Commercial 

Airplanes MD90

Service Bulletin

Number: MD90-28-013

Original Issue: September 27, 2013

Revision 1: August 27, 2015

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.

ECCN: 9E991

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Unpublished Work.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.

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connection with this document unless provided in writing by Boeing.

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BLANK PAGE
Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

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

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

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

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

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 22

4. Process Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 31

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 33

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

FIGURE 1: REMOVE RELAYS R2-218 AND R2-219 - FORWARD CARGO COMPARTMENT, LEFT SIDE

[Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

FIGURE 2: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK [Group

1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

FIGURE 3: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK [Group

3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

FIGURE 4: REMOVE RELAYS R2-336, R2-337 AND RECEPTACLES R5-406, R5-407 - ELECTRICAL

POWER CENTER [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53

FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES [Group 1] . . . . . . . . . . . . . . . . . 55

FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES [Group 2] . . . . . . . . . . . . . . . . . 62

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BOEING SERVICE BULLETIN MD90-28-013
FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES [Group 3] . . . . 68

FIGURE 8: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

[Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81

FIGURE 9: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

[Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84

FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

[Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES [Group 1] . . . . . . . . 92

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES [Group 2] . . . . . . . 105

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES [Group 3] . . . 119

APPENDIX D: BOEING PART DEMAND INTENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 140

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BOEING SERVICE BULLETIN MD90-28-013
Commercial 

Airplanes MD90

Service Bulletin

Revision Transmittal Sheet Number: MD90-28-013

Original Issue: September 27, 2013

Revision 1: August 27, 2015

ATA System: 2800

SUBJECT: FUEL - Fuel Systems - Install Ground Fault Interrupter Relays and Change Fuel Pump

System Wiring

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-18-05 is related to this service bulletin.

Effects of this Revision on airplanes on which Original Issue was previously done:

None.

REASON FOR REVISION

This revision is sent to incorporate engineering released after the original issue of this service bulletin to address

the no work conditions due to Ground Fault Interrupter (GFI) panel washers, GFI panel mounting holes too

small, wire assembly routing and process issues encountered during validation of the original issue of this service

bulletin.

The data given in Information Notice MD90-28-013 IN 01 is included in this revision.

As a part of a service bulletin validation program, this installation was completed on airplane fuselage number

2097 by Service Bulletin MD90-28-013 Original Issue before the release of Revision 1 of this service bulletin.

The installation/change completed on airplane fuselage number 2097 by Service Bulletin MD90-28-013 Original

Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane fuselage number 2097 has the

configuration of a Group 1 airplane.

These sections were changed:

1. In Background, added Boeing Fleet Team Digest (FTD) statement.

2. In Background, added Summary Evaluation Table.

3. In Paragraph 1.C., Reason, added statements.

4. In Paragraph 1.D., Description, added Compliance statement.

5. In Paragraph 1.G., Manpower, updated Manpower.

6. In Paragraph 1.H., Weight and Balance Changes, updated Group 1 through Group 3, information.

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7. In Paragraph 1.J.1., Existing Data: added additional references.

8. In Paragraph 1.J.2.a., Drawings: changed drawing revision.

9. In Paragraph 1.J.3., Installation Drawings Used in the preparation of this Service Bulletin: changed

drawing revision.

10. In Paragraph 1.K.1., Publications: updated information.

11. In Paragraph 2.A., Material - Price and Availability, added survey information.

12. In Paragraph 2.C.1., Kits/Parts, Group 1 through Group 3, Service KIt, updated information.

13. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added part information.

14. In Paragraph 2.C.3., Parts Modified and Reidentified, Group 1 through Group 3, added parts.

15. In Paragraph 3.A., General Information, Note: added new note.

16. In paragraph 3.B., Work Instructions, Group 1 through Group 3, added instructions.

17. In Figure 5 through Figure 7, added a reference.

18. In Figure 8, changed view A and B and added view C.

19. In Figure 8, changed part number and added footnotes (b), (c), (d) and (e).

20. In Figure 9, changed view A and B and added view C.

21. In Figure 9, changed part number and added footnotes (b), (c), (d) and (e).

22. In Figure 10, changed view A and B and added view C.

23. In Figure 10, changed part number and added footnotes (b), (c), (d) and (e).

24. Added Appendix D.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,

to show the location of all content changes.

Pages with no vertical lines have no changes.

REVISION HISTORY

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BOEING SERVICE BULLETIN MD90-28-013
Commercial 

Airplanes MD90

Service Bulletin

Summary Number: MD90-28-013

Original Issue: September 27, 2013

Revision 1: August 27, 2015

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) MD90 FTD 28-03001 and MD90 FTD 28-12002 are related to this service

bulletin.

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

information.

Planning Data Affected Reference

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

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change Yes Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed Yes Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

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Planning Data Affected Reference

Airplane Flight Operations Affected (Flight Crew Yes Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

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

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

by the Operator

Operator Supplied Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

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

MD90-30 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.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

MANPOWER

Group Total Task Hours Elapsed Hours

1 58.0 31.0

2 45.3 24.4

3 142.7 73.7

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BLANK PAGE
Commercial 

Airplanes MD90

Service Bulletin

Number: MD90-28-013

Original Issue: September 27, 2013

Revision 1: August 27, 2015

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.

GROUP CONFIGURATION DESCRIPTION

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

Fuselage Num- Group

ber

2094 - 2099 1

2100 1

2115 1

2117 1

2120 1

2122 - 2123 1

2125 - 2126 1

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Fuselage Num- Group

ber

2129 1

2131 1

2133 1

2136 1

2138 1

2140 - 2144 1

2146 - 2147 1

2149 - 2150 1

2153 - 2154 1

2156 - 2159 1

2161 - 2166 1

2169 - 2171 1

2173 1

2175 1

2177 1

2179 1

2181 - 2182 1

2184 1

2186 1

2190 1

2191 2

2193 - 2195 1

2197 - 2198 1

2200 1

2202 - 2203 1

2205 2

2207 1

2209 2

2210 - 2212 1

2213 2

2215 - 2216 2

2217 1

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Fuselage Num- Group

ber

2219 2

2220 1

2221 2

2222 1

2223 2

2224 1

2225 - 2227 2

2228 1

2229 - 2232 2

2233 1

2235 2

2236 1

2237 2

2238 1

2240 1

2242 1

2243 3

2245 - 2246 1

2248 1

2250 - 2251 2

2253 1

2255 - 2257 2

2258 - 2259 1

2260 2

2261 1

2262 - 2263 2

2288 - 2290 2

4001 - 4002 1

2. Spares Affected

None.

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BOEING SERVICE BULLETIN MD90-28-013
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.

Revision 1 is sent to incorporate engineering released after the original issue of this service bulletin to

address the no work conditions due to Ground Fault Interrupter (GFI) panel washers, GFI panel mounting

holes too small, wire assembly routing and process issues encountered during validation of the original

issue of this service bulletin.

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) MD90 FTD 28-03001 and MD90 FTD 28-12002 are related to this

service bulletin.

The data given in Information Notice MD90-28-013 IN 01 is included in this revision.

As a part of a service bulletin validation program, this installation was completed on airplane fuselage

number 2097 by Service Bulletin MD90-28-013 Original Issue before the release of Revision 1 of this

service bulletin. The installation completed on airplane fuselage number 2097 by Service Bulletin

MD90-28-013 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane

fuselage number 2097 has the configuration of a Group 1 airplane.

D. Description

Revision 1 - Effects of this Revision on airplanes on which Original Issue was previously done:

None.

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

Model Zone

MD-90-30 112, 114, 115, 121, 211, 221

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BOEING SERVICE BULLETIN MD90-28-013
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.

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:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 2.5 2.5

FIGURE 2 1 0.3 0.3

Route and Clip Wire 2 47.0 23.5

FIGURE 5 2 5.8 2.9

FIGURE 8 1 0.6 0.6

Close Access 1 2.5 2.5

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Group 1:

Task Number of Persons Task Hours Elapsed Hours

Test 2 1.2 0.6

TOTAL FOR EACH AIRPLANE 59.9 32.9

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 2.0 2.0

FIGURE 2 1 0.3 0.3

FIGURE 4 1 0.5 0.5

Route and Clip Wire 2 35.0 17.5

FIGURE 6 2 5.0 2.5

FIGURE 9 1 0.6 0.6

Close Access 1 2.0 2.0

Test 2 1.8 0.9

TOTAL FOR EACH AIRPLANE 47.2 26.3

Group 3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 2.5 2.5

FIGURE 1 1 0.2 0.2

FIGURE 3 1 0.5 0.5

Route and Clip Wire 2 124.0 62.0

FIGURE 7 2 10.4 5.2

FIGURE 10 1 1.0 1.0

Close Access 1 2.5 2.5

Test 2 3.6 1.8

TOTAL FOR EACH AIRPLANE 144.7 75.7

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H. Weight and Balance Changes

Group 1:

Moment Change

(MEW) IN.-LBS

Mfr's Empty

Weight (MEW)

LBS

Approximate StaAirplane tion (Inches)

MD-90-30 + 368.0 +0.7 +257.6

Group 2:

Moment Change

(MEW) IN.-LBS

Mfr's Empty

Weight (MEW)

LBS

Approximate StaAirplane tion (Inches)

MD-90-30 + 174.6 -0.5 -87.3

Group 3:

Moment Change

(MEW) IN.-LBS

Mfr's Empty

Weight (MEW)

LBS

Approximate StaAirplane tion (Inches)

MD-90-30 + 163.4 +3.5 +571.9

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 International

EQUIPMENT NAME

PART NUMBER

GFI FWD AUX Tank Fuel

XFR Pump A

KDG-X4L-001

ITEM

R2-

1496

CHAP

280

BUS

1L

% TIME OPR AVERAGE AMPS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

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Group 3:

UNITS

%OPR

1

100

E/NE

E

UNIT

LOAD

AMPS

0.112

NOTES

(B1-903)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

GFI FWD AUX Tank Fuel

XFR Pump A

KDG-X4L-001

ITEM

R2-

1496

CHAP

280

BUS

1L

% TIME OPR AVERAGE AMPS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

TAKEOFF & CLIMB 100 100 0.112 0.112 0.112

CRUISE COLD 100 100 0.112 0.112 0.112

CRUISE HOT 100 100 0.112 0.112 0.112

DESCENT & LAND 50 50 0.112 0.056 0.056

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

Group 3:

UNITS

%OPR

1

100

E/NE

E

UNIT

LOAD

AMPS

0.112

NOTES

(B1-904)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

GFI FWD AUX Tank Fuel

XFR Pump B

KDG-X4L-001

ITEM

R2-

1497

CHAP

280

BUS

2R

% TIME OPR AVERAGE AMPS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 100 100 0.112 0.112 0.112

CRUISE COLD 100 100 0.112 0.112 0.112

CRUISE HOT 100 100 0.112 0.112 0.112

DESCENT & LAND 50 50 0.112 0.056 0.056

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

b. Delete DC loads by amounts shown below:

Group 1-2:

No DC loads deleted.

