Commercial 

Airplanes MD11

Service Bulletin

ALERT

Number: MD11-28A133

Original Issue: June 05, 2014

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Control Relays with Fault Current

Detectors and Change Fuel Tank Boost/Transfer Pump Wire Termination

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 300-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2014 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

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BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

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

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 26

4. Process Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 37

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 39

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

APPENDIX A: INPUT SURVEY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

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Commercial 

Airplanes MD11

Service Bulletin

ALERT

Summary Number: MD11-28A133

Original Issue: June 05, 2014

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Control Relays with Fault Current

Detectors and Change Fuel Tank Boost/Transfer Pump Wire Termination

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

MD-11 fuel boost/transfer pumps failures have occurred due to electrical ground or phase to phase fault within

the fuel pump electrical interface connector shell, pump motor windings and pump motor assembly lead wires.

These failures have caused arcing damage to the interface connector shell or fuel pump explosion proof

compartment. Investigation by Boeing has determined that during an electrical arcing event the affected Remote

Control Circuit Breaker (RCCB) may not react to the thermal rise from an electrical fault fast enough to prevent

arcing damage. Replacing the fuel boost/transfer pump control relays with Fault Current Detectors (FCD) will

minimize arcing events at the fuel pump electrical interface connector, pump motor windings and pump motor

assembly lead wires that could breach the explosion proof compartment. If not corrected, failure of the connector

or fuel pump motor could result in a breach of the fuel boost/transfer pump interface connector shell or the fuel

pump housing assembly and potentially become a fuel tank ignition source.

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, MD-11 FTD 28-12001, MD-11 FTD 28-13001 and

MD-11 FTD 28-13004 are related to this service bulletin.

ACTION

This service bulletin provides instructions to do as follows:

1. Replaces fuel boost/transfer pump control relays in the Center Accessory Compartment (CAC), Electrical

Power Center (EPC) and Avionics Compartment (AC) forward equipment panel with fuel boost/transfer

pump FCDs.

2. Changes lower auxiliary fuel boost/transfer pump terminal board installation and associated wiring

located in the Main Landing Gear (MLG) right-side wheel-well.

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3. Changes fuel tank boost/transfer pump wire termination.

4. Group 4:

Removes the Forward Aux tank relays and associated wiring.

NOTE: The FCD is intended for use with ONLY airplane Original Equipment Manufacturer (OEM) certified fuel

pumps and fuel pump housings, including OEM pump/housing spare parts and parts repaired per OEM

approved repair instructions.

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 Directives AD 2013-08-23, AD 2002-13-10 and AD

2011-11-05 are 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.

INDUSTRY SUPPORT INFORMATION

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

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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

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

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BLANK PAGE
Commercial 

Airplanes MD11

Service Bulletin

ALERT

Number: MD11-28A133

Original Issue: June 05, 2014

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Control Relays with Fault Current

Detectors and Change Fuel Tank Boost/Transfer Pump Wire Termination

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below.

NOTE: Group 2 airplanes modified to a freighter configuration by Boeing Engineering will become

Group 1 airplanes.

GROUP CONFIGURATION DESCRIPTION

Applicable to MD-11 and MD11F Airplanes with fuel tanks 1, 2, 3,

upper and lower auxiliary, and tail configuration which are affected

by Service Rework Drawings SR11280076-7001, -7002 and

SR11280134-7001, -7002.

1 -

Applicable to operators that have Not accomplished Service Bulletins

MD11-28-132 and MD11-28-146.

1

Applicable to operators that have accomplished Service Bulletin

MD11-28-132 and have Not accomplished Service Bulletin

MD11-28-146.

2

Applicable to operators that have accomplished Service Bulletin

MD11-28-146.

3

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GROUP CONFIGURATION DESCRIPTION

Applicable to MD-11 and MD-11F Airplanes with fuel tanks 1, 2, 3,

upper and lower auxiliary, forward auxiliary, and tail configuration

which are affected by Service Rework Drawing SR11280076-7003,

-7004 and SR11280134-7003, -7004.

2 -

Applicable to operators that have Not accomplished Service Bulletins

MD11-28-132 and MD11-28-146.

1

Applicable to operators that have accomplished Service Bulletin

MD11-28-132 and have Not accomplished Service Bulletin

MD11-28-146.

2

Applicable to operators that have accomplished Service Bulletin

MD11-28-146.

3

Applicable to MD-11 Airplanes with fuel tanks 1, 2, 3, upper, lower

and forward auxiliary, and tail configuration which are affected by

Service Rework Drawing SR11280076-7005, -7006 and

SR11280134-7001, -7002.

3 -

Applicable to operators that have Not accomplished Service Bulletins

MD11-28-132 and MD11-28-146.

1

Applicable to operators that have accomplished Service Bulletin

MD11-28-132 and have Not accomplished Service Bulletin

MD11-28-146.

2

Applicable to operators that have accomplished Service Bulletin

MD11-28-146.

3

Applicable to MD-11 Airplanes with fuel tanks 1, 2, 3, upper and lower

auxiliary, and tail configuration which are affected by Service Rework

Drawing SR11280076-7007, -7008 and SR11280134-7001, -7002.

4 -

Applicable to operators that have Not accomplished Service Bulletins

MD11-28-132 and MD11-28-146.

1

Applicable to operators that have accomplished Service Bulletin

MD11-28-132 and have Not accomplished Service Bulletin

MD11-28-146.

2

Applicable to operators that have accomplished Service Bulletin

MD11-28-146.

3

Airplane Models:

MD-11, MD-11F

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Fuselage Num- Group

ber

447 - 449 1

451 - 459 1

460 - 464 1

466 - 469 1

470 - 479 1

480 - 489 1

491 - 499 1

500 - 509 1

510 4

511 - 513 1

514 4

515 - 517 1

519 1

520 - 529 1

530 - 531 1

532 3

533 - 539 1

540 - 543 1

544 3

545 - 549 1

550 - 552 1

554 - 559 1

560 - 569 1

570 - 579 1

580 - 589 1

590 2

591 - 596 1

597 2

598 - 599 1

600 - 609 1

610 - 619 1

620 - 629 1

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Fuselage Num- Group

ber

630 - 639 1

640 - 646 1

2. Spares Affected

None.

B. Concurrent Requirements

For operators who have not accomplished Service Bulletin MD11-28A113 and MD11-28A138 there

are no concurrent requirements.

For operators who have accomplished Service Bulletin MD11-28A113 and MD11-28A138 the service

bulletin or special product drawing listed below must be done before or at the same time as this service

bulletin:

Group 1, Configuration 1-2; Group 2, Configuration 1-2; Group 3, Configuration 1-2; Group 4,

Configuration 1-2:

Service Bulletin or Spe- Description

cial Product Drawing

Company

Replaces fuel pump housing electrical connector assembly part number 60-84355-1

with part number 60-84351.

The Boeing Company MD11-28A143 Revision 01

Replaces fuel pump housing electrical connector assembly part number 60-84355-1

with part number 60-84351.

