Commercial 

Airplanes MD11

Service Bulletin

Number: MD11-28-132

Original Issue: November 25, 2008

Revision 1: July 06, 2010

ATA System: 2800

SUBJECT: FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses

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

CFR 730-774). 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 © 2008 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable

subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

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

Treatment of the document and the information it contains is governed by contract with Boeing. For more

information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,

BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the

Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in

connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

1 of 45

2.0
BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

2 of 45

BOEING SERVICE BULLETIN MD11-28-132

BLANK PAGE
Table of Contents

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

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

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

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

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

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

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

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

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

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

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

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 13

4. Process Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 22

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

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

Appendix A: FUEL TANK 1 [Group 1-4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

Appendix B: FUEL TANK 2 [Group 1-4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

Appendix C: FUEL TANK 3 [Group 1-4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

Appendix D: UPPER AND LOWER AUXILIARY FUEL TANKS [Group 1-4] . . . . . . . . . . . . . . . . 33

Appendix E: TAIL FUEL TANK [Group 1-4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

Appendix F: FORWARD AUXILIARY FUEL TANK [Group 2] . . . . . . . . . . . . . . . . . . . . . . . 35

Appendix G: FORWARD AUXILIARY FUEL TANK [Group 3] . . . . . . . . . . . . . . . . . . . . . . . 36

Appendix H: FORWARD AUXILIARY FUEL TANK NO. 1 STATION 1044.437 AND NO. 2 STATION 1124.437

[Group 4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

Appendix I: FUEL TESTS [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

3 of 45

BOEING SERVICE BULLETIN MD11-28-132
Appendix J: FUEL TESTS [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40

Appendix K: FUEL TESTS [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

Appendix L: FUEL TESTS [Group 4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

4 of 45

BOEING SERVICE BULLETIN MD11-28-132
Commercial 

Airplanes MD11

Service Bulletin

Revision Transmittal Sheet Number: MD11-28-132

Original Issue: November 25, 2008

Revision 1: July 06, 2010

ATA System: 2800

SUBJECT: FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on the airplane(s) changed in accordance with the original issue of this service

bulletin.

Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2010-NM-003-AD, is related to this

service bulletin.

Airplane fuselage number 0608 was moved to Group 1 from Group 3 of this service bulletin effectivity.

REASON FOR REVISION

This revision is sent to incorporate changes outlined in Information Notices (IN)s MD11-28-132 IN 01, IN 02 and

IN 03.

The data given in Information Notices (IN)s MD11-28-132 IN 01, IN 02 and IN 03, is included in this revision.

These sections were changed:

1. In Paragraph 1.D., Description, added Maintenance Zone table.

2. In Paragraph 1.E., Compliance, added Federal Aviation Administration (FAA) Notice of Proposed Rule

Making 2010-NM-003-AD and changed recommended compliance statement.

3. In Paragraph 1.F., Approval, changed statement.

4. In Paragraph 1.J.1., Existing Data, added Federal Aviation Administration (FAA) Notice of Proposed Rule

Making 2010-NM-003-AD.

5. In Paragraph 1.H., Weight and Balance Changes, changed values.

6. In Paragraph 1.K.1., Publications, changed Aircraft Maintenance Manual and Fault Isolation Manual

chapter-section.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

5 of 45
7. In Paragraph 1.K.2., Damage Tolerance Based Structural Inspections, added statement.

8. In Paragraph 2.A., Material - Price and Availability, changed pricing data.

9. In Paragraph 2.C.1., Kit/Parts, changed wire kit number for Groups 1 through 4, Group 3 top kit number

and AEPL drawing number.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: November 25, 2008

Revision 1: July 06, 2010

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

6 of 45

BOEING SERVICE BULLETIN MD11-28-132
Commercial 

Airplanes MD11

Service Bulletin

Summary Number: MD11-28-132

Original Issue: November 25, 2008

Revision 1: July 06, 2010

ATA System: 2800

SUBJECT: FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses

CONCURRENT REQUIREMENTS

None.

BACKGROUND

An investigation by Boeing has determined that float level switch wires located on the left and right wing forward

spar, right main landing gear wheel well, horizontal stabilizer front spar, empennage, and forward cargo

compartment are routed in the same bundles as power wires. If a short circuit between a float level switch wire

and a power wire occurs, an over current can cause excessive temperatures in the float level switch wires,

resulting in damage. Adding an in-line fuse as a self-contained component in each float level switch circuit and

sleeving the wires between the fuel tank and the in-line fuse will minimize the possibility of excessive temperatures

in the float level switch wires. If not corrected, and there is a short circuit of the float level switch wire to a power

wire, possible damage to the float level switch wire could occur, and become a potential ignition source for the

fuel tank.

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.

ACTION

This service bulletin installs fuel tank float level switch in-line fuses.

EFFECTIVITY

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

COMPLIANCE

Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2010-NM-003-AD, is related to this

service bulletin.

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.

Boeing recommends that the operators do this service bulletin within 5 years after the original issue date on this

service bulletin.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

7 of 45
INDUSTRY SUPPORT INFORMATION

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

MANPOWER

Refer to Paragraph 1.G, for Manpower information.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

8 of 45

BOEING SERVICE BULLETIN MD11-28-132
Commercial 

Airplanes MD11

Service Bulletin

Number: MD11-28-132

Original Issue: November 25, 2008

Revision 1: July 06, 2010

ATA System: 2800

SUBJECT: FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below.

NOTE: When any Group 3 or 4 passenger airplane shown below is modified to a freighter

configuration by Boeing Passenger to Freighter (P to F) engineering, it will become a

Group 1 airplane.

GROUP CONFIGURATION DESCRIPTION

Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower

auxiliary, and tail configuration.

1 -

Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower

auxiliary, foward auxiliary, tail, and unique wiring configuration.

2 -

Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower

auxiliary, foward auxiliary, tail, and unique wiring configuration.

3 -

Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower

auxiliary, foward auxiliary No. 1, foward auxiliary No. 2, and tail

configuration.

