Commercial 

Airplanes 767

Service Bulletin

ALERT

Number: 767-57A0122

Original Issue: October 22, 2009

ATA System: 5710

SUBJECT: WINGS - Center Wing - Sleeve and Clamp Installation

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

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

laws.

ECCN: 9E991

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Unpublished Work - All Rights Reserved

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BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected ......................................... 9

B. Concurrent Requirements ....................................... 9

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

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

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

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

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 12

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 14

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 14

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

FIGURE 1: REAR SPAR - RIGHT MAIN WHEEL WELL - SLEEVE AND CLAMP INSTALLATION . . 17

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Commercial 

Airplanes 767

Service Bulletin

ALERT

Summary Number: 767-57A0122

Original Issue: October 22, 2009

ATA System: 5710

SUBJECT: WINGS - Center Wing - Sleeve and Clamp Installation

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

None.

BACKGROUND

Accomplishment of the modifications within this service bulletin will help prevent possible ignition sources in the

center auxiliary fuel tank caused by a wiring short. An ignition source in a fuel tank could result in a fire or an

explosion.

A safety assessment by Boeing identified a certain type of fastener that penetrates the fuel tank wall and has

an insufficient electrical bond to the fuel tank structure. These fasteners can be a path for electrical energy to

enter the fuel tank if a wiring short occurs in a wire bundle installed along the fuel tank boundary structure. The

electrical energy from the wiring short can go through these fasteners because they have an insufficient bond

to the fuel tank structure. This energy can be sufficient to cause arcing at the ends of these fasteners in the fuel

tank. The necessary changes were incorporated in production by PRRB13421-11. A review of the production

records found that three airplanes did not met the production requirements. On these three airplanes, there is

one location on the rear spar of the center wing fuel tank where the specified tetrafluoroethylene (TFE 2X) sleeve

and clamp change was not accomplished.

This Service Bulletin makes these changes at one location on the rear spar of the center wing where a high

energy short can occur. A TFE 2X sleeve on the wire bundle gives more protection from chafing. The wire bundle

clamps has a design with protection on its metal edges. These changes make sure that the risk of an ignition

source in the fuel tank from a short is kept to a minimum.

This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank

System Fault Tolerance Evaluation Requirements".

ACTION

Get access to the rear spar of the center wing in the main wheel well on the right side and install the TFE 2X

sleeve and the full cushion wire bundle clamp at one location.

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EFFECTIVITY

767-300 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 this service bulletin be incorporated within 5 years after the original issue date on this

service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of November 18, 2008. Please refer to

Paragraph 2.B., Industry Support Information.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

All 2.50 2.50

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BLANK PAGE
Commercial 

Airplanes 767

Service Bulletin

ALERT

Number: 767-57A0122

Original Issue: October 22, 2009

ATA System: 5710

SUBJECT: WINGS - Center Wing - Sleeve and Clamp Installation

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

Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

This service bulletin is for the airplanes shown below.

GROUP CONFIGURATION DESCRIPTION

1 - 767-300

Airplane Models:

767-300

Variable Number Group

VS911 - VS912 1

VS916 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

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C. Reason

Accomplishment of the modifications within this service bulletin will help prevent possible ignition

sources in the center auxiliary fuel tank caused by a wiring short. An ignition source in a fuel tank could

result in a fire or an explosion.

A safety assessment by Boeing identified a certain type of fastener that penetrates the fuel tank wall

and has an insufficient electrical bond to the fuel tank structure. These fasteners can be a path for

electrical energy to enter the fuel tank if a wiring short occurs in a wire bundle installed along the fuel

tank boundary structure. The electrical energy from the wiring short can go through these fasteners

because they have an insufficient bond to the fuel tank structure. This energy can be sufficient to cause

arcing at the ends of these fasteners in the fuel tank. The necessary changes were incorporated in

production by PRRB13421-11. A review of the production records found that three airplanes did not

met the production requirements. On these three airplanes, there is one location on the rear spar of

the center wing fuel tank where the specified tetrafluoroethylene (TFE 2X) sleeve and clamp change

was not accomplished.

This Service Bulletin makes these changes at one location on the rear spar of the center wing where

a high energy short can occur. A TFE 2X sleeve on the wire bundle gives more protection from chafing.

The wire bundle clamps has a design with protection on its metal edges. These changes make sure

that the risk of an ignition source in the fuel tank from a short is kept to a minimum.

This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel

Tank System Fault Tolerance Evaluation Requirements".

D. Description

Get access to the rear spar of the center wing in the main wheel well on the right side and install the

TFE 2X sleeve and the full cushion clamp on the wire bundle at one location.

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

Affected Maintenance Zones

Model Zone

767-300 144

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 change given in this service bulletin be done within 5 years after the

original issue date on this service bulletin.

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BOEING SERVICE BULLETIN 767-57A0122

ALERT ALERT
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:

• 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.