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Group 3:

UNITS

%OPR

1

100

E/NE

E

UNIT

LOAD

AMPS

0.37

NOTES

(B1-907)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

FWD AUX Tank Fuel XFR

Pump A

5D0281-1

ITEM

R2-218

CHAP

280

BUS

1L

% TIME OPR AVERAGE AMPS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 100 100 0.37 0.37 0.37

CRUISE COLD 100 100 0.37 0.37 0.37

CRUISE HOT 100 100 0.37 0.37 0.37

DESCENT & LAND 50 50 0.37 0.19 0.19

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

Group 3:

UNITS

%OPR

1

100

E/NE

E

UNIT

LOAD

AMPS

0.37

NOTES

(B1-908)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

FWD AUX Tank Fuel XFR

Pump B

5D0281-1

ITEM

R2-219

CHAP

280

BUS

2R

% TIME OPR AVERAGE AMPS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 100 100 0.37 0.37 0.37

CRUISE COLD 100 100 0.37 0.37 0.37

CRUISE HOT 100 100 0.37 0.37 0.37

DESCENT & LAND 50 50 0.37 0.19 0.19

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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2. Alternating Current (AC) Load Changes

a. Add AC loads by amounts shown below:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

1

UNIT

LOAD

(W)

5.75

NOTES

(B1-922)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Center FWD Boost Pump

GFI Relay

KDAG-X4F-001

ITEM

R2-

1494

CHAP

280

BUS

1L

% TIME OPR AVERAGE WATTS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 6 2 5.75 0.345 0.115

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 100 100 5.75 5.75 5.75

CRUISE COLD 100 100 5.75 5.75 5.75

CRUISE HOT 100 100 5.75 5.75 5.75

DESCENT & LAND 50 50 5.75 2.9 2.9

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

1

UNIT

LOAD

(W)

5.75

NOTES

(B1-923)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Center AFT Boost Pump

GFI Relay

KDAG-X4F-001

ITEM

R2-

1495

CHAP

280

BUS

2R

% TIME OPR AVERAGE WATTS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 6 2 5.75 0.345 0.115

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 100 100 5.75 5.75 5.75

CRUISE COLD 100 100 5.75 5.75 5.75

CRUISE HOT 100 100 5.75 5.75 5.75

DESCENT & LAND 50 50 5.75 2.9 2.9

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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b. Delete AC loads shown below:

Group 1, 3:

No AC loads deleted.

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 International

EQUIPMENT NAME

PART NUMBER

CNTR FWD BOOST PUMP

5D0024-1

ITEM

R2-

336

CHAP

280

BUS

1L

% TIME OPR AVERAGE WATTS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 100 100 11.5 11.5 11.5

CRUISE COLD 100 100 11.5 11.5 11.5

CRUISE HOT 100 100 11.5 11.5 11.5

DESCENT & LAND 50 50 5.75 5.75 5.75

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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 International

EQUIPMENT NAME

PART NUMBER

CNTR AFT BOOST PUMP

5D0024-1

ITEM

R2-

337

CHAP

280

BUS

2R

% TIME OPR AVERAGE WATTS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

LOADING 0 0 0 0 0

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 100 100 11.5 11.5 11.5

CRUISE COLD 100 100 11.5 11.5 11.5

CRUISE HOT 100 100 11.5 11.5 11.5

DESCENT & LAND 50 50 5.75 5.75 5.75

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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 International

EQUIPMENT NAME

PART NUMBER

CNTR AFT BOOST PUMP

5D0024-1

ITEM

R2-

337

CHAP

280

BUS

2R

% TIME OPR AVERAGE WATTS

CONDITION 2/5 M 15/30 M 5 S 2/5 M 15/30 M

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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. MD-90 Aircraft Maintenance Manual (AMM) MD90 AMM 06-31-00, 06-32-00, 08-10-00,

12-11-03, 12-11-07, 24-00-00, 25-23-01, 25-50-01, 27-50-00, 31-00-02, 31-14-00, 32-00-00,

32-11-01 and 52-63-00 .

d. Structural Repair Manual (SRM) Chapter 51.

e. Boeing Fleet Team Digest (FTD) 28-03001 and MD90 FTD 28-12002.

2. Data Supplied with this Service Bulletin:

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

ELEC INSTL - CTR & AUX TANKS FUEL DWG - -

BOOST & TRANSFER

SR90280010

SFAR 88 FUEL PUMP FRICTIONAL DWG G -

HEATING

SR90280011

CTR & AUX TANKS FUEL BOOST & DWG C -

TRANSFER

SR90280012

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

Document Number Title Change

ELEC INSTL - CTR & AUX TANKS -

FUEL BOOST & TRANSFER

SR90280010

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Document Number Title Change

SFAR 88 FUEL PUMP FRICTIONAL G

HEATING

SR90280011

CTR & AUX TANKS FUEL BOOST C

& TRANSFER

SR90280012

These drawings were used to prepare this service bulletin. These drawings are necessary to make

the specified changes, and are supplied with this service bulletin. These drawings may not be

applicable to all airplane configurations or operators.

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:

Publication Chapter-Section

FAA Approved Airplane Flight Manual Section 1 and 3

Flight Crew Operations Manual FCOM Advisory Bulletin 2-007

Illustrated Parts Catalog 24-50, 25-57

Aircraft Maintenance Manual 28-22

Special Compliance Item Report MDC-92K9145 (CDCCL 28-8)

Fault Isolation Manual 28-22

Wiring Diagram Manual 28-21, 28-24, 28-25, 28-42

System Schematic Manual 25-57, 28-22, 28-23, 28-25, 91-12

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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BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

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

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

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

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

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

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of the original issue date of this Service Bulletin

(US Dollars)

ROLT as of the original issue

date of this Service Bulletin

(Calendar Days)

Kit Number Name

SB90280013-3 Service Kit 150 $12,392.00

SB90280013-5 Service Kit 150 $13,043.00

SB90280013-7 Service Kit 150 $36,978.00

Operators are encouraged to complete the survey provided in APPENDIX D 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

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

New Part Number QTY Name Notes

SB90280013-101 1 WIRE KIT (a)

5D0010-15 2 TERM BLOCK (b)

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Group 1:

SB90280013-3 Service Kit

New Part Number QTY Name Notes

5D0101-2 2 END CLAMP (b)

5D0107-3 9 TERM BLOCK L (b)

9D0090-12U 1 TRACK (b)

9D0254-1-1-9 6 STRAP (b)

ABN7294-629 2 BRACKET

CSCS-M 6 MOUNT

KDAG-X4F-001 2 GFI RELAY

MS21042L08 2 NUT

MS21042L3 4 NUT

MS35206-242 2 SCREW

MS35338-43 1 LOCKWASHER

NAS1096-3-11 1 SCREW

NAS1096-3-6 4 SCREW

NAS1149F0332P 1 WASHER

NAS1252-10L 4 WASHER

S124682-3D8-3 2 WASHER (b)

SO-1061-8916 2 RELAY SOCKET

NAS620C10 (.063 8 WASHER (c) (d)

Thickness)

(a) Refer to SB90280013-101 Wire Kit table for Wire Kit contents.

(b) Or approved equivalent. Refer to AEPL Drawing 7595071.

(c) Boeing furnished part.

(d) NAS620C10L Washers are furnished with Relay Socket and are not

used in this installation. Keep the washers if there are other uses for

them.

Group 1:

SB90280013-101 Wire Kit

New Part Number QTY Name Notes

175 WIRE CODE 801 (a)

FT.

D2426-1C-16NM

369 WIRE CODE 801 (a)

FT.

D2426-1C-18NM

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Group 1:

SB90280013-101 Wire Kit

New Part Number QTY Name Notes

D2426-1C-20NM 96 FT. WIRE CODE 801 (a)

D2426-1C-24NM 57 FT. WIRE CODE 801 (a)

5D0086-17 2 TERM LUG, T/C 888 (b)

5D0086-18 6 TERM LUG, T/C 889 (b)

5D0086-19 2 TERM LUG, T/C 890 (b)

DC38-16P 28 PIN, T/C 1131

DC38-20P 10 PIN, T/C 1126

LRC16M-32DJ5 6 SOCKET, T/C 706

LRC22M-1DE5 1 SOCKET, T/C 604

M39029/92-533 8 SOCKET, T/C 1268

M39029/92-535 12 SOCKET, T/C 1266B

SOCKET, T/C (b)

602/702

S00023-20S 5

(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

New Part Number QTY Name Notes

SB90280013-102 1 WIRE KIT (a)

5D0010-15 1 TERM BLOCK (b)

5D0101-2 2 END CLAMP (b)

5D0107-3 10 TERM BLOCK L (b)

9D0090-12U 1 TRACK (b)

9D0254-1-1-9 6 STRAP (b)

ABN7294-629 2 BRACKET

AN315-3R 2 NUT

CSCS-M 6 MOUNT

KDAG-X4F-001 2 GFI RELAY

MS21042L08 2 NUT

MS21042L3 4 NUT

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Group 2:

SB90280013-5 Service Kit

New Part Number QTY Name Notes

MS35206-242 2 SCREW

MS35338-43 2 LOCKWASHER

NAS1096-3-11 1 SCREW

NAS1096-3-6 4 SCREW

NAS1149F0332P 3 WASHER

NAS1252-10L 4 WASHER

S124682-3D8-3 2 WASHER (b)

SO-1061-8916 2 RELAY SOCKET

NAS620C10 (.063 8 WASHER (c) (d)

Thickness)

(a) Refer to SB90280013-102 Wire Kit table for Wire Kit contents.

(b) Or approved equivalent. Refer to AEPL Drawing 7595071.

(c) Boeing furnished part.

(d) NAS620C10L Washers are furnished with Relay Socket and are not

used in this installation. Keep the washers if there are other uses for

them.

Group 2:

SB90280013-102 Wire Kit

New Part Number QTY Name Notes

175 WIRE CODE 801 (a)

FT.

D2426-1C-16NM

115 WIRE CODE 801 (a)

FT.

D2426-1C-18NM

210 WIRE CODE 801 (a)

FT.

D2426-1C-20NM

5D0086-6 2 TERM LUG, T/C 762 (b)

DC38-16P 32 PIN, T/C 1131

DC38-20P 8 PIN, T/C 1126

M39029/92-533 8 SOCKET, T/C 1268

M39029/92-535 12 SOCKET, T/C 1266B

SOCKET, T/C (b)

602/702

S00023-20S 6

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Group 2:

SB90280013-102 Wire Kit

New Part Number QTY Name Notes

YHMM16-3F50 12 PIN, T/C 612

(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

New Part Number QTY Name Notes

SB90280013-103 1 WIRE KIT (a)

5D0010-15 2 TERM BLOCK (b)

5D0101-2 4 END CLAMP (b)

5D0107-1 2 TERM BLOCK (b)

5D0107-3 18 TERM BLOCK L (b)

9D0090-12U 2 TRACK (b)

9D0254-1-1-9 6 STRAP (b)

ABN7294-629 3 BRACKET

CSCS-M 6 MOUNT

KDAG-X4F-001 2 GFI RELAY

KDG-X4L-001 2 GFI RELAY

MS21042L08 4 NUT

MS21042L3 6 NUT

MS35206-242 4 SCREW

MS35338-43 1 LOCKWASHER

NAS1096-3-11 1 SCREW

NAS1096-3-6 6 SCREW

NAS1149F0332P 1 WASHER

NAS1252-10L 6 WASHER

RSE500311 2 RELAY SOCKET

S124682-3D8-3 4 WASHER (b)

SO-1061-8916 2 RELAY SOCKET

NAS620C10 (.063 8 WASHER (c) (d)

Thickness)

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Group 3:

SB90280013-7 Service Kit

New Part Number QTY Name Notes

(a) Refer to SB90280013-103 Wire Kit table for Wire Kit contents.

(b) Or approved equivalent. Refer to AEPL Drawing 7595071.

(c) Boeing furnished part.

(d) NAS620C10L Washers are furnished with Relay Socket and are not

used in this installation. Keep the washers if there are other uses for

them.

Group 3:

SB90280013-103 Wire Kit

New Part Number QTY Name Notes

350 WIRE CODE 801 (a)

FT.

D2426-1C-16NM

369 WIRE CODE 801 (a)

FT.

D2426-1C-18NM

1003 WIRE CODE 801 (a)

FT.

D2426-1C-20NM

D2426-1C-24NM 57 FT. WIRE CODE 801 (a)

5D0086-17 2 TERM LUG, T/C 888 (b)

5D0086-18 6 TERM LUG, T/C 889 (b)

5D0086-19 2 TERM LUG, T/C 890 (b)

5D0086-5 10 TERM LUG, T/C 761 (b)

5D0086-6 8 TERM LUG, T/C 762 (b)

DC38-16P 62 PIN, T/C 1131

DC38-20P 10 PIN, T/C 1126

LRC16M-32DJ5 12 SOCKET, T/C 706

LRC22M-1DE5 1 SOCKET, T/C 604

M39029/92-533 16 SOCKET, T/C 1268

M39029/92-535 24 SOCKET, T/C 1266B

S00023-20P 16 PIN, T/C 601/701 (b)

SOCKET, T/C (b)

602/702

S00023-20S 19

(a) Or approved alternate. Refer to SWPM 20-00-13.

