# Boeing Service Bulletin 747-28-2344: No revision named

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- Title as filed: SB-747-28-2344-00
- Pages: 128
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## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
Number: 747-28-2344
Original Issue: October 12, 2018
ATA System: 2841
SUBJECT: FUEL - Fuel Quantity Indicating System - Center Wing Tank Fuel Quantity Indicating
System Wire 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 © 2018 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Unpublished Work.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, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, 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.
Original Issue: October 12, 2018
747-28-2344
1 of 128
7.0

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### Page 3

Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 22
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 33
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 34
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
FIGURE 1: LEFT SIDE - FQIS WIRE X1008 (S283U007-518) INSPECTION  [Group 1, 6] . . . . . . . 53
FIGURE 2: LEFT SIDE - FQIS WIRE X1008 (S283U007-518 OR S283U007-318) INSPECTION [Group
2-5, 7-8] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64
FIGURE 3: LEFT SIDE - STATION 920 THROUGH STA 980 - BRACKET ASSY AND STANDOFF
INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75
FIGURE 4: LEFT SIDE - E6 FQPU TO PRESSURE SEAL STATION 1278 - FQIS WIRE X1008
(S283U007-518) WIRE ROUTING CHANGE  [Group 1, 3, 5-8] . . . . . . . . . . . . . . . 84
FIGURE 5: LEFT SIDE - E6 FQPU TO PRESSURE SEAL STATION 1278 - FQIS WIRE X1008
(S283U007-318) WIRE ROUTING CHANGE [Group 2, 4] . . . . . . . . . . . . . . . . . . 99
FIGURE 6: LEFT WHEEL WELL AND CENTER WING TANK - SINGLE POINT SENSOR (SPS) WIRES
X1012 (S283U007-312) AND X1011 (S283U007-502) REMOVAL  [Group 2-3, 7] . . . . 114
FIGURE 7: E6 FQPU TO PRESSURE SEAL STATION 1278 - WIRING CHANGE [Group 1, 3, 5-8] . 122
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FIGURE 8: E6 FQPU TO PRESSURE SEAL STATION 1278 - WIRING CHANGE  [Group 2, 4] . . . 124
FIGURE 9: LEFT WHEEL WELL AND CENTER WING TANK WIRING - REMOVAL  [Group 2-3, 7] . 126
APPENDIX A: INPUT SURVEY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 128
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Commercial 
Airplanes
747
Service Bulletin
SummaryNumber: 747-28-2344Original Issue: October 12, 2018
ATA System: 2841
SUBJECT: FUEL - Fuel Quantity Indicating System - Center Wing Tank Fuel Quantity Indicating
System Wire Change
CONCURRENT REQUIREMENTS
The Airworthiness Limitations (AWL) listed below must be added to the airplane's maintenance program before
or at the same time as this service bulletin.
DescriptionAWLDocumentCompany
Fuel Quantity Indicating System
(FQIS) - Out Of Tank Wiring Light-
ning Shield to Ground Termination
28-AWL-03747-400 Maintenance Planning Data
(MPD) Document, Section 9, Airworthi-
ness Limitations (AWLs) and Certifica-
tion Maintenance Requirements
(CMRs), D621U400-9, Revision August
2016 or later revision that has been
approved by the FAA Oversight Office
(Boeing Aviation Safety Oversight Of-
fice (BASOO))
Boeing
Wire Separation Requirements for
New Wiring Installed in Proximity to
Wiring That Goes Into the Fuel Tanks
28-AWL-08
Fuel Quantity Indicating System
(FQIS), Single Point Sensor (SPS),
and Auxiliary Fuel Tank (Cell) Elec-
tronic Fuel Level Indication (EFLI) -
In-Tank Hardware Installation - Sep-
aration From Structure (FQIS Tank
Units, Compensators, SPS, and
Auxiliary Fuel Tank (Cell) EFLI
Probes (If Installed)
28-AWL-14
Visible Means of Identification for
Fuel Quantity Indicating System
(FQIS) Wiring that Goes into the
Center Wing Tank
28-AWL-38
BACKGROUND
The changes given in this service bulletin will improve the wire routing for Fuel Quantity Indicating System (FQIS)
wire outside the fuel tank on 747-400F and 747-400 Boeing Converted Freighters (BCF) aircraft. The FQIS
wiring from the Fuel Quantity Processor Unit (FQPU) to the pressure seal area station 1278 must be separated
from other airplane system wiring. If this service bulletin is not done, an undetected failure of the FQIS components
inside the center wing tank (CWT), in combination with an electrical hot short to FQIS wiring outside the tank,
can cause ignition source of the fuel tank which could result in smoke and/or fire in the fuel tank.
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### Page 6

A Federal Aviation Administration (FAA) review of the Boeing Special Federal Aviation Regulation No. 88
(SFAR88) System Safety Assessment identified a non-safety fuel tank condition on delivered and modified
freighter airplanes which do not have Nitrogen Generating System (NGS) installed to reduce flammability in the
CWT. An investigation identified that the FQIS wiring was routed together with other airplane system wires,
which did not meet the 747 System Separation Requirement. The entire length of the FQIS wire from the FQPU
to the pressure seal area will be sleeved, to address areas where increased separation is not possible.
This service bulletin gives instructions to do a General Visual Inspection for any damage to FQIS wire. Install a
bracket and standoff, then install pink sleeving over the FQIS wire from the FQPU to the pressure seal area to
identify it as an FQIS wire bundle with separation limitation. The change will meet the wire separation requirements
for FQIS wire from the other airplane system wires.
This service bulletin is the result of the safety assessments conducted by Boeing under a SFAR88, Fuel Tank
System Fault Tolerance Evaluation Requirements.
Boeing Service Related Problem (SRP) 747-SRP-28-0149 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 28-13004 is related to this service bulletin.
Sufficient data is not available to Boeing from operators to establish reliability and maintenance rates to support
cost benefit analysis. Operators should examine their own data to evaluate the impact to their fleets.
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
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD 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 Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION (PRR 85901-132RS)
Group 1, 5:
Open access. Do a General Visual Inspection to find any damage to the FQIS wire bundle. Replace an existing
bracket and install a standoff. Change the FQIS wire bundle. Do the Fuel Quantity Indicating System Operational
Test. Close access.
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### Page 7

Group 2, 7:
Open access. Do a General Visual Inspection to find any damage to the FQIS wire bundle. Replace an existing
bracket and install a standoff. Change the FQIS wire bundle. Remove the Single Point Sensor (SPS) wires
X1012 (S283U007-312) from the wheel well spar connector and X1011 (S283U007-502) from the CWT. Do the
Fuel Quantity Indicating System Operational Test. Close access.
Group 3:
Open access. Do a General Visual Inspection to find any damage to the FQIS wire bundle. Replace an existing
bracket and install a standoff. Change the FQIS wire bundle. Remove the SPS wires X1012 (S283U007-312)
from the wheel well spar connector, and X1011 (S283U007-502) from CWT. Do the Fuel Quantity Indicating
System Operational Test. Close access.
Group 4, 6, 8:
Open access. Do a General Visual Inspection to find any damage to the FQIS wire bundle. Replace an existing
bracket and install a standoff. Change the FQIS wire bundle. Do the Fuel Quantity Indicating System Operational
Test. Close access.
EFFECTIVITY
747-400, 747-400F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive (AD) related to this
service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service
bulletin mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to help Boeing
predict the quantity and timing of the Boeing Supplied Kits/Parts.
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### Page 8 (OCR)

BOEING SERVICE BULLETIN 747-28-2344
STA
1000
CENTER WING TANK FUEL
QUANTITY INDICATING
SYSTEM (FQIS) WIRE BUNDLE
CHANGE AND INSPECTION
SIA
780
E6
FUEL QUANTITY  2386176
PROCESSOR
UNIT(FQPU)
Original Issue: October 12, 2018
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-28-2344
Work - See page 1 for detalls.  8 of 128

### Page 9

Commercial 
Airplanes
747
Service Bulletin
Number: 747-28-2344
Original Issue: October 12, 2018
ATA System: 2841
SUBJECT: FUEL - Fuel Quantity Indicating System - Center Wing Tank Fuel Quantity Indicating
System Wire Change
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is applicable to 747-400BCF and 747-400F Airplanes in eight (8) Groups. The
Variable Numbers and Group Information for the applicable airplanes is given below. An equivalent
change is on subsequent production airplanes. Refer to PRR 85901-132RS for data about this
change.
NOTE: The 747-400BCF may also be known as 747-400SF. Where 747-400BCF is noted in this
SB, it is also applicable to the 747-400SF that were modified by Boeing Service Bulletin.
DESCRIPTIONCONFIGURATIONGROUP
747-400F airplanes, FQIS wire bundle change that use Top Kit
015U2132-1.
-1
747-400 BCF airplanes with the single point sensor installed. FQIS
wire bundle change that use Top Kit 015U2132-2.
-2
747-400 BCF airplanes with the single point sensor installed. FQIS
wire bundle change that use Top Kit 015U2132-3.
-3
747-400 BCF airplanes, FQIS wire bundle change that use Top Kit
015U2132-4.
-4
747-400 BCF airplanes, FQIS wire bundle change that use Top Kit
015U2132-1.
-5
747-400F airplanes, FQIS wire bundle change that use Top Kit
015U2132-1.
-6
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### Page 10

