# Boeing Alert Service Bulletin 747-25A3368: Revision 2

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Commercial        
Airplane
Group 
 747
Service Bulletin
Number: 747-25A3368
Date: August 25, 2005
Revision 2: June 12, 2008
ATA System: 2557
SUBJECT: EQUIPMENT/FURNISHINGS - Main Deck Cargo Systems - Electrical/Electronic Rack
Moisture Barrier Installation
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2005 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P .O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the Boeing livery are all trademarks
owned by The Boeing Company; and no trademark license is granted in connection with this document unless
provided in writing by Boeing.
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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 3
B. Concurrent Requirements ...................................... 1 4
C. Reason ................................................ 1 4
D. Description .............................................. 1 6
E. Compliance .............................................. 1 7
F . Approval ............................................... 1 7
G. Manpower .............................................. 1 7
H. Weight and Balance Changes .................................... 2 2
I. Electrical Load Data ......................................... 2 2
J. References .............................................. 2 2
1. Existing Data: .......................................... 2 2
2. Data supplied with this Service Bulletin: ........................... 2 2
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 2
K. Publications Affected ......................................... 2 3
L. Interchangeability and Intermixability of Parts ........................... 2 3
2. MATERIAL INFORMATION ........................................ 2 5
A. Material - Price and Availability ................................... 2 5
B. Industry Support Information .................................... 2 5
C. Parts Necessary For Each Airplane ................................. 2 5
1. Kits/Parts: ............................................ 2 5
2. Parts and Materials Supplied by the Operator: ........................ 2 9
3. Parts Modified and Reidentified: ................................ 3 0
4. Parts Removed and Not Replaced: .............................. 3 0
D. Parts Necessary to Change Spares ................................. 3 0
E. Special Tooling - Price and Availability ............................... 3 0
F . Special Tooling Necessary to do this Service Bulletin ....................... 3 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 1
A. GENERAL INFORMATION ..................................... 3 1
B. WORK INSTRUCTIONS ....................................... 3 1
FIGURE 1: RIGHT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - ALL GROUPS . . 35
FIGURE 2: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 3 .................................. 4 2
FIGURE 3: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 2 AND 4 .................................. 4 8
FIGURE 4: CENTER MOUTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 2 .................................. 5 5
FIGURE 5: CLOSEOUT INSTALLATION - GROUPS 1 AND 2, CONFIGURATION 1 AND 3 ...... 6 3
FIGURE 6: CLOSEOUT INSTALLATION - GROUPS 1 AND 2, CONFIGURATION 2 AND 4 ...... 7 0
FIGURE 7: MOISTURE CURTAIN INSTALLATION - GROUP 1 AIRPLANES .............. 7 7
FIGURE 8: MOISTURE CURTAIN INSTALLATIOIN - GROUP 2 AIRPLANES .............. 8 5
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FIGURE 9: CENTER MOUTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 3 AND 4 .................................. 9 1
FIGURE 10: FASTENER CAP SEALING - ALL GROUPS ......................... 9 6
FIGURE 11: RIGHT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION [Group 3] ...... 9 8
FIGURE 12: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION [Group 3] ...... 1 0 4
FIGURE 13: CENTER MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION [Group 3] .... 1 1 0
FIGURE 14: RUBBER CLOSEOUT INSTALLATION [Group 3] ...................... 1 1 5
APPENDIX A: FABRICATION OF SHIMS .................................. 1 1 8
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Commercial        
Airplane
Group 
 747
Service Bulletin
Revision Transmittal SheetNumber: 747-25A3368Date: August 25, 2005
Revision 2: June 12, 2008
ATA System: 2557
SUBJECT: EQUIPMENT/FURNISHINGS - Main Deck Cargo Systems - Electrical/Electronic Rack
Moisture Barrier Installation
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2007-NM-322-AD, is related to this
service bulletin.
No more work is necessary on airplanes changed as shown in the original issue and Revision 01 of this service
bulletin.
Airplanes RD646 and RD771 were added to Group 1of this service bulletin effectivity.
Airplanes RA101-RA103, RA112, RA161-RA163, RA784, RA910 were added to Group 2 of this service bulletin
effectivity.
REASON FOR REVISION
This revision is sent to add instructions to install the moisture curtains and rubber closeout on airplanes that
have already installed the large PDU drain pans.
These sections were changed:
1. In Effectivity, Section 1.A., moved airplanes RD301, RD302, RD411, RD412, RS721, RS722, RS762 from
Group 1, into new Group 3.
2. In Effectivity, Section 1.A., added airplanes RD646 and RD771 to Group 1.
3. In Effectivity, Section 1.A., added airplanes RA101-RA103, RA112, RA161-RA163, RA784, RA910 to Group
2.
4. In Compliance, Section 1.E., added NPRM 2007-NM-322-AD to compliance statement.
5. In Operator Supplied Parts, Section 2.C.2., added new table for Group 3 airplanes to include parts fabricated
in Appendix A
6. New Figure 11, Figure 12, Figure 13, Figure 14 have been added.
7. New Appendix A was added to include instructions to fabricate parts.
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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
August 25, 2005Original Issue:
June 25, 2007Revision 1:
June 12, 2008Revision 2:
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Commercial        
Airplane
Group 
 747
Service Bulletin
SummaryNumber: 747-25A3368Date: August 25, 2005
Revision 2: June 12, 2008
ATA System: 2557
SUBJECT: EQUIPMENT/FURNISHINGS - Main Deck Cargo Systems - Electrical/Electronic Rack
Moisture Barrier Installation
CONCURRENT REQUIREMENTS
None
BACKGROUND
This change will provide protection for the electrical/electronics units in main equipment center from water
contamination.
When loading cargo in rain or snow conditions, a large amount of water can come into the airplane on the cargo
or open main deck doors. The water can spill onto the main deck cargo floor and flow through the power drive
units (PDU's). If the amount of water exceeds the drain capacity of the PDU's above the main equipment center,
water can spill onto the electrical/electronic units. Water contamination of the electrical/electronic units may
cause the electrical/electronic units to malfunction.
Three 747 Special Freighter operators have reported water contamination in the electrical/electronic units in the
main equipment center. The water contamination resulted in malfunctions and replacement of multiple
electrical/electronic units in the main equipment center. One operator experienced an air turn back due to
malfunctions of electronic equipment in the main equipment center resulting in high pilot workload and minimal