(b) Or approved equivalent. Refer to AEPL Drawing 7595071.

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2. Parts and Materials Supplied by the Operator

Part Number / Specifica- QTY Name Notes

tion

18XTZ, 23XTZ As Required Tie Tape (a)

(DMS 2089)

or

Equivalent

Alodine 1200S As Required Chemical Conversion Coating (b)

(DPM 1453-5)

or

Equivalent

CYW20 2 End Cap

Koropon 515-700 with Cata- As Required Primer, Fluid Resistant (b)

lyst 910-704

(DMS 1786)

or

Equivalent

9D0254-1-1-9 As Required Strap (c) (d)

(PLT2S-9)(SST2S)

or

Equivalent

2712453-BN As Required Spacer

DMS 2109 As Required Sleeve

(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

Group 1:

New Part Name

Number

Existing Part Number QTY Name

7927157-707 1 Clip Assembly SR90280011-3 Bracket

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Group 2:

Existing Part Num- QTY Name New Part Number

ber

7961078-795 1 Bracket SR90280011-5

Group 3:

Existing Part Num- QTY Name New Part Number

ber

7927157-707 1 Bracket SR90280011-7

4. Parts Removed and Not Replaced

Group 1:

None.

Group 2:

Existing Part Number Name QTY Notes

R2-336 and R2-337 (a)

(b)

5D0024-1 RELAY 2

R5-406 and R5-407 (a)

(b)

5D0020-10 RELAY SOCKET 2

(a) Keep the part if there are other uses for it.

(b) Or approved equivalent. Refer to AEPL Drawing 7595071.

Group 3:

Existing Part Number Name QTY Notes

R2-218 and R2-219 (a)

(b)

5D0281-1 RELAY 2

ABN7294-627 BRACKET 1 (a)

(a) Keep the part if there are other uses for it.

(b) Or approved equivalent. Refer to AEPL Drawing 7595071.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

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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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BLANK PAGE
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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Chapter Title

SWPM 20-00-00 General - Maintenance Safety Practices

SWPM 20-00-09 General Maintenance Practices - Electrical

SWPM 20-00-13 Electrical Wire Codes

SWPM 20-00-16 Electrical Wire End Termination Codes and Tool Codes

SWPM 20-10-01 Wiring Installation - Maintenance Practices

SWPM 20-10-02 Shielding - Maintenance Practices

SWPM 20-10-04 Coil and Stow - Maintenance Practices

SWPM 20-20-02 Terminal Blocks - Maintenance Practices

SWPM 20-20-03 General Installations Hardware - Maintenance Practices

SWPM 20-31-00 Electrical Connectors - Maintenance Practices

SWPM 20-40-01 Power Distribution Bus - Maintenance Practices

SWPM 20-50-01 Electrical Bonding - Maintenance Practices

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:

Terminal Block ID Letter Part Number

B 5D0010-15

J 5D0010-13

L 5D0107-3

CC 5D0106-1

DD 5D0107-1

HH 5D0010-11

EE (End Clamp) 5D0101-2

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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. 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.

17. 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.

18. 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.

19. Use DMS 2109 Sleeve as required. Refer to SWPM 20-10-01.

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.

Access Door Location

110BL Electrical/Electronics (E/E) Compartment

115AZ Forward Accessory Compartment

610BB Right Wing Leading Edge

b. Open Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted

procedure.

c. Open Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure.

d. Open overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02

as an accepted procedure.

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e. Remove and keep left cockpit sidewall panels. Refer to MD90 AMM 06-32-00 as an accepted

procedure.

f. Remove and keep left console. Refer to MD90 AMM 31-14-00 as an accepted procedure.

g. 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.

h. 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.

i. Remove and keep forward cabin attendant's seat and attaching parts. Refer to MD90 AMM

25-23-01 as an accepted procedure.

j. Remove and keep aft Electrical Power Center (EPC) panel 221CL and attaching parts. Refer

to MD90 AMM 06-32-00.

3. Install brackets and track in accordance with FIGURE 2.

4. Enlarge holes and identify as Bracket, 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 Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure.

h. Close Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted

procedure.

i. Close overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02

as an accepted procedure.

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j. Close access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.

Access Door Location

110BL Electrical/Electronics (E/E) Compartment

115AZ Forward Accessory Compartment

610BB Right Wing Leading Edge

8. Do 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.

Access Door Location

110BL Electrical/Electronics (E/E) Compartment

115AZ Forward Accessory Compartment

610BB Right Wing Leading Edge

b. Open Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted

procedure.

c. Open Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure.

d. Remove and keep left console. Refer to MD90 AMM 31-14-00 as an accepted procedure.

e. Remove and keep forward cabin attendant's seat and attaching parts. Refer to MD90 AMM

25-23-01 as an accepted procedure.

f. 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 track in accordance with FIGURE 2.

5. Enlarge holes and identify as Bracket, install Ground Fault Interrupter (GFI) relays and receptacles

in accordance with FIGURE 9.

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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 Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure.

e. Close Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted

procedure.

f. Close access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.

Access Door Location

110BL Electrical/Electronics (E/E) Compartment

115AZ Forward Accessory Compartment

610BB Right Wing Leading Edge

9. Do 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.

Access Door Location

110BL Electrical/Electronics (E/E) Compartment

115AZ Forward Accessory Compartment

610BB Right Wing Leading Edge

b. Open Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted

procedure.

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c. Open Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure.

d. Open overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02

as an accepted procedure.

e. Remove and keep left cockpit sidewall panels. Refer to MD90 AMM 06-32-00 as an accepted

procedure.

f. Remove and keep left console. Refer to MD90 AMM 31-14-00 as an accepted procedure.

g. 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.

h. 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.

i. Remove and keep cargo compartment aft panel at station Y=879.000. Refer to MD90 AMM

25-50-01 as an accepted procedure.

j. Remove and keep forward cabin attendant's seat and attaching parts. Refer to MD90 AMM

25-23-01 as an accepted procedure.

k. 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 track in accordance with FIGURE 3.

5. Enlarge holes and identify as Bracket, 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.

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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 Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure.

i. Close Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted

procedure.

j. Close overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02

as an accepted procedure.

k. Close access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.

Access Door Location

110BL Electrical/Electronics (E/E) Compartment

115AZ Forward Accessory Compartment

610BB Right Wing Leading Edge

9. Restore electrical power to the airplane. Refer to MD90 AMM 24-00-00 as an accepted procedure.

10. Do 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.

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This Figure applies only to: Group 3.

FIGURE 1: REMOVE RELAYS R2-218 AND R2-219 - FORWARD CARGO COMPARTMENT, LEFT SIDE

(SHEET 1 OF 2)

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

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove Screw NAS1096-2-8 8

Washer NAS1149DN816H 8

Relay 5D0281-1 2 R2-218, R2-219 (a)

(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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This Figure applies only to: Group 1-2.

FIGURE 2: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 1 OF 4)

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FIGURE 2: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 2 OF 4)

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FIGURE 2: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 3 OF 4)

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

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install/New Bracket ABN7294-629 2 (a)

2 Screw NAS1096-3-6 4

Washer NAS1252-10L 4

Nut MS21042L3 4

3 Install/New Track 9D0090-12U 1 (b)

4 Screw MS35206-242 2

Washer S124682-3D8-3 2

Nut MS21042L08 2

(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 TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 4 OF 4)

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This Figure applies only to: Group 3.

FIGURE 3: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 1 OF 4)

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FIGURE 3: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 2 OF 4)

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FIGURE 3: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 3 OF 4)

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

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove Screw NAS1096-3-7 2

Washer NAS1252-10L 2

Nut MS21042L3 2

Bracket ABN7294-627 1

2 Install/New Bracket ABN7294-629 3 (a)

3 Screw NAS1096-3-6 6

Washer NAS1252-10L 6

Nut MS21042L3 6

4 Install/New Track 9D0090-12U 2 (b) (c)

5 Screw MS35206-242 4

Washer S124682-3D8-3 4

Nut MS21042L08 4

(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 TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 4 OF 4)

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This Figure applies only to: Group 2.

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

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove RELAY (R2-336) 5D0024-1 1 (a) (b)

RECEPTACLE (R5- 5D0020-10 1

406)

2 Remove RELAY (R2-337) 5D0024-1 1 (a) (b)

RECEPTACLE (R5- 5D0020-10 1

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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This Figure applies only to: Group 1.

FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 1 OF 7)

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FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 2 OF 7)

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FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 3 OF 7)

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FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 4 OF 7)

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FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 5 OF 7)

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FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 6 OF 7)

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BOEING SERVICE BULLETIN MD90-28-013
Reference: MD90 WDM 28-42-00 and MD90 WDM 28-25-11.

The term code numbers shown below agree with the numbers shown in the term code symbols in the figure.

TERM NAME PART NUMBER QTY MORE DATA

CODE

1126 PIN, T/C 1126 DC38-20P 10

1131 PIN, T/C 1131 DC38-16P 28

1266B SOCKET, T/C 1266B M39029/92-535 12

1268 SOCKET, T/C 1268 M39029/92-533 8

702 SOCKET, T/C 602/702 S00023-20S 5 (a)

604 SOCKET, T/C 604 LRC22M-1DE5 1

706 SOCKET, T/C 706 LRC16M-32DJ5 6

888 TERM LUG, T/C 888 5D0086-17 2 (a)

889 TERM LUG, T/C 889 5D0086-18 6 (a)

890 TERM LUG, T/C 890 5D0086-19 2 (a)

914 END CAP CYW20 2 (b)

TERM BLOCK 5D0010-15 2 (a)

END CLAMP 5D0101-2 2 (a)

TERM BLOCK L 5D0107-3 9 (a)

(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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This Figure applies only to: Group 2.

FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 1 OF 6)

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FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 2 OF 6)

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FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 3 OF 6)

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FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 4 OF 6)

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FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 5 OF 6)

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Reference: MD90 WDM 28-42-00 and MD90 WDM 28-25-11.

The term code numbers shown below agree with the numbers shown in the term code symbols in the figure.

TERM NAME PART NUMBER QTY MORE DATA

CODE

1126 PIN, T/C 1126 DC38-20P 8

1131 PIN, T/C 1131 DC38-16P 32

1266B SOCKET, T/C 1266B M39029/92-535 12

1268 SOCKET, T/C 1268 M39029/92-533 8

702 SOCKET, T/C 602/702 S00023-20S 6 (a)

612 PIN, T/C 612 YHMM16-3F50 12

762 TERM LUG, T/C 762 5D0086-6 2 (a)

914 END CAP CYW20 2 (b)

TERM BLOCK 5D0010-15 1 (a)

END CLAMP 5D0101-2 2 (a)

TERM BLOCK L 5D0107-3 10 (a)

(a) Or approved equivalent. Refer to AEPL Drawing 7595071.

(b) Operator supplied parts.

FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES

(SHEET 6 OF 6)

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This Figure applies only to: Group 3.

FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 1 OF 13)

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FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 2 OF 13)

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FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 3 OF 13)

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FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 4 OF 13)

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FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 5 OF 13)

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FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 6 OF 13)

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FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 7 OF 13)

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FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 8 OF 13)

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FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 9 OF 13)

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FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 10 OF 13)

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FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 11 OF 13)

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BOEING SERVICE BULLETIN MD90-28-013
FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 12 OF 13)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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79 of 140

BOEING SERVICE BULLETIN MD90-28-013
Reference: MD90 WDM 28-42-00 and MD90 WDM 28-25-11.

