# Boeing Service Bulletin MD90-28-013: Revision 1

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- Document: [Boeing Service Bulletin MD90-28-013](https://openairdocs.org/service-documents/boeing/md90-28-013.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin MD90-28-013
- Pages: 134
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## Text

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### Page 1

Commercial 
Airplanes
MD90
Service Bulletin
Number: MD90-28-013
Original Issue: September 27, 2013
ATA System: 2800
SUBJECT: FUEL - Fuel Systems - Install Ground Fault Interrupter Relays and Change Fuel Pump
System Wiring
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 © 2013 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Unpublished Work.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: September 27, 2013
MD90-28-013
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4.0

### Page 2

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BLANK PAGE

### Page 3

Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 1
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 2
D. Description .............................................. 1 2
E. Compliance .............................................. 1 2
F. Approval ............................................... 1 2
G. Manpower .............................................. 1 3
H. Weight and Balance Changes .................................... 1 4
I. Electrical Load Data ......................................... 1 5
J. References .............................................. 2 0
1. Existing Data: ......................................... 2 0
2. Data Supplied with this Service Bulletin: ........................... 2 0
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 0
4. Process Data: ......................................... 2 1
K. Publications Affected ........................................ 2 1
L. Interchangeability and Intermixability of Parts ........................... 2 1
M. Software Accomplishment Summary ................................ 2 1
2. MATERIAL INFORMATION ........................................ 2 3
A. Material - Price and Availability ................................... 2 3
B. Industry Support Information .................................... 2 3
C. Parts Necessary for Each Airplane ................................. 2 3
1. Kits/Parts ............................................ 2 3
2. Parts and Materials Supplied by the Operator ........................ 2 8
3. Parts Modified and Reidentified ................................ 2 9
4. Parts Removed and Not Replaced .............................. 2 9
D. Parts Necessary to Change Spares ................................. 3 0
E. Special Tooling - Price and Availability ............................... 3 0
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 1
A. GENERAL INFORMATION ..................................... 3 1
B. WORK INSTRUCTIONS ....................................... 3 3
FIGURE 1: REMOVE RELAYS R2-218 AND R2-219 - FORWARD CARGO COMPARTMENT, LEFT SIDE
[Group 3] ............................................ 3 8
FIGURE 2: INSTALL BRACKETS AND MOD BLOCK RAIL - E/E COMPARTMENT, AFT LEFT RADIO
RACK [Group 1-2] ....................................... 4 0
FIGURE 3: INSTALL BRACKETS AND MOD BLOCK RAILS - E/E COMPARTMENT, AFT LEFT RADIO
RACK [Group 3] ........................................ 4 4
FIGURE 4: REMOVE RELAYS R2-336, R2-337 AND RECEPTACLES R5-406, R5-407 - ELECTRICAL
POWER CENTER [Group 2] .................................. 4 8
FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES [Group 1] ................. 5 0
FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES [Group 2] ................. 5 7
FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES [Group 3] .... 6 3
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### Page 4

FIGURE 8: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK
[Group 1] ............................................ 7 6
FIGURE 9: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK
[Group 2] ............................................ 7 9
FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK
[Group 3] ............................................ 8 2
APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS
LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES  [Group 1] ........ 8 7
APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS
LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES [Group 2] ....... 1 0 0
APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK
PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES [Group 3] . . . 114
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Commercial 
Airplanes
MD90
Service Bulletin
SummaryNumber: MD90-28-013Original Issue: September 27, 2013
ATA System: 2800
SUBJECT: FUEL - Fuel Systems - Install Ground Fault Interrupter Relays and Change Fuel Pump
System Wiring
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Frictional heating or sparking may develop from fuel pump failure, wear of fuel pump rotating components, or
ingestion of debris by the pump. Electrical faults in a fuel pump may result in electrical arc burn through of a fuel
pump. Frictional heating or sparking and electrical arc burn through in fuel pump inlets or priming system outlets
exposed (i.e. not covered by fuel) to the tank ullage in combination with the ullage being flammable, may result
in a fuel tank ignition event. A fuel tank ignition event could develop with a pump running in an empty tank if the
normal shutoff command is delayed or as a result of control system failures that keep the pump in a latent
uncommanded running condition. Center wing fuel tanks and auxiliary fuel tank may be subject to this condition
since they are normally pumped dry over the course of a flight. If not corrected frictional heating or sparking,
electrical arc burn through, or a fuel tank pump running in an empty fuel tank may result in a fuel tank ignition
event.
This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation
Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.
Boeing Fleet Team Digest (FTD) MD-90 FTD 28-03001 is related to this service bulletin.
ACTION
This service bulletin installs Ground Fault Interrupter (GFI) relays and cuts/coils/stows wires to center wing and
auxiliary fuel tank pump motor neutral circuits.
EFFECTIVITY
MD-90-30 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-18-05 is related to this service bulletin.
Boeing recommends that the change given in this service bulletin be done within 60 months after the effective
date of AD 2012-18-05.
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### Page 6

INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Elapsed HoursTotal Task HoursGroup
31.058.01
24.445.32
73.7142.73
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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### Page 7 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
INSTALL GROUND FAULT INTERRUPTER RELAYS
AND CHANGE FUEL PUMP SYSTEM WIRING
1885979
Original Issue: September 27, 2013
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### Page 8

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### Page 9

Commercial 
Airplanes
MD90
Service Bulletin
Number: MD90-28-013
Original Issue: September 27, 2013
ATA System: 2800
SUBJECT: FUEL - Fuel Systems - Install Ground Fault Interrupter Relays and Change Fuel Pump
System Wiring
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes that install GFI relays for center fuel tank boost pumps
which are affected by SR90280011-7001 drawing configuration.
-1
Airplanes that install GFI relays for center fuel tank boost pumps
which are affected by SR90280011-7003 drawing configuration.
-2
Airplanes that install GFI relays for center fuel tank and forward
auxiliary fuel tank boost pumps which are affected by
SR90280011-7005 drawing configuration.
-3
Airplane Models:
MD-90-30
GroupFuselage Num-
ber
12094 - 2099
12100
12115
12117
12120
12122 - 2123
12125 - 2126
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### Page 10

GroupFuselage Num-
ber
12129
12131
12133
12136
12138
12140 - 2144
12146 - 2147
12149 - 2150
12153 - 2154
12156 - 2159
12161 - 2166
12169 - 2171
12173
12175
12177
12179
12181 - 2182
12184
12186
12190
22191
12193 - 2195
12197 - 2198
12200
12202 - 2203
22205
12207
22209
12210 - 2212
22213
22215 - 2216
12217
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GroupFuselage Num-
ber
22219
12220
22221
12222
22223
12224
22225 - 2227
12228
22229 - 2232
12233
22235
12236
22237
12238
12240
12242
32243
12245 - 2246
12248
22250 - 2251
12253
22255 - 2257
12258 - 2259
22260
12261
22262 - 2263
22288 - 2290
14001 - 4002
2. Spares Affected
None.
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### Page 12