cockpit indication.
This change provides a closeout panel and moisture curtains to protect the electrical/electronics units in the
main equipment center from water contamination.
Boeing Service Related Problem (SRP) 747-SRP-25-0228 is related to this service bulletin.
ACTION (PRR 85901-43RS)
Remove the units from the top row of the electrical/electronics rack. Install mounting plates and support angles.
Install closeout. Install moisture curtains. Install and test units on the top row of the electrical/electronics rack.
EFFECTIVITY
747 Special Freighter Airplanes. Refer to service bulletin Paragraph 1.A.1 for detailed effectivity.
COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2007-NM-322-AD, is related to this
service bulletin.
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Boeing recommends that operators do this service bulletin as soon as manpower, material and facilities are
available, not to exceed 24 months after the release date on this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of December 12, 2002. Please refer to
Paragraph 2.B., Industry Support Information.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
9.7018.63Group 1, Configuration 1
10.1619.55Group 1, Configuration 2
9.8618.95Group 1, Configuration 3
10.3219.87Group 1, Configuration 4
9.5818.39Group 2, Configuration 1
10.0419.31Group 2, Configuration 2
9.7418.71Group 2, Configuration 3
10.2019.63Group 2, Configuration 4
11.3721.98Group 3, Configuration 1
11.8322.90Group 3, Configuration 2
MATERIAL INFORMATION
Boeing Supplied Kits.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 747-25A3368
INSTALL MOISTURE BARRIER
SUPPORT STRUCTURE
INSTALL CLOSEOUT
REMOVE THE TOP  PANEL
SHELF COMPONENT
INSTALL MOISTURE BARRIER
ON THE E/E/RACKS
FUDD
MAIN EQUIPMENT CENTER  D71064
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Commercial        
Airplane
Group 
 747
Service Bulletin
Number: 747-25A3368
Date: August 25, 2005
Revision 2: June 12, 2008
ATA System: 2557
SUBJECT: EQUIPMENT/FURNISHINGS - Main Deck Cargo Systems - Electrical/Electronic Rack
Moisture Barrier Installation
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D6-30300 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below. Refer to PRR 85901-43RS for data about
this change.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes with a P73 Panel located forward of the existing water
shield
-1
Airplanes without a PDU 4L installed (29 pallet cargo system)1
Airplanes with a PDU 4L installed (30 pallet cargo system)2
Airplanes without a PDU 4L installed (29 pallet cargo system) and
have the extended shear web installed.
3
Airplanes with a PDU 4L installed (30 pallet cargo system) and have
the extended shear web installed.
4
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DESCRIPTIONCONFIGURATIONGROUP
Airplanes with a P73 Panel located aft of the existing water shield-2
Airplanes without a PDU 4L installed (29 pallet cargo system)1
Airplanes with a PDU 4L installed (30 pallet cargo system)2
Airplanes without a PDU 4L installed (29 pallet cargo system) and
have the extended shear web installed.
3
Airplanes with a PDU 4L installed (30 pallet cargo system) and have
the extended shear web installed.
4
Airplanes with a P73 Panel locate forward of the existing watershield
and have the large PDU drain pans installed.
-3
Airplanes without a PDU 4L installed (29 pallet cargo system)1
Airplanes with a PDU 4L installed (30 pallet cargo system)2
Airplane Models:
747-100, 747-200B, 747-300, 747SR
GroupVariable Number
2RA026
2RA029
2RA033
2RA101 - RA103
2RA112
2RA161 - RA163
2RA524
2RA632
2RA634 - RA635
2RA784
2RA901 - RA902
2RA910 - RA913
2RA915 - RA916
1RB604 - RB605
1RB607
1RB696
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GroupVariable Number
1RD041
1RD043 - RD044
1RD055
1RD082 - RD083
1RD142
1RD144
1RD225
1RD227
1RD233 - RD235
3RD301 - RD302
1RD358
1RD361 - RD366
3RD411 - RD412
1RD441 - RD442
1RD461
1RD581 - RD583
1RD601 - RD602
1RD622 - RD623
1RD641 - RD643
1RD646
1RD691
1RD752
1RD771
3RS721 - RS722
1RS741
1RS743
3RS762
1RS771
1RS786
2. Spares Affected
None.
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B. Concurrent Requirements
None
C. Reason
This change will provide protection for the electrical/electronics units in main equipment center from
water contamination.
When loading cargo in rain or snow conditions, a large amount of water can come into the airplane on
the cargo or open main deck doors.The water can spill onto the main deck cargo floor and flow through
the power drive units (PDU's). If the amount of water exceeds the drain capacity of the PDU's above
the main equipment center, water can spill onto the electrical/electronic units. Water contamination of
the electrical/electronic units may cause the electrical/electronic units to malfunction.
Three 747 Special Freighter operators have reported water contamination in the electrical/electronic
units in the main equipment center.The water contamination resulted in malfunctions and replacement
of multiple electrical/electronic units in the main equipment center. One operator experienced an air
turn back due to malfunctions of electronic equipment in the main equipment center resulting in high
pilot workload and minimal cockpit indication.
This change provides a closeout panel and moisture curtains to protect the electrical/electronics units
in the main equipment center from water contamination.
Boeing Service Related Problem (SRP) 747-SRP-25-0228 is related to this service bulletin.
Revision 1 is sent to incorporate changes to the service bulletin found during the initial service bulletin
incorporation.
These sections were changed:
1. In Effectivity, Paragraph 1.A., changed the Group Configuration table.
2. In Manpower, Paragraph 1.G., changed the Manpower Estimates tables.
3. In References, Paragraph 1.J., added 747-100/200/300 AMM 25-57-00, 53-21-02, and SOPM
20-50-19
4. In Material - Price and Availability, Paragraph 2.A., added superseding kits 672U7100-60 and
672U7100-61 and supplemental kit 672U7100-62
5. In Kits/Parts, Paragraph 2.C.1., added superseding kits 672U7100-60 and 672U7100-61 and
supplemental kit 672U7100-62
6. In Work Instructions, Paragraph 3.B.1., added steps to remove and install floor panels, PDU4L,
and PDU4R
7. In Figure 1, the following was changed:
a. Steps 4, 8, 11, added superseding part numbers.
b. Removed Qty 2, Washer NAS1149DN532J and increased to Qty 5, Washer NAS1149DN332J.
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8. In Figure 2, the following was changed:
a. Added step to remove existing fasteners.
b. Renumbered circle notes to reflect this added step.
c. Removed Qty 2, Washer NAS1149DN532J and increased to Qty 5, Washer NAS1149DN332J.
9. In Figure 3, the following was changed:
a. Steps 4, 8, 11, added superseding part numbers.
b. Removed Qty 2, Washer NAS1149DN532J and increased to Qty 5, Washer NAS1149DN332J.
10. In Figure 4, the following was changed:
a. Added steps for an optional installation.
11. In Figure 5, the following was changed:
a. Changed the quantity of MOUNTING PLATES installed in Step 2 from 2 to 1.
b. Changed the quantity of RIVET, UNIVERSAL HD BACR15BB3AD5C installed in Step 6 from
42 to 39.
c. In Step 7, added an optional installation.
12. In Figure 6, the following was changed:
