Commercial 

Airplanes MD11

Service Bulletin

Number: MD11-28-137

Original Issue: June 24, 2014

ATA System: 2800

SUBJECT: FUEL - Fuel - Change Fuel Pump Control and Indication 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

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ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2014 Boeing.

Unpublished Work. All Rights Reserved.

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Boeing Company.

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BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 20

4. Process Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 29

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 29

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

APPENDIX B: INPUT SURVEY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69

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BLANK PAGE
Commercial 

Airplanes MD11

Service Bulletin

Summary Number: MD11-28-137

Original Issue: June 24, 2014

ATA System: 2800

SUBJECT: FUEL - Fuel - Change Fuel Pump Control and Indication System Wiring

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

Frictional heating or sparking resulting from fuel pump failure, wear of fuel pump rotating components, or ingestion

of debris by the fuel pump may result in development of a fuel tank ignition source. Frictional heating or sparking

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. Center wing auxiliary, tail, and fuselage

auxiliary fuel tanks may be subject to this condition since they are normally pumped dry over the course of a

mission. A fuel tank ignition event could develop with a fuel pump running in an empty tank if the normal shutoff

command is delayed or as a result of control system failures that keep the fuel pump in a latent uncommanded

running condition. To ensure a timely fuel pump shutoff command revise flight crew shutoff procedures for center

wing auxiliary, tail, and fuselage auxiliary fuel pumps. To address the latent fuel pump uncommanded running

condition change center wing auxiliary, tail, and fuselage auxiliary fuel pump control and indication system wiring

to detect and indicate fuel pump uncommanded running conditions. If not corrected, a fuel pump running in an

empty fuel tank may result in a fuel tank ignition event.

This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation

Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.

Boeing Fleet Team Digest (FTD) MD-11 FTD 28-03006 and MD-11 FTD 28-13001 are related to this service

bulletin.

ACTION

This service bulletin changes fuel pump control and indication system wiring to detect and indicate fuel pump

uncommanded running conditions.

EFFECTIVITY

MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-08-23 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 2013-08-23.

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INDUSTRY SUPPORT INFORMATION

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

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

Operators are encouraged to complete the survey provided in APPENDIX B of this service bulletin to help Boeing

predict the quantity and timing of the Boeing Supplied Kits/Parts.

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BLANK PAGE
Commercial 

Airplanes MD11

Service Bulletin

Number: MD11-28-137

Original Issue: June 24, 2014

ATA System: 2800

SUBJECT: FUEL - Fuel - Change Fuel Pump Control and Indication System Wiring

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below.

GROUP CONFIGURATION DESCRIPTION

MD-11 and MD-11F Airplanes that change fuel pump control and

indication system wiring to detect and indicate uncommanded fuel

pump running conditions in accordance with SR11280077-7001,

-7002 and SR11280083-7001 drawing configurations.

1 -

MD-11 Airplanes that change fuel pump control and indication system

wiring to detect and indicate uncommanded fuel pump running

conditions in accordance with SR11280077-7003, -7004 and

SR11280083-7003 drawing configurations.

2 -

MD-11 and MD-11F Airplanes that change fuel pump control and

indication system wiring to detect and indicate uncommanded fuel

pump running conditions in accordance with SR11280077-7005,

-7006 and SR11280083-7005 drawing configurations.

3 -

Airplane Models:

MD-11, MD-11F

Fuselage Num- Group

ber

447 - 449 1

451 - 459 1

460 - 464 1

466 - 469 1

470 - 479 1

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Fuselage Num- Group

ber

480 - 489 1

491 - 499 1

500 - 509 1

510 - 517 1

519 1

520 - 529 1

530 - 531 1

532 2

533 - 539 1

540 - 543 1

544 2

545 - 549 1

550 - 552 1

554 - 559 1

560 - 569 1

570 - 579 1

580 - 589 1

590 - 596 1

597 - 599 3

600 - 609 3

610 - 619 3

620 - 629 3

630 - 639 3

640 - 646 3

2. Spares Affected

None.

B. Concurrent Requirements

The service bulletin listed below must be done before or at the same time as this service bulletin:

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BOEING SERVICE BULLETIN MD11-28-137
Company Service Bulletin Description

Replace Fuel Pump Control Relays with Fault Current

Detectors and Change Fuel Tank Boost/Transfer Pump

Wire Termination

MD11-28A133

Original Issue

The Boeing Company

C. Reason

Frictional heating or sparking resulting from fuel pump failure, wear of fuel pump rotating components,

or ingestion of debris by the fuel pump may result in development of a fuel tank ignition source. Frictional

heating or sparking 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.

Center wing auxiliary, tail, and fuselage auxiliary fuel tanks may be subject to this condition since they

are normally pumped dry over the course of a mission. A fuel tank ignition event could develop with a

fuel pump running in an empty tank if the normal shutoff command is delayed or as a result of control

system failures that keep the fuel pump in a latent uncommanded running condition. To ensure a timely

fuel pump shutoff command revise flight crew shutoff procedures for center wing auxiliary, tail, and

fuselage auxiliary fuel pumps. To address the latent fuel pump uncommanded running condition change

center wing auxiliary, tail, and fuselage auxiliary fuel pump control and indication system wiring to

detect and indicate fuel pump uncommanded running conditions. If not corrected, a fuel pump running

in an empty fuel tank may result in a fuel tank ignition event.

This service bulletin is the result of the safety assessments conducted by Boeing under a Special

Federal Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.

Boeing Fleet Team Digest (FTD) MD-11 FTD 28-03006 and MD-11 FTD 28-13001 are related to this

service bulletin.

D. Description

This service bulletin changes fuel pump control and indication system wiring to detect and indicate fuel

pump uncommanded running conditions.

The work in this service bulletin is done in the maintenance zone(s) given below.

Group 1, 3:

Affected Maintenance Zones

Model Zone

112, 113, 114, 121, 122, 123, 125, 126, 127,

131, 132

MD-11, MD-11F

Group 2:

Affected Maintenance Zones

Model Zone

112, 113, 114, 121, 122, 123, 125, 126, 127,

131, 132

MD-11

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E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-08-23 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 2013-08-23.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

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

(AMOC) to the requirements of paragraph (g)(2) and (g)(4) of AD 2013-08-23. All provisions of AD

2013-08-23 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 2 6.0 3.0

Install Hardware 2 1.2 0.6

Route and Terminate 2 84.8 42.4

Wiring

Close Access 2 6.0 3.0

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Group 1:

Task Number of Persons Task Hours Elapsed Hours

Test 2 1.0 0.5

TOTAL FOR EACH AIRPLANE 99.0 49.5

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.0 3.0

Install Hardware 2 2.6 1.3

Route and Terminate 2 146.6 73.3

Wiring

Close Access 2 6.0 3.0

Test 2 1.0 0.5

TOTAL FOR EACH AIRPLANE 162.2 81.1

Group 3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 6.0 3.0

Install Hardware 2 1.2 0.6

Route and Terminate 2 84.0 42.0

Wiring

Close Access 2 6.0 3.0

Test 2 1.0 0.5

TOTAL FOR EACH AIRPLANE 98.2 49.1

H. Weight and Balance Changes

Group 1:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

MD-11, MD-11F 595.3 +6.6 +3928.9

Group 2:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

MD-11 588.5 +11.0 +6473.5

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Group 3:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

MD-11, MD-11F 624.8 +5.6 +3498.9

I. Electrical Load Data

1. Direct Current DC Load Changes:

No DC loads added or deleted.

2. Alternating Current (AC) Load Changes:

a. Add AC loads by amounts shown below:

UNITS

%OPR

1

100

E/NE

PHASE

E

C

VAC

PF

115

VAC-2

1

UNIT

LOAD

(W)

5

NOTES

(B1-

1209)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

LWR AUX TK L PUMP

SLAVE RELAY

5D0123-1

ITEM

500X

R2-

5875A

CHAP

280

BUS

2B

% 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 5 5 5

CRUISE COLD 100 100 5 5 5

CRUISE HOT 100 100 5 5 5

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

UNITS

%OPR

1

100

E/NE

PHASE

E

C

VAC

PF

115

VAC-2

1

UNIT

LOAD

(W)

5

NOTES

(B1-

1207)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

UPR AUX TK L PUMP

SLAVE RELAY

5D0123-1

ITEM

500X

R2-

5880A

CHAP

280

BUS

2B

% 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

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BOEING SERVICE BULLETIN MD11-28-137
UNITS

%OPR

1

100

E/NE

PHASE

E

C

VAC

PF

115

VAC-2

1

UNIT

LOAD

(W)

