Commercial 

Airplanes 747

Service Bulletin

Number: 747-24A2360

Original Issue: January 18, 2012

Revision 2: October 02, 2013

ATA System: 2421

SUBJECT: ELECTRICAL POWER - 115 Volt AC Power Generation and Protection - APU Power

Feeder Cable Inspection and Clamp Change

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 300-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2012 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

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5.0
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BOEING SERVICE BULLETIN 747-24A2360

BLANK PAGE
Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 20

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 23

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 24

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT

BULKHEAD STA 2638 [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

FIGURE 2: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638

[Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT

BULKHEAD STA 2638 [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

FIGURE 4: CLAMP REPLACEMENT AND GROMMET INSTALLATION - RIGHT BULKHEAD STA 2638

[Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT

BULKHEAD STA 2638 [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

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BOEING SERVICE BULLETIN 747-24A2360
FIGURE 6: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638

[Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

FIGURE 7: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT

BULKHEAD STA 2638 [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47

FIGURE 8: GROMMET INSTALLATION AND CLAMP REPLACEMENT - RIGHT BULKHEAD STA 2638

[Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

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BOEING SERVICE BULLETIN 747-24A2360
Commercial 

Airplanes 747

Service Bulletin

Revision Transmittal Sheet Number: 747-24A2360

Original Issue: January 18, 2012

Revision 2: October 02, 2013

ATA System: 2421

SUBJECT: ELECTRICAL POWER - 115 Volt AC Power Generation and Protection - APU Power

Feeder Cable Inspection and Clamp Change

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2012-NM-166-AD is related to

this service bulletin.

No more work is necessary on the airplane(s) in accordance with the Original Issue or Revision 1 of this service

bulletin.

REASON FOR REVISION

Revision 2 is sent to add the Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)

2012-NM-166-AD. Extend compliance times for all groups as requested by FAA. Additional, this revision corrects

discrepancies found by operators during the accomplishment of this service bulletin.

These sections were changed:

Summary Background: Updated planning table for this revision.

Summary Action: Changed detailed visual inspection to detailed inspection.

Summary Compliance: Added FAA NPRM 2012-NM-166-AD and update compliance time.

Paragraph 1.C Reason: Added reason for revision.

Paragraph 1.D Description: Changed detailed visual inspection to detailed inspection.

Paragraph 1.D Description: Added "No more work is necessary" statement.

Paragraph 1.E Compliance: Added FAA NPRM 2012-NM-166-AD, compliance information tables and updated

compliance time paragraph.

Paragraph 1.E Compliance: Table 1 and table 2, update "all airplane" compliance time.

Paragraph 1.J Reference: Added FAA NPRM 2012-NM-166-AD.

Paragraph 1.K.1 Publications Affected: Added chapter-section.

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Paragraph 1.M Software Accomplishment Summary: Added "Not affected".

Paragraph 2.B Industry Support Information: Updated warranty statement.

Paragraph 3.A General Information: Notes have been added or deleted to meet new requirements.

Paragraph 3.B Work Instructions: Through out work instructions changed detailed visual inspection to detailed

inspection.

Paragraph 3.B Work Instructions: Item 3.a, removed referenced figures and added steps for group 1.

Paragraph 3.B Work Instructions: Item 3.b.(1)(a)1) updated to new requirements.

Paragraph 3.B Work Instructions: Item 3.b.(1)(b) added statement for no damage found.

Paragraph 3.B Work Instructions: Item 4.a, removed referenced figures and added steps for group 2.

Paragraph 3.B Work Instructions: Item 4.b.(1)(a)1) updated to new requirements.

Paragraph 3.B Work Instructions: Item 4.b.(1)(b) added statement for no damage found.

Paragraph 3.B Work Instructions: Item 6, revised to close accesses.

Paragraph 3.B Work Instructions: Added item 7 to return airplane to serviceable condition.

Figure 1: Changed detailed visual inspection to detailed inspection, in the more data column.

Figure 3: Changed detailed visual inspection to detailed inspection, in the more data column.

Figure 5: Changed detailed visual inspection to detailed inspection, in the more data column.

Figure 6: Added Note (b) to step 1 in step table.

Figure 7: Correct figure and changed detailed visual inspection to detailed inspection, in the more data column.

The data given in Information Notice (IN) 747-24A2360 IN 03 is included in this revision.

