Commercial McDonnell Douglas

Airplanes MD11

Service Bulletin

ALERT

Number: MD11-28A143

Original Issue: December 02, 2009

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and

Fuel Boost/Transfer Pump - Inspection/Replacement

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ECCN: 9E991

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Unpublished Work - All Rights Reserved

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This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

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BLANK PAGE
Table of Contents

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

1. PLANNING INFORMATION ........................................ 7

A. Effectivity ................................................ 7

1. Airplanes ............................................. 7

2. Spares Affected ......................................... 8

B. Concurrent Requirements ....................................... 8

C. Reason ................................................. 8

D. Description ............................................... 8

E. Compliance .............................................. 9

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

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

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

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 14

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 21

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 23

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1 . . 35

APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N

60-84351 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351 . . . 40

APPENDIX D: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER

60-84355-1 INSPECTION LOGIC DIAGRAM . . . . . . . . . . . . . . . . . . . . . . . . . 43

APPENDIX E: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER

60-84351 INSPECTION LOGIC DIAGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . 44

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BLANK PAGE
Commercial McDonnell Douglas

Airplanes MD11

Service Bulletin

ALERT

Summary Number: MD11-28A143

Original Issue: December 02, 2009

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and

Fuel Boost/Transfer Pump - Inspection/Replacement

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 and DC-10 operators have reported instances of fuel pump housing electrical connector assembly, part

number 60-84355-1, failures. Inspecting the fuel boost/transfer pump housing electrical connector assembly,

fuel boost/transfer pump, and replacing any non-serviceable part with a serviceable part as required based on

inspection results, will minimize the possibility of a potential ignition source in the fuel tanks and potential fuel

tank explosion. If not corrected, insulation resistance degradation and/or arcing in the potted backside of the

fuel boost/transfer pump housing electrical connector assembly could compromise the performance of the fuel

boost/transfer pump housing electrical connector assembly and result in a failure that can introduce an ignition

source into the fuel tank and potential fuel tank explosion.

ACTION

This service bulletin provides instructions to inspect/replace each fuel pump housing electrical connector assembly

and fuel boost/transfer pump.

EFFECTIVITY

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

COMPLIANCE

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes and repair procedures given in this

service bulletin.

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MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
Commercial McDonnell Douglas

Airplanes MD11

Service Bulletin

ALERT

Number: MD11-28A143

Original Issue: December 02, 2009

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and

Fuel Boost/Transfer Pump - Inspection/Replacement

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

NOTE: The fuel pump housing electrical connector replacement with part number 60-84351 was

done on fuselage number 466 prior to the original issue of this service bulletin in

accordance with Drawing SP11280022 and FAA Alternative Method of Compliance

(AMOC) approval letter with referenced Boeing letter CP-L4L-09-00243.

This service bulletin is applicable to airplanes that have installed fuel pump housing electrical

connector assembly part number 60-84355-1 in accordance with Service Bulletin MD11-28A138.

GROUP CONFIGURATION DESCRIPTION

1 - Applicable to airplanes without ER3060 gallon forward auxiliary.

Applicable to airplanes with ER3060 gallon forward auxiliary fuel

tanks.

2 -

Airplane Models:

MD-11, MD-11F

Fuselage Num- Group

ber

447 - 589 1

590 2

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Fuselage Num- Group

ber

591 - 596 1

597 2

598 - 607 1

608 2

609 - 612 1

613 2

614 1

615 2

616 - 646 1

2. Spares Affected

Examine your spares supply for the parts or components identified in below. For the recommended

use Paragraph 2.D., Parts Necessary to Change Spares. If any parts or components are found.

Part Number Name

60-843-3 Pump Housing

60-845-3 Pump Housing

60-84355-1 Connector

B. Concurrent Requirements

None.

C. Reason

MD-11 and DC-10 operators have reported instances of fuel pump housing electrical connector assembly,

part number 60-84355-1, failures. Inspecting the fuel boost/transfer pump housing electrical connector

assembly, fuel boost/transfer pump, and replacing any non-serviceable part with a serviceable part as

required based on inspection results, will minimize the possibility of a potential ignition source in the

fuel tanks and potential fuel tank explosion. If not corrected, insulation resistance degradation and/or

arcing in the potted backside of the fuel boost/transfer pump housing electrical connector assembly

could compromise the performance of the fuel boost/transfer pump housing electrical connector assembly

and result in a failure that can introduce an ignition source into the fuel tank and potential fuel tank

explosion.

D. Description

This service bulletin provides instructions to inspect/replace fuel pump housing electrical connector

assembly and fuel boost/transfer pump.

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

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ALERT ALERT
Group 1:

Affected Maintenance Zones

Model Zone

141, 142, 311, 515, 517, 531, 532, 533, 541,

615, 617, 632, 633, 641

MD-11, MD-11F

Group 2:

Affected Maintenance Zones

Model Zone

141, 142, 143, 311, 515, 517, 531, 532, 533,

541, 615, 617, 632, 633, 641

MD-11, MD-11F

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

Federal Aviation Administration (FAA) Airworthiness Directive No. FAA AD 2007-15-05 is related to

this service bulletin.

Refer to Appendix D and E for a logic diagram of the work instructions.

TABLE 1: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84355-1 AND FUEL

BOOST/TRANSFER PUMP - REPLACEMENT/INSPECTION

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 10 months af- (a)

ter the original issue

date on this service

bulletin.

Replace fuel pump electrical

connector assemblies with P/N

60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 2 and Part

5.

All Airplanes.

OR

Within 10 months after the original issue

date on this service

bulletin.

Do continuity, resistance and

insulation resistance inspection

in accordance with Accomplishment Instructions 3.B. Part 3.

AND

Replace fuel pump electrical

connector assemblies with P/N

60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 2 and Part

5.

Within 12 months af- (a)

ter inspection.

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TABLE 1: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84355-1 AND FUEL

BOOST/TRANSFER PUMP - REPLACEMENT/INSPECTION

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Do restoration in accordance Before further flight.

with Accomplishment Instructions 3.B. Part 5.