DESCRIPTIONCONFIGURATIONGROUP
747-400 BCF airplanes with the single point sensor installed. FQIS
wire bundle change that use Top Kit 015U2132-3.
-7
747-400 BCF airplanes, FQIS wire bundle change that use Top Kit
015U2132-1.
-8
Airplane Models:
747-400, 747-400F
GroupVariable Number
1RL401 - RL403
1RL411 - RL436
1RL451 - RL456
1RL461 - RL462
1RL471 - RL481
1RL491 - RL492
1RL501 - RL502
1RL511 - RL516
1RL521 - RL522
1RL531 - RL534
1RL551
1RL561
1RL563 - RL568
1RL571 - RL572
1RL576 - RL577
1RL579
1RL581 - RL586
1RL651 - RL655
1RL671 - RL675
1RL681 - RL684
1RL751 - RL752
5RM128
1RM851 - RM859
1RM861 - RM862
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### Page 11

GroupVariable Number
1RM871 - RM899
1RM901 - RM906
1RM911
6RR701
1RR721 - RR724
1RR746 - RR748
1RR851 - RR856
1RR861 - RR862
1RR951 - RR952
2RT021 - RT022
4RT031 - RT033
2RT061
7RT071 - RT072
3RT161
3RT164
7RT456
2RT501
2RT506
7RT507 - RT510
7RT513
7RT516
7RT518 - RT519
3RT520
3RT524
3RT528
3RT530
2RT572 - RT573
7RT574 - RT576
7RT578 - RT579
2RT642
8RT654 - RT657
2RT691 - RT692
7RT751 - RT752
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### Page 12

GroupVariable Number
7RT781 - RT782
3RT837
5RT967
2. Spares Affected
None.
B. Concurrent Requirements
The Airworthiness Limitations (AWL) listed below must be added to the airplane's maintenance program
before or at the same time as this service bulletin.
DescriptionAWLDocumentCompany
Fuel Quantity Indicating System
(FQIS) - Out Of Tank Wiring Light-
ning Shield to Ground Termination
28-AWL-03747-400 Maintenance Planning Data
(MPD) Document, Section 9, Airworthi-
ness Limitations (AWLs) and Certifica-
tion Maintenance Requirements
(CMRs), D621U400-9, Revision August
2016 or later revision that has been
approved by the FAA Oversight Office
(Boeing Aviation Safety Oversight Of-
fice (BASOO))
Boeing
Wire Separation Requirements for
New Wiring Installed in Proximity to
Wiring That Goes Into the Fuel Tanks
28-AWL-08
Fuel Quantity Indicating System
(FQIS), Single Point Sensor (SPS),
and Auxiliary Fuel Tank (Cell) Elec-
tronic Fuel Level Indication (EFLI) -
In-Tank Hardware Installation - Sep-
aration From Structure (FQIS Tank
Units, Compensators, SPS, and
Auxiliary Fuel Tank (Cell) EFLI
Probes (If Installed)
28-AWL-14
Visible Means of Identification for
Fuel Quantity Indicating System
(FQIS) Wiring that Goes into the
Center Wing Tank
28-AWL-38
C. Reason
The changes given in this service bulletin will improve the wire routing for Fuel Quantity Indicating
System (FQIS) wire outside the fuel tank on 747-400F and 747-400 Boeing Converted Freighters (BCF)
aircraft. The FQIS wiring from the Fuel Quantity Processor Unit (FQPU) to the pressure seal area
station 1278 must be separated from other airplane system wiring. If this service bulletin is not done,
an undetected failure of the FQIS components inside the center wing tank (CWT), in combination with
an electrical hot short to FQIS wiring outside the tank, can cause ignition source of the fuel tank which
could result in smoke and/or fire in the fuel tank.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 12, 2018
747-28-2344
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BOEING SERVICE BULLETIN 747-28-2344

### Page 13

A Federal Aviation Administration (FAA) review of the Boeing Special Federal Aviation Regulation No.
88 (SFAR88) System Safety Assessment identified a non-safety fuel tank condition on delivered and
modified freighter airplanes which do not have Nitrogen Generating System (NGS) installed to reduce
flammability in the CWT. An investigation identified that the FQIS wiring was routed together with other
airplane system wires, which did not meet the 747 System Separation Requirement. The entire length
of the FQIS wire from the FQPU to the pressure seal area will be sleeved, to address areas where
increased separation is not possible.
This service bulletin gives instructions to do a General Visual Inspection for any damage to FQIS wire.
Install a bracket and standoff, then install pink sleeving over the FQIS wire from the FQPU to the
pressure seal area to identify it as an FQIS wire bundle with separation limitation. The change will meet
the wire separation requirements for FQIS wire from the other airplane system wires.
This service bulletin is the result of the safety assessments conducted by Boeing under a SFAR88,
Fuel Tank System Fault Tolerance Evaluation Requirements.
Boeing Service Related Problem (SRP) 747-SRP-28-0149 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 28-13004 is related to this service bulletin.
Sufficient data is not available to Boeing from operators to establish reliability and maintenance rates
to support cost benefit analysis. Operators should examine their own data to evaluate the impact to
their fleets.
D. Description
Group 1, 5:
Open access. Do a General Visual Inspection to find any damage to the FQIS wire bundle. Replace
an existing bracket and install a standoff. Change the FQIS wire bundle. Do the Fuel Quantity Indicating
System Operational Test. Close access.
Group 2, 7:
Open access. Do a General Visual Inspection to find any damage to the FQIS wire bundle. Replace
an existing bracket and install a standoff. Change the FQIS wire bundle. Remove the Single Point
Sensor (SPS) wires X1012 (S283U007-312) from the wheel well spar connector and X1011
(S283U007-502) from the CWT. Do the Fuel Quantity Indicating System Operational Test. Close access.
Group 3:
Open access. Do a General Visual Inspection to find any damage to the FQIS wire bundle. Replace
an existing bracket and install a standoff. Change the FQIS wire bundle. Remove the SPS wires X1012
(S283U007-312) from the wheel well spar connector, and X1011 (S283U007-502) from CWT. Do the
Fuel Quantity Indicating System Operational Test. Close access.
Group 4, 6, 8:
Open access. Do a General Visual Inspection to find any damage to the FQIS wire bundle. Replace
an existing bracket and install a standoff. Change the FQIS wire bundle. Do the Fuel Quantity Indicating
System Operational Test. Close access.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Group 1, 6:
Affected Maintenance Zones
ZoneModel
123, 241747-400F
Group 2-3, 7:
Affected Maintenance Zones
ZoneModel
123, 131, 241747-400
Group 4-5, 8:
Affected Maintenance Zones
ZoneModel
123, 241747-400
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive (AD) related
to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in
this service bulletin mandatory.
Group 1, 5:
Table 1: FQIS WIRE BUNDLE CHANGE
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 60 months
after the Original
Issue date of this
service bulletin.
Do a General Visual In-
spection for any damage
to the FQIS wire bundle.
and
All Airplanes
Install bracket and stand-
off.
and
Do the change the FQIS
wire bundle in accor-
dance with Accomplish-
ment Instructions 3.B.2,
3.B.6.
(a)
-Before further
flight.
Repair the FQIS wire
bundle.
CONDITION 1: ANY DAM-
AGE IS FOUND ON FQIS
WIRE BUNDLE
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Group 1, 5:
Table 1: FQIS WIRE BUNDLE CHANGE
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
--No repair is required.CONDITION 2: NO DAM-
AGE FOUND ON FQIS
WIRE BUNDLE
(a) These changes are required to be accomplished at the same maintenance visit.
Group 2, 7:
Table 2: FQIS WIRE BUNDLE CHANGE
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 60 months
after the Original
Issue date of this
service bulletin.
Do a General Visual In-
spection for any damage
to the FQIS wire bundle.
and
All Airplanes
Install bracket and stand-
off.
and
Do the change the FQIS
wire bundle.
and
Remove the SPS wire
X1012 (S283U007-312)
from the wheel well spar
connector, and X1011
(S283U007-502) from
CWT, in accordance with
Accomplishment Instruc-
tions 3.B.3, 3.B.8.
(a)
-Before further
flight.
Repair the FQIS wire
bundle.
CONDITION 1: ANY DAM-
AGE IS FOUND ON FQIS
WIRE BUNDLE
--No repair is required.CONDITION 2: NO DAM-
AGE FOUND ON FQIS
WIRE BUNDLE
(a) These changes are required to be accomplished at the same maintenance visit.
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### Page 16

Group 3:
Table 3: FQIS WIRE BUNDLE CHANGE
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 60 months
after the Original
Issue date of this
service bulletin.
Do a General Visual In-
spection for any damage
to the FQIS wire bundle.
and
All Airplanes
Install bracket and stand-
off.
and
Do the change the FQIS
wire bundle.
and
Remove the SPS wire
X1012 (S283U007-312)
from the wheel well spar
connector, and X1011
(S283U007-502) from
CWT in accordance with
Accomplishment Instruc-
tions 3.B.4.
(a)
-Before further
flight.
Repair the FQIS wire
bundle.
CONDITION 1: ANY DAM-
AGE IS FOUND ON FQIS
WIRE BUNDLE
--No repair is required.CONDITION 2: NO DAM-
AGE FOUND ON FQIS
WIRE BUNDLE
(a) These changes are required to be accomplished at the same maintenance visit.
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### Page 17

