# Boeing Alert Service Bulletin 747-24A2360: U.S. DOT/FAA - Service Information

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- Title as filed: U.S. DOT/FAA - Service Information
- Pages: 50
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## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-24A2360
Original Issue: January 18, 2012
Revision 1: May 02, 2012
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.
9E991ECCN:
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Unpublished Work.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.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner™,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing
liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection
with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management
Company.
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 4
B. Concurrent Requirements ...................................... 1 4
C. Reason ................................................ 1 5
D. Description .............................................. 1 5
E. Compliance .............................................. 1 5
F. Approval ............................................... 1 6
G. Manpower .............................................. 1 6
H. Weight and Balance Changes .................................... 1 7
I. Electrical Load Data ......................................... 1 7
J. References .............................................. 1 7
1. Existing Data: ......................................... 1 7
2. Data Supplied with this Service Bulletin: ........................... 1 8
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 8
K. Publications Affected ........................................ 1 8
L. Interchangeability and Intermixability of Parts ........................... 1 8
M. Software Accomplishment Summary ................................ 1 8
2. MATERIAL INFORMATION ........................................ 1 9
A. Material - Price and Availability ................................... 1 9
B. Industry Support Information .................................... 1 9
C. Parts Necessary for Each Airplane ................................. 1 9
1. Kits/Parts ............................................ 1 9
2. Parts and Materials Supplied by the Operator ........................ 2 1
3. Parts Modified and Reidentified ................................ 2 1
4. Parts Removed and Not Replaced .............................. 2 1
D. Parts Necessary to Change Spares ................................. 2 1
E. Special Tooling - Price and Availability ............................... 2 2
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 2
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 3
A. GENERAL INFORMATION ..................................... 2 3
B. WORK INSTRUCTIONS ....................................... 2 4
FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT
BULKHEAD STA 2638 [Group 1] ............................... 2 7
FIGURE 2: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638
[Group 1] ............................................ 3 0
FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT
BULKHEAD STA 2638 [Group 1] ............................... 3 3
FIGURE 4: CLAMP REPLACEMENT AND GROMMET INSTALLATION - RIGHT BULKHEAD STA 2638
[Group 1] ............................................ 3 6
FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT
BULKHEAD STA 2638 [Group 2] ............................... 3 9
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FIGURE 6: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638
[Group 2] ............................................ 4 2
FIGURE 7: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT
BULKHEAD STA 2638 [Group 2] ............................... 4 5
FIGURE 8: GROMMET INSTALLATION AND CLAMP REPLACEMENT - RIGHT BULKHEAD STA 2638
[Group 2] ............................................ 4 8
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 747-24A2360Original Issue: January 18, 2012
Revision 1: May 02, 2012
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
No more work is necessary on the airplane(s) changed in accordance with the original issue of this service
bulletin.
Airplanes were deleted to the service bulletin effectivities.
REASON FOR REVISION
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.
Airplanes deleted from Group 1:
RT041-RT042, RT074, RT531-RT535, RT641, RT643-RT653, RT711-RT717, RT861-RT864, RU002-RU003,
RU803, RU805, RU831 and RU833-RU839.
Airplanes deleted from Group 2:
RM001-RM009, RT756-RT757, RU004-RU006, RU122-RU125 and RU840-RU841.
This revision also corrects and changes the following information:
Updated 1.A Planning Information - Effectivity, to delete effectivities
Updated 1.C Planning Information - Reason, updated to add reason for service bulletin revision.
Updated 1.D Planning Information - Description, updated to add additional description.
Updated 1.E Planning Information - Compliance Time, updated to add new compliance time.
Updated 2.C Material Information - Updated to include new parts in kits and added footnotes.
Update 3.A Accomplishment Instruction - Updated to include additional general information.
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Update 3.B Accomplishment Instruction - updated to revise work instructions.
Figure 2, 4, 6 - Updated to add new parts numbers and notes.
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
January 18, 2012Original Issue:
May 02, 2012Revision 1:
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-24A2360Original Issue: January 18, 2012
Revision 1: May 02, 2012
ATA System: 2421
SUBJECT: ELECTRICAL POWER - 115 Volt AC Power Generation and Protection - APU Power
Feeder Cable Inspection and Clamp Change
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
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.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