5

NOTES

(B1-

1207)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

UPR AUX TK L PUMP

SLAVE RELAY

5D0123-1

ITEM

500X

R2-

5880A

CHAP

280

BUS

2B

% TIME OPR AVERAGE WATTS

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

START 0 0 0 0 0

TAXI 0 0 0 0 0

TAKEOFF & CLIMB 100 100 5 5 5

CRUISE COLD 100 100 5 5 5

CRUISE HOT 100 100 5 5 5

DESCENT & LAND 10 10 5 0.5 0.5

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

UNITS

%OPR

1

100

E/NE

PHASE

E

A

VAC

PF

115

VAC-1

1

UNIT

LOAD

(W)

5

NOTES

(B1-497)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

L TAIL TANK PUMP

SLAVE RELAY

5D0123-1

ITEM

500X

R2-

5888A

CHAP

280

BUS

1A

% 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 0 0 0 0 0

CRUISE COLD 50 50 5 2.5 2.5

CRUISE HOT 50 50 5 2.5 2.5

DESCENT & LAND 50 50 5 2.5 2.5

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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BOEING SERVICE BULLETIN MD11-28-137
UNITS

%OPR

1

100

E/NE

PHASE

E

A

VAC

PF

115

VAC

Emer

1

UNIT

LOAD

(W)

5

NOTES

(B1-

1577)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

TAIL ALT PUMP

SLAVE RELAY

5D0123-1

ITEM

500X

R2-

7000

CHAP

280

BUS

3A

% 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 0 0 0 0 0

CRUISE COLD 0 5 5 0 0.25

CRUISE HOT 0 5 5 0 0.25

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

UNITS

%OPR

1

100

E/NE

PHASE

E

C

VAC

PF

115

VAC-1

1

UNIT

LOAD

(W)

5

NOTES

(B1-

1206)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

UPR AUX TK R PUMP

SLAVE RELAY

5D0123-1

ITEM

500X

R2-

5878A

CHAP

280

BUS

1A

% 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 5 5 5

CRUISE COLD 100 100 5 5 5

CRUISE HOT 100 100 5 5 5

DESCENT & LAND 10 10 5 0.5 0.5

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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UNITS

%OPR

1

100

E/NE

PHASE

E

C

VAC

PF

115

VAC-3

1

UNIT

LOAD

(W)

5

NOTES

(B1-

1208)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

LWR AUX TK R PUMP

SLAVE RELAY

5D0123-1

ITEM

500X

R2-

5884A

CHAP

280

BUS

3C

% 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 5 5 5

CRUISE COLD 100 100 5 5 5

CRUISE HOT 100 100 5 5 5

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

UNITS

%OPR

1

100

E/NE

PHASE

E

A

VAC

PF

115

VAC-2

1

UNIT

LOAD

(W)

5

NOTES

(B1-496)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

R TAIL TANK PUMP

SLAVE RELAY

5D0123-1

ITEM

500X

R2-

5889A

CHAP

280

BUS

2B

% 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 0 0 0 0 0

CRUISE COLD 50 50 5 2.5 2.5

CRUISE HOT 50 50 5 2.5 2.5

DESCENT & LAND 50 50 5 2.5 2.5

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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Group 2:

UNITS

%OPR

1

100

E/NE

PHASE

E

C

VAC

PF

115

VAC-1

1

UNIT

LOAD

(W)

5

NOTES

(B1-

1645)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

FWD AUX-1 L PUMP

SLAVE RELAY

5D0123-1

ITEM

500X

R2-

7001

CHAP

280

BUS

1A

% 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 5 5 5

CRUISE COLD 100 100 5 5 5

CRUISE HOT 100 100 5 5 5

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

Group 2:

UNITS

%OPR

1

100

E/NE

PHASE

E

C

VAC

PF

115

VAC-1

1

UNIT

LOAD

(W)

5

NOTES

(B1-542)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

FWD AUX-2 L PUMP

SLAVE RELAY

5D0123-1

ITEM

500X

R2-

7002

CHAP

280

BUS

1A

% 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 5 5 5

CRUISE COLD 100 100 5 5 5

CRUISE HOT 100 100 5 5 5

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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Group 2:

UNITS

%OPR

1

100

E/NE

PHASE

E

C

VAC

PF

115

VAC-3

1

UNIT

LOAD

(W)

5

NOTES

(B1-

1644)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

FWD AUX-1 R PUMP

SLAVE RELAY

5D0123-1

ITEM

500X

R2-

7003

CHAP

280

BUS

3C

% 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 5 5 5

CRUISE COLD 100 100 5 5 5

CRUISE HOT 100 100 5 5 5

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

Group 2:

UNITS

%OPR

1

100

E/NE

PHASE

E

C

VAC

PF

115

VAC-3

1

UNIT

LOAD

(W)

5

NOTES

(B1-543)

SUPPLIER

DACO

EQUIPMENT NAME

PART NUMBER

FWD AUX-2 R PUMP

SLAVE RELAY

5D0123-1

ITEM

5002

R2-

7004

CHAP

280

BUS

3C

% 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 5 5 5

CRUISE COLD 100 100 5 5 5

CRUISE HOT 100 100 5 5 5

DESCENT & LAND 0 0 0 0 0

EMERGENCY 0 0 0 0 0

GROUND SERVICE 0 0 0 0 0

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b. Delete AC loads by amounts shown below:

No AC loads deleted.

J. References

1. Existing Data:

a. Boeing Service Bulletin MD11-28A133.

b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2013-08-23.

c. Standard Overhaul Practices Manual (SOPM) 20-50-01.

d. Standard Wiring Practices Manual (SWPM) 20-00-09, 20-00-13, 20-00-16, 20-10-04, 20-20-02,

20-20-03, 20-31-00, 20-40-01 and 20-50-01.

e. MD11 Aircraft Maintenance Manual (AMM) 06-31-00, 06-31-06, 06-31-08, 24-40-00, 28-22-01

and 52-31-00.

f. MD-11 Fleet Team Digest (FTD) 28-03006 and 28-13001.

g. MD-11 Structural Repair Manual (SRM) 51.

2. Data Supplied with this Service Bulletin:

No data is supplied with this service bulletin. To obtain the data necessary to support this service

bulletin submit a data request to:

Data and Services Management

Mail Code: 110-SE20 (bldg 80)

2201 Seal Beach Blvd.

Seal Beach, California 90740 USA

Phone: (562) 797-1717

Fax: (562) 797-3783

E-mail: lbd.dataservicesmanagement@boeing.com

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

ELEC INSTL - FUEL PUMP UNCOMMAND- DWG B -

ED SIGNAL

SR11280077

WIRE INSTL - FUEL PUMP UNCOMMAND- DWG A -

ED SIGNAL

SR11280083

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

None.

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4. Process Data:

Douglas Process Specifications referred to on the drawings are not given in this service bulletin

since these procedures are frequently used as standard shop practices.

K. Publications Affected

1. Publications:

Publication Chapter-Section

Aircraft Maintenance Manual 28-22

FAA Approved Flight Manual Section 1 and 3

Fault Isolation Manual 28-02, 28-14, 28-22

Flight Crew Operations Manual Volumes I, II & III

Special Compliance Item Report MDC-02K1003 (ALI 28-4)

Wiring Diagram Manual 28-21, 28-22, 28-44

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated this service bulletin for effects on Fatigue Critical Structure (FCS) and for

changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This

service bulletin does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

M. Software Accomplishment Summary

Not affected.

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BLANK PAGE
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

SB11280137-3 Service Kit 120 $14,149.00

SB11280137-5 Service Kit 120 $17,765.00

SB11280137-7 Service Kit 120 $14,856.00

Operators are encouraged to complete the survey provided in APPENDIX B 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:

SB11280137-3

Part Number QTY Name Notes

3D0005-04-9 14 SCREW (a)

3D0005-08-11 6 SCREW (a)

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Group 1:

SB11280137-3

Part Number QTY Name Notes

3D0191-04 14 CLIPNUT (a)

5D0010-15 5 TERM BLOCK (a)

5D0021-2 7 SOCKET (a)

5D0107-1 1 TERM BLOCK (a)

5D0123-1 7 RELAY (a)

MS35338-42 6 LOCKWASHER

NAS1252-4L 14 WASHER

NAS1252-8L 6 WASHER

NAS1329S08K75 6 RIVNUT

SR11280077-101 1 WIRE KIT (b)

SR11280077-104 1 WIRE KIT (b)

SR11280077-108 1 WIRE KIT (b)

SR11280077-112 1 WIRE KIT (b)

SR11280077-114 1 WIRE KIT (b)

SR11280077-116 1 WIRE KIT (b)

SR11280077-117 1 WIRE KIT (b)

SR11280077-119 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table below for Wire Kit Contents.

Group 1:

Wire Kit Table

SR11280077 -101 -104 -108 -112 -114 -116 -117 -119

Part Number QTY Name Notes

5D0086-24 2 TERMINAL LUG 764 (a)

5D0086-26 1 TERMINAL LUG 766 (a)

5D0086-3 3 TERMINAL LUG 878 (a)

5D0086-5 4 6 2 TERMINAL LUG 761 (a)

5D0086-6 4 2 3 1 TERMINAL LUG 762 (a)

32 WIRE CODE 801 (b)

FT.

