2114
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)

give the recommended sequence of steps. The sequence of steps to do this service

bulletin can be changed, but the order of removing electrical power, gaining access

to the work area, inspection, repair of damaged wire bundle, repair or replace

damaged fuel feed tube, and closing access to the work area should not be changed.

2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

3. Obey all of the warnings and cautions given in the specified manual sections.

4. The work instructions are divided into work packages. Task Hours and Elapsed Hours

for each package are given in Paragraph 1.G., Manpower. You can do each work

package independently.

5. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Torque limits to tighten nuts and bolts are in 747-400 Structural Repair Manual

(SRM), Chapter 51

6. Use the approved fastener and process material substitutions in accordance with

747-400 Structural Repair Manual (SRM), Chapter 51. Alternate fasteners are listed

in 747-400 Structural Repair Manual (SRM) Chapter 51 and Boeing Drawing

012W6100.

7. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,

and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

8. The necessary conditions for selection of a clamp and clamp size are included in

SWPM 20-10-12. If the clamp size for the wire harness supports specified in this

service bulletin does not make a correct fit on the wire bundle, refer to SWPM

20-10-12 as an accepted procedure to select the correct clamp.

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BOEING SERVICE BULLETIN 747-29A2114
9. A General Visual Inspection is defined as: A visual examination of an interior or

exterior area, installation or assembly to detect obvious damage, failure or irregularity.

This level of inspection is made from within touching distance unless otherwise

specified. A mirror may be necessary to enhance visual access to all exposed surfaces

in the inspection area. This level of inspection is made under normally available

lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may

require removal or opening of access panels or doors. Stands, ladders or platforms

may be required to gain proximity to the area being checked.

10. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

11. Materials and supplies in the manuals given in Paragraph 1.J., References, can be

necessary. Examine the specified maintenance manual procedures to make sure all

necessary supplies are available.

B. WORK INSTRUCTIONS

WORK PACKAGE 1 - Left Wing - Wire Bundle Inspection

1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted

procedure.

2. Remove door 511CT located in the upper inboard nacelle if necessary for access. Refer to 747-400

AMM 06-09-08 as an accepted procedure.

3. Gain access to fuel feed tube and power feeder cable in the number two pylon area.

4. Find if the wire bundle W4300 has correct or incorrect routing in accordance with FIGURE 1.

a. Do a General Visual Inspection of the wire bundle.

(1) If the wire bundle routing goes above the support bracket no more action is required.

(2) If the wire bundle routing goes under the support bracket, do a General Visual Inspection

for damage between the wire bundle and the fuel feed tube.

(a) If damage is found, repair the wire bundle. Refer to SWPM 20-10-13 as an accepted

procedure.

(b) If damage is found, repair the fuel feed tube where wire bundles goes across the

tube. Refer to 747-400 AMM 28-22-07, for fuel system tubing damage check as an

accepted procedure.

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BOEING SERVICE BULLETIN 747-29A2114
1) If the fuel feed tube has damage that is not permitted, repair or replace the tube.

Refer to 747-400 AMM 28-22-07 as an accepted procedure.

2) If the fuel feed tube does not have damage more than the permitted limits, go

to step three.

(3) Move the wire bundle above the support bracket in accordance with Work Package 2.

5. Install access door 511CT located in the upper inboard nacelle if removed for access. Refer to

747-400 AMM 06-09-08 as an accepted procedure.

6. Put the airplane back to the serviceable condition.

WORK PACKAGE 2 - Left Wing - Wire Bundle Change

1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted

procedure.

2. Remove the door 511CT located in the upper inboard nacelle if necessary for access. Refer to

747-400 AMM 06-09-08 as an accepted procedure.

3. Gain access to fuel feed tube and power feeder cable in the number two pylon area.

4. Move the wire bundle to the specified location in accordance with FIGURE 2.

5. If the wire bundle must have more slack to let it to be moved to the new routing, refer to this list

of steps:

a. Remove door 464AL and 464AR in the aft fairing if necessary for access. Refer to 747-400

AMM 29-11-19 as an accepted procedure.

b. Move the wire bundle to get more slack in accordance with FIGURE 3.

c. Install door 464AL and 464AR in the aft fairing if removed for access. Refer to 747-400 AMM

29-11-19 as an accepted procedure.

6. Install access door 511CT if removed for access. Refer to 747-400 AMM 06-09-08 as an accepted

procedure.

7. Put the airplane back to the serviceable condition.

WORK PACKAGE 3 - Right Wing - Wire Bundle Inspection

1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted

procedure.

2. Remove door 611CT located in the upper inboard nacelle if necessary for access. Refer to 747-400

AMM 06-09-08 as an accepted procedure.

3. Gain access to fuel feed tube and power feeder cable in the number three pylon area.

4. Find if the wire bundle W4302 has correct or incorrect routing in accordance with FIGURE 4.

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BOEING SERVICE BULLETIN 747-29A2114
a. Do a General Visual Inspection of the wire bundle.