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ReferenceAffectedPlanning Data
Paragraph 1.E., ComplianceYesAD Related
Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Get access to the in the area just forward of the APU bulkhead STA 2638. Do a detailed visual 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 visual 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
Boeing recommends that the inspection, change and/or repair given in this service bulletin be done within 14
months after the Revision 1 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
Elapsed HoursTotal Task HoursAirplanes
5.705.70Group 1 airplanes
5.855.85Group 2 airplanes
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
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BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
Refer to Paragraph 2.A., Material - Price and Availability.
STA
2638
STA
2658
STA
2638
STA
2618
STA
APU  2598
FIREWALL
LEFT SIDE
DIAGONAL BRACE
- INSPECT POWER
FEEDER CABLE
- INSPECT ADJACENT
STRUCTURE
- REPAIR DAMAGED
POWER FEEDER
CLAMPS
- INSTALL GROMMETS
W866
OR
W944
RIGHT SIDE
DIAGONAL BRACE
- INSPECT POWER
FEEDER CABLE
- INSPECT ADJACENT
STRUCTURE
- REPAIR DAMAGED
POWER FEEDER  • BULKHEAD
CLAMPS
- INSTALL GROMMETS
W868  2124415
OR
W946
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-24A2360
Original Issue: January 18, 2012
Revision 1: May 02, 2012
ATA System: 2421
SUBJECT: ELECTRICAL POWER - 115 Volt AC Power Generation and Protection - APU Power
Feeder Cable Inspection and Clamp Change
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
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.
DESCRIPTIONCONFIGURATIONGROUP
747-400 Airplanes with a certain clamp configuration-1
747-400 Airplanes with a certain clamp configuration-2
Airplane Models:
747-400
GroupVariable Number
2RF001 - RF006
2RM010 - RM013
2RM021 - RM024
2RM026 - RM030
2RM036 - RM045
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GroupVariable Number
2RM051 - RM053
2RM071
2RM081 - RM084
2RM091
2RM096 - RM097
2RM116 - RM117
2RM136 - RM147
2RM156 - RM158
2RM166 - RM177
2RM191 - RM192
2RM231 - RM233
2RM241 - RM246
2RM261 - RM264
2RM331 - RM333
2RM341
2RM351 - RM355
2RM366 - RM367
2RM401 - RM403
2RM426
2RM431
2RM441 - RM443
2RM445
2RM801 - RM803
1RT001 - RT011
2RT012 - RT014
1RT043 - RT047
1RT073
1RT101 - RT103
1RT121
1RT131 - RT134
2RT135 - RT137
2RT151 - RT152
1RT162 - RT163
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GroupVariable Number
2RT165 - RT168
1RT401 - RT412
1RT431 - RT441
2RT442 - RT447
1RT452 - RT455
1RT457 - RT460
1RT462 - RT467
2RT468 - RT469
1RT471 - RT498
2RT499
1RT502 - RT505
1RT511 - RT512
1RT514 - RT515
1RT517
1RT521 - RT523
2RT525
2RT527
2RT529
1RT551 - RT568
1RT571
1RT580 - RT583
2RT584 - RT588
2RT590
1RT591
1RT601 - RT614
1RT616 - RT622
2RT623 - RT630
1RT633 - RT634
2RT636 - RT640
1RT672 - RT673
1RT693 - RT697
2RT698 - RT699
1RT701 - RT704
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GroupVariable Number
1RT741
1RT744 - RT748
2RT749 - RT750
1RT753 - RT755
1RT783 - RT784
2RT801 - RT803
2RT811 - RT814
2RT831 - RT835
1RT931 - RT932
2RT945 - RT949
1RT951 - RT954
2RT955
2RU016 - RU017
1RU031
2RU032
1RU051 - RU052
2RU059 - RU060
1RU061
2RU062
2RU081 - RU083
2RU101 - RU102
2RU121
2RU126 - RU132
2. Spares Affected
None.
B. Concurrent Requirements
None.
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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.
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.
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 visual 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 visual 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.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
315, 316747-400
E. Compliance
Boeing recommends that the inspection, change and/or repair given in this service bulletin be done
within 14 months after the Revision 1 date of this service bulletin.
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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.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open access
2.002.001Inspect/Repair (Left
Side)
FIGURE 1
0.300.301Inspect/Repair (Right
Side)
FIGURE 3
0.400.401Remove & Replace
clamp/Install grom-
met (Left Side)
FIGURE 2
0.500.501Remove & Replace
clamp/Install grom-
met (Right Side)
FIGURE 4
.50.501Close access
5.705.70TOTAL FOR EACH AIRPLANE
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Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open access
2.002.001Inspect/Repair (Left
Side)
FIGURE 5
2.002.001Inspect/Repair (Right
Side)
FIGURE 7
0.500.501Remove & Replace
clamp/Install grom-
met (Left Side)
FIGURE 6
0.350.351Remove & Replace
clamp/Install grom-
met (Right Side)
FIGURE 8
.50.501Close access
5.855.85TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+317.76+0.1Group 1 and 2
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
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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
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
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:
Chapter-SectionPublication
53-13747 Illustrated Parts Catalog
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
M. Software Accomplishment Summary
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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 Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
61.00385155/31/2012TOP KIT - APU GEN-
ERATOR POWER
FEEDER CLAMPS
015U1924-1
61.0038556/28/2012TOP KIT - APU GEN-
ERATOR POWER
FEEDER CLAMPS
015U1924-1
61.0038557/27/2012TOP KIT - APU GEN-
ERATOR POWER
FEEDER CLAMPS
015U1924-1
71.00385255/31/2012TOP KIT - APU GEN-
ERATOR POWER
FEEDER CLAMPS
015U1924-2
B. 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.
C. Parts Necessary for Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for
each installation figure shown in the table below.
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### Page 20