The Boeing Company SP11280022

C. Reason

MD-11 fuel boost/transfer pumps failures have occurred due to electrical ground or phase to phase

fault within the fuel pump electrical interface connector shell, pump motor windings and pump motor

assembly lead wires. These failures have caused arcing damage to the interface connector shell or

fuel pump explosion proof compartment. Investigation by Boeing has determined that during an electrical

arcing event the affected Remote Control Circuit Breaker (RCCB) may not react to the thermal rise

from an electrical fault fast enough to prevent arcing damage. Replacing the fuel boost/transfer pump

control relays with Fault Current Detectors (FCD) will minimize arcing events at the fuel pump electrical

interface connector, pump motor windings and pump motor assembly lead wires that could breach the

explosion proof compartment. If not corrected, failure of the connector or fuel pump motor could result

in a breach of the fuel boost/transfer pump interface connector shell or the fuel pump housing assembly

and potentially become a fuel tank ignition source.

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, MD-11 FTD 28-12001, MD-11 FTD 28-13001

and MD-11 FTD 28-13004 are related to this service bulletin.

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D. Description

This service bulletin provides instructions to do as follows:

1. Replaces fuel boost/transfer pump control relays in the Center Accessory Compartment (CAC),

Electrical Power Center (EPC) and Avionics Compartment (AC) forward equipment panel with fuel

boost/transfer pump FCDs.

2. Changes lower auxiliary fuel boost/transfer pump terminal board installation and associated wiring

located in the Main Landing Gear (MLG) right-side wheel-well.

3. Changes fuel tank boost/transfer pump wire termination.

4. Group 4:

Removes the Forward Aux tank relays and associated wiring.

NOTE: The FCD is intended for use with ONLY airplane Original Equipment Manufacturer (OEM)

certified fuel pumps and fuel pump housings, including OEM pump/housing spare parts and

parts repaired per OEM approved repair instructions.

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

Group 1:

Affected Maintenance Zones

Model Zone

112, 131, 132, 141, 142, 144, 311, 515, 518,

541, 615, 618, 641

MD-11, MD-11F

Group 2:

Affected Maintenance Zones

Model Zone

112, 127, 131, 132, 141, 142, 144, 311, 515,

518, 541, 615, 618, 641

MD-11

Group 3:

Affected Maintenance Zones

Model Zone

112, 131, 132, 141, 142, 144, 311, 515, 518,

541, 615, 618, 641

MD-11

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Group 4:

Affected Maintenance Zones

Model Zone

112, 131, 132, 141, 142, 144, 311, 515, 518,

541, 615, 618, 641

MD-11F

E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directives AD 2013-08-23, AD 2002-13-10 and

AD 2011-11-05 are 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 modification

defined in this service bulletin as an Alternative Method of Compliance (AMOC) to the requirements

of paragraph (g), (g)(1) and (h) of AD 2013-08-23 and to the repetitive inspection interval requirement

of paragraph (a) of AD 2002-13-10 and paragraph (j) of AD 2011-11-05 as follows. Accomplishment

of this service bulletin will allow the existing repetitive 18 month inspection interval to be increased to

no later than 24 months and no later than every 24 months thereafter. All provisions of AD 2013-08-23,

AD 2002-13-10 and AD 2011-11-05 that are not specifically referenced in the above statement remain

fully applicable and must be complied with.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

G. Manpower

The table below shows an estimate of the task hours necessary to do this change for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

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Group 1, Configuration 1-2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 3.6 1.8

Replace 1 8.5 8.5

Change 1 4.3 4.3

Test 1 0.5 0.5

Close Access 2 3.6 1.8

TOTAL FOR EACH AIRPLANE 20.5 16.9

Group 1, Configuration 3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 3.6 1.8

Replace 1 8.5 8.5

Change 1 2.6 2.6

Test 1 0.5 0.5

Close Access 2 3.6 1.8

TOTAL FOR EACH AIRPLANE 18.8 15.2

Group 2, Configuration 1-2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 4.6 2.3

Replace 1 9.5 9.5

Change 1 4.6 4.6

Test 1 0.5 0.5

Close Access 2 4.6 2.3

TOTAL FOR EACH AIRPLANE 23.8 19.2

Group 2, Configuration 3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 4.6 2.3

Replace 1 9.5 9.5

Change 1 2.7 2.7

Test 1 0.5 0.5

Close Access 2 4.6 2.3

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Group 2, Configuration 3:

Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR EACH AIRPLANE 21.9 17.3

Group 3, Configuration 1-2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 3.6 1.8

Replace 1 10.5 10.5

Change 1 4.3 4.3

Test 1 0.5 0.5

Close Access 2 3.6 1.8

TOTAL FOR EACH AIRPLANE 22.5 18.9

Group 3, Configuration 3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 3.6 1.8

Replace 1 10.5 10.5

Change 1 2.6 2.6

Test 1 0.5 0.5

Close Access 2 3.6 1.8

TOTAL FOR EACH AIRPLANE 20.8 17.2

Group 4, Configuration 1-2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 3.6 1.8

Replace 1 12.5 12.5

Change 1 4.3 4.3

Test 1 0.5 0.5

Close Access 2 3.6 1.8

TOTAL FOR EACH AIRPLANE 24.5 20.9

Group 4, Configuration 3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 3.6 1.8

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Group 4, Configuration 3:

Task Number of Persons Task Hours Elapsed Hours

Replace 1 12.5 12.5

Change 1 2.6 2.6

Test 1 0.5 0.5

Close Access 2 3.6 1.8

TOTAL FOR EACH AIRPLANE 22.8 19.2

H. Weight and Balance Changes

Group 1, Configuration 1-2:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

MD-11, MD-11F 1,019.6 +7.4 +7,545.0

Group 1, Configuration 3:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

MD-11, MD-11F 1,019.6 +7.2 +7,341.1

Group 2:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

MD-11 1,030.0 +8.0 +8,240.0

Group 3, Configuration 1-2:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

MD-11 1,038.4 +9.0 +9,345.6

Group 3, Configuration 3:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

MD-11 1,038.4 +8.8 +9,137.9

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Group 4, Configuration 1-2:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

MD-11F 1,019.6 +4.5 +4,588.2

Group 4, Configuration 3:

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

Airplane (Inches)

MD-11F 1,019.6 +4.3 +4,384.3

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:

NOTE: Retain removed relay % TIME OPR for each BUS/CHAP/ITEM shown below (for

example BUS 1E, CHAP 280, ITEM 5006, U1-701 shall retain the % TIME OPR for

R2-101).