(Serviceable Fuel pump and housing electrical connector assembly)

Fuel pump housing electrical connector assembly wiring resistance

reading is less than or equal to 2.5

ohms and terminal E is open.

AND

Fuel boost/transfer pump resistance

reading is less than or equal to 2.5

ohms and pin E is open.

AND

Fuel pump housing electrical connector assembly wiring insulation

resistance reading is greater than

or equal to 10 gigaohm.

Replace fuel boost/transfer Before further flight.

pump and restore in accordance

with Accomplishment Instructions 3.B. Part 3 and Part 5.

(Defective Fuel boost/transfer

pump)

Fuel boost/transfer pump resistance

reading is greater than 2.5 ohms or

pin E is not open and fuel pump

housing electrical connector assembly wiring resistance reading is less

than or equal to 2.5 ohms and terminal E is open and fuel pump

housing electrical connector assembly wiring insulation resistance

reading is greater than or equal to

10 gigaohm.

Replace fuel pump electrical Before further flight. (a)

connector assemblies with P/N

60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 2 and Part

5.

(Defective Fuel pump housing

electrical connector assembly)

Fuel pump housing electrical connector assembly wiring resistance

reading is greater than 2.5 ohms or

terminal E is not open and fuel

boost/transfer pump resistance

reading is less than or equal to 2.5

ohms and pin E is open.

OR

Fuel pump housing electrical connector assembly wiring insulation

resistance reading is less than 10

gigaohm.

(a) REFER TO TABLE 2 AFTER REPLACEMENT OF FUEL PUMP HOUSING ELECTRICAL CONNECTOR

ASSEMBLY P/N 60-84355-1 WITH P/N 60-84351.

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TABLE 2: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84351 AND FUEL

BOOST/TRANSFER PUMP - INSPECTION

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 18 months af- 18 Months

ter P/N 60-84351 installation.

Do continuity, resistance and

insulation resistance inspection

in accordance with Accomplishment Instructions 3.B. Part 4.

All Airplanes

Do restoration in accordance Before further flight.

with Accomplishment Instructions 3.B. Part 5.

(Serviceable Fuel pump and housing electrical connector assembly)

Fuel pump housing electrical connector assembly wiring resistance

reading is less than or equal to 2.5

ohms and terminal E is open.

AND

Fuel boost/transfer pump resistance

reading is less than or equal to 2.5

ohms and pin E is open.

AND

Fuel pump housing electrical connector assembly wiring insulation

resistance reading is greater than

or equal to 10 megaohm.

Replace fuel boost/transfer Before further flight.

pump and restore in accordance

with Accomplishment Instructions 3.B. Part 4 and Part 5.

(Defective Fuel boost/transfer

pump)

Fuel boost/transfer pump resistance

reading is greater than 2.5 ohms or

pin E is not open and fuel pump

housing electrical connector assembly wiring resistance reading is less

than or equal to 2.5 ohms and terminal E is open and fuel pump

housing electrical connector assembly wiring insulation resistance

reading is greater than or equal to

10 megaohm.

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TABLE 2: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84351 AND FUEL

BOOST/TRANSFER PUMP - INSPECTION

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Replace fuel pump electrical Before further flight.

connector assemblies with P/N

60-84351 and restore in accordance with Accomplishment Instructions 3.B. Part 4 and Part

5.

(Defective Fuel pump housing

electrical connector assembly)

Fuel pump housing electrical connector assembly wiring resistance

reading is greater than 2.5 ohms or

terminal E is not open and fuel

boost/transfer pump resistance

reading is less than or equal to 2.5

ohms and pin E is open.

OR

Fuel pump housing electrical connector assembly wiring insulation

resistance reading is less than 10

megaohm.

F. Approval

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

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

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

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

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

changes.

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

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

before incorporating this service bulletin.

In addition, the Manager of the FAA Los Angles Aircraft Certification Office approves the action (i.e.

inspection or modification) defined in this service bulletin as an alternative method of compliance to

the requirements of Paragraph (l) of FAA AD 2007-15-05. All provisions of FAA AD 2007-15-05 that

are not specifically referenced in the above statement remain fully applicable and must be complied

with.

G. Manpower

The table below shows an estimate of the task hours necessary to do this inspection 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

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• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Group 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 8.0 8.0

Inspect 2 30.0 15.0

Change 2 *0.2 - 86.0 *0.1 - 43.0

Close Access 1 8.0 8.0

Test 2 2.0 1.0

TOTAL FOR EACH AIRPLANE *48.2 -134.0 *32.1 - 75.0

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 9.0 9.0

Inspect 2 34.0 17.0

Change 2 *0.2 - 96.0 *0.1 - 48.0

Close Access 1 9.0 9.0

Test 2 2.0 1.0

TOTAL FOR EACH AIRPLANE *54.2 - 150.0 *36.1 - 84.0

*A range of total task hours and elapsed hours and given for inspection per airplane. Actual task hours

and elapsed hours for the change are contingent upon inspection findings and are to be estimated by

the operator.

H. Weight and Balance Changes

Weight and balance changes affected by incorporation of this service bulletin are contingent upon the

changes to each particular airplane. Weight data is to be computed by the operator by weighing parts

removed and parts installed during this change. Necessary revisions should be made to the appropriate

airplane weight and balance report.

I. Electrical Load Data

Not changed.

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J. References

1. Existing Data

a. Boeing Service Bulletin MD11-28A138.

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

20-20-01, 20-20-02, 20-20-03, 20-31-00, and 20-50-01.

c. MD11 Aircraft Maintenance Manual (AMM) 12-11-03, 28-00-00, 28-22-01, 28-22-02 and

28-22-10.

d. MD11 Structural Repair Manual (SRM) 51.

e. FAA Airworthiness Directive (FAA) 2007-15-05.

f. Wiring Diagram Manual (WDM) 28-22-01, 28-22-02, 28-22-03, 28-22-04 and 28-22-05.

g. Crane Hydro-Aire Service Information Letters 60-847-3-1 and 60-843-845-3-28-2.

h. FAA Alternative Method of Compliance (AMOC) approval letter with referenced Boeing letter

CP-L4L-09-00243.