24

FT.

D2426-1C-16NM

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Group 1:

Wire Kit Table

SR11280077 -101 -104 -108 -112 -114 -116 -117 -119

Part Number QTY Name Notes

100 WIRE CODE 801 (b)

FT.

11

FT.

29

FT.

20

FT.

250

FT.

250

FT.

255

FT.

50

FT.

D2426-1C-20NM

52 WIRE CODE 801 (b)

FT.

D2426-1C-22NM

20 WIRE CODE 801 (b)

FT.

D2426-1C-24NM

DC38-16P 4 2 PIN, T/C 1131

DC38-20P 33 4 2 3 1 3 PIN, T/C 1126

DC39-16S 1 28 2 SKT T/C 1123

DC39-20S 6 6 7 SKT T/C 1124

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

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

Group 2:

SB11280137-5

Part Number QTY Name Notes

3D0005-04-9 22 SCREW (a)

3D0005-08-11 16 SCREW (a)

3D0005-3-11 2 SCREW (a)

3D0191-04 22 CLIPNUT (a)

5D0010-13 1 TERM BLOCK (a)

5D0010-15 8 TERM BLOCK (a)

5D0021-2 11 SOCKET (a)

5D0107-1 1 TERM BLOCK (a)

5D0123-1 11 RELAY (a)

MS35338-42 16 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10L 2 WASHER

NAS1252-4L 22 WASHER

NAS1252-8L 16 WASHER

NAS1329S08K75 7 RIVNUT

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Group 2:

SB11280137-5

Part Number QTY Name Notes

SR11280077-102 1 WIRE KIT (b)

SR11280077-105 1 WIRE KIT (b)

SR11280077-107 1 WIRE KIT (b)

SR11280077-109 1 WIRE KIT (b)

SR11280077-111 1 WIRE KIT (b)

SR11280077-113 1 WIRE KIT (b)

SR11280077-115 1 WIRE KIT (b)

SR11280077-116 1 WIRE KIT (b)

SR11280077-118 1 WIRE KIT (b)

SR11280077-120 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table below for Wire Kit Contents.

Group 2:

Wire Kit Table

SR11280077 -102 -105 -107 -109 -111 -113 -115 -116 -118 -120

Part Number QTY Name Notes

5D0013-2A 2 DIODE (a)

TERMINAL (a)

LUG 764

5D0086-24 2

TERMINAL (a)

LUG 766

5D0086-26 1

TERMINAL (a)

LUG 878

5D0086-3 3

TERMINAL (a)

LUG 761

5D0086-5 8 6 6

TERMINAL (a)

LUG 762

5D0086-6 2 6 4 3 3

WIRE CODE (b)

801

32

FT.

24

FT.

D2426-1C16NM

WIRE CODE (b)

801

150

FT.

33

FT.

29

FT.

39

FT.

334

FT.

84

FT.

334

FT.

85

FT.

349

FT.

236

FT.

D2426-1C20NM

WIRE CODE (b)

801

108

FT.

42

FT.

D2426-1C22NM

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Group 2:

Wire Kit Table

SR11280077 -102 -105 -107 -109 -111 -113 -115 -116 -118 -120

Part Number QTY Name Notes

WIRE CODE (b)

801

20

FT.

D2426-1C24NM

DC38-16P 4 1 3 PIN, T/C 1131

DC38-20P 7 55 1 1 6 3 3 2 6 PIN, T/C 1126

DC39-16S 9 36 1 2 1 SKT T/C 1123

DC39-20S 13 8 1 1 10 SKT T/C 1124

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

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

Group 3:

SB11280137-7

Part Number QTY Name Notes

3D0005-08-10 2 SCREW (a)

3D0005-08-11 6 SCREW (a)

3D0039-8 2 NUT-CLIP (a)

5D0123-1 7 RELAY (a)

65009-020-513 7 RELAY SOCKET

65009-021-513 1 RELAY SOCKET

9D0062-3-08-08 2 BRACKET (a)

M39029/1-102 1 PIN T/C 1145

MS20470AD4-3D 4 RIVET

MS35338-42 6 LOCKWASHER

NAS1252-8L 6 WASHER

NAS1329S08K75 6 RIVNUT

NMC1001-2 2 CLAMP

SR11280077-103 1 WIRE KIT (b)

SR11280077-106 1 WIRE KIT (b)

SR11280077-110 1 WIRE KIT (b)

SR11280077-112 1 WIRE KIT (b)

SR11280077-114 1 WIRE KIT (b)

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BOEING SERVICE BULLETIN MD11-28-137
Group 3:

SB11280137-7

Part Number QTY Name Notes

SR11280077-116 1 WIRE KIT (b)

SR11280077-117 1 WIRE KIT (b)

SR11280077-119 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table below for Wire Kit Contents.

Group 3:

Wire Kit Table

SR11280077 -103 -106 -110 -112 -114 -116 -117 -119

Part Number QTY Name Notes

5D0086-24 2 TERMINAL LUG 764 (a)

5D0086-26 1 TERMINAL LUG 766 (a)

5D0086-5 4 6 2 TERMINAL LUG 761 (a)

5D0086-6 2 3 1 TERMINAL LUG 762 (a)

5D0187-2222P 14 PIN T/C 1005 (a)

617240 8 PIN T/C 579

617340 4 3 SOCKET T/C 578

25 WIRE CODE 801 (b)

FT.

24

FT.

D2426-1C-16NM

100 WIRE CODE 801 (b)

FT.

11

FT.

29

FT.

20

FT.

250

FT.

250

FT.

188

FT.

50

FT.

D2426-1C-20NM

126 WIRE CODE 801 (b)

FT.

D2426-1C-24NM

DC38-16P 2 PIN, T/C 1131

DC38-20P 4 2 3 1 3 PIN, T/C 1126

DC39-16S 2 SKT T/C 1123

DC39-20S 3 3 7 SKT T/C 1124

M39029/1-101 34 PIN T/C 1147

M39029/1-102 2 PIN T/C 1145

M39029/22-193 28 CONTACT

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

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

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2. Parts and Materials Supplied by the Operator

Part Number / Specification QTY Name Notes

DMS 2089 As Required TIE TAPE (a)

(18XTZ), (23XTZ)

or

Equivalent

(a) Can be purchased from: Gudenbrod, Incorporated, 274 Shoemaker Road,

Pottstown, Pennsylvania, 19464, CAGE 82110

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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BOEING SERVICE BULLETIN MD11-28-137

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: 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.

CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE

TO THE AIRPLANE OR EQUIPMENT.

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

MD-11 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 in SRM

Chapter 51 may be used. In addition, washers may be installed for fastener grip

length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate

full threaded fasteners (screws) needed for installation in this service bulletin.

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 are in MD-11 SRM 51.

• Torque limits to tighten nuts and bolts are in MD-11 SRM 51.

7. Refer to these SWPM chapters for applicable operations, as accepted procedures:

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Chapter Title

SWPM 20-00-09 GENERAL MAINTENANCE PRACTICES - ELECTRICAL

SWPM 20-00-13 ELECTRICAL WIRE CODES

ELECTRICAL WIRE END TERMINATION CODES AND TOOL

CODES

SWPM 20-00-16

SWPM 20-10-04 COIL AND STOW - MAINTENANCE PRACTICES

SWPM 20-20-02 TERMINAL BLOCKS - MAINTENANCE PRACTICES

GENERAL INSTALLATIONS HARDWARE - MAINTENANCE

PRACTICES

SWPM 20-20-03

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. 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.

10. Some Boeing parts are supplied in a temporary configuration. Those parts are

identified with a 'U' or 'Y' in place of the '-' (dash) in the part number. It is permitted

to install parts identified with a 'U' or 'Y' as an alternative to the '-' (dash) number

part. Boeing Drawing SE10000000, Sheets 5.0 and 6.0 contain more data.

11. 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.

12. 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.

13. 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.

14. Review and understand all general notes of Service Rework Drawings that follow:

Service Rework Drawing Sheets

SR11280077 3, 3.1, 3.2, 3.3, 3.4

SR11280083 1

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BOEING SERVICE BULLETIN MD11-28-137
B. WORK INSTRUCTIONS

1. Gain access:

a. Open access doors in the table as follow:

Access Door Reference Location/Description

112AB MD11 AMM 06-31-00 Avionics Equipment Compartment

113AL Left-side Air-conditioning Compartment

113DL

114AR Right-side Air-conditioning Compartment

131AB Center Accessory Compartment

b. Open forward cargo compartment door. Refer to MD11 AMM 52-31-00 as an accepted

procedure.

c. Remove/Keep forward cargo compartment ceiling panels and attaching hardware right and

left sides between stations Y=595.000 and Y=673.500. Refer to MD11 AMM 06-31-06 and

MD11 AMM 06-31-08.