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: January 18, 2012

Revision 1: May 02, 2012

Revision 2: October 02, 2013

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BOEING SERVICE BULLETIN 747-24A2360
Commercial 

Airplanes 747

Service Bulletin

Summary Number: 747-24A2360

Original Issue: January 18, 2012

Revision 2: October 02, 2013

ATA System: 2421

SUBJECT: ELECTRICAL POWER - 115 Volt AC Power Generation and Protection - APU Power

Feeder Cable Inspection and Clamp Change

CONCURRENT REQUIREMENTS

None

BACKGROUND

Accomplishment of this service bulletin will prevent possible damage to Auxiliary Power Unit (APU) power feeder

cables from chafing against the forward flange of the frame inner chord on the structure near Station 2638 on

the left and right sides. If the power feeders have damage, arcs can occur and introduce an ignition source in

a flammable fluid leakage zone which does not have smoke detectors or fire extinguishers. Arcing in a flammable

fluid leakage zone can be an ignition source for fuel vapors and cause a fire.

Operators have given reports of faults of the APU. Investigations showed that the power feeder cables on APU

generator number 2 had damage from chafing at Station 2638. The cables showed evidence of a hot short to

the adjacent structure. Reports show that the adjacent structure had damage from arcs. An investigation shows

that the location and configuration of the existing clamps must be changed. Also, the protective grommets must

be installed on the structure to prevent possible chafing. The chafing and subsequent arcing occurred in a

flammable leakage zone.

This service bulletin gives the instructions to inspect the APU power feeder cables for damage and to inspect

the structure for damage. Also, this bulletin gives instructions to install protection on edges of the structure, and

change the clamp configuration on the wire bundles to give sufficient clearance from the structure. These changes

will prevent chafing and remove the risk of a fire.

Boeing Service Related Problem (SRP) 747-SRP-24-0142 is related to this service bulletin.

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

information.

Planning Data Affected Reference

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

AD Related Yes Paragraph 1.E., Compliance

Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes

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

Publications Affected No Paragraph 1.K., Publications Affected

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Planning Data Affected Reference

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

Operations Manual and/or FAA Approved Airplane Flight Manual)

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

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

by the Operator

Operator Supplied Material No

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

Get access to the in the area just forward of the APU bulkhead STA 2638. Do a detailed inspection of APU

power feeders W866 or W944 on the left side and W868 or W946 on the right side for damage. If damage to

the power feeder cable is found, do a detailed inspection of the adjacent structure for damage. If damage is

found to the power feeder cables and/or the structure, repair the damage. Replace certain clamps on the power

feeder cables and install grommets on the structure. Close access.

EFFECTIVITY

747-400 Airplanes with a horizontal stabilizer fuel tank. Refer to Paragraph 1.A.1., Airplanes, for the list of

affected airplane(s).

COMPLIANCE

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2012-NM-166-AD is related to

this service bulletin.

Boeing recommends that the inspection, change and/or repair given in this service bulletin be done within 18

months after the Revision 2 date of this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of July 13, 2011. Please refer to Paragraph

2.B., Industry Support Information.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

Group 1 airplanes 5.70 5.70

Group 2 airplanes 5.85 5.85

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BOEING SERVICE BULLETIN 747-24A2360

BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

Number: 747-24A2360

Original Issue: January 18, 2012

Revision 2: October 02, 2013

ATA System: 2421

SUBJECT: ELECTRICAL POWER - 115 Volt AC Power Generation and Protection - APU Power

Feeder Cable Inspection and Clamp Change

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplane(s) shown below.

Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

1 - 747-400 Airplanes with a certain clamp configuration

2 - 747-400 Airplanes with a certain clamp configuration

Airplane Models:

747-400

Variable Number Group

RF001 - RF006 2

RM010 - RM013 2

RM021 - RM024 2

RM026 - RM030 2

RM036 - RM045 2

RM051 - RM053 2

RM071 2

RM081 - RM084 2

RM091 2

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Variable Number Group

RM096 - RM097 2

RM116 - RM117 2

RM136 - RM147 2

RM156 - RM158 2

RM166 - RM177 2

RM191 - RM192 2

RM231 - RM233 2

RM241 - RM246 2

RM261 - RM264 2

RM331 - RM333 2

RM341 2

RM351 - RM355 2

RM366 - RM367 2

RM401 - RM403 2

RM426 2

RM431 2

RM441 - RM443 2

RM445 2

RM801 - RM803 2

RT001 - RT011 1

RT012 - RT014 2

RT043 - RT047 1

RT073 1

RT101 - RT103 1

RT121 1

RT131 - RT134 1

RT135 - RT137 2

RT151 - RT152 2

RT162 - RT163 1

RT165 - RT168 2

RT401 - RT412 1

RT431 - RT441 1

RT442 - RT447 2

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BOEING SERVICE BULLETIN 747-24A2360
Variable Number Group