Figure Kit
8642Top Kit
--11015U1924-1
11--015U1924-2
Group 1:
KIT 015U1924-1
Notes
Existing Part
NumberName
Figure
New Part Number
42
Qty
(b)GROMMET.1BACG20Z-
P001900B
(b)GROMMET.1BACG20Z-
Q001900B
NUT11BACN10YR3CD
(a)BOLT.1BACS12HN3-12
(a)Screw1.BACS12HN3-22
(a)WASHER, PLAIN.1BACW10P391AA
(a)WASHER, FLAT21BACW10P411CG
SPACERS FOR
BOLTS
.1NAS43DD3-15FC
SPACERS FOR
BOLTS
2.NAS43DD3-24FC
CLAMP21TA025097L16
(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.
Group 2:
KIT 015U1924-2
Notes
Existing Part
NumberName
Figure
New Part Number
86
Qty
(b)GROMMET1.BACG20Z-
N001900B
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### Page 21

Group 2:
KIT 015U1924-2
Notes
Existing Part
NumberName
Figure
New Part Number
86
Qty
(b)GROMMET.1BACG20Z-
P001900B
(b)GROMMET.1BACG20Z-
Q001900B
NUT12BACN10YR3CD
(a)BOLT1.BACS12HN3-10
(a)BOLT.2BACS12HN3-12
(a)WASHER, PLAIN.2BACW10P391AA
(a)WASHER, FLAT.2BACW10P411CG
(a)WASHER1.NAS1149D0332J
SPACERS FOR
BOLTS
.2NAS43DD3-15FC
SPACERS FOR
BOLTS
1.NAS43DD3-4FC
CLAMP22TA025097L16
(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.
D. Parts Necessary to Change Spares
None.
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### Page 22

E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 23

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
4. 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.
5. 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.
6. 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.
7. 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.
8. 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.
9. 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.
10. 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.
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### Page 24

11. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51.
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 visual inspection of certain APU power feeder cables within each wire bundle on the
left of the bulkhead in accordance with FIGURE 1.
Do a detailed visual inspection of certain APU power feeder cables within each wire bundle 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 FIGURE 2 and FIGURE 4 .
b. If a cable has damage:
(1) Do a detailed visual 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 prior to
further flight, or contact Boeing with damage findings, for repair instructions.
– 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.
(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 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
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### Page 25

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 visual inspection of certain APU power feeder cables within each wire bundle on the
left side of the bulkhead in accordance with FIGURE 5.
Do a detailed visual inspection of certain APU power feeder cables within each wire bundle 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 FIGURE 6 and FIGURE 8 .
b. If a cable has damage:
(1) Do a detailed visual 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 prior to
further flight, or contact Boeing with damage findings, for repair instructions.
– 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.
(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.
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
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### Page 26

5. Restore electrical power back to the airplane. Refer to747-400 AMM 24-22-00 as an accepted
procedure.
6. Close access and return airplane to a serviceable condition.
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
This Figure applies only to: Group 1.
STA
2638
W866
OR
W944
W866
OR
W944
STA
2658
STA  2136704
2638
FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD
STA 2638
(SHEET 1 OF 3)
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### Page 28 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
W866
OR
W944
FWD
WIRE BUNDLES NOT SHOWN
FWD  2136716
FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD
STA 2638
(SHEET 2 OF 3)
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### Page 29

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
Do a detailed visual
inspection. Refer to
SWPM 20-10-13 as
an accepted proce-
dure.
1-Wire BundleInspect1
Do a detailed visual
inspection.
--StructureInspect2
FIGURE 1: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD
STA 2638
(SHEET 3 OF 3)
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ALERTALERT

### Page 30 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
This Figure applies only to: Group 1.
STA
2638
W866
OR
W944
STA
2658
STA  2136730
2638
FIGURE 2: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638
(SHEET 1 OF 3)
Original Issue: January 18, 2012
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Work - See page 1 for details.