2. Install relays and hardware in accordance with the table(s) as follow:

Group 1:

Drawing Sheets

SR11280077-7001 13, 14, 22, 24, 25

Group 2:

Drawing Sheets

SR11280077-7003 15, 16, 18, 20, 21, 22, 23, 24, 25, 26, 27

Group 3:

Drawing Sheets

SR11280077-7005 17, 18, 19, 22, 24, 25

3. Route wiring in accordance with the table(s) as follow:

Group 1:

Drawing Sheet(s) Additional Data

SR11280083 1, 4.1, 5, 6, 7, 8, 9, 10

SR11280083 2 Views C, B-B, FORWARD EQUIPMENT RACK

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BOEING SERVICE BULLETIN MD11-28-137
Group 1:

Drawing Sheet(s) Additional Data

SR11280083 3 Views N, F-F, G-G, D

SR11280083 11 Views AL-AL, AM for -7001, AN, AP

Group 2:

Drawing Sheet(s) Additional Data

SR11280083 1, 2, 4.1, 5, 6, 7, 8, 9, 10

SR11280083 3 Views N, F-F, G-G, D

SR11280083 11 Views AL-AL, AM for -7003, AN, AP

Group 3:

Drawing Sheet(s) Additional Data

SR11280083 1, 3, 4, 5, 6, 7, 8, 9, 10

SR11280083 2 Views C, B-B, FORWARD EQUIPMENT RACK

SR11280083 11 Views AL-AL, AM for -7005, AN, AP

4. Change wiring in accordance with the table(s) as follow:

Group 1:

Drawing Sheets

6.8, 6.9, 6.10, 6.11, 6.12, 8, 101.201, 104.201, 104.202, 108.201,

112.201, 114.201, 116.201, 117.201, 119.201, 302.201

SR11280077-7001

Group 2:

Drawing Sheets

6.13, 6.14, 6.15, 6.16, 6.17, 6.18, 6.19, 6.20, 8, 102.201, 105.201,

105.202, 107.201, 109.201, 111.201, 113.201, 115.201, 116.201,

118.201, 120.201, 301.201, 303.201, 305.201

SR11280077-7003

Group 3:

Drawing Sheets

6.21, 6.22, 6.23, 6.24, 6.25, 6.26, 103.201, 106.201, 106.202,

110.201, 112.201, 114.201, 116.201, 117.201, 119.201, 304.201

SR11280077-7005

5. Test fuel pumps uncommanded on detection circuits as follow:

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BOEING SERVICE BULLETIN MD11-28-137
Group 1, 3:

Perform Functional Test of the Fuel Pumps Uncommanded On Detection Circuit in accordance

with MD-11 AMM 28-22-01.

Group 2:

Perform Functional Test of the Fuel Pumps Uncommanded On Detection Circuit in accordance

with APPENDIX A.

6. Close access:

a. Install/Kept forward cargo compartment ceiling panels and attaching hardware right and left

sides between stations Y=595.000 and Y=673.500. Refer to MD11 AMM 06-31-06 and MD11

AMM 06-31-08.

b. Close forward cargo compartment door. Refer to MD11 AMM 52-31-00 as an accepted

procedure.

c. Close access doors in the table as follow:

Access Door Reference Location/Description

112AB MD11 AMM 06-31-00 Avionics Equipment Compartment

113AL Left-side Air-conditioning Compartment

113DL

114AR Right-side Air-conditioning Compartment

131AB Center Accessory Compartment

7. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN MD11-28-137
1. Test equipment required:

a. Electrical jumper wire, 22 gauge, two feet in length with alligator clips at both ends large enough

to grasp Fault Current Detector (FCD) terminal posts.

b. Multimeter, with alligator clips at end of wire leads large enough to grasp FCD terminal posts.

2. Test set up:

a. Apply electrical power to the aircraft. Refer to MD-11 AMM 24-40-00 as an accepted procedure.

b. On the Systems Control Panel do as follows:

(1) Turn the six BRT knobs (15) to the middle position.

(2) Push the FUEL switchlight (16).

c. Adjust the applicable fuel quantities as follows:

(1) Total aux fuel quantity is less than 600 lb (272 kg).

(2) Forward aux tank (if installed) fuel quantity must be less than 200 lb (91 kg).

(3) Tail tank fuel quantity must be less than 300 lb (136 kg).

d. On the Fuel System Control Panel (FSCP) set the SYSTEM switchlight (17) to MANUAL and after

10 seconds verify the following on the FUEL synoptic page:

(1) All main tank forward and aft boost pumps (total of 7) are shown as ON (green or amber circle

and pump vanes).

(2) Upper Aux Left Pump is shown as ON (green or amber circle and pump vanes).

(3) Upper Aux Right Pump is shown as ON (green or amber circle and pump vanes).

(4) Lower Aux Left Pump is shown as ON (green or amber circle and pump vanes).

(5) Lower Aux Right Pump is shown as ON (green or amber circle and pump vanes).

(6) Tail Tank Left Pump is shown as ON (green or amber circle and pump vanes).

(7) Tail Tank Right Pump is shown as ON (green or amber circle and pump vanes).

e. On the FSCP push the 1 PUMPS, 2 PUMPS, 3 PUMPS, AUX TANKS L TRANS, AUX TANKS R

TRANS and TAIL TANK TRANS switches and verify the following on the FUEL synoptic page:

(1) All main tank forward and aft boost pumps (total of 7) are shown as OFF (white empty circle).

(2) Upper Aux Left Pump is shown as OFF (white empty circle).

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 1 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
(3) Upper Aux Right Pump is shown as OFF (white empty circle).

(4) Lower Aux Left Pump is shown as OFF (white empty circle).

(5) Lower Aux Right Pump is shown as OFF (white empty circle).

(6) Tail Tank Left Pump is shown as OFF (white empty circle).

(7) Tail Tank Right Pump is shown as OFF (white empty circle).

NOTE: If other fuel pumps are shown as ON, push the applicable pump switch on the FSCP

until all fuel pumps are shown as OFF.

f. On the FWD AUX FUEL TANK switch panel, verify that the L TRANS and R TRANS switches are

OFF.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT

BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS

AND DAMAGE TO EQUIPMENT CAN OCCUR.

g. Open circuit breakers and install safety tags as follow:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

B 20 B1-1578 FUEL PUMP POWER TAIL TANK L XFR

B 21 B1-394 FUEL PUMP POWER AUX TANK 1 L FWD

B 22 B1-1647 FUEL PUMP POWER AUX TANK 2 L FWD

B 23 B1-1250 FUEL PUMP POWER AUX TANK R UPR

B 24 B1-614 FUEL PUMP POWER TANK 1 FWD

B 25 B1-608 FUEL PUMP POWER TANK 2 FWD

B 26 B1-618 FUEL PUMP POWER TANK 3 XFR

E 20 B1-497 FUEL PUMP CONTROL TAIL TANK L XFR

E 21 B1-1645 FUEL PUMP CONTROL AUX TANK 1 L FWD

E 22 B1-542 FUEL PUMP CONTROL AUX TANK 2 L FWD

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

E 24 B1-615 FUEL PUMP CONTROL TANK 1 FWD

E 25 B1-609 FUEL PUMP CONTROL TANK 2 FWD

E 26 B1-619 FUEL PUMP CONTROL TANK 3 XFR

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 2 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 20 B1-1576 FUEL PUMP POWER TAIL TANK R XFR

C 22 B1-1248 FUEL PUMP POWER AUX TANK L UPR

C 23 B1-1249 FUEL PUMP POWER AUX TANK L LWR

C 24 B1-610 FUEL PUMP POWER TANK 1 XFR

C 25 B1-596 FUEL PUMP POWER TANK 2 R AFT

C 26 B1-620 FUEL PUMP POWER TANK 3 AFT

F 21 B1-496 FUEL PUMP CONTROL TAIL TANK R XFR

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

F 24 B1-611 FUEL PUMP CONTROL TANK 1 XFR

F 25 B1-603 FUEL PUMP CONTROL TANK 2 R AFT

F 26 B1-621 FUEL PUMP CONTROL TANK 3 AFT

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

D 21 B1-393 FUEL PUMP POWER AUX TANK 1 R FWD

D 22 B1-1646 FUEL PUMP POWER AUX TANK 2 R FWD

D 23 B1-1251 FUEL PUMP POWER AUX TANK R LWR

D 24 B1-612 FUEL PUMP POWER TANK 1 AFT

D 25 B1-756 FUEL PUMP POWER TANK 2 XFR

D 26 B1-616 FUEL PUMP POWER TANK 3 FWD

G 21 B1-1644 FUEL PUMP CONTROL AUX TANK 1 R FWD

G 22 B1-543 FUEL PUMP CONTROL AUX TANK 2 R FWD

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

G 24 B1-613 FUEL PUMP CONTROL TANK 1 AFT

G 25 B1-757 FUEL PUMP CONTROL TANK 2 XFR

G 26 B1-617 FUEL PUMP CONTROL TANK 3 FWD

3. Test procedure - Fuel Pumps Uncommanded On Detection Circuit Functional Test:

a. Upper Aux Left Pump (M1-1934) Test:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 3 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
(1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-2, remove

the terminal shield of FCD U1-702 (1) as follows:

(a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14).