B. Concurrent Requirements
None.
C. Reason
Frictional heating or sparking may develop from fuel pump failure, wear of fuel pump rotating
components, or ingestion of debris by the pump. Electrical faults in a fuel pump may result in electrical
arc burn through of a fuel pump. Frictional heating or sparking and electrical arc burn through in fuel
pump inlets or priming system outlets exposed (i.e. not covered by fuel) to the tank ullage in combination
with the ullage being flammable, may result in a fuel tank ignition event. A fuel tank ignition event could
develop with a pump running in an empty tank if the normal shutoff command is delayed or as a result
of control system failures that keep the pump in a latent uncommanded running condition. Center wing
fuel tanks and auxiliary fuel tank may be subject to this condition since they are normally pumped dry
over the course of a flight. If not corrected frictional heating or sparking, electrical arc burn through, or
a fuel tank pump running in an empty fuel tank may result in a fuel tank ignition event.
This service bulletin is the result of the safety assessments conducted by Boeing under a Special
Federal Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.
Boeing Fleet Team Digest (FTD) MD-90 FTD 28-03001 is related to this service bulletin.
D. Description
This service bulletin installs Ground Fault Interrupter (GFI) relays and cuts/coils/stows wires to center
wing and auxiliary fuel tank pump motor neutral circuits.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
112, 114, 115, 121, 211, 221MD-90-30
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-18-05 is related to this service
bulletin.
Boeing recommends that the change given in this service bulletin be done within 60 months after the
effective date of AD 2012-18-05.
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. 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.
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### Page 13

In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the action (i.e.
inspection or modification) defined in this service bulletin as an Alternative Method of Compliance to
the requirements of paragraph (g)(1) and (2) of AD 2012-18-05. All provisions of AD 2012-18-05 that
are not specifically referenced in the above statement remain fully applicable and must be complied
with.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
1.71.71Open Access
0.30.31FIGURE 2
23.547.02Route and Clip Wire
2.95.82FIGURE 5
0.30.31FIGURE 8
1.71.71Close Access
0.61.22Test
31.058.0TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
1.21.21Open Access
0.30.31FIGURE 2
0.50.51FIGURE 4
17.535.02Route and Clip Wire
2.55.02FIGURE 6
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Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
0.30.31FIGURE 9
1.21.21Close Access
0.91.82Test
24.445.3TOTAL FOR EACH AIRPLANE
Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
1.71.71Open Access
0.20.21FIGURE 1
0.50.51FIGURE 3
62.0124.02Route and Clip Wire
5.210.42FIGURE 7
0.60.61FIGURE 10
1.71.71Close Access
1.83.62Test
73.7142.7TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Group 1:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+236.2+0.5472.4MD-90-30
Group 2:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
-87.3-0.5174.5MD-90-30
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Group 3:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+482.4+3.0160.8MD-90-30
I. Electrical Load Data
1. Direct Current (DC) Load Changes
a. Add DC loads by amounts shown below:
Group 1-2:
No DC loads added.
Group 3:
UNITS
%OPR
1
100
E/NE
E
UNIT
LOAD
AMPS
0.112
NOTES
(B1-903)
SUPPLIER
Leach In-
ternational
EQUIPMENT NAME
PART NUMBER
GFI FWD AUX Tank Fuel
XFR Pump A
KDG-X4L-001
ITEM
R2-
1496
CHAP
280
BUS
1L
AVERAGE AMPS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
0.1120.1120.112100100TAKEOFF & CLIMB
0.1120.1120.112100100CRUISE COLD
0.1120.1120.112100100CRUISE HOT
0.0560.0560.1125050DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
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Group 3:
UNITS
%OPR
1
100
E/NE
E
UNIT
LOAD
AMPS
0.112
NOTES
(B1-904)
SUPPLIER
Leach In-
ternational
EQUIPMENT NAME
PART NUMBER
GFI FWD AUX Tank Fuel
XFR Pump B
KDG-X4L-001
ITEM
R2-
1497
CHAP
280
BUS
2R
AVERAGE AMPS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
0.1120.1120.112100100TAKEOFF & CLIMB
0.1120.1120.112100100CRUISE COLD
0.1120.1120.112100100CRUISE HOT
0.0560.0560.1125050DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
b. Delete DC loads by amounts shown below:
Group 1-2:
No DC loads deleted.
Group 3:
UNITS
%OPR
1
100
E/NE
E
UNIT
LOAD
AMPS
0.37
NOTES
(B1-907)
SUPPLIER
Leach In-
ternational
EQUIPMENT NAME
PART NUMBER
FWD AUX Tank Fuel XFR
Pump A
5D0281-1
ITEM
R2-218
CHAP
280
BUS
1L
AVERAGE AMPS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
0.370.370.37100100TAKEOFF & CLIMB
0.370.370.37100100CRUISE COLD
0.370.370.37100100CRUISE HOT
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Group 3:
UNITS
%OPR
1
100
E/NE
E
UNIT
LOAD
AMPS
0.37
NOTES
(B1-907)
SUPPLIER
Leach In-
ternational
EQUIPMENT NAME
PART NUMBER
FWD AUX Tank Fuel XFR
Pump A
5D0281-1
ITEM
R2-218
CHAP
280
BUS
1L
AVERAGE AMPS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
0.190.190.375050DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
Group 3:
UNITS
%OPR
1
100
E/NE
E
UNIT
LOAD
AMPS
0.37
NOTES
(B1-908)
SUPPLIER
Leach In-
ternational
EQUIPMENT NAME
PART NUMBER
FWD AUX Tank Fuel XFR
Pump B
5D0281-1
ITEM
R2-219
CHAP
280
BUS
2R
AVERAGE AMPS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
0.370.370.37100100TAKEOFF & CLIMB
0.370.370.37100100CRUISE COLD
0.370.370.37100100CRUISE HOT
0.190.190.375050DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
2. Alternating Current (AC) Load Changes
a. Add AC loads by amounts shown below:
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### Page 18

UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
1
UNIT
LOAD
(W)
5.75
NOTES
(B1-922)
SUPPLIER
Leach In-
ternational
EQUIPMENT NAME
PART NUMBER
Center FWD Boost Pump
GFI Relay
KDAG-X4F-001
ITEM
R2-
1494
CHAP
280
BUS
1L
AVERAGE WATTS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
0.1150.3455.7526LOADING
00000START
00000TAXI
5.755.755.75100100TAKEOFF & CLIMB
5.755.755.75100100CRUISE COLD
5.755.755.75100100CRUISE HOT
2.92.95.755050DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
1
UNIT
LOAD
(W)
5.75
NOTES
(B1-923)
SUPPLIER
Leach In-
ternational
EQUIPMENT NAME
PART NUMBER
Center AFT Boost Pump
GFI Relay
KDAG-X4F-001
ITEM
R2-
1495
CHAP
280
BUS
2R
AVERAGE WATTS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
0.1150.3455.7526LOADING
00000START
00000TAXI
5.755.755.75100100TAKEOFF & CLIMB
5.755.755.75100100CRUISE COLD
5.755.755.75100100CRUISE HOT
2.92.95.755050DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
b. Delete AC loads shown below:
Group 1, 3:
No AC loads deleted.
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### Page 19

