Commercial 

Airplane

Group 757

Service Bulletin

SPECIAL ATTENTION

Number: 757-32-0176

Date: September 10, 2007

Revision 1: October 16, 2008

ATA System: 3245

SUBJECT: LANDING GEAR - Nose Wheel Spin Brake - Spring Inspection and Replacement

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 © 2007 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Unpublished Work - All Rights Reserved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, MD-10, MD-11, MD-80, MD-88, MD-90, 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.

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8.0
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BOEING SERVICE BULLETIN 757-32-0176

BLANK PAGE
Table of Contents

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

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

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 21

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 25

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 28

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

FIGURE 1: SPIN BRAKE ASSEMBLY- GENERAL VISUAL INSPECTION . . . . . . . . . . . . . . . . 32

FIGURE 2: SPRING - DETAILED INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

FIGURE 3: SPRING - SPECIAL DETAILED INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . 36

FIGURE 4: SPRING - REPLACEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 5: SPIN BRAKE ASSEMBLY (COMPOSITE) - REPLACEMENT . . . . . . . . . . . . . . . . 43

FIGURE 6: SPIN BRAKE ASSEMBLY (CRES) - REPLACEMENT . . . . . . . . . . . . . . . . . . . . 47

FIGURE 7: SPIN BRAKE ASSEMBLY (COMPOSITE) - ASSEMBLE . . . . . . . . . . . . . . . . . . 51

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BOEING SERVICE BULLETIN 757-32-0176
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BOEING SERVICE BULLETIN 757-32-0176

BLANK PAGE
Commercial 

Airplane

Group 757

Service Bulletin

SPECIAL ATTENTION

Revision Transmittal Sheet Number: 757-32-0176

Date: September 10, 2007

Revision 1: October 16, 2008

ATA System: 3245

SUBJECT: LANDING GEAR - Nose Wheel Spin Brake - Spring Inspection and Replacement

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on the airplanes changed as shown in the original issue of this service bulletin.

However, operators must continue to do the inspection detailed at the times given in Paragraph 1.E., Compliance

until the newly designed spin brake assemblies made from Corrosion Resistant Steel (CRES) springs or the

composite springs are installed. After installation of the new spin brake assemblies that have CRES springs or

the composite springs, it is not necessary to do the repeat inspections.

REASON FOR REVISION

This revision is sent to add new Top Kit 012N0045-1 which supplies new spin brake assemblies that have CRES

springs. Part 5 of the Work Instructions is updated to add a new Option 3 for operators who want to install the

new spin brake assemblies that have CRES springs. Also "spin brake spring arms" is changed to "springs" and

"Toe Plate" is changed to "Toe Piece" in all the sections of the service bulletin.

Changes to the service bulletin include:

— Summary - Background and Action - Instructions are added to install the new spin brake assemblies that

have CRES springs as the recommended terminating action to the repeat inspections.

— Paragraph 1.C., Reason - Instructions are added to install the new spin brake assemblies that have CRES

springs as the recommended terminating action to the repeat inspections.

— Paragraph 1.D., Description - Instructions are added to install the new spin brake assemblies that have

CRES springs as the recommended terminating action to the repeat inspections.

— Paragraph 1.E., Compliance - Compliance Table and Note (c) updated.

— Paragraph 1.G., Manpower - Existing tables removed. New table added.

— Paragraph 1.J.3., - "Installation Drawings Used in the Preparation of this Service Bulletin" - Installation

drawing number 012N0045 added.

— Paragraph 1.K., - "Publications Affected" - Reference to 757 Illustrated Parts Catalog (IPC) 32-45 added.

— Paragraph 2.A., Material - Price and Availability - New table for the top kit 012N0045-1 added.

— Paragraph 2.C.1., Parts Necessary for Each Airplane - New table for the top kit 012N0045-1 added.

— Paragraph 2.C.2., Parts and Materials Supplied by the Operator

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5 of 55
— Table 1 - Optional part BACS40R014Y050F added.

— Table 2 - Table 2 changed to Table 2-1. Optional part BACS40R014Y046F added. New Washer

AN960KD516 added. Part number 141N0096-1 and BACB30NM5K14 deleted. Part number

141N0091-13 moved to the new Table 2-2.

— New table 3 for Option 3 added.

— Paragraph 3.B., Work Instructions - Option 3 added in PART 5 to install the new spin brake assemblies that

have CRES springs. Also reference to AMM 32-45-05 added.

— Figure 4 - Optional part BACS40R014Y050F added in step 7, 8 and 10.

— Figure 5 - Optional part BACS40R014Y046F added in step 13, 14 and 16. Salvaged filler 141N0096-1

deleted. New fillers to be used which are included in the Spin Brake Assembly 141N0091-13. Note (a)

updated and Note (c) deleted.

— Figure 6 - New figure with steps to install the new spin brake assemblies that have CRES springs.

— Figure 7 - New figure with steps to assemble the new spin brake assembly with a composite spring.

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: September 10, 2007

Revision 1: October 16, 2008

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BOEING SERVICE BULLETIN 757-32-0176
Commercial 

Airplane

Group 757

Service Bulletin

SPECIAL ATTENTION

Summary Number: 757-32-0176

Date: September 10, 2007

Revision 1: October 16, 2008

ATA System: 3245

SUBJECT: LANDING GEAR - Nose Wheel Spin Brake - Spring Inspection and Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to inspect the springs of the nose wheel spin brake assemblies to determine

if they are aluminum or composite. Spin brake assemblies fitted with aluminum springs can crack. Operators

must inspect the aluminum springs for any crack and replace them if necessary. A crack in the aluminum spring

can result in a separation of the aluminum spring from the airplane. If this service bulletin is not done, an aluminum

spring could break and separate from the airplane which could result in potential hazard to persons or property

on the ground, or ingestion into the engine with engine damage and potential shut down, or damage to the

airplane.

Two spin brake assemblies are installed in the nose wheel well and include the springs. Wear bars or brake

pads installed on the springs bring the nose wheels to a stop after the gear is retracted. Boeing has been informed

by operators of 26 incidents of cracked aluminum springs and 10 incidents of broken aluminum spring separations

from the airplane between October 2001 and February 2007.These incidents have occurred in a range between

6,363 flight cycles and 19,069 flight cycles. The cracks have been found in a 2 inch curved section of the

aluminum spring at a distance of 13 inches from the bottom of the spring.

This service bulletin will inspect the spin brake assemblies, that have aluminum springs, for any cracks. Where

a crack is found, operators must replace the applicable aluminum spring with a new aluminum spring, or install

a complete new composite or CRES spin brake assembly. The spin brake assembly with the composite spring

is an earlier production configuration and has been found to produce flight deck noise. Boeing therefore

recommends installation of the new CRES spin brake assembly. The Top Kit provided in Revision 1 of this

service bulletin includes spin brake assemblies that have CRES springs. Installation of spin brake assemblies

that have CRES or composite springs is the terminating action to the repeat inspections given in this service

bulletin.