a. Changed the quantity of MOUNTING PLATES installed in Step 2 from 2 to 1.
b. Changed the quantity of RIVET, UNIVERSAL HD BACR15BB3AD5C installed in Step 6 from
42 to 39.
13. In Figure 7, the following was changed:
a. Added steps to install a shim under MOUNTING BRACKET ASSY 672U7100-21.
b. Added an optional installation for using velcro strips in lieu of snaps to secure the moisture
curtain.
14. In Figure 8, the following was changed:
a. Added an optional installation for using velcro strips in lieu of snaps to secure the moisture
curtain.
15. Added Figure 9 for installation of center mounting plate and support angle.
16. Added Figure 10 for cap sealing of fasteners.
Revision 2 is sent to add instructions to install the moisture curtains and rubber closeout on airplanes
that have already installed the large PDU drain pans.
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These sections were changed:
1. In Effectivity, Section 1.A., moved airplanes RD301, RD302, RD411, RD412, RS721, RS722,
RS762 from Group 1, into new Group 3.
2. In Effectivity, Section 1.A., added airplanes RD646 and RD771 to Group 1.
3. In Effectivity, Section 1.A., added airplanes RA101-RA103, RA112, RA161-RA163, RA784, RA910
to Group 2.
4. In Compliance, Section 1.E., added NPRM 2007-NM-322-AD to compliance statement.
5. In Operator Supplied Parts, Section 2.C.2., added new table for Group 3 airplanes to include parts
fabricated in Appendix A
6. New Figure 11, Figure 12, Figure 13, Figure 14 have been added.
7. New Appendix A was added to include instructions to fabricate parts.
D. Description
Remove the units from the top row of the electrical/electronics rack. Install mounting supports. Install
closeout. Install moisture curtains.
The airplane effectivity is divided in two groups based on the location of the P73 panel in relation to
the existing water shield.
Revision 1 - More work is necessary on airplanes changed as shown in the original issue of this service
bulletin. All groups must cap seal all rivets fastening the mounting base assembly to the moisture
shroud as given in Figure 10. All groups must fill any unused pilot holes in mounting base assembly
as given in Figures 1, 2, 3, 4, and 9.
Revision 2 - No more work is necessary on airplanes changed as shown in the original issue and
Revision 01 of this service bulletin.
Group 1:
Affected Maintenance Zones
ZoneModel
117, 118747-200B, 747-300, 747SR
Group 2:
Affected Maintenance Zones
ZoneModel
117, 118747-100, 747-200B
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Group 3:
Affected Maintenance Zones
ZoneModel
117, 118747-200B, 747-300
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2007-NM-322-AD, is related
to this service bulletin.
Boeing recommends that operators do this service bulletin as soon as manpower, material and facilities
are available, not to exceed 24 months after the release date on this service bulletin.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA).The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task-hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task-hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Group 1, Configuration 1:
Elapsed HoursTask-HoursNumber of
Persons
Task
2.104.202Open Access
0.841.672Figure 1
0.681.352Figure 2
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Group 1, Configuration 1:
Elapsed HoursTask-HoursNumber of
Persons
Task
0.841.682Figure 4
1.002.002Figure 5
0.891.782Figure 7
0.750.751Figure 10
2.104.202Close Access
0.501.002Test
9.7018.63TOTAL FOR EACH AIRPLANE
Group 1, Configuration 2:
Elapsed HoursTask-HoursNumber of
Persons
Task
2.254.502Open Access
0.841.672Figure 1
0.841.672Figure 3
0.841.682Figure 4
1.002.002Figure 6
0.891.782Figure 7
0.750.751Figure 10
2.254.502Close Access
0.501.002Test
10.1619.55TOTAL FOR EACH AIRPLANE
Group 1, Configuration 3:
Elapsed HoursTask-HoursNumber of
Persons
Task
2.104.202Open Access
0.841.672Figure 1
0.681.352Figure 2
1.002.002Figure 5
0.891.782Figure 7
1.002.002Figure 9
0.750.751Figure 10
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Group 1, Configuration 3:
Elapsed HoursTask-HoursNumber of
Persons
Task
2.104.202Close Access
0.501.002Test
9.8618.95TOTAL FOR EACH AIRPLANE
Group 1, Configuration 4:
Elapsed HoursTask-HoursNumber of
Persons
Task
2.254.502Open Access
0.841.672Figure 1
0.841.672Figure 3
1.002.002Figure 6
0.891.782Figure 7
1.002.002Figure 9
0.750.751Figure 10
4.504.502Close Access
0.501.002Test
10.3219.87TOTAL FOR EACH AIRPLANE
Group 2, Configuration 1:
Elapsed HoursTask-HoursNumber of
Persons
Task
2.104.202Open Access
0.841.672Figure 1
0.681.352Figure 2
0.841.682Figure 4
1.002.002Figure 5
0.771.542Figure 8
0.750.751Figure 10
2.104.202Close Access
0.501.002Test
9.5818.39TOTAL FOR EACH AIRPLANE
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Group 2, Configuration 2:
Elapsed HoursTask-HoursNumber of
Persons
Task
2.254.502Open Access
0.841.672Figure 1
1.671.672Figure 3
1.681.682Figure 4
1.002.002Figure 6
0.771.542Figure 8
0.750.751Figure 10
2.254.502Close Access
0.501.002Test
10.0419.31TOTAL FOR EACH AIRPLANE
Group 2, Configuration 3:
Elapsed HoursTask-HoursNumber of
Persons
Task
2.104.202Open Access
0.841.672Figure 1
0.681.352Figure 2
1.002.002Figure 5
0.771.542Figure 8
1.002.002Figure 9
0.750.751Figure 10
2.104.202Close Access
0.501.002Test
9.7418.71TOTAL FOR EACH AIRPLANE
Group 2, Configuration 4:
Elapsed HoursTask-HoursNumber of
Persons
Task
2.254.502Open Access
0.841.672Figure 1
0.841.672Figure 3
1.002.002Figure 6
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Group 2, Configuration 4:
Elapsed HoursTask-HoursNumber of
Persons
Task
0.771.542Figure 8
1.002.002Figure 9
0.750.751Figure 10
2.254.502Close Access
0.501.002Test
10.2019.63TOTAL FOR EACH AIRPLANE
Group 3, Configuration 1:
Elapsed HoursTask HoursNumber of
Persons
Task
2.104.202Open Access
0.681.352Figure 2
0.891.782Figure 7
1.002.002Figure 9
0.750.751Figure 10
0.801.602Figure 11
0.801.602Figure 12
1.002.002Figure 13
0.751.502Figure 14
2.104.202Close Access
0.501.002Test
11.3721.98TOTAL FOR EACH AIRPLANE
Group 3, Configuration 2:
Elapsed HoursTask HoursNumber of
Persons
Task
2.254.502Open Access
0.841.672Figure 3
0.891.782Figure 7
1.002.002Figure 9
0.750.751Figure 10
0.801.602Figure 11
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Group 3, Configuration 2:
Elapsed HoursTask HoursNumber of
Persons
Task
0.801.602Figure 12
1.002.002Figure 13
0.751.502Figure 14
2.254.502Close Access
1.001.002Test
11.8322.90TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane Group
+11,836.0+26.9Group 1
+11,748.0+26.7Group 2
+11,836.0+26.9Group 3
I. Electrical Load Data
Not changed
J. References
1. Existing Data:
a. Engineering Change Memo PRR85901-43RS
b. 747-100/200/300 Aircraft Maintenance Manual (AMM) 20-11-22, 21-61-01, 23-21-00, 24-23-01,
28-21-06, 30-41-04, 34-14-00, 34-15-00, 34-21-00, 34-44-00, 34-46-00, 73-31-02
c. 747 Structural Repair Manual (SRM) Subject 51
d. Boeing Standard Wiring Practices Manual (BSWPM) 20-10-11, 20-10-12
e. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-50-12
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
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K. Publications Affected
Chapter-SectionPublication
34-14, 34-15, 34-21, 34-44747 Maintenance Manual
25-57747 Illustrated Parts Catalog
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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BLANK PAGE