Group 2:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
1
UNIT
LOAD
(W)
11.5
NOTES
(B1-922)
SUPPLIER
Leach In-
ternational
EQUIPMENT NAME
PART NUMBER
CNTR FWD BOOST PUMP
5D0024-1
ITEM
R2-
336
CHAP
280
BUS
1L
AVERAGE WATTS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
11.511.511.5100100TAKEOFF & CLIMB
11.511.511.5100100CRUISE COLD
11.511.511.5100100CRUISE HOT
5.755.755.755050DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
Group 2:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
1
UNIT
LOAD
(W)
11.5
NOTES
(B1-923)
SUPPLIER
Leach In-
ternational
EQUIPMENT NAME
PART NUMBER
CNTR AFT BOOST PUMP
5D0024-1
ITEM
R2-
337
CHAP
280
BUS
2R
AVERAGE WATTS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
11.511.511.5100100TAKEOFF & CLIMB
11.511.511.5100100CRUISE COLD
11.511.511.5100100CRUISE HOT
5.755.755.755050DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
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J. References
1. Existing Data:
a. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2012-18-05.
b. Standard Wiring Practices Manual (SWPM) 20-00-00, 20-00-09, 20-00-16, 20-10-01, 20-10-02,
20-10-04, 20-20-02, 20-20-03, 20-31-00, 20-40-01 and 20-50-01.
c. MD90 Aircraft Maintenance Manual (AMM) 06-31-00, 06-32-00, 06-36-00, 08-10-00, 12-11-03,
12-11-07, 24-00-00, 24-40-00, 25-23-01, 25-50-01, 27-50-00, 31-00-02, 31-14-00, 32-00-00
and 32-11-01.
d. Structural Repair Manual (SRM) Chapter 51.
e. MD-90 Fleet Team Digest (FTD) 28-03001.
2. Data Supplied with this Service Bulletin:
No data is supplied with this service bulletin. To obtain the data necessary to support this service
bulletin submit a data request to:
Data and Services Management
MS D800-0019
3855 Lakewood Boulevard
Long Beach, California 90846
Phone: (562) 593-6996
Fax: (562) 593-2001
E-mail: dse.boecom@boeing.com
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
D-AEOSFAR 88 FUEL PUMP FRICTIONAL
HEATING
SR90280011
-CDWG
3. Installation Drawings Used in the Preparation of this Service Bulletin:
ChangeTitleDocument Number
-ELEC INSTL - CTR & AUX TANKS
FUEL BOOST & TRANSFER
SR90280010
CCTR & AUX TANKS FUEL BOOST
& TRANSFER
SR90280012
These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
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4. Process Data:
Douglas Process Specifications referred to on the drawings are not given in this service bulletin
since these procedures are frequently used as standard shop practices.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
Section 1 and 3FAA Approved Airplane Flight Manual
FCOM Advisory Bulletin 2-007Flight Crew Operations Manual
24-50, 25-57Illustrated Parts Catalog
28-22Aircraft Maintenance Manual
MDC-92K9145 (CDCCL 20-13)Special Compliance Item Report
28-22Fault Isolation Manual
28-21, 28-24, 28-25, 28-42Wiring Diagram Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
NOTE: This service bulletin replaces existing relays with GFI relays. After accomplishment of this
service bulletin airplanes cannot revert to the previously installed non-GFI relays.
M. Software Accomplishment Summary
Not affected.
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### Page 23