2. Data supplied with this Service Bulletin

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

bulletin submit a data request to:

Data and Services Management

MS D800-0019

3855 Lakewood Boulevard

Long Beach, California 90846

Phone: (562) 593-6996

Fax: (562) 593-2001

E-mail: dse.boecom@boeing.com

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

ELEC INSTL - FUEL PUMP ELECTRICAL DWG E -

CONNECTOR

SR11280084

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

None.

K. Publications Affected

1. Publications:

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ALERT ALERT
Publication Chapter-Section

Fault Isolation Manual 28-14 and 28-22

Illustrated Parts Catalog 28-13 and 28-22

Aircraft Maintenance Manual 28-22

Maintenance Planning Data 28

Wiring Diagram Manual Equipment List 28-22

Wiring Diagram Manual 28-22

2. Damage Tolerance Based Structural Inspections:

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

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

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

L. Interchangeability and Intermixability of Parts

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

information.

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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 as shown

below. If there is a limit to the quantity of available kits, a supply sequence is given by Spares. More

kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date

Boeing gets the purchase order.

Unit Price thru

November 30,

2010

Part Number Name ROLT (Weeks)

SR11280084-3 SERVICE KIT 13 $267.00

SR11280084-5 SERVICE KIT 13 41.00

SR11280084-7 SERVICE KIT 13 9.00

SR11280084-9 SERVICE KIT 13 155.00

SR11280084-11 SERVICE KIT 13 526.00

SR11280084-13 SERVICE KIT 13 526.00

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

After the Unit Price date, new price ROLT data is applicable. Prices are in United States dollars. Terms:

Net 30 days.

Reference this service bulletin and submit your purchase order by one of the methods that follow:

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

2. Fax to (206) 662-7145

3. Mail to:

Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes and repair procedures 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.

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Group 1:

New Part Number QTY Name Notes

SR11280084-3 4 KIT (a)

SR11280084-5 8 KIT (a)

SR11280084-7 2 KIT (a)

SR11280084-9 3 KIT (a)

(a) Total quantity required per airplane.

Group 1:

SR11280084

New Part Number QTY Name Notes

-3 -5 -7 -9

10-35916-16 . . 1 . SLEEVE

10-60766-8 . . 1 . GROMMET

10-74916-8 . 1 . 1 NUT GROMMET ASSY

2768771-1 1 . . . COMB

3D0005-3-12 1 1 1 1 SCREW (a)

5D0086-25 3 3 3 5 TERMINAL LUG 765 (a)

5D0086-26 2 2 2 . TERMINAL LUG 766 (a)

687-118NF08 . . . 1 CLAMP

7D0294-1 1 . . . FERRULE

9D0067-4 . . . 1 FERRULE ASSY (a)

9D0180-2 . . . 1 BAND,RETAINING (a)

9D0196-1 2 . . . PIN (a)

9D0197-1 1 . . . BUSHING (a)

M8700-7/3 1 . . . GLAND NUT

MS35338-137 3 3 3 3 WASHER

MS35338-43 1 1 1 1 LOCKWASHER

MS35649-284 3 3 3 3 NUT

NAS1149CN832R 3 3 3 3 WASHER

NAS1149F0332P 1 1 1 1 WASHER

NEQL48830 2 FT OVERBRAID

SR11280084-15 2 FT TUBING (b)

(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
Group 1:

SR11280084

New Part Number QTY Name Notes

-3 -5 -7 -9

(b) Material specification DMS 2380 Class 1 or approved Equivalent.

Group 2:

SR11280084

New Part Number QTY Name Notes

SR11280084-11 1 KIT (a)

SR11280084-13 1 KIT (a)

SR11280084-3 4 KIT (a)

SR11280084-5 8 KIT (a)

SR11280084-7 2 KIT (a)

SR11280084-9 3 KIT (a)

(a) Total quantity required per airplane.

Group 2:

SR11280084

New Part Number QTY Name Notes

-3 -5 -7 -9 -11 -13

10-35916-16 . . 1 . . . SLEEVE

10-60766-8 . . 1 . . . GROMMET

10-74916-8 . 1 . 1 . . NUT GROMMET ASSY

2768771-1 1 . . . . . COMB

3D0005-3-12 1 1 1 1 1 1 SCREW (a)

5D0086-25 3 3 3 5 . . TERMINAL LUG 765 (a)

5D0086-26 2 2 2 . . . TERMINAL LUG 766 (a)

687-118NF08 . . . 1 . . CLAMP

7D0294-1 1 . . . . . FERRULE

9D0067-4 . . . 1 . . FERRULE ASSY (a)

9D0180-2 . . . 1 . . BAND,RETAINING (a)

9D0196-1 2 . . . . . PIN (a)

9D0197-1 1 . . . . . BUSHING (a)

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
Group 2:

SR11280084

New Part Number QTY Name Notes

-3 -5 -7 -9 -11 -13

DC64-16P . . . . 5 5 PIN T/C 1127

M8700-7/3 1 . . . . . GLAND NUT

MS3450L16-8P . . . . . 1 CONNECTOR (a)

MS3450L16-8PX . . . . 1 . CONNECTOR (a)

MS35338-137 3 3 3 3 . . WASHER

MS35338-43 1 1 1 1 1 1 LOCKWASHER

MS35649-284 3 3 3 3 . . NUT

NAS1149CN832R 3 3 3 3 . . WASHER

NAS1149F0332P 1 1 1 1 1 1 WASHER

NEQL48830 2 FT OVERBRAID

SR11280084-15 2 FT TUBING (c)

SR11280084-101 . . . . 1 . WIRE KIT (b)

SR11280084-102 . . . . . 1 WIRE KIT (b)

SR11280084-103 . . . . 1 . WIRE KIT (b)

SR11280084-104 . . . . . 1 WIRE KIT (b)

(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.