Boeing Service Related Problem (SRP) 757-SRP-32-0148 is related to this service bulletin.

ACTION (PRR 54530-282RS)

Get access to the left and right nose wheel spin brake assemblies. Do a General Visual inspection to check if

the springs are aluminum or composite.

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1. If the left and right nose wheel spin brake assemblies have composite springs, no more work is necessary.

Put the airplane back to a serviceable condition.

NOTE: Because of excessive flight deck noise on airplanes fitted with spin brake assemblies that have

composite springs, Boeing recommends installation of new spin brake assemblies with CRES

spring.

2. If either of the springs are aluminum, do a Detailed and a High Frequency Eddy Current (HFEC) inspection

of each aluminum spring for a crack.

a. If a crack is not found in either aluminum spring, put the airplane back to a serviceable condition. Do

the repeat inspections at the times given in Paragraph 1.E., Compliance.

b. If a crack is found on either aluminum spring, do one of the following three options:

(1) Option 1: Install new applicable aluminum spring(s). Put the airplane back to a serviceable condition.

Do the repeat inspections of the new part(s) at the times given in Paragraph 1.E., Compliance.

(2) Option 2: Replace the applicable aluminum spin brake assembly with a new composite spin brake

assembly. Put the airplane back to a serviceable condition.

NOTE: Because of excessive flight deck noise on airplanes fitted with spin brake assemblies

that have composite springs, Boeing recommends installation of new spin brake

assemblies with CRES springs.

(3) Option 3: Replace the applicable aluminum spin brake assembly with a new spin brake assembly

that have CRES springs. Put the airplane back to a serviceable condition.

EFFECTIVITY

All 757-200/-200CB/-200PF/-300 Airplanes. Refer to Paragraph 1.A., Effectivity, for the list of affected airplanes.

COMPLIANCE

Refer to Paragraph 1.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.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of April 14, 2006. Please refer to Paragraph

2.B., Industry Support Information.

MANPOWER

Refer to Paragraph 1.G., Manpower

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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BOEING SERVICE BULLETIN 757-32-0176
Refer to Paragraph 2.A., Material - Price and Availability.

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BOEING SERVICE BULLETIN 757-32-0176
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BOEING SERVICE BULLETIN 757-32-0176

BLANK PAGE
Commercial 

Airplane

Group 757

Service Bulletin

SPECIAL ATTENTION

Number: 757-32-0176

Date: September 10, 2007

Revision 1: October 16, 2008

ATA System: 3245

SUBJECT: LANDING GEAR - Nose Wheel Spin Brake - Spring Inspection and Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D624N001 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

This service bulletin is for the airplanes shown below. An equivalent change is on subsequent

production airplanes. Refer to PRR 54530-282RS for data about this change.

GROUP CONFIGURATION DESCRIPTION

1 - All 757-200/-200CB/-200PF/-300 airplanes.

Airplane Models:

757-200, 757-200CB, 757-200PF, 757-300

Variable Number Group

NA001 - NA028 1

NA191 - NA199 1

NA201 - NA239 1

NA301 - NA305 1

NA341 - NA352 1

NA391 - NA399 1

NA401 - NA408 1

NA441 - NA447 1

NA501 - NA586 1

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11 of 55
Variable Number Group

NB001 - NB004 1

NB021 - NB023 1

NB036 - NB041 1

NB051 - NB053 1

NB061 - NB073 1

NB079 1

NB131 - NB148 1

NB161 - NB162 1

NB166 - NB168 1

NB201 - NB204 1

NB221 - NB228 1

NB230 1

NB236 1

NB239 1

NB261 - NB267 1

NB291 - NB299 1

NB301 - NB302 1

NB311 - NB312 1

NB321 - NB331 1

NB421 - NB438 1

NB446 1

NB451 - NB454 1

NB501 - NB523 1

NB561 1

NB571 1

NB581 - NB583 1

NC001 - NC033 1

NC041 - NC042 1

NC051 - NC052 1

NC056 - NC062 1

NC066 - NC084 1

NC091 - NC094 1

NC151 1

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BOEING SERVICE BULLETIN 757-32-0176
Variable Number Group

NC161 1

NC901 - NC951 1

NC971 - NC974 1

ND001 - ND007 1

ND011 - ND059 1

ND111 - ND113 1

ND161 - ND199 1

ND201 - ND203 1

ND221 - ND225 1

ND241 - ND248 1

ND301 - ND322 1

ND401 1

ND891 1

ND895 1

NE001 - NE008 1

NE011 - NE088 1

NE091 - NE094 1

NE141 - NE150 1

NE161 - NE177 1

NE201 - NE204 1

NE301 - NE302 1

NE311 - NE325 1

NJ001 - NJ004 1

NJ031 - NJ032 1

NJ551 - NJ555 1

NL001 - NL002 1

NL006 - NL017 1

NL101 - NL109 1

NL141 1

NL601 - NL616 1

NN001 - NN002 1

NN051 - NN052 1

NP901 - NP904 1

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BOEING SERVICE BULLETIN 757-32-0176
Variable Number Group

NS601 - NS616 1

NT001 - NT009 1

NT201 - NT202 1

NT231 - NT234 1

NT237 - NT240 1

NT242 1

NT245 - NT248 1

NT281 - NT289 1

NT341 - NT347 1

NT351 - NT360 1

NT371 - NT373 1

NT375 - NT379 1

NT381 - NT386 1

NT401 - NT409 1

NT411 - NT412 1

NT426 - NT427 1

NT431 - NT432 1

NT436 - NT438 1

NT441 - NT442 1

NT446 1

NT701 - NT769 1

NT791 - NT796 1

NT861 - NT862 1

NT881 - NT885 1

NT901 - NT916 1

NT971 - NT985 1

NU031 - NU038 1

NU701 - NU705 1

NU721 - NU728 1

NU731 - NU732 1

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BOEING SERVICE BULLETIN 757-32-0176
2. Spares Affected

Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts

Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for

the recommended use.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to inspect the springs of the nose wheel spin brake assemblies

to determine if they are aluminum or composite. Spin brake assemblies fitted with aluminum springs

can crack. Operators must inspect the aluminum springs for any crack and replace them if necessary.

A crack in the aluminum spring can result in a separation of the aluminum spring from the airplane. If

this service bulletin is not done, an aluminum spring could break and separate from the airplane which

could result in potential hazard to persons or property on the ground, or ingestion into the engine with

engine damage and potential shut down, or damage to the airplane.