Group 4, 6, 8:
Table 4: FQIS WIRE BUNDLE CHANGE
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 60 months
after the Original
Issue date of this
service bulletin.
Do a General Visual In-
spection for any damage
to the FQIS wire bundle.
and
All Airplanes
Install bracket and stand-
off.
and
Do the change the FQIS
wire bundle, in accor-
dance with Accomplish-
ment Instructions 3.B.5,
3.B.7, 3.B.9.
(a)
-Before further
flight.
Repair the FQIS wire
bundle.
CONDITION 1: ANY DAM-
AGE IS FOUND ON FQIS
WIRE BUNDLE
--No repair is required.CONDITION 2: NO DAM-
AGE FOUND ON FQIS
WIRE BUNDLE
(a) These changes are required to be accomplished at the same maintenance visit.
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
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### Page 18

• Time to make the parts
• Time to find the tools.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Open Access
1.501.501Figure 1
(a)(a)-Repair (a)
1.751.751Figure 3
5.5011.002Figure 4 and Figure
7
4.509.002Close Access
1.251.251Test
19.0033.50TOTAL FOR EACH AIRPLANE
(a) If CONDITION 1 is found, the hours to do the repair will change.
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Open Access and
Defuel
1.501.501Figure 2
(a)(a)-Repair (a)
1.751.751Figure 3
5.5011.002Figure 5 and Figure
8
3.406.802Figure 6 and Figure
9
4.509.002Close Access
1.251.251Test
22.4040.30TOTAL FOR EACH AIRPLANE
(a) If CONDITION 1 is found, the hours to do the repair will change.
Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Open Access and
Defuel
1.501.501Figure 2
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Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
(a)(a)-Repair (a)
1.751.751Figure 3
5.5011.002Figure 4 and Figure
7
3.406.802Figure 6 and Figure
9
4.509.002Close Access
1.251.251Test
22.4040.30TOTAL FOR EACH AIRPLANE
(a) If CONDITION 1 is found, the hours to do the repair will change.
Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Open Access
1.501.501Figure 2
(a)(a)-Repair (a)
1.751.751Figure 3
5.5011.002Figure 5 and Figure
8
4.509.002Close Access
1.251.251Test
19.0033.50TOTAL FOR EACH AIRPLANE
(a) If CONDITION 1 is found, the hours to do the repair will change.
Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Open Access
1.501.501Figure 2
(a)(a)-Repair (a)
1.751.751Figure 3
5.5011.002Figure 4 and Figure
7
4.509.002Close Access
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### Page 20

Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
1.251.251Test
19.0033.50TOTAL FOR EACH AIRPLANE
(a) If CONDITION 1 is found, the hours to do the repair will change.
Group 6:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Open Access
1.501.501Figure 1
(a)(a)-Repair (a)
1.751.751Figure 3
5.5011.002Figure 4 and Figure
7
4.509.002Close Access
1.251.251Test
19.0033.50TOTAL FOR EACH AIRPLANE
(a) If CONDITION 1 is found, the hours to do the repair will change.
Group 7:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Open Access and
Defuel
1.501.501Figure 2
(a)(a)-Repair (a)
1.751.751Figure 3
5.5011.002Figure 4 and Figure
7
3.406.802Figure 6 and Figure
9
4.509.002Close Access
1.251.251Test
22.4040.30TOTAL FOR EACH AIRPLANE
(a) If CONDITION 1 is found, the hours to do the repair will change.
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### Page 21

Group 8:
Elapsed HoursTask HoursNumber of PersonsTask
4.509.002Open Access
1.501.501Figure 2
(a)(a)-Repair (a)
1.751.751Figure 3
5.5011.002Figure 4 and Figure
7
4.509.002Close Access
1.251.251Test
19.0033.50TOTAL FOR EACH AIRPLANE
(a) If CONDITION 1 is found, the hours to do the repair will change.
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+ 1,637.0+ 1.6Group 1, 4-5, 6, 8
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+1,968.1+1.9Group 2-3, 7
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Engineering Change Memo PRR 85901-132RS
b. Boeing Service Related Problem (SRP) 747-SRP-28-0149
c. Service Bulletin Index D6-30300
d. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-43-03, 20-50-01, 20-50-19
e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-13, 20-10-19, 20-30-16
f. System Schematic Manual (SSM) 28-41-01
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### Page 22

g. 747-400 Maintenance Planning Data (MPD) Document, Section 9, Airworthiness Limitations
(AWLs) and Certification Maintenance Requirements (CMRs), D621U400-9, Revision August
2016 or later revision that has been approved by the FAA Oversight Office (Boeing Aviation
Safety Oversight Office (BASOO)
h. 747 Fleet Team Digest (FTD) 28-13004
i. 747-400 Aircraft Maintenance Manual (AMM) 20-60-04, 24-22-00, 25-52-05, 28-11-09,
28-17-09, 28-26-00, 28-41-00, 28-41-09, 32-00-15, 32-00-30, 53-21-02
j. 747-400 Wiring Diagram Manual (WDM) 28-41-11, 28-41-24
k. 747-400SF Structural Repair Manual (SRM) 51-40-04
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
WIRE BUNDLE INSTALLATION - CARGO AREA FLOOR BEAMS,
STA 723 THRU 997.
288U4229
WIRE BUNDLE INSTALLATION - FORWARD CARGO AREA
BULKHEAD, STA 1000
288U4232
WIRE BUNDLE INSTALLATION - PRESSURE DECK AND MAIN
DECK FLR BEAMS LH, STA 997 THRU 1243
288U4411
WIRE BUNDLE INSTALLATION - PRESSURE DECK AND MAIN
DECK FLR BMS LH, STA 1243 THRU 1483
288U4431
REAR SPAR INSTL - WING CENTER SECTION111U1000
WIRE BUNDLE INSTL - FORWARD WHEEL WELL LH, STA 1241
THRU 1350.
288U4427
WIRE BUNDLE INSTALLATION - WING CENTER SECTION, LH288U1191
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
28-41747 Wiring Diagram Manual
28-41747 System Schematic Manual
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### Page 23

Chapter-SectionPublication
Section 9 - Airworthiness Limitations
(AWLs) and Certification Mainte-
nance Requirements (CMRs)
747-400 Maintenance Planning Data (MPD)
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
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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BLANK PAGE

### Page 25

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits/parts 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/parts 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
Group 1, 5-6, 8:
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 date of this
Service Bulletin
(US Dollars)
ROLT as of the
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameNumber
$2,613.0024420June 22, 2016Top Kit - Fuel Quantity
Indicating System -
Wire Separation
015U2132-1
20July 22, 2016
20August 22,
2016
20October 17,
2016
Group 2:
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 date of this
Service Bulletin
(US Dollars)
ROLT as of the
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameNumber
$3,652.002446October 17,
2016
Top Kit - Fuel Quantity
Indicating System -
Wire Separation
015U2132-2
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### Page 26

Group 3, 7:
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 date of this
Service Bulletin
(US Dollars)
ROLT as of the
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameNumber
$3,652.002441 (a)July 18, 2016
(a)
Top Kit - Fuel Quantity
Indicating System -
Wire Separation
015U2132-3
4July 15, 2016
11July 26, 2016
(a) A quantity of 1 kit will be available on July 18, 2016, for the validation of this service bulletin.
Group 4:
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 date of this
Service Bulletin
(US Dollars)
ROLT as of the
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameNumber
$2,613.002442August 03,
2016
Top Kit - Fuel Quantity
Indicating System -
Wire Separation
015U2132-4
Operators are encouraged to complete the survey provided in Appendix A of this service bulletin to
help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
Figure Kit
6543Top Kit
--11015U2132-1
11-1015U2132-2
1-11015U2132-3
-1-1015U2132-4
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### Page 27

Group 1, 5-6, 8:
KIT 015U2132-1
Notes
Existing Part
NumberName
Figure
New Part Number
43
Qty
(a)LABEL -
015U2132-201
14.015U2132-40
BMS13-54 LACING
TAPE
1.015U2132-101
Sleeving, Pink1.015U2132-102
(a)CLAMP83.287T0011-3
SLEEVE,
TFE-2X
SLEEVE2.65C38488-2
747-400F FQIS
WIRE SEPARA-
TION BRACKET
ASSY
.1672U7108-1
NUT CLIP-ON10.BACN10FX83
(a)SPACER PLATE
NUT
.6BACN10TL3A6
(a)(b)RIVET, UNIVER-
SAL HEAD
.11BACR15BB4D5C
(a)(b)RIVET, UNIVER-
SAL HD
.6BACR15BB5D6C
(b)BOLT2.BACS12HN3-6
(c)BOLT10.BACS12HN3-9
(a)(b)BOLT13.BACS12HN3-10
(a)(b)Screw18.BACS12HN3-23
SCREW2.BACS12HN3-31
(a)RINGPOST, WIRE
HARNESS
MOUNTING SUP-
PORT
12.BACS31H1B
(c)RINGPOST, WIRE
HARNESS
MOUNTING SUP-
PORT
14.BACS31H2B
(a)STRAP75.BACS38K10
(a)STRAP34.BACS38W3
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Group 1, 5-6, 8:
KIT 015U2132-1
Notes
Existing Part
NumberName
Figure
New Part Number
43
Qty
TIE PLATE2.MTP4H-E10
SPACERS FOR
RIVETS
17.NAS42DD6-32FC
(c)SPACERS FOR
RIVETS
1.NAS42DD6-48FC
(a)SPACERS FOR
BOLTS
18.NAS43DD6-16FC
(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.
(c) These parts are extra.
Group 2:
KIT 015U2132-2
Notes
Existing Part
NumberName
Figure
New Part Number
653
Qty
(a)LABEL -
015U2132-202
.14.015U2132-50
BMS13-54 LACING
TAPE
.1.015U2132-101
Sleeving, Pink.1.015U2132-102
PLUG1..111U1004-2
COVER2..111U1005-1
(a)CLAMP.83.287T0011-3
SLEEVE,
TFE-2X
SLEEVE.2.65C38488-2
747-400F FQIS
WIRE SEPARA-
TION BRACKET
ASSY
..1672U7108-1
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### Page 29