### Page 25

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown
below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares.
More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the
date Boeing gets the purchase order.
Unit Price thru
June 30, 2008
ROLT
(Weeks)
QTYDateNameKit Number
REPLACED-139/26/05Top Kit672U7100-1 (a)
REPLACED---Top Kit672U7100-39 (b)
(a) Group 1, Group 3
(b) Group 2
Unit Price thru
June 30, 2008
ROLT
(Weeks)
QTYDateNameKit Number
$12,489.0030--Top Kit672U7100-60 (a)
$11,953.0030--Top Kit672U7100-61 (b)
$7,533.0036910/25/06Supplemental Kit672U7100-62 (c)
(a) Group 1, Group 3
(b) Group 2
(c) 672U7100-62 Supplemental Kit contains the necessary parts to change the 672U7100-1 Top
Kit into the 672U7100-60 Top Kit, and the 672U7100-39 Top Kit into the 672U7100-61 Top Kit.
B. Industry Support Information
Boeing warranty remedies are available for 747 SF airplanes in warranty as of December 12, 2002.
For man-hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing
Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be
supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service
bulletin number and reference the airplane variable numbers in your purchase order.
C. Parts Necessary For Each Airplane
1. Kits/Parts:
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.
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
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Kit 672U7100
NotesExisting Part
Number
NameQTYNew Part Number
-1-39-60-61-62
672U7100-1 is
replaced by
672U7100-60
KIT - MOISTURE
CURTAIN, INSTL
-....672U7100-1
REPLACED
672U7100-39 is
replaced by
672U7100-61
KIT - MOISTURE
CURTAIN, INSTL
.-...672U7100-39
REPLACED
672U7100-60
replaces
672U7100-1
KIT - MOISTURE
CURTAIN, INSTL
..-..672U7100-60
672U7100-61
replaces
672U7100-39
KIT - MOISTURE
CURTAIN, INSTL
...-.672U7100-61
KIT - MOISTURE
CURTAIN, INSTL
....-672U7100-62
MOISTURE
CURTAIN ASSY
1.1..672U7100-3
MOISTURE
CURTAIN ASSY
1111.672U7100-5
This part is
similar to
672U7100-48
SUPPORT
BRACKET ASSY
11...672U7100-13
This part is
similar to
672U7100-49
SUPPORT
BRACKET ASSY
11...672U7100-14
This part is
similar to
672U7100-50
MOUNTING PLATE
ASSY
22...672U7100-15
This part is
similar to
672U7100-51
MOUNTING BASE
ASSY
22...672U7100-16
This part is
similar to
672U7100-52
MOUNTING PLATE
ASSY
11...672U7100-17
This part is
similar to
672U7100-53
MOUNTING BASE
ASSY
11...672U7100-18
This part is
similar to
672U7100-54
SUPPORT
BRACKET ASSY
11...672U7100-19
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Kit 672U7100
NotesExisting Part
Number
NameQTYNew Part Number
-1-39-60-61-62
MOUNTING
BRACKET ASSY
3.3..672U7100-21
SHIM2222.672U7100-22
SHIM2222.672U7100-23
SHIM22...672U7100-24
SHIM11...672U7100-25
MOUNTING PLATE2211.672U7100-26
MOUNTING PLATE22331672U7100-27
MOUNTING PLATE2222.672U7100-28
MOUNTING PLATE1111.672U7100-29
RUBBER
CLOSEOUT
1111.672U7100-30
MOISTURE
CURTAIN ASSY
1111.672U7100-32
MOISTURE
CURTAIN ASSY
.1.1.672U7100-34
VELCRO HOOK1111.672U7100-40
This part is
similar to
672U7100-13
SUPPORT
BRACKET ASSY
..111672U7100-48
This part is
similar to
672U7100-14
SUPPORT
BRACKET ASSY
..111672U7100-49
This part is
similar to
672U7100-15
MOUNTING PLATE
ASSY
..222672U7100-50
This part is
similar to
672U7100-16
MOUNTING BASE
ASSY
..222672U7100-51
This part is
similar to
672U7100-17
MOUNTING PLATE
ASSY
..111672U7100-52
This part is
similar to
672U7100-18
MOUNTING BASE
ASSY
..111672U7100-53
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Kit 672U7100
NotesExisting Part
Number
NameQTYNew Part Number
-1-39-60-61-62
This part is
similar to
672U7100-19
SUPPORT
BRACKET ASSY
..111672U7100-54
VELCRO LOOP..11.672U7100-55
VELCRO HOOK..11.672U7100-56
SHIM..222672U7100-57
SHIM..111672U7100-58
SHIM..1.1672U7100-59
SHIM..111672U7100-65
BOLT2222.BACB30LM3-55
(a)(b)SELF-LOCKING
NUT
47581BACN10JC08CD
(a)(b)NUT3333.BACN10JC3CD
(a)(b)RIVET,
UNIVERSAL HD
464650507BACR15BB3AD5C
(a)(b)RIVET,
UNIVERSAL HD
20202020.BACR15BB3AD7C
(a)(b)RIVET,
UNIVERSAL HD
7.5..BACR15BB4AD4C
(a)(b)RIVETS..3..BACR15BB4AD5C
(a)(b)RIVET,
UNIVERSAL HD
1212...BACR15BB5AD10C
(a)(b)RIVET,
UNIVERSAL HD
..171717BACR15BB5AD11C
(a)(b)RIVET,
UNIVERSAL HD
..151515BACR15BB5AD12C
(a)(b)RIVET,
UNIVERSAL HD
14141414.BACR15BB5AD13C
(a)(b)RIVET 100 DEG HD12121212.BACR15DR4A4
(a)(b)BOLT20202020.BACS12HN3-11
(a)(b)BOLT20202020.BACS12HN3-12
(a)(b)STUD12121212.MS27980-7N
(a)(b)FASTENER, SNAP47581MS27980-13N
(a)(b)WASHER51515151.NAS1149D0332J
(a)(b)WASHER20202020.NAS1149DN232J
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### Page 29