Two spin brake assemblies are installed in the nose wheel well and include the springs. Wear bars or

brake pads installed on the springs bring the nose wheels to a stop after the gear is retracted. Boeing

has been informed by operators of 26 incidents of cracked aluminum springs and 10 incidents of broken

aluminum spring separations from the airplane between October 2001 and February 2007. These

incidents have occurred in a range between 6,363 flight cycles and 19,069 flight cycles. The cracks

have been found in a 2 inch curved section of the aluminum spring at a distance of 13 inches from the

bottom of the spring.

This service bulletin will inspect the spin brake assemblies, that have aluminum springs, for any cracks.

Where a crack is found, operators must replace the applicable aluminum spring with a new aluminum

spring, or install a complete new composite or CRES spin brake assembly. The spin brake assembly

with the composite spring is an earlier production configuration and has been found to produce flight

deck noise. Boeing therefore recommends installation of the new CRES spin brake assembly. The Top

Kit provided in Revision 1 of this service bulletin includes spin brake assemblies that have CRES

springs. Installation of spin brake assemblies that have CRES or composite springs is the terminating

action to the repeat inspections given in this service bulletin.

Boeing Service Related Problem (SRP) 757-SRP-32-0148 is related to this service bulletin.

Revision 1 is sent to add new Top Kit 012N0045-1 which supplies new spin brake assemblies that

have CRES springs. Part 5 of the Work Instructions is updated to add a new Option 3 for operators

who want to install the new spin brake assemblies that have CRES springs. Also "spin brake spring

arms" is changed to "springs" and "Toe Plate" is changed to "Toe Piece" in all the sections of the service

bulletin.

Changes to the service bulletin include:

— Summary - Background and Action - Instructions are added to install the new spin brake assemblies

that have CRES springs as the recommended terminating action to the repeat inspections.

— Paragraph 1.C., Reason - Instructions are added to install the new spin brake assemblies that

have CRES springs as the recommended terminating action to the repeat inspections.

— Paragraph 1.D., Description - Instructions are added to install the new spin brake assemblies that

have CRES springs as the recommended terminating action to the repeat inspections.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

September 10, 2007

Revision 1: October 16, 2008 757-32-0176

15 of 55

BOEING SERVICE BULLETIN 757-32-0176
— Paragraph 1.E., Compliance - Compliance Table and Note (c) updated.

— Paragraph 1.G., Manpower - Existing tables removed. New table added.

— Paragraph 1.J.3., - "Installation Drawings Used in the Preparation of this Service Bulletin" -

Installation drawing number 012N0045 added.

— Paragraph 1.K., - "Publications Affected" - Reference to 757 Illustrated Parts Catalog (IPC) 32-45

added.

— Paragraph 2.A., Material - Price and Availability - New table for the top kit 012N0045-1 added.

— Paragraph 2.C.1., Parts Necessary for Each Airplane - New table for the top kit 012N0045-1 added.

— Paragraph 2.C.2., Parts and Materials Supplied by the Operator

— Table 1 - Optional part BACS40R014Y050F added.

— Table 2 - Table 2 changed to Table 2-1. Optional part BACS40R014Y046F added. New

Washer AN960KD516 added. Part number 141N0096-1 and BACB30NM5K14 deleted. Part

number 141N0091-13 moved to the new Table 2-2.

— New table 3 for Option 3 added.

— Paragraph 3.B., Work Instructions - Option 3 added in PART 5 to install the new spin brake

assemblies that have CRES springs. Also reference to AMM 32-45-05 added.

— Figure 4 - Optional part BACS40R014Y050F added in step 7, 8 and 10.

— Figure 5 - Optional part BACS40R014Y046F added in step 13, 14 and 16. Salvaged filler

141N0096-1 deleted. New fillers to be used which are included in the Spin Brake Assembly

141N0091-13. Note (a) updated and Note (c) deleted.

— Figure 6 - New figure with steps to install the new spin brake assemblies that have CRES springs.

— Figure 7 - New figure with steps to assemble the new spin brake assembly with a composite spring.

D. Description

Get access to the left and right nose wheel spin brake assemblies. Do a General Visual inspection to

check if the springs are aluminum or composite.

1. If the left and right nose wheel spin brake assemblies have composite springs, no more work is

necessary. Put the airplane back to a serviceable condition.

NOTE: Because of excessive flight deck noise on airplanes fitted with spin brake assemblies

that have composite springs, Boeing recommends installation of new spin brake

assemblies with CRES springs.

2. If either of the springs are aluminum, do a Detailed and a High Frequency Eddy Current (HFEC)

inspection of each aluminum spring for a crack.

a. If a crack is not found in either of the aluminum springs, put the airplane back to a serviceable

condition. Do the repeat inspections at the times given in Paragraph 1.E., Compliance.

b. If a crack is found on either aluminum spring, do one of the following three options:

(1) Option 1: Install new applicable aluminum spring(s). Put the airplane back to a serviceable

condition. Do the repeat inspections of the new part(s) at the times given in Paragraph

1.E., Compliance.

(2) Option 2: Replace the applicable aluminum spin brake assembly with a new composite

spin brake assembly. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

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BOEING SERVICE BULLETIN 757-32-0176
NOTE: Because of excessive flight deck noise on airplanes fitted with spin brake

assemblies that have composite springs, Boeing recommends installation of

new spin brake assemblies with CRES springs.

(3) Option 3: Replace the applicable aluminum spin brake assembly with a new spin brake

assembly that has a CRES spring. Put the airplane back to a serviceable condition.

Revision 1 - No more work is necessary on the airplanes changed as shown in the original issue of

this service bulletin. However, operators must continue to do the inspection detailed at the times given

in Paragraph 1.E., Compliance until the newly designed spin brake assemblies made from Corrosion

Resistant Steel (CRES) or composite are installed. After installation of the new spin brake assemblies

that have CRES or composite springs, it is not necessary to do the repeat inspections.

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

Affected Maintenance Zones

Model Zone

757-200, 757-200CB, 115, 116

757-200PF, 757-300

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.

Table 1: Spring Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 300 flight -

cycles after the

date on this

service bulletin.

Before 6,000

total flight cycles

on the spring(s)

(a)

Do a general visual

inspection to determine if

the left and right springs

are made of aluminum or

composites in

accordance with

Accomplishment

Instructions, Part 2.

All airplanes.

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BOEING SERVICE BULLETIN 757-32-0176
Table 1: Spring Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

300 flight cycles.

(c)

Within 300 flight

cycles after the

date on this

service bulletin.

Before 6,000

total flight cycles

on the spring(s)

(a)

Do a detailed inspection

of the left and right spring

in accordance with

Accomplishment

Instructions, Part 3.

All 757 airplanes fitted with

aluminum springs.

1,500 flight cycles.

(c)

Within 1,500

flight cycles

after the date on

this service

bulletin.