### Page 31 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
LEFT SIDE
DIAGONAL
BRACE
NUT  • SPACER
BOLT
WASHER
CLAMP —→
A-A
LEFT SIDE
DIAGONAL  1.37
BRACE  0.37
WIRE BUNDLES NOT SHOWN
FWD  2136731
FIGURE 2: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638
(SHEET 2 OF 3)
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### Page 32

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
1-ClampRemove1
1-ScrewRemove
2-WasherRemove
1-NutRemove
1TA025097L16CLAMPInstall (New)2
1BACS12HN3-12BOLTInstall (New)
1NAS43DD3-15FCSPACERS FOR
BOLTS
Install (New)
Install washer be-
tween the bracket
and spacer
1BACW10P411CGWASHER, FLATInstall (New)
1BACN10YR3CDNUTInstall (New)
Install washer be-
tween the bolt head
and bracket
1BACW10P391AAWASHER, PLAINInstall (New)
Refer to  SOPM 20-
50-09 as an accept-
ed procedure. (a)
1BACG20Z-Q001900BGROMMETInstall (New)3
Refer to  SOPM 20-
50-09 as an accept-
ed procedure. (a)
1BACG20Z-P001900BGROMMETInstall (New)4
(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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ALERTALERT

### Page 33 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
This Figure applies only to: Group 1.
STA
2638
W4610
W868
OR
W946
STA
2658
STA  2136732
2638
FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD
STA 2638
(SHEET 1 OF 3)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
W868
OR
W946
FWD
WIRE BUNDLES NOT SHOWN
FWD  2136733
FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD
STA 2638
(SHEET 2 OF 3)
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### Page 35

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
Do a detailed visual
inspection. Refer to
SWPM 20-10-13 as
an accepted proce-
dure.
1-Wire BundleInspect1
Do a detailed visual
inspection.
--StructureInspect2
FIGURE 3: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD
STA 2638
(SHEET 3 OF 3)
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ALERTALERT

### Page 36 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
This Figure applies only to: Group 1.
STA
2638
W4610
W868
OR
W946
STA
2658
STA  2136750
2638
FIGURE 4: CLAMP REPLACEMENT AND GROMMET INSTALLATION - RIGHT BULKHEAD STA 2638
(SHEET 1 OF 3)
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 747-24A2360C
ALERT  ALERT
RIGHT SIDE
DIAGONAL BRACE
WASHER  SPACER
SPACER
- NUT
BOLT -
W4610 ~  — W868
OR
12-  W946
CLAMP •
CLAMP
A-A
•1.60
0.60
WIRE BUNDLES NOT SHOWN
FWD  2136752
FIGURE 4: CLAMP REPLACEMENT AND GROMMET INSTALLATION - RIGHT BULKHEAD STA 2638
(SHEET 2 OF 3)
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### Page 38

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
2-ClampRemove1
1-ScrewRemove
2-WasherRemove
1-NutRemove
2TA025097L16CLAMPInstall (New)2
1BACS12HN3-22ScrewInstall (New)
Install washer be-
tween the bracket
and spacer.
2BACW10P411CGWASHER, FLATInstall (New)
2NAS43DD3-24FCSPACERS FOR
BOLTS
Install (New)
1BACN10YR3CDNUTInstall (New)
Refer to  SOPM 20-
50-09 as an accept-
ed procedure. (a)
-BACG20Z-Q001900BGROMMETInstall (New)3
Refer to  SOPM 20-
50-09 as an accept-
ed procedure. (a)
-BACG20Z-P001900BGROMMETInstall (New)4
(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)
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ALERTALERT

### Page 39 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
This Figure applies only to: Group 2.
STA
2638
W944
STA
2658
2638  STA  2136754
FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD
STA 2638
(SHEET 1 OF 3)
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### Page 40 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
‚W944
WIRE BUNDLES NOT SHOWN
B  FWD  2136755
FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD
STA 2638
(SHEET 2 OF 3)
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### Page 41

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure..
More DataQtyIdentificationNameTaskStep
Do a detailed visual
inspection. Refer to
SWPM 20-10-13 as
an accepted proce-
dure.
1-Wire BundleInspect1
Do a detailed visual
inspection.
--StructureInspect2
FIGURE 5: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - LEFT BULKHEAD
STA 2638
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 747-24A2360
ALERTALERT