Group 2:
KIT 015U2132-2
Notes
Existing Part
NumberName
Figure
New Part Number
653
Qty
(a)(b)SHOULDER BOLT4..BACB30LM3-10
NUT CLIP-ON.10.BACN10FX83
(a)SPACER PLATE
NUT
..6BACN10TL3A6
(a)NUT4..BACN11Z3CD
(a)(b)RIVET, UNIVER-
SAL HEAD
..11BACR15BB4D5C
(a)(b)RIVET, UNIVER-
SAL HD
..6BACR15BB5D6C
(b)BOLT.2.BACS12HN3-6
(c)BOLT.10.BACS12HN3-9
(a)(b)BOLT.13.BACS12HN3-10
(a)(b)Screw.18.BACS12HN3-23
(a)(b)SCREW.2.BACS12HN3-31
(a)RINGPOST, WIRE
HARNESS
MOUNTING SUP-
PORT
.12.BACS31H1B
(c)RINGPOST, WIRE
HARNESS
MOUNTING SUP-
PORT
.14.BACS31H2B
(a)STRAP.75.BACS38K10
(a)STRAP.34.BACS38W3
TIE PLATE.2.MTP4H-E10
(a)WASHER6..NAS1149D0332J
SPACERS FOR
RIVETS
.17.NAS42DD6-32FC
(c)SPACERS FOR
RIVETS
.1.NAS42DD6-48FC
(a)SPACERS FOR
BOLTS
.18.NAS43DD6-16FC
(a) There are more parts than are necessary.
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### Page 30

Group 2:
KIT 015U2132-2
Notes
Existing Part
NumberName
Figure
New Part Number
653
Qty
(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.
(c) These parts are extra.
Group 3, 7:
KIT 015U2132-3
Notes
Existing Part
NumberName
Figure
New Part Number
643
Qty
(a)LABEL -
015U2132-201
.14.015U2132-40
BMS13-54 LACING
TAPE
.1.015U2132-101
Sleeving, Pink.1.015U2132-102
PLUG1..111U1004-2
COVER2..111U1005-1
(a)CLAMP.83.287T0011-3
SLEEVE,
TFE-2X
SLEEVE.2.65C38488-2
747-400F FQIS
WIRE SEPARA-
TION BRACKET
ASSY
..1672U7108-1
(a)(b)SHOULDER BOLT4..BACB30LM3-10
NUT CLIP-ON.10.BACN10FX83
SPACER PLATE
NUT
..6BACN10TL3A6
(a)NUT4..BACN11Z3CD
(a)(b)RIVET, UNIVER-
SAL HEAD
..11BACR15BB4D5C
(a)(b)RIVET, UNIVER-
SAL HD
..6BACR15BB5D6C
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Group 3, 7:
KIT 015U2132-3
Notes
Existing Part
NumberName
Figure
New Part Number
643
Qty
(b)BOLT.2.BACS12HN3-6
(c)BOLT.10.BACS12HN3-9
(a)(b)BOLT.13.BACS12HN3-10
(a)(b)Screw.18.BACS12HN3-23
(a)(b)SCREW.2.BACS12HN3-31
(a)RINGPOST, WIRE
HARNESS
MOUNTING SUP-
PORT
.12.BACS31H1B
(c)RINGPOST, WIRE
HARNESS
MOUNTING SUP-
PORT
.14.BACS31H2B
(a)STRAP.75.BACS38K10
(a)STRAP.34.BACS38W3
TIE PLATE.2.MTP4H-E10
(a)WASHER6..NAS1149D0332J
SPACERS FOR
RIVETS
.17.NAS42DD6-32FC
(c)SPACERS FOR
RIVETS
.1.NAS42DD6-48FC
(a)SPACERS FOR
BOLTS
.18.NAS43DD6-16FC
(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.
(c) These parts are extra.
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Group 4:
KIT 015U2132-4
Notes
Existing Part
NumberName
Figure
New Part Number
53
Qty
(a)LABEL -
015U2132-202
14.015U2132-50
BMS13-54 LACING
TAPE
1.015U2132-101
Sleeving, Pink1.015U2132-102
(a)CLAMP83.287T0011-3
SLEEVE,
TFE-2X
SLEEVE2.65C38488-2
747-400F FQIS
WIRE SEPARA-
TION BRACKET
ASSY
.1672U7108-1
NUT CLIP-ON10.BACN10FX83
SPACER PLATE
NUT
.6BACN10TL3A6
(a)(b)RIVET, UNIVER-
SAL HEAD
.11BACR15BB4D5C
(a)(b)RIVET, UNIVER-
SAL HD
.6BACR15BB5D6C
(b)BOLT2.BACS12HN3-6
(c)BOLT10.BACS12HN3-9
(a)(b)BOLT13.BACS12HN3-10
(a)(b)Screw18.BACS12HN3-23
(a)(b)SCREW2.BACS12HN3-31
(a)RINGPOST, WIRE
HARNESS
MOUNTING SUP-
PORT
12.BACS31H1B
(c)RINGPOST, WIRE
HARNESS
MOUNTING SUP-
PORT
14.BACS31H2B
(a)STRAP75.BACS38K10
(a)STRAP34.BACS38W3
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### Page 33