The term code numbers shown below agree with the numbers shown in the term code symbols in the figure.

TERM NAME PART NUMBER QTY MORE DATA

CODE

1126 PIN, T/C 1126 DC38-20P 10

1131 PIN, T/C 1131 DC38-16P 62

1266B SOCKET, T/C 1266B M39029/92-535 24

1268 SOCKET, T/C 1268 M39029/92-533 16

601/701 PIN, T/C 601/701 S00023-20P 16 (a)

702 SOCKET, T/C 602/702 S00023-20S 19 (a)

604 SOCKET, T/C 604 LRC22M-1DE5 1

706 SOCKET, T/C 706 LRC16M-32DJ5 12

761 TERM LUG, T/C 761 5D0086-5 10 (a)

762 TERM LUG, T/C 762 5D0086-6 8 (a)

888 TERM LUG, T/C 888 5D0086-17 2 (a)

889 TERM LUG, T/C 889 5D0086-18 6 (a)

890 TERM LUG, T/C 890 5D0086-19 2 (a)

914 END CAP CYW20 2 (b)

TERM BLOCK 5D0010-15 2 (a)

END CLAMP 5D0101-2 4 (a)

TERM BLOCK 5D0107-1 2 (a)

TERM BLOCK L 5D0107-3 18 (a)

(a) Or approved equivalent. Refer to AEPL Drawing 7595071.

(b) Operator supplied parts.

FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES

(SHEET 13 OF 13)

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This Figure applies only to: Group 1.

FIGURE 8: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 1 OF 3)

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FIGURE 8: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN MD90-28-013
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Drill Clip Assembly 7927157-707 1 (e)

2 Identify (not shown) Bracket SR90280011-3 1 (f)

3 Install/New RELAY KDAG-X4F-001 1 R2-1495 (a) (b)

4 RECEPTACLE SO-1061-8916 1 R5-1495

NAS620C10 (.063 4 (c) (d)

Thickness)

5 WASHER

6 SPACER 002-9559-000-000 4 (b)

7 WASHER NAS620C4L 4 (b)

8 NUT NAS1291C04CM 4 (b)

9 Install/New RELAY KDAG-X4F-001 1 R2-1494 (a) (b)

10 RECEPTACLE SO-1061-8916 1 R5-1494

NAS620C10 (.063 4 (c) (d)

Thickness)

11 WASHER

12 SPACER 002-9559-000-000 4 (b)

13 WASHER NAS620C4L 4 (b)

14 NUT NAS1291C04CM 4 (b)

(a) Applicable item number must be adjacent and visible after equipment is installed. Refer to SWPM 20-00-

09 as an accepted procedure.

(b) Mounting Hardware vendor furnished.

(c) Boeing furnished part.

(d) NAS620C10L Washers are furnished with Receptacle and are not used in this installation. Keep the

washers if there are other uses for them.

(e) Drill .199-.202 diameter holes, 8 places.

(f) Reidentify Clip Assembly 7927157-707 as SR90280011-3 Bracket.

FIGURE 8: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 3 OF 3)

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This Figure applies only to: Group 2.

FIGURE 9: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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FIGURE 9: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 2 OF 3)

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

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Drill Clip Assembly 7961078-795 1 (e)

2 Identify (not shown) Bracket SR90280011-5 1 (f)

3 Install/New RELAY KDAG-X4F-001 1 R2-1495 (a) (b)

4 RECEPTACLE SO-1061-8916 1 R5-1495

NAS620C10 (.063 4 (c) (d)

Thickness)

5 WASHER

6 SPACER 002-9559-000-000 4 (b)

7 WASHER NAS620C4L 4 (b)

8 NUT NAS1291C04CM 4 (b)

9 Install/New RELAY KDAG-X4F-001 1 R2-1494 (a) (b)

10 RECEPTACLE SO-1061-8916 1 R5-1494

NAS620C10(.063 4 (c) (d)

Thickness)

11 WASHER

12 SPACER 002-9559-000-000 4 (b)

13 WASHER NAS620C4L 4 (b)

14 NUT NAS1291C04CM 4 (b)

(a) Applicable item number must be adjacent and visible after equipment is installed. Refer to SWPM 20-00-

09 as an accepted procedure.

(b) Mounting Hardware vendor furnished.

(c) Boeing furnished part.

(d) NAS620C10L Washers are furnished with Receptacle and are not used in this installation. Keep the

washers if there are other uses for them.

(e) Drill .199-.202 diameter holes, 8 places.

(f) Reidentify Clip Assembly 7961078-795 as SR90280011-5 Bracket.

FIGURE 9: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 3 OF 3)

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This Figure applies only to: Group 3.

FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 1 OF 5)

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FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 2 OF 5)

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FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 3 OF 5)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN MD90-28-013
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Drill Clip Assembly 7927157-707 1 (e)

2 Identify (not shown) Bracket SR90280011-7 1 (f)

3 Install/New RELAY KDAG-X4F-001 1 R2-1495 (a) (b)

4 RECEPTACLE SO-1061-8916 1 R5-1495

NAS620C10 (.063 4 (c) (d)

Thickness)

5 WASHER

6 SPACER 002-9559-000-000 4 (b)

7 WASHER NAS620C4L 4 (b)

8 NUT NAS1291C04CM 4 (b)

9 Install/New RELAY KDAG-X4F-001 1 R2-1494 (a) (b)

10 RECEPTACLE SO-1061-8916 1 R5-1494

NAS620C10 (.063 4 (c) (d)

Thickness)

11 WASHER

12 SPACER 002-9559-000-000 4 (b)

13 WASHER NAS620C4L 4 (b)

14 NUT NAS1291C04CM 4 (b)

15 Install/New RELAY KDG-X4L-001 1 R2-1497 (a) (b)

16 RECEPTACLE RSE500311 1 R5-1497(b)

17 SCREW 002-9653-000-000 3 (b)

18 SPLIT WASHER MS35338-135 3 (b)

19 WASHER NAS620C4L 3 (b)

20 SPACER 002-9447-000-000 3 (b)

21 MOUNTING STUD 200500101 3 (b)

22 WASHER 200500401 3 (b)

23 LOCK-NUT NAS679C04W 3 (b)

FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 4 OF 5)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

24 Install/New RELAY KDG-X4L-001 1 R2-1496 (a) (b)

25 RECEPTACLE RSE500311 1 R5-1496(b)

26 SCREW 002-9653-000-000 3 (b)

27 SPLIT WASHER MS35338-135 3 (b)

28 WASHER NAS620C4L 3 (b)

29 SPACER 002-9447-000-000 3 (b)

30 MOUNTING STUD 200500101 3 (b)

31 WASHER 200500401 3 (b)

32 LOCK-NUT NAS679C04W 3 (b)

(a) Applicable item number must be adjacent and visible after equipment is installed. Refer to SWPM 20-00-

09 as an accepted procedure.

(b) Mounting Hardware vendor furnished.

(c) Boeing furnished part.

(d) NAS620C10L Washers are furnished with Receptacle and are not used in this installation. Keep the

washers if there are other uses for them.

(e) Drill .199-.202 diameter holes, 14 places.

(f) Reidentify Clip Assembly 7927157-707 as SR90280011-7 Bracket.

FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK

(SHEET 5 OF 5)

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This Appendix applies only to: Group 1.

WARNING: DO NOT OPERATE A FUEL PUMP IN AN EMPTY FUEL TANK. PROLONGED DRY RUNNING

OF A FUEL PUMP IN AN EMPTY TANK CAN DEGRADE INTERNAL PUMP COMPONENTS

AND INCREASE THE RISK OF DEVELOPING A FUEL TANK IGNITION SOURCE.

WARNING: MONITOR THE CENTER AND MAIN TANK FUEL QUANTITIES AND MAKE SURE THE

AIRPLANE BALANCE IS MAINTAINED. REFER TO MD90 AMM 12-11-03 AS AN ACCEPTED

PROCEDURE.

WARNING: BEFORE EACH TEST MAKE SURE THE AFFECTED TANKS CONTAIN ENOUGH FUEL

FOR THE TRANSFER REQUIREMENTS.

1. GROUND FAULT INTERRUPTER (GFI) CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND

CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

a. Apply electrical power. Refer to MD90 AMM 24-40-00 as an accepted procedure.

b. Make sure the center tank has a minimum of 1000 pounds. of fuel. Refer to MD90 AMM 12-11-07

as an accepted procedure.

c. Open access panel 610TB. Refer to MD90 AMM 06-36-00.

d. Close circuit breakers as follow:

LOWER EPC, XFER BUS

Row Column Number Name

T 41 B1-994 CENTER FUEL LOW PRESSURE

UPPER EPC, FUEL

Row Column Number Name

J 17 B1-822 FUEL QUANTITY POWER TRANSFER

UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

H 19 B1-918 FWD RIGHT FUEL TANK BOOST PUMP

H 21 B1-922 FWD CENTER FUEL TANK BOOST PUMP

H 23 B1-921 AFT LEFT FUEL TANK BOOST PUMP

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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UPPER EPC, FUEL - R AC BUS

Row Column Number Name

J 21 B1-923 AFT CENTER FUEL TANK BOOST PUMP

J 23 B1-920 FWD LEFT FUEL TANK BOOST PUMP

UPPER EPC, GND SERV

Row Column Number Name

J 19 B1-919 AFT RIGHT FUEL TANK BOOST PUMP

UPPER EPC, LEFT AC BUS

Row Column Number Name

H 14 B1-955 FUEL QUANTITY POWER TRANSFER

e. Make sure the landing gear is safe for maintenance. Refer to MD90 AMM 32-00-00 as an accepted

procedure.

f. Do the Center Fuel Pressure Low Indication System Functional Test as follows:

(1) Position the FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00

as an accepted procedure.

(2) Position LEFT AFT PUMPS switch (5) to the OFF position.

(3) Position CTR AFT PUMPS switch (6) to the OFF position.

(4) Position RIGHT AFT PUMPS switch (7) to the OFF position.

(5) Position LEFT FWD PUMPS switch (8) to the OFF position.

(6) Position CTR FWD PUMPS switch (9) to the OFF position.

(7) Position RIGHT FWD PUMPS switch (10) to the OFF position. Verify as follows:

(a) Electronic Overhead Annunciator Panel (EOAP) (4) CENTER FUEL PRESS LO indication

is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(8) Position the CTR FWD PUMPS switch (9) to the ON position. After 12 to 32 seconds verify

as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is ON.

(b) MASTER CAUTION (13) indication is ON.

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(9) Position the CTR FWD PUMPS switch (9) to the OFF position. Verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(10) Position the CTR AFT PUMPS switch (6) to the ON position. After 12 to 32 seconds verify as

follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is ON.

(b) MASTER CAUTION (13) indication is ON.

(11) Position the CTR AFT PUMPS switch (6) to the OFF position. Verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

2. CENTER TANK GFI BUILT IN TEST (BIT)

a. Do a test of the center tank GFI BIT as follows:

(1) Make sure the center tank has a minimum of 1000 pounds of fuel. Refer to MD90 AMM

12-11-07 as an accepted procedure.

(2) Position FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00 as an

accepted procedure.

(3) Position LEFT AFT PUMPS switch (5) to the OFF position.

(4) Position CTR AFT PUMPS switch (6) to the OFF position.

(5) Position RIGHT AFT PUMPS switch (7) to the OFF position.

(6) Position LEFT FWD PUMPS switch (8) to the OFF position.

(7) Position CTR FWD PUMPS switch (9) to the OFF position.

(8) Position RIGHT FWD PUMPS switch (10) to the OFF position. Verify as follows:

(a) Electronic Overhead Annunciator Panel (EOAP) (4) CENTER FUEL PRESS LO indication

is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(9) Close circuit breakers as follows:

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

H 21 B1-922 FWD CENTER FUEL TANK BOOST PUMP

J 21 B1-923 AFT CENTER FUEL TANK BOOST PUMP

(10) Position the CTR FWD PUMPS switch (9) and the CTR AFT PUMPS switch (6) to the ON

position. After 12 to 32 seconds verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(11) Press the CENTER FWD PUMP GFI Relay (R2-1494) TEST (23) button. The CENTER FWD

PUMP is disabled, verify as follows:

(a) CENTER FWD PUMP GFI Relay (R2-1494) reset indicator (24) has popped up and the

white band on the indicator is visible.