(1) If the wire bundle routing goes above the support bracket no more action is required.

(2) If the wire bundle routing goes under the support bracket, do a General Visual Inspection

for damage between the wire bundle and the fuel feed tube.

(a) If damage is found, repair the wire bundle. Refer to SWPM 20-10-13 as an accepted

procedure.

(b) If damage is found, repair the fuel feed tube where wire bundles goes across the

tube. Refer to 747-400 AMM 28-22-07, for fuel system tubing damage check as an

accepted procedure.

1) If the fuel feed tube has damage that is not permitted, repair or replace the tube.

Refer to 747-400 AMM 28-22-07 as an accepted procedure.

2) If the fuel feed tube does not have damage more than the permitted limits, go

to step three.

(3) Move the wire bundle above the support bracket in accordance with Work Package 4.

5. Install access door 611CT located in the upper inboard nacelle if removed for access. Refer to

747-400 AMM 06-09-08 as an accepted procedure.

6. Put the airplane back to the serviceable condition.

WORK PACKAGE 4 - Right Wing - Wire Bundle Change

1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted

procedure.

2. Remove the door 611CT located in the upper inboard nacelle if necessary for access. Refer to

747-400 AMM 06-09-08 as an accepted procedure.

3. Gain access to fuel feed tube and power feeder cable in the number three pylon area.

4. Move the wire bundle to the specified location in accordance with FIGURE 5.

5. If the wire bundle must have more slack to let it to be moved to the new routing, refer to this list

of steps:

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BOEING SERVICE BULLETIN 747-29A2114
a. Remove door 474AL and 474AR in the aft fairing if necessary for access. Refer to 747-400

AMM 29-11-19 as an accepted procedure.

b. Move the wire bundle to get more slack in accordance with FIGURE 6.

c. Install door 474AL and 474AR in the aft fairing if removed for access. Refer to 747-400 AMM

29-11-19 as an accepted procedure.

6. Install access door 611CT if removed for access. Refer to 747-400 AMM 06-09-08 as an accepted

procedure.

7. Put the airplane back to the serviceable condition.

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BOEING SERVICE BULLETIN 747-29A2114
FIGURE 1: LEFT WING - WIRE BUNDLE INSPECTION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for this figure.

FIGURE 1: LEFT WING - WIRE BUNDLE INSPECTION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Inspect WIRE BUNDLE W4300 - (a) (b)

(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)

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BOEING SERVICE BULLETIN 747-29A2114
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for this figure.

FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep SCREW - -

Remove / Keep WASHER - -

Remove / Keep CLAMP - -

2 Remove / Keep SCREW - -

Remove / Keep WASHER - -

Remove / Keep CLAMP - -

3 Remove SCREW - -

Remove washer between the head of

the screw and

clamp.

Remove WASHER - -

Remove / Keep NUT - -

Keep washer between the nut and

clamp.

Remove / Keep WASHER - -

4 Remove SPACER - -

5 Remove CLAMP - -

Remove WASHER - -

6 Remove / Keep CLAMP - 1

7 Remove / Keep CLAMP - 1

8 Remove / Keep BLOCK - -

9 Remove / Keep CLAMP - 1

BACS12GU3K14 1 (a)

(BACS12GU3K16 optional)

10 Install (New) SCREW

Install (New) WASHER NAS1149D0332J 1

NAS43DD3-32FC 1 (a)

(NAS43DD3-22FC optional)

11 Install (New) SPACER

Refer to SWPM 20-

10-12 as an accepted procedure.

CLAMP, WIRE BUN- BACC10GU104 1

DLE

12 Install (New)

Refer to SWPM 20-

10-12 as an accepted procedure.

13 Install (Kept) CLAMP - 1

FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SWPM 20-

10-12 as an accepted procedure.

CLAMP, WIRE BUN- - 1

DLE

14 Install (Kept)

15 Install (Kept) BLOCK - 1

Refer to SWPM 20-

10-12 as an accepted procedure.

16 Install (Kept) CLAMP - 1

Install (Kept) WASHER - 1

Install (Kept) NUT - 1

Refer to SWPM 20-

10-12 as an accepted procedure.

17 Install (Kept) CLAMP - -

Install (Kept) SCREW - -

Install (Kept) WASHER - -

Refer to SWPM 20-

10-12 as an accepted procedure.

18 Install (Kept) CLAMP - -

Install (Kept) SCREW - -

Install (Kept) WASHER - -

(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.

NAME IDENTIFICATION QTY MORE DATA

CLAMP, WIRE BUN- BACC10GU104 3

DLE

SCREW BACS12GU3K14 1

SCREW BACS12GU3K8 3

SPACER NAS43DD3-32FC 1

WASHER NAS1149D0332J 2

SPACERS FOR NAS43DD3-22FC 2

BOLTS

SCREW, CAP BACS12GU3K16 2

FIGURE 2: LEFT WING - WIRE BUNDLE CHANGE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for this figure.

FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Loosen CLAMP - -

Refer to SWPM 20-

10-20 as an accepted procedure for removal and installation of pressure seal.

2 Remove / Keep SEAL - 1

3 Move WIRE BUNDLE W4300 1 (a)

Refer to SWPM 20-

10-20 as an accepted procedure for removal and installation of pressure seal.

4 Install (Kept) SEAL - 1

Refer to SWPM 20-

10-12 as an accepted procedure.

CLAMP, WIRE BUN- BACC10GU104 1

DLE

5 Tighten

(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.

NAME IDENTIFICATION QTY MORE DATA

SEAL BACS45B1 3

CLAMP, WIRE BUN- BACC10GU104 1

DLE

WASHER NAS1149D0332J 1

SCREW BACS12GU3K8 1

FIGURE 3: LEFT WING - GIVE WIRE BUNDLE SLACK

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
FIGURE 4: RIGHT WING - WIRE BUNDLE INSPECTION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
FIGURE 4: RIGHT WING - WIRE BUNDLE INSPECTION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Inspect WIRE BUNDLE W4302 - (a) (b)

(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)

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Copyright © Unpublished Work - See page 1 for details.

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37 of 43

BOEING SERVICE BULLETIN 747-29A2114
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for this figure.

FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep SCREW - -

Remove / Keep WASHER - -

Remove / Keep CLAMP - -

2 Remove / Keep SCREW - -

Remove / Keep WASHER - -

Remove / Keep CLAMP - -

3 Remove SCREW - -

Remove washer between the head of

the screw and

clamp.

Remove WASHER - -

Remove / Keep NUT - -

Keep washer between the nut and

clamp.

Remove / Keep WASHER - -

4 Remove SPACER - -

5 Remove CLAMP - -

Remove WASHER - -

6 Remove / Keep CLAMP - 1

7 Remove / Keep CLAMP - 1

8 Remove / Keep BLOCK - -

9 Remove / Keep CLAMP - 1

BACS12GU3K14 1 (a)

(BACS12GU3K16 optional)

10 Install (New) SCREW

Install (New) WASHER NAS1149D0332J 1

NAS43DD3-32FC 1 (a)

(NAS43DD3-22FC optional)

11 Install (New) SPACER

Refer to SWPM 20-

10-12 as an accepted procedure.

CLAMP, WIRE BUN- BACC10GU104 1

DLE

12 Install (New)

Refer to SWPM 20-

10-12 as an accepted procedure.

13 Install (Kept) CLAMP - 1

FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SWPM 20-

10-12 as an accepted procedure.

14 Install (Kept) CLAMP - 1

15 Install (Kept) BLOCK - 1

Refer to SWPM 20-

10-12 as an accepted procedure.

16 Install (Kept) CLAMP - 1

Install (Kept) WASHER - 1

Install (Kept) NUT - 1

Refer to SWPM 20-

10-12 as an accepted procedure.

17 Install (Kept) CLAMP - -

Install (Kept) SCREW - -

Install (Kept) WASHER - -

Refer to SWPM 20-

10-12 as an accepted procedure.

18 Install (Kept) CLAMP - -

Install (Kept) SCREW - -

Install (Kept) WASHER - -

(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.

NAME IDENTIFICATION QTY MORE DATA

CLAMP, WIRE BUN- BACC10GU104 3

DLE

SCREW BACS12GU3K14 1

SCREW BACS12GU3K8 3

SPACER NAS43DD3-32FC 1

WASHER NAS1149D0332J 2

SPACERS FOR NAS43DD3-22FC 2

BOLTS

SCREW, CAP BACS12GU3K16 2

FIGURE 5: RIGHT WING - WIRE BUNDLE CHANGE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114
FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 01, 2009

Revision 1 July 15, 2010 747-29A2114

41 of 43

BOEING SERVICE BULLETIN 747-29A2114
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for this figure.

FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK

(SHEET 2 OF 3)

BOEING PROPRIETARY -

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42 of 43

BOEING SERVICE BULLETIN 747-29A2114
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Loosen CLAMP - -

Refer to SWPM 20-

10-20 as an accepted procedure for removal and installation of pressure seal.

2 Remove / Keep SEAL - 1

3 Move WIRE BUNDLE W4302 1 (a)

Refer to SWPM 20-

10-20 as an accepted procedure for removal and installation of pressure seal.

4 Install (Kept) SEAL - 1

Refer to SWPM 20-

10-12 as an accepted procedure.

CLAMP, WIRE BUN- BACC10GU104 -

DLE

5 Tighten

(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.

NAME IDENTIFICATION QTY MORE DATA

SEAL BACS45B1 3

CLAMP, WIRE BUN- BACC10GU104 1

DLE

WASHER NAS1149D0332J 1

SCREW BACS12GU3K8 1

FIGURE 6: RIGHT WING - GIVE WIRE BUNDLE SLACK

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-29A2114