4 -

Airplane Models:

MD-11, MD-11F

Fuselage Num- Group

ber

447 - 449 1

451 - 464 1

466 - 489 1

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

9 of 45
Fuselage Num- Group

ber

491 - 517 1

519 - 531 1

532 4

533 - 543 1

544 4

545 - 552 1

554 - 589 1

590 2

591 - 596 1

597 3

598 - 646 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

An investigation by Boeing has determined that float level switch wires located on the left and right

wing forward spar, right main landing gear wheel well, horizontal stabilizer front spar, empennage, and

forward cargo compartment are routed in the same bundles as power wires. If a short circuit between

a float level switch wire and a power wire occurs, an over current can cause excessive temperatures

in the float level switch wires, resulting in damage. Adding an in-line fuse as a self-contained component

in each float level switch circuit and sleeving the wires between the fuel tank and the in-line fuse will

minimize the possibility of excessive temperatures in the float level switch wires. If not corrected, and

there is a short circuit of the float level switch wire to a power wire, possible damage to the float level

switch wire could occur, and become a potential ignition source for the fuel tank.

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.

Revision 1 is sent to incorporate changes outlined in Information Notices (IN)s MD11-28-132 IN 01, IN

02 and IN 03.

The data given in Information Notices (IN)s MD11-28-132 IN 01, IN 02 and IN 03, is included in this

revision.

D. Description

This service bulletin installs fuel tank float level switch in-line fuses.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

10 of 45

BOEING SERVICE BULLETIN MD11-28-132
Revision 1 - No more work is necessary on the airplane(s) changed in accordance with the original

issue of this service bulletin.

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

Group 1:

Affected Maintenance Zones

Model Zone

144, 145, 146, 371, 516, 518, 525, 526, 527,

618, 625, 626, 627

MD-11, MD-11F

Group 2-4:

Affected Maintenance Zones

Model Zone

123, 144, 145, 146, 254, 371, 516, 518, 525,

526, 527, 618, 625, 626, 627

MD-11

E. Compliance

Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2010-NM-003-AD, is related

to this service bulletin.

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.

Boeing recommends that the operators do this service bulletin within 5 years after the original issue

date on this service bulletin.

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.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

11 of 45

BOEING SERVICE BULLETIN MD11-28-132
G. Manpower

The table below shows an estimate of the task hours necessary to do this modification 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 examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Group 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 21.0 10.5

Change 2 125.0 62.5

Test 2 6.0 3.0

Close Access 2 25.0 12.5

TOTAL FOR EACH AIRPLANE 177.0 88.5

Group 2-3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 21.0 10.5

Change 2 132.0 66.0

Test 2 6.2 3.1

Close Access 2 25.0 12.5

TOTAL FOR EACH AIRPLANE 184.2 92.1

Group 4:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 21.0 10.5

Change 1 135.2 67.6

Test 2 6.6 3.3

Close Access 2 25.0 12.5

TOTAL FOR EACH AIRPLANE 187.8 93.9

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

12 of 45

BOEING SERVICE BULLETIN MD11-28-132
H. Weight and Balance Changes

Moment Change

(MEW) IN.-LBS

Mfr's Empty Weight

(MEW) LBS

Approximate Station

(Inches)

Airplane

Group

1 1511.8 +6.7 +10129.1

2 and 3 1541.0 +7.0 +10787.0

4 1475.8 +7.1 +10478.2

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. MD-11-1F Structural Repair Manual (SRM) 51-00-01.

b. MD-11-1P Structural Repair Manual (SRM) 51-00-01.

c. MD-11 Aircraft Maintenance Manual (AMM) 06-28-00, 06-32-34, 06-33-00, 06-35-00, 06-36-00,

12-11-03, 28-14-01 and 28-00-00.

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

20-10-04, 20-20-02, 20-20-03 and 20-40-01.

e. Wire Diagram Manual (WDM) 28-21-01, 28-22-06, 28-22-07, 28-22-08, 28-43-01, 28-43-02,

and 28-46-01.

f. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)

2010-NM-003-AD.

2. Data supplied with this Service Bulletin:

None.

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

None.

4. Process Data:

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

since these procedures are frequently used as standard shop practices.

K. Publications Affected

1. Publications:

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

13 of 45

BOEING SERVICE BULLETIN MD11-28-132
Publication Chapter-Section

28-14, 28-21, 28-30, 28-40, 28-43, 28-46

and 36-14

Aircraft Maintenance Manual

Fault Isolation Manual 28-14, 36-23

Illustrated Parts Catalog 28-42 and 28-43

Wiring Diagram Manual 28-21, 28-22, 28-43 and 28-46

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

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

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

14 of 45

BOEING SERVICE BULLETIN MD11-28-132
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

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

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

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

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

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

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

Revision 1 date of

this Service Bulletin (US Dollars)

ROLT as of Revision 1 date of this

Service Bulletin

(Calendar Days)

Kit Number Name Date QTY

SB11280132-3 Service Kit 1 90 $9,951.00

SB11280132-5 Service Kit 1 90 10,212.00

SB11280132-7 Service Kit 1 90 10,541.00

B. Industry Support Information

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

C. Parts Necessary For Each Airplane

1. Kits/Parts:

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

Group 1:

Kit SB11280132

New Part Number QTY Name Notes

-3

3D0005-08-10 7 SCREW (a)

3D0005-08-8 37 SCREW (a)

3D0005-3-22 5 SCREW (a)

3D0005-3-26 8 SCREW (a)

3D0005-3-28 3 SCREW (a)

3D0005-3-8 2 SCREW (a)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

15 of 45

BOEING SERVICE BULLETIN MD11-28-132
Group 1:

Kit SB11280132

New Part Number QTY Name Notes

-3

5D0086-3 6 TERMINAL LUG 878 (a)

5D0086-6 11 TERMINAL LUG 762 (a)

5D0206-20 48 SEALING PLUG (a)