(b) After 12 to 32 seconds:

1) The EOAP (4) CENTER FUEL PRESS LO indication is ON.

2) The MASTER CAUTION (13) indication is ON.

(12) Position the CTR AFT PUMPS switch (6) to the OFF position. Verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(13) Position the CTR FWD PUMPS switch (9) to the OFF position.

(14) Press the CENTER FWD PUMP GFI Relay (R2-1494) RESET (24) button. Verify as follows:

(a) CENTER FWD PUMP GFI Relay (R2-1494) RESET (24) button remains depressed and

the white band is no longer visible.

(b) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(c) MASTER CAUTION (13) indication is OFF.

(15) Position the CTR FWD PUMPS switch (9) to the ON position. After 12 to 32 seconds verify

as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is ON.

(b) MASTER CAUTION (13) indication is ON.

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(16) Position the CTR AFT PUMPS switch (6) to the ON position. Verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(17) Press the CENTER AFT PUMP GFI Relay (R2-1495) TEST (23) button. The CENTER AFT

PUMP is disabled, verify as follows:

(a) CENTER AFT PUMP GFI Relay (R2-1495) reset indicator (24) has popped up and the

white band on the indicator is visible.

(b) After 12 to 32 seconds:

1) The EOAP (4) CENTER FUEL PRESS LO indication is ON.

2) The MASTER CAUTION (13) indication is ON.

(18) Position the CTR FWD PUMPS switch (9) to the OFF position. Verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(19) Position the CTR AFT PUMPS switch (6) to the OFF position.

(20) Press the CENTER AFT PUMP GFI Relay (R2-1495) RESET (24) button. Verify as follows:

(a) CENTER AFT PUMP GFI Relay (R2-1495) RESET (24) button remains depressed and

the white band is no longer visible.

(b) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(c) MASTER CAUTION (13) indication is OFF.

(21) Position the CTR AFT PUMPS switch (6) to the ON position. After 12 to 32 seconds verify as

follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is ON.

(b) MASTER CAUTION (13) indication is ON.

(22) Position the CTR FWD PUMPS switch (9) to the ON position. Verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(23) Position the CTR FWD PUMPS switch (9) and CTR AFT PUMPS switch (6) to the OFF position.

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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3. ALTERNATE FUEL BURN SYSTEM TEST

a. Place aircraft in attitude of -0.75 to -1.25 degree pitch and -.25 to .25 degree roll. Refer to MD90

AMM 08-10-00 as an accepted procedure.

b. Make sure fuel tank levels are as follows:

Tank Quantity

Left Main 5500-5700 pounds

Right Main 5500-5700 pounds

Center 3400-3600 pounds

c. Position controls as follows:

(1) On the center console do what follows:

(a) Position the FUEL X FEED lever (3) to the OFF position.

(b) Position the FUEL switches (2) to the OFF position.

(2) On the overhead switch panel, do what follows:

(a) Position the START PUMP switch (11) to the OFF position.

(b) Position the FUEL TANKS PUMPS switches (5)(6)(7)(8)(9)(10) to the OFF position.

(c) Position the APU MASTER switch (12) to the OFF position.

(d) Position the FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00

as an accepted procedure.

d. Close circuit breaker as follows:

LOWER EPC, DC

Row Column Number Name

M 37 B1-1007 ALT FUEL BURN

e. Do a functional test of the alternate fuel burn test system as follows:

(1) On the Load Selector Display Unit (LSDU) (18), do what follows:

(a) Position the POWER switch (19) to the ON position.

(b) Position the AUTO/OVERRIDE switch (20) to the OVERRIDE position.

(2) Open defueling shutoff valve (22).

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(3) Open left main tank fill valve (14).

(4) Open right main tank fill valve (15).

(5) On the Overhead Fuel Panel, do what follows:

(a) Position CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO

position.

NOTE: This initiates the transfer of fuel from the center tank to the left and right main

tanks.

(b) On the EOAP (4), when either the L INLET FUEL PRESS LOW or the R INLET FUEL

PRESS LOW warning indication occurs, position the CTR AFT PUMPS switch (6) and

CTR FWD PUMPS switch (9) to the OFF position.

(c) Position CTR AFT PUMPS (6) and CTR FWD PUMPS (9) switches to the ON position.

(d) After 50 - 100 pounds of fuel has been removed from the center tank, position the CTR

AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the OFF position.

(e) At the right wing fuel control station, close the left main tank fill valve (14).

(f) At the center console fuel controls, position the crossfeed lever (3) to the ON position.

(g) Position the CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO

position.

(h) Open circuit breaker as follows:

UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

H 21 B1-922 FWD CENTER FUEL TANK BOOST PUMP

1) Verify that EOAP (4) CENTER FUEL PRESS LO warning indication does not appear.

(i) Position the LEFT AFT PUMPS switch (5) and LEFT FWD PUMPS switch (8) to the ON

position.

(j) On the EOAP (4), when the CENTER FUEL PRESS LO warning indication appears,

immediately place LEFT AFT PUMPS switch (5), CTR AFT PUMPS switch (6), LEFT

FWD PUMPS switch (8), and CTR FWD PUMPS switch (9) to the OFF position.

(k) Close circuit breaker as follows:

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

H 21 B1-922 FWD CENTER FUEL TANK BOOST PUMP

(l) Open circuit breaker as follows:

UPPER EPC, FUEL - R AC BUS

Row Column Number Name

J 21 B1-923 AFT CENTER FUEL TANK BOOST PUMP

(m) At the right wing fuel control station, close the right main tank fill valve (15).

(n) At the right wing fuel control station, open the left main tank fill valve (14).

(o) Position RIGHT AFT PUMPS switch (7) and RIGHT FWD PUMPS switch (10) to the ON

position.

(p) Position CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO

position.

(q) When EOAP (4) CENTER FUEL PRESS LOW warning indication reappears, immediately

place RIGHT AFT PUMPS switch (7), RIGHT FWD PUMPS switch (10), CTR AFT PUMPS

switch (6) and CTR FWD PUMPS switch (9) to the OFF position.

(r) Close circuit breaker as follows:

UPPER EPC, FUEL - R AC BUS

Row Column Number Name

J 21 B1-923 AFT CENTER FUEL TANK BOOST PUMP

(s) On the right wing, close defueling shutoff valve (22) and left main tank fill valve (14).

CAUTION: ENSURE CENTER TANK HAS SUFFICIENT FUEL TO TRANSFER TO MAIN TANKS. VERIFY

MAIN TANKS CAN ACCEPT TRANSFERRED FUEL QUANTITY TO AVOID FUEL SPILLAGE

VIA THE VENT SYSTEM.

4. Do CENTER FUEL TANK TRANSFER (AT REFUEL STATION). Refer to MD90 AMM 12-11-03 as an

accepted procedure.

5. Close access panel 610TB. Refer to MD90 AMM 06-36-00.

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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This Appendix applies only to: Group 2.

WARNING: DO NOT OPERATE A FUEL PUMP IN AN EMPTY FUEL TANK. PROLONGED DRY RUNNING

OF A FUEL PUMP IN AN EMPTY TANK CAN DEGRADE INTERNAL PUMP COMPONENTS

AND INCREASE THE RISK OF DEVELOPING A FUEL TANK IGNITION SOURCE.

WARNING: MONITOR THE CENTER AND MAIN TANK FUEL QUANTITIES AND MAKE SURE THE

AIRPLANE BALANCE IS MAINTAINED. REFER TO MD90 AMM 12-11-03 AS AN ACCEPTED

PROCEDURE.

WARNING: BEFORE EACH TEST MAKE SURE THE AFFECTED TANKS CONTAIN ENOUGH FUEL

FOR THE TRANSFER REQUIREMENTS.

1. GROUND FAULT INTERRUPTER (GFI) CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND

CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

a. Apply electrical power. Refer to MD90 AMM 24-40-00 as an accepted procedure.

b. Make sure the center tank has a minimum of 1000 pounds of fuel. Refer to MD90 AMM 12-11-07

as an accepted procedure.

c. Open access panel 610TB. Refer to MD90 AMM 06-36-00.

d. Close circuit breakers as follow:

UPPER EPC, FUEL

Row Column Number Name

J 17 B1-822 FUEL QUANTITY POWER TRANSFER

UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

H 19 B1-918 FWD RIGHT FUEL TANK BOOST PUMP

H 21 B1-922 FWD CENTER FUEL TANK BOOST PUMP

H 23 B1-921 AFT LEFT FUEL TANK BOOST PUMP

UPPER EPC, FUEL - R AC BUS

Row Column Number Name

J 21 B1-923 AFT CENTER FUEL TANK BOOST PUMP

J 23 B1-920 FWD LEFT FUEL TANK BOOST PUMP

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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UPPER EPC, GND SERV

Row Column Number Name

J 19 B1-919 AFT RIGHT FUEL TANK BOOST PUMP

UPPER EPC, LEFT AC BUS

Row Column Number Name

H 14 B1-955 FUEL QUANTITY POWER TRANSFER

e. Set the Electronic Instrument System (EIS) controls as follows:

(1) Turn the six BRT knobs (1) on the system control panel (3) to the middle position.

(2) Position the FUEL switchlight (2) on the system control panel (3) to the ON position.

(3) The FUEL synoptic page will come into view on the System Display (SD) (31).

f. Make the landing gear safe for maintenance. Refer to MD90 AMM 32-00-00 as an accepted

procedure.

g. Do the Center Fuel Pressure Low Indication System Functional Test as follows:

(1) Position the FLAP/SLAT handle (6) on the center console to the UP/RET position. Refer to

MD90 AMM 27-50-00 as an accepted procedure.

(2) Position the L AFT PUMP switchlight (13) on the FUEL panel to the OFF position.

(3) Position the C AFT PUMP switchlight (17) on the FUEL panel to the OFF position. After 1.5

to 2.5 minutes verify as follows:

(a) CTR AFT PUMP LO alert on the SD (31) is not illuminated.

(4) Position the R AFT PUMP switchlight (15) on the FUEL panel to the OFF position.

(5) Position the L FWD PUMP switchlight (12) on the FUEL panel to the OFF position.

(6) Position the C FWD PUMP switchlight (16) on the FUEL panel to the OFF position. After 1.5

to 2.5 minutes verify as follows:

(a) CTR FWD PUMP LO alert on the SD (31) is not illuminated.

(7) Position the R FWD PUMP switchlight (14) on the FUEL panel to the OFF position.

(8) Position the C FWD PUMP switch (16) to the ON position. Verify as follows:

(a) C FWD PUMP switchlight (16) illuminates.

(b) After 1.5 to 2.5 minutes verify as follows:

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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1) On the SD (31), the CTR FWD PUMP LO alert comes on.

2) On the Engine and Alert Display (EAD) (32) and SD (31), the CTR FUEL PRES LO

alert comes on.

(9) Position the C FWD PUMP switch (16) to the OFF position. Verify as follows:

(a) C FWD PUMP switchlight (16) is OFF.

(b) On the SD (31), the CTR FWD PUMP LO alert is off.

(c) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is OFF.

(10) Position the C AFT PUMP switchlight (17) to the ON position. Verify as follows:

(a) C AFT PUMP switchlight (17) illuminates.

(b) After 1.5 to 2.5 minutes verify as follows:

1) On the SD (31), the CTR AFT PUMP LO alert comes on.

2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert comes on.

(11) Position the C AFT PUMP switchlight (17) to the OFF position. Verify as follows:

(a) C AFT PUMP switchlight (17) is OFF.

(b) On the SD (31), the CTR AFT PUMP LO alert is off.