Before 6,000

total flight cycles

on the spring(s)

(a)

Do a special detailed

inspection (HFEC) of the

left and right spring in

accordance with

Accomplishment

Instructions, Part 4.

Replace the spring(s) or - - (c)

spin brake assemblies in

accordance with

Accomplishment

Instructions, Part 5.

Remove and replace the spring(s) -

before further flight (b)

Replace the spring(s) or

spin brake assemblies in

accordance with

Accomplishment

Instructions, Part 5.

Airplanes with aluminum

spring that have any

crack.

300 flight cycles.

(c)

Before 6,000 total flight cycles on

the replaced spring(s) (a)

Do a detailed inspection

in accordance with

Accomplishment

Instructions, Part 3.

Airplanes on which an

aluminum spring is

replaced with an aluminum

spring.

1,500 flight cycles.

(c)

Before 6,000 total flight cycles on

the replaced spring(s) (a)

Do a special detailed

inspection (HFEC) in

accordance with

Accomplishment

Instructions, Part 4.

Replace the spring(s) or - - (c)

spin brake assemblies in

accordance with

Accomplishment

Instructions, Part 5.

(a) For spring(s) that have been replaced with new parts and the number of flight cycles since replacement

are known. Otherwise the compliance time is before the airframe reaches 6,000 total flight cycles.

(b) The airplane can be operated with the restrictions in accordance with the 757 Master Minimum Equipment

List (MMEL), for 10 calendar days, with the spin brake assembly removed.

(c) The installation of spin brake assemblies that have CRES or composite springs in accordance with

Accomplishment Instructions, Part 5 Option 2 or Option 3, is terminating action for the repetitive inspections.

Because of excessive flight deck noise on airplanes fitted with spin brake assemblies that have composite

springs, Boeing recommends installation of new spin brake assemblies with CRES springs.

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BOEING SERVICE BULLETIN 757-32-0176
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

Number of Task Hours Elapsed Hours

Persons

Task

PART 1 - ACCESS 2 1.00 0.50

PART 2 - INITIAL INSPECTION 1 0.20 0.20

PART 3 - DETAILED 1 0.25 0.25

INSPECTION

PART 4 - SPECIAL DETAILED 1 1.50 1.50

INSPECTION

PART 5 - OPTION 1 - SPIN 2 2.50 1.25

BRAKE ASSEMBLY

REPLACEMENT (WITH

ALUMINUM) (b)

PART 5 - OPTION 2 - SPIN 1 5.00 5.00

BRAKE ASSEMBLY

REPLACEMENT (WITH

COMPOSITE) (b)

PART 5 - OPTION 3 - SPIN 1 1.50 1.50

BRAKE ASSEMBLY

REPLACEMENT (WITH CRES)

(b)

PART 6 - RESTORATION 2 1.00 0.50

TOTAL FOR EACH AIRPLANE (a) (a)

(a) Total for each airplane is not given as the Parts and Options to be accomplished are

variable for each airplane.

(b) This value is for the replacement of one Spring or Spin Brake Assembly (as applicable).

Double the value if both Springs or Spin Brake Assemblies are being replaced.

H. Weight and Balance Changes

NOTE: The values that follow are for operators who choose to replace both left and right Spin Brake

Assemblies. If only one Spin Brake Assembly is replaced, divide the values by two.

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BOEING SERVICE BULLETIN 757-32-0176
757- 200

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

Replace 141N0091-22 (Aluminum) with None None

same

Replace 141N0091-22 (Aluminum) with - 3.0 - 830

141N0091-13 (Composite)

Replace 141N0091-22 (Aluminum) with + 6.0 + 1,670

012N0042-1 (CRES)

757- 300

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

Replace 141N0091-22 (Aluminum) with None None

same

Replace 141N0091-22 (Aluminum) with - 3.0 - 350

141N0091-13 (Composite)

Replace 141N0091-22 (Aluminum) with + 6.0 + 710

012N0042-1 (CRES)

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 54530-282RS.

b. Standard Overhaul Practices Manual (SOPM) 20-50-12, 20-50-19.

c. 757 Aircraft Maintenance Manual (AMM) 32-00-15, 32-00-20, 32-45-05.

d. 757 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-19.

e. 757 Structural Repair Manual (SRM) 51-40-02.

2. Data supplied with this Service Bulletin:

None.

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BOEING SERVICE BULLETIN 757-32-0176
3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

141N0091 SPIN BRAKE INSTALLATION - NOSE WHEEL WELL

012N0045 KIT INSTL - SPRING ARM SPIN BRAKE

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

Publication Chapter-Section

757 Maintenance Manual 32-45

757 Illustrated Parts Catalog 32-45

L. Interchangeability and Intermixability of Parts

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

information.

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BOEING SERVICE BULLETIN 757-32-0176
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BOEING SERVICE BULLETIN 757-32-0176

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

below. If there is a limit to the quantity (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.

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BOEING SERVICE BULLETIN 757-32-0176
Unit Price thru

May 31/08

ROLT

(Weeks)

Kit Number Name Date QTY

KIT INSTL - SPRING ARM Nov. 21/08 12 44 $9,069.00

SPIN BRAKE

012N0045-1

Dec. 09/08 12

Dec. 23/08 12

Jan. 15/09 12

Jan. 29/09 9

Feb. 12/09 7

Feb. 26/09 7

Mar. 12/09 7

Mar. 26/09 7

Apr. 09/09 7

Apr. 23/09 7

May. 07/09 7

May. 21/09 7

Jun. 05/09 7

Jun. 19/09 7

Jul. 06/09 7

Jul. 20/09 7

Aug. 03/09 7

Aug. 17/09 7

Aug. 31/09 7

Sep. 15/09 7

Sep. 29/09 7

Oct. 13/09 7

Oct. 27/09 7

Nov. 10/09 7

Nov. 24/09 7

Dec. 10/09 7

Jan. 04/10 7

Jan. 18/10 4

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.

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BOEING SERVICE BULLETIN 757-32-0176
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. 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 757 airplanes in warranty as of April 14, 2006. 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:

NOTE: For operators who choose to replace the existing aluminum spring(s) with new CRES

spring(s) in accordance with Accomplishment Instructions Part 5, Option 3, use the parts

given in this Table and materials given in Paragraph 2.C.2., Parts and Materials Supplied

by the Operator (Table 3).

Kit 012N0045

Existing Part Notes

Number

New Part Number QTY Name

-1

Kit provides parts for

replacement of left and

right Spin Brake

Assemblies.