65053-220 24 IN-LINE FUSE

ANN0012-1 1 BRACKET ASSEMBLY

M39029/22-192 3 SOCKET T/C 524

MS18029-6S8 1 COVER ASSEMBLY

MS20470AD4-5D 2 RIVET

MS20470AD5-5D 4 RIVET

MS21042L08 74 NUT

MS21042L3 2 NUT

MS21919WDG10 4 CLAMP

MS21919WDG3 6 CLAMP

MS21919WDG5 2 CLAMP

MS21919WDG7 2 CLAMP

MS27212-6-8 1 TERMINAL BOARD

MS35338-42 37 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10H 6 WASHER

NAS1252-10L 55 WASHER

NAS1252-8H 7 WASHER

NAS1252-8L 118 WASHER

NAS43DD3-48FC 5 SPACER

NAS43DD3-64FC 8 SPACER

NAS43DD3-72FC 3 SPACER

NAS620A4 3 WASHER

NAS7700-3 3 BOLT

S7934111-2SA 1 CLAMP (a)

S7934111-3SA 21 CLAMP (a)

S7934111-4SA 5 CLAMP (a)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

16 of 45

BOEING SERVICE BULLETIN MD11-28-132
Group 1:

Kit SB11280132

New Part Number QTY Name Notes

-3

S7934111-5SA 3 CLAMP (a)

S7934111-6SA 1 CLAMP (a)

S7934111-7SA 4 CLAMP (a)

S7934111-8SA 1 CLAMP (a)

S7934111-9SA 24 CLAMP (a)

SR11280063-103 1 WIRE KIT

SR11280063-104 1 WIRE KIT

SR11280063-105 1 WIRE KIT

136 FT X SLEEVING

.166 I.D.

SR11280063-3(DMS

2109, Type 1) or

equivalent

SR11280063-7 (DMS 50 YD TIE TAPE

2089) or equivalent

TA4012B12 1 BRACKET

TA4012F21 2 BRACKET

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

Group 1:

Wire Kit SR11280063

New Part Number QTY QTY QTY Name Notes

-103 -104 -105

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

DC2426-1C-20NM (DMS 2426) - 14 FT 14 FT WIRE CODE 801

or equivalent

DC2426-1C-22NM (DMS 2426) 26FT - 158 FT WIRE CODE 801

or equivalent

M39029/22-192 4 7 33 SOCKET T/C 524

5D0086-3 - - 4 TERMINAL LUG 878 (a)

5D0086-6 4 6 29 TERMINAL LUG 762 (a)

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

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

17 of 45

BOEING SERVICE BULLETIN MD11-28-132
Group 2-3:

Kit SB11280132

New Part Number QTY Name Notes

-5

3D0005-08-10 7 SCREW (a)

3D0005-08-12 1 SCREW (a)

3D0005-08-8 38 SCREW (a)

3D0005-3-22 5 SCREW (a)

3D0005-3-26 8 SCREW (a)

3D0005-3-28 3 SCREW (a)

3D0005-3-8 2 SCREW (a)

5D0086-3 6 TERMINAL LUG 878 (a)

5D0086-6 11 TERMINAL LUG 762 (a)

5D0206-20 50 SEALING PLUG (a)

65053-220 25 IN-LINE FUSE

9D0254-1-1-9 5 STRAP (a)

ANN0012-1 1 BRACKET ASSEMBLY

M39029/22-192 4 SOCKET T/C 524

MS18029-6S8 1 COVER ASSEMBLY

MS20470AD4-5D 4 RIVET

MS20470AD5-5D 4 RIVET

MS21042L08 76 NUT

MS21042L3 2 NUT

MS21919WDG10 4 CLAMP

MS21919WDG3 6 CLAMP

MS21919WDG5 2 CLAMP

MS21919WDG7 2 CLAMP

MS27212-6-8 1 TERMINAL BOARD

MS35338-42 37 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10H 6 WASHER

NAS1252-10L 55 WASHER

NAS1252-8H 7 WASHER

NAS1252-8L 122 WASHER

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

18 of 45

BOEING SERVICE BULLETIN MD11-28-132
Group 2-3:

Kit SB11280132

New Part Number QTY Name Notes

-5

NAS43DD3-48FC 5 SPACER

NAS43DD3-64FC 8 SPACER

NAS43DD3-72FC 3 SPACER

NAS620A4 3 WASHER

NAS7700-3 3 BOLT

NMC1001-2 1 CLAMP (a)

S7934111-2SA 1 CLAMP (a)

S7934111-3SA 21 CLAMP (a)

S7934111-4SA 5 CLAMP (a)

S7934111-5SA 3 CLAMP (a)

S7934111-6SA 1 CLAMP (a)

S7934111-7SA 4 CLAMP (a)

S7934111-8SA 1 CLAMP (a)

S7934111-9SA 25 CLAMP (a)

SR11280063-101 1 WIRE KIT

SR11280063-103 1 WIRE KIT

SR11280063-104 1 WIRE KIT

SR11280063-105 1 WIRE KIT

136 FT X SLEEVING

.166 I.D.

SR11280063-3(DMS

2109, Type 1) or

equivalent

15 FT X 3/16 SLEEVE

I.D.

SR11280063-5 (DMS

2379, Class 4) or

equivalent

SR11280063-7 (DMS 50 YD TIE TAPE

2089) or equivalent

TA4012B12 2 BRACKET

TA4012F21 2 BRACKET

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

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

19 of 45

BOEING SERVICE BULLETIN MD11-28-132
Group 2-3:

Wire Kit SR11280063

New Part Number QTY QTY QTY QTY Name Notes

-101 -103 -104 -105

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

DC2426-1C-20NM (DMS - - 14 FT 14 FT WIRE CODE 801

2426) or equivalent

DC2426-1C-22NM (DMS 2 FT 26 FT - 158 FT WIRE CODE 801

2426) or equivalent

M39029/22-192 1 4 7 33 SOCKET T/C 524

5D0086-3 - - - 4 TERMINAL LUG 878 (a)

5D0086-6 - 4 6 29 TERMINAL LUG 762 (a)

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

Group 4:

Kit SB11280132

New Part Number QTY Name Notes

-7

3D0005-08-10 7 SCREW (a)

3D0005-08-12 2 SCREW (a)

3D0005-08-8 39 SCREW (a)

3D0005-3-22 5 SCREW (a)

3D0005-3-26 8 SCREW (a)

3D0005-3-28 3 SCREW (a)