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1206)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

R Fuel Pump Upper Aux

HDGE-X3F-001

ITEM

5006

U1-

701

CHAP

280

BUS

1E

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1207)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

L Fuel Pump Upper Aux

HDGE-X3F-001

ITEM

5004

U1-

702

CHAP

280

BUS

2F

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1208)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

R Fuel Pump Lower Aux

HDGE-X3F-001

ITEM

5005

U1-

703

CHAP

280

BUS

3G

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1209)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

L Fuel Pump Lower Aux

HDGE-X3F-001

ITEM

5005

U1-

704

CHAP

280

BUS

2F

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-615)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

FWD Fuel Pump No 1

Tank

HDGE-X3F-001

ITEM

5003

U1-

751

CHAP

280

BUS

1E

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-613)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

AFT Fuel Pump No 1

Tank

HDGE-X3F-001

ITEM

5002

U1-

752

CHAP

280

BUS

3G

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-611)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Transfer Fuel Pump

No.1

HDGE-X3F-001

ITEM

5001

U1-

753

CHAP

280

BUS

2F

UNITS

%OPR

1

100

E/NE/M

PHASE

E

B

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-609)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

FWD Fuel Pump No 2

Tank

HDGE-X3F-001

ITEM

5004

U1-

754

CHAP

280

BUS

1E

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-757)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Transfer Fuel Pump

No.2

HDGE-X3F-001

ITEM

5003

U1-

755

CHAP

280

BUS

3G

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115 VAC

Emer

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1572)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

L AFT Fuel Pump No. 2

Tank

HDGE-X3F-001

ITEM

5001

U1-

756

CHAP

280

BUS

3A

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ALERT ALERT
UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-603)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

R AFT Fuel Pump No.

2 Tank

HDGE-X3F-001

ITEM

5002

U1-

757

CHAP

280

BUS

2F

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-617)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

FWD Fuel Pump No 3

Tank

HDGE-X3F-001

ITEM

5004

U1-

758

CHAP

280

BUS

3G

UNITS

%OPR

1

100

E/NE/M

PHASE

E

B

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-621)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

AFT Fuel Pump No 3

Tank

HDGE-X3F-001

ITEM

5003

U1-

759

CHAP

280

BUS

2F

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-619)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Transfer Fuel Pump

No.3

HDGE-X3F-001

ITEM

5005

U1-

760

CHAP

280

BUS

1E

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115 VAC

Emer

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1577)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tail Tank Alternate

Pump

HDGE-X3F-001

ITEM

5002

U1-

850

CHAP

280

BUS

3A

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-497)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tail Tank L Transfer

Pump

HDGE-X3F-001

ITEM

5002

U1-

851

CHAP

280

BUS

1E

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-496)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

Tail Tank R Transfer

Pump

HDGE-X3F-001

ITEM

5006

U1-

852

CHAP

280

BUS

2F

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ALERT ALERT
Group 2-3:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1645)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

L Fwd Aux Tank Pump

1

HDGE-X3F-001

ITEM

5003

U1-

709

CHAP

280

BUS

1E

Group 2-3:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-

1644)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

R Fwd Aux Tank Pump

1

HDGE-X3F-001

ITEM

5002

U1-

710

CHAP

280

BUS

3G

Group 3:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-542)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

L FWD Aux Tank Pump

2

HDGE-X3F-001

ITEM

5003

U1-

790

CHAP

280

BUS

1E

Group 3:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

6

NOTES

(B1-543)

SUPPLIER

Leach International

EQUIPMENT NAME

PART NUMBER

R FWD Aux Tank Pump

2

HDGE-X3F-001

ITEM

5002

U1-

789

CHAP

280

BUS

3G

b. Delete AC loads by amounts shown below:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1206)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

R Fuel Pump Control

Upper Aux Tank

DVR-7VC

ITEM

5006

R2-

101

CHAP

280

BUS

1E

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1207)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

Upper Aux Left Tank

DVR-7VC

ITEM

5004

R2-

102

CHAP

280

BUS

2F

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1208)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

R Fuel Pump Control

Lower Aux Tank

DVR-7VC

ITEM

5005

R2-

103

CHAP

280

BUS

3G

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1209)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

Lower Aux Left Tank

DVR-7VC

ITEM

5005

R2-

104

CHAP

280

BUS

2F

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-615)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

FWD Fuel Pump -1

DVR-7VC

ITEM

5003

R2-51

CHAP

280

BUS

1E

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-613)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

L Fuel Pump Control

Upper Aux Tank

DVR-7VC

ITEM

5002

R2-52

CHAP

280

BUS

3G

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-611)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

Transfer Pump Control

DVR-7VC

ITEM

5001

R2-53

CHAP

280

BUS

2F

UNITS

%OPR

1

100

E/NE/M

PHASE

E

B

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-609)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

FWD Fuel Pump -2

DVR-7VC

ITEM

5004

R2-54

CHAP

280

BUS

1E

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-757)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

XFR Fuel Pump -2

DVR-7VC

ITEM

5003

R2-55

CHAP

280

BUS

3G

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1572)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

L AFT Pump - 2

DVR-7VC

ITEM

5001

R2-56

CHAP

280

BUS

3A

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-603)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

R AFT Pump - 2

DVR-7VC

ITEM

5002

R2-57

CHAP

280

BUS

2F

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-617)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

Fuel Pump -3

DVR-7VC

ITEM

5004

R2-58

CHAP

280

BUS

3G

UNITS

%OPR

1

100

E/NE/M

PHASE

E

B

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-621)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

AFT Fuel Pump -3

DVR-7VC

ITEM

5003

R2-59

CHAP

280

BUS

2F

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-619)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

Fuel XFR Pump -3

DVR-7VC

ITEM

5005

R2-60

CHAP

280

BUS

1E

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115 VAC

Emer

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1577)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

Tail Tank Alt Pump

DVR-7VC

ITEM

5002

R2-

250

CHAP

280

BUS

3A

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115 VAC

Emer

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-497)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

Tail Tank Alt Pump

DVR-7VC

ITEM

5002

R2-

251

CHAP

280

BUS

1E

UNITS

%OPR

1

100

E/NE/M

PHASE

E

A

VAC

PF

115

VAC-2

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-496)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

Tail Tank R Pump

DVR-7VC

ITEM

5006

R2-

252

CHAP

280

BUS

2F

Group 2-3:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1645)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

L Fuel Pump Control

Fwd Aux Tank 1

DVR-7VC

ITEM

5003

R2-

109

CHAP

280

BUS

1E

Group 2-3:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1644)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

R Fuel Pump Control

Fwd Aux Tank 1

DVR-7VC

ITEM

5002

R2-

110

CHAP

280

BUS

3G

Group 3:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-542)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

L Fuel Pump Control

Fwd Aux Tank 2

DVR-7VC

ITEM

5003

R2-90

CHAP

280

BUS

1E

Group 3:

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-543)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

R Fuel Pump Control

Fwd Aux Tank 2

DVR-7VC

ITEM

5002

R2-89

CHAP

280

BUS

3G

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
Group 4:

Remove and not replace.

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1645)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

L Fuel Pump Control

Fwd Aux Tank 1

DVR-7VC

ITEM

5003

R2-

109

CHAP

280

BUS

1E

Group 4:

Remove and not replace.

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-

1644)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

R Fuel Pump Control

Fwd Aux Tank 1

DVR-7VC

ITEM

5002

R2-

110

CHAP

280

BUS

3G

Group 4:

Remove and not replace.

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-1

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-542)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

L Fuel Pump Control

Fwd Aux Tank 2

DVR-7VC

ITEM

5003

R2-90

CHAP

280

BUS

1E

Group 4:

Remove and not replace.