KIT INSTL - SPRING ARM

SPIN BRAKE

012N0045-1 -

SPIN BRAKE ASSY - NOSE

WHEEL

012N0042-1 2

012N0056-1 4 FILLER

BACS40R014Y050F 4 SHIM, LAMINATED

NAS1149C0563R 8 WASHER, PLAIN

2. Parts and Materials Supplied by the Operator:

NOTE: For operators who choose to replace the existing aluminum spring(s) with new aluminum

spring(s) in accordance with Accomplishment Instructions Part 5, Option 1, use the parts

and materials shown in Table 1.

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BOEING SERVICE BULLETIN 757-32-0176
TABLE 1: PARTS AND MATERIALS REQUIRED FOR PART 5 OPTION 1

Part Number / QTY Name Notes

Specification

141N0091-19 1 Spring (aluminum) (d)

BMS 5-95 4 oz Sealant (a) (d)

BAC 5010, Type 60 1 oz Adhesive (a) (d)

141N0091-10 2 Insulator (d)

141N0097-6 1 Toe Piece (b) (d)

141N0092-1 4 Wear Bar (c) (d)

BACS40R014F050F 2 Laminated Shim (d) (e)

(BACS40R014Y050F

Optional)

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

supplier data.

(b) Required if the upper surface of the existing toe pieces are 1/32 inch or less above the

countersunk fastener head. Inspect the toe pieces in accordance with 757 AMM 32-45-05.

(c) Required if the upper surface of the existing wear bars are 1/32 inch or less above the bolt

head. Inspect the wear bars in accordance with 757 AMM 32-45-05.

(d) The QTY numbers shown are the number of parts necessary to replace one spin brake

assembly.

(e) Sources for procurement of laminated sheet stock are contained in the Qualified Products

List of BMS 7-335.

NOTE: For operators who choose to replace the existing aluminum spring(s) with new composite

spring(s) in accordance with Accomplishment Instructions Part 5, Option 2, use the parts

and materials shown in Table 2-1 and Table 2-2.

TABLE 2-1: PARTS AND MATERIALS REQUIRED FOR PART 5 OPTION 2

Part Number / QTY Name Existing Part Number Notes

Specification

Spin Brake Instl 141N0091-22 (b) (c)

(composite spring)

141N0091-13 1

BACS40R014F046F 2 Laminated Shim - (c) (d)

(BACS40R014Y046F

Optional)

BMS 5-95 4 oz Sealant - (a) (c)

BAC5010, Type 60 2 oz Adhesive - (c)

AN960KD516 2 Washer - (c)

(NAS1149D0563K

Optional)

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BOEING SERVICE BULLETIN 757-32-0176
TABLE 2-1: PARTS AND MATERIALS REQUIRED FOR PART 5 OPTION 2

Part Number / QTY Name Existing Part Number Notes

Specification

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

supplier data.

(b) Discard the existing part where cracks are found.

(c) The QTY numbers shown are the number of parts necessary to replace one spin brake

assembly.

(d) Sources for procurement of laminated sheet stock are contained in the Qualified Products List

of BMS 7-335.

TABLE 2-2: PARTS AND MATERIALS REQUIRED FOR PART 5 OPTION 2

Kit 141N0091

Existing Part Notes

Number

New Part Number QTY Name

-13

SPIN BRAKE

INSTL

141N0091-13 -

141N0091-10 2 INSULATOR

141N0091-11 2 BUSHING

141N0091-12 8 BUSHING

141N0091-14 1 BRAKE PAD

141N0091-15 1 INSULATOR

141N0091-16 1 ROLL THREAD

141N0091-21 1 ROLL THREAD

141N0091-5 1 SPRING

141N0096-1 3 FILLER

141N0096-2 2 WASHER

141N0097-4 1 TOE PIECE

AN960XC516 2 WASHER

(NAS1149C0563B

Optional)

BACB30NM5K14 4 BOLT, HEX HEAD

WASHER,

INSULATING

NAS549-10 8

NOTE: For operators who choose to replace the existing aluminum spring(s) with new CRES

spring(s) in accordance with Accomplishment Instructions Part 5, Option 3, use the Top

Kit 012N0045-1 and materials shown in Table 3.

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BOEING SERVICE BULLETIN 757-32-0176
TABLE 3: PARTS AND MATERIALS REQUIRED FOR PART 5 OPTION 3

Part Number / QTY Name Existing Part Number Notes

Specification

BMS 5-95 4 oz Sealant - (a) (b)

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

supplier data.

(b) The QTY numbers shown are the number of parts necessary to replace one spin brake

assembly.

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 757-32-0176
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(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. 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

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets are given in 757 SRM, Chapter 51

– Torque limits to tighten nuts and bolts are given in 757 SRM, Chapter 51

5. For approved fastener and process material substitutions, refer to 757 SRM, Chapter

51. Alternate fasteners are given in 757 SRM Chapter 51 and Boeing Drawing

65-88700.

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

installation standards given in SRM Chapter 51, then a fastener of the same

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

standards given in SRM Chapter 51 may be used.

7. A Detailed Inspection is defined as: An intensive examination of a specific item,

installation, or assembly to detect damage, failure, or irregularity. Available lighting

is normally supplemented with a direct source of good lighting at an intensity deemed

appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be

necessary. Surface cleaning and elaborate procedures may be required.

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.

B. WORK INSTRUCTIONS

1. PART 1 - ACCESS

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BOEING SERVICE BULLETIN 757-32-0176
a. Make sure the landing gear downlocks are installed. Refer to 757 AMM 32-00-20 as an

accepted procedure.

b. Open the doors for the nose landing gear and install the door locks. Refer to 757 AMM 32-00-15

as an accepted procedure.

c. Get access to the nose wheel spin brake assemblies located on the top surface of the nose

gear wheel well.

2. PART 2 - INITIAL INSPECTION

a. Inspect to determine if the left and right springs are aluminum or composite in accordance

with FIGURE 1.

(1) If the left and right springs are composite, do PART 6 - RESTORATION.

NOTE: Operators can choose to do Part 5 Option 3 and replace spin brake assemblies,

that have composite spring, with the new spin brake assemblies with CRES

spring. This could reduce flight deck noise.

(2) If either of the springs are aluminum, do PART 3 - DETAILED INSPECTION and PART

4 - SPECIAL DETAILED INSPECTION on the spring(s) that is/are aluminum.

NOTE: Both PART 3 - DETAILED INSPECTION and PART 4 - SPECIAL DETAILED

INSPECTION can be done at the same time as part of the Initial Inspection

where aluminum springs are installed. Refer to Paragraph 1.E., Compliance for

the thresholds of the repeat Detailed and Special Detailed Inspections.

3. PART 3 - DETAILED INSPECTION

a. At the times given in Paragraph 1.E., Compliance, do a detailed inspection of the left or right

aluminum springs (as applicable) for any crack in accordance with FIGURE 2.