3D0005-3-8 2 SCREW (a)

5D0086-3 6 TERMINAL LUG 878 (a)

5D0086-6 11 TERMINAL LUG 762 (a)

5D0206-20 52 SEALING PLUG (a)

65053-220 26 IN-LINE FUSE

9D0062-1-16-10 2 BRACKET (a)

ANN0012-1 1 BRACKET ASSEMBLY

M39029/22-192 5 SOCKET T/C 524

MS18029-6S8 1 COVER ASSEMBLY

MS20470AD4-5D 6 RIVET

MS20470AD5-5D 4 RIVET

MS21042L08 78 NUT

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

20 of 45

BOEING SERVICE BULLETIN MD11-28-132
Group 4:

Kit SB11280132

New Part Number QTY Name Notes

-7

MS21042L3 2 NUT

MS21919WDG10 4 CLAMP

MS21919WDG3 6 CLAMP

MS21919WDG4 2 CLAMP

MS21919WDG5 2 CLAMP

MS21919WDG7 2 CLAMP

MS27212-6-8 1 TERMINAL BOARD

MS35338-42 37 LOCKWASHER

MS35338-43 2 LOCKWASHER

NAS1252-10H 6 WASHER

NAS1252-10L 55 WASHER

NAS1252-8H 7 WASHER

NAS1252-8L 126 WASHER

NAS43DD3-48FC 5 SPACER

NAS43DD3-64FC 8 SPACER

NAS43DD3-72FC 3 SPACER

NAS620A4 3 WASHER

NAS7700-3 3 BOLT

NMC1001-2 2 CLAMP (a)

S7934111-2SA 1 CLAMP (a)

S7934111-3SA 21 CLAMP (a)

S7934111-4SA 5 CLAMP (a)

S7934111-5SA 3 CLAMP (a)

S7934111-6SA 1 CLAMP (a)

S7934111-7SA 4 CLAMP (a)

S7934111-8SA 1 CLAMP (a)

S7934111-9SA 26 CLAMP (a)

SR11280063-102 1 WIRE KIT

SR11280063-103 1 WIRE KIT

SR11280063-104 1 WIRE KIT

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

21 of 45

BOEING SERVICE BULLETIN MD11-28-132
Group 4:

Kit SB11280132

New Part Number QTY Name Notes

-7

SR11280063-105 1 WIRE KIT

136 FT X SLEEVING

.166 I.D.

SR11280063-3(DMS

2109, Type 1) or

equivalent

15 FT X 3/16 SLEEVE

I.D.

SR11280063-5 (DMS

2379, Class 4) or

equivalent

SR11280063-7 (DMS 50 YD TIE TAPE

2089) or equivalent

TA4012B12 1 BRACKET

TA4012F21 2 BRACKET

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

Group 4:

Wire Kit SR11280063

New Part Number QTY QTY QTY QTY Name Notes

-102 -103 -104 -105

DC39-20S 2 - 1 - SOCKET T/C 1124

DC2426-1C-20NM (DMS - - 14 FT 14 FT WIRE CODE 801

2426) or equivalent

DC2426-1C-22NM (DMS - 26 FT - 158 FT WIRE CODE 801

2426) or equivalent

DC2426-1C-24NM (DMS 4 FT - WIRE CODE 801

2426) or equivalent

M39029/22-192 2 4 7 33 SOCKET T/C 524

5D0086-3 - - - 4 TERMINAL LUG 878 (a)

5D0086-6 - 4 6 29 TERMINAL LUG 762 (a)

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

2. Parts and Materials Supplied by the Operator:

None.

3. Parts Modified and Reidentified:

None.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

22 of 45

BOEING SERVICE BULLETIN MD11-28-132
4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

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

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

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

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

23 of 45

BOEING SERVICE BULLETIN MD11-28-132
BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

24 of 45

BOEING SERVICE BULLETIN MD11-28-132

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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.

WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY

ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE

PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE

CAN OCCUR.

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

TO THE AIRPLANE OR EQUIPMENT.

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

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

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

OTHER ELECTRICAL DAMAGE.

NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions give the recommended

sequence of steps. The sequence of steps to do this service bulletin can be changed.

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

definition of the acronyms.

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

4. Use the approved fastener and process material substitutions, MD-11-1F SRM

51-00-01, and MD-11-1P SRM 51-00-01.

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

against nearby wire assemblies or components.

6. 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.

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

Chapter Operation

SWPM 20-00-00 General - Maintenance Safety Practices

SWPM 20-00-09 Electrical Identification and Shop Practices

SWPM 20-00-13 Electrical Wire Codes

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

25 of 45

BOEING SERVICE BULLETIN MD11-28-132
SWPM 20-00-16 Electrical Wire End Termination Codes

Fabricating and Installing Wire Harness -

Commercial

SWPM 20-10-01

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

SWPM 20-20-02 Terminal Blocks - Maintenance Practices

General Installation Hardwares - Maintenance

Practices

SWPM 20-20-03

Power Distribution Bus - Maintenance PracticeSWPM 20-40-01

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

applicable.

9. Review and understand all general notes of Service Rework Drawing SR11280063

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

modification.

10. These work instructions refer to procedures included on 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.

B. WORK INSTRUCTIONS

Group 1:

1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to

MD-11 AMM 28-14-01 as an accepted procedure.

2. Gain access to area of modification, refer to Table below:

Panel Number Name/Location Refer to

Access Panel Left Wing MD-11 AMM 06-35-00

Leading Edge

516AB, 516DB, 516EB,

518AB, 518BB, 518CB,

518GB, 525DB, 526DB,

526FB, 527AB

Access Panel Right Wing MD-11 AMM 06-36-00

Leading Edge

618BB, 618CB, 618GB,

625DB, 626DB, 627AB

Right Main Landing Gear MD-11 AMM 06-28-00

Wheel Well

Right Main Landing Gear

Door

Horizontal Stabilizer/fuel, MD-11 AMM 06-33-00

jack screw, and motors

311AB

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices:

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

26 of 45

BOEING SERVICE BULLETIN MD11-28-132
Location In Accordance with Appendix

Fuel Tank 1 A

Fuel Tank 2 B

Fuel Tank 3 C

Upper and Lower Auxiliary Fuel Tanks D

Tail Fuel Tank E

4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix I.