Number of Per- Task Hours Elapsed Hours

sons

Task

Open Access 1 1.00 1.00

Figure 1 1 0.50 0.50

Close Access 1 1.00 1.00

TOTAL FOR EACH AIRPLANE 2.50 2.50

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

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J. References

1. Existing Data

a. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19

b. 767 Aircraft Maintenance Manual (AMM) 24-22-00, 32-00-15, 32-00-20

c. Engineering Change Memo PRRB13421-11

2. Data supplied with this Service Bulletin

None.

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

Drawing Number Title

288T4570 Wire Bundle Installation Wheel Well Area Right, STA 955 Thru 1065

These drawings were used to prepare this service bulletin. These drawings are not necessary to

make the specified changes, and are not supplied with this service bulletin. These drawings may

not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

None.

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.

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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 (QTY) 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

Apr 31/10

ROLT

(Weeks)

Kit Number Name Date QTY

015T1842-1 Top Kit 05/21/2009 3 13 $ 189.00

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

After the Unit Price date, new price and 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 available for 767 airplanes in warranty as of November 18, 2008. For

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

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

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

bulletin number and reference the airplane variable numbers in your purchase order.

C. Parts Necessary For Each Airplane

1. Kits/Parts

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

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for

each installation figure shown in the table below.

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

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Figure Kit

Top Kit 1

015T1842-1 1

Group 1:

KIT 015T1842-1

NOTES

Existing Part

Name Number

Figure

New Part Number

1

QTY

Sleeve - 1 inch I.D.

(As supplied 1.5

inch I.D.)

005W3281-5 1

WIRE BUNDLE

CLAMP

BACC10JU106 1

2. Parts and Materials Supplied by the Operator

Part Number/ Specification QTY Name Notes

BMS 13-54, TYPE III, CLASS 3 ft LACING TAPE (a)

1, FINISH C, WHITE

(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for

supplier data.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

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

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

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

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BOEING SERVICE BULLETIN 767-57A0122

ALERT ALERT
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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

4. 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

– Torque limits to tighten nuts and bolts are in 767 SRM, Chapter 51

5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,

and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

6. 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.

B. WORK INSTRUCTIONS

1. Remove electrical power from the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure.

2. Install the downlocks on the nose and main landing gear. Refer to 767 AMM 32-00-20 as an

accepted procedure.

3. Install the door locks on the nose and main landing gear. Refer to 767 AMM 32-00-15 as an

accepted procedure.

4. Get access to the rear spar at the main wheel well on the right side of the airplane.

5. Install the tetrafluoroethylene (TFE 2X) sleeve and clamp in accordance with Figure 1.

6. Remove the door locks on the nose and main landing gear. Refer to 767 AMM 32-00-15 as an

accepted procedure.

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7. Remove the downlocks on the nose and main landing gear. Refer to 767 AMM 32-00-20 as an

accepted procedure.

8. Restore electrical power to the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure.

9. Put the airplane back to a serviceable condition.

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FIGURE 1: REAR SPAR - RIGHT MAIN WHEEL WELL - SLEEVE AND CLAMP INSTALLATION

(SHEET 1 OF 3)

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FIGURE 1: REAR SPAR - RIGHT MAIN WHEEL WELL - SLEEVE AND CLAMP INSTALLATION

(SHEET 2 OF 3)

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ALERT ALERT
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 this figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep SCREW - 1

Remove / Keep WASHER - 1

If a spacer is installed.Remove / Keep SPACER - 1

It is not necessary to

remove the nut if it

is attached to the

bracket.

Remove / Keep NUT - 1

2 Remove CLAMP - 1

Sleeve is TFE 2X.

Cut the sleeve to the

requirement length

is necessary.

3 Cut SLEEVE - -

Sleeve is TFE 2X.

Cut the sleeve longitudinally for installation on the wire bundle.

Cut SLEEVE - -

Sleeve - 1 inch I.D. (As 005W3281-5 1 Sleeve is TFE 2X.

supplied 1.5 inch I.D.)

Install (New)

Refer to SWPM 20-

10-12 as an accepted procedure for installation of wire

bundle support

clamp.

WIRE BUNDLE BACC10JU106 1

CLAMP

4 Install (New)

5 Install (Kept) WASHER - 1

Install (Kept) SCREW - 1

Install (Kept) SPACER - 1

Install (Kept) NUT - 1

Install in shaded

area. Refer to SWPM 20-10-11 as an

accepted procedure

to install a wire harness tie.

BMS 13-54, TYPE III, -

CLASS 1, FINISH C,

WHITE

6 Install (New) LACING TAPE

FIGURE 1: REAR SPAR - RIGHT MAIN WHEEL WELL - SLEEVE AND CLAMP INSTALLATION

(SHEET 3 OF 3)

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