(b) Refer to Wire Kit Components Table.

(c) Material specification DMS 2380 Class 1 or approved Equivalent.

Group 2:

Wire Kit SR11280084

New Part Number QTY Name Notes

-101 -102 -103 -104

5D0086-26 1 1 TERMINAL LUG T/C 766 (a)

D2426-1C-16NM 2 FT 2 FT 7 FT 7 FT WIRE CODE 801 (a)

DC62L16SJ8SN 1 PLUG

DC62L16SJ8SX 1 PLUG

DC64-16P 1 1 PIN T/C 1127

DC65-16SS 1 1 5 5 SKT T/C 1125

(a) Or approved Equivalent.

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
2. Parts and Materials Supplied by the Operator

NOTE: The items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator,

show the total quantity necessary for each airplane unless noted otherwise.

Group 1:

New Part Number / Specifica- QTY Name Notes

tion

60-84351 17 CONNECTOR ASSY (a)

60-847-X 17 PUMP ASSY (a) (c)

M25988/1-019 17 PACKING (a)

LL500D4-6 68 SCREW (a)

Or

ES500D4-6

1 Inch x .030 TAPE (b)

Inch x 12 Feet

SR11280084-17

(DMS 2186 Type 2)

Or

AR 386

Or

Equivalent

(a) Can be purchased from: Hydro-Aire, Incorporated CAGE

3000 Winona Avenue 81982

Burbank, California 91504-2540 USA

(b) Can be purchased from: Freudenberg-NOK 02988

65 Spruce Street

Tillsonburg, Ontario N4G 4H3 Canada

(c) Refer to Illustrated Parts Catalog (IPC) for applicable fuel boost/transfer pump configuration.

Group 2:

New Part Number / Specifica- QTY Name Notes

tion

60-84351 19 CONNECTOR ASSY (a)

60-847-X 19 PUMP ASSY (a) (c)

M25988/1-019 19 PACKING (a)

LL500D4-6 76 SCREW (a)

Or

ES500D4-6

1 Inch x .030 TAPE (b)

Inch x 12 Feet

SR11280084-17

(DMS 2186 Type 2)

Or

AR 386

Or

Equivalent

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
Group 2:

New Part Number / Specifica- QTY Name Notes

tion

(a) Can be purchased from: Hydro-Aire, Incorporated CAGE

3000 Winona Avenue 81982

Burbank, California 91504-2540 USA

(b) Can be purchased from: Freudenberg-NOK 02988

65 Spruce Street

Tillsonburg, Ontario N4G 4H3 Canada

(c) Refer to IPC for applicable fuel boost/transfer pump configuration.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

To get parts shown below, contact the Crane Spares Department at (818) -526-2500 or FAX to

(818)-526-2658.

New Part Number / Specifica- Name Notes

tion

60-84351 CONNECTOR ASSY (a) (d)

M25988/1-019 PACKING (a) (d)

LL500D4-6 SCREW (a) (d)

Or

ES500D4-6

SR11280084-17 TAPE (b) (c)

(DMS 2186 Type 2)

Or

AR 386

Or

Equivalent

(a) Can be purchased from: Hydro-Aire, Incorporated CAGE

3000 Winona Avenue 81982

Burbank, California 91504-2540 USA

(b) Can be purchased from: Freudenberg-NOK 02988

65 Spruce Street

Tillsonburg, Ontario N4G 4H3 Canada

(c) Stock size 1 inch x .030 inch x 12 feet.

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
New Part Number / Specifica- Name Notes

tion

(d) Use applicable quantities to revise spare 60-843-3 and 60-845-3 fuel pump housing

assemblies. Replace spare 60-84355-1 with 60-84351 as needed.

E. Special Tooling - Price and Availability

The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this

Service Bulletin. Tool price and supply data are not given.

F. Special Tooling Necessary to do this Service Bulletin

To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.

Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be

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

Tool / Kit Number Name Supplier CAGE

Multimeter Model 10 Fluke Corporation 0HYG7

Or 1420 75TH Street Southwest

Equivalent Everett, Washington 98206

Megohm meter Model 1864 Quadtech, Incorporated 0PK96

Or 5 Clock Tower Place, Suite 210

Equivalent Maynard, Massachusetts 01754

* An Equivalent Megohm meter must be able to apply voltage at 100+/-10 Volts DC and be current limited

to 5 Milliamps.

A T67291 or T67291-1 test tool/alternate tool is required to accomplish this inspection. Refer to Crane

Hydro-Aire Service Information Letter 60-847-3-1.

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ALERT ALERT
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BOEING SERVICE BULLETIN MD11-28A143

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.

WARNING: WHILE YOU DO WORK IN THE TAILCONE AREA, MAKE SURE THAT YOU OBEY

ALL SAFETY PRECAUTIONS. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH

OR INJURY TO PERSONS CAN OCCUR.

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

TO THE AIRPLANE OR EQUIPMENT.

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Equivalent parts are listed in the AEPL, Drawing 7595071.

3. Use the approved fastener and process material substitutions, in accordance with

MD11 SRM, Chapter 51.

4. If the length of any fastener specified in this service bulletin does not meet the

installation standards 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. Not applicable to Crane Hydro-Aire fuel pump or fuel

pump housing or attaching parts.

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.

– Torque limits to tighten nuts and bolts are in SRM, Chapter 51.

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

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
– CHAPTER TITLE

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 FABRICATING AND INSTALLING WIRE HARNESSES - COMMERCIAL

SWPM 20-20-01 TERMINALS - MAINTENANCE PRACTICES

SWPM 20-20-02 TERMINAL BLOCKS - MAINTENANCE PRACTICES

SWPM 20-20-03 GENERAL INSTALLATIONS HARDWARE - MAINTENANCE PRACTICES

SWPM 20-31-00 ELECTRICAL CONNECTORS - MAINTENANCE PRACTICES

SWPM 20-50-01 ELECTRICAL BONDING - MAINTENANCE PRACTICES

8. Refer to Wiring Diagram Manual (WDM) for applicable wiring diagrams as follows:

LOCATION – WIRING DIAGRAM

Tank 1 28-22-01

Tank 2 28-22-02

Tank 3 28-22-03

Aux Tank * 28-22-04

Tail Tank 28-22-05

* Including Fwd Aux Tanks (If Installed).