RT452 - RT455 1

RT457 - RT460 1

RT462 - RT467 1

RT468 - RT469 2

RT471 - RT498 1

RT499 2

RT502 - RT505 1

RT511 - RT512 1

RT514 - RT515 1

RT517 1

RT521 - RT523 1

RT525 2

RT527 2

RT529 2

RT551 - RT568 1

RT571 1

RT580 - RT583 1

RT584 - RT588 2

RT590 2

RT591 1

RT601 - RT614 1

RT616 - RT622 1

RT623 - RT630 2

RT633 - RT634 1

RT636 - RT640 2

RT672 - RT673 1

RT693 - RT697 1

RT698 - RT699 2

RT701 - RT704 1

RT741 1

RT744 - RT748 1

RT749 - RT750 2

RT753 - RT755 1

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BOEING SERVICE BULLETIN 747-24A2360
Variable Number Group

RT783 - RT784 1

RT801 - RT803 2

RT811 - RT814 2

RT831 - RT835 2

RT931 - RT932 1

RT945 - RT949 2

RT951 - RT954 1

RT955 2

RU016 - RU017 2

RU031 1

RU032 2

RU051 - RU052 1

RU059 - RU060 2

RU061 1

RU062 2

RU081 - RU083 2

RU101 - RU102 2

RU121 2

RU126 - RU132 2

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

Accomplishment of this service bulletin will prevent possible damage to Auxiliary Power Unit (APU)

power feeder cables from chafing against the forward flange of the frame inner chord on the structure

near Station 2638 on the left and right sides. If the power feeders have damage, arcs can occur and

introduce an ignition source in a flammable fluid leakage zone which does not have smoke detectors

or fire extinguishers. Arcing in a flammable fluid leakage zone can be an ignition source for fuel vapors

and cause a fire.

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BOEING SERVICE BULLETIN 747-24A2360
Operators have given reports of faults of the APU. Investigations showed that the power feeder cables

on APU generator number 2 had damage from chafing at Station 2638. The cables showed evidence

of a hot short to the adjacent structure. Reports show that the adjacent structure had damage from

arcs. An investigation shows that the location and configuration of the existing clamps must be changed.

Also, the protective grommets must be installed on the structure to prevent possible chafing. The chafing

and subsequent arcing occurred in a flammable leakage zone.

This service bulletin gives the instructions to inspect the APU power feeder cables for damage and to

inspect the structure for damage. Also, this bulletin gives instructions to install protection on edges of

the structure, and change the clamp configuration on the wire bundles to give sufficient clearance from

the structure. These changes will prevent chafing and remove the risk of a fire.

Revision 1 is sent to revise the Original Issued service bulletin to delete airplanes from this service

bulletin. Also, to revise the kits and the work instruction.

The data given in Information Notice 747-24A2360 IN01 and 747-24A2360 IN02 are included in this

revision.

Revision 2 is sent to add the Federal Aviation Administration (FAA) Notice of Proposed Rule Making

(NPRM) 2012-NM-166-AD. Extend compliance times for all groups as requested by FAA. Additional,

this revision corrects discrepancies found by operators during the accomplishment of this service

bulletin.

The data given in Information Notice 747-24A2360 IN03 is included in this revision.

Boeing Service Related Problem (SRP) 747-SRP-24-0142 is related to this service bulletin.

D. Description

Get access to the in the area just forward of the APU bulkhead STA 2638. Do a detailed inspection of

APU power feeders W866 or W944 on the left side and W868 or W946 on the right side for damage.

If damage to the power feeder cable is found, do a detailed inspection of the adjacent structure for

damage. If damage is found to the power feeder cables and/or the structure, repair the damage. Replace

certain clamps on the power feeder cables and install grommets on the structure. Close access.

Revision 1 - No more work is necessary on airplanes changed in accordance with the Original Issue

of this service bulletin.