(b) Remove the terminal shield (14).

(2) At the CAC EPC Bay-2 connect the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-702 (1).

(3) Close circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

(4) On the FUEL synoptic page, verify the Upper Aux Left Pump is shown as ON (amber circle

and pump vanes).

NOTE: If the Upper Aux Left Pump is not shown as ON, this indicates that there is a possible

wiring or component failure of the uncommanded on detection circuitry and

troubleshooting is necessary.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(5) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

(6) On the FUEL synoptic page verify the Upper Aux Left Pump is shown in as OFF (white empty

circle).

(7) At the CAC EPC Bay-2 remove the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-702 (1).

(8) At the CAC EPC Bay-2 attach the multimeter lead, set to measure AC voltage, to terminal

stud 12 of FCD U1-702 (1) and verify that it reads less than 10 volts.

(9) Close circuit breaker as follows:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 4 OF 33)

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UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

(10) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-702 (1)

reads more than 110 volts.

WARNING: THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-702 TO BE POWERED

WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR

OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY

COULD RESULT.

(11) On the FSCP, push the AUX TANKS L TRANS switch and verify as follows:

(a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-702 (1)

reads less than 10 volts.

(b) On the FUEL synoptic page the Upper Aux Left Pump is shown as ON (amber circle and

pump vanes).

(12) On the FSCP, push the AUX TANKS L TRANS switch and verify as follows:

(a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-702 (1)

reads more than 110 volts.

(b) On the FUEL synoptic page the Upper Aux Left Pump is shown as OFF (white empty

circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(13) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

(14) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-702 (1)

reads less than 10 volts.

(15) At the CAC EPC Bay-2 remove the multimeter lead from terminal stud 12 of FCD U1-702 (1).

(16) At the CAC EPC Bay-2 install the terminal shield (14) on FCD U1-702 (1) as follows:

(a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

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b. Upper Aux Right Pump (M1-1933) Test:

(1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-1, remove

the terminal shield of FCD U1-701 (2) as follows:

(a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14).

(b) Remove the terminal shield (14).

(2) At the CAC EPC Bay-1 connect the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-701 (2).

(3) Close circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

(4) On the FUEL synoptic page, verify the Upper Aux Right Pump is shown as ON (amber circle

and pump vanes).

NOTE: If the Upper Aux Right Pump is not shown as ON, this indicates that there is a possible

wiring or component failure of the uncommanded on detection circuitry and

troubleshooting is necessary.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(5) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

(6) On the FUEL synoptic page verify the Upper Aux Right Pump is shown in as OFF (white empty

circle).

(7) At the CAC EPC Bay-1 remove the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-701 (2).

(8) At the CAC EPC Bay-1 attach the multimeter lead, set to measure AC voltage, to terminal

stud 12 of FCD U1-701 (2) and verify that it reads less than 10 volts.

(9) Close circuit breaker as follows:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 6 OF 33)

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UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

(10) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-701 (2)

reads more than 110 volts.

WARNING: THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-701 TO BE POWERED

WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR

OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY

COULD RESULT.

(11) On the FSCP, push the AUX TANKS R TRANS switch and verify as follows:

(a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-701 (2)

reads less than 10 volts.

(b) On the FUEL synoptic page the Upper Aux Right Pump is shown as ON (amber circle

and pump vanes).

(12) On the FSCP, push the AUX TANKS R TRANS switch and verify as follows:

(a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-701 (2)

reads more than 110 volts.

(b) On the FUEL synoptic page the Upper Aux Right Pump is shown as OFF (white empty

circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(13) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

(14) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-701 (2)

reads less than 10 volts.

(15) At the CAC EPC Bay-1 remove the multimeter lead from terminal stud 12 of FCD U1-701 (2).

(16) At the CAC EPC Bay-1 install the terminal shield (14) on FCD U1-701 (2) as follows:

(a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

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c. Lower Aux Left Pump (M1-1936) Test:

(1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-2, remove

the terminal shield of FCD U1-704 (3) as follows:

(a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14).

(b) Remove the terminal shield (14).

(2) At the CAC EPC Bay-2 connect the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-704 (3).

(3) Close circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(4) On the FUEL synoptic page, verify the Lower Aux Left Pump is shown as ON (amber circle

and pump vanes).

NOTE: If the Lower Aux Left Pump is not shown as ON, this indicates that there is a possible

wiring or component failure of the uncommanded on detection circuitry and

troubleshooting is necessary.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(5) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(6) On the FUEL synoptic page verify the Lower Aux Left Pump is shown in as OFF (white empty

circle).

(7) At the CAC EPC Bay-2 remove the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-704 (3).

(8) At the CAC EPC Bay-2 attach the multimeter lead, set to measure AC voltage, to terminal

stud 12 of FCD U1-704 (3) and verify that it reads less than 10 volts.

(9) Close circuit breaker as follows:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

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UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(10) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-704 (3)

reads more than 110 volts.

WARNING: THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-704 TO BE POWERED

WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR

OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY

COULD RESULT.

(11) On the FSCP, push the AUX TANKS L TRANS switch and verify as follows:

(a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-704 (3)

reads less than 10 volts.

(b) On the FUEL synoptic page the Lower Aux Left Pump is shown as ON (amber circle and

pump vanes).

(12) On the FSCP, push the AUX TANKS L TRANS switch and verify as follows:

(a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-704 (3)

reads more than 110 volts.

(b) On the FUEL synoptic page the Lower Aux Left Pump is shown as OFF (white empty

circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(13) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

(14) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-704 (3)

reads less than 10 volts.

(15) At the CAC EPC Bay-2 remove the multimeter lead from terminal stud 12 of FCD U1-704 (3).

(16) At the CAC EPC Bay-2 install the terminal shield (14) on FCD U1-704 (3) as follows:

(a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

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d. Lower Aux Right Pump (M1-1935) Test:

(1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-3, remove

the terminal shield of FCD U1-703 (4) as follows:

(a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14).

(b) Remove the terminal shield (14).

(2) At the CAC EPC Bay-3 connect the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-703 (4).

(3) Close circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

B 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(4) On the FUEL synoptic page, verify the Lower Aux Right Pump is shown as ON (amber circle

and pump vanes).

NOTE: If the Lower Aux Right Pump is not shown as ON, this indicates that there is a possible

wiring or component failure of the uncommanded on detection circuitry and

troubleshooting is necessary.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(5) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

B 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(6) On the FUEL synoptic page verify the Lower Aux Right Pump is shown in as OFF (white empty

circle).

(7) At the CAC EPC Bay-3 remove the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-703 (4).

(8) At the CAC EPC Bay-3 attach the multimeter lead, set to measure AC voltage, to terminal

stud 12 of FCD U1-703 (4) and verify that it reads less than 10 volts.

(9) Close circuit breaker as follows:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

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UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

B 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(10) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-703 (4)

reads more than 110 volts.

WARNING: THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-703 TO BE POWERED

WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR

OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY

COULD RESULT.

(11) On the FSCP, push the AUX TANKS R TRANS switch and verify as follows:

(a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-703 (4)

reads less than 10 volts.

(b) On the FUEL synoptic page the Lower Aux Right Pump is shown as ON (amber circle

and pump vanes).

(12) On the FSCP, push the AUX TANKS R TRANS switch and verify as follows:

(a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-703 (4)

reads more than 110 volts.

(b) On the FUEL synoptic page the Lower Aux Right Pump is shown as OFF (white empty

circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(13) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

B 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

(14) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-703 (4)

reads less than 10 volts.

(15) At the CAC EPC Bay-3 remove the multimeter lead from terminal stud 12 of FCD U1-703 (4).

(16) At the CAC EPC Bay-3 install the terminal shield (14) on FCD U1-703 (4) as follows:

(a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 11 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
e. Tail Tank Left Pump (M1-2802) Test:

(1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-1, remove

the terminal shield of FCD U1-851 (5) as follows:

(a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14).

(b) Remove the terminal shield (14).

(2) At the CAC EPC Bay-1 connect the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-851 (5).

(3) Close circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 20 B1-497 FUEL PUMP CONTROL TAIL TANK L XFR

(4) On the FUEL synoptic page, verify the Tail Tank Left Pump is shown as ON (amber circle and

pump vanes).

