Commercial 

Airplanes MD11

Service Bulletin

SPECIAL ATTENTION

Number: MD11-55-027

Original Issue: March 17, 2011

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Change Rub Strips of Tail Fuel Tank Center

Box Front Spar Access Doors

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 © 2011 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Unpublished Work - All Rights Reserved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Copyright © Unpublished Work - See page 1 for details.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: March 17, 2011

MD11-55-027

1 of 18

3.0
BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

2 of 18

BOEING SERVICE BULLETIN MD11-55-027

BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected ......................................... 7

B. Concurrent Requirements ....................................... 7

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

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

E. Compliance .............................................. 8

F. Approval ................................................ 8

G. Manpower ............................................... 8

H. Weight and Balance Changes .................................... 9

I. Electrical Load Data .......................................... 9

J. References .............................................. 9

1. Existing Data .......................................... 9

2. Data supplied with this Service Bulletin ............................ 9

3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 9

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 12

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 12

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

FIGURE 1: CHANGE RUB STRIPS OF TAIL FUEL TANK CENTER BOX FRONT SPAR ACCESS DOOR

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

3 of 18

BOEING SERVICE BULLETIN MD11-55-027
BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

4 of 18

BOEING SERVICE BULLETIN MD11-55-027

BLANK PAGE
Commercial 

Airplanes MD11

Service Bulletin

SPECIAL ATTENTION

Summary Number: MD11-55-027

Original Issue: March 17, 2011

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Change Rub Strips of Tail Fuel Tank Center

Box Front Spar Access Doors

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

An investigation by Boeing revealed that the rub strips of tail fuel tank center box front spar access doors were

manufactured improperly. Tail center box fuel tank front spar access door rub strips were inadvertently anodized

(electrically non-conductive) instead of alodined (electrically conductive) as prescribed in design drawings.

Anodization of the rub strips may prevent adequate electrical bonding between the rub strips and the doors.

Replacing anodized rub strips with alodined rub strips will provide adequate electrical bonding between the rub

strips and the fuel access doors. If not corrected, inadequate electrical bonding can contribute to possible ignition

of flammable fuel vapor in the tail fuel tank as a result of a lightning strike.

ACTION

This service bulletin provides instructions to change the rub strips of the tail fuel tank center box front spar access

doors.

EFFECTIVITY

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

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.

Boeing recommends that the rub strips of the tail fuel tank center box front spar access doors be changed within

60 months after the original issue date on this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of July 21, 2010. Please refer to Paragraph

2.B., Industry Support Information.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

5 of 18
MANPOWER

Airplanes Total Task Hours Elapsed Hours

MD-11, MD-11F 32.0 16.0

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: March 17, 2011

MD11-55-027

6 of 18

BOEING SERVICE BULLETIN MD11-55-027
Commercial 

Airplanes MD11

Service Bulletin

SPECIAL ATTENTION

Number: MD11-55-027

Original Issue: March 17, 2011

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Change Rub Strips of Tail Fuel Tank Center

Box Front Spar Access Doors

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below.

GROUP CONFIGURATION DESCRIPTION

Change Rub Strips of Tail Fuel Tank Center Box Front Spar Access

Doors for Fuselage Number 447 - 613

1 -

Airplane Models:

MD-11, MD-11F

Fuselage Num- Group

ber

447 - 613 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

7 of 18
C. Reason

An investigation by Boeing revealed that the rub strips of tail fuel tank center box front spar access

doors were manufactured improperly. Tail center box fuel tank front spar access door rub strips were

inadvertently anodized (electrically non-conductive) instead of alodined (electrically conductive) as

prescribed in design drawings. Anodization of the rub strips may prevent adequate electrical bonding

between the rub strips and the doors. Replacing anodized rub strips with alodined rub strips will provide

adequate electrical bonding between the rub strips and the fuel access doors. If not corrected, inadequate

electrical bonding can contribute to possible ignition of flammable fuel vapor in the tail fuel tank as a

result of a lightning strike.

D. Description

This service bulletin provides instructions to change the rub strips of the tail fuel tank center box front

spar access doors.

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

Affected Maintenance Zones

Model Zone

MD-11, MD-11F 189

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.

Boeing recommends that the rub strips of the tail fuel tank center box front spar access doors be

changed within 60 months 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.

G. Manpower

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

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

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

time:

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

8 of 18

BOEING SERVICE BULLETIN MD11-55-027
• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Task Number of Persons Task Hours Elapsed Hours

Defuel and Purge 2 10.0 5.0

Remove Fuel Tank 2 2.0 1.0

Access Doors

Change Rub Strips 2 15.0 7.5

Install Fuel Tank Ac- 2 2.0 1.0

cess Doors

Leak Check 2 3.0 1.5

TOTAL FOR EACH AIRPLANE 32.0 16.0

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. MD-11, MD-11F Aircraft Maintenance Manual (AMM) 52-57-19.

b. MD-11, MD-11F Structural Repair Manual (SRM) 51-42-07.

2. Data supplied with this Service Bulletin

None.