(1) If a crack is found, do PART 5 - LEFT OR RIGHT SPRING/SPIN BRAKE ASSEMBLY

REPLACEMENT

(2) If no crack is found, do PART 6 - RESTORATION.

4. PART 4 - SPECIAL DETAILED INSPECTION

a. At the times given in Paragraph 1.E., Compliance, do a High Frequency Eddy Current (HFEC)

inspection of the left or right aluminum spring (as applicable) for any crack in accordance with

FIGURE 3.

(1) If a crack is found, do PART 5 - LEFT OR RIGHT SPRING/SPIN BRAKE ASSEMBLY

REPLACEMENT

(2) If no crack is found, do PART 6 - RESTORATION.

5. PART 5 - LEFT OR RIGHT SPRING/SPIN BRAKE ASSEMBLY REPLACEMENT

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BOEING SERVICE BULLETIN 757-32-0176
a. Option 1: Replace the left or right (as applicable) aluminum spring with a new aluminum spring

in accordance with FIGURE 4 , or replace the existing aluminum spin brake assembly with a

new aluminum spin brake assembly in accordance with 757 AMM 32-45-05.

NOTE: Option 1 is not a terminating action and operators must continue to do PART 3 and

PART 4 on the replaced aluminum spring at the times given in Paragraph 1.E.,

Compliance.

b. Option 2: Replace the left or right (as applicable) aluminum spin brake assembly with a new

composite spin brake assembly. First assemble the composite spin brake assembly in

accordance with FIGURE 7 and then install the spin brake assembly in accordance with

FIGURE 5 or, replace the existing aluminum spin brake assembly with a new composite spin

brake assembly in accordance with 757 AMM 32-45-05.

NOTE: Option 2 is a terminating action for this service bulletin. However, Boeing recommends

installation of the new CRES spin brake assembly given in Option 3 because of

excessive flight deck noise on airplanes fitted with composite spin brake assemblies.

c. Option 3: Replace the left or right (as applicable) aluminum spin brake assembly with a new

CRES spin brake assembly in accordance with FIGURE 6 or, replace the existing aluminum

spin brake assembly with a new CRES spin brake assembly in accordance with 757 AMM

32-45-05.

NOTE: Option 3 is the terminating action for this Service Bulletin.

6. PART 6 - RESTORATION

a. Remove the door locks and close the doors for the nose landing gear. Refer to 757 AMM

32-00-15 as an accepted procedure.

b. Remove the landing gear downlocks. Refer to 757 AMM 32-00-20 as an accepted procedure.

c. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 757-32-0176
FIGURE 1: SPIN BRAKE ASSEMBLY- GENERAL VISUAL INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 757-32-0176
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

to check for aluminum spin

brake assembly P/N

141N0091-22 or composite

spin brake assembly P/N

141N0091-13.

Spin Brake 141N0091-( ) 2

Assembly

General Visual

Inspection

1

FIGURE 1: SPIN BRAKE ASSEMBLY- GENERAL VISUAL INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 757-32-0176
FIGURE 2: SPRING - DETAILED INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 757-32-0176
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below is for the inspection of one spring.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

for any crack on the

surface or edge of the

spring.

1 Detailed Inspection Spring (Aluminum) 141N0091-19 1

FIGURE 2: SPRING - DETAILED INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 757-32-0176
FIGURE 3: SPRING - SPECIAL DETAILED INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 757-32-0176
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below is for the inspection of one spring.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

for any crack on the

surface or edge of the

spring in accordance with

757 NDT, Part 6,

51-00-01 or 757 NDT,

Part 6, 51-00-19.

1 HFEC Inspection Spring (Aluminum) 141N0091-19 1

FIGURE 3: SPRING - SPECIAL DETAILED INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 757-32-0176
FIGURE 4: SPRING - REPLACEMENT

(SHEET 1 OF 5)

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FIGURE 4: SPRING - REPLACEMENT

(SHEET 2 OF 5)

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39 of 55

BOEING SERVICE BULLETIN 757-32-0176
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 to replace one spring.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Spin Brake 141N0091-22 1 (a)

Assembly

1 Remove (Keep)

Filler 141N0096-1 2

Bolt BACB30NM5K16 4

Washer AN960JD516 4

Remove Shim BACS40R014F050F 2 and discard.

from the existing Spin

Brake Assembly. (b)

2 Remove (Keep) Wear Bar 141N0092-1 4

Bolt BACB30VU6K8 8

Nut BACN10YR3CD 8

Washer AN960JD10 8

from the existing Spin

Brake Assembly. (c)

3 Remove (Keep) Toe Piece 141N0097-6 1

Bolt BACB30VT8K9 2

Washer AN960JD416 2

Washer 141N0096-2 2

Nut BACN10YR4CD 2

Remove Insulator 141N0091-10 2 and discard.

onto the new Spring P/N

141N0091-19 if kept from

Step 2. Or install new

wear bars and fasteners

onto the Spring as

necessary. (d) (h)

Install (Kept) or Wear Bar 141N0092-1 4

(New)

4

Bolt BACB30VU6K8 8

Nut BACN10YR3CD 8

Washer AN960JD10 8

5 Apply Adhesive BAC5010, Type 60 1 oz. to the insulator. (e)

onto the new Spring P/N

141N0091-19 if kept from

Step 3. Or install a new

toe piece and insulators

onto the Spring as

necessary. (d) (h)

6 Install (New) Insulator 141N0091-10 2

Install (Kept) or Toe Piece 141N0097-6 1

(New) Bolt BACB30VT8K9 2

Washer AN960JD416 2

Washer 141N0096-2 2

Nut BACN10YR4CD 2

FIGURE 4: SPRING - REPLACEMENT

(SHEET 3 OF 5)

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BOEING SERVICE BULLETIN 757-32-0176
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Spin Brake 141N0091-22 1 (f)

Assembly

7 Locate (Changed)

Locate (New) Shim BACS40R014F050F 2

(BACS40R014Y050F

Optional)

Locate (Kept) Filler 141N0096-1 2

Bolt BACB30NM5K16 4

Washer AN960JD516 4

to prepare the parts for

final installation.

Spin Brake 141N0091-22 1

Assembly

Remove

(Changed)

8

Remove (New) Shim BACS40R014F050F 2

(BACS40R014Y050F

Optional)

Remove (Kept) Filler 141N0096-1 2

Bolt BACB30NM5K16 4

Washer AN960JD516 4

to the shims, fillers, bolts,

washers and the spin

brake surface that will

contact the wheel well

ceiling.

9 Apply Sealant BMS 5-95 3 oz

Spin Brake 141N0091-22 1 (g) (h)

Assembly

10 Install (Changed)

Install (New) Shim BACS40R014F050F 2

(BACS40R014Y050F

Optional)

Install (Kept) Filler 141N0096-1 2

Bolt BACB30NM5K16 4

Washer AN960JD516 4

to the bolt heads and

washers once the spin

brake assembly is

installed.