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane . Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPON-
DER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFOR-
MATION
Unit Price as of the original is-
sue date of this Service Bulletin
(US Dollars)
ROLT as of the original issue
date of this Service Bulletin
(Calendar Days)
NameKit Number
$12,392.00150Service KitSB90280013-3
$13,043.00150Service KitSB90280013-5
$36,978.00150Service KitSB90280013-7
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
Group 1:
SB90280013-3 Service Kit
NotesNameQTYNew Part Number
(a)WIRE KIT1SB90280013-101
(b)TERM BLOCK25D0010-15
(b)END CLAMP25D0101-2
(b)TERM BLOCK L95D0107-3
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Group 1:
SB90280013-3 Service Kit
NotesNameQTYNew Part Number
(b)TRACK19D0090-12U
(b)STRAP69D0254-1-1-9
BRACKET2ABN7294-629
MOUNT6CSCS-M
GFI RELAY2KDAG-X4F-001
NUT2MS21042L08
NUT4MS21042L3
SCREW2MS35206-242
LOCKWASHER1MS35338-43
SCREW1NAS1096-3-11
SCREW4NAS1096-3-6
WASHER1NAS1149F0332P
WASHER4NAS1252-10L
(b)WASHER2S124682-3D8-3
RELAY SOCKET2SO-1061-8916
(a) Refer to SB90280013-101 Wire Kit table for Wire Kit contents.
(b) Or approved equivalent. Refer to AEPL Drawing 7595071.
Group 1:
SB90280013-101 Wire Kit
NotesNameQTYNew Part Number
(a)WIRE CODE 801175
FT.
D2426-1C-16NM
(a)WIRE CODE 801369
FT.
D2426-1C-18NM
(a)WIRE CODE 80196 FT.D2426-1C-20NM
(a)WIRE CODE 80157 FT.D2426-1C-24NM
(b)TERM LUG, T/C 88825D0086-17
(b)TERM LUG, T/C 88965D0086-18
(b)TERM LUG, T/C 89025D0086-19
PIN, T/C 113128DC38-16P
PIN, T/C 112610DC38-20P
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Group 1:
SB90280013-101 Wire Kit
NotesNameQTYNew Part Number
SOCKET, T/C 7066LRC16M-32DJ5
SOCKET, T/C 6041LRC22M-1DE5
SOCKET, T/C 12688M39029/92-533
SOCKET, T/C 1266B12M39029/92-535
(b)SOCKET, T/C
602/702
5S00023-20S
(a) Or approved alternate. Refer to SWPM 20-00-13.
(b) Or approved equivalent. Refer to AEPL Drawing 7595071.
Group 2:
SB90280013-5 Service Kit
NotesNameQTYNew Part Number
(a)WIRE KIT1SB90280013-102
(b)TERM BLOCK15D0010-15
(b)END CLAMP25D0101-2
(b)TERM BLOCK L105D0107-3
(b)TRACK19D0090-12U
(b)STRAP69D0254-1-1-9
BRACKET2ABN7294-629
NUT2AN315-3R
MOUNT6CSCS-M
GFI RELAY2KDAG-X4F-001
NUT2MS21042L08
NUT4MS21042L3
SCREW2MS35206-242
LOCKWASHER2MS35338-43
SCREW1NAS1096-3-11
SCREW4NAS1096-3-6
WASHER3NAS1149F0332P
WASHER4NAS1252-10L
(b)WASHER2S124682-3D8-3
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Group 2:
SB90280013-5 Service Kit
NotesNameQTYNew Part Number
RELAY SOCKET2SO-1061-8916
(a) Refer to SB90280013-102 Wire Kit table for Wire Kit contents.
(b) Or approved equivalent. Refer to AEPL Drawing 7595071.
Group 2:
SB90280013-102 Wire Kit
NotesNameQTYNew Part Number
(a)WIRE CODE 801175
FT.
D2426-1C-16NM
(a)WIRE CODE 801115
FT.
D2426-1C-18NM
(a)WIRE CODE 801210
FT.
D2426-1C-20NM
(b)TERM LUG, T/C 76225D0086-6
PIN, T/C 113132DC38-16P
PIN, T/C 11268DC38-20P
SOCKET, T/C 12688M39029/92-533
SOCKET, T/C 1266B12M39029/92-535
(b)SOCKET, T/C
602/702
6S00023-20S
PIN, T/C 61212YHMM16-3F50
(a) Or approved alternate. Refer to SWPM 20-00-13.
(b) Or approved equivalent. Refer to AEPL Drawing 7595071.
Group 3:
SB90280013-7 Service Kit
NotesNameQTYNew Part Number
(a)WIRE KIT1SB90280013-103
(b)TERM BLOCK25D0010-15
(b)END CLAMP45D0101-2
(b)TERM BLOCK25D0107-1
(b)TERM BLOCK L185D0107-3
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Group 3:
SB90280013-7 Service Kit
NotesNameQTYNew Part Number
(b)TRACK29D0090-12U
(b)STRAP69D0254-1-1-9
BRACKET3ABN7294-629
MOUNT6CSCS-M
GFI RELAY2KDAG-X4F-001
GFI RELAY2KDG-X4L-001
NUT4MS21042L08
NUT6MS21042L3
SCREW4MS35206-242
LOCKWASHER1MS35338-43
SCREW1NAS1096-3-11
SCREW6NAS1096-3-6
WASHER1NAS1149F0332P
WASHER6NAS1252-10L
RELAY SOCKET2RSE500311
(b)WASHER4S124682-3D8-3
RELAY SOCKET2SO-1061-8916
(a) Refer to SB90280013-103 Wire Kit table for Wire Kit contents.
(b) Or approved equivalent. Refer to AEPL Drawing 7595071.
Group 3:
SB90280013-103 Wire Kit
NotesNameQTYNew Part Number
(a)WIRE CODE 801350
FT.
D2426-1C-16NM
(a)WIRE CODE 801369
FT.
D2426-1C-18NM
(a)WIRE CODE 8011003
FT.
D2426-1C-20NM
(a)WIRE CODE 80157 FT.D2426-1C-24NM
(b)TERM LUG, T/C 88825D0086-17
(b)TERM LUG, T/C 88965D0086-18
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Group 3:
SB90280013-103 Wire Kit
NotesNameQTYNew Part Number
(b)TERM LUG, T/C 89025D0086-19
(b)TERM LUG, T/C 761105D0086-5
(b)TERM LUG, T/C 76285D0086-6
PIN, T/C 113162DC38-16P
PIN, T/C 112610DC38-20P
SOCKET, T/C 70612LRC16M-32DJ5
SOCKET, T/C 6041LRC22M-1DE5
SOCKET, T/C 126816M39029/92-533
SOCKET, T/C 1266B24M39029/92-535
(b)PIN, T/C 601/70116S00023-20P
(b)SOCKET, T/C
602/702
19S00023-20S
(a) Or approved alternate. Refer to SWPM 20-00-13.
(b) Or approved equivalent. Refer to AEPL Drawing 7595071.
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number / Specifica-
tion
(a)Tie TapeAs Required18XTZ, 23XTZ
(DMS 2089)
or
Equivalent
(b)Chemical Conversion CoatingAs RequiredAlodine 1200S
(DPM 1453-5)
or
Equivalent
End Cap2CYW20
(b)Primer, Fluid ResistantAs RequiredKoropon 515-700 with Cata-
lyst 910-704
(DMS 1786)
or
Equivalent
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NotesNameQTYPart Number / Specifica-
tion
(c) (d)StrapAs Required9D0254-1-1-9
(PLT2S-9)(SST2S)
or
Equivalent
SpacerAs Required2712453-BN
(a) Can be purchased from: Gudebrod Incorporated, 274 Shoemaker Road, Pottstown,
Pennsylvania, 19464, CAGE 82110.
(b) Can be purchased from: Henkel Corporation, 32100 Stephenson Highway, Madison
Heights, Michigan, 48071, CAGE 1N6B3.
(c) Can be purchased from: Panduit Corporation, 17301 Ridgeland Avenue, Tinley Park,
Illinois, 60477, CAGE 06383.
(d) Or approved equivalent. Refer to AEPL Drawing 7595071.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
Group 1:
None.
Group 2:
NotesQTYNameExisting Part Number
R2-336 and R2-337 (a)
(b)
2RELAY5D0024-1
R5-406 and R5-407 (a)
(b)
2RELAY SOCKET5D0020-10
(a) Keep the part if there are other uses for it.
(b) Or approved equivalent. Refer to AEPL Drawing 7595071.
Group 3:
NotesQTYNameExisting Part Number
R2-218 and R2-219 (a)
(b)
2RELAY5D0281-1
(a)1BRACKETABN7294-627
(a) Keep the part if there are other uses for it.
(b) Or approved equivalent. Refer to AEPL Drawing 7595071.
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D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY
ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE
CAN OCCUR.
CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
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. Equivalent parts are listed in the AEPL, Drawing 7595071.
3. Use the approved fastener and process material substitutions, in accordance with
Structural Repair Manual (SRM) 51.
4. 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.
5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is
the maximum thickness which may be used under fastener head or nut to counteract
accumulation of tolerances.
EXCEPTION: When the available fastener length increments are greater than
1/16-inch, a 3/16-inch thick stack of the same type washers may be used.
6. 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 limits to tighten nuts and bolts are in SRM Chapter 51.
7. Refer to these SWPM chapters for applicable operations, as accepted procedures:
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TitleChapter
General - Maintenance Safety PracticesSWPM 20-00-00
General Maintenance Practices - ElectricalSWPM 20-00-09
Electrical Wire CodesSWPM 20-00-13
Electrical Wire End Termination Codes and Tool CodesSWPM 20-00-16
Wiring Installation - Maintenance PracticesSWPM 20-10-01
Shielding - Maintenance PracticesSWPM 20-10-02
Coil and Stow - Maintenance PracticesSWPM 20-10-04
Terminal Blocks - Maintenance PracticesSWPM 20-20-02
General Installations Hardware - Maintenance PracticesSWPM 20-20-03
Electrical Connectors - Maintenance PracticesSWPM 20-31-00
Power Distribution Bus - Maintenance PracticesSWPM 20-40-01
Electrical Bonding - Maintenance PracticesSWPM 20-50-01
8. Obey all of the warnings and cautions given in the specified manual sections.
9. Review and understand all general notes of Service Rework Drawing SR90280011
sheets 3.0, 3.1, 3.2, 3.3, 3.4 and 3.5.
10. If an existing clamp specified in this service bulletin is too large or too small, a smaller
or larger clamp with the same basic part number can be used to provide a snug fit.
11. Mark electrical item numbers on structure adjacent to part. Refer to SWPM 20-00-09
as an accepted procedure.
12. The modules on a terminal block are controlled by the wire data. Verify/Install terminal
block modules and end clamps to agree with the wire data, refer to SWPM 20-20-02
as an accepted procedure.
Use the following parts as required:
Part NumberTerminal Block ID Letter
5D0010-15B
5D0010-13J
5D0107-3L
5D0106-1CC
5D0107-1DD
5D0010-11HH
5D0101-2EE (End Clamp)
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13. Install terminal block at noted position. If noted position is occupied with a spare
terminal block replace it with a specified terminal block. If specified terminal block is
same type as existing spare terminal block it is not necessary to replace the terminal
block.
14. Perform continuity checks on changed wires after completion of electrical wiring
changes.
15. 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.
16. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U' or 'Y' in place of the '-' (dash) in the part number. It is permitted
to install parts identified with a 'U' or 'Y' as an alternative to the '-' (dash) number
part. Boeing Drawing SE10000000, Sheets 5.0 and 6.0 contain more data.
17. 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.
18. 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.
19. 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.
B. WORK INSTRUCTIONS
Group 1:
1. Remove electrical power from the airplane. Refer to MD90 AMM 24-00-00 as an accepted
procedure.
2. Gain access to areas of change as follows:
a. Open access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.
LocationAccess Door
Electrical/Electronics (E/E) Compartment110BL
Forward Accessory Compartment115AZ
b. Open overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02
as an accepted procedure.
c. Remove and keep left cockpit sidewall panels. Refer to MD90 AMM 06-32-00 as an accepted
procedure.
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d. Remove and keep left console. Refer to MD90 AMM 31-14-00 as an accepted procedure.
e. Remove and keep forward cargo compartment left outboard side panel 121AL and attaching
parts. Refer to MD90 AMM 25-50-01 as an accepted procedure.
f. Remove and keep cargo compartment ceiling panels between stations Y=218.000 and
Y=256.000. Refer to MD90 AMM 25-50-01 as an accepted procedure.
g. Remove and keep forward cabin attendant's seat and attaching parts. Refer to MD90 AMM
25-23-01 as an accepted procedure.
h. Remove and keep aft Electrical Power Center (EPC) panel 221CL and attaching parts. Refer
to MD90 AMM 06-32-00.
3. Install brackets and mod block rails in accordance with FIGURE 2.
4. Install Ground Fault Interrupter (GFI) relays and receptacles in accordance with FIGURE 8.
5. Route and clip wire in accordance with Service Rework Drawing SR90280011 sheets 6.0, 7.0,
7.2, 7.5, 7.6, 7.7, 7.8, 7.9, 8.0, 8.2, 8.3, 8.4, 9.0, 9.1, 10.0, 10.1, 10.2, 10.3, 10.4, 11.0, 11.1 and
11.10.
6. Make wire changes in accordance with FIGURE 5.
7. Close access to areas of change as follows:
a. Replace kept aft EPC panel 221CL and attaching parts. Refer to MD90 AMM 06-32-00.
b. Replace kept forward cabin attendant's seat and attaching parts. Refer to MD90 AMM 25-23-01
as an accepted procedure.
c. Replace kept cargo compartment ceiling panels between stations Y=218.000 and Y=256.000.
Refer to MD90 AMM 25-50-01 as an accepted procedure.
d. Replace kept forward cargo compartment left outboard side panel 121AL and attaching parts.
Refer to MD90 AMM 25-50-01 as an accepted procedure.
e. Replace kept left console. Refer to MD90 AMM 31-14-00 as an accepted procedure.
f. Replace kept left cockpit sidewall panels. Refer to MD90 AMM 06-32-00 as an accepted
procedure.
g. Close overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02
as an accepted procedure.
h. Close access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.
LocationAccess Door
Electrical/Electronics (E/E) Compartment110BL
Forward Accessory Compartment115AZ
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8. Do Ground Fault Interrupter (GFI) Center Fuel Tank Pumps Control Circuit, and Center Fuel Tank
Pumps Low Pressure Indication System Test Procedures in accordance with APPENDIX A.
9. Put the airplane back to a serviceable condition.
Group 2:
1. Remove electrical power from the airplane. Refer to MD90 AMM 24-00-00 as an accepted
procedure.
2. Gain access to areas of change as follows:
a. Open access doors listed in the following table. Refer to MD90 AMM 06-31-00.
LocationAccess Door
Electrical/Electronics (E/E) Compartment110BL
Forward Accessory Compartment115AZ
b. Remove and keep left console. Refer to MD90 AMM 31-14-00 as an accepted procedure.
c. Remove and keep forward cabin attendant's seat and attaching parts. Refer to MD90 AMM
25-23-01 as an accepted procedure.
d. Remove and keep aft Electrical Power Center (EPC) panel 221CL and attaching parts. Refer
to MD90 AMM 06-32-00.
3. Remove relays R2-336 and R2-337 and corresponding relay sockets R5-406 and R5-407 in
accordance with FIGURE 4.
4. Install brackets and mod block rails in accordance with FIGURE 2.
5. Install Ground Fault Interrupter (GFI) relays and receptacles in accordance with FIGURE 9.
6. Route and clip wire in accordance with Service Rework Drawing SR90280011 sheets 6.0, 7.0,
7.3, 7.5, 7.6, 7.8, 8.0, 8.1, 8.2, 8.4, 9.0, 10.0, 10.1, 10.2 and 11.10.
7. Make wire changes in accordance with FIGURE 6.
8. Close access to areas of change as follows:
a. Replace kept aft EPC panel 221CL and attaching parts. Refer to MD90 AMM 06-32-00.
b. Replace kept forward cabin attendant's seat and attaching parts. Refer to MD90 AMM 25-23-01
as an accepted procedure.
c. Replace kept left console. Refer to MD90 AMM 31-14-00 as an accepted procedure.
d. Close access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.
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BOEING SERVICE BULLETIN MD90-28-013