Group 4:
KIT 015U2132-4
Notes
Existing Part
NumberName
Figure
New Part Number
53
Qty
TIE PLATE2.MTP4H-E10
SPACERS FOR
RIVETS
17.NAS42DD6-32FC
(c)SPACERS FOR
RIVETS
1.NAS42DD6-48FC
(a)SPACERS FOR
BOLTS
18.NAS43DD6-16FC
(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.
(c) These parts are extra.
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
Group 2-3, 7:
NotesNameQTYPart Number / Specification
(a)Sealant8 OzBMS5-45, CLASS B
(a)Primer (Yellow)2 OzBMS10-11, TYPE I
(a)Chemical Conversion Coating2 OzALODINE 600
END CAP8324486
CAP1M83723-60-112AN
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
3. Parts Modified and Reidentified
None.
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4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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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 and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 747 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 747
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
6. The necessary conditions for selection of clamp type and size are included in SWPM
20-10-12. If any wire bundle support clamp specified in this service bulletin does not
make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted
procedure to select a clamp that fits correctly.
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7. 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. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
8. 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.
9. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure or irregularity.
This level of inspection is made from within touching distance unless otherwise
specified. A mirror may be necessary to enhance visual access to all exposed surfaces
in the inspection area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may
require removal or opening of access panels or doors. Stands, ladders or platforms
may be required to gain proximity to the area being checked.
10. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
11. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
12. 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.
13. 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.
14. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
15. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
16. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
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17. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. An Alternative Method of
Compliance (AMOC) is required for any deviations to RC steps, including sub-steps
and identified figures. Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection program without
obtaining approval of an AMOC. This is provided that the RC steps, including
sub-steps and identified figures, can still be done as specified, and the airplane can
be put back in an airworthy condition.
B. WORK INSTRUCTIONS
1. Remove electrical power from the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
2. Group 1:
a. Open access to the FQIS wire bundle X1008 (S283U007-518).
(1) Remove and keep the forward left cargo compartment floor panels between station 780
to station 970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
(2) Remove and keep left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(3) Do a General Visual Inspection of the wire bundle for contamination between station 780
and pressure seal area, and remove all contamination. Contamination includes combustible
material such as dust, lint, and other surface contamination. Refer to 747-400 AMM
20-60-04 as an accepted procedure.
b. RC - Do a General Visual Inspection for any damage to the FQIS wire bundle, between station
780 and the pressure seal area, in accordance with FIGURE 1.
CONDITION 1: ANY DAMAGE IS FOUND ON FQIS WIRE BUNDLE
(1) Repair the FQIS wire bundle. Refer to SWPM 20-10-13 as an accepted procedure.
CONDITION 2: NO DAMAGE FOUND ON FQIS WIRE BUNDLE
(1) No repair required.
c. RC- Install a bracket and standoff in accordance with FIGURE 3.
d. RC - Do the change of the FQIS wire bundle and wire routing, from the Fuel Quantity Processor
Unit (FQPU) station 780 to the pressure seal area, in accordance with FIGURE 4 and FIGURE
7.
e. RC - Make sure that any existing wiring with a separation of 2.0 inches or less from the altered
FQIS wiring that was completed in FIGURE 4, at any routing location from the FQPU Station
780 to the pressure seal area station 1278, meets the following separation/sleeving criteria:
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(1) For existing wiring carrying data signals such as Coaxial, USB, or Ethernet wiring, the
installation and separation requirements of the Standard Wiring Practices Manual (SWPM)
apply.
(2) For all other existing wiring installed on the airplane, the final configuration must meet
the requirements of steps 2(a) through 2(d). If the existing wire types are not the following:
BMS 13-48, BMS 13-60, BMS 13-58, BMS 13-51, MIL-W-81381, and BMS 13-35, OR
are not the following existing wire types that have been approved by the FAA Seattle
Aircraft Certification Office (not certified as part of Boeing Type Design): MIL-W-22759/16,
MIL-W-22759/32, MIL-W-22759/34, MIL-W-22759/41, MIL-W-22759/86, MIL-W-22759/87,
MIL-W-22759/92, and MIL-C-27500 cables constructed from these wire types, contact
FAA Oversight Office (Seattle Aircraft Certification Office) for configuration approval.
(a) For existing wiring installed in parallel to the FQIS wiring with a separation between
2.0 inches and 0.5 inch, maintain a separation of no less than 0.5 inch from the FQIS
wiring under any single failure of a support point.
(b) For existing wiring installed in parallel to the FQIS wiring with a separation less than
0.5 inch, sleeve the existing wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 1.0 inch
beyond the point where the separation is less than 0.5 inch.
(c) For existing wiring that crosses the FQIS wiring with a separation between 2.0 inches
and 0.5 inch from the FQIS wiring, maintain a separation of no less than 0.5 inch
from the FQIS wiring under any single failure of a support point.
(d) For existing wiring that crosses the FQIS wiring with a separation less than 0.5 inch
from the FQIS wiring, the following requirements also apply:
1) Sleeve the existing wiring wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 6.0
inches on either side of the crossing point.
2) Maintain a separation of no less than 0.25 inch from the FQIS wiring at the
crossing point using a mechanical device such as a spacer or a clamp.
f. Close access
(1) Install the kept left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(2) Install the kept forward left cargo compartment floor panels between station 780 to station
970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
g. Supply electrical power to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
h. RC - Do the Fuel Quantity Indicating System (FQIS) - Operational Test. If the test fail, do
corrective actions, repeat the test, and do applicable corrective actions until passes the test.
Refer to 747-400 AMM 28-41-00 as an accepted procedure.
i. Put the airplane back to a serviceable condition.
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3. Group 2:
WARNING: MAKE SURE THAT THE GROUND LOCKS ARE INSTALLED IN ALL OF THE
LANDING GEAR. WITHOUT THE GROUND LOCKS, THE LANDING GEAR CAN
RETRACT. THIS CAN CAUSE INJURIES TO PERSONNEL, AND DAMAGE TO
EQUIPMENT.
a. Make sure Landing Gear Ground Locks are installed on the landing gears. Refer to 747-400
AMM 32-00-15 as an accepted procedure.
WARNING: OBEY THE INSTALLATION PROCEDURE FOR THE DOOR LOCKS. THE DOORS
OPEN AND CLOSE QUICKLY. THE MOVEMENT OF THE DOORS CAN CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
b. Make sure the Landing Gear Door Locks are installed on the landing gear doors. Refer to
747-400 AMM 32-00-30 as an accepted procedure.
c. Defuel the center wing tank (CWT). Refer to 747-400 AMM 28-26-00 as an accepted procedure.
d. Open access to the inside rear spar of the CWT through access door 131EZ or 132CZ and
the spanwise beam access doors. Refer to 747-400 AMM 28-11-09 as an accepted procedure.
e. Open access to the FQIS wire bundle X1008 (S283U007-518 or S283U007-318).
(1) Remove and keep the forward left cargo compartment floor panels between station 780
to station 970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
(2) Remove and keep left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(3) Do a General Visual Inspection of the wire bundle for contamination between station 780
and pressure seal area, and remove all contamination. Contamination includes combustible
material such as dust, lint, and other surface contamination. Refer to 747-400 AMM
20-60-04 as an accepted procedure.
f. RC - Do a General Visual Inspection for any damage to the FQIS wire bundle, between station
780 and the pressure seal area, in accordance with FIGURE 2.
CONDITION 1: ANY DAMAGE IS FOUND ON FQIS WIRE BUNDLE
(1) Repair the FQIS wire bundle. Refer to SWPM 20-10-13 as an accepted procedure.
CONDITION 2: NO DAMAGE FOUND ON FQIS WIRE BUNDLE
(1) No repair required.
g. RC- Install a bracket and standoff in accordance with FIGURE 3.
h. RC - Do the change of the FQIS wire bundle and wire routing, from the Fuel Quantity Processor
Unit (FQPU) station 780 to the pressure seal area, in accordance with FIGURE 5 and FIGURE
8.
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i. RC - Make sure that any existing wiring with a separation of 2.0 inches or less from the altered
FQIS wiring that was completed in FIGURE 5, at any routing location from the FQPU Station
780 to the pressure seal area station 1278, meets the following separation/sleeving criteria:
(1) For existing wiring carrying data signals such as Coaxial, USB, or Ethernet wiring, the
installation and separation requirements of the Standard Wiring Practices Manual (SWPM)
apply.
(2) For all other existing wiring installed on the airplane, the final configuration must meet
the requirements of steps 2(a) through 2(d). If the existing wire types are not the following:
BMS 13-48, BMS 13-60, BMS 13-58, BMS 13-51, MIL-W-81381, and BMS 13-35, OR
are not the following existing wire types that have been approved by the FAA Seattle
Aircraft Certification Office (not certified as part of Boeing Type Design): MIL-W-22759/16,
MIL-W-22759/32, MIL-W-22759/34, MIL-W-22759/41, MIL-W-22759/86, MIL-W-22759/87,
MIL-W-22759/92, and MIL-C-27500 cables constructed from these wire types, contact
FAA Oversight Office (Seattle Aircraft Certification Office) for configuration approval.
(a) For existing wiring installed in parallel to the FQIS wiring with a separation between
2.0 inches and 0.5 inch, maintain a separation of no less than 0.5 inch from the FQIS
wiring under any single failure of a support point.
(b) For existing wiring installed in parallel to the FQIS wiring with a separation less than
0.5 inch, sleeve the existing wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 1.0 inch
beyond the point where the separation is less than 0.5 inch.
(c) For existing wiring that crosses the FQIS wiring with a separation between 2.0 inches
and 0.5 inch from the FQIS wiring, maintain a separation of no less than 0.5 inch
from the FQIS wiring under any single failure of a support point.
(d) For existing wiring that crosses the FQIS wiring with a separation less than 0.5 inch
from the FQIS wiring, the following requirements also apply:
1) Sleeve the existing wiring wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 6.0
inches on either side of the crossing point.
2) Maintain a separation of no less than 0.25 inch from the FQIS wiring at the
crossing point using a mechanical device such as a spacer or a clamp.
j. RC - Remove the Single Point Sensor (SPS) wire X1012 (S283U007-312) from the wheel
well spar connector, and X1011 (S283U007-502) from CWT in accordance with FIGURE 6
and FIGURE 9.
k. Close access
(1) Close access to the inside rear spar of the CWT through access door 131EZ or 132CZ
and the spanwise beam access doors. Refer to 747-400 AMM 28-11-09 as an accepted
procedure.
(2) Install the kept left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
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(3) Install the kept forward left cargo compartment floor panels between station 780 to station
970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
(4) Remove the Landing Gear Ground Locks. Refer to 747-400 AMM 32-00-15 as an accepted
procedure.
(5) Remove the Landing Gear Door Locks. Refer to 747-400 AMM 32-00-30 as an accepted
procedure.
l. Supply electrical power to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
m. RC - Do the Fuel Quantity Indicating System (FQIS) - Operational Test. If the test fail, do
corrective actions, repeat the test, and do applicable corrective actions until passes the test.
Refer to 747-400 AMM 28-41-00 as an accepted procedure.
n. Put the airplane back to a serviceable condition.
4. Group 3:
WARNING: MAKE SURE THAT THE GROUND LOCKS ARE INSTALLED IN ALL OF THE
LANDING GEAR. WITHOUT THE GROUND LOCKS, THE LANDING GEAR CAN
RETRACT. THIS CAN CAUSE INJURIES TO PERSONNEL, AND DAMAGE TO
EQUIPMENT.
a. Make sure Landing Gear Ground Locks are installed on the landing gears. Refer to 747-400
AMM 32-00-15 as an accepted procedure.
WARNING: OBEY THE INSTALLATION PROCEDURE FOR THE DOOR LOCKS. THE DOORS
OPEN AND CLOSE QUICKLY. THE MOVEMENT OF THE DOORS CAN CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
b. Make sure the Landing Gear Door Locks are installed on the landing gear doors. Refer to
747-400 AMM 32-00-30 as an accepted procedure.
c. Defuel the center wing tank (CWT). Refer to 747-400 AMM 28-26-00 as an accepted procedure.
d. Open access to the inside rear spar of the CWT through access door 131EZ or 132CZ and
the spanwise beam access doors. Refer to 747-400 AMM 28-11-09 as an accepted procedure.
e. Open access to the FQIS wire bundle X1008 (S283U007-518 or S283U007-318).
(1) Remove and keep the forward left cargo compartment floor panels between station 780
to station 970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
(2) Remove and keep left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(3) Do a General Visual Inspection of the wire bundle for contamination between station 780
and pressure seal area, and remove all contamination. Contamination includes combustible
material such as dust, lint, and other surface contamination. Refer to 747-400 AMM
20-60-04 as an accepted procedure.
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f. RC - Do a General Visual Inspection for any damage to the FQIS wire bundle, between station
780 and the pressure seal area, in accordance with FIGURE 2.
CONDITION 1: ANY DAMAGE IS FOUND ON FQIS WIRE BUNDLE
(1) Repair the FQIS wire bundle. Refer to SWPM 20-10-13 as an accepted procedure.
CONDITION 2: NO DAMAGE FOUND ON FQIS WIRE BUNDLE
(1) No repair required.
g. RC- Install a bracket and standoff in accordance with FIGURE 3.
h. RC - Do the change of the FQIS wire bundle and wire routing, from the Fuel Quantity Processor
Unit (FQPU) station 780 to the pressure seal area, in accordance with FIGURE 4 and FIGURE
7.
i. RC - Make sure that any existing wiring with a separation of 2.0 inches or less from the altered
FQIS wiring that was completed in FIGURE 4, at any routing location from the FQPU Station
780 to the pressure seal area station 1278, meets the following separation/sleeving criteria:
(1) For existing wiring carrying data signals such as Coaxial, USB, or Ethernet wiring, the
installation and separation requirements of the Standard Wiring Practices Manual (SWPM)
apply.
(2) For all other existing wiring installed on the airplane, the final configuration must meet
the requirements of steps 2(a) through 2(d). If the existing wire types are not the following:
BMS 13-48, BMS 13-60, BMS 13-58, BMS 13-51, MIL-W-81381, and BMS 13-35, OR
are not the following existing wire types that have been approved by the FAA Seattle
Aircraft Certification Office (not certified as part of Boeing Type Design): MIL-W-22759/16,
MIL-W-22759/32, MIL-W-22759/34, MIL-W-22759/41, MIL-W-22759/86, MIL-W-22759/87,
MIL-W-22759/92, and MIL-C-27500 cables constructed from these wire types, contact
FAA Oversight Office (Seattle Aircraft Certification Office) for configuration approval.
(a) For existing wiring installed in parallel to the FQIS wiring with a separation between
2.0 inches and 0.5 inch, maintain a separation of no less than 0.5 inch from the FQIS
wiring under any single failure of a support point.
(b) For existing wiring installed in parallel to the FQIS wiring with a separation less than
0.5 inch, sleeve the existing wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 1.0 inch
beyond the point where the separation is less than 0.5 inch.
(c) For existing wiring that crosses the FQIS wiring with a separation between 2.0 inches
and 0.5 inch from the FQIS wiring, maintain a separation of no less than 0.5 inch
from the FQIS wiring under any single failure of a support point.
(d) For existing wiring that crosses the FQIS wiring with a separation less than 0.5 inch
from the FQIS wiring, the following requirements also apply:
1) Sleeve the existing wiring wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 6.0
inches on either side of the crossing point.
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### Page 43