Revision 2 - No more work is necessary on the airplane(s) in accordance with the Original Issue or

Revision 1 of this service bulletin.

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

Affected Maintenance Zones

Model Zone

747-400 315, 316

E. Compliance

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2012-NM-166-AD is

related to this service bulletin.

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BOEING SERVICE BULLETIN 747-24A2360
Boeing recommends that the inspection, change and/or repair given in this service bulletin be done

within 18 months after the Revision 2 date of this service bulletin.

Group 1:

Table 1: BULKHEAD STATION 2638, Inspection APU power feeder cables and adjacent structure

for damage

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 18 months --

after the Revision

2 date of this service bulletin.

Do a detailed inspection

of APU power feeder cable for damage in accordance with 3.B.3, left and

right side of bulkhead.

All airplanes

Replace the clamps and Before further flight --

install the grommets in

accordance with 3.B.3.a.

No damage to APU power

feeder cable is found

Do a detailed inspection Before further flight --

adjacent structure for

damage in accordance

with 3.B.3.b.(1).

Any damage to APU power

feeder cable is found

And

Repair the damage to the

cable in accordance with

3.B.3.b.(2)

And

Replace the clamps and

install the grommets in

accordance with 3.B.3.c.

through 3.B.3.f.

Do the repair in accor- Before further flight --

dance with

3.B.3.b.(1)(a)1).

Any damage to the adjacent structure is found

or

Contact Boeing for repair

instructions and do the

repair.

No further action is re- -- --

quired.

No damage to the adjacent

structure is found

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BOEING SERVICE BULLETIN 747-24A2360
Group 2:

Table 2: BULKHEAD STATION 2638, Inspection APU power feeder cables and adjacent structure

for damage

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 18 months --

after the Revision

2 date of this service bulletin.

Do a detailed inspection

of APU power feeder cable for damage in accordance with 3.B.4, left and

right side of bulkhead.

All airplanes

Replace the clamps and Before further flight --

install the grommets in

accordance with 3.B.4.a.

No damage to APU power

feeder cable is found

Do a detailed inspection Before further flight --

adjacent structure for

damage in accordance

with 3.B.4.b.(1).

Any damage to APU power

feeder cable is found

And

Repair the damage to the

cable in accordance with

3.B.4.b.(2)

And

Replace the clamps and

install the grommets in

accordance with 3.B.4.c.

through 3.B.4.f.

Do the repair in accor- Before further flight --

dance with

3.B.4.b.(1)(a)1).

Any damage to the adjacent structure is found

or

Contact Boeing for repair

instructions and do the

repair.

No further action is re- -- --

quired.

No damage to the adjacent

structure is found

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.

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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.

Group 1:

Task Number of Persons Task Hours Elapsed Hours

Open access 1 0.50 0.50

Inspect/Repair (Left 1 2.00 2.00

Side)

FIGURE 1

Inspect/Repair (Right 1 0.30 0.30

Side)

FIGURE 3

Remove & Replace 1 0.40 0.40

clamp/Install grommet (Left Side)

FIGURE 2

Remove & Replace 1 0.50 0.50

clamp/Install grommet (Right Side)

FIGURE 4

Close access 1 .50 .50

TOTAL FOR EACH AIRPLANE 5.70 5.70

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Open access 1 0.50 0.50

Inspect/Repair (Left 1 2.00 2.00

Side)

FIGURE 5

Inspect/Repair (Right 1 2.00 2.00

Side)

FIGURE 7

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Group 2:

Task Number of Persons Task Hours Elapsed Hours

Remove & Replace 1 0.50 0.50

clamp/Install grommet (Left Side)

FIGURE 6

Remove & Replace 1 0.35 0.35

clamp/Install grommet (Right Side)

FIGURE 8

Close access 1 .50 .50

TOTAL FOR EACH AIRPLANE 5.85 5.85

H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

Group 1 and 2 +0.1 +317.76

I. Electrical Load Data

Not applicable.

J. References

1. Existing Data:

a. Boeing Service Letter 747-SL-747-51-48

b. Service Related Problem (SRP) 747-SRP-24-0142

c. Service Bulletin Index D6-30300

d. Standard Overhaul Practices Manual (SOPM) 20-50-09

e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-13, 20-10-19

f. 747-400 Aircraft Maintenance Manual (AMM) 24-22-00, 52-49-00

g. 747-400 Structural Repair Manual (SRM) 51-10-02, 51-20-01, 51-20-02, 51-20-03, 51-70-11,

51-70-12, 51-70-13, 53-80-07

h. Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM

2012-NM-166-AD

2. Data Supplied with this Service Bulletin:

None.