### Page 36

LocationAccess Door
Electrical/Electronics (E/E) Compartment110BL
Forward Accessory Compartment115AZ
9. Do Ground Fault Interrupter (GFI) Center Fuel Tank Pumps Control Circuit, and Center Fuel Tank
Pumps Low Pressure Indication System Test Procedures in accordance with APPENDIX B.
10. Put the airplane back to a serviceable condition.
Group 3:
1. Remove electrical power from the airplane. Refer to MD90 AMM 24-00-00 as an accepted
procedure.
2. Gain access to areas of change as follows:
a. Open access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.
LocationAccess Door
Electrical/Electronics (E/E) Compartment110BL
Forward Accessory Compartment115AZ
b. Open overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02
as an accepted procedure.
c. Remove and keep left cockpit sidewall panels. Refer to MD90 AMM 06-32-00 as an accepted
procedure.
d. Remove and keep left console. Refer to MD90 AMM 31-14-00 as an accepted procedure.
e. Gain access to forward cargo compartment. Remove and keep forward cargo compartment
left outboard side panel 121AL and attaching parts. Refer to MD90 AMM 25-50-01 as an
accepted procedure.
f. Remove and keep cargo compartment ceiling panels between stations Y=218.000 and
Y=879.000. Refer to MD90 AMM 25-50-01 as an accepted procedure.
g. Remove and keep cargo compartment aft panel at station Y=879.000. Refer to MD90 AMM
25-50-01 as an accepted procedure.
h. Remove and keep forward cabin attendant's seat and attaching parts. Refer to MD90 AMM
25-23-01 as an accepted procedure.
i. Remove and keep aft Electrical Power Center (EPC) panel 221CL and attaching parts. Refer
to MD90 AMM 06-32-00.
3. Remove Relays R2-218 and R2-219 in accordance with FIGURE 1.
4. Remove bracket, install brackets and mod block rails in accordance with FIGURE 3.
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BOEING SERVICE BULLETIN MD90-28-013