2) Maintain a separation of no less than 0.25 inch from the FQIS wiring at the
crossing point using a mechanical device such as a spacer or a clamp.
j. RC - Remove the SPS wire X1012 (S283U007-312) from the wheel well spar connector, and
X1011 (S283U007-502) from CWT in accordance with FIGURE 6 and FIGURE 9.
k. Close access
(1) Close access to the inside rear spar of the CWT through access door 131EZ or 132CZ
and the spanwise beam access doors. Refer to 747-400 AMM 28-11-09 as an accepted
procedure.
(2) Install the kept left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(3) Install the kept forward left cargo compartment floor panels between station 780 to station
970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
(4) Remove the Landing Gear Ground Locks. Refer to 747-400 AMM 32-00-15 as an accepted
procedure.
(5) Remove the Landing Gear Door Locks. Refer to 747-400 AMM 32-00-30 as an accepted
procedure.
l. Supply electrical power to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
m. RC - Do the Fuel Quantity Indicating System (FQIS) - Operational Test. If the test fail, do
corrective actions, repeat the test, and do applicable corrective actions until passes the test.
Refer to 747-400 AMM 28-41-00 as an accepted procedure.
n. Put the airplane back to a serviceable condition.
5. Group 4:
a. Open access to the FQIS wire bundle X1008 (S283U007-518 or S283U007-318).
(1) Remove and keep the forward left cargo compartment floor panels between station 780
to station 970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
(2) Remove and keep left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(3) Do a General Visual Inspection of the wire bundle for contamination between station 780
and pressure seal area, and remove all contamination. Contamination includes combustible
material such as dust, lint, and other surface contamination. Refer to 747-400 AMM
20-60-04 as an accepted procedure.
b. RC - Do a General Visual Inspection for any damage to the FQIS wire bundle, between station
780 and the pressure seal area, in accordance with FIGURE 2.
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### Page 44

CONDITION 1: ANY DAMAGE IS FOUND ON FQIS WIRE BUNDLE
(1) Repair the FQIS wire bundle. Refer to SWPM 20-10-13 as an accepted procedure.
CONDITION 2: NO DAMAGE FOUND ON FQIS WIRE BUNDLE
(1) No repair required.
c. RC- Install a bracket and standoff in accordance with FIGURE 3.
d. RC - Do the change of the FQIS wire bundle and wire routing, from the Fuel Quantity Processor
Unit (FQPU) station 780 to the pressure seal area, in accordance with FIGURE 5 and FIGURE
8.
e. RC - Make sure that any existing wiring with a separation of 2.0 inches or less from the altered
FQIS wiring that was completed in FIGURE 5, at any routing location from the FQPU Station
780 to the pressure seal area station 1278, meets the following separation/sleeving criteria:
(1) For existing wiring carrying data signals such as Coaxial, USB, or Ethernet wiring, the
installation and separation requirements of the Standard Wiring Practices Manual (SWPM)
apply.
(2) For all other existing wiring installed on the airplane, the final configuration must meet
the requirements of steps 2(a) through 2(d). If the existing wire types are not the following:
BMS 13-48, BMS 13-60, BMS 13-58, BMS 13-51, MIL-W-81381, and BMS 13-35, OR
are not the following existing wire types that have been approved by the FAA Seattle
Aircraft Certification Office (not certified as part of Boeing Type Design): MIL-W-22759/16,
MIL-W-22759/32, MIL-W-22759/34, MIL-W-22759/41, MIL-W-22759/86, MIL-W-22759/87,
MIL-W-22759/92, and MIL-C-27500 cables constructed from these wire types, contact
FAA Oversight Office (Seattle Aircraft Certification Office) for configuration approval.
(a) For existing wiring installed in parallel to the FQIS wiring with a separation between
2.0 inches and 0.5 inch, maintain a separation of no less than 0.5 inch from the FQIS
wiring under any single failure of a support point.
(b) For existing wiring installed in parallel to the FQIS wiring with a separation less than
0.5 inch, sleeve the existing wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 1.0 inch
beyond the point where the separation is less than 0.5 inch.
(c) For existing wiring that crosses the FQIS wiring with a separation between 2.0 inches
and 0.5 inch from the FQIS wiring, maintain a separation of no less than 0.5 inch
from the FQIS wiring under any single failure of a support point.
(d) For existing wiring that crosses the FQIS wiring with a separation less than 0.5 inch
from the FQIS wiring, the following requirements also apply:
1) Sleeve the existing wiring wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 6.0
inches on either side of the crossing point.
2) Maintain a separation of no less than 0.25 inch from the FQIS wiring at the
crossing point using a mechanical device such as a spacer or a clamp.
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### Page 45

f. Close access
(1) Install the kept left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(2) Install the kept forward left cargo compartment floor panels between station 780 to station
970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
g. Supply electrical power to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
h. RC - Do the Fuel Quantity Indicating System (FQIS) - Operational Test. If the test fail, do
corrective actions, repeat the test, and do applicable corrective actions until passes the test.
Refer to 747-400 AMM 28-41-00 as an accepted procedure.
i. Put the airplane back to a serviceable condition.
6. Group 5:
a. Open access to the FQIS wire bundle X1008 (S283U007-518 or S283U007-318).
(1) Remove and keep the forward left cargo compartment floor panels between station 780
to station 970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
(2) Remove and keep the left main deck floor panels between station 1000 to station 1280.
Refer to 747-400 AMM 53-21-02 as an accepted procedure.
(3) Do a General Visual Inspection of the wire bundle for contamination between station 780
and pressure seal area, and remove all contamination. Contamination includes combustible
material such as dust, lint, and other surface contamination. Refer to 747-400 AMM
20-60-04 as an accepted procedure.
b. RC - Do a General Visual Inspection for any damage to the FQIS wire bundle, between station
780 and the pressure seal area, in accordance with FIGURE 2.
CONDITION 1: ANY DAMAGE IS FOUND ON FQIS WIRE BUNDLE
(1) Repair the FQIS wire bundle. Refer to SWPM 20-10-13 as an accepted procedure.
CONDITION 2: NO DAMAGE FOUND ON FQIS WIRE BUNDLE
(1) No repair required.
c. RC- Install a bracket and standoff in accordance with FIGURE 3.
d. RC - Do the change of the FQIS wire bundle and wire routing, from the Fuel Quantity Processor
Unit (FQPU) station 780 to the pressure seal area, in accordance with FIGURE 4 and FIGURE
7.
e. RC - Make sure that any existing wiring with a separation of 2.0 inches or less from the altered
FQIS wiring that was completed in FIGURE 4, at any routing location from the FQPU Station
780 to the pressure seal area station 1278, meets the following separation/sleeving criteria:
Export Controlled ECCN: 9E991 - BOEING
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### Page 46