9. Obey all of the warnings and cautions given in the specified manual sections.

10. Review and understand all general notes of Service Rework Drawing SR11280084

sheets 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.7.1, 3.8, 3.9, 3.10 and 7 before start of

modification.

11. 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.

12. Any protrusion of threads is acceptable provided that the threads do not rub or ride

against nearby wire assemblies or components.

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
13. Access panel numbers and locations may vary.

14. Identify and note location of wires prior to removal from terminal strip and/or ground

stud.

15. The inspection order of operation procedures outlined in Parts 3 and 4 of Paragraph

3.B., Work Instructions must be followed. The instructions identified in Paragraph

3.B., Work Instructions give the recommended sequence of steps for which pump

location to inspect. The sequence of steps to inspect the pump locations can be

changed.

B. WORK INSTRUCTIONS

PART 1 (ACCESS/PREPARATION)

WARNING: FUEL TANKS MUST BE FILLED TO SPECIFIED LEVEL OR DRAINED, PURGED, AND

SAFE FOR MAINTENANCE. THIS WILL PREVENT INJURY TO PERSONS AND

DAMAGE TO EQUIPMENT.

1. Make sure fuel tanks are filled to specified level or defuel, purge, and make fuel system safe for

maintenance. Refer to MD11 AMM 12-11-03 and MD11 AMM 28-00-00 as accepted procedures.

Tank Minimum Fuel Level

Pounds Kilogram

1* 20000 9070

2 23000 10430

3* 20000 9070

Upper Aux 11000 4980

Lower Aux 4500 2040

Tail 7000 3170

* Tanks 1 and 3 aft fuel boost/transfer pumps and conduits are located in tank 2. Tank 2 must be filled to

specified level when accomplishing this inspection for tanks 1 and 3 aft fuel boost/transfer pumps.

Group 2:

Tank Minimum Fuel Level

Pounds Kilogram

Fwd Aux 4500 2040

2. Place Fuel System Controller (FSC) in manual mode and make sure all pumps are off. Refer to

MD11 AMM 28-00-00 as an accepted procedure.

3. Gain access to inspection areas. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an

accepted procedure.

4. Open/verify circuit breakers as follows:

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
a. Open fuel boost/transfer pump power circuit breakers. Refer to MD11 AMM 28-22-01 and

MD11 AMM 28-22-02 as an accepted procedure.

b. Make sure Remote Control Circuit Breaker (RCCB) indicators are green/open.

RCCB Circuit Breaker Location

B1-672 Tank 1 Trans EPC Bay 2

B1-673 Tank 1 Aft EPC Bay 3

B1-190* Tank 1 Aft ADG Equipment Panel

B1-674 Tank 1 Fwd EPC Bay 1

B1-675 Tank 2 R Aft EPC Bay 1

B1-676 Tank 2 Fwd EPC Bay 1

B1-677 Tank 3 Fwd EPC Bay 3

B1-678 Tank 3 Trans EPC Bay 1

B1-682 Tank 2 Trans EPC Bay 3

B1-679 Tank 3 Aft EPC Bay 2

B1-191* Tank 3 Aft ADG Equipment Panel

B1-1258 R Upper Aux Tank EPC Bay 1

B1-1259 R Lower Aux Tank EPC Bay 3

B1-1260 L Upper Aux Tank EPC Bay 2

B1-1261 L Lower Aux Tank EPC Bay 2

B1-1572 Tank 2 L Aft Electrical Power Panel

B1-1573 Tail Tank L Trans EPC Bay 1

B1-1575 Tail Tank R Trans EPC Bay 2

B1-1577 Tail Tank Altn Electrical Power Panel

*If installed

Group 2:

RCCB Circuit Breaker Location

B1-391 Fwd Aux L EPC Bay 1

B1-392 Fwd Aux R EPC Bay 3

PART 2 (FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY - REPLACEMENT)

1. Replace existing 60-84355-1 fuel pump housing electrical connector assembly in accordance with

Appendix B.

2. Proceed to Part 5 (Restoration).

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
PART 3 (FUEL BOOST/TRANSFER PUMP AND FUEL PUMP HOUSING ELECTRICAL CONNECTOR

ASSEMBLY PART NUMBER 60-84355-1 INSPECTION)

1. Using a digital multimeter, check electrical continuity and resistance from terminal strip through

fuel boost/transfer pump as follows:

a. Disconnect fuel boost/transfer pump wires from terminal strip/ground stud (or disconnect

connectors) and check disconnected wires terminal to terminal in accordance with Appendix

A, Tables below and refer to MD11 AMM 28-22-10 as an accepted procedure:

NOTE: Fuel boost/transfer pump wiring resistance should be less than or equal to 2.5 ohms.

NOTE: Terminal E should read open during multimeter check.

Wiring Resistance Check

Check Results Check Results

1-2 2-3

1-3 2-E

1-E 3-E

Group 2:

Wiring Resistance Check

Check Results Check Results

A-B B-C

A-C B-E

A-E C-E

b. If fuel boost/transfer pump wiring resistance is greater than 2.5 ohms or terminal E is not open,

remove fuel boost/transfer pump, refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as

an acceptable procedure and check pin-to-pin as follows:

NOTE: Fuel boost/transfer pump resistance should be less than or equal to 2.5 ohms.

NOTE: Pin E should read open during multimeter check.