11 Apply Sealant BMS 5-95 1 oz

(a) Remove and keep the bolts, washers and fillers that attach the spin brake assembly to the top surface

of the wheel well. Remove and keep the spin brake assembly and discard the shims.

(b) if the upper surface of the wear bar is greater than 1/32 inch above the bolt head. If not, discard the wear

bar and fasteners. Inspect each wear bar in accordance with 757 AMM 32-45-05.

FIGURE 4: SPRING - REPLACEMENT

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN 757-32-0176
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(c) If the upper surface of the toe piece is greater than 1/32 inch above the countersunk fastener head. If

not, discard the toe piece. Inspect the toe piece in accordance with 757 AMM 32-45-05.

(d) The installation of the wear bars and toe piece onto the new spin brake spring 141N0091-19 creates the

changed spin brake assembly 141N0091-22.

(e) Bond the insulator P/N 141N0091-10 to the spin brake spring as part of the toe piece installation.

(f) Temporarily locate the spin brake assembly as follows: -- Loosely install the four bolts and washers to

hold the spin brake in the installed position. -- Make sure the aft surface of the spin brake is 15.42 to

15.52 inches from the nose wheel well forward bulkhead as shown in View A-A. -- Increase or decrease

the thickness of shim material if necessary to retain the 15.42 to 15.52 inches dimension between the

nose wheel well forward bulkhead and aft surface of the spin brake assembly above the toe piece.

(g) Put the spin brake in position on the wheel well ceiling and install with the bolts and washers (4 locations),

shims (2 locations) and fillers (2 locations). Install the fasteners with BMS 5-95 sealant in accordance

with SOPM 20-50-19.

(h) Install the fasteners in accordance with 757 SRM 51-40-02.

FIGURE 4: SPRING - REPLACEMENT

(SHEET 5 OF 5)

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BOEING SERVICE BULLETIN 757-32-0176
FIGURE 5: SPIN BRAKE ASSEMBLY (COMPOSITE) - REPLACEMENT

(SHEET 1 OF 4)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

September 10, 2007

Revision 1 October 16, 2008 757-32-0176

43 of 55

BOEING SERVICE BULLETIN 757-32-0176
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 one spin brake assembly.

FIGURE 5: SPIN BRAKE ASSEMBLY (COMPOSITE) - REPLACEMENT

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 757-32-0176
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Spin Brake 141N0091-22 1 (a)

Assembly

1 Remove

Shim BACS40R014F050F 2

Bolt BACB30NM5K16 4

Filler 141N0096-1 2

Washer AN960JD516 4

Spin Brake 141N0091-13 1 (b)

Assembly

2 Locate (New)

Filler 141N0096-1 3

BACS40R014F046F 2

(BACS40R014Y046F

Optional)

Shim

Bolt BACB30NM5K14 4

with the two bolts in the the

aft position.

Washer AN906KD516 2

with the two bolts in the

forward position.

Washer AN960XC516 2

to prepare the parts for the

final installation.

Spin Brake 141N0091-13 1

Assembly

3 Remove (New)

Filler 141N0096-1 3

BACS40R014F046F 2

(BACS40R014Y046F

Optional)

Shim

Bolt BACB30NM5K14 4

Washer AN960KD516 2

Washer AN960XC516 2

to the shims, fillers,

bolts,washers and the spin

brake assembly surface

that will contact the wheel

well ceiling.

4 Apply Sealant BMS 5-95 3 oz

FIGURE 5: SPIN BRAKE ASSEMBLY (COMPOSITE) - REPLACEMENT

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 757-32-0176
STEP TASK NAME IDENTIFICATION QTY MORE DATA

onto the nose wheel well

ceiling. (d) (e) (f) (g)

Spin Brake 141N0091-13 1

Assembly

5 Install (New)

Filler 141N0096-1 3

BACS40R014F046F 2

(BACS40R014Y046F

Optional)

Shim

Bolt BACB30NM5K14 4

with the two bolts in the the

aft position.

Washer AN960KD516 2

with the two bolts in the

forward position.

Washer AN960XC516 2

to the bolt heads and

washers once the spin

brake assembly is installed.

6 Apply Sealant BMS 5-95 1 oz

(a) Remove the spin brake assembly. Discard the spin brake assembly, bolts, shims, washers and fillers.

(b) Temporarily locate the spin brake assembly as follows: -- Loosely install the four bolts and washers

to hold the spin brake in the installed position. -- Make sure the forward surface of the spin brake is

14.95 to 15.05 inches from the nose wheel well forward bulkhead as shown in View A-A. -- Increase

or decrease the thickness of shim material as necessary, to retain a 14.95 to 15.05 inches dimension

between the nose wheel well forward bulkhead and the forward surface of the spin brake assembly

above the toe piece.

(c) This note is deleted.

(d) An additional filler P/N 141N0096-1 is required to install the replacement composite spin brake

assembly.

(e) Put the spin brake in position on the wheel well ceiling and install with the bolts and washers (4

locations),shims (2 locations) and fillers (3 locations). Install the fasteners with BMS 5-95 sealant in

accordance with SOPM 20-50-19.

(f) A shorter grip length is required to install the 141N0091-13 spin brake assembly. Bolt

P/NBACB30NM5K14 replaces P/N BACB30NM5K16. Alternatively, operators can install additional

washers under the heads of P/N BACB30NM5K16 to get the correct grip length.

(g) Tighten the bolts within a torque range of 40 to 60 inch pounds.

FIGURE 5: SPIN BRAKE ASSEMBLY (COMPOSITE) - REPLACEMENT

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 757-32-0176
FIGURE 6: SPIN BRAKE ASSEMBLY (CRES) - REPLACEMENT

(SHEET 1 OF 4)

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September 10, 2007

Revision 1 October 16, 2008 757-32-0176

47 of 55

BOEING SERVICE BULLETIN 757-32-0176
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 one spin brake assembly.

FIGURE 6: SPIN BRAKE ASSEMBLY (CRES) - REPLACEMENT

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 757-32-0176
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Spin Brake 141N0091-( ) 1 (a)

Assembly

1 Remove

Shim BACS40R014F050F 2

Filler 141N0096-1 2

Washer AN960JD516 4

Remove (Keep) Bolt BACB30NM5K16 4

Spin Brake 012N0042-1 1 (b)

Assembly

2 Locate (New)

Filler 012N0056-1 2

Shim BACS40R014Y050F 2

Washer, Plain NAS1149C0563R 4

Locate (kept) Bolt BACB30NM5K16 4

to prepare the parts for the

final installation.