NOTE: If the Tail Tank Left Pump is not shown as ON, this indicates that there is a possible

wiring or component failure of the uncommanded on detection circuitry and

troubleshooting is necessary.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(5) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 20 B1-497 FUEL PUMP CONTROL TAIL TANK L XFR

(6) On the FUEL synoptic page verify the Tail Tank Left Pump is shown in as OFF (white empty

circle).

(7) At the CAC EPC Bay-1 remove the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-851 (5).

(8) At the CAC EPC Bay-1 attach the multimeter lead, set to measure AC voltage, to terminal

stud 12 of FCD U1-851 (5) and verify that it reads less than 10 volts.

(9) Close circuit breaker as follows:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 12 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 20 B1-497 FUEL PUMP CONTROL TAIL TANK L XFR

(10) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-851 (5)

reads more than 110 volts.

WARNING: THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-851 TO BE POWERED

WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR

OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY

COULD RESULT.

(11) On the FSCP, push the TAIL TANK TRANS switch and verify as follows:

(a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-851 (5)

reads less than 10 volts.

(b) On the FUEL synoptic page the Tail Tank Left Pump is shown as ON (amber circle and

pump vanes).

(12) On the FSCP, push the TAIL TANK TRANS switch and verify as follows:

(a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-851 (5)

reads more than 110 volts.

(b) On the FUEL synoptic page the Tail Tank Left Pump is shown as OFF (white empty

circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(13) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 20 B1-497 FUEL PUMP CONTROL TAIL TANK L XFR

(14) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-851 (5)

reads less than 10 volts.

(15) At the CAC EPC Bay-1 remove the multimeter lead from terminal stud 12 of FCD U1-851 (5).

(16) At the CAC EPC Bay-1 install the terminal shield (14) on FCD U1-851 (5) as follows:

(a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 13 OF 33)

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48 of 69

BOEING SERVICE BULLETIN MD11-28-137
f. Tail Tank Right Pump (M1-2800) Test:

(1) At the Center Accessory Compartment (CAC) Electrical Power Center (EPC) Bay-2, remove

the terminal shield of FCD U1-852 (6) as follows:

(a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14).

(b) Remove the terminal shield (14).

(2) At the CAC EPC Bay-2 connect the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-852 (6).

(3) Close circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 21 B1-496 FUEL PUMP CONTROL TAIL TANK R XFR

(4) On the FUEL synoptic page, verify the Tail Tank Right Pump is shown as ON (amber circle

and pump vanes).

NOTE: If the Tail Tank Right Pump is not shown as ON, this indicates that there is a possible

wiring or component failure of the uncommanded on detection circuitry and

troubleshooting is necessary.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(5) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 21 B1-496 FUEL PUMP CONTROL TAIL TANK R XFR

(6) On the FUEL synoptic page verify the Tail Tank Right Pump is shown as OFF (white empty

circle).

(7) At the CAC EPC Bay-2 remove the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-852 (6).

(8) At the CAC EPC Bay-2 attach the multimeter lead, set to measure AC voltage, to terminal

stud 12 of FCD U1-852 (6) and verify that it reads less than 10 volts.

(9) Close circuit breaker as follows:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 14 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 21 B1-496 FUEL PUMP CONTROL TAIL TANK R XFR

(10) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-852 (6)

reads more than 110 volts.

WARNING: THE NEXT STEP WILL CAUSE TERMINAL X1 OF FCD U1-852 TO BE POWERED

WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN CLEAR

OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR INJURY

COULD RESULT.

(11) On the FSCP, push the TAIL TANK TRANS switch and verify as follows:

(a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-852 (6)

reads less than 10 volts.

(b) On the FUEL synoptic page the Tail Tank Right Pump is shown as ON (amber circle and

pump vanes).

(12) On the FSCP, push the TAIL TANK TRANS switch and verify as follows:

(a) At the CAC EPC Bay-2 the multimeter attached to terminal stud 12 of FCD U1-852 (6)

reads more than 110 volts.

(b) On the FUEL synoptic page the Tail Tank Right Pump is shown as OFF (white empty

circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(13) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

F 21 B1-496 FUEL PUMP CONTROL TAIL TANK R XFR

(14) At the CAC EPC Bay-2 verify the multimeter attached to terminal stud 12 of FCD U1-852 (6)

reads less than 10 volts.

(15) At the CAC EPC Bay-2 remove the multimeter lead from terminal stud 12 of FCD U1-852 (6).

(16) At the CAC EPC Bay-2 install the terminal shield (14) on FCD U1-852 (6) as follows:

(a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 15 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
g. Tail Altn Pump (M1-2801) Test:

(1) On the FUEL synoptic page, verify the Tail Altn Pump is shown as OFF (white empty circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(2) Open and tag circuit breakers as follow:

OVERHEAD, RIGHT EMER AC BUS

Row Column Number Name

G 17 B1-680 FUEL PUMP TANK 2 L AFT

G 18 B1-1574 FUEL PUMP TAIL TANK ALTN

(3) At the Avionics Compartment Forward Equipment Panel remove the terminal shield of FCD

U1-850 (7) as follows:

(a) Remove the two screws (12) and lockwashers (13) from the FCD terminal shield (14).

(b) Remove the terminal shield (14).

(4) At the Avionics Compartment Forward Equipment Panel connect the jumper wire from terminal

stud 11 to terminal stud 12 of FCD U1-850 (7).

(5) Close circuit breaker as follows:

OVERHEAD, RIGHT EMER AC BUS

Row Column Number Name

G 18 B1-1574 FUEL PUMP TAIL TANK ALTN

(6) On the FUEL synoptic page, verify the Tail Tank Altn Pump is shown as ON (amber circle

and pump vanes).

NOTE: If the Tail Tank Altn Pump is not shown as ON, this indicates that there is a possible

wiring or component failure of the uncommanded on detection circuitry and

troubleshooting is necessary.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(7) Open circuit breaker as follows:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 16 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
OVERHEAD, RIGHT EMER AC BUS

Row Column Number Name

G 18 B1-1574 FUEL PUMP TAIL TANK ALTN

(8) On the FUEL synoptic page verify the Tail Tank Altn Pump is shown as OFF (white empty

circle).

(9) At the Avionics Compartment Forward Equipment Panel remove the jumper wire from terminal

stud 11 to terminal stud 12 of FCD U1-850 (7).

(10) At the Avionics Compartment Forward Equipment Panel attach the multimeter lead, set to

measure AC voltage, to terminal stud 12 of FCD U1-850 (7) and verify that it reads less than

10 volts.

WARNING: THE NEXT STEPS WILL CAUSE TERMINALS 12, A2, B2, C2, A1, B1, C1, AND X1

OF FCD U1-850 TO BE POWERED WITH 115 VAC POWER. PERSONNEL IN THE

AVIONICS COMPARTMENT SHOULD REMAIN CLEAR OF THESE EXPOSED

TERMINALS UNTIL POWER IS REMOVED OR INJURY COULD RESULT.

(11) Close circuit breaker as follows:

OVERHEAD, RIGHT EMER AC BUS

Row Column Number Name

G 18 B1-1574 FUEL PUMP TAIL TANK ALTN

(12) At the Avionics Compartment Forward Equipment Panel verify the multimeter attached to

terminal stud 12 of FCD U1-850 (7) reads more than 110 volts.

(13) On the FSCP, push the TAIL TANK ALT PUMP switch and verify as follows:

(a) At the Avionics Compartment Forward Equipment Panel the multimeter attached to

terminal stud 12 of FCD U1-850 (7) reads less than 10 volts.

(14) On the FSCP, push the TAIL TANK ALT PUMP switch and verify as follows:

(a) At the Avionics Compartment Forward Equipment Panel the multimeter attached to

terminal stud 12 of FCD U1-850 (7) reads more than 110 volts.

(b) On the FUEL synoptic page the Tail Tank Altn Pump is shown as OFF (white empty

circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(15) Open circuit breaker as follows:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 17 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
OVERHEAD, RIGHT EMER AC BUS

Row Column Number Name

G 18 B1-1574 FUEL PUMP TAIL TANK ALTN

(16) At the Avionics Compartment Forward Equipment Panel verify the multimeter attached to

terminal stud 12 of FCD U1-850 (7) reads less than 10 volts.

(17) At the Avionics Compartment Forward Equipment Panel remove the multimeter lead from

terminal stud 12 of FCD U1-850 (7).

(18) At the Avionics Compartment Forward Equipment Panel install the terminal shield (14) on

FCD U1-850 (7) as follows:

(a) Install the terminal shield (14) with two screws (12) and two lockwashers (13).