UNITS

%OPR

1

100

E/NE/M

PHASE

E

C

VAC

PF

115

VAC-3

0.95

UNIT

LOAD

(W)

5

NOTES

(B1-543)

SUPPLIER

Hartman

EQUIPMENT NAME

PART NUMBER

R Fuel Pump Control

Fwd Aux Tank 2

DVR-7VC

ITEM

5002

R2-89

CHAP

280

BUS

3G

J. References

1. Existing Data:

a. Boeing Service Bulletin MD11-28A113, MD11-28A138 and MD11-28A143 Revision 01.

b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2002-13-10, 2011-11-05

and 2013-08-23.

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
c. MD11 Aircraft Maintenance Manual (AMM) 06-31-02, 06-31-03, 06-31-12, 06-31-13, 06-31-27,

06-37-00, 28-00-00, 28-22-01, 28-22-10, 28-22-12 and 28-22-13.

d. MD-11 Fleet Team Digest (FTD) 28-03006, 28-12001, 28-13001 and 28-13004.

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

f. Special Product Drawing SP11280022.

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

h. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-13, 20-00-16, 20-10-01,

20-10-03, 20-20-03, 20-31-01, and 20-50-01.

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 Boulevard

Seal Beach, California 90740 USA

Phone: (562) 797-1717

Fax: (562) 797-3783

E-mail: lbd.dataservicesmanagement@boeing.com

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

bulletin submit a data request to:

Data and Services Management

MS D800-0019

3855 Lakewood Boulevard

Long Beach, California 90846

Phone: (562) 593-6996

Fax: (562) 593-2001

E-mail: dse.boecom@boeing.com

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

ELECTRICAL INSTALLATION - FUEL AEO - E

PUMP FAULT CURRENT DETECTOR

SR11280076

DWG D -

WIRE INSTALLATION - ELIMINATE CIR- AEO - H

CUIT GROUND FOR FUEL PUMPS

SR11280134

DWG G -

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

None.

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ALERT ALERT
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

Fault Isolation Manual 28-14, 28-22, 28-23

Illustrated Parts Catalog 28-22

MDC-02K1003 (ALI 28-1, CDCCL 28-

10)

Special Compliance Item Report

System Schematic Manual 28-22

Wiring Diagram Manual 28-22

2. Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

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

L. Interchangeability and Intermixability of Parts

Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability

information.

NOTE: This service bulletin replaces existing fuel pump control relays with FCDs. After accomplishment

of this service bulletin airplanes cannot revert to the previously installed non-FCD fuel pump

control relays.

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

Paragraph 2.D., Parts Necessary to Change Spares. Operators are encouraged to share schedule

requirements with Boeing for incorporation of the service bulletin. The kits/parts are subject to the terms

and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States

Dollars. Terms: Net 30 days.

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

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

2. Fax to (206) 662-7145

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

SB11280133-3 Service Kit 150 $83,732.00

SB11280133-5 Service Kit 150 $92,615.00

SB11280133-7 Service Kit 150 $101,151.00

SB11280133-9 Service Kit 150 $79,752.00

SB11280133-11 Service Kit 150 $88,631.00

SB11280133-13 Service Kit 150 $97,171.00

Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to

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

B. Industry Support Information

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

C. Parts Necessary for Each Airplane

1. Kits/Parts

Group 1, Configuration 1-2; Group 4, Configuration 1-2:

Kit SB11280133-3

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 6 SCREW (a)

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ALERT ALERT
Group 1, Configuration 1-2; Group 4, Configuration 1-2:

Kit SB11280133-3

Part Number QTY Name Notes

3D0005-08-24 2 SCREW (a)

3D0005-08-28 12 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 68 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

5D0086-25 14 TERMINAL LUG 765 (a)

ABN7377-600 1 BRACKET ASSEMBLY

CYW20 3 END CAP

HDGE-X3F-001 17 FAULT CURRENT DTCTR

MS18029-6S7 1 COVER ASSEMBLY

MS20470AD3-3D 32 RIVET

MS20470AD4-7D 7 RIVET

MS27212-6-7 1 TERM BOARD ASSEMBLY

MS35338-42 13 LOCKWASHER

MS35338-43 2 LOCKWASHER

MS35649-282 13 NUT

NAS1149F0332P 2 WASHER

NAS1149FN816P 81 WASHER

NAS1252-8L 50 WASHER

NAS1329S08KB75 2 RIVNUT

NAS1474A08 16 NUTPLATE

NAS1801-3-10 2 SCREW

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 6 SPACER

NAS43DD3-80FC 16 SPACER

NAS620-4L 4 WASHER

NAS8200U7 4 SCREW

SR11280076-101 1 WIRE KIT (b)

SR11280076-102 1 WIRE KIT (b)

SR11280076-103 1 WIRE KIT (b)

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ALERT ALERT
Group 1, Configuration 1-2; Group 4, Configuration 1-2:

Kit SB11280133-3

Part Number QTY Name Notes

SR11280076-104 1 WIRE KIT (b)

SR11280134-3 1 BRACKET ASSEMBLY

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

(b) Refer to Wire Kit Table.

Group 2, Configuration 1-2:

Kit SB11280133-5

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 6 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-24 2 SCREW (a)

3D0005-08-28 12 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 76 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

5D0086-25 14 TERMINAL LUG 765 (a)

ABN7377-600 1 BRACKET ASSEMBLY

CYW20 5 END CAP

HDGE-X3F-001 19 FAULT CURRENT DTCTR

MS18029-6S7 1 COVER ASSEMBLY

MS20470AD3-3D 32 RIVET

MS20470AD4-7D 7 RIVET

MS27212-6-7 1 TERM BOARD ASSEMBLY

MS35338-42 13 LOCKWASHER

MS35338-43 2 LOCKWASHER

MS35649-282 13 NUT

NAS1149F0332P 2 WASHER

NAS1149FN816P 89 WASHER

NAS1252-8L 52 WASHER

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ALERT ALERT
Group 2, Configuration 1-2:

Kit SB11280133-5

Part Number QTY Name Notes

NAS1329S08KB75 2 RIVNUT

NAS1474A08 16 NUTPLATE

NAS1801-3-10 2 SCREW

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 16 SPACER

NAS620-4L 4 WASHER

NAS8200U7 4 SCREW

SR11280076-101 1 WIRE KIT (b)

SR11280076-102 1 WIRE KIT (b)

SR11280076-103 1 WIRE KIT (b)

SR11280076-105 1 WIRE KIT (b)

SR11280134-3 1 BRACKET ASSEMBLY

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

(b) Refer to Wire Kit Table.