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BOEING SERVICE BULLETIN 747-24A2360
3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

WIRE BUNDLE INSTALLATION 48 SEC RH, LH BULKHEAD STA

2598-2658

288U4806

WIRE PROVISIONS INSTL - SECT 48 FRAMES STA 2598 TO

2777

287U4804

The table above lists applicable drawings used to prepare this service bulletin. The drawings are

not necessary to make the specified changes, and are not supplied with this service bulletin. The

drawings may not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

747 Illustrated Parts Catalog 53-13, 53-44

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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2. MATERIAL INFORMATION

A. Material - Price and Availability

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

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

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

Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

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

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the Original Issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

Original Issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

TOP KIT - APU GEN- 5/31/2012 15 385 61.00

ERATOR POWER

FEEDER CLAMPS

015U1924-1

TOP KIT - APU GEN- 6/28/2012 5 385 61.00

ERATOR POWER

FEEDER CLAMPS

015U1924-1

TOP KIT - APU GEN- 7/27/2012 5 385 61.00

ERATOR POWER

FEEDER CLAMPS

015U1924-1

TOP KIT - APU GEN- 5/31/2012 25 385 71.00

ERATOR POWER

FEEDER CLAMPS

015U1924-2

B. Industry Support Information

Boeing warranty remedies are available for 747 airplanes in warranty as of July 13, 2011. For inspection

labor task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing

Warranty & Product Assurance Contracts. If the condition described in this service bulletin is found

during the inspection for airplanes in warranty as of that date and additional task hours are required,

send a warranty claim to Boeing Warranty & Product Assurance Contracts. Please refer to this service

bulletin number and reference the airplane number in your purchase order.

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.

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NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for

each installation figure shown in the table below.

Figure Kit

Top Kit 2 4 6 8

015U1924-1 1 1 - -

015U1924-2 - - 1 1

Group 1:

KIT 015U1924-1

Notes

Existing Part

Name Number

Figure

New Part Number

2 4

Qty

BACG20Z- 1 . GROMMET (b)

P001900B

BACG20Z- 1 . GROMMET (b)

Q001900B

BACN10YR3CD 1 1 NUT

BACS12HN3-12 1 . BOLT (a)

BACS12HN3-22 . 1 Screw (a)

BACW10P391AA 1 . WASHER, PLAIN (a)

BACW10P411CG 1 2 WASHER, FLAT (a)

SPACERS FOR

BOLTS

NAS43DD3-15FC 1 .

SPACERS FOR

BOLTS

NAS43DD3-24FC . 2

TA025097L16 1 2 CLAMP

(a) If grip length shown is not available at Boeing, fasteners supplied in kits may

be one grip length longer than indicated. Also, if any fasteners part numbers

listed are not available or have been superseded, substitute fasteners may be

supplied in kits.

(b) Kit part number is bulk coil of grommet material.

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Group 2:

KIT 015U1924-2

Notes

Existing Part

Name Number

Figure

New Part Number

6 8

Qty

BACG20Z- . 1 GROMMET (b)

N001900B

BACG20Z- 1 . GROMMET (b)

P001900B

BACG20Z- 1 . GROMMET (b)

Q001900B

BACN10YR3CD 2 1 NUT

BACS12HN3-10 . 1 BOLT (a)

BACS12HN3-12 2 . BOLT (a)

BACW10P391AA 2 . WASHER, PLAIN (a)

BACW10P411CG 2 . WASHER, FLAT (a)

NAS1149D0332J . 1 WASHER (a)

SPACERS FOR

BOLTS

NAS43DD3-15FC 2 .

SPACERS FOR

BOLTS

NAS43DD3-4FC . 1

TA025097L16 2 2 CLAMP

(a) If grip length shown is not available at Boeing, fasteners supplied in kits may

be one grip length longer than indicated. Also, if any fasteners part numbers

listed are not available or have been superseded, substitute fasteners may be

supplied in kits.

(b) Kit part number is bulk coil of grommet material.