(19) Close circuit breakers as follow:

OVERHEAD, RIGHT EMER AC BUS

Row Column Number Name

G 17 B1-680 FUEL PUMP TANK 2 L AFT

G 18 B1-1574 FUEL PUMP TAIL TANK ALTN

h. Forward Aux Tank Left Pumps (M1-1492 and M1-1494) Test:

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(1) Verify circuit breakers are open and tagged as follow:

OVERHEAD, RIGHT EMER AC BUS

Row Column Number Name

E 21 B1-1645 FUEL PUMP CONTROL AUX TANK 1 L FWD

E 22 B1-542 FUEL PUMP CONTROL AUX TANK 2 L FWD

(2) At the CAC EPC Bay-1 remove the terminal shields of FCDs U1-709 (8) and U1-790 (9) as

follow:

(a) Remove the two screws (12) and lockwashers (13) from each FCD terminal shield (14).

(b) Remove the terminal shields (14).

(3) At the CAC EPC Bay-1 connect the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-709 (8).

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 18 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
(4) Close circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 21 B1-1645 FUEL PUMP CONTROL AUX TANK 1 L FWD

(5) On the FUEL synoptic page, verify the two Fwd Aux Left Pumps are shown as ON (amber

circle and pump vanes).

(6) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the L TRANS

switch is illuminated.

NOTE: If the ON annunciator light in the L TRANS switch is not illuminated or the Fwd Aux

Left Pumps are not shown as ON, then there is a possible wiring or component failure

of the uncommanded on detection circuitry and troubleshooting is necessary.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(7) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 21 B1-1645 FUEL PUMP CONTROL AUX TANK 1 L FWD

(8) On the FUEL synoptic page verify both Fwd Aux Left Pumps are shown as OFF (white empty

circle).

(9) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the L TRANS

switch is not illuminated.

(10) At the CAC EPC Bay-1 remove the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-709 (8).

(11) At the CAC EPC Bay-1 attach the multimeter lead, set to measure AC voltage, to terminal

stud 12 of FCD U1-709 (8) and verify that it reads less than 10 volts.

(12) Close circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 21 B1-1645 FUEL PUMP CONTROL AUX TANK 1 L FWD

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 19 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
(13) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-709 (8)

reads more than 110 volts.

WARNING: THE NEXT STEP WILL CAUSE TERMINAL X1 OF THE FCD U1-709 TO BE

POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN

CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR

INJURY COULD RESULT.

(14) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows:

(a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-709 (8)

reads less than 10 volts.

(b) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as ON (amber circle

and pump vanes).

(c) After approximately 20 - 30 seconds the multimeter reads more than 110 volts.

NOTE: If the voltage does not increase to more than 110 volts and remain there, then

there is a possible wiring or component failure of the uncommanded on detection

circuitry and troubleshooting is necessary.

1) Monitor the voltage for an additional minute and verify that the voltage does not drop

back below 10 volts at any time.

(15) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows:

(a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-709 (8)

reads more than 110 volts.

(b) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as OFF (white empty

circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(16) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 21 B1-1645 FUEL PUMP CONTROL AUX TANK 1 L FWD

(17) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-709 (8)

reads less than 10 volts.

(18) At the CAC EPC Bay-1 remove the multimeter lead from terminal stud 12 of FCD U1-709 (8).

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 20 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
(19) At the CAC EPC Bay-1 connect the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-790 (9).

(20) Close circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 22 B1-542 FUEL PUMP CONTROL AUX TANK 2 L FWD

(21) On the FUEL synoptic page, verify the two Fwd Aux Left Pumps are shown as ON (amber

circle and pump vanes).

(22) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the L TRANS

switch is illuminated.

NOTE: If the ON annunciator light in the L TRANS switch is not illuminated or the Left Forward

Aux Pumps are not shown as ON, then there is a possible wiring or component failure

of the uncommanded on detection circuitry and troubleshooting is necessary.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(23) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 22 B1-542 FUEL PUMP CONTROL AUX TANK 2 L FWD

(24) On the FUEL synoptic page verify both Fwd Aux Left Pumps are shown as OFF (white empty

circle).

(25) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the L TRANS

switch is not illuminated.

(26) At the CAC EPC Bay-1 remove the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-790 (9).

(27) At the CAC EPC Bay-1 attach the multimeter lead, set to measure AC voltage, to terminal

stud 12 of FCD U1-790 (9) and verify that it reads less than 10 volts.

(28) Close circuit breaker as follows:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 21 OF 33)

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BOEING SERVICE BULLETIN MD11-28-137
UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 22 B1-542 FUEL PUMP CONTROL AUX TANK 2 L FWD

(29) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-790 (9)

reads more than 110 volts.

WARNING: THE NEXT STEP WILL CAUSE TERMINAL X1 OF THE FCD U1-790 TO BE

POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN

CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR

INJURY COULD RESULT.

(30) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows:

(a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-790 (9)

reads less than 10 volts.

(b) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as ON (amber circle

and pump vanes).

(c) After approximately 20 - 30 seconds the multimeter reads more than 110 volts.

NOTE: If the voltage does not increase to more than 110 volts and remain there, then

there is a possible wiring or component failure of the uncommanded on detection

circuitry and troubleshooting is necessary.

1) Monitor the voltage for an additional minute and verify that the voltage does not drop

back below 10 volts at any time.

(31) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows:

(a) At the CAC EPC Bay-1 the multimeter attached to terminal stud 12 of FCD U1-790 (9)

reads more than 110 volts.

(b) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as OFF (white empty

circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(32) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 22 B1-542 FUEL PUMP CONTROL AUX TANK 2 L FWD

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 22 OF 33)

Export Controlled ECCN: 9E991 - BOEING

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(33) At the CAC EPC Bay-1 verify the multimeter attached to terminal stud 12 of FCD U1-790 (9)

reads less than 10 volts.

(34) At the CAC EPC Bay-1 remove the multimeter lead from terminal stud 12 of FCD U1-790 (9).

(35) At the CAC EPC Bay-1 install the terminal shields (14) on FCDs U1-709 (8) and U1-790 (9)

as follow:

(a) Install the terminal shields (14) with two screws (12) each and two lockwashers (13) each.

(36) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows:

(a) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as ON (amber circle

and pump vanes).

(b) On the Fwd Aux Fuel Tank Overhead Panel the ON annunciator light in the L TRANS

switch is illuminated.

NOTE: If the ON annunciator light in the L TRANS switch is not illuminated or the Fwd

Aux Left Pumps are not shown as ON, verify that diode R7-361 is installed

correctly.

(37) On the Fwd Aux Fuel Tank Overhead Panel push the L TRANS switch and verify as follows:

(a) On the FUEL synoptic page both Fwd Aux Left Pumps are shown as OFF (white empty

circle).

(b) On the Fwd Aux Fuel Tank Overhead Panel the ON annunciator light in the L TRANS

switch is not illuminated.

i. Forward Aux Tank Right Pumps (M1-1491 and M1-1493) Test:

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(1) Verify circuit breakers are open and tagged as follow:

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 21 B1-1644 FUEL PUMP CONTROL AUX TANK 1 R FWD

G 22 B1-543 FUEL PUMP CONTROL AUX TANK 2 R FWD

(2) At the CAC EPC Bay-3 remove the terminal shields of the FCDs U1-710 (10) and U1-789

(11) as follow:

(a) Remove the two screws (12) and lockwashers (13) from each FCD terminal shield (14).

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 23 OF 33)

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(b) Remove the terminal shields (14).

(3) At the CAC EPC Bay-3 connect the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-710 (10).

(4) Close circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 21 B1-1644 FUEL PUMP CONTROL AUX TANK 1 R FWD

(5) On the FUEL synoptic page, verify the two Fwd Aux Right Pumps are shown as ON (amber

circle and pump vanes).

(6) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the R TRANS

switch is illuminated.

NOTE: If the ON annunciator light in the R TRANS switch is not illuminated or the Forward

Aux Right Pumps are not shown as ON, then there is a possible wiring or component

failure of the uncommanded on detection circuitry and troubleshooting is necessary.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(7) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 21 B1-1644 FUEL PUMP CONTROL AUX TANK 1 R FWD

(8) On the FUEL synoptic page verify both Fwd Aux Right Pumps are shown as OFF (white empty

circle).

(9) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the R TRANS

switch is not illuminated.

(10) At the CAC EPC Bay-3 remove the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-710 (10).

(11) At the CAC EPC Bay-3 attach the multimeter lead, set to measure AC voltage, to terminal

stud 12 of FCD U1-710 (10) and verify that it reads less than 10 volts.

(12) Close circuit breaker as follows:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 24 OF 33)

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UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 21 B1-1644 FUEL PUMP CONTROL AUX TANK 1 R FWD

(13) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-710 (10)

reads more than 110 volts.