Kit 672U7100
NotesExisting Part
Number
NameQTYNew Part Number
-1-39-60-61-62
(a)(b)WASHER24242424.NAS1149DN432J
(a)(b)WASHER47581NAS1149FN816P
SPACERS FOR
BOLTS
2222.NAS43DD3-196FC
(a) There are more parts than are necessary.
(b) 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. Boeing Document D-590 and Boeing Drawing 65B88700 are used to determine the part
numbers used as substitutes.
2. Parts and Materials Supplied by the Operator:
Group 1-2:
NotesNameQTYPart Number /
Specification
(a)Sealant4 ozBMS 5-95, Type 1
Optional parts BMS 5-92
Type 1 or BMS 5-92 Type
2
Adhesive8 ozBMS 5-95 Class
B-1/2, BMS 5-95
Class B-2, or BMS
5-95 Class B-4
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for
supplier data.
Group 3:
NotesNameQTYPart Number /
Specification
(a)Sealant4 ozBMS 5-95, Type 1
Optional parts BMS 5-92
Type 1 or BMS 5-92 Type
2
Adhesive8 ozBMS 5-95 Class
B-1/2, BMS 5-95
Class B-2, or BMS
5-95 Class B-4
Fabricate part as given in
Appendix A
MOUNTING PLATE1672U7100-42
Fabricate part as given in
Appendix A
MOUNTING PLATE1672U7100-43
Fabricate part as given in
Appendix A
SHIM1672U7100-70
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Group 3:
NotesNameQTYPart Number /
Specification
Fabricate parts as given in
Appendix A
SHIM2672U7100-71
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for
supplier data.
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None
E. Special Tooling - Price and Availability
None
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph I.K., 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
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
— Linear dimensions are in inches
— Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch.
— Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
— Angular tolerance is plus or minus 2 degrees
— Hole dimensions for standard solid rivets are given in 747 Structural Repair
Manual, Chapter 51
— Torque limits to tighten nuts and bolts are given in 747 Structural Repair Manual,
Chapter 51.
4. For approved fastener and process material substitutions, refer to 747 Structural
Repair Manual, Chapter 51, Alternate fasteners are given in 747 Structural Repair
Manual Chapter 51 and Boeing Drawing 012W6100.
5. Refer to the Boeing Standard Wiring Practices Manuals 20-10-11 and 20-10-12 for
the wire installation procedures.
6. If the length of fasteners specified in this service bulletin do not meet the installation
standards, fasteners of the same specification, or an approved substitute, one grip
length longer or shorter may be used.
B. WORK INSTRUCTIONS
1. All Airplane Groups. Remove electrical/electronic rack components on the top shelf as required
for access. Remove electrical/electronic rack components as shown in 747-100/200/300 AMM
20-11-22.
Generator Control Units (GCU), 747-100/200/300 AMM 24-23-01, page 401.
Bus Power Control Units (BPCU), 747-100/200/300 AMM 24-23-01, page 401.
Upper Deck Zone Controller, 747-100/200/300 AMM 21-61-01
Volumetric Shutoff, 747-100/200/300 AMM 28-21-06
Fuel Flow, 747-100/200/300 AMM 73-31-02
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Window Heat, 747-100/200/300 AMM 30-41-04
Mach Airspeed Switch, 747-100/200/300 AMM 34-14-00
TAT/EPR/N1, 747-100/200/300 AMM 34-15-00
Ground Prox Computer, 747-100/200/300 AMM 34-46-00
Central Instrument Warning Computer, 747-100/200/300 AMM 34-44-00
Magnetic Heading, 747-100/200/300 AMM 34-21-00
VHF Comm 3 XCVR, 747-100/200/300 AMM 23-21-00
2. All airplane groups. Remove floor panels from STA 420 to STA 460 and from LBL 60 to RBL 60
as necessary to gain access to STA 440 floor beam below. Refer to 747-100/200/300 AMM
53-21-02.
3. Group 1, Configuration 1, 3; Group 2, Configuration 1, 3; Group 3, Configuration 1:
Remove PDU 4R. Refer to 747-100/200/300 AMM 25-57-00.
4. Group 1, Configuration 2, 4; Group 2, Configuration 2, 4; Group 3, Configuration 2:
Remove PDU 4R and PDU 4L. Refer to 747-100/200/300 AMM 25-57-00.
5. Group 1-2:
Install the right mounting plate and support angle as shown in Figure 1.
6. Group 3:
Install the right mounting plate and support angle as shown in Figure 11.
7. Group 1, Configuration 1, 3; Group 2, Configuration 1, 3; Group 3, Configuration 1:
Install the left mounting plate and support angle as shown in Figure 2.
8. Group 1, Configuration 2, 4; Group 2, Configuration 2, 4; Group 3, Configuration 2:
Install the left mounting plate and support angle as shown in Figure 3.
9. Group 3:
Install the left mounting plate and support angle as shown in Figure 12.
10. Group 1, Configuration 1-2; Group 2, Configuration 1-2:
Install the center mounting plate and support angle as shown in Figure 4.
11. Group 1, Configuration 3-4; Group 2, Configuration 3-4:
Install the center mounting plate and support angle as shown in Figure 9.
12. Group 3:
Install the center mounting plate and support angle as shown in Figure 13.
13. Apply a cap seal to new fasteners as shown in Figure 10.
14. Group 1, Configuration 1, 3; Group 2, Configuration 1, 3:
Install the closeout panel as shown in Figure 5.
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15. Group 1, Configuration 2, 4; Group 2, Configuration 2, 4:
Install the closeout panel as shown in Figure 6.
16. Group 3:
Install the closeout panel as shown in Figure 14.
17. Group 1, 3:
Install the moisture curtains as shown in Figure 7.
18. Group 2:
Install the moisture curtains as shown in Figure 8.
19. Install and Test the electrical/electronic rack components on the top shelf as required for access.
Install electrical/electronic rack components as shown in 747-100/200/300 AMM 20-11-22.
Generator Control Units (GCU), 747-100/200/300 AMM 24-23-01, page 401.
Bus Power Control Units (BPCU), 747-100/200/300 AMM 24-23-01, page 401.
Upper Deck Zone Controller, 747-100/200/300 AMM 21-61-01
Volumetric Shutoff, 747-100/200/300 AMM 28-21-06
Fuel Flow, 747-100/200/300 AMM 73-31-02
Window Heat, 747-100/200/300 AMM 30-41-04
Mach Airspeed Switch, 747-100/200/300 AMM 34-14-00
TAT/EPR/N1, 747-100/200/300 AMM 34-15-00
Ground Prox Computer, 747-100/200/300 AMM 34-46-00
Central Instrument Warning Computer, 747-100/200/300 AMM 34-44-00
Magnetic Heating, 747-100/200/300 AMM 34-21-00
VHF Comm 3 XCVR, 747-100/200/300 AMM 23-21-00
20. Group 1, Configuration 1, 3; Group 2, Configuration 1, 3; Group 3, Configuration 1:
Install PDU 4R. Refer to 747-100/200/300 AMM 25-57-00.
21. Group 1, Configuration 2, 4; Group 2, Configuration 2, 4; Group 3, Configuration 2:
Install PDU 4R and PDU 4L. Refer to 747-100/200/300 AMM 25-57-00.
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### Page 34