2. Parts and Materials Supplied by the Operator

None.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

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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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3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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

– 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. 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.

8. 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.

9. Boeing Service Letter 747-SL-51-048, Damage Reporting and Repair Plan/Design

Guidelines, is an acceptable procedure to request information from Boeing for

additional structural repair instructions. The Service Letter describes what information

must be provided to Boeing before a structural repair can be provided.

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.

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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. Shaded areas in Figures are to separate the non-critical and non-authoritative

information from the critical and authoritative information.

14. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS

are in Paragraph 1.E., Compliance.

B. WORK INSTRUCTIONS

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

procedure.

2. Open the Auxiliary Power Unit (APU) battery access door. Refer to 747-400 AMM 52-49-00 as an

accepted procedure.

3. Group 1:

Do a detailed inspection of certain APU power feeder cables within each wire bundle for damage

on the left of the bulkhead in accordance with FIGURE 1.

Do a detailed inspection of certain APU power feeder cables within each wire bundle for damage

on the right side of the bulkhead in accordance with FIGURE 3.

a. If the power feeder cables do not have damage, then replace the clamp(s) and install the

grommets in accordance with steps 3.c through 3.f.

b. If a cable has damage:

(1) Do a detailed inspection of the adjacent structure for damage. Inspect for surface finish

integrity, excessive wear, and possible heat damage. Refer to 747-400 SRM 53-80-07

frame identification and allowable damage limits.

(a) If the structure has damage:

1) Repair any damage in accordance with the 747-400 SRM listed below before

further flight, or contact Boeing with damage findings for repair instructions and

do the repairs.

– 747-400 SRM 51-10-02 for inspection and damage removal procedures.

– 747-400 SRM 51-20-03 for heat damage evaluation.

– 747-400 SRM 51-20-02 for heat treatment verification.

– 747-SL-747-51-48 for damage reporting instructions.

– 747-400 SRM 51-70-11 for typical repair of formed sections.

– 747-400 SRM 51-70-12 for typical repair of extruded sections.

– 747-400 SRM 51-70-13 for typical repair of webs.

– 747-400 SRM 51-20-01 for restoring surface finish.

(b) If the structure has no damage: No further action is required.

(2) Repair the cable. Refer to SWPM 20-10-13 as an accepted procedure.

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c. Remove and replace the clamp(s) on power feeder cable W866 or W944 on the left side of

STA 2638, between the bulkhead and the APU firewall in accordance with FIGURE 2.

d. Install the grommets on the left side of frame APU bulkhead at STA 2638 in accordance with

FIGURE 2

e. Remove and replace the clamp(s) on power feeder cables W4610 and W868 or W946 on the

right side of STA 2638, between the bulkhead and the APU firewall in accordance with FIGURE

4.

f. Install the grommets on the right side of frame APU bulkhead at STA 2638 in accordance with

FIGURE 4.

4. Group 2:

Do a detailed inspection of certain APU power feeder cables within each wire bundle for damage

on the left side of the bulkhead in accordance with FIGURE 5.

Do a detailed inspection of certain APU power feeder cables within each wire bundle for damage

on the right side of the bulkhead in accordance with FIGURE 7.

a. If the power feeder cables do not have damage, then replace the clamp(s) and install the

grommets in accordance with steps 4.c through 4.f.

b. If a cable has damage:

(1) Do a detailed inspection of the adjacent structure for damage. Inspect for surface finish

integrity, excessive wear, and possible heat damage. Refer to 747-400 SRM 53-80-07

frame identification and allowable damage limits.

(a) If the structure has damage:

1) Repair any damage in accordance with the 747-400 SRM listed below before

further flight, or contact Boeing with damage findings for repair instructions and

do the repair.

– 747-400 SRM 51-10-02 for inspection and damage removal procedures.

– 747-400 SRM 51-20-03 for heat damage evaluation.

– 747-400 SRM 51-20-02 for heat treatment verification.

– 747-SL-747-51-48 for damage reporting instructions.

– 747-400 SRM 51-70-11 for typical repair of formed sections.

– 747-400 SRM 51-70-12 for typical repair of extruded sections.

– 747-400 SRM 51-70-13 for typical repair of webs.

– 747-400 SRM 51-20-01 for restoring surface finish.

(b) If the structure has no damage: No further action is required.