Fuel Boost/Transfer Pump Resistance Check

Check Results Check Results

A-B B-C

A-C B-E

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
Fuel Boost/Transfer Pump Resistance Check

Check Results Check Results

A-E C-E

2. If any fuel boost/transfer pump wiring resistance reading is greater than 2.5 ohms or terminal E is

not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms with

pin E open, replace existing fuel pump housing electrical connector assembly in accordance with

Appendix B.

3. Remove and retain fuel boost/transfer pumps, if not previously removed. Refer to MD11 AMM

28-22-01 and MD11 AMM 28-22-02 as an accepted procedure.

4. Using Quadtech 1864 Megohm meter, do a fuel pump housing electrical connector assembly

insulation resistance check as follows:

a. Install T67291 or T6729-1 test tool/alternate tool.

b. Set Megohm meter at 100+/-10 volts DC and current limit to 5 milliamps. Check insulation

resistance by applying test voltage terminal-to-terminal in accordance with Appendix A, and

Tables below:

NOTE: Insulation resistance should be greater or equal to 10 gigaohm.

Insulation Resistance Check

Check Results Check Results

1-2 2-3

1-3 2-E

1-E 3-E

Group 2:

Insulation Resistance Check

Check Results Check Results

A-B B-C

A-C B-E

A-E C-E

c. Remove test pump/alternate tool.

5. If any fuel boost/transfer pump resistance reading is greater than 2.5 ohms or pin E is not open.

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
a. Replace fuel boost/transfer pump. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02

as an accepted procedure.

b. Proceed to Part 5 (Restoration).

6. If any fuel pump housing electrical connector assembly insulation resistance reading is less than

10 gigaohm.

a. Replace existing fuel pump housing electrical connector assembly in accordance with Appendix

B.

b. Proceed to Part 5 (Restoration).

7. Proceed to Part 5 (Restoration) If all continuity, resistance and insulation resistance, results are

as follows:

a. Fuel boost/transfer pump wiring resistance reading is less than or equal to 2.5 ohms and

terminal E is open.

b. Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is

open.

c. Fuel pump housing electrical connector assembly insulation resistance reading is greater than

or equal to 10 gigaohm.

PART 4 (FUEL BOOST/TRANSFER PUMP AND FUEL PUMP HOUSING ELECTRICAL CONNECTOR

ASSEMBLY PART NUMBER 60-84351 INSPECTION)

1. Using a digital multimeter, check electrical continuity and resistance from terminal strip through

fuel boost/transfer pump as follows:

a. Disconnect fuel boost/transfer pump wires from terminal strip/ground stud (or disconnect

connectors) and check disconnected wires terminal to terminal in accordance with Appendix

C, Tables below and refer to MD11 AMM 28-22-10 as an accepted procedure:

NOTE: Fuel boost/transfer pump wiring resistance should be less than or equal to 2.5 ohms.

NOTE: Terminal E should read open during multimeter check.

Wiring Resistance Check

Check Results Check Results

1-2 2-D

1-3 2-E

1-D 3-D

1-E 3-E

2-3 D-E

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ALERT ALERT
Group 2:

Wiring Resistance Check

Check Results Check Results

A-B B-D

A-C B-E

A-D C-D

A-E C-E

B-C D-E

b. If fuel boost/transfer pump wiring resistance is greater than 2.5 ohms or terminal E is not open,

remove fuel boost/transfer pump, refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as

an acceptable procedure and check pin-to-pin as follow:

NOTE: Fuel boost/transfer pump resistance should be less than or equal to 2.5 ohms.

NOTE: Pin E should read open during multimeter check.

Fuel Boost/Transfer Pump Resistance Check

Check Results Check Results

A-B B-D

A-C B-E

A-D C-D

A-E C-E

B-C D-E

2. If any fuel boost/transfer pump wiring resistance reading is greater than 2.5 ohms or terminal E is

not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms with

pin E open, replace the affected fuel pump housing electrical connector assembly. Refer to MD11

AMM 28-22-10, Section entitled "Pump Housing, A and B Repairs", and "Pre Service Bulletin

MD11-28A113" as an accepted procedure.

3. Remove and retain fuel boost/transfer pumps, if not previously removed. Refer to MD11 AMM

28-22-01 and MD11 AMM 28-22-02 as an accepted procedure.

4. Using Quadtech 1864 Megohm meter, do a fuel pump housing electrical connector assembly

insulation resistance check as follows:

a. Install T67291 or T6729-1 test tool/alternate tool.

b. Set Megohm meter at 100+/-10 volts DC and current limit to 5 milliamps. Check insulation

resistance by applying test voltage terminal-to-terminal in accordance with Appendix C, and

Tables below:

NOTE: Insulation resistance should be greater or equal to 10 megaohm.

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
Insulation Resistance Check

Check Results Check Results

1-2 2-D

1-3 2-E

1-D 3-D

1-E 3-E

2-3 D-E

Group 2:

Insulation Resistance Check

Check Results Check Results

A-B B-D

A-C B-E

A-D C-D

A-E C-E

B-C D-E

c. Remove test pump/alternate tool.

5. If any fuel boost/transfer pump resistance reading is greater than 2.5 ohms or pin E is not open.

a. Replace fuel boost/transfer pump. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02

as an accepted procedure.

b. Proceed to Part 5 (Restoration).

6. If any fuel pump housing electrical connector assembly insulation resistance reading is less than

10 megaohm.

a. Replace the affected fuel pump housing electrical connector assembly. Refer to MD11 AMM

28-22-10, Section entitled "Pump Housing, A and B Repairs", and "Pre Service Bulletin

MD11-28A113" as an accepted procedure.

b. Proceed to Part 5 (Restoration).

7. Proceed to Part 5 (Restoration) If all continuity, resistance and insulation resistance, results are

as follows:

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
a. Fuel boost/transfer pump wiring resistance reading is less than or equal to 2.5 ohms and

terminal E is open.

b. Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is

open.

c. Fuel pump housing electrical connector assembly insulation resistance reading is greater than

or equal to 10 megaohm.