(1) For existing wiring carrying data signals such as Coaxial, USB, or Ethernet wiring, the
installation and separation requirements of the Standard Wiring Practices Manual (SWPM)
apply.
(2) For all other existing wiring installed on the airplane, the final configuration must meet
the requirements of steps 2(a) through 2(d). If the existing wire types are not the following:
BMS 13-48, BMS 13-60, BMS 13-58, BMS 13-51, MIL-W-81381, and BMS 13-35, OR
are not the following existing wire types that have been approved by the FAA Seattle
Aircraft Certification Office (not certified as part of Boeing Type Design): MIL-W-22759/16,
MIL-W-22759/32, MIL-W-22759/34, MIL-W-22759/41, MIL-W-22759/86, MIL-W-22759/87,
MIL-W-22759/92, and MIL-C-27500 cables constructed from these wire types, contact
FAA Oversight Office (Seattle Aircraft Certification Office) for configuration approval.
(a) For existing wiring installed in parallel to the FQIS wiring with a separation between
2.0 inches and 0.5 inch, maintain a separation of no less than 0.5 inch from the FQIS
wiring under any single failure of a support point.
(b) For existing wiring installed in parallel to the FQIS wiring with a separation less than
0.5 inch, sleeve the existing wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 1.0 inch
beyond the point where the separation is less than 0.5 inch.
(c) For existing wiring that crosses the FQIS wiring with a separation between 2.0 inches
and 0.5 inch from the FQIS wiring, maintain a separation of no less than 0.5 inch
from the FQIS wiring under any single failure of a support point.
(d) For existing wiring that crosses the FQIS wiring with a separation less than 0.5 inch
from the FQIS wiring, the following requirements also apply:
1) Sleeve the existing wiring wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 6.0
inches on either side of the crossing point.
2) Maintain a separation of no less than 0.25 inch from the FQIS wiring at the
crossing point using a mechanical device such as a spacer or a clamp.
f. Close access
(1) Install the kept left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(2) Install the kept forward left cargo compartment floor panels between station 780 to station
970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
g. Supply electrical power to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
h. RC - Do the Fuel Quantity Indicating System (FQIS) - Operational Test. If the test fail, do
corrective actions, repeat the test, and do applicable corrective actions until passes the test.
Refer to 747-400 AMM 28-41-00 as an accepted procedure.
i. Put the airplane back to a serviceable condition.
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### Page 47

7. Group 6:
a. Open access to the FQIS wire bundle X1008 (S283U007-518).
(1) Remove and keep the forward left cargo compartment floor panels between station 780
to station 970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
(2) Remove and keep left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(3) Do a General Visual Inspection of the wire bundle for contamination between station 780
and pressure seal area, and remove all contamination. Contamination includes combustible
material such as dust, lint, and other surface contamination. Refer to 747-400 AMM
20-60-04 as an accepted procedure.
b. RC - Do a General Visual Inspection for any damage to the FQIS wire bundle, between station
780 and the pressure seal area, in accordance with FIGURE 1.
CONDITION 1: ANY DAMAGE IS FOUND ON FQIS WIRE BUNDLE
(1) Repair the FQIS wire bundle. Refer to SWPM 20-10-13 as an accepted procedure.
CONDITION 2: NO DAMAGE FOUND ON FQIS WIRE BUNDLE
(1) No repair required.
c. RC- Install a bracket and standoff in accordance with FIGURE 3.
d. RC - Do the change of the FQIS wire bundle and wire routing, from the Fuel Quantity Processor
Unit (FQPU) station 780 to the pressure seal area, in accordance with FIGURE 4 and FIGURE
7.
e. RC - Make sure that any existing wiring with a separation of 2.0 inches or less from the altered
FQIS wiring that was completed in FIGURE 4, at any routing location from the FQPU Station
780 to the pressure seal area station 1278, meets the following separation/sleeving criteria:
(1) For existing wiring carrying data signals such as Coaxial, USB, or Ethernet wiring, the
installation and separation requirements of the Standard Wiring Practices Manual (SWPM)
apply.
(2) For all other existing wiring installed on the airplane, the final configuration must meet
the requirements of steps 2(a) through 2(d). If the existing wire types are not the following:
BMS 13-48, BMS 13-60, BMS 13-58, BMS 13-51, MIL-W-81381, and BMS 13-35, OR
are not the following existing wire types that have been approved by the FAA Seattle
Aircraft Certification Office (not certified as part of Boeing Type Design): MIL-W-22759/16,
MIL-W-22759/32, MIL-W-22759/34, MIL-W-22759/41, MIL-W-22759/86, MIL-W-22759/87,
MIL-W-22759/92, and MIL-C-27500 cables constructed from these wire types, contact
FAA Oversight Office (Seattle Aircraft Certification Office) for configuration approval.
(a) For existing wiring installed in parallel to the FQIS wiring with a separation between
2.0 inches and 0.5 inch, maintain a separation of no less than 0.5 inch from the FQIS
wiring under any single failure of a support point.
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 747-28-2344

### Page 48

(b) For existing wiring installed in parallel to the FQIS wiring with a separation less than
0.5 inch, sleeve the existing wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 1.0 inch
beyond the point where the separation is less than 0.5 inch.
(c) For existing wiring that crosses the FQIS wiring with a separation between 2.0 inches
and 0.5 inch from the FQIS wiring, maintain a separation of no less than 0.5 inch
from the FQIS wiring under any single failure of a support point.
(d) For existing wiring that crosses the FQIS wiring with a separation less than 0.5 inch
from the FQIS wiring, the following requirements also apply:
1) Sleeve the existing wiring wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 6.0
inches on either side of the crossing point.
2) Maintain a separation of no less than 0.25 inch from the FQIS wiring at the
crossing point using a mechanical device such as a spacer or a clamp.
f. Close access
(1) Install the kept left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(2) Install the kept forward left cargo compartment floor panels between station 780 to station
970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
g. Supply electrical power to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
h. RC - Do the Fuel Quantity Indicating System (FQIS) - Operational Test. If the test fail, do
corrective actions, repeat the test, and do applicable corrective actions until passes the test.
Refer to 747-400 AMM 28-41-00 as an accepted procedure.
i. Put the airplane back to a serviceable condition.
8. Group 7:
WARNING: MAKE SURE THAT THE GROUND LOCKS ARE INSTALLED IN ALL OF THE
LANDING GEAR. WITHOUT THE GROUND LOCKS, THE LANDING GEAR CAN
RETRACT. THIS CAN CAUSE INJURIES TO PERSONNEL, AND DAMAGE TO
EQUIPMENT.
a. Make sure Landing Gear Ground Locks are installed on the landing gears. Refer to 747-400
AMM 32-00-15 as an accepted procedure.
WARNING: OBEY THE INSTALLATION PROCEDURE FOR THE DOOR LOCKS. THE DOORS
OPEN AND CLOSE QUICKLY. THE MOVEMENT OF THE DOORS CAN CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
b. Make sure the Landing Gear Door Locks are installed on the landing gear doors. Refer to
747-400 AMM 32-00-30 as an accepted procedure.
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### Page 49

c. Defuel the center wing tank (CWT). Refer to 747-400 AMM 28-26-00 as an accepted procedure.
d. Open access to the inside rear spar of the CWT through access door 131EZ or 132CZ and
the spanwise beam access doors. Refer to 747-400 AMM 28-11-09 as an accepted procedure.
e. Open access to the FQIS wire bundle X1008 (S283U007-518 or S283U007-318).
(1) Remove and keep the forward left cargo compartment floor panels between station 780
to station 970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
(2) Remove and keep left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(3) Do a General Visual Inspection of the wire bundle for contamination between station 780
and pressure seal area, and remove all contamination. Contamination includes combustible
material such as dust, lint, and other surface contamination. Refer to 747-400 AMM
20-60-04 as an accepted procedure.
f. RC - Do a General Visual Inspection for any damage to the FQIS wire bundle, between station
780 and the pressure seal area, in accordance with FIGURE 2.
CONDITION 1: ANY DAMAGE IS FOUND ON FQIS WIRE BUNDLE
(1) Repair the FQIS wire bundle. Refer to SWPM 20-10-13 as an accepted procedure.
CONDITION 2: NO DAMAGE FOUND ON FQIS WIRE BUNDLE
(1) No repair required.
g. RC- Install a bracket and standoff in accordance with FIGURE 3.
h. RC - Do the change of the FQIS wire bundle and wire routing, from the Fuel Quantity Processor
Unit (FQPU) station 780 to the pressure seal area, in accordance with FIGURE 4 and FIGURE
7.
i. RC - Make sure that any existing wiring with a separation of 2.0 inches or less from the altered
FQIS wiring that was completed in FIGURE 4, at any routing location from the FQPU Station
780 to the pressure seal area station 1278, meets the following separation/sleeving criteria:
(1) For existing wiring carrying data signals such as Coaxial, USB, or Ethernet wiring, the
installation and separation requirements of the Standard Wiring Practices Manual (SWPM)
apply.
(2) For all other existing wiring installed on the airplane, the final configuration must meet
the requirements of steps 2(a) through 2(d). If the existing wire types are not the following:
BMS 13-48, BMS 13-60, BMS 13-58, BMS 13-51, MIL-W-81381, and BMS 13-35, OR
are not the following existing wire types that have been approved by the FAA Seattle
Aircraft Certification Office (not certified as part of Boeing Type Design): MIL-W-22759/16,
MIL-W-22759/32, MIL-W-22759/34, MIL-W-22759/41, MIL-W-22759/86, MIL-W-22759/87,
MIL-W-22759/92, and MIL-C-27500 cables constructed from these wire types, contact
FAA Oversight Office (Seattle Aircraft Certification Office) for configuration approval.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 12, 2018
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### Page 50