5. Close access to area of modification.

6. Put the airplane back to a serviceable condition.

Group 2:

1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to

MD-11 AMM 28-14-01 as an accepted procedure.

2. Gain access to area of modification, refer to Table below:

Panel Number Name/Location Refer to

Access Panel Left Wing MD-11 AMM 06-35-00

Leading Edge

516AB, 516DB, 516EB,

518AB, 518BB, 518CB,

518GB, 525DB, 526DB,

526FB, 527AB

Access Panel Right Wing MD-11 AMM 06-36-00

Leading Edge

618BB, 618CB, 618GB,

625DB, 626DB, 627AB

Right Main Landing Gear MD-11 AMM 06-28-00

Wheel Well

Right Main Landing Gear

Door

Horizontal Stabilizer/fuel, MD-11 AMM 06-33-00

jack screw, and motors

311AB

Cabin Floor Panels Station MD-11 AMM 06-32-34

979 to 6-70

253GF, 253HF

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices:

Location In accordance with Appendix

Fuel Tank 1 A

Fuel Tank 2 B

Fuel Tank 3 C

Upper and Lower Auxiliary Fuel Tanks D

Tail Fuel Tank E

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

27 of 45

BOEING SERVICE BULLETIN MD11-28-132
Location In accordance with Appendix

Forward Auxiliary Fuel Tank F

4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix J.

5. Close access to area of modification.

6. Put the airplane back to a serviceable condition.

Group 3:

1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to

MD-11 AMM 28-14-01 as an accepted procedure.

2. Gain access to area of modification, refer to Table below:

Panel Number Name/Location Refer to

Access Panel Left Wing MD-11 AMM 06-35-00

Leading Edge

516AB, 516DB, 516EB,

518AB, 518BB, 518CB,

518GB, 525DB, 526DB,

526FB, 527AB

Access Panel Right Wing MD-11 AMM 06-36-00

Leading Edge

618BB, 618CB, 618GB,

625DB, 626DB, 627AB

Right Main Landing Gear MD-11 AMM 06-28-00

Wheel Well

Right Main Landing Gear

Door

Horizontal Stabilizer/fuel, MD-11 AMM 06-33-00

jack screw, and motors

311AB

Cabin Floor Panels Station MD-11 AMM 06-32-34

979 to 6-70

253GF, 253HF

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices:

Location In accordance with Appendix

Fuel Tank 1 A

Fuel Tank 2 B

Fuel Tank 3 C

Upper and Lower Auxiliary Fuel Tanks D

Tail Fuel Tank E

Forward Auxiliary Fuel Tank G

4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix K.

5. Close access to area of modification.

6. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

28 of 45

BOEING SERVICE BULLETIN MD11-28-132
Group 4:

1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to

MD-11 AMM 28-14-01 as an accepted procedure.

2. Gain access to area of modification, refer to Table below:

Panel Number Name/Location Refer to

Access Panel Left Wing MD-11 AMM 06-35-00

Leading Edge

516AB, 516DB, 516EB,

518AB, 518BB, 518CB,

518GB, 525DB, 526DB,

526FB, 527AB

Access Panel Right Wing MD-11 AMM 06-36-00

Leading Edge

618BB, 618CB, 618GB,

625DB, 626DB, 627AB

Right Main Landing Gear MD-11 AMM 06-28-00

Wheel Well

Right Main Landing Gear

Door

Horizontal Stabilizer/fuel, MD-11 AMM 06-33-00

jack screw, and motors

311AB

Cabin Floor Panels Station MD-11 AMM 06-32-34

979 to 6-70

253DF, 253EF, 253GF,

253HF

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices:

Location In accordance with Appendix

Fuel Tank 1 A

Fuel Tank 2 B

Fuel Tank 3 C

Upper and Lower Auxiliary Fuel Tanks D

Tail Fuel Tank E

Forward Auxiliary Fuel Tanks No. 1 and 2 H

4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix L.

5. Close access to area of modification.

6. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1: July 06, 2010 MD11-28-132

29 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 1-4.

STEP DESCRIPTION OF TASK MORE DATA

In accordance with Drawing SR11280063 sheets

10, 11, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,

9.8, 105.201 and 305.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-119 within

float level switch reference designator

S1-119 wiring.

1

In accordance with Drawing SR11280063 sheets

10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7,

3.8, 9.7, 9.8, 105.201, 305.201 and 306.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-120 within

float level switch reference designator

S1-120 wiring.

2

In accordance with Drawing SR11280063 sheets

10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7,

3.8, 9.7, 9.8, 105.201 and 305.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-121 within

float level switch reference designator

S1-121 wiring.

3

In accordance with Drawing SR11280063 sheets

10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7,

3.8, 9.7, 9.9, 105.201, 305.202 and 306.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-176 within

float level switch reference designator

S1-176 wiring.

4

In accordance with Drawing SR11280063 sheets

10, 14, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,

9.9, 105.201 and 306.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-1391

within float level switch reference designator S1-1391 wiring.

5

In accordance with Drawing SR11280063 sheets

10, 13, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.9,

105.201 and 305.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-1392

within float level switch reference designator S1-1392 wiring.

6

In accordance with Drawing SR11280063 sheets

10, 12, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,

9.10, 105.201 and 305.202.

Install fuel tank float level switch In-line

fuse, reference designator F1-735 within

float level switch reference designator

S1-735 wiring.

7

Appendix A: FUEL TANK 1

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

30 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 1-4.

STEP DESCRIPTION OF TASK MORE DATA

In accordance with Drawing SR11280063

sheets 16, 16.3, 3, 3.1, 3.3, 3.5, 3.6 and 3.8.

Install new Terminal Board, item number

S3-454.

1

In accordance with Drawing SR11280063

sheets 10, 16, 16.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5,

3.6, 3.7, 3.8, 9.7, 9.11, 105.201 and 305.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-90 within

float level switch reference designator S1-

90 wiring.