22. All airplane groups. Install floor panels from STA 420 to STA 460 and from LBL 60 to RBL 60.
Refer to 747-100/200/300 AMM 53-21-02.
23. If the aircraft inspections, modifications and/or repairs cause a disruption in wire continuity or result
in disconnecting a connector, perform the appropriate system functional test for the wire bundle(s)
which have been modified or the connector(s) which have been unmated in accordance with the
appropriate section of the 747 AMM.
24. Put the airplane back to a serviceable condition.
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### Page 35 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
SEE DOO
FWDE
MAIN EQUIPMENT CENTER
PDU DRAIN
PAN BRACKET
PDU DRAIN
PAN
UP
INBD  → FWD  D71452
FIGURE 1: RIGHT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - ALL GROUPS
(SHEET 1 OF 7)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
STA
RIGHT E/E  440
MOISTURE  FLOOR BEAM
SHROUD
INTERCOSTAL
TIE STRAP
E/E RACK
STANCHION
PDU DRAIN
PAN
BRACKET  PDU DRAIN
PAN
UP
INBD ‹  • FWD  D71536
FIGURE 1: RIGHT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - ALL GROUPS
(SHEET 2 OF 7)
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
FLOOR BEAM
FLOOR BEAM  INTERCOSTAL
STA
440
. EXISTING  4.84-
FASTENERS  - 0.86
-0.86
RIGHT MOISTURE
PDU DRAIN
PAN BRACKET
T (6 LOCATIONS)
(4 LOCATIONS)
(5 LOCATIONS)
10)  UP  12) (5 LOCATIONS)
(5 LOCATIONS)
13) (5 LOCATIONS)
INBD '  • FWD  D71538
FIGURE 1: RIGHT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - ALL GROUPS
(SHEET 3 OF 7)
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### Page 38

FIGURE 1: RIGHT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - ALL GROUPS
(SHEET 4 OF 7)
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### Page 39 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
E/E RACK
INTERCOSTAL
FLOOR BEAM
INTERCOSTAL
RBL
RIGHT  55.5
MOISTURE  (18)
SHROUD  2 REQUIRED
RIGHT  TIE
MOISTURE  STRAP
SHROUD  INBD
FWD
C-C
TIE
E/E RACK  STRAP
INTERCOSTAL
STANCHION
B-B
INBD<  D71131
FIGURE 1: RIGHT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - ALL GROUPS
(SHEET 5 OF 7)
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### Page 40

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 one airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove existing fasteners. Do
not remove the PDU drain pan.
5-FASTENERRemove1
Adjust the dimensions as required to maintain proper edge margin when drilling the hole in Step 14.
Locate the shim to the aft and
outboard edge of the PDU drain
pan bracket.
1672U7100-23SHIMInstall (New)2
Locate the shim to the aft and
outboard edge of the PDU drain
pan bracket.
1672U7100-22SHIMInstall (New)3
-1672U7100-16MOUNTING BASE
ASSY
Install (New)4
Use the smallest diameter rivet
to fill any unused pilot holes.
-BACR15BA()A()C or
BACR15BA()AD()C
RIVET
Or
Seal any unused pilot holes with
BMS 5-95. Refer to SOPM
20-50-12 as an acceptable
procedure.
-BMS 5-95SEALANT
Optional Installation
-1672U7100-51MOUNTING BASE
ASSY
Install (New)
Backdrill through the mounting
base assembly and shims.
4-HOLEDrill5
Drill through pilot hole in the
mounting base assembly.
2-HOLEDrill6
-6BACR15BB5AD13CRIVET,
UNIVERSAL HD
Install (New)7
-1672U7100-15MOUNTING
PLATE ASSY
Install (New)8
Optional Installation
-1672U7100-50MOUNTING
PLATE ASSY
Install (New)
-5NAS1149D0332JWASHERInstall (New)9
-5BACS12HN3-12BOLTInstall (New)10
FIGURE 1: RIGHT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - ALL GROUPS
(SHEET 6 OF 7)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
August 25, 2005
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### Page 41

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
-1672U7100-14SUPPORT
BRACKET ASSY
Install (New)11
Optional Installation
-1672U7100-49SUPPORT
BRACKET ASSY
Install (New)
-5NAS1149D0332JWASHERInstall (New)12
-5BACS12HN3-11BOLTInstall (New)13
Align hole with the existing hole
in the support bracket assembly.
Drill through tie strap and
intercostal. Maintain proper
edge margins.
10.1920 - 0.2030HOLEDrill14
-5NAS1149D0332JWASHERInstall (New)15
-1NAS43DD3-196FCSPACERS FOR
BOLTS
Install (New)16
-1BACB30LM3-55BOLT, SHOULDERInstall (New)17
-1BACN10JC03CDNUTInstall (New)18
FIGURE 1: RIGHT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - ALL GROUPS
(SHEET 7 OF 7)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
August 25, 2005
747-25A3368Revision 2 June 12, 2008
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BOEING SERVICE BULLETIN 747-25A3368