Group 3, Configuration 1-2:

Kit SB11280133-7

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 6 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-24 2 SCREW (a)

3D0005-08-28 12 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 84 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

5D0086-25 14 TERMINAL LUG 765 (a)

ABN7377-600 1 BRACKET ASSEMBLY

CYW20 3 END CAP

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ALERT ALERT
Group 3, Configuration 1-2:

Kit SB11280133-7

Part Number QTY Name Notes

HDGE-X3F-001 21 FAULT CURRENT DTCTR

MS18029-6S7 1 COVER ASSEMBLY

MS20470AD3-3D 32 RIVET

MS20470AD4-7D 7 RIVET

MS27212-6-7 1 TERM BOARD ASSEMBLY

MS35338-42 13 LOCKWASHER

MS35338-43 2 LOCKWASHER

MS35649-282 13 NUT

NAS1149F0332P 2 WASHER

NAS1149FN816P 97 WASHER

NAS1252-8L 52 WASHER

NAS1329S08KB75 2 RIVNUT

NAS1474A08 16 NUTPLATE

NAS1801-3-10 2 SCREW

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 16 SPACER

NAS620-4L 4 WASHER

NAS8200U7 4 SCREW

SR11280076-101 1 WIRE KIT (b)

SR11280076-102 1 WIRE KIT (b)

SR11280076-103 1 WIRE KIT (b)

SR11280076-104 1 WIRE KIT (b)

SR11280134-3 1 BRACKET ASSEMBLY

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

(b) Refer to Wire Kit Table.

Group 1, 4, Configuration 3:

Kit SB11280133-9

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

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ALERT ALERT
Group 1, 4, Configuration 3:

Kit SB11280133-9

Part Number QTY Name Notes

3D0005-08-20 6 SCREW (a)

3D0005-08-24 2 SCREW (a)

3D0005-08-28 12 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 68 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

HDGE-X3F-001 17 FAULT CURRENT DTCTR

MS20470AD3-3D 32 RIVET

NAS1149FN816P 68 WASHER

NAS1252-8L 50 WASHER

NAS1329S08KB75 2 RIVNUT

NAS1474A08 16 NUTPLATE

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 6 SPACER

NAS43DD3-80FC 16 SPACER

SR11280076-101 1 WIRE KIT (b)

SR11280076-102 1 WIRE KIT (b)

SR11280076-103 1 WIRE KIT (b)

SR11280076-104 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

Group 2, Configuration 3:

Kit SB11280133-11

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 6 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-24 2 SCREW (a)

3D0005-08-28 12 SCREW (a)

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ALERT ALERT
Group 2, Configuration 3:

Kit SB11280133-11

Part Number QTY Name Notes

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 76 SCREW (a)

5D0061-2 2 TIE MOUNT (a)

HDGE-X3F-001 19 FAULT CURRENT DTCTR

MS20470AD3-3D 32 RIVET

NAS1149FN816P 76 WASHER

NAS1252-8L 52 WASHER

NAS1329S08KB75 2 RIVNUT

NAS1474A08 16 NUTPLATE

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 16 SPACER

SR11280076-101 1 WIRE KIT (b)

SR11280076-102 1 WIRE KIT (b)

SR11280076-103 1 WIRE KIT (b)

SR11280076-105 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

Group 3, Configuration 3:

Kit SB11280133-13

Part Number QTY Name Notes

3D0005-08-18 2 SCREW (a)

3D0005-08-20 6 SCREW (a)

3D0005-08-22 1 SCREW (a)

3D0005-08-24 2 SCREW (a)

3D0005-08-28 12 SCREW (a)

3D0005-08-30 2 SCREW (a)

3D0005-08-32 2 SCREW (a)

3D0005-08-8 84 SCREW (a)

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ALERT ALERT
Group 3, Configuration 3:

Kit SB11280133-13

Part Number QTY Name Notes

5D0061-2 2 TIE MOUNT (a)

HDGE-X3F-001 21 FAULT CURRENT DTCTR

MS20470AD3-3D 32 RIVET

NAS1149FN816P 84 WASHER

NAS1252-8L 52 WASHER

NAS1329S08KB75 2 RIVNUT

NAS1474A08 16 NUTPLATE

NAS43DD3-32FC 2 SPACER

NAS43DD3-64FC 7 SPACER

NAS43DD3-80FC 16 SPACER

SR11280076-101 1 WIRE KIT (b)

SR11280076-102 1 WIRE KIT (b)

SR11280076-103 1 WIRE KIT (b)

SR11280076-104 1 WIRE KIT (b)

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

(b) Refer to Wire Kit Table.

Group 1, 3-4:

Wire Kit Table

Part Number QTY SR11280076 Name Notes

-101 -102 -103 -104

D2426-1C-16NM 64 FT 99 FT 98 FT 49 FT WIRE CODE 801 (a)

D2426-1C-20NM 21 FT 12 FT WIRE CODE 801 (a)

D2426-1C-22NM 13 FT 15 FT WIRE CODE 801 (a)

5D0086-26 9 9 9 9 TERM LUG 766 (b)

5D0086-5 2 2 TERMINAL LUG 761 (b)

5D0086-6 1 1 TERMINAL LUG 762 (b)

5D0086-3 1 1 TERMINAL LUG 878 (b)

5D0086-2 2 2 TERMINAL LUG 877 (b)

DC39-16S 3 3 3 3 SOCKET T/C 1123

DC39-20S 1 1 1 1 SOCKET T/C 1124

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ALERT ALERT
Group 1, 3-4:

Wire Kit Table

Part Number QTY SR11280076 Name Notes

-101 -102 -103 -104

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

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

Group 2:

Wire Kit Table

Part Number QTY SR11280076 Name Notes

-101 -102 -103 -105

D2426-1C-16NM 64 FT 99 FT 98 FT 49 FT WIRE CODE 801 (a)

D2426-1C-20NM 21 FT 29 FT WIRE CODE 801 (a)

D2426-1C-22NM 13 FT 15 FT WIRE CODE 801 (a)

5D0086-26 9 9 9 9 TERM LUG 766 (b)

5D0086-5 2 4 TERMINAL LUG 761 (b)

5D0086-6 1 1 TERMINAL LUG 762 (b)

5D0086-3 1 1 TERMINAL LUG 878 (b)

5D0086-2 2 2 TERMINAL LUG 877 (b)

DC39-16S 3 3 3 3 SOCKET T/C 1123

DC39-20S 1 1 1 3 SOCKET T/C 1124

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

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

2. Parts and Materials Supplied by the Operator

Part Number / Specifica- QTY Name Notes

tion

18XTZ, 23XTZ 1 ROLL STRING TIE (a)

(DMS 2089)

or

Equivalent

COATING CHEMICAL FILM, (b)

LIQUID

Alodine 1200S As Required

(DPM 1453-5)

or

Equivalent

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ALERT ALERT
Part Number / Specifica- QTY Name Notes

tion

515X347 Base with 4 Oz PRIMER, FR (c)

910X527 Catalyst

(DMS 1786)

or

Equivalent

ENAMEL, HIGH SOLIDS (d)

EPOXY TOPCOAT, GLOSS

WHITE

446-21-Ser Base with 530 1 Oz

Activator

(DMS 2433)

or

Equivalent

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

Pennsylvania 19464, CAGE: 82110

(b) Can be purchased from: Henkel Corporation, 32100 Stephenson Highway, Madison

Heights, Michigan 48071, CAGE: 1N6B3

(c) Can be purchased from: PRC-Desoto International, Incorporated, 11601 United Street,

Mojave, California 93501, CAGE: 85570

(d) Can be purchased from: Akzo Nobel Aerospace Coatings, Incorporated, 1 East Water

Street, Waukegan, Illinois 60085, CAGE: 91342

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

Group 1-3:

None.