### Page 42 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
This Figure applies only to: Group 2.
STA
2638
W944
STA
2658
2638  STA  2136756
FIGURE 6: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638
(SHEET 1 OF 3)
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### Page 43 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
‚W944
FWD
- W944
BOLT
• CLAMP
1(2)
NUT
SPACER
WASHER
A-A
_1.37
2.90  -0.37
1.90  WIRE BUNDLES NOT SHOWN
FWD  2136758
FIGURE 6: CLAMP REPLACEMENT AND GROMMET INSTALLATION - LEFT BULKHEAD STA 2638
(SHEET 2 OF 3)
Original Issue: January 18, 2012
Revision 1 May 02, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-24A2360
Work - See page 1 for details.  43 of 50

### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
2-ClampRemove1
2-ScrewRemove
4-WasherRemove
2-NutRemove
2TA025097L16CLAMPInstall (New)2
2BACS12HN3-12BOLTInstall (New)
2NAS43DD3-15FCSPACERS FOR
BOLTS
Install (New)
Install washer be-
tween the bolt head
and bracket.
2BACW10P391AAWASHER, PLAINInstall (New)
2BACN10YR3CDNUTInstall (New)
Install washer be-
tween the bracket
and spacer.
2BACW10P411CGWASHER, FLATInstall (New)
Refer to  SOPM 20-
50-09 as an accept-
ed procedure.
1BACG20Z-P001900BGROMMETInstall (New)3
Refer to  SOPM 20-
50-09 as an accept-
ed procedure. (a)
1BACG20Z-Q001900BGROMMETInstall (New)4
(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 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
747-24A2360Revision 1 May 02, 2012
44 of 50
BOEING SERVICE BULLETIN 747-24A2360
ALERTALERT

### Page 45 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
This Figure applies only to: Group 2.
STA
2638
W4610 •
N946
STA
2658
STA  2136761
2638
FIGURE7: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD
STA 2638
(SHEET 1 OF 3)
Original Issue: January 18, 2012
Revision 1 May 02, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-24A2360
Work - See page 1 for details.  45 of 50

### Page 46 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
W4610
W946
FWD
WIRE BUNDLES NOT SHOWN  FWD
2136764
FIGURE 7: POWER FEEDER INSPECTION AND REPAIR - STRUCTURAL INSPECTION - RIGHT BULKHEAD
STA 2638
(SHEET 2 OF 3)
Original Issue: January 18, 2012
Revision 1 May 02, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-24A2360
Work - See page 1 for details.  46 of 50

### Page 47

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
Do a detailed visual
inspection. Refer to
SWPM 20-10-13 as
an accepted proce-
dure.
1-Wire BundleInspect1
Do a detailed visual
inspection.
--StructureInspect2
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
747-24A2360Revision 1 May 02, 2012
47 of 50
BOEING SERVICE BULLETIN 747-24A2360
ALERTALERT

### Page 48 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
This Figure applies only to: Group 2.
STA
2638
W4610
W946
STA
2658
STA  2136773
2638
FIGURE 8: GROMMET INSTALLATION AND CLAMP REPLACEMENT - RIGHT BULKHEAD STA 2638
(SHEET 1 OF 3)
Original Issue: January 18, 2012
Revision 1 May 02, 2012  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-24A2360
Work - See page 1 for details.  48 of 50

### Page 49 (OCR)

BOEING SERVICE BULLETIN 747-24A2360
ALERT  ALERT
W4610  A —
W946
CLAMP
SPACER
BOLT
NUT
WASHER
CLAMP
RIGHT SIDE
DIAGONAL
BRACE
A-A
FWD
2.5
WIRE BUNDLES NOT SHOWN  1.5  2136774
FIGURE 8: GROMMET INSTALLATION AND CLAMP REPLACEMENT - RIGHT BULKHEAD STA 2638
(SHEET 2 OF 3)
Original Issue: January 18, 2012
Revision 1 May 02, 2012  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-24A2360
Work - See page 1 for details.  49 of 50

### Page 50

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
2-ClampRemove1
1-ScrewRemove
2-WasherRemove
1-NutRemove
2TA025097L16CLAMPInstall (New)2
1BACS12HN3-10BOLTInstall (New)
1NAS43DD3-4FCSPACERS FOR
BOLTS
Install (New)
1NAS1149D0332JWASHERInstall (New)
1BACN10YR3CDNUTInstall (New)
Refer to  SOPM 20-
50-09 as an accept-
ed procedure. (a)
-BACG20Z-Q001900BGROMMETInstall (New)3
Refer to  SOPM 20-
50-09 as an accept-
ed procedure.
1BACG20Z-N001900BGROMMETInstall (New)4
(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
747-24A2360Revision 1 May 02, 2012
50 of 50
BOEING SERVICE BULLETIN 747-24A2360
ALERTALERT

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