WARNING: THE NEXT STEP WILL CAUSE TERMINAL X1 OF THE FCD U1-710 TO BE

POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN

CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR

INJURY COULD RESULT.

(14) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows:

(a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-710 (10)

reads less than 10 volts.

(b) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as ON (amber circle

and pump vanes).

(c) After approximately 20 - 30 seconds the multimeter reads more than 110 volts.

NOTE: If the voltage does not increase to more than 110 volts and remain there, then

there is a possible wiring or component failure of the uncommanded on detection

circuitry and troubleshooting is necessary.

1) Monitor the voltage for an additional minute and verify that the voltage does not drop

back below 10 volts at any time.

(15) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows:

(a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-710 (10)

reads more than 110 volts.

(b) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as OFF (white empty

circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(16) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 21 B1-1644 FUEL PUMP CONTROL AUX TANK 1 R FWD

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 25 OF 33)

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(17) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-710 (10)

reads less than 10 volts.

(18) At the CAC EPC Bay-3 remove the multimeter lead from terminal stud 12 of FCD U1-710 (10).

(19) At the CAC EPC Bay-3 connect the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-789 (11).

(20) Close circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 22 B1-543 FUEL PUMP CONTROL AUX TANK 2 R FWD

(21) On the FUEL synoptic page, verify the two Fwd Aux Right Pumps are shown as ON (amber

circle and pump vanes).

(22) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the R TRANS

switch is illuminated.

NOTE: If the ON annunciator light in the R TRANS switch is not illuminated or the Fwd Aux

Right Pumps are not shown as ON, then there is a possible wiring or component

failure of the uncommanded on detection circuitry and troubleshooting is necessary.

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(23) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 22 B1-543 FUEL PUMP CONTROL AUX TANK 2 R FWD

(24) On the FUEL synoptic page verify both Fwd Aux Right Pumps are shown as OFF (white empty

circle).

(25) On the Fwd Aux Fuel Tank Overhead Panel, verify the ON annunciator light in the R TRANS

switch is not illuminated.

(26) At the CAC EPC Bay-3 remove the jumper wire from terminal stud 11 to terminal stud 12 of

FCD U1-789 (11).

(27) At the CAC EPC Bay-3 attach the multimeter lead, set to measure AC voltage, to terminal

stud 12 of FCD U1-789 (11) and verify that it reads less than 10 volts.

(28) Close circuit breaker as follows:

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 26 OF 33)

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UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 22 B1-543 FUEL PUMP CONTROL AUX TANK 2 R FWD

(29) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-789 (11)

reads more than 110 volts.

WARNING: THE NEXT STEP WILL CAUSE TERMINAL X1 OF THE FCD U1-789 TO BE

POWERED WITH 115 VAC POWER. PERSONNEL IN THE CAC SHOULD REMAIN

CLEAR OF THIS EXPOSED TERMINAL UNTIL POWER IS SWITCHED OFF OR

INJURY COULD RESULT.

(30) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows:

(a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-789 (11)

reads less than 10 volts.

(b) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as ON (amber circle

and pump vanes).

(c) After approximately 20 - 30 seconds the multimeter reads more than 110 volts.

NOTE: If the voltage does not increase to more than 110 volts and remain there, then

there is a possible wiring or component failure of the uncommanded on detection

circuitry and troubleshooting is necessary.

1) Monitor the voltage for an additional minute and verify that the voltage does not drop

back below 10 volts at any time.

(31) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows:

(a) At the CAC EPC Bay-3 the multimeter attached to terminal stud 12 of FCD U1-789 (11)

reads more than 110 volts.

(b) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as OFF (white empty

circle).

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE

CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY

TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(32) Open circuit breaker as follows:

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 22 B1-543 FUEL PUMP CONTROL AUX TANK 2 R FWD

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 27 OF 33)

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(33) At the CAC EPC Bay-3 verify the multimeter attached to terminal stud 12 of FCD U1-789 (11)

reads less than 10 volts.

(34) At the CAC EPC Bay-3 remove the multimeter lead from terminal stud 12 of FCD U1-789 (11).

(35) At the CAC EPC Bay-3 install the terminal shields (14) on FCDs U1-710 (10) and U1-789 (11)

as follow:

(a) Install the terminal shields (14) with two screws (12) each and two lockwashers (13) each.

(36) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows:

(a) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as ON (amber circle

and pump vanes).

(b) On the Fwd Aux Fuel Tank Overhead Panel the ON annunciator light in the R TRANS

switch is illuminated.

NOTE: If the ON annunciator light in the R TRANS switch is not illuminated or the Fwd

Aux Right Pumps are not shown as ON, verify that diode R7-362 is installed

correctly.

(37) On the Fwd Aux Fuel Tank Overhead Panel push the R TRANS switch and verify as follows:

(a) On the FUEL synoptic page both Fwd Aux Right Pumps are shown as OFF (white empty

circle).

(b) On the Fwd Aux Fuel Tank Overhead Panel the ON annunciator light in the R TRANS

switch is not illuminated.

4. Test close up:

a. Remove safety tags and close circuit breakers as follow:

UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

B 20 B1-1578 FUEL PUMP POWER TAIL TANK L XFR

B 21 B1-394 FUEL PUMP POWER AUX TANK 1 L FWD

B 22 B1-1647 FUEL PUMP POWER AUX TANK 2 L FWD

B 23 B1-1250 FUEL PUMP POWER AUX TANK R UPR

B 24 B1-614 FUEL PUMP POWER TANK 1 FWD

B 25 B1-608 FUEL PUMP POWER TANK 2 FWD

B 26 B1-618 FUEL PUMP POWER TANK 3 XFR

E 20 B1-497 FUEL PUMP CONTROL TAIL TANK L XFR

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 28 OF 33)

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UPPER MAIN, FUEL AC BUS 1

Row Column Number Name

E 21 B1-1645 FUEL PUMP CONTROL AUX TANK 1 L FWD

E 22 B1-542 FUEL PUMP CONTROL AUX TANK 2 L FWD

E 23 B1-1206 FUEL PUMP CONTROL AUX TANK R UPR

E 24 B1-615 FUEL PUMP CONTROL TANK 1 FWD

E 25 B1-609 FUEL PUMP CONTROL TANK 2 FWD

E 26 B1-619 FUEL PUMP CONTROL TANK 3 XFR

UPPER MAIN, FUEL AC BUS 2

Row Column Number Name

C 20 B1-1576 FUEL PUMP POWER TAIL TANK R XFR

C 22 B1-1248 FUEL PUMP POWER AUX TANK L UPR

C 23 B1-1249 FUEL PUMP POWER AUX TANK L LWR

C 24 B1-610 FUEL PUMP POWER TANK 1 XFR

C 25 B1-596 FUEL PUMP POWER TANK 2 R AFT

C 26 B1-620 FUEL PUMP POWER TANK 3 AFT

F 21 B1-496 FUEL PUMP CONTROL TAIL TANK R XFR

F 22 B1-1207 FUEL PUMP CONTROL AUX TANK L UPR

F 23 B1-1209 FUEL PUMP CONTROL AUX TANK L LWR

F 24 B1-611 FUEL PUMP CONTROL TANK 1 XFR

F 25 B1-603 FUEL PUMP CONTROL TANK 2 R AFT

F 26 B1-621 FUEL PUMP CONTROL TANK 3 AFT

UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

D 21 B1-393 FUEL PUMP POWER AUX TANK 1 R FWD

D 22 B1-1646 FUEL PUMP POWER AUX TANK 2 R FWD

D 23 B1-1251 FUEL PUMP POWER AUX TANK R LWR

D 24 B1-612 FUEL PUMP POWER TANK 1 AFT

D 25 B1-756 FUEL PUMP POWER TANK 2 XFR

D 26 B1-616 FUEL PUMP POWER TANK 3 FWD

G 21 B1-1644 FUEL PUMP CONTROL AUX TANK 1 R FWD

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 29 OF 33)

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UPPER MAIN, FUEL AC BUS 3

Row Column Number Name

G 22 B1-543 FUEL PUMP CONTROL AUX TANK 2 R FWD

G 23 B1-1208 FUEL PUMP CONTROL AUX TANK R LWR

G 24 B1-613 FUEL PUMP CONTROL TANK 1 AFT

G 25 B1-757 FUEL PUMP CONTROL TANK 2 XFR

G 26 B1-617 FUEL PUMP CONTROL TANK 3 FWD

b. On the Fuel System Control Panel (FSCP) set the SYSTEM switchlight (17) to AUTO and verify

on the FUEL synoptic page that all Aux and Tail pumps remain OFF.

APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 30 OF 33)

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APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 31 OF 33)

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APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 32 OF 33)

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APPENDIX A: FUNCTIONAL TEST OF THE FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT

(SHEET 33 OF 33)

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APPENDIX B: INPUT SURVEY

(SHEET 1 OF 1)

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