(a) For existing wiring installed in parallel to the FQIS wiring with a separation between
2.0 inches and 0.5 inch, maintain a separation of no less than 0.5 inch from the FQIS
wiring under any single failure of a support point.
(b) For existing wiring installed in parallel to the FQIS wiring with a separation less than
0.5 inch, sleeve the existing wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 1.0 inch
beyond the point where the separation is less than 0.5 inch.
(c) For existing wiring that crosses the FQIS wiring with a separation between 2.0 inches
and 0.5 inch from the FQIS wiring, maintain a separation of no less than 0.5 inch
from the FQIS wiring under any single failure of a support point.
(d) For existing wiring that crosses the FQIS wiring with a separation less than 0.5 inch
from the FQIS wiring, the following requirements also apply:
1) Sleeve the existing wiring wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 6.0
inches on either side of the crossing point.
2) Maintain a separation of no less than 0.25 inch from the FQIS wiring at the
crossing point using a mechanical device such as a spacer or a clamp.
j. RC - Remove the SPS wire X1012 (S283U007-312) from the wheel well spar connector, and
X1011 (S283U007-502) from CWT in accordance with FIGURE 6 and FIGURE 9.
k. Close access
(1) Close access to the inside rear spar of the CWT through access door 131EZ or 132CZ
and the spanwise beam access doors. Refer to 747-400 AMM 28-11-09 as an accepted
procedure.
(2) Install the kept left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(3) Install the kept forward left cargo compartment floor panels between station 780 to station
970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
(4) Remove the Landing Gear Ground Locks. Refer to 747-400 AMM 32-00-15 as an accepted
procedure.
(5) Remove the Landing Gear Door Locks. Refer to 747-400 AMM 32-00-30 as an accepted
procedure.
l. Supply electrical power to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
m. RC - Do the Fuel Quantity Indicating System (FQIS) - Operational Test. If the test fail, do
corrective actions, repeat the test, and do applicable corrective actions until passes the test.
Refer to 747-400 AMM 28-41-00 as an accepted procedure.
n. Put the airplane back to a serviceable condition.
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BOEING SERVICE BULLETIN 747-28-2344

### Page 51

9. Group 8:
a. Open access to the FQIS wire bundle X1008 (S283U007-518 or S283U007-318).
(1) Remove and keep the forward left cargo compartment floor panels between station 780
to station 970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
(2) Remove and keep the main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(3) Do a General Visual Inspection of the wire bundle for contamination between station 780
and pressure seal area, and remove all contamination. Contamination includes combustible
material such as dust, lint, and other surface contamination. Refer to 747-400 AMM
20-60-04 as an accepted procedure.
b. RC - Do a General Visual Inspection for any damage to the FQIS wire bundle is not damaged,
between station 780 and the pressure seal area in accordance with FIGURE 2.
CONDITION 1: ANY DAMAGE IS FOUND ON FQIS WIRE BUNDLE
(1) Repair the FQIS wire bundle. Refer to SWPM 20-10-13 as an accepted procedure.
CONDITION 2: NO DAMAGE FOUND ON FQIS WIRE BUNDLE
(1) No repair required.
c. RC- Install a bracket and standoff in accordance with FIGURE 3.
d. RC - Do the change of the FQIS wire bundle and wire routing, from the Fuel Quantity Processor
Unit (FQPU) station 780 to the pressure seal area, in accordance with FIGURE 4 and FIGURE
7.
e. RC - Make sure that any existing wiring with a separation of 2.0 inches or less from the altered
FQIS wiring that was completed in FIGURE 4, at any routing location from the FQPU Station
780 to the pressure seal area station 1278, meets the following separation/sleeving criteria:
(1) For existing wiring carrying data signals such as Coaxial, USB, or Ethernet wiring, the
installation and separation requirements of the Standard Wiring Practices Manual (SWPM)
apply.
(2) For all other existing wiring installed on the airplane, the final configuration must meet
the requirements of steps 2(a) through 2(d). If the existing wire types are not the following:
BMS 13-48, BMS 13-60, BMS 13-58, BMS 13-51, MIL-W-81381, and BMS 13-35, OR
are not the following existing wire types that have been approved by the FAA Seattle
Aircraft Certification Office (not certified as part of Boeing Type Design): MIL-W-22759/16,
MIL-W-22759/32, MIL-W-22759/34, MIL-W-22759/41, MIL-W-22759/86, MIL-W-22759/87,
MIL-W-22759/92, and MIL-C-27500 cables constructed from these wire types, contact
FAA Oversight Office (Seattle Aircraft Certification Office) for configuration approval.
(a) For existing wiring installed in parallel to the FQIS wiring with a separation between
2.0 inches and 0.5 inch, maintain a separation of no less than 0.5 inch from the FQIS
wiring under any single failure of a support point.
Export Controlled ECCN: 9E991 - BOEING
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### Page 52

(b) For existing wiring installed in parallel to the FQIS wiring with a separation less than
0.5 inch, sleeve the existing wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 1.0 inch
beyond the point where the separation is less than 0.5 inch.
(c) For existing wiring that crosses the FQIS wiring with a separation between 2.0 inches
and 0.5 inch from the FQIS wiring, maintain a separation of no less than 0.5 inch
from the FQIS wiring under any single failure of a support point.
(d) For existing wiring that crosses the FQIS wiring with a separation less than 0.5 inch
from the FQIS wiring, the following requirements also apply:
1) Sleeve the existing wiring wire bundle with TFE-2X Standard wall (manufactured
in accordance with MIL-I-23053). The sleeving must extend a minimum of 6.0
inches on either side of the crossing point.
2) Maintain a separation of no less than 0.25 inch from the FQIS wiring at the
crossing point using a mechanical device such as a spacer or a clamp.
f. Close access
(1) Install the kept left main deck floor panels between station 1000 to station 1280. Refer
to 747-400 AMM 53-21-02 as an accepted procedure.
(2) Install the kept forward left cargo compartment floor panels between station 780 to station
970. Refer to 747-400 AMM 25-52-05 as an accepted procedure.
g. Supply electrical power to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted
procedure.
h. RC - Do the Fuel Quantity Indicating System (FQIS) - Operational Test. If the test fail, do
corrective actions, repeat the test, and do applicable corrective actions until passes the test.
Refer to 747-400 AMM 28-41-00 as an accepted procedure.
i. Put the airplane back to a serviceable condition.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 12, 2018
747-28-2344
52 of 128
BOEING SERVICE BULLETIN 747-28-2344

### Page 53 (OCR)

BOEING SERVICE BULLETIN 747-28-2344
This Figure applies only to: Group 1, 6.
STA
1000  STA
1278
THROUGH
E6
FUEL QUANTITY
PROCESSOR
UNIT(FQPU)
2403056
FIGURE 1: LEFT SIDE - FQIS WIRE X1008 (S283U007-518) INSPECTION
(SHEET 1 OF 11)
Original Issue: October 12, 2018
Export Controlled ECCN: 9E991 - BOEING  747-28-2344
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  53 of 128

### Page 54 (OCR)

BOEING SERVICE BULLETIN 747-28-2344
E6 FUEL QUANTITY
PROCESSOR UNIT
STA
800
2401835
FIGURE 1: LEFT SIDE - FQIS WIRE X1008 (S283U007-518) INSPECTION
(SHEET 2 OF 11)
Original Issue: October 12, 2018
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.

### Page 55 (OCR)

BOEING SERVICE BULLETIN 747-28-2344
STA
840  STA
820
FIGURE 1: LEFT SIDE - FQIS WIRE X1008 (S283U007-518) INSPECTION
(SHEET 3 OF 11)
Original Issue: October 12, 2018
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  +EZ-82-L+L
Work - See page 1 for details.

### Page 56 (OCR)

BOEING SERVICE BULLETIN 747-28-2344
STA
880  STA
860
2401864
FIGURE 1: LEFT SIDE - FQIS WIRE X1008 (S283U007-518) INSPECTION
(SHEET 4 OF 11)
Original Issue: October 12, 2018
Export Controlled ECCN: 9E991 - BOEING  ₩ŁЕZ-8Z-LĐL
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  56 of 128

### Page 57 (OCR)

BOEING SERVICE BULLETIN 747-28-2344
STA  STA
920  900
FWD
2402085
FIGURE 1: LEFT SIDE - FQIS WIRE X1008 (S283U007-518) INSPECTION
(SHEET 5 OF 11)
Original Issue: October 12, 2018
Export Controlled ECCN: 9E991 - BOEING  747-28-2344
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  57 of 128

### Page 58 (OCR)

BOEING SERVICE BULLETIN 747-28-2344
STA
980
2402112
FIGURE 1: LEFT SIDE - FQIS WIRE X1008 (S283U007-518) INSPECTION
(SHEET 6 OF 11)
Original Issue: October 12, 2018
Export Controlled ECCN: 9E991 - BOEING  747-28-2344
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  58 of 128

### Page 59 (OCR)

BOEING SERVICE BULLETIN 747-28-2344
FWD  2402162
FIGURE 1: LEFT SIDE - FQIS WIRE X1008 (S283U007-518) INSPECTION
(SHEET 7 OF 11)
Original Issue: October 12, 2018
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.

### Page 60 (OCR)

BOEING SERVICE BULLETIN 747-28-2344
STA
1000
G  FWD  2402200
FIGURE 1: LEFT SIDE - FQIS WIRE X1008 (S283U007-518) INSPECTION
(SHEET 8 OF 11)
Original Issue: October 12, 2018
Export Controlled ECCN: 9E991 - BOEING  747-28-2344
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  60 of 128

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