### Page 37

5. Install Ground Fault Interrupter (GFI) relays and receptacles in accordance with FIGURE 10.
6. Route and clip wire in accordance with Service Rework Drawing SR90280011 sheets 6.0, 7.0,
7.4, 7.5, 7.6, 7.7, 7.8, 7.9, 8.0, 8.2, 8.3, 8.4, 9.0, 9.1, 10.0, 10.1, 10.2, 10.3, 10.4, 11.0, 11.1, 11.2,
11.3, 11.4, 11.8, 11.9 and 11.10.
7. Make wire changes in accordance with FIGURE 7.
8. Close access to areas of change as follows:
a. Replace kept aft EPC panel 221CL and attaching parts. Refer to MD90 AMM 06-32-00.
b. Replace kept forward cabin attendant's seat and attaching parts. Refer to MD90 AMM 25-23-01
as an accepted procedure.
c. Replace kept cargo compartment aft panel at station Y=879.000. Refer to MD90 AMM 25-50-01
as an accepted procedure.
d. Replace kept cargo compartment ceiling panels between stations Y=218.000 and Y=879.000.
Refer to MD90 AMM 25-50-01 as an accepted procedure.
e. Replace kept forward cargo compartment left outboard side panel 121AL and attaching parts.
Refer to MD90 AMM 25-50-01 as an accepted procedure.
f. Replace kept left console. Refer to MD90 AMM 31-14-00 as an accepted procedure.
g. Replace kept left cockpit sidewall panels. Refer to MD90 AMM 06-32-00 as an accepted
procedure.
h. Close overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02
as an accepted procedure.
i. Close access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.
LocationAccess Door
Electrical/Electronics (E/E) Compartment110BL
Forward Accessory Compartment115AZ
9. Restore electrical power to the airplane. Refer to MD90 AMM 24-00-00 as an accepted procedure.
10. Do Ground Fault Interrupter (GFI) Center/Aux Fuel Tank Pumps Control Circuit, and Center/Aux
Fuel Tank Pumps Low Pressure Indication System Test Procedures in accordance with APPENDIX
C.
11. Put the airplane back to a serviceable condition.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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MD90-28-013
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### Page 38 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
This Figure applies only to: Group 3.
STA
408
000000000000000
Z=-6.00
R2-218  R2-219
•
•  •
FWD
STA  STA  1877252
408  389
FIGURE 1: REMOVE RELAYS R2-218 AND R2-219 - FORWARD CARGO COMPARTMENT, LEFT SIDE
(SHEET 1 OF 2)
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PROPRIETARY - Copyright @ Unpublished
Work - See page 1 for details.  38 of 134

### Page 39

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
8NAS1096-2-8ScrewRemove1
8NAS1149DN816HWasher
R2-218, R2-219 (a)25D0281-1Relay
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
FIGURE 1: REMOVE RELAYS R2-218 AND R2-219 - FORWARD CARGO COMPARTMENT, LEFT SIDE
(SHEET 2 OF 2)
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Work - See page 1 for details.
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### Page 40 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
This Figure applies only to: Group 1-2.
STA
200
000000000000000
STA  STA  STA
218  200  160
Z=-15.00
Z=-24.250
— Z=-34.00
FWD
LOOKING OUTBOARD  LAI  1877253
FIGURE 2: INSTALL BRACKETS AND MOD BLOCK RAIL - E/E COMPARTMENT, AFT LEFT RADIO RACK
(SHEET 1 OF 4)
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Work - See page 1 for details.  40 of 134

### Page 41 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
STA
200
(REF
27.05
Z=-24.250
0000
FWD
1877256
FIGURE 2: INSTALL BRACKETS AND MOD BLOCK RAIL - E/E COMPARTMENT, AFT LEFT RADIO RACK
(SHEET 2 OF 4)
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Work - See page 1 for details.  41 of 134

### Page 42 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
(REF)  (REF)
3.94  1.25
Z=-24.250
XOO
S30-236
X=34.000
Z=-24.250 -
D-D  1952279
FIGURE 2: INSTALL BRACKETS AND MOD BLOCK RAIL - E/E COMPARTMENT, AFT LEFT RADIO RACK
(SHEET 3 OF 4)
Original Issue: September 27, 2013
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Work - See page 1 for details.  42 of 134

### Page 43

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)2ABN7294-629BracketInstall/New1
4NAS1096-3-6Screw2
4NAS1252-10LWasher
4MS21042L3Nut
(b)19D0090-12UTrack AssemblyInstall/New3
2MS35206-242Screw4
2S124682-3D8-3Washer
2MS21042L08Nut
(a) Electrical bond between surfaces common to bracket and mating structure. Refer to SWPM 20-50-01 as
an accepted procedure.
(b) Item number S30-236 must be adjacent and visible after equipment is installed. Refer to SWPM 20-00-
09 as an accepted procedure.
FIGURE 2: INSTALL BRACKETS AND MOD BLOCK RAIL - E/E COMPARTMENT, AFT LEFT RADIO RACK
(SHEET 4 OF 4)
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MD90-28-013
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### Page 44 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
This Figure applies only to: Group 3.
STA
200
0000000000000
STA  STA  STA
218  200  160
Z=-15.00
￾ Z=-24.250
- Z=-34.00
B  FWD
LOOKING OUTBOARD  1877265
FIGURE 3: INSTALL BRACKETS AND MOD BLOCK RAILS - E/E COMPARTMENT, AFT LEFT RADIO
RACK
(SHEET 1 OF 4)
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### Page 45 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
STA
200
18.00 -
Z=-24.250
•doo  •••  .....  ....0  ...  .....b..
0000000000000000  0000  0000
FWD
BEFORE
STA
200
(REF)
27.05
Z=-24.250
›00
0000000000000
FWD  C
AFTER  1877266
FIGURE 3: INSTALL BRACKETS AND MOD BLOCK RAILS - E/E COMPARTMENT, AFT LEFT RADIO
RACK
(SHEET 2 OF 4)
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### Page 46 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
(REF)  (REF)  (REF
3.28  3.94  1.25
Z=-24.250
FWD
S30-237  S30-236
X=34.000
Z=-24.250 -
D-D  1952397
FIGURE 3: INSTALL BRACKETS AND MOD BLOCK RAILS - E/E COMPARTMENT, AFT LEFT RADIO
RACK
(SHEET 3 OF 4)
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Work - See page 1 for details.  46 of 134