Group 4:

Existing Part Number Name QTY Notes

5D0163-1 Relay 4 (a)

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

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

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ALERT ALERT
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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ALERT ALERT

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 Structural Repair Manual (SRM) Chapter 51, then a fastener of

the same specification, or an approved substitute, with a length which meets the

installation standards given in SRM Chapter 51 may be used. In addition, washers

may be installed for fastener grip length in accordance with SRM Chapter 51. Refer

to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation

in this service bulletin.

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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ALERT ALERT
SWPM 20-00-03 Identification of Electrical Wire - Commercial

SWPM 20-00-09 General Maintenance Practices - Electrical

SWPM 20-00-13 Electrical Wire Codes

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

SWPM 20-10-01 Wiring Installation - Maintenance Practices

SWPM 20-10-03 Wire Splicing - Maintenance Practices

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

Amphenol Series 48 Electrical Connectors - Maintenance

Practices

SWPM 20-31-01

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

SR11280076 3, 3.1, 3.2, 3.3, 3.4

SR11280134 3, 3.1, 3.2

15. The FCD is intended for use with ONLY airplane Original Equipment Manufacturer

(OEM) certified fuel pumps and fuel pump housings, including OEM pump/housing

spare parts and parts repaired per OEM approved repair instructions.

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
B. WORK INSTRUCTIONS

Group 1, Configuration 1-2:

1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Equipment Compartment MD11 AMM 06-31-02

112CZ Forward Equipment Panel MD11 AMM 06-31-03

131AB Center Accessory Compartment (CAC) MD11 AMM 06-31-13

131AZ Electrical Power Center (EPC) components (Bay 1) MD11 AMM 06-31-12

131BZ EPC components (Bay 2)

132AZ EPC components (Bay 3)

741AR Main Landing Gear (MLG) door, right-side MD11 AMM 06-37-00

3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM

28-22-13 as an accepted procedure.

Location Service Rework Drawing SR11280076 Sheets

Generator 1 EPC equipment panel 7, 8, 9

Upper EPC equipment panel 7, 8, 10

Generator 3 EPC equipment panel 7, 8, 11

AC forward equipment panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076

sheets 25 and 26.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR11280076 Sheets

Generator 1 EPC equipment panel 6.14, 6.18, 6.22, 6.29, 6.38, 6.42, 7, 8, 9, 13

Generator 2 EPC equipment panel 6.17, 6.27, 6.28, 6.42, 7, 8, 9, 14, 17, 18, 19

Generator 3 EPC equipment panel 6.16, 6.19, 6.20, 6.23, 6.26, 6.42, 7, 8, 11, 15

AC forward equipment panel 6.24, 6.37, 6.42, 7, 8.1, 12, 16

Upper EPC equipment panel 6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1

CAC 7, 8, 20, 21, 22, 23, 24

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in steps 7 and

8 below. Refer to MD11 AMM 28-22-10 as an accepted procedure.

7. Change terminal board installation and fuel boost/transfer pump wire termination in accordance

with the table that follows:

Service Rework Drawing SR11280134

Sheets

Equipment Item

Numbers

Location

MLG wheel well, right-side S3-804, S3-805 8.4, 10, 11, 12, 13, 15, 303.201

8. Change fuel boost/transfer pump wire termination in accordance with the table that follows:

Service Rework Drawing

SR11280134 Sheets

Equipment Item NumbersLocation

Center and lower wing fuel S3-802, S3-803 8.4, 10, 14, 303.201

tanks

Wing trailing edge, right-side S3-373, S3-375, S3-376 8.2, 8.3, 10, 16, 304.201

Wing leading edge, right-side S3-374, S3-377 8.2, 8.3, 10, 17, 18, 304.201

Wing trailing edge, left-side S3-369, S3-370, S3-372 8.1, 8.2, 10, 19, 304.201

Wing leading edge, left-side S3-368, S3-371 8.1, 8.2, 10, 20, 21, 304.201

Tail fuel tank, front spar rear S3-755, S3-764, S3-765 8.6, 10, 23, 305.201

horizontal

9. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.

10. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.

11. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.

12. Close access.

13. Put the airplane back to a serviceable condition.

Group 1, Configuration 3:

1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Equipment Compartment MD11 AMM 06-31-02

112CZ Forward Equipment Panel MD11 AMM 06-31-03

131AB Center Accessory Compartment (CAC) MD11 AMM 06-31-13

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
Door Number Location Refer to

131AZ Electrical Power Center (EPC) components (Bay 1) MD11 AMM 06-31-12

131BZ EPC components (Bay 2)

132AZ EPC components (Bay 3)

741AR Main Landing Gear (MLG) door, right-side MD11 AMM 06-37-00

3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM

28-22-13 as an accepted procedure.

Location Service Rework Drawing SR11280076 Sheets

Generator 1 EPC equipment panel 7, 8, 9

Upper EPC equipment panel 7, 8, 10

Generator 3 EPC equipment panel 7, 8, 11

AC forward equipment panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076

sheets 25 and 26.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR11280076 Sheets

Generator 1 EPC equipment panel 6.14, 6.18, 6.22, 6.29, 6.38, 6.42, 7, 8, 9, 13

Generator 2 EPC equipment panel 6.17, 6.27, 6.28, 6.42, 7, 8, 9, 14, 17, 18, 19

Generator 3 EPC equipment panel 6.16, 6.19, 6.20, 6.23, 6.26, 6.42, 7, 8, 11, 15

AC forward equipment panel 6.24, 6.37, 6.42, 7, 8.1, 12, 16

Upper EPC equipment panel 6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1

CAC 7, 8, 20, 21, 22, 23, 24

6. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.

7. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.

8. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.

9. Close access.

10. Put the airplane back to a serviceable condition.

Group 2, Configuration 1-2:

1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted

procedure.

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) MD11 AMM 06-31-02

112CZ Forward Equipment Panel MD11 AMM 06-31-03

131AB Center Accessory Compartment (CAC) MD11 AMM 06-31-13

131AZ Electrical Power Center (EPC) components (Bay 1) MD11 AMM 06-31-12

131BZ EPC components (Bay 2)

132AZ EPC components (Bay 3)

741AR Main Landing Gear (MLG) door, right-side MD11 AMM 06-37-00

127RA Forward Auxiliary Tank Structure MD11 AMM 06-31-27

127SA

127TA

127UA

3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM

28-22-13 as an accepted procedure.