2

In accordance with Drawing SR11280063

sheets 10, 16, 16.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5,

3.6, 3.7, 3.8, 9.7, 9.11, 105.201 and 305.202.

Install fuel tank float level switch In-line

fuse, reference designator F1-177 within

float level switch reference designator S1-

177 wiring.

3

In accordance with Drawing SR11280063

sheets 10, 16, 16.1, 16.2, 3, 3.1, 3.2, 3.3, 3.4,

3.5, 3.6, 3.7, 9.7, 9.11, 105.201 and 305.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-1363 within

float level switch reference designator S1-

1363 wiring.

4

In accordance with Drawing SR11280063

sheets 10, 16, 16.1, 16.2, 3, 3.1, 3.2, 3.3, 3.4,

3.5, 3.6, 3.7, 3.8, 9.7, 9.12, 105.201 and

305.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-1393 within

float level switch reference designator S1-

1393 wiring.

5

Appendix B: FUEL TANK 2

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

31 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 1-4.

STEP DESCRIPTION OF TASK MORE DATA

In accordance with Drawing SR11280063 sheets

10, 17, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,

9.13, 105.201 and 305.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-124

within level switch reference designator

S1-124 wiring.

1

In accordance with Drawing SR11280063 sheets

10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8,

9.7, 9.13, 105.201 and 305.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-122

within float level switch reference designator S1-122 wiring.

2

In accordance with Drawing SR11280063 sheets

10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8,

9.7, 9.13, 105.201 305.201 and 307.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-123

within float level switch reference designator S1-123 wiring.

3

In accordance with Drawing SR11280063 sheets

10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8,

9.7, 9.14, 105.201, 305.202 and 307.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-178

within float level switch reference designator S1-178 wiring.

4

In accordance with Drawing SR11280063 sheets

10, 20, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,

9.14, 105.201 and 307.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-1394

within float level switch reference designator S1-1394 wiring.

5

In accordance with Drawing SR11280063 sheets

10, 19, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,

9.15, 105.201 and 305.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-1395

within float level switch reference designator S1-1395 wiring.

6

In accordance with Drawing SR11280063 sheets

10, 18, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,

9.15, 105.201 and 305.202.

Install fuel tank float level switch In-line

fuse, reference designator F1-734

within float level switch reference designator S1-734 wiring.

7

Appendix C: FUEL TANK 3

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

32 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 1-4.

STEP DESCRIPTION OF TASK MORE DATA

In accordance with Drawing

SR11280063 sheets 10, 22, 3, 3.1, 3.2,

3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.16,

103.201 and 303.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-1359 within

float level switch reference designator S1-

1359 wiring.

1

In accordance with Drawing

SR11280063 sheets 10, 23, 3, 3.1, 3.2,

3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 9.7, 9.16,

103.201 and 303.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-1360 within

float level switch reference designator S1-

1360 wiring.

2

Appendix D: UPPER AND LOWER AUXILIARY FUEL TANKS

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

33 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 1-4.

STEP DESCRIPTION OF TASK MORE DATA

In accordance with Drawing SR11280063

sheets 10, 24, 24.1, 3, 3.1, 3.2, 3.3, 3.4,

3.5, 3.6, 3.7, 3.8, 9.7, 9.17, 104.201 and

304.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-1396 within

float level switch reference designator S1-

1396 wiring.

1

In accordance with Drawing SR11280063

sheets 10, 24, 24.2, 3, 3.1, 3.2, 3.4, 3.5,

3.6, 3.7, 3.8, 9.7, 9.17, 104.201 and

304.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-1397 within

float level switch reference designator S1-

1397 wiring.

2

Install fuel tank float level switch In-line

fuse, reference designator F1-1398 within

float level switch reference designator S1-

1398 wiring.

3

In accordance with Drawing SR11280063

sheets 10, 25, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6,

3.7, 3.8, 9.7, 9.18, 104.201 and 304.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-1399 within

float level switch reference designator S1-

1399 wiring.

4

Appendix E: TAIL FUEL TANK

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

34 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 2.

STEP DESCRIPTION OF TASK MORE DATA

In accordance with Drawing SR11280063

sheets 10, 26, 26.1, 3, 3.1, 3.2, 3.3, 3.4,

3.5, 3.6, 3.7, 3.8, 3.10, 9.7, 9.20, 101.201

and 302.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-631 within

float level switch reference designator

S1-631 wiring.

1

Appendix F: FORWARD AUXILIARY FUEL TANK

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

35 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 3.

STEP DESCRIPTION OF TASK MORE DATA

In accordance with Drawing SR11280063

sheets 10, 26, 26.1, 3, 3.1, 3.2, 3.3, 3.4,

3.5, 3.6, 3.7, 3.8, 3.10, 9.7, 9.20, 101.201

and 301.201.

Install fuel tank float level switch In-line

fuse, reference designator F1-631 within

float level switch reference designator

S1-631 wiring.

1

Appendix G: FORWARD AUXILIARY FUEL TANK

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

36 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 4.

STEP DESCRIPTION OF TASK MORE DATA

In accordance with Drawing SR11280063

sheets 10, 27, 27.1, 27.2, 27.3, 3, 3.1, 3.2,

3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.19,

102.201 and 308.201.

Install bracket and fuel tank float level

switch In-line fuse, reference designator

F1-191 within float level switch reference designator S1-191 wiring.

1

In accordance with Drawing SR11280063

sheets 10, 27, 27.1, 27.2, 27.3, 3, 3.1, 3.2,

3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.19,

102.201 and 308.201.

Install bracket and fuel tank float level

switch In-line fuse, reference designator

F1-243 within float level switch reference designator S1-243 wiring.

2

Appendix H: FORWARD AUXILIARY FUEL TANK NO. 1 STATION 1044.437 AND NO. 2 STATION 1124.437

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

37 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 1.

RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

This test can be performed for each float switch circuit independently as the fuse is installed.

REFERENCES (AMM) Tasks:

MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT

This procedure should be used as necessary.

Depower the Fuel system and open the related C/Bs.

After fuse installation do a continuity test as shown in the table below.