### Page 47

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
2NAS1096-3-7ScrewRemove1
2NAS1252-10LWasher
2MS21042L3Nut
1ABN7294-627Bracket
(a)3ABN7294-629BracketInstall/New2
6NAS1096-3-6Screw3
6NAS1252-10LWasher
6MS21042L3Nut
(b) (c)29D0090-12UTrack AssemblyInstall/New4
4MS35206-242Screw5
4S124682-3D8-3Washer
4MS21042L08Nut
(a) Electrical bond between surfaces common to bracket and mating structure, refer to SWPM 20-50-01 as
an accepted procedure.
(b) Item numbers S30-236 and S30-237 must be adjacent and visible after equipment is installed. Refer to
SWPM 20-00-09 as an accepted procedure.
(c) Or approved equivalent. Refer to AEPL Drawing 7595071.
FIGURE 3: INSTALL BRACKETS AND MOD BLOCK RAILS - E/E COMPARTMENT, AFT LEFT RADIO
RACK
(SHEET 4 OF 4)
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MD90-28-013
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### Page 48 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
This Figure applies only to: Group 2.
ELECTRICAL POWER CENTER  1883728
FIGURE 4: REMOVE RELAYS R2-336, R2-337 AND RECEPTACLES R5-406, R5-407 - ELECTRICAL POWER
_ CENTER
(SHEET 1 OF 2)
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### Page 49

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)15D0024-1RELAY (R2-336)Remove1
15D0020-10RECEPTACLE (R5-
406)
(a) (b)15D0024-1RELAY (R2-337)Remove2
15D0020-10RECEPTACLE (R5-
407)
(a) And attaching hardware.
(b) Or approved equivalent. Refer to AEPL Drawing 7595071.
FIGURE 4: REMOVE RELAYS R2-336, R2-337 AND RECEPTACLES R5-406, R5-407 - ELECTRICAL POWER
CENTER
(SHEET 2 OF 2)
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### Page 50 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
This Figure applies only to: Group 1.
R5-611 R2-583  CENTER FWD BOOST  PUMP CONTROL
H Q601C18C+/  + Q602C18B++  1Q5H18B +  + *94H18C ++  (RAF) (RAB)  - *0254×18  F**Q603C18AX  (RAF)  - *Q258K18  EL 012P18C +  + Q13P18B +  AFT RIGHT RADIO RACK - TOP SHELF
M  Z  P1-2272 R5-24  STA 148 R  6DD  4DD  5DD  S3-501  STA 200
+
Q258 G20  150 IN.  Q254W20  150 IN.  Q254S24  Q264C24  (RAF) (RAB)  *Q603D18  • *Q14R18A  (RAF)  *014Z18  + Q12R18C +  † Q13R18B +
O/+ Q601B18C  0++Q12N18C+  1 Q602B18B  Of Q13N18B +  Q5J18B +  + Q4J18C +  CENTER FWD BOOST PUMP  OVERHEAD SWITCH PANEL  126  D2  A1  COILED AND STORED WIRES  B2  C2  B1  R2-578 R5-606  AUTO CENTER  FWD BOOST PUMP
ADDED WIRE OR NEW ROUTING
B1
S1-36  10BA  / DELETED WIRE OR FORMER ROUTING
EXISTING WIRE
*NOTED WIRES ARE EXISTING, REROUTED AND
REIDENTIFIED WIRES
**NOTED WIRES Q7B20N AND Q8B20N SHALL BE
CUT, CAPPED AND STOWED BETWEEN THE
TWO SUPPORT CLAMPS AS SHOWN ON
DRAWING SR90280011, SHEET 11.10.
FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES
(SHEET 1 OF 7)
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### Page 51 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
+ B1  R5-610 R2-582  CENTER AFT BOOST  PUMP CONTROL
+ Q608C18C+  + Q607C18B →  / / Q2H18B -  (RAF) (RAB)  - *Q253×18 -  · 0606C18A+  1 *Q9P18C +  2DD / / Q10P18B +  (RAF)  *0258L18 •  AFT RIGHT RADIO RACK - TOP SHELF
*H  P1-2272 R5-2472  STA 148 R  1DD  3DD  4DD  S3-501  STA 200
Q253W20  150 IN.  1126  + Q253S24 →  + Q263C24 +  (RAF) (RAB)  *Q606D18  + *Q11R18A +  (RAF)  *011718  1 Q9R18C +  111 Q10R18B +
S30-236  STA 160 L  AUTO CENTER AFT BOOST PUMP
01/ Q608B18C +  D2  A1  B2  A2  R2-579 R5-607
FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES
(SHEET 2 OF 7)
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### Page 52 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
CENTER FUEL TANK  P1-530  P1-529
**Q7B20N  **Q8B2
R5-1307 P1-1307  STA 248 1  R5-1306 P1-1306  STA 246 L
C2 0C1  03109A180++  B2 | 0 B1  017 02B18В+110-  OY Q10A18B+  A2 | OA1  TOA7+011A18A+11  S1-37  CENTER AFT BOOST PUMP  C2 0C1  011 Q4B180 +10  0731012A180+11  B2 | 0 B1  0L2 0581881 B2  ВЗ  077 Q13A18B+  A2 | OA1  10A3  + 014A18A +  S1-36  CENTER FWD BOOST PUMP  D2  Q258C24+  T D3/ 0254A24 +  S1-36  CENTER FWD BOOST PUMP  D1  D2  "D3  + Q253A24 +  S1-37  CENTER AFT BOOST PUMP  OVERHEAD SWITCH PANEL
B1-923  CENTER AFT FUEL BOOST PUMP  B1-922  CENTER FWD FUEL BOOST PUMP  UPPER EPC CIRCUIT BREAKER PANEL  CENTER PUMP PRESS INHIBIT  LOWER ELECTRICAL POWER CENTER
15VAC-ØC-R  115VAC-ØB-R  15VAC-ØB-L
1888394
FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES
(SHEET 3 OF 7)
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### Page 53 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
1268  890
X2  Q642A18N '  -3556
175 IN
1131  (1131
Q14X18
175 IN.
R2-1494 R5-1494  S30-236
CENTER FWD BOOST PUMP GFI RELAY  STA 160 L
AFT LEFT EQUIPMENT BAY
A2 1 O A1
a  (888
А3 0  Q14Y18
330 IN.
S1-36
CENTER FWD BOOST PUMP
OVERHEAD SWITCH PANEL
1268  890
Х2  Q642B18N  3556
175 IN
1268  (1131)  (1131
Q11X18  9LX
175 IN
CENTER AFT BOOST PUMP GFI RELAY  R2-1495 R5-1495  STA 160 L  S30-236
AFT LEFT EQUIPMENT BAY
A2 I 0A1
888
АЗО  Q11Y18
S1-37  330 IN.
CENTER AFT BOOST PUMP
OVERHEAD SWITCH PANEL
1889424
FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES
(SHEET 4 OF 7)
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### Page 54 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
(3 PLACES)  (12 PLACES)  (12 PLACES)  (3 PLACES)  (3 PLACES)
889  (1131  (1131  (1266B  1266B
115VAC-ØC-R  Q1P18C  4LA  Q1M16C  C2  C1  Q9U16C
_3  310 IN.  175 IN.  175 IN.
115VAC-ØB-R  Q2R18B  3LX  Q2N16B  B2  B1  • Q10U16B
310 IN.  175 IN  175 IN.
115VAC-ØA-R  Q3S18A  3LA  Q3P16A  A2  A1  Q11U16A•
310 IN.  175 IN.  175 IN.
B1-923
R5-1495 R2-1495 R5-1495
CENTER AFT FUEL BOOST PUMP  CENTER AFT BOOST PUMP
GFI RELAY
5A (3 PLACES)  (3 PLACES)  (3 PLACES)
889  1266B  1266B
115VAC-ØC-L  T3  Q4P18C  2LA  Q4M16C  C2  C1  • Q12U16C
L3  310 IN.  175 IN.  1175 IN.
115VAC-ØB-L  Q5P18B  1LX  Q5M16B  B2  B1  • Q13U16B
310 IN.  175 IN.  1175 IN.
115VAC-ØA-L  Q6S18A  1LA  Q6P16A  A2  A1  • Q14U16A
310 IN.  175 IN  ,175 IN.
B1-922  R5-1494 R2-1494 R5-1494
CENTER FWD FUEL BOOST PUMP  | CENTER FWD BOOST PUMP|  GFI RELAY
UPPER EPC CIRCUIT BREAKER PANEL
AFT LEFT EQUIPMENT BAY
(6 PLACES)
706
Q14V18A  5LA
200 IN.
N  Q13V18B  5LX
200 IN.
M  Q12V18C  6LA
200 IN.
L  Q11V18A  7LA
200 IN.
K  Q10V18B  7LX
200 IN.
J  Q9V18C  8LA
200 IN.
P1-1307 R5-1307  S30-236
STA 246 L  STA 160 L
FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES
(SHEET 5 OF 7)
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### Page 55 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
R5-1306 P1-1306  STA 246 L
Q254V24  240 IN  Q253V24  240 IN.
1126
11BA  11BX  S30-236  STA 160 L
(1126
1268  Q254U20  175 IN.  R5-1494 R2-1494 R5-1494  CENTER FWD BOOST PUMP GFI RELAY  1268 0253U20  (1268)  175 IN  R5-1495 R2-1495 R5-1495  CENTER AFT BOOST PUMP GFI RELAY
175 IN  • Q258F20 •  175 IN
(2 PLACES)  | 126
10BA  S30-236  STA 160 L
126
Q258D24  200 IN.
R2-593 R5-619  CENTER PUMP  PRESS INHIBIT
1889445
FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES
(SHEET 6 OF 7)
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### Page 56