(2) Repair the cable. Refer to SWPM 20-10-13 as an accepted procedure.

c. Remove and replace the clamp(s) on power feeder cable W944 on the left side of STA 2638,

between the bulkhead and the APU firewall in accordance with FIGURE 6.

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d. Install the grommets on the left side of frame APU bulkhead at STA 2638 in accordance with

FIGURE 6

e. Remove and replace the clamp(s) on power feeder cables W4610 and W946 on the right side

of STA 2638, between the bulkhead and the APU firewall in accordance with FIGURE 8.

f. Install the grommets on the right side of frame APU bulkhead at STA 2638 in accordance with

FIGURE 8

5. Restore electrical power back to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted

procedure.

6. Close access. Refer to 747-400 AMM 52-49-00 as an accepted procedure.

7. Put airplane into a serviceable condition.

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This Figure applies only to: Group 1.

FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD

STA 2638

(SHEET 1 OF 3)

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FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD

STA 2638

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-24A2360
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

Step Task Name Identification Qty More Data

Do a detailed inspection. Refer to SWPM 20-10-13 as an

accepted procedure.

1 Inspect Wire Bundle - 1

Do a detailed inspection.2 Inspect Structure - -

FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD

STA 2638

(SHEET 3 OF 3)

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This Figure applies only to: Group 1.

FIGURE 2: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638

(SHEET 1 OF 3)

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FIGURE 2: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-24A2360
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

Step Task Name Identification Qty More Data

1 Remove Clamp - 1

Remove Screw - 1

Remove Washer - 2

Remove Nut - 1

2 Install (New) CLAMP TA025097L16 1

Install (New) BOLT BACS12HN3-12 1

SPACERS FOR NAS43DD3-15FC 1

BOLTS

Install (New)

Install washer between the bracket

and spacer

Install (New) WASHER, FLAT BACW10P411CG 1

Install (New) NUT BACN10YR3CD 1

Install washer between the bolt head

and bracket

Install (New) WASHER, PLAIN BACW10P391AA 1

Refer to SOPM 20-

50-09 as an accepted procedure. (a)

3 Install (New) GROMMET BACG20Z-Q001900B 1

Refer to SOPM 20-

50-09 as an accepted procedure. (a)

4 Install (New) GROMMET BACG20Z-P001900B 1

(a) Cut the length of the grommet to fit the location. Keep the remainder of the length of the grommet for

other use. Trim as required.

FIGURE 2: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638

(SHEET 3 OF 3)

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This Figure applies only to: Group 1.

FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD

STA 2638

(SHEET 1 OF 3)

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FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD

STA 2638

(SHEET 2 OF 3)

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

Step Task Name Identification Qty More Data

Do a detailed inspection. Refer to SWPM 20-10-13 as an

accepted procedure.

1 Inspect Wire Bundle - 1

Do a detailed inspection.2 Inspect Structure - -

FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD

STA 2638

(SHEET 3 OF 3)

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This Figure applies only to: Group 1.

FIGURE 4: CLAMP REPLACEMENT AND GROMMET INSTALLATION - RIGHT BULKHEAD STA 2638

(SHEET 1 OF 3)

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FIGURE 4: CLAMP REPLACEMENT AND GROMMET INSTALLATION - RIGHT BULKHEAD STA 2638

(SHEET 2 OF 3)

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39 of 52

BOEING SERVICE BULLETIN 747-24A2360
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

Step Task Name Identification Qty More Data

1 Remove Clamp - 2

Remove Screw - 1

Remove Washer - 2

Remove Nut - 1

2 Install (New) CLAMP TA025097L16 2

Install (New) Screw BACS12HN3-22 1

Install washer between the bracket

and spacer.

Install (New) WASHER, FLAT BACW10P411CG 2

SPACERS FOR NAS43DD3-24FC 2

BOLTS

Install (New)

Install (New) NUT BACN10YR3CD 1

Refer to SOPM 20-

50-09 as an accepted procedure. (a)

3 Install (New) GROMMET BACG20Z-Q001900B -

Refer to SOPM 20-

50-09 as an accepted procedure. (a)

4 Install (New) GROMMET BACG20Z-P001900B -

(a) Use the remainder of the length of the grommet in the kit. Cut the length of the grommet to fit location.

Trim as required.