(c) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off.

2. CENTER TANK GFI BUILT IN TEST (BIT)

a. Do a test of the center tank GFI BIT as follows:

(1) Position the FLAP/SLAT handle (6) to the UP/RET position. Refer to MD90 AMM 27-50-00

as an accepted procedure.

(2) Make sure the center tank has a minimum of 1000 pounds of fuel. Refer to MD90 AMM

12-11-07 as an accepted procedure.

(3) Close circuit breakers as follow:

UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

H 21 B1-922 FWD CENTER FUEL TANK BOOST PUMP

J 21 B1-923 AFT CENTER FUEL TANK BOOST PUMP

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(4) Position the C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) to the ON

position. Verify as follows:

(a) C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) illuminate.

(b) After 1.5 to 2.5 minutes verify as follows:

1) On the SD (31), the CTR FWD PUMP LO and CTR AFT PUMP LO alerts are off.

2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off.

(5) Press the CENTER FWD PUMP GFI Relay (R2-1494) TEST button (33). The CENTER FWD

PUMP is disabled, verify as follows:

(a) CENTER FWD PUMP GFI Relay (R2-1494) reset indicator (34) has popped up and the

white band on the indicator is visible.

(b) After 1 to 15 seconds, verify the FUEL synoptic page on the SD (31) will show an amber

vaned circle and amber (P) as low pressure indication for the center forward pump.

(c) After 1.5 to 2.5 minutes verify as follows:

1) On the SD (31), the CTR FWD PUMP LO alert comes on.

2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert comes on.

(6) Position the C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) to the OFF

position. Verify as follows:

(a) On the SD (31), the CTR FWD PUMP LO alert is off.

(b) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off.

(7) Press the CENTER FWD PUMP GFI Relay (R2-1494) RESET button (34). Verify as follows:

(a) CENTER FWD PUMP GFI Relay (R2-1494) RESET button (34) remains depressed and

that the white band is no longer visible.

(8) Position the C FWD PUMP switchlight (16) to the ON position. The CENTER FWD PUMP is

enabled, verify as follows:

(a) After 1 to 15 seconds, the FUEL synoptic page on the SD (31) will show a green vaned

circle for the CENTER FWD PUMP.

(b) After 1.5 to 2.5 minutes verify as follows:

1) On the SD (31), the CTR FWD PUMP LO alert comes on.

2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert comes on.

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

(SHEET 4 OF 14)

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(9) Position the C AFT PUMP switchlight (17) to the ON position. Verify as follows:

(a) On the SD (31), the CTR FWD PUMP LO alert is off.

(b) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off.

(10) Press the CENTER AFT PUMP GFI Relay (R2-1495) TEST button (33). The CENTER AFT

PUMP is disabled, verify as follows:

(a) CENTER AFT PUMP GFI Relay (R2-1495) reset indicator (34) has popped up and the

white band on the indicator is visible.

(b) After 1 to 15 seconds, the FUEL synoptic page on the SD (31) will show an amber vaned

circle and amber (P) as low pressure indication for the center aft pump.

(c) After 1.5 to 2.5 minutes verify as follows:

1) On the SD (31), the CTR AFT PUMP LO alert comes on.

2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert comes on.

(11) Position the C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) to the OFF

position. Verify as follows:

(a) On the SD (31), the CTR AFT PUMP LO alert is off.

(b) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off.

(12) Press the CENTER AFT PUMP GFI Relay (R2-1495) RESET button (34). Verify as follows:

(a) CENTER AFT PUMP GFI Relay (R2-1495) RESET button (34) remains depressed and

that the white band is no longer visible.

(13) Position the C AFT PUMP switchlight (17) to the ON position. The CENTER AFT PUMP is

enabled, verify as follows:

(a) After 1 to 15 seconds, the FUEL synoptic page on the SD (31) will show a green vaned

circle for the CENTER AFT PUMP.

(b) After 1.5 to 2.5 minutes verify as follows:

1) On the SD (31), the CTR AFT PUMP LO alert comes on.

2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert comes on.

(14) Position the C FWD PUMP switchlight (16) to the ON position. Verify as follows:

(a) On the SD (31), the CTR AFT PUMP LO alert is off.

(b) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off.

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(15) Position the C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) to the OFF

position.

3. ALTERNATE FUEL BURN SYSTEM TEST

a. Place aircraft in attitude of -0.75 to -1.25 degree pitch and -.25 to .25 degree roll. Refer to MD90

AMM 08-10-00 as an accepted procedure.

b. Make sure fuel tank levels are as follows:

Tank Quantity

Left Main 6100-6300 pounds

Right Main 6100-6300 pounds

Center 3300-3500 pounds

c. Set the Electronic Instrument System (EIS) controls as follows:

(1) Turn the six BRT knobs (1) on the system control panel (3) to the middle position.

(2) Position the FUEL switchlight (2) on the system control panel (3) to the ON position.

(3) The FUEL synoptic page will come into view on the SD (31).

(4) Position controls as follows:

(a) Position the FUEL X FEED lever (4) on the center console to the OFF position.

(b) Position the FUEL shutoff switches (5) on the center console to the OFF position.

(c) Position the START PUMP switchlight (11) on the FUEL panel to the OFF position.

(d) Position the L FWD PUMP switchlight (12) and L AFT PUMP switchlight (13) to the OFF

position.

(e) Position the R FWD PUMP switchlight (14) and R AFT PUMP switchlight (15) to the OFF

position.

(f) Position the C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) to the OFF

position.

(g) Position the APU MASTER switchlight (9) on the overhead panel to the OFF position.

(h) Position the FLAP/SLAT handle (6) to the UP/RET position.

(i) Push the MENU switch (7) on the Multifunction Control Display Unit (MCDU) (8).

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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WARNING: MAKE SURE THE APPLICABLE CIRCUIT BREAKERS ARE OPEN, TAGGED,

AND SAFETIED BEFORE YOU TURN THE FIRE CONTROL HANDLES. YOU

CAN ACCIDENTALLY OPERATE THE FIREX AGENT CONTAINERS AND

CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.

(j) Pull the LEFT and RIGHT ENG FIRE shutoff handles (21) out.

d. Close circuit breaker as follows:

LOWER EPC, DC

Row Column Number Name

M 37 B1-1007 ALT FUEL BURN

e. Do a functional test of the alternate fuel burn test system as follows:

(1) Position the POWER switch (28) on the Load Selector Display Unit (LSDU) (26) to the ON

position.

(2) Position the AUTO/OVERRIDE switch (28) on the LSDU (26) to the OVERRIDE position.

(3) Position the defueling shutoff valve (25) at the right wing refueling station to the OPEN position.

(4) Position the LEFT MAIN TANK fill valve switch (29) on the right wing refueling panel to the

AUTO FILL position.

(5) Position the RIGHT MAIN TANK fill valve switch (30) on the right wing refueling panel to the

AUTO FILL position.

(6) Position the ALTN FUEL BURN switchlight (22) on the FUEL panel to the ON position. Verify

as follows:

(a) Fuel begins to transfer from the center fuel tank to the left and right main fuel tanks.

(b) The FUEL synoptic page on the SD (31) shows a green circle with green vanes for the

FWD and AFT boost pumps in the center fuel tank.

(7) When the FWD and AFT boost pumps in the center fuel tank turn to white circles with the

letter A inside, and fuel stops transferring from the center tank, place the ALTN FUEL BURN

switchlight (22) in the OFF position.

(a) FWD and AFT boost pumps in the center fuel tank turn to white circles without the letter

A inside.

(8) Position the LEFT MAIN TANK fill valve switch (29) to the CLOSED position. Verify as follows:

(a) Left Main Tank fill valve (23) override handle at the right wing refueling station moves to

the closed position.

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(9) Position the FUEL X FEED lever on the center console to the ON position. Verify as follows:

(a) The FUEL synoptic page on SD (31) shows a green circle with two horizontal parallel

lines for the fuel crossfeed valve.

(10) Position the ALTN FUEL BURN switchlight (22) to the ON position. Verify as follows:

(a) ALTN FUEL BURN switchlight (22) ON indiction is illuminated.

(b) The FUEL synoptic page on the SD (31) shows white circles with letter A inside for the

FWD and AFT center tank pumps.

(11) Position the L FWD PUMP switchlight (12) and L AFT PUMP switchlight (13) to the ON position.

Verify as follows:

(a) L FWD PUMP switchlight (12) and L AFT PUMP switchlight (13) are not illuminated.

(12) When the FUEL synoptic page on the SD (31) shows green circles with green vanes for the

FWD and AFT center tank pumps, position the ALTN FUEL BURN switchlight (22), L FWD

PUMP switchlight (12) and L AFT PUMP switchlight (13) to the OFF position. Verify as follows:

(a) The ALTN FUEL BURN switchlight (22) is not illuminated.

(b) L FWD PUMP switchlight (12) and L AFT PUMP switchlight (13) OFF indication is

illuminated.

(13) Position the RIGHT MAIN TANK fill valve switch (30) to the CLOSED position and the LEFT

MAIN TANK fill valve switch (29) to the AUTOFILL position. Verify as follows:

(a) Right Main Tank fill valve (24) override handle moves to the CLOSED position.

(b) Left Main Tank fill valve (23) override handle moves to the OPEN position.

(14) Position the FUEL X FEED lever (4) to the OFF position. Verify as follows:

(a) The FUEL synoptic page on SD (31) a shows a white circle with two parallel vertical lines

for the fuel crossfeed valve.

(15) Position the ALTN FUEL BURN switchlight (22) to the ON position. Verify as follows:

(a) ALTN FUEL BURN switchlight (22) ON indication is illuminated.

(b) The FUEL synoptic page on SD (31) shows green circles with green vanes for the FWD

and AFT center tank pumps.

(16) When the FWD and AFT center tank pumps turn to white circles with the letter A inside, place

the R FWD PUMP switchlight (14) and R AFT PUMP switchlight (15) in the ON position. Verify

as follows:

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(a) The FUEL synoptic page on the SD (31) shows white circles with letter A inside for the

FWD and AFT center tank pumps.

(b) R FWD PUMP switchlight (14) and R AFT PUMP switchlight (15) are not illuminated.

(17) When the FUEL synoptic page on SD (31) shows green circles with green vanes for the FWD

and AFT center tank pumps, position the ALTN FUEL BURN switchlight (22), R FWD PUMP

switchlight (14) and R AFT PUMP switchlight (15) to the OFF position. Verify as follows:

(a) ALTN FUEL BURN switchlight is not illuminated.

(b) R FWD PUMP switchlight (14) and R AFT PUMP switchlight (15) have OFF indication

illuminated.

(18) Position the defueling shutoff valve (25) to the CLOSED position.

(19) Position the LEFT MAIN TANK fill valve switch (29) to the CLOSED position.

(20) Push the LEFT and RIGHT ENG FIRE shutoff handles (21) in.

CAUTION: ENSURE CENTER TANK HAS SUFFICIENT FUEL TO TRANSFER TO MAIN TANKS. VERIFY

MAIN TANKS CAN ACCEPT TRANSFERRED FUEL QUANTITY TO AVOID FUEL SPILLAGE

VIA THE VENT SYSTEM.

4. Do CENTER FUEL TANK TRANSFER (AT REFUEL STATION). Refer to MD90 AMM 12-11-03 as an

accepted procedure.

5. Close access panel 610TB. Refer to MD90 AMM 06-36-00.

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS

LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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This Appendix applies only to: Group 3.

WARNING: DO NOT OPERATE A FUEL PUMP IN AN EMPTY FUEL TANK. PROLONGED DRY RUNNING

OF A FUEL PUMP IN AN EMPTY TANK CAN DEGRADE INTERNAL PUMP COMPONENTS

AND INCREASE THE RISK OF DEVELOPING A FUEL TANK IGNITION SOURCE.