The term code numbers shown below agree with the numbers shown in the term code symbols in the figure.
MORE DATAQTYPART NUMBERNAMETERM
CODE
10DC38-20PPIN, T/C 11261126
28DC38-16PPIN, T/C 11311131
12M39029/92-535SOCKET, T/C 1266B1266B
8M39029/92-533SOCKET, T/C 12681268
(a)5S00023-20SSOCKET, T/C 602/702702
1LRC22M-1DE5SOCKET, T/C 604604
6LRC16M-32DJ5SOCKET, T/C 706706
(a)25D0086-17TERM LUG, T/C 888888
(a)65D0086-18TERM LUG, T/C 889889
(a)25D0086-19TERM LUG, T/C 890890
(b)2CYW20END CAP914
(a)25D0010-15TERM BLOCK
(a)25D0101-2END CLAMP
(a)95D0107-3TERM BLOCK L
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Operator supplied parts.
FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES
(SHEET 7 OF 7)
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BOEING SERVICE BULLETIN MD90-28-013

### Page 57 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
This Figure applies only to: Group 2.
R2-583  CTR FWD BOOST  PUMP CNTRL  AFT RADIO RIGHT RACK  - TOP SHELF  STA 200
R5-611
+ T  + *F  P1-2272 R5-2472  STA 148 R
→ Q620A18B +  - Q621A18C +1  ‡  Q624B18C + / /  Q623B18B +-  11 Q622B18A
S3-290  STA 148 L  + Q627C20 +  71 Q641A20  R5-406  CENTER FWD BOOST PUMP CNTRL  LOWER EPC AFT LEFT SIDE
R2-336
1889466
FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES
(SHEET 1 OF 6)
Original Issue: September 27, 2013
Export Controlled ECCN: 9E991 - BOEING  MD90-28-013
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  57 of 134

### Page 58 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
R2-582  R5-610  CTR AFT BOOST  PUMP CNTRL  AFT RADIO RIGHT RACK  002 VIS
‡
00
63
1+ *C  P1.-3742R5-2472
Q636D18 +  Q635D18 +  Q634D18
S3-287  STA 148 L  D2 71 Q638A20 →  →
D3 7/ Q640A20  R5-407  CENTER AFT BOOST PUMP CNTRL  ЕРС
R2-337
1891142
FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES
(SHEET 2 OF 6)
Original Issue: September 27, 2013
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  MD90-28-013
Work - See page 1 for details.  58 of 134

### Page 59 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
CENTER FUEL TANK  P 1-530
**Q7B20N
12  17  22  S3-287  STA 148 L  S3-290  STA 148 L
017 Q95180 +  B1++ Q10518B +  A1 Y Q11S18A +  R5-407 R2-337 R5-407  CTR AFT BOOST PUMP CNTRL PANEL  xi„I  A1 + Q14S18A +  01/+ Q125180+11  B1 7 Q13S18B +→  R5-406 R2-336 R5-406  CTR FWD BOOST PUMP CNTRL PANEL  ЕРС
Q1L18C+/+ C2  Q2L18B+/ B2  1 Q3L18A +/ A2  —  + Q20A20++X1  250 + 021A20N +14 X2  Q15A20 -  289+14 Q16A20N+++ X2  +Q6L18A +++A2  111+ Q4L180+1C2  Q5L18B+/ B2
S3-18
S3-287  STA 148 L  1889501
FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES
(SHEET 3 OF 6)
Original Issue: September 27, 2013
Export Controlled ECCN: 9E991 - BOEING  MD90-28-013
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  59 of 134

### Page 60 (OCR)

BOEING SERVICE BULLETIN MD90-28-013
(2 PLACES)  (6 PLACES)
1126)  (1126  - (1126  702
1BX  Q622D20  9BA  Q622E20
270 IN.  150 IN.
S3-18
STA 148 L
(4 PLACES)
1268
X1  Q622C20
175 IN.
(4 PLACES)  (4 PLACES)
(1131)  (1131
12  Q627G20  10LA  Q627H20  T
175 IN.  150 IN.
13  Q641D20  I1LA  • Q641C20 -  *F
175 IN.  762  150 IN.
X2  Q643A20N  3022
15 IN
R2-1494 R5-1494
CENTER FWD BOOST PUMP GFI RELAY
4 PLACES)
1268)  762
X2  Q643B20N  3022
15 IN.
12  Q638G20  10LX  Q638H20  *C
175 IN.  150 IN.
13  Q640D20  11LX  Q640C20
175 IN.  150 IN.
X1  Q634E20
175 IN.
R2-1495 R5-1495
CENTER AFT BOOST PUMP GFI RELAY
AFT LEFT EQUIPMENT BAY
(2 PLACES)
(1126  (1126  (1126
9BX  Q634F20  9BX -  - Q634G20 -  G
270 IN.  150 IN.
S3-18  S30-236
STA 148 L  STA 160 L
P1-2272 R5-2472
STA 148 R  1891147
FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES
(SHEET 4 OF 6)
Original Issue: September 27, 2013
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  MD90-28-013
Work - See page 1 for details.  60 of 134

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