FIGURE 4: CLAMP REPLACEMENT AND GROMMET INSTALLATION - RIGHT BULKHEAD STA 2638

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

40 of 52

BOEING SERVICE BULLETIN 747-24A2360
This Figure applies only to: Group 2.

FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD

STA 2638

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

41 of 52

BOEING SERVICE BULLETIN 747-24A2360
FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD

STA 2638

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

42 of 52

BOEING SERVICE BULLETIN 747-24A2360
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

Step Task Name Identification Qty More Data

Do a detailed inspection. Refer to SWPM 20-10-13 as an

accepted procedure.

1 Inspect Wire Bundle - 1

Do a detailed inspection.2 Inspect Structure - -

FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD

STA 2638

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

43 of 52

BOEING SERVICE BULLETIN 747-24A2360
This Figure applies only to: Group 2.

FIGURE 6: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

44 of 52

BOEING SERVICE BULLETIN 747-24A2360
FIGURE 6: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

45 of 52

BOEING SERVICE BULLETIN 747-24A2360
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

Step Task Name Identification Qty More Data

1 Remove Clamp - 2 (b)

Remove Screw - 2

Remove Washer - 4

Remove Nut - 2

2 Install (New) CLAMP TA025097L16 2

Install (New) BOLT BACS12HN3-12 2

SPACERS FOR NAS43DD3-15FC 2

BOLTS

Install (New)

Install washer between the bolt head

and bracket.

Install (New) WASHER, PLAIN BACW10P391AA 2

Install (New) NUT BACN10YR3CD 2

Install washer between the bracket

and spacer.

Install (New) WASHER, FLAT BACW10P411CG 2

Refer to SOPM 20-

50-09 as an accepted procedure.

3 Install (New) GROMMET BACG20Z-P001900B 1

Refer to SOPM 20-

50-09 as an accepted procedure. (a)

4 Install (New) GROMMET BACG20Z-Q001900B 1

(a) Cut the length of the grommet to fit the location. Keep the remainder of the length of the grommet for

other use. Trim as required.

(b) Some configurations may require the removal of 1 clamp and mounting hardware. Two clamp configuration

shown.

FIGURE 6: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

46 of 52

BOEING SERVICE BULLETIN 747-24A2360
This Figure applies only to: Group 2.

FIGURE 7: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD

STA 2638

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

47 of 52

BOEING SERVICE BULLETIN 747-24A2360
FIGURE 7: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD

STA 2638

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

48 of 52

BOEING SERVICE BULLETIN 747-24A2360
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

Step Task Name Identification Qty More Data

Do a detailed inspection. Refer to SWPM 20-10-13 as an

accepted procedure.

1 Inspect Wire Bundle - 1

Do a detailed inspection.2 Inspect Structure - -

FIGURE 7: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD

STA 2638

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

49 of 52

BOEING SERVICE BULLETIN 747-24A2360
This Figure applies only to: Group 2.

FIGURE 8: GROMMET INSTALLATION AND CLAMP REPLACEMENT - RIGHT BULKHEAD STA 2638

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

50 of 52

BOEING SERVICE BULLETIN 747-24A2360
FIGURE 8: GROMMET INSTALLATION AND CLAMP REPLACEMENT - RIGHT BULKHEAD STA 2638

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

51 of 52

BOEING SERVICE BULLETIN 747-24A2360
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

Step Task Name Identification Qty More Data

1 Remove Clamp - 2

Remove Screw - 1

Remove Washer - 2

Remove Nut - 1

2 Install (New) CLAMP TA025097L16 2

Install (New) BOLT BACS12HN3-10 1

SPACERS FOR NAS43DD3-4FC 1

BOLTS

Install (New)

Install (New) WASHER NAS1149D0332J 1

Install (New) NUT BACN10YR3CD 1

Refer to SOPM 20-

50-09 as an accepted procedure. (a)

3 Install (New) GROMMET BACG20Z-Q001900B -

Refer to SOPM 20-

50-09 as an accepted procedure.

4 Install (New) GROMMET BACG20Z-N001900B 1

(a) Use the remainder of the length of the grommet in the kit. Cut the length of the grommet to fit location.

Trim as required.

FIGURE 8: GROMMET INSTALLATION AND CLAMP REPLACEMENT - RIGHT BULKHEAD STA 2638

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: January 18, 2012

Revision 2 October 02, 2013 747-24A2360

52 of 52

BOEING SERVICE BULLETIN 747-24A2360