Note: For some fuses check continuity between two pins, for others check continuity to ground.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 1

F1-176 - TANK 1 DUMP LOOP CONTINUITY S3-450 7 & 8

F1-121 Tank 1 4000 lb LOOP CONTINUITY S3-450 1 & 6

F1-120 Tank 1 6000 lb LOOP CONTINUITY S3-450 4 & 5

F1-1391 TK 1 INBD FULL LOOP CONTINUITY S3-1301 1 & 2

F1-1392 TK 1 OUTBD FULL LOOP CONTINUITY S3-1300 1 & 2

F1-119 TK 1 TIP LOOP CONT NOT FULL S3-366 1 & 3

F1-735 L WING OVERFILL LOOP CONTINUITY S3-684 1 & 2 VENT BOX

TANK 3

F1-178 - TANK 3 DUMP LOOP CONTINUITY S3-451 7 & 8

F1-122 Tank 3 4000 lb LOOP CONTINUITY S3-451 6 & 2

F1-123 Tank 3 6000 lb LOOP CONTINUITY S3-451 4 & 5

F1-1394 TK 3 INBD FULL LOOP CONTINUITY S3-1302 1 & 2

F1-1395 TK 3 OUTBD FULL LOOP CONTINUITY S3-1303 1 & 2

F1-124 TK 3 TIP LOOP CONT NOT FULL S3-452 2 & 3

F1-734 R WING OVERFILL LOOP CONTINUITY S3-683 1 & 2 VENT BOX

TANK 2

F1-177 TK 2 DUMP LOOP CONTINUITY S3-454 1 & 5

F1-90 TK 2 40000 LB LOOP CONTINUITY S3-454 4 & 6

F1-1363 TK 2 10000 LB CONT TO GND ON EMPTY S3-454 3

F1-1393 TK 2 FULL LOOP CONTINUITY S3-454 2 & 7

Appendix I: FUEL TESTS

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

38 of 45

BOEING SERVICE BULLETIN MD11-28-132
RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

TAIL TANK

F1-1396 TAIL TK EMPTY LOOP CONTINUITY S3-756 1 & 3

F1-1397 TAIL L FULL LOOP CONTINUITY S3-758 1 & 3

F1-1398 TAIL R FULL LOOP CONTINUITY S3-759 2 & 3

F1-1399 Tail Tank Vent box CONT BTW CONNECT S3-739 PIN 1JX VENT BOX

P1-930 PIN 3

AUX TANKS

F1-1359 UPPR AUX FULL LOOP CONTINUITY S3-1186 1 & 2

F1-1360 LWR AUX FULL LOOP CONTINUITY S3-805 4 & 5

Appendix I: FUEL TESTS

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

39 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 2.

RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

This test can be performed for each float switch circuit independently as the fuse is installed.

REFERENCES (AMM) Tasks:

MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT

This procedure should be used as necessary.

Depower the Fuel system and open the related C/Bs.

After fuse installation do a continuity test as shown in the table below.

Note: For some fuses check continuity between two pins, for others check continuity to ground.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 1

F1-176 - TANK 1 DUMP LOOP CONTINUITY S3-450 7 & 8

F1-121 Tank 1 4000 lb LOOP CONTINUITY S3-450 1 & 6

F1-120 Tank 1 6000 lb LOOP CONTINUITY S3-450 4 & 5

F1-1391 TK 1 INBD FULL LOOP CONTINUITY S3-1301 1 & 2

F1-1392 TK 1 OUTBD FULL LOOP CONTINUITY S3-1300 1 & 2

F1-119 TK 1 TIP LOOP CONT NOT FULL S3-366 1 & 3

F1-735 L WING OVERFILL LOOP CONTINUITY S3-684 1 & 2 VENT BOX

TANK 3

F1-178 - TANK 3 DUMP LOOP CONTINUITY S3-451 7 & 8

F1-122 Tank 3 4000 lb LOOP CONTINUITY S3-451 6 & 2

F1-123 Tank 3 6000 lb LOOP CONTINUITY S3-451 4 & 5

F1-1394 TK 3 INBD FULL LOOP CONTINUITY S3-1302 1 & 2

F1-1395 TK 3 OUTBD FULL LOOP CONTINUITY S3-1303 1 & 2

F1-124 TK 3 TIP LOOP CONT NOT FULL S3-452 2 & 3

F1-734 R WING OVERFILL LOOP CONTINUITY S3-683 1 & 2 VENT BOX

TANK 2

F1-177 TK 2 DUMP LOOP CONTINUITY S3-454 1 & 5

F1-90 TK 2 40000 LB LOOP CONTINUITY S3-454 4 & 6

F1-1363 TK 2 10000 LB CONT TO GND ON EMPTY S3-454 3

F1-1393 TK 2 FULL LOOP CONTINUITY S3-454 2 & 7

Appendix J: FUEL TESTS

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

40 of 45

BOEING SERVICE BULLETIN MD11-28-132
RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

TAIL TANK

F1-1396 TAIL TK EMPTY LOOP CONTINUITY S3-756 1 & 3

F1-1397 TAIL L FULL LOOP CONTINUITY S3-758 1 & 3

F1-1398 TAIL R FULL LOOP CONTINUITY S3-759 2 & 3

F1-1399 Tail Tank Vent box CONT BTW CONNECT S3-739 PIN 1JX VENT BOX

P1-930 PIN 3

AUX TANKS

F1-1359 UPPR AUX FULL LOOP CONTINUITY S3-1186 1 & 2

F1-1360 LWR AUX FULL LOOP CONTINUITY S3-805 4 & 5

FWD AUX TANK

F1-631 FWD AUX EMPTY CONT TO GND ON EMPTY R5-448 E

Appendix J: FUEL TESTS

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

41 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 3.

RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

This test can be performed for each float switch circuit independently as the fuse is installed.

REFERENCES (AMM) Tasks:

MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT

This procedure should be used as necessary.

Depower the Fuel system and open the related C/Bs.

After fuse installation do a continuity test as shown in the table below.