WARNING: MONITOR THE CENTER AND MAIN TANK FUEL QUANTITIES AND MAKE SURE THE

AIRPLANE BALANCE IS MAINTAINED. REFER TO MD90 AMM 12-11-03 AS AN ACCEPTED

PROCEDURE.

WARNING: BEFORE EACH TEST MAKE SURE THE AFFECTED TANKS CONTAIN ENOUGH FUEL

FOR THE TRANSFER REQUIREMENTS.

1. GROUND FAULT INTERRUPTER (GFI) CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND

CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION TEST PROCEDURES

a. Apply electrical power. Refer to MD90 AMM 24-40-00 as an accepted procedure.

b. Make sure the center tank has a minimum of 1000 pounds of fuel. Refer to MD90 AMM 12-11-07

as an accepted procedure.

c. Open access panel 610TB. Refer to MD90 AMM 06-36-00.

d. Close circuit breakers as follow:

LOWER EPC, XFER BUS

Row Column Number Name

T 41 B1-994 CENTER FUEL LOW PRESSURE

UPPER EPC, FUEL

Row Column Number Name

J 17 B1-822 FUEL QUANTITY POWER TRANSFER

UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

H 19 B1-918 FWD RIGHT FUEL TANK BOOST PUMP

H 21 B1-922 FWD CENTER FUEL TANK BOOST PUMP

H 23 B1-921 AFT LEFT FUEL TANK BOOST PUMP

UPPER EPC, FUEL - R AC BUS

Row Column Number Name

J 21 B1-923 AFT CENTER FUEL TANK BOOST PUMP

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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UPPER EPC, FUEL - R AC BUS

Row Column Number Name

J 23 B1-920 FWD LEFT FUEL TANK BOOST PUMP

UPPER EPC, GND SERV

Row Column Number Name

J 19 B1-919 AFT RIGHT FUEL TANK BOOST PUMP

UPPER EPC, LEFT AC BUS

Row Column Number Name

H 14 B1-955 FUEL QUANTITY POWER TRANSFER

e. Make sure the landing gear is safe for maintenance. Refer to MD90 AMM 32-00-00 as an accepted

procedure.

f. Do the Center Fuel Pressure Low Indication System Functional Test as follows:

(1) Position FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00 as an

accepted procedure.

(2) Position LEFT AFT PUMPS switch (5) to the OFF position.

(3) Position CTR AFT PUMPS switch (6) to the OFF position.

(4) Position RIGHT AFT PUMPS switch (7) to the OFF position.

(5) Position LEFT FWD PUMPS switch (8) to the OFF position.

(6) Position CTR FWD PUMPS switch (9) ton the OFF position.

(7) Position RIGHT FWD PUMPS switch (10) to the OFF position. Verify as follows:

(a) Electronic Overhead Annunciator Panel (EOAP) (4) CENTER FUEL PRESS LO indication

is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(8) Position the CTR FWD PUMPS switch (9) to the ON position. After 12 to 32 seconds verify

as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is ON.

(b) MASTER CAUTION (13) indication is ON.

(9) Position the CTR FWD PUMPS switch (9) to the OFF position. Verify as follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(10) Position the CTR AFT PUMPS switch (6) to the ON position. After 12 to 32 seconds verify as

follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is ON.

(b) MASTER CAUTION (13) indication is ON.

(11) Position the CTR AFT PUMPS switch (6) to the OFF position. Verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

2. CENTER TANK GFI BUILT IN TEST (BIT)

a. Do a test of the center tank GFI BIT as follows:

(1) Make sure the center tank has a minimum of 1000 pounds of fuel in center tank.

(2) Position FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00 as an

accepted procedure.

(3) Position LEFT AFT PUMPS switch (5) to the OFF position.

(4) Position CTR AFT PUMPS switch (6) to the OFF position.

(5) Position RIGHT AFT PUMPS switch (7) to the OFF position.

(6) Position LEFT FWD PUMPS switch (8) to the OFF position.

(7) Position CTR FWD PUMPS switch (9) ton the OFF position.

(8) Position RIGHT FWD PUMPS switch (10) to the OFF position. Verify as follows:

(a) Electronic Overhead Annunciator Panel (EOAP) (4) CENTER FUEL PRESS LO indication

is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(9) Close circuit breakers as follows:

UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

H 21 B1-922 FWD CENTER FUEL TANK BOOST PUMP

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

J 21 B1-923 AFT CENTER FUEL TANK BOOST PUMP

(10) Position the CTR FWD PUMPS switch (9) and CTR AFT PUMPS switch (6) to the ON position.

After 12 to 32 seconds verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(11) Press the CENTER FWD PUMP GFI Relay (R2-1494) TEST (23) button. The CENTER FWD

PUMP is disabled, verify as follows:

(a) CENTER FWD PUMP GFI Relay (R2-1494) reset indicator (24) has popped up and the

white band on the indicator is visible.

(b) After 12 to 32 seconds:

1) The EOAP (4) CENTER FUEL PRESS LO indication is ON.

2) The MASTER CAUTION (13) indication is ON.

(12) Position the CTR AFT PUMPS switch (6) to the OFF position. Verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(13) Position the CTR FWD PUMPS switch (9) to the OFF position.

(14) Press the CENTER FWD PUMP GFI Relay (R2-1494) RESET (24) button. Verify as follows:

(a) CENTER FWD PUMP GFI Relay (R2-1494) RESET (24) button remains depressed and

the white band is no longer visible.

(b) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(c) MASTER CAUTION (13) indication is OFF.

(15) Position the CTR FWD PUMPS switch (9) to the ON position. After 12 to 32 seconds verify

as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is ON.

(b) MASTER CAUTION (13) indication is ON.

(16) Position the CTR AFT PUMPS switch (6) to the ON position. Verify as follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(17) Press the CENTER AFT PUMP GFI Relay (R2-1495) TEST (23) button. The CENTER AFT

PUMP is disabled, verify as follows:

(a) CENTER AFT PUMP GFI Relay (R2-1495) reset indicator (24) has popped up and the

white band on the indicator is visible.

(b) After 12 to 32 seconds:

1) The EOAP (4) CENTER FUEL PRESS LO indication is ON.

2) The MASTER CAUTION (13) indication is ON.

(18) Position the CTR FWD PUMPS switch (9) to the OFF position. Verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(19) Position the CTR AFT PUMPS switch (6) to the OFF position.

(20) Press the CENTER AFT PUMP GFI Relay (R2-1495) RESET (24) button. Verify as follows:

(a) CENTER AFT PUMP GFI Relay (R2-1495) RESET (24) button remains depressed and

the white band is no longer visible.

(b) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(c) MASTER CAUTION (13) indication is OFF.

(21) Position the CTR AFT PUMPS switch (6) to the ON position. After 12 to 32 seconds verify as

follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is ON.

(b) MASTER CAUTION (13) indication is ON.

(22) Position the CTR FWD PUMPS switch (9) to the ON position. Verify as follows:

(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF.

(b) MASTER CAUTION (13) indication is OFF.

(23) Position the CTR FWD PUMPS switch (9) and CTR AFT PUMPS switch (6) to the OFF position.

3. ALTERNATE FUEL BURN SYSTEM TEST

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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a. Place aircraft in attitude of -0.75 to -1.25 degree pitch and -.25 to .25 degree roll. Refer to MD90

AMM 08-10-00 as an accepted procedure.

b. Make sure fuel tank levels are as follows:

Tank Quantity

Left Main 5500-5700 pounds

Right Main 5500-5700 pounds

Center 3400-3600 pounds

c. Position controls as follows:

(1) On the center console do what follows:

(a) Position the FUEL X FEED lever (3) to the OFF position.

(b) Position the FUEL switches (2) to the OFF position.

(2) On the overhead switch panel, do what follows:

(a) Position the START PUMP switch (11) to the OFF position.

(b) Position the FUEL TANKS PUMPS switches (5)(6)(7)(8)(9)(10) to the OFF position.

(c) Position the APU MASTER switch (12) to the OFF position.

(d) Position the FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00

as an acceptable procedure.

d. Close circuit breaker as follows:

LOWER EPC, DC

Row Column Number Name

M 37 B1-1007 ALT FUEL BURN

e. Do a functional test of the alternate fuel burn test system as follows:

(1) On the Load Selector Display Unit (LSDU) (18), do what follows:

(a) Position the POWER switch (19) to the ON position.

(b) Position the AUTO/OVERRIDE switch (20) to the OVERRIDE position.

(2) Open defueling shutoff valve (22).

(3) Open left main tank fill valve (14).

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

(SHEET 6 OF 21)

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(4) Open right main tank fill valve (15).

(5) On the Overhead Fuel Panel, do what follows:

(a) Position CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO

position.

NOTE: This initiates the transfer of fuel from the center tank to the left and right main

tanks.

(b) On the EOAP (4), when either the L INLET FUEL PRESS LOW or the R INLET FUEL

PRESS LOW warning indication occurs, position the CTR AFT PUMPS switch (6) and

CTR FWD PUMPS switch (9) to the OFF position.

(c) Position CTR AFT PUMPS switch (6) and CTR FWD PUMPS (9) switches to the ON

position.

(d) After 50 - 100 pounds of fuel has been removed from the center tank, position the CTR

AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the OFF position.

(e) At the right wing fuel control station, close the left main tank fill valve (14).

(f) At the center console fuel controls, position the crossfeed lever (3) to the ON position.

(g) Position the CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO

position.

(h) Open circuit breaker as follows:

UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

H 21 B1-922 FWD CENTER FUEL TANK BOOST PUMP

1) Verify that EOAP (4) CENTER FUEL PRESS LO warning indication does not appear.

(i) Position the LEFT AFT PUMPS switch (5) and LEFT FWD PUMPS switch (8) to the ON

position.

(j) On the EOAP (4), when the CENTER FUEL PRESS LO warning indication appears,

immediately place LEFT AFT PUMPS switch (5), CTR AFT PUMPS switch (6), LEFT

FWD PUMPS switch (8), and CTR FWD PUMPS switch (9) to the OFF position.

(k) Close circuit breaker as follows:

UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

H 21 B1-922 FWD CENTER FUEL TANK BOOST PUMP

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(l) Open circuit breaker as follows:

UPPER EPC, FUEL - R AC BUS

Row Column Number Name

J 21 B1-923 AFT CENTER FUEL TANK BOOST PUMP

(m) At the right wing fuel control station, close the right main tank fill valve (15).

(n) At the right wing fuel control station, open the left main tank fill valve (14).

(o) Position RIGHT AFT PUMPS switch (7) and RIGHT FWD PUMPS switch (10) to the ON

position.

(p) Position CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO

position.

(q) When EOAP (4) CENTER FUEL PRESS LOW warning indication reappears, immediately

place RIGHT AFT PUMPS switch (7), RIGHT FWD PUMPS switch (10), CTR AFT PUMPS

switch (6) and CTR FWD PUMPS switch (9) to the OFF position.

(r) Close circuit breaker as follows:

UPPER EPC, FUEL - R AC BUS

Row Column Number Name

J 21 B1-923 AFT CENTER FUEL TANK BOOST PUMP

(s) On the right wing, close defueling shutoff valve (22) and left main tank fill valve (14).

CAUTION: ENSURE CENTER TANK HAS SUFFICIENT FUEL TO TRANSFER TO MAIN TANKS. VERIFY

MAIN TANKS CAN ACCEPT TRANSFERRED FUEL QUANTITY TO AVOID FUEL SPILLAGE

VIA THE VENT SYSTEM.

4. Do CENTER FUEL TANK TRANSFER (AT REFUEL STATION). Refer to MD90 AMM 12-11-03 as an

accepted procedure.

5. FUNCTIONAL TEST OF THE FORWARD AUXILIARY TANK FEED SYSTEM

a. Make sure the center fuel tank is refueled between 18,500 and 19,000 pounds. Refer to MD90

AMM 12-11-07 as an accepted procedure.