PART 5 (RESTORATION)

1. If not already accomplished, connect fuel pump housing electrical connector assemblies to terminal

strip and ground studs. Refer to MD11 AMM 28-22-10 and Appendix A (part number 60-84355-1),

or Appendix C (part number 60-84351) as an accepted procedure.

2. Install fuel boost/transfer pumps if not previously installed refer to MD11 AMM 28-22-01 and MD11

AMM 28-22-02 as an accepted procedure.

3. Do operational test of fuel boost/transfer pumps and using a digital multimeter check that voltage

between applicable terminal strip post and ground is 104 to 122VAC. Refer to MD11 AMM 28-22-01,

MD11 AMM 28-22-02 and Appendix A (part number 60-84355-1), or Appendix C (part number

60-84351) as an accepted procedure.

4. Close access. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an accepted procedure.

5. Put the airplane back to a serviceable condition.

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MD11-28A143

34 of 44

BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
ALL GROUPS:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-368

A

1/Forward R5-1102 B 2 -

C 3 -

E* 5022A

1 -

S3-370

A

1/Transfer R5-1100 B 2 -

C 3 -

E* 4726A

1 -

S3-369

A

1/Aft R5-1101 B 2 -

C 3 -

E* 4727A

1 -

S3-371

A

2/Forward R5-1105 B 2 -

C 3 -

E* 5009A

1 -

S3-372

A

2/Left Aft R5-1104 B 2 -

C 3 -

E* 4728A

1 -

S3-374

A

2/Transfer R5-1099 B 2 -

C 3 -

E* 6078A

1 -

S3-373

A

2/Right Aft R5-1103 B 2 -

C 3 -

E* 4821A

1 -

S3-377

A

3/Forward R5-1106 B 2 -

C 3 -

E* 6022A

1 -

S3-376

A

3/Transfer R5-1107 B 2 -

C 3 -

E* 4823A

APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1

(SHEET 1 OF 3)

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Original Issue: December 02, 2009

MD11-28A143

35 of 44

BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
ALL GROUPS:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-375

A

3/Right Aft R5-1108 B 2 -

C 3 -

E* 4822A

1 -

S3-803

A

R5-1934 Center Aux/Left

Upper

B 2 -

C 3 -

E* 4729A

1 -

S3-802

A

R5-1933 Center Aux/Right

Upper

B 2 -

C 3 -

E* 4824A

1 -

S3-805

A

R5-1936 Center Aux/Left

Lower

B 2 -

C 3 -

E* 4895A

1 -

S3-804

A

R5-1935 Center Aux/Right

Lower

B 2 -

C 3 -

E* 4894A

1 -

S3-764

A

Tail/Left Transfer R5-2802 B 2 -

C 3 -

E* 5 7043A

1 -

S3-765

A

R5-2800 Tail/Right Transfer

B 2 -

C 3 -

E* 5 7043A

1 -

S3-755

A

Tail/Altn R5-2801 B 2 -

C 3 -

E* 5 7043A

* E should read open during multimeter check.

APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1

(SHEET 2 OF 3)

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Original Issue: December 02, 2009

MD11-28A143

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
GROUP 2:

Ground Stud Connector (Pump) ConnectorTank/Pump Number Socket Number Socket

A -

R5-9668

A

R5-1347 Forward Aux

Right

B B -

C C -

E* E* 9079A

A -

R5-9669

A

Forward Aux Left R5-1348 B B -

C C -

E* E* 9078A

* E should read open during multimeter check.

GROUP 2:

Tank/Pump Location Relay Terminal

Forward Aux Right R2-110 A1

B1

C1

Forward Aux Left R2-109 A1

B1

C1

APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
1. Put the Fuel System Controller (FSC) in manual mode and make sure all pumps are off. Refer to MD11

AMM 28-00-00 as an accepted procedure.

2. Replace the affected fuel pump housing electrical connector assembly in accordance with Table below and

refer to MD11 AMM 28-22-10, Section entitled "Pump Housing, A and B Repairs", and "Pre Service Bulletin

MD11-28A113" as an accepted procedure.

ALL GROUPS:

Drawing

SR11280084

Connector IdentificationFuel Pump IdentificationTank Location

Sheets 3, 3.1, 3.3,

3.4, 3.8, 3.9, 3.10, 4,

4.1, 5, 5.1, 6, 6.1, 7,

9, 9.6, 10 and 21

1 Forward M1-1102 R5-1102

Sheets 3, 3.1, 3.3,

3.5, 3.8, 3.9, 3.10, 4,

4.1, 5, 5.1, 6, 6.1, 7,

9, 9.6, 10 and 19.

1 Transfer M1-1100 R5-1100

1 Left Aft M1-1101 R5-1101

Sheets 3, 3.1, 3.3,

3.4, 3.8, 3.9, 3.10, 4,

4.1, 5, 5.1, 6, 6.1, 7,

9.1, 9.6, 10 and 20.

2 Forward M1-1105 R5-1105

Sheets 3, 3.1, 3.3,

3.5, 3.8, 3.9, 3.10, 4,

4.1, 5, 5.1, 6, 6.1, 7,

9.1, 9.6, 10 and 19.

2 Left Aft M1-1104 R5-1104

Sheets 3, 3.1, 3.3,

3.4, 3.8, 3.9, 3.10, 4,

4.1, 5, 5.1, 6, 6.1, 7,

9.1, 9.6, 10 and 17.

2 Transfer M1-1099 R5-1099

Sheets 3, 3.1, 3.3,

3.5, 3.8, 3.9, 3.10, 4,

4.1, 5., 5.1, 6, 6.1, 7,

9.1, 9.7, 10 and 16.

2 Right Aft M1-1103 R5-1103

Sheets 3, 3.1, 3.3,

3.4, 3.8, 3.9, 3.10, 4,

4.1, 5, 5.1, 6, 6.1, 7,

9.2, 9.7, 10 and 18.