Spin Brake 012N0042-1 1

Assembly

3 Remove (New)

Filler 012N0056-1 2

Shim BACS40R014Y050F 2

Washer, Plain NAS1149C0563R 4

Remove (Kept) Bolt BACB30NM5K16 4

to the shims, fillers, bolts,

washers and the spin

brake surface that will

contact the wheel well

ceiling.

4 Apply Sealant BMS 5-95 3 oz.

onto the nose wheel well

ceiling. (c) (d)

Spin Brake 012N0042-1 1

Assembly

5 Install (New)

Filler 012N0056-1 2

Shim BACS40R014Y050F 2

Washer, Plain NAS1149C0563R 4

Install (Kept) Bolt BACB30NM5K16 4

to the bolt heads and

washers once the spin

brake assembly is

installed.

6 Apply Sealant BMS 5-95 1 oz.

(a) Remove and keep the bolts that attach the spin brake assembly to the top surface of the wheel well and

remove the spin brake assembly. Discard the spin brake assembly, filler, washers and shims.

FIGURE 6: SPIN BRAKE ASSEMBLY (CRES) - REPLACEMENT

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 757-32-0176
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(b) Temporarily locate the spin brake assembly as follows: -- Loosely install the four bolts and washers to

hold the spin brake in the installed position. -- Make sure the aft surface of the spin brake is 15.42 to 15.52

inches from the nose wheel well forward bulkhead as shown in View A-A.-- Increase or decrease the

thickness of shim material as necessary, to retain a 15.42 to 15.52 inches dimension between the nose

wheel well forward bulkhead and the aft surface of the spin brake assembly above the toe piece.

(c) Put the spin brake in position on the wheel well ceiling and install with the bolts and washers (4 locations),

shims (2 locations) and fillers (2 locations). Install the fasteners with BMS 5-95 sealant in accordance with

SOPM 20-50-19.

(d) Tighten the bolts within a torque range of 40 to 60 inch pounds.

FIGURE 6: SPIN BRAKE ASSEMBLY (CRES) - REPLACEMENT

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 757-32-0176
FIGURE 7: SPIN BRAKE ASSEMBLY (COMPOSITE) - ASSEMBLE

(SHEET 1 OF 5)

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September 10, 2007

Revision 1 October 16, 2008 757-32-0176

51 of 55

BOEING SERVICE BULLETIN 757-32-0176
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 one spin brake assembly.

FIGURE 7: SPIN BRAKE ASSEMBLY (COMPOSITE) - ASSEMBLE

(SHEET 2 OF 5)

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BOEING SERVICE BULLETIN 757-32-0176
STEP TASK NAME IDENTIFICATION QTY MORE DATA

0.380 - 0.384 inch

diameter in the new

141N0091-5 Spring only.

1 Drill Holes - 8

0.443 - 0.447 inch

diameter in the new

141N0091-5 Spring only

2 Drill Holes - 2

on the new Spring

141N0091-5. (b)

3 Put/Hold Brake Pad 141N0091-14 1

0.203 - 0.207 inch

diameter. Use the holes

drilled in the new Spring

141N0091-5 as guides for

hole locations.

Drill Brake Pad 141N0091-14 8

0.375 inch diameter to the

depth shown.

Counterbore Brake Pad 141N0091-14 8

to 0.315 inch diameter,

100 degrees as shown.

Countersink Brake Pad 141N0091-14 8

4 Remove/Keep Brake Pad 141N0091-14 1 from the new Spring.

on the new Spring. Mark

the Insulator around its

edge to match Spring and

brake Pad contour.

1

1

141N0091-15

141N0091-14

Insulator

and

Brake Pad

5 Put/Hold

Remove Brake Pad 141N0091-14 1 from the new Spring.

Remove Insulator 141N0091-15 1 from the new Spring.

to match spring and brake

pad contour as shown. (c)

Cut Insulator 141N0091-15 1

in Toe Piece Insulator if

necessary.

6 Make Hole - 2

7 Apply Adhesive BAC5010, Type 60 - to 141N0091-12 Bushing.

bond the bushing in the

new Spring 141N0091-5

Spring. Refer to SOPM

20-50-12, Type 60.

Install (New) Bushing 141N0091-12 8

FIGURE 7: SPIN BRAKE ASSEMBLY (COMPOSITE) - ASSEMBLE

(SHEET 3 OF 5)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

to 141N0091-11 Bushing

and 141N0091-10 Toe

Piece Insulators.

8 Apply Adhesive BAC5010, Type 60 -

bond the bushing to the

141N0091-5 Spring.

Refer to SOPM 20-50-12

as an accepted procedure

Install (New) Bushing 141N0091-11 2

bond the insulator to the

141N0091-5 Spring.

Refer to SOPM 20-50-12

as an accepted

procedure.

Install (New) Toe Piece Insulator 141N0091-10 2

9 Apply Adhesive BAC5010, Type 60 - to washer 141N0096-2.

bond the washer to the

new Insulator. Refer to

SOPM 20-50-12 as an

accepted procedure.

Install (New) Washer 141N0096-2 2

10 Apply Adhesive BAC5010, Type 60 - to insulator 141N0091-15.

bond the insulator to the

141N0091-5 Spring.

Refer to SOPM 20-50-12

as an accepted

procedure.

Install (New) Insulator 141N0091-15 1

Install (New) Toe Piece 141N0097-4 1

Install (New) Bolt BACB30MY8K8 2

Install (New) Nut BACN10JC4CD 2 (a)

11 Install (New) Brake Pad 141N0091-14 1

Apply Adhesive BAC5010, Type 60 - to washer NAS549-10

bond the washer to the

141N0091-5 Spring.

Refer to SOPM 20-50-12

as an accepted

procedure.

Install (New) Washer NAS549-10 8

torque tighten to 8 -10

inch-pounds.

Install (New) Bolt BACB30NW6K7 8

Install (New) Nut BACN10JC3CM 8

(a) Torque tighten the nuts to between 40 to 60 inch pounds.

FIGURE 7: SPIN BRAKE ASSEMBLY (COMPOSITE) - ASSEMBLE

(SHEET 4 OF 5)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

(b) Clamp the brake pad to the new spring to achieve 0.00/0.06 maximum gap between the spring and the

brake pad. The contour or the brake pad can vary at the large radius. If necessary the brake pad can

be heated to 250 degree Fahrenheit (max) to form the brake pad to the contour of the spring.

(c) Zig-Zag stitch edges to prevent fraying of edges. Use 141N0091-16 Teflon coated glass fiber thread in

accordance with BAC5437, or 141N0091-21 Nomex size E thread in accordance with MIL-T-43636.

FIGURE 7: SPIN BRAKE ASSEMBLY (COMPOSITE) - ASSEMBLE

(SHEET 5 OF 5)

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BOEING SERVICE BULLETIN 757-32-0176