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

Document Number Title Change

SPAR ASSY - CONSTANT HORIZ Z, AEO AA

STAB, FORWARD

ALC8020

This drawing was used to prepare this service bulletin. This drawing is not necessary to make the

specified changes, and is not supplied with this service bulletin. This drawing may not be applicable

to all airplane configurations or operators.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

9 of 18

BOEING SERVICE BULLETIN MD11-55-027
K. Publications Affected

1. Publications:

Publication Chapter-Section

Structural Repair Manual 51-42-07

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.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

10 of 18

BOEING SERVICE BULLETIN MD11-55-027
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the parts 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 parts are subject to the terms and conditions of the Boeing standard purchase order

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

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

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

2. Fax to (206) 662-7145

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

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

ROLT as of the original

issue date of this Service

Bulletin (Calendar Days)

Part Number Name QTY

ALC8028-1 RUB STRIP 2 60

BACR15BA3AD8C RIVET 36 60

B. Industry Support Information

Boeing warranty remedies are available for MD-11 airplanes in warranty as of July 21, 2010. For task

hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing

Commercial Airplanes Group - Warranties. The parts for airplanes in warranty as of that date will be

supplied at no charge. Send a purchase order for the parts to Boeing Spares. Please refer to this

service bulletin number and reference the airplane fuselage number in your purchase order.

Boeing Commercial Airplanes Group - Warranties

P.O. Box 3707

M/C 2L-46

Seattle, Washington 98124-2207 USA

(Service Bulletin MD11-55-027)

C. Parts Necessary For Each Airplane

1. Kits/Parts

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

NOTE: The parts shown below and the items shown in Paragraph 2.C.2., Parts and Materials

Supplied by the Operator, are necessary for each airplane.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

11 of 18

BOEING SERVICE BULLETIN MD11-55-027
New Part Number QTY Name Existing Part Notes

ALC8028-1 2 RUB STRIP ALC8028-1 (a)

BACR15BA3AD8C 36 RIVET MS20426AD3 (b)

(a) Alodined rub strip, part number ALC8028-1 replaces existing anodized

rub strip part number ALC8028-1.

(b) Alodined rivet, part number BACR15BA3AD8C replaces existing rivet,

part number MS20426AD3.

2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

Sealing Compound, Integral Fuel (a)

Tanks and Fuel Cell Cavities

PR-1422 B-2 1 Quart

(DMS 2082 B-2)

or

Equivalent

(a) Can be purchased from: PRC-DeSoto International, Incorporation CAGE

24811 Avenue Rockefeller 83574

Valencia, California 91355-3468

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

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

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

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

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

12 of 18

BOEING SERVICE BULLETIN MD11-55-027
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, and the Figure(s)

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, in accordance with

Structural Repair Manual MD-11, MD11F SRM 51.

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

standards given in MD-11, MD-11F SRM 51, then a fastener of the same specification,

or an approved substitute, with a length which meets the installation standards given

in MD-11, MD-11F SRM 51 may be used. In addition, washers may be installed for

fastener grip length in accordance with MD-11, MD-11F SRM 51.

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. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

13 of 18

BOEING SERVICE BULLETIN MD11-55-027
– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets are in Structural Repair Manual MD-11,

MD-11F SRM 51

– Torque limits to tighten nuts and bolts are in MD-11, MD-11F SRM 51.

8. 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.

9. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

The removed part can be discarded if a new or serviceable part is installed.

10. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

B. WORK INSTRUCTIONS

1. Remove and keep tail fuel tank center box front spar access doors 352AZ and 352BZ. Refer to

MD-11, MD-11F AMM 52-57-19 as an accepted procedure.

2. Change rub strips in accordance with Figure 1 and MD-11, MD-11F SRM 51-42-07.

NOTE: Proper installation of the rub strips prevents fuel leaks and sparking during a lightning

strike to the airplane.

3. Install kept tail fuel tank center box front spar access doors 352AZ and 352BZ. Refer to MD-11,

MD-11F AMM 52-57-19 as an accepted procedure.

4. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

14 of 18

BOEING SERVICE BULLETIN MD11-55-027
FIGURE 1: CHANGE RUB STRIPS OF TAIL FUEL TANK CENTER BOX FRONT SPAR ACCESS DOOR

(SHEET 1 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

15 of 18

BOEING SERVICE BULLETIN MD11-55-027
FIGURE 1: CHANGE RUB STRIPS OF TAIL FUEL TANK CENTER BOX FRONT SPAR ACCESS DOOR

(SHEET 2 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

16 of 18

BOEING SERVICE BULLETIN MD11-55-027
FIGURE 1: CHANGE RUB STRIPS OF TAIL FUEL TANK CENTER BOX FRONT SPAR ACCESS DOOR

(SHEET 3 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

17 of 18

BOEING SERVICE BULLETIN MD11-55-027
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

IDENTIFICA- QTY MORE DATA

TION

STEP TASK NAME

Remove (Dis- Rivet MS20426AD3 36 (a)

card)

1

Remove (Dis- Rub Strip ALC8028-1 2

card)

Remove (Keep) Gang Channel 3D0292-1 2

Remove (Dis- Sealant PR-1422 B-2 -

card) (DMS 2082 B-2)

2 Apply (New) Sealant PR-1422 B-2 -

(DMS 2082 B-2)

Install (New) Rub Strip ALC8028-1 2

Drill Rub Strip ALC8028-1 2

Install (Kept) Gang Channel 3D0292-1 2

Install (New) Rivet BACR15BA3AD8C 36

(a) In accordance with MD-11, MD-11F SRM 51-42-07.

FIGURE 1: CHANGE RUB STRIPS OF TAIL FUEL TANK CENTER BOX FRONT SPAR ACCESS DOOR

(SHEET 4 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: March 17, 2011

MD11-55-027

18 of 18

BOEING SERVICE BULLETIN MD11-55-027