### Page 42 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
SEE A ®
STA
440  FLOOR BEAM  SHROUD  MOISTURE  FWDE
MAIN EQUIPMENT CENTER
INTERCOSTAL
0.94
TIE STRAP
INTERCOSTAL
E/E RACK
STANCHION
FWD  INBD  J12292
FIGURE 2: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 3
(SHEET 1 OF 6)
August 25, 2005
Revision 2 June 12, 2008  747-25A3368
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### Page 43 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
FLOOR BEAM
INTERCOSTAL  FLOOR BEAM
STA
440
EXISTING
FASTENERS
RIGHT MOISTURE
SHROUD
0.86
(6 LOCATIONS)  0.86
(4 LOCATIONS)
(5 LOCATIONS)
(5 LOCATIONS) 10  UP
(5 LOCATIONS)
(5 LOCATIONS) (11
FWD  * INBD  J12295
FIGURE 2: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 3
(SHEET 2 OF 6)
August 25, 2005
Revision 2 June 12, 2008  747-25A3368
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### Page 44

FIGURE 2: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 3
(SHEET 3 OF 6)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
August 25, 2005
747-25A3368Revision 2 June 12, 2008
44 of 119
BOEING SERVICE BULLETIN 747-25A3368

### Page 45 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
E/E RACK
INTERCOSTAL
FLOOR BEAM
INTERCOSTAL
LBL
55.5
MOISTURE
16)  SHROUD
2 REQUIRED (13
TIE  MOISTURE
STRAP  SHROUD
→ INBD
FWD
C-C
TIE
STRAP  E/E RACK
INTERCOSTAL
STANCHION
B-B
→INBD  J12305
FIGURE 2: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 3
(SHEET 4 OF 6)
August 25, 2005
Revision 2 June 12, 2008  747-25A3368
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### Page 46

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 one airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove existing fasteners from
moisture shield common to the
mounting base assembly
5-FASTENERRemove1
Adjust the dimensions as required to maintain proper edge margin when drilling the hole in Step 11.
-1672U7100-16MOUNTING BASE
ASSY
Install (New)2
Use the smallest diameter rivet
to fill any unused pilot holes.
-BACR15BA()A()C or
BACR15BA()AD()C
RIVET
Or
Seal any unused pilot holes with
BMS 5-95. Refer to SOPM
20-50-12 as an acceptable
procedure.
-BMS 5-95SEALANT
Optional Installation
-1672U7100-51MOUNTING BASE
ASSY
Install (New)
Backdrill through the mounting
base assembly.
4-HOLEDrill3
Drill through pilot hole in the
mounting base assembly.
2-HOLEDrill4
-6BACR15BB5AD13CRIVET,
UNIVERSAL HD
Install (New)5
-1672U7100-15MOUNTING
PLATE ASSY
Install (New)6
Optional Installation
-1672U7100-50MOUNTING
PLATE ASSY
Install (New)
-5NAS1149D0332JWASHERInstall (New)7
-5BACS12HN3-12BOLTInstall (New)8
-1672U7100-13SUPPORT
BRACKET ASSY
Install (New)9
Optional Installation
-1672U7100-48SUPPORT
BRACKET ASSY
Install (New)
-5NAS1149D0332JWASHERInstall (New)10
FIGURE 2: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 3
(SHEET 5 OF 6)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
August 25, 2005
747-25A3368Revision 2 June 12, 2008
46 of 119
BOEING SERVICE BULLETIN 747-25A3368

### Page 47

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
-5BACS12HN3-11BOLTInstall (New)11
Align hole with the existing hole
in the support bracket assembly.
Drill through tie strap and
intercostal. Maintain Proper
edge margins.
10.1920 - 0.2030HOLEDrill12
-5NAS1149D0332JWASHERInstall (New)13
-1NAS43DD3-196FCSPACERS FOR
BOLTS
Install (New)14
-1BACB30LM3-55BOLT, SHOULDERInstall (New)15
-1BACN10JC03CDNUTInstall (New)16
FIGURE 2: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 3
(SHEET 6 OF 6)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
August 25, 2005
747-25A3368Revision 2 June 12, 2008
47 of 119
BOEING SERVICE BULLETIN 747-25A3368

### Page 48 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
SEE DOO
FWDI
MAIN EQUIPMENT CENTER
PDU DRAIN
PAN BRACKET
PDU DRAIN
PAN
UP
FWD<  INBD  D74395
FIGURE 3: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 2 AND 4
(SHEET 1 OF 7)
August 25, 2005
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### Page 49 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
STA
440  RIGHT E/E
FLOOR BEAM  MOISTURE
SHROUD
INTERCOSTAL
TIE STRAP
E/E RACK
STANCHION
PDU DRAIN
PAN
PDU DRAIN  BRACKET
PAN
UP
FWD  INBD  D74403
FIGURE 3: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 2 AND 4
(SHEET 2 OF 7)
August 25, 2005
Revision 2 June 12, 2008  747-25A3368
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  49 of 119

### Page 50 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
FLOOR BEAM
INTERCOSTAL  FLOOR BEAM
STA
440
15)
4.84
EXISTING_
FASTENERS
RIGHT MOISTURE
SHROUD
0.86  PDU DRAIN
PAN BRACKET
16
(6 LOCATIONS)  -0.86
(4 LOCATIONS)
(5 LOCATIONS)
(5 LOCATIONS) 12  10
(5 LOCATIONS)
(5 LOCATIONS) 13
FWD  → INBD  D74400
FIGURE 3: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 2 AND 4
(SHEET 3 OF 7)
August 25, 2005
Revision 2 June 12, 2008  747-25A3368
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### Page 51

FIGURE 3: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 2 AND 4
(SHEET 4 OF 7)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
August 25, 2005
747-25A3368Revision 2 June 12, 2008
51 of 119
BOEING SERVICE BULLETIN 747-25A3368

### Page 52 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
E/E RACK
INTERCOSTAL
FLOOR BEAM
INTERCOSTAL
LBL
55.5  LEFT
MOISTURE
(18)  SHROUD
2 REQUIRED 15
TIE  LEFT
STRAP  MOISTURE
—INBD  SHROUD
FWD
C-C
TIE
STRAP  E/E RACK
INTERCOSTAL
STANCHION
B-B
→INBD  D74428
FIGURE 3: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 2 AND 4
(SHEET 5 OF 7)
August 25, 2005
Revision 2 June 12, 2008  747-25A3368
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  52 of 119