Location Service Rework Drawing SR11280076 Sheets

Generator 1 EPC equipment panel 7, 8, 9, 9.2

Upper EPC equipment panel 7, 8, 10

Generator 3 EPC equipment panel 7, 8, 11.1

AC forward equipment panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076

sheets 25 and 26.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR11280076 Sheets

6.14, 6.18, 6.22, 6.29, 6.30, 6.39, 6.42, 7, 8, 9,

9.2, 13, 13.2

Generator 1 EPC equipment panel

Generator 2 EPC equipment panel 6.17, 6.27, 6.28, 6.42, 7, 8, 9, 14, 17, 18, 19

6.16, 6.19, 6.20, 6.23, 6.26, 6.32, 6.42, 7, 8, 11.1,

15.1

Generator 3 EPC equipment panel

AC forward equipment panel 6.24, 6.37, 6.42, 7, 8.1, 12, 16

Upper EPC equipment panel 6.15, 6.21, 6.25, 6.41, 6.42, 7, 8, 10, 14.1

CAC 7, 8, 20, 21, 22, 23, 24

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in steps 7 and

8 below. Refer to MD11 AMM 28-22-10 as an accepted procedure.

7. Change terminal board installation and fuel boost/transfer pump wire termination in accordance

with the table that follows:

Service Rework Drawing SR11280134

Sheets

Equipment Item

Numbers

Location

MLG wheel well, right-side S3-804, S3-805 8.4, 10, 11, 12, 13, 15, 303.201

8. Change fuel boost/transfer pump wire termination in accordance with the table that follows:

Service Rework

Drawing SR11280134

Sheets

Connector Receptacle Item NumberEquipment Item

Numbers

Location

Center and lower wing S3-802, S3-803 - 8.4, 10, 14, 303.201

fuel tanks

8.2, 8.3, 10, 16,

304.201

S3-373, S3-375, S3- -

376

Wing trailing edge,

right-side

8.2, 8.3, 10, 17, 18,

304.201

Wing leading edge, S3-374, S3-377 -

right-side

8.1, 8.2, 10, 19,

304.201

S3-369, S3-370, S3- -

372

Wing trailing edge, leftside

8.1, 8.2, 10, 20, 21,

304.201

Wing leading edge, left- S3-368, S3-371 -

side

8.5, 10, 22, 301.201,

302.201

Forward auxiliary fuel - R5-9664, R5-9665

tank

S3-755, S3-764, S3- - 8.6, 10, 23, 305.201

765

Tail fuel tank, front spar

rear horizontal

9. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.

10. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.

11. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.

12. Close access.

13. Put the airplane back to a serviceable condition.

Group 2, Configuration 3:

1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

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ALERT ALERT
Door Number Location Refer to

112AB Avionics Compartment (AC) MD11 AMM 06-31-02

112CZ Forward Equipment Panel MD11 AMM 06-31-03

131AB Center Accessory Compartment (CAC) MD11 AMM 06-31-13

131AZ Electrical Power Center (EPC) components (Bay 1) MD11 AMM 06-31-12

131BZ EPC components (Bay 2)

132AZ EPC components (Bay 3)

741AR Main Landing Gear (MLG) door, right-side MD11 AMM 06-37-00

127RA Forward Auxiliary Tank Structure MD11 AMM 06-31-27

127SA

127TA

127UA

3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM

28-22-13 as an accepted procedure.

Location Service Rework Drawing SR11280076 Sheets

Generator 1 EPC equipment panel 7, 8, 9, 9.2

Upper EPC equipment panel 7, 8, 10

Generator 3 EPC equipment panel 7, 8, 11.1

AC forward equipment panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076

sheets 25 and 26.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR11280076 Sheets

6.14, 6.18, 6.22, 6.29, 6.30, 6.39, 6.42, 7, 8, 9,

9.2, 13, 13.2

Generator 1 EPC equipment panel

Generator 2 EPC equipment panel 6.17, 6.27, 6.28, 6.42, 7, 8, 9, 14, 17, 18, 19

6.16, 6.19, 6.20, 6.23, 6.26, 6.32, 6.42, 7, 8, 11.1,

15.1

Generator 3 EPC equipment panel

AC forward equipment panel 6.24, 6.37, 6.42, 7, 8.1, 12, 16

Upper EPC equipment panel 6.15, 6.21, 6.25, 6.41, 6.42, 7, 8, 10, 14.1

CAC 7, 8, 20, 21, 22, 23, 24

6. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.

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ALERT ALERT
7. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.

8. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.

9. Close access.

10. Put the airplane back to a serviceable condition.

Group 3, Configuration 1-2:

1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) MD11 AMM 06-31-02

112CZ Forward Equipment Panel MD11 AMM 06-31-03

131AB Center Accessory Compartment (CAC) MD11 AMM 06-31-13

131AZ Electrical Power Center (EPC) components (Bay 1) MD11 AMM 06-31-12

131BZ EPC components (Bay 2)

132AZ EPC components (Bay 3)

741AR Main Landing Gear (MLG) door, right-side MD11 AMM 06-37-00

3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM

28-22-13 as an accepted procedure.

Location Service Rework Drawing SR11280076 Sheets

Generator 1 EPC equipment panel 7, 8, 9.1, 9.2

Upper EPC equipment panel 7, 8, 10

Generator 3 EPC equipment panel 7, 8, 11.2

AC forward equipment panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076

sheets 25 and 26.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR11280076 Sheets

6.14, 6.18, 6.22, 6.29, 6.31, 6.36, 6.38, 6.42, 7,

8, 9.1, 9.2, 13.1, 13.2

Generator 1 EPC equipment panel

Generator 2 EPC equipment panel 6.17, 6.27, 6.28, 6.42, 7, 8, 9.1, 14, 17, 18, 19

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Location Service Rework Drawing SR11280076 Sheets

6.16, 6.19, 6.20, 6.23, 6.26, 6.33, 6.35, 6.42, 7,

8, 11.2, 15.2

Generator 3 EPC equipment panel

AC forward equipment panel 6.24, 6.37, 6.42, 7, 8.1, 12, 16

Upper EPC equipment panel 6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1

CAC 7, 8, 20, 21, 22, 23, 24

6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in steps 7 and

8 below. Refer to MD11 AMM 28-22-10 as an accepted procedure.

7. Change terminal board installation and fuel boost/transfer pump wire termination in accordance

with the table that follows:

Service Rework Drawing SR11280134

Sheets

Equipment Item

Numbers

Location

MLG wheel well, right-side S3-804, S3-805 8.4, 10, 11, 12, 13, 15, 303.201

8. Change fuel boost/transfer pump wire termination in accordance with the table that follows:

Service Rework Drawing

SR11280134 Sheets

Equipment Item NumbersLocation

Center and lower wing fuel S3-802, S3-803 8.4, 10, 14, 303.201

tanks

Wing trailing edge, right-side S3-373, S3-375, S3-376 8.2, 8.3, 10, 16, 304.201

Wing leading edge, right-side S3-374, S3-377 8.2, 8.3, 10, 17, 18, 304.201

Wing trailing edge, left-side S3-369, S3-370, S3-372 8.1, 8.2, 10, 19, 304.201

Wing leading edge, left-side S3-368, S3-371 8.1, 8.2, 10, 20, 21, 304.201

Tail fuel tank, front spar rear S3-755, S3-764, S3-765 8.6, 10, 23, 305.201

horizontal

9. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.

10. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.

11. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.