Note: For some fuses check continuity between two pins, for others check continuity to ground.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 1

F1-176 - TANK 1 DUMP LOOP CONTINUITY S3-450 7 & 8

F1-121 Tank 1 4000 lb LOOP CONTINUITY S3-450 1 & 6

F1-120 Tank 1 6000 lb LOOP CONTINUITY S3-450 4 & 5

F1-1391 TK 1 INBD FULL LOOP CONTINUITY S3-1301 1 & 2

F1-1392 TK 1 OUTBD FULL LOOP CONTINUITY S3-1300 1 & 2

F1-119 TK 1 TIP LOOP CONT NOT FULL S3-366 1 & 3

F1-735 L WING OVERFILL LOOP CONTINUITY S3-684 1 & 2 VENT BOX

TANK 3

F1-178 - TANK 3 DUMP LOOP CONTINUITY S3-451 7 & 8

F1-122 Tank 3 4000 lb LOOP CONTINUITY S3-451 6 & 2

F1-123 Tank 3 6000 lb LOOP CONTINUITY S3-451 4 & 5

F1-1394 TK 3 INBD FULL LOOP CONTINUITY S3-1302 1 & 2

F1-1395 TK 3 OUTBD FULL LOOP CONTINUITY S3-1303 1 & 2

F1-124 TK 3 TIP LOOP CONT NOT FULL S3-452 2 & 3

F1-734 R WING OVERFILL LOOP CONTINUITY S3-683 1 & 2 VENT BOX

TANK 2

F1-177 TK 2 DUMP LOOP CONTINUITY S3-454 1 & 5

F1-90 TK 2 40000 LB LOOP CONTINUITY S3-454 4 & 6

F1-1363 TK 2 10000 LB CONT TO GND ON EMPTY S3-454 3

F1-1393 TK 2 FULL LOOP CONTINUITY S3-454 2 & 7

Appendix K: FUEL TESTS

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

42 of 45

BOEING SERVICE BULLETIN MD11-28-132
RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

TAIL TANK

F1-1396 TAIL TK EMPTY LOOP CONTINUITY S3-756 1 & 3

F1-1397 TAIL L FULL LOOP CONTINUITY S3-758 1 & 3

F1-1398 TAIL R FULL LOOP CONTINUITY S3-759 2 & 3

F1-1399 Tail Tank Vent box CONT BTW CONNECT S3-739 PIN 1JX VENT BOX

P1-930 PIN 3

AUX TANKS

F1-1359 UPPR AUX FULL LOOP CONTINUITY S3-1186 1 & 2

F1-1360 LWR AUX FULL LOOP CONTINUITY S3-805 4 & 5

FWD AUX TANK

F1-631 FWD AUX EMPTY CONT TO GND ON EMPTY P10-4410B 22

Appendix K: FUEL TESTS

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

43 of 45

BOEING SERVICE BULLETIN MD11-28-132
This Appendix applies only to: Group 4.

RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

This test can be performed for each float switch circuit independently as the fuse is installed.

REFERENCES (AMM) Tasks:

MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT

This procedure should be used as necessary.

Depower the Fuel system and open the related C/Bs.

After fuse installation do a continuity test as shown in the table below.

Note: For some fuses check continuity between two pins, for others check continuity to ground.

FUSE TO BE TESTED TEST TYPE TERMINAL PINS REMARKS

TANK 1

F1-176 - TANK 1 DUMP LOOP CONTINUITY S3-450 7 & 8

F1-121 Tank 1 4000 lb LOOP CONTINUITY S3-450 1 & 6

F1-120 Tank 1 6000 lb LOOP CONTINUITY S3-450 4 & 5

F1-1391 TK 1 INBD FULL LOOP CONTINUITY S3-1301 1 & 2

F1-1392 TK 1 OUTBD FULL LOOP CONTINUITY S3-1300 1 & 2

F1-119 TK 1 TIP LOOP CONT NOT FULL S3-366 1 & 3

F1-735 L WING OVERFILL LOOP CONTINUITY S3-684 1 & 2 VENT BOX

TANK 3

F1-178 - TANK 3 DUMP LOOP CONTINUITY S3-451 7 & 8

F1-122 Tank 3 4000 lb LOOP CONTINUITY S3-451 6 & 2

F1-123 Tank 3 6000 lb LOOP CONTINUITY S3-451 4 & 5

F1-1394 TK 3 INBD FULL LOOP CONTINUITY S3-1302 1 & 2

F1-1395 TK 3 OUTBD FULL LOOP CONTINUITY S3-1303 1 & 2

F1-124 TK 3 TIP LOOP CONT NOT FULL S3-452 2 & 3

F1-734 R WING OVERFILL LOOP CONTINUITY S3-683 1 & 2 VENT BOX

TANK 2

F1-177 TK 2 DUMP LOOP CONTINUITY S3-454 1 & 5

F1-90 TK 2 40000 LB LOOP CONTINUITY S3-454 4 & 6

F1-1363 TK 2 10000 LB CONT TO GND ON EMPTY S3-454 3

F1-1393 TK 2 FULL LOOP CONTINUITY S3-454 2 & 7

Appendix L: FUEL TESTS

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

44 of 45

BOEING SERVICE BULLETIN MD11-28-132
RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES

TAIL TANK

F1-1396 TAIL TK EMPTY LOOP CONTINUITY S3-756 1 & 3

F1-1397 TAIL L FULL LOOP CONTINUITY S3-758 1 & 3

F1-1398 TAIL R FULL LOOP CONTINUITY S3-759 2 & 3

F1-1399 Tail Tank Vent box CONT BTW CONNECT S3-739 PIN 1JX VENT BOX

P1-930 PIN 3

AUX TANKS

F1-1359 UPPR AUX FULL LOOP CONTINUITY S3-1186 1 & 2

F1-1360 LWR AUX FULL LOOP CONTINUITY S3-805 4 & 5

FWD AUX TANKS

F1-191 FWD AUX TK 1 LOW CONT TO GND ON EMPTY R5-448 E

F1-243 FWD AUX TK 2 LOW CONT TO GND ON EMPTY R5-448 D

Appendix L: FUEL TESTS

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 25, 2008

Revision 1 July 06, 2010 MD11-28-132

45 of 45

BOEING SERVICE BULLETIN MD11-28-132