CAUTION: TO PREVENT FUEL SPILLAGE, ENSURE LEFT AND RIGHT MAIN FUEL TANKS WILL

ACCOMMODATE THE FUEL TO BE TRANSFERRED TO THEM.

b. Place aircraft in attitude of -0.75 to -1.25 degree pitch and -.25 to .25 degree roll. Refer to MD90

AMM 08-10-00 as an accepted procedure.

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

(SHEET 8 OF 21)

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NOTE: The landing gear struts can be deflated to establish the necessary attitude and roll. Refer

to MD90 AMM 32-11-01 as an accepted procedure.

c. Close circuit breakers as follow:

UPPER EPC, BATT DIR BUS

Row Column Number Name

B 16 B1-106 GROUND REFUELING

UPPER EPC, ENGINE - LEFT DC BUS

Row Column Number Name

S 36 B1-903 AUX FUEL XFER CONTROL A

UPPER EPC, ENGINE - RIGHT DC BUS

Row Column Number Name

T 36 B1-904 AUX FUEL XFER CONTROL B

UPPER EPC, FUEL

Row Column Number Name

J 17 B1-822 FUEL QUANTITY POWER TRANSFER

UPPER EPC, FUEL - LEFT AC BUS

Row Column Number Name

H 19 B1-918 FWD RIGHT FUEL TANK BOOST PUMP

H 21 B1-922 FWD CENTER FUEL TANK BOOST PUMP

H 23 B1-921 AFT LEFT FUEL TANK BOOST PUMP

H 25 B1-907 FWD AUX TANK FUEL XFER PUMP A

UPPER EPC, FUEL - R AC BUS

Row Column Number Name

J 21 B1-923 AFT CENTER FUEL TANK BOOST PUMP

J 23 B1-920 FWD LEFT FUEL TANK BOOST PUMP

J 25 B1-908 FWD AUX TANK FUEL XFER PUMP B

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

(SHEET 9 OF 21)

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UPPER EPC, GND SERV

Row Column Number Name

J 19 B1-919 AFT RIGHT FUEL TANK BOOST PUMP

WARNING: DO NOT OPERATE A FUEL PUMP IN AN EMPTY FUEL TANK. PROLONGED DRY

RUNNING OF A FUEL PUMP IN AN EMPTY TANK CAN DEGRADE INTERNAL PUMP

COMPONENTS AND INCREASE THE RISK OF DEVELOPING A FUEL TANK IGNITION

SOURCE.

d. Do Forward Auxiliary Tank Feed System Test as follows:

(1) You must continuously monitor pump operation to make sure that the pump does not run dry.

(2) If it is necessary to operate a pump that is not continuously monitored, make sure that there

is sufficient fuel in the related tank that the pump will not run dry.

(3) The pump must be turned off when you get to the necessary fuel level, or before, if the related

low pressure indication comes on.

(4) On the overhead switch panel, do what follows:

(a) Position the FWD AUX TRANS A switch (25) to the TEST position. Verify as follows:

1) On the Electronic Overhead Annunciator panel (EOAP) (4), the FWD AUX FUEL

PRESS LO message comes on momentarily and then goes out.

(b) Position the FWD AUX TRANS A switch (25) to the OFF position.

(c) Position the FWD AUX TRANS B switch (26) to the TEST position. Verify as follows:

1) On the EOAP (4), FWD AUX FUEL PRESS LO message comes on momentarily

and then goes out.

(d) Position the FWD AUX TRANS B switch (26) to the OFF position.

(e) Position the FWD AUX TRANS A switch (25) and FWD AUX TRANS B switch (26) to the

AUTO position. Verify as follows:

1) FWD AUX FUEL PRESS LO message is not displayed on the EOAP (4).

2) FWD tank on the COCKPIT DISPLAY UNIT (CDU) (27) does not decrease in fuel

level.

(f) Position the FWD CTR PUMP switch (9) and AFT CTR PUMP switch (6) to the ON

position.

(5) On the refuel control panel, do what follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

(SHEET 10 OF 21)

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(a) Open the defueling shutoff valve (22).

(b) Position the POWER switch (19) to the ON position.

(c) Position the LEFT MAIN TANK fill valve switch (28) and RIGHT MAIN TANK fill valve

switch (29) to the AUTOFILL position.

(d) Position the AUTO OVERRIDE switch (20) to the OVERRIDE position.

(6) On the main instrument panel, do what follows:

(a) On the CDU (27), verify that fuel in the CTR tank decreases.

(b) Monitor the fuel quantity in the CTR tank until the fuel level decreases to 16,600 to 18,400

pounds.

(c) When the fuel quantity reaches 16,600 to 18,400 pounds, verify that FWD AUX FUEL

PRES LO message comes on momentarily on the EOAP (4).

(d) When the forward auxiliary tank starts to transfer fuel, make a note of the fuel quantity in

the center tank.

(e) Monitor the CDU (27) and verify that the fuel quantity in the FWD tank decreases.

(7) On the overhead switch panel, position the FWD CTR PUMP switch (9) and AFT CTR PUMP

switch (6) to the OFF position.

(8) On the refuel control panel, do what follows:

(a) Close the defueling shutoff valve (22).

(b) Position the LEFT MAIN TANK fill valve switch (28) and RIGHT MAIN TANK fill valve

switch (29) to the CLOSED position.

(9) On the CDU (27), verify that fuel quantity in the CTR tank increases and the fuel quantity in

the FWD tank decreases.

(10) On the overhead switch panel, do what follows:

(a) Position the FWD AUX TRANS A switch (25) in the OFF position. Verify as follows:

1) The fuel quantity in the CTR tank on the CDU (27) continues to increase.

2) The fuel quantity in the FWD tank on the CDU (27) continues to decrease.

NOTE: Do not place both AUX TRANS switches in the OFF position at the same

time. At least one pump must remain ON to keep the pump holding relays

closed.

(b) Position the FWD AUX TRANS A switch (25) to the AUTO position. Verify as follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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1) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off.

(c) Position FWD AUX TRANS B switch (26) to the off position. Verify as follows:

1) The fuel quantity in the CTR tank on the CDU (27) continues to increase.

2) The fuel quantity in the FWD tank on the CDU (27) continues to decrease.

(d) Position the FWD AUX TRANS B switch (26) to the AUTO position. Verify as follows:

1) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off.

(e) Open circuit breakers as follow:

LOWER EPC, FUEL LEFT AC BUS

Row Column Number Name

H 25 B1-907 AUX FUEL XFER CONTROL A

LOWER EPC, FUEL - R AC BUS

Row Column Number Name

J 25 B1-908 AUX FUEL XFER CONTROL B

1) Verify the FWD AUX FUEL PRESS LO message on the EOAP (4) comes on.

6. FORWARD AUX TANK GROUND FAULT INTERRUPTER (GFI) BUILT IN TEST (BIT) AND

ALTERNATE ENABLE TEST

WARNING: BE SURE THE CENTER FUEL TANK QUANTITY IS BELOW 17,500 POUNDS DURING

THE TEST THAT FOLLOWS, THE CENTER FUEL TANK SHOULD REMAIN BELOW

17,500 POUNDS. REFER TO MD90 AMM 12-11-07 AS AN ACCEPTED PROCEDURE.

a. Open circuit breakers as follow:

LOWER EPC, FUEL LEFT AC BUS

Row Column Number Name

H 25 B1-907 AUX FUEL XFER CONTROL A

LOWER EPC, FUEL - R AC BUS

Row Column Number Name

J 25 B1-908 AUX FUEL XFER CONTROL B

b. On the overhead switch panel, do what follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(1) Position the FWD AUX TRANS A switch (25) and FWD AUX TRANS B switches (26) to the

AUTO position. Verify as follows:

(a) FWD AUX FUEL PRESS LO message on the EOAP (4) comes on and remains on.

(2) Position the FWD AUX TRANS A switch (25) and FWD AUX TRANS B switch (26) to the OFF

position. Verify as follows:

(a) FWD AUX FUEL PRESS LO message on the EOAP (4) goes off.

c. Close circuit breaker as follows:

LOWER EPC, FUEL LEFT AC BUS

Row Column Number Name

H 25 B1-907 AUX FUEL XFER CONTROL A

d. On the overhead switch panel, position the FWD AUX TRANS A switch (25) to the AUTO position.

Verify as follows:

(1) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off.

e. Press the FWD AUX TRANS A GFI Relay (R2-1496) TEST (23) button. Verify what follows:

(1) FWD AUX TRANS A GFI Relay (R2-1496) reset indicator (24) has popped up and that the

white band on the indicator is visible.

(2) FWD AUX FUEL PRESS LO message on the EOAP (4) comes on and remains on.

(3) On the CDU (27), the transfer of fuel from the FWD tank to the CTR tank ceases.

f. On the overhead switch panel, position the FWD AUX TRANS A switch (25) to the OFF position.

Verify as follows:

(1) FWD AUX FUEL PRESS LO message on the EOAP (4) goes off.

g. Press the FWD AUX TRANS A GFI Relay (R2-1496) RESET (24) button. Verify as follows:

(1) FWD AUX TRANS A GFI Relay (R2-1496) RESET (24) button remains depressed and the

white band is no longer visible.

(2) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off.

h. On the overhead switch panel, do as follows:

(1) Position the FWD AUX TRANS A switch (25) to the TEST position. Verify as follows:

(a) On the EOAP (4), the FWD AUX FUEL PRESS LO message comes on momentarily and

then goes out.

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(2) Place the FWD AUX TRANS A switch (25) to OFF position. Verify as follows:

(a) On the EOAP (4), verify the FWD AUX FUEL PRESS LO message remains off.

i. On the overhead switch panel, place the FWD AUX TRANS A switch (25) and FWD AUX TRANS

B switch (26) to the AUTO position.

j. Open circuit breaker as follows:

LOWER EPC, FUEL LEFT AC BUS

Row Column Number Name

H 25 B1-907 AUX FUEL XFER CONTROL A

(1) Verify FWD AUX FUEL PRESS LO message on the EOAP (4) comes on and remains on.

k. On the overhead switch panel, position the FWD AUX TRANS A switch (25) and FWD AUX TRANS

B switch (26) to the OFF position. Verify as follows:

(1) FWD AUX FUEL PRESS LO message on the EOAP (4) goes off.

l. Close circuit breaker as follows:

LOWER EPC, FUEL LEFT AC BUS

Row Column Number Name

J 25 B1-908 AUX FUEL XFER CONTROL B

m. On the overhead switch panel, position the FWD AUX TRANS B switch (26) to the AUTO position.

Verify as follows:

(1) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off.

n. Press the FWD AUX TRANS B GFI Relay (R2-1497) TEST (23) button. Verify as follows:

(1) FWD AUX TRANS B GFI Relay (R2-1497) reset indicator (24) has popped up and the white

band on the indicator is visible.

(2) FWD AUX FUEL PRESS LO message on the EOAP (4) comes on and remains on.

(3) On the CDU (27), the transfer of fuel from the FWD tank to the CTR tank ceases.

o. On the overhead switch panel, position the FWD AUX TRANS B switch (26) to the OFF position.

Verify as follows:

(1) FWD AUX FUEL PRESS LO message on the EOAP (4) goes off.

p. Press the FWD AUX TRANS B GFI Relay (R2-1497) RESET (24) button. Verify as follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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(1) FWD AUX TRANS B GFI Relay (R2-1497) RESET (24) button remains depressed and the

white band is no longer visible.

(2) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off.

q. On the overhead switch panel, do as follows:

(1) Position the FWD AUX TRANS B switch (26) to the TEST position. Verify as follows:

(a) On the EOAP (4), the FWD AUX FUEL PRESS LO message comes on momentarily and

then goes out.

(2) Position the FWD AUX TRANS B switch (26) to the OFF position. Verify as follows:

(a) On the EOAP (4), verify the FWD AUX FUEL PRESS LO message remains off.

7. Close access panel 610TB. Refer to MD90 AMM 06-36-00.

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK

PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES

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APPENDIX D: BOEING PART DEMAND INTENT

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