12. Close access.

13. Put the airplane back to a serviceable condition.

Group 3, Configuration 3:

1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted

procedure.

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ALERT ALERT
2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) MD11 AMM 06-31-02

112CZ Forward Equipment Panel MD11 AMM 06-31-03

131AB Center Accessory Compartment (CAC) MD11 AMM 06-31-13

131AZ Electrical Power Center (EPC) components (Bay 1) MD11 AMM 06-31-12

131BZ EPC components (Bay 2)

132AZ EPC components (Bay 3)

741AR Main Landing Gear (MLG) door, right-side MD11 AMM 06-37-00

3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM

28-22-13 as an accepted procedure.

Location Service Rework Drawing SR11280076 Sheets

Generator 1 EPC equipment panel 7, 8, 9.1, 9.2

Upper EPC equipment panel 7, 8, 10

Generator 3 EPC equipment panel 7, 8, 11.2

AC forward equipment panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076

sheets 25 and 26.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR11280076 Sheets

6.14, 6.18, 6.22, 6.29, 6.31, 6.36, 6.38, 6.42, 7,

8, 9.1, 9.2, 13.1, 13.2

Generator 1 EPC equipment panel

Generator 2 EPC equipment panel 6.17, 6.27, 6.28, 6.42, 7, 8, 9.1, 14, 17, 18, 19

6.16, 6.19, 6.20, 6.23, 6.26, 6.33, 6.35, 6.42, 7,

8, 11.2, 15.2

Generator 3 EPC equipment panel

AC forward equipment panel 6.24, 6.37, 6.42, 7, 8.1, 12, 16

Upper EPC equipment panel 6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1

CAC 7, 8, 20, 21, 22, 23, 24

6. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.

7. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.

8. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.

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ALERT ALERT
9. Close access.

10. Put the airplane back to a serviceable condition.

Group 4, Configuration 1-2:

1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

Door Number Location Refer to

112AB Avionics Compartment (AC) MD11 AMM 06-31-02

112CZ Forward Equipment Panel MD11 AMM 06-31-03

131AB Center Accessory Compartment (CAC) MD11 AMM 06-31-13

131AZ Electrical Power Center (EPC) components (Bay 1) MD11 AMM 06-31-12

131BZ EPC components (Bay 2)

132AZ EPC components (Bay 3)

741AR Main Landing Gear (MLG) door, right-side MD11 AMM 06-37-00

3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM

28-22-13 as an accepted procedure.

NOTE: Some relays and associated wiring will be removed and not replaced.

Location Service Rework Drawing SR11280076 Sheets

Generator 1 EPC equipment panel 7, 8, 9.3, 9.4

Upper EPC equipment panel 7, 8, 10

Generator 3 EPC equipment panel 7, 8, 11.3

AC forward equipment panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076

sheets 25 and 26.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR11280076 Sheets

6.14, 6.18, 6.22, 6.29, 6.34, 6.38, 6.42, 7, 8, 9.3,

13

Generator 1 EPC equipment panel

Generator 2 EPC equipment panel 6.17, 6.27, 6.28, 6.42, 7, 8, 9.3, 14, 17, 18, 19

6.16, 6.19, 6.20, 6.23, 6.26, 6.34, 6.42, 7, 8, 11.3,

15

Generator 3 EPC equipment panel

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Location Service Rework Drawing SR11280076 Sheets

AC forward equipment panel 6.24, 6.37, 6.42, 7, 8.1, 12, 16

Upper EPC equipment panel 6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1

CAC 7, 8, 20, 21, 22, 23, 24

6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in steps 7 and

8 below. Refer to MD11 AMM 28-22-10 as an accepted procedure.

7. Change terminal board installation and fuel boost/transfer pump wire termination in accordance

with the table that follows:

Service Rework Drawing SR11280134

Sheets

Equipment Item

Numbers

Location

MLG wheel well, right-side S3-804, S3-805 8.4, 10, 11, 12, 13, 15, 303.201

8. Change fuel boost/transfer pump wire termination in accordance with the table that follows:

Service Rework Drawing

SR11280134 Sheets

Equipment Item NumbersLocation

Center and lower wing fuel S3-802, S3-803 8.4, 10, 14, 303.201

tanks

Wing trailing edge, right-side S3-373, S3-375, S3-376 8.2, 8.3, 10, 16, 304.201

Wing leading edge, right-side S3-374, S3-377 8.2, 8.3, 10, 17, 18, 304.201

Wing trailing edge, left-side S3-369, S3-370, S3-372 8.1, 8.2, 10, 19, 304.201

Wing leading edge, left-side S3-368, S3-371 8.1, 8.2, 10, 20, 21, 304.201

Tail fuel tank, front spar rear S3-755, S3-764, S3-765 8.6, 10, 23, 305.201

horizontal

9. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.

10. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.

11. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.

12. Close access.

13. Put the airplane back to a serviceable condition.

Group 4, Configuration 3:

1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted

procedure.

2. Gain access to the area of change. Refer to the table below:

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BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT
Door Number Location Refer to

112AB Avionics Compartment (AC) MD11 AMM 06-31-02

112CZ Forward Equipment Panel MD11 AMM 06-31-03

131AB Center Accessory Compartment (CAC) MD11 AMM 06-31-13

131AZ Electrical Power Center (EPC) components (Bay 1) MD11 AMM 06-31-12

131BZ EPC components (Bay 2)

132AZ EPC components (Bay 3)

741AR Main Landing Gear (MLG) door, right-side MD11 AMM 06-37-00

3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM

28-22-13 as an accepted procedure.

NOTE: Some relays and associated wiring will be removed and not replaced.

Location Service Rework Drawing SR11280076 Sheets

Generator 1 EPC equipment panel 7, 8, 9.3, 9.4

Upper EPC equipment panel 7, 8, 10

Generator 3 EPC equipment panel 7, 8, 11.3

AC forward equipment panel 7, 8.1, 12

4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076

sheets 25 and 26.

5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that

follows:

Location Service Rework Drawing SR11280076 Sheets

6.14, 6.18, 6.22, 6.29, 6.34, 6.38, 6.42, 7, 8, 9.3,

13

Generator 1 EPC equipment panel

Generator 2 EPC equipment panel 6.17, 6.27, 6.28, 6.42, 7, 8, 9.3, 14, 17, 18, 19

6.16, 6.19, 6.20, 6.23, 6.26, 6.34, 6.42, 7, 8, 11.3,

15

Generator 3 EPC equipment panel

AC forward equipment panel 6.24, 6.37, 6.42, 7, 8.1, 12, 16

Upper EPC equipment panel 6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1

CAC 7, 8, 20, 21, 22, 23, 24

6. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.

7. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.

8. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: June 05, 2014

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BOEING SERVICE BULLETIN MD11-28A133

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9. Close access.

10. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: June 05, 2014

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BOEING SERVICE BULLETIN MD11-28A133

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APPENDIX A: INPUT SURVEY

(SHEET 1 OF 1)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: June 05, 2014

MD11-28A133

56 of 56

BOEING SERVICE BULLETIN MD11-28A133

ALERT ALERT