3 Forward M1-1106 R5-1106

APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N

60-84351

(SHEET 1 OF 2)

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MD11-28A143

38 of 44

BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
ALL GROUPS:

Drawing

SR11280084

Connector IdentificationFuel Pump IdentificationTank Location

Sheets 3, 3.1, 3.3,

3.5, 3.8, 3.9, 3.10, 4,

4.1, 5, 5.1, 6. 6.1, 7,

9.2, 9.7, 10 and 16.

3 Transfer M1-1107 R5-1107

3 Right Aft M1-1108 R5-1108

Sheets 3, 3.1, 3.3,

3.5, 3.8, 3.9, 3.10, 4,

4.1, 5, 5.1, 6, 6.1, 7,

9.3, 9.7, 10 and 13.

Center Aux/Upper Left M1-1934 R5-1934

Center Aux/Upper Right M1-1933 R5-1933

Sheets 3, 3.1, 3.2,

3.3, 3.8, 3.9, 3.10, 4,

4.1, 5, 5.1, 6, 6.1, 7,

9.3, 9.8, 10, 14 and

15.

Center Aux/Lower Left M1-1936 R5-1936

Center Aux/Lower Right M1-1935 R5-1935

Sheets 3, 3.1, 3.3,

3.7, 3.7.1, 3.8, 3.9,

3.10, 4, 4.1, 5, 5.1, 6,

6.1, 7, 9.5, 9.8, 10

and 11.

Tail Left Transfer M1-2802 R5-2802

Sheets 3, 3.1, 3.3,

3.7, 3.7.1, 3.9, 3.10,

4, 4.1, 5, 5.1, 6, 6.1,

7, 9.5, 9.8, 10 and

11.

Tail Right Transfer M1-2800 R5-2800

Sheets 3, 3.1, 3.3,

3.7, 3.7.1, 3.8, 3.9,

3.10, 4, 4.1, 5, 5.1, 6,

6.1, 7, 9.5, 9.9, 10

and 11.

Tail Alt Feed M1-2801 R5-2801

GROUP 2:

Drawing

SR11280084

Connector IdentificationFuel Pump IdentificationTank Location

Sheets 3, 3.1, 3.3,

3.6, 3.9, 3.10, 4.1,

5.1, 6.1, 7, 8, 8.1,

8.2, 8.3, 9.4, 9.8, 10

and 12.

Forward Aux Right M1-1347 R5-1347

Forward Aux Left M1-1348 R5-1348

APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N

60-84351

(SHEET 2 OF 2)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 02, 2009

MD11-28A143

39 of 44

BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
ALL GROUPS:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-368

A

1/Forward R5-1102

B 2 -

C 3 -

D 5022A

E* 5022A

1 -

S3-370

A

1/Transfer R5-1100

B 2 -

C 3 -

D 4726A

E* 4726A

1 -

S3-369

A

1/Aft R5-1101

B 2 -

C 3 -

D 4727A

E* 4727A

1 -

S3-371

A

2/Forward R5-1105

B 2 -

C 3 -

D 5009A

E* 5009A

1 -

S3-372

A

2/Left Aft R5-1104

B 2 -

C 3 -

D 4728A

E* 4728A

1 -

S3-374

A

2/Transfer R5-1099

B 2 -

C 3 -

D 6078A

E* 6078A

1 -

S3-373

A

2/Right Aft R5-1103

B 2 -

C 3 -

D 4821A

E* 4821A

APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 02, 2009

MD11-28A143

40 of 44

BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
ALL GROUPS:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-377

A

3/Forward R5-1106

B 2 -

C 3 -

D 6022A

E* 6022A

1 -

S3-376

A

3/Transfer R5-1107

B 2 -

C 3 -

D 4823A

E* 4823A

1 -

S3-375

A

3/Right Aft R5-1108

B 2 -

C 3 -

D 4822A

E* 4822A

1 -

S3-803

A

R5-1934 Center Aux/Left

Upper

B 2 -

C 3 -

D 4729A

E* 4729A

1 -

S3-802

A

R5-1933 Center Aux/Right

Upper

B 2 -

C 3 -

D 4824A

E* 4824A

1 -

S3-805

A

R5-1936 Center Aux/Left

Lower

B 2 -

C 3 -

D 4895A

E* 4895A

1 -

S3-804

A

R5-1935 Center Aux/Right

Lower

B 2 -

C 3 -

D 4894A

E* 4894A

1 -

S3-764

A

Tail/Left Transfer R5-2802

B 2 -

C 3 -

D 5 7043A

E* 5 7043A

APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351

(SHEET 2 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 02, 2009

MD11-28A143

41 of 44

BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
ALL GROUPS:

Ground Stud

Connector Terminal Strip Tank/Pump Number Socket Number Post

1 -

S3-765

A

R5-2800 Tail/Right Transfer

B 2 -

C 3 -

D 5 7043A

E* 5 7043A

1 -

S3-755

A

Tail/Altn R5-2801

B 2 -

C 3 -

D 5 7043A

E* 5 7043A

* E should read open during multimeter check.

GROUP 2:

Ground Stud Connector (Pump) ConnectorTank/Pump Number Socket Number Socket

A -

R5-9668

A

R5-1347 Forward Aux

Right

B B -

C C -

D D 9079A

E* E* 9079A

A -

R5-9669

A

Forward Aux Left R5-1348

B B -

C C -

D D 9078A

E* E* 9078A

* E should read open during multimeter check.

GROUP 2:

Tank/Pump Location Relay Terminal

Forward Aux Right R2-110 A1

B1

C1

Forward Aux Left R2-109 A1

B1

C1

APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351

(SHEET 3 OF 3)

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Original Issue: December 02, 2009

MD11-28A143

42 of 44

BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
APPENDIX D: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER

60-84355-1 INSPECTION LOGIC DIAGRAM

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 02, 2009

MD11-28A143

43 of 44

BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT
APPENDIX E: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER

60-84351 INSPECTION LOGIC DIAGRAM

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 02, 2009

MD11-28A143

44 of 44

BOEING SERVICE BULLETIN MD11-28A143

ALERT ALERT