### Page 53

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 one airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove existing fasteners.5-FASTENERRemove1
Adjust the dimensions as required to maintain proper edge margin when drilling the hole in Step 14.
Locate the shim to the aft and
outboard edge of the PDU drain
pan bracket.
1672U7100-23SHIMInstall (New)2
Locate the shim to the aft and
outboard edge of the PDU drain
pan bracket.
1672U7100-22SHIMInstall (New)3
-1672U7100-16MOUNTING BASE
ASSY
Install (New)4
Use the smallest diameter rivet
to fill any unused pilot holes.
-BACR15BA()A()C or
BACR15BA()AD()C
RIVET
Or
Seal any unused pilot holes with
BMS 5-95. Refer to SOPM
20-50-12 as an acceptable
procedure.
-BMS 5-95SEALANT
Optional Installation
-1672U7100-51MOUNTING BASE
ASSY
Install (New)
Backdrill through the mounting
base assembly and shims.
4-HOLEDrill5
Drill through pilot hole in the
mounting base assembly.
2-HOLEDrill6
-6BACR15BB5AD13CRIVET,
UNIVERSAL HD
Install (New)7
-1672U7100-15MOUNTING
PLATE ASSY
Install (New)8
Optional Installation
-1672U7100-50MOUNTING
PLATE ASSY
Install (New)
-5NAS1149D0332JWASHERInstall (New)9
-5BACS12HN3-12BOLTInstall (New)10
FIGURE 3: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 2 AND 4
(SHEET 6 OF 7)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
August 25, 2005
747-25A3368Revision 2 June 12, 2008
53 of 119
BOEING SERVICE BULLETIN 747-25A3368

### Page 54

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
-1672U7100-13SUPPORT
BRACKET ASSY
Install (New)11
Optional Installation
-1672U7100-48SUPPORT
BRACKET ASSY
Install (New)
-5NAS1149D0332JWASHERInstall (New)12
-5BACS12HN3-11BOLTInstall (New)13
Align hole with the existing hole
in the support bracket assembly.
Drill through tie strap and
intercostal. Maintain proper
edge margins.
10.1920 - 0.2030HOLEDrill14
-5NAS1149D0332JWASHERInstall (New)15
-1NAS43DD3-196FCSPACERS FOR
BOLTS
Install (New)16
-1BACB30LM3-55BOLT, SHOULDERInstall (New)17
-1BACN10JC03CDNUTInstall (New)18
FIGURE 3: LEFT MOUNTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 2 AND 4
(SHEET 7 OF 7)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
August 25, 2005
747-25A3368Revision 2 June 12, 2008
54 of 119
BOEING SERVICE BULLETIN 747-25A3368

### Page 55 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
SEE A B
FOR OPTIONAL
INSTALLATION
SEE CO
FWDE
MAIN EQUIPMENT CENTER
CENTER
MOISTURE
SHROUD
INTERCOSTAL
UP
»TWD
D74543
FIGURE 4: CENTER MOUTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 2
(SHEET 1 OF 8)
August 25, 2005
Revision 2 June 12, 2008  747-25A3368
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### Page 56 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
CENTER
MOISTURE
SHROUD
EXISTING
FASTENERS  3) .  LOCATIONS)
(10 LOCATIONS)
INTERCOSTAL
4.10
4(10 LOCATIONS)
2.40 °
(2 LOCATIONS)
0.13
(8 LOCATIONS) 6
UP
(8 LOCATIONS)
SEND
(8 LOCATIONS)
(8 LOCATIONS) 10  D74649
FIGURE 4: CENTER MOUTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 2
(SHEET 2 OF 8)
August 25, 2005
Revision 2 June 12, 2008  747-25A3368
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### Page 57 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
CENTER  BL  (8 LOCATIONS) 6(7
INTERCOSTAL  MOISTURE  4(10 LOCATIONS)
SHROUD
0.13
2) (2 LOCATIONS)
(8 LOCATIONS › 910
11.33  LBL  (LOOKING UP)  FWD  11.33  RBL
A-A
STA 440
FLOOR BEAM
LOWER CHORD
CENTER
0.27 -  MOISTURE
SHROUD
UP
> FWD
B-B  D74560
FIGURE 4: CENTER MOUTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 2
(SHEET 3 OF 8)
August 25, 2005
Revision 2 June 12, 2008  747-25A3368
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### Page 58

FIGURE 4: CENTER MOUTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 2
(SHEET 4 OF 8)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
August 25, 2005
747-25A3368Revision 2 June 12, 2008
58 of 119
BOEING SERVICE BULLETIN 747-25A3368

### Page 59 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
DO NOT REMOVE  EXISTING
EXISTING FASTENER  THIS EXISTING  FASTENERS
(6 LOCATIONS)  FASTENER
CENTER
MOISTURE
SHROUD
1 12 13 14
DO NOT REMOVE  (15) (2 LOCATIONS)
THIS EXISTING  E
FASTENER
EXISTING
FASTENERS
4.10
17(10 LOCATIONS)
INTERCOSTAL
- 2.40
(2 LOCATIONS)
0.13
(8 LOCATIONS) (19)
(8 LOCATIONS) 20
UP
(8 LOCATIONS)  @ INBD
(8 LOCATIONS)  SFWD
OPTIONAL INSTALLATION
U88325
FIGURE 4: CENTER MOUTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 2
(SHEET 5 OF 8)
August 25, 2005
Revision 2 June 12, 2008  747-25A3368
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  59 of 119

### Page 60 (OCR)

BOEING SERVICE BULLETIN 747-25A3368
INTERCOSTAL  MOISTURE  CENTER  BL  (8 LOCATIONS 19) 20  (17) (10 LOCATIONS)
SHROUD  (11 12 13)14
0.13
15) (2 LOCATIONS)  0.43
0.50  EXISTING  1.90
• 1.90  FASTENER  0.50-
EXISTING  22) 23
FASTENER  (8 LOCATIONS)
LBL
11.33  (LOOKING UP)  FWD  11.33  RBL
C-C
STA 440
FLOOR BEAM
LOWER CHORD
STA 440  CENTER
FLOOR BEAM  MOISTURE
13 14  SHROUD
0.27  CENTER  MOISTURE
SHROUD
EXISTING
FASTENER
UP  UP
> FWD  INBD ‹  U88352
D-D  E—E
FIGURE 4: CENTER MOUTING PLATE AND SUPPORT ANGLE INSTALLATION - GROUPS 1 AND 2,
CONFIGURATION 1 AND 2
(SHEET 6 OF 8)
August 25, 2005
Revision 2 June 12, 2008  747-25A3368
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  60 of 119

The text continues at https://openairdocs.org/service-documents/boeing/747-25a3368/file/b5c349b1b394.md?from=61

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