Commercial 

Airplanes 767

Service Bulletin

SPECIAL ATTENTION

Number: 767-29-0113

Original Issue: May 29, 2013

ATA System: 2911

SUBJECT: MAIN HYDRAULIC SYSTEMS - Center Hydraulic System Air Driven Pump (ADP) -

Turbine Gearbox Assembly (TGA) Replacement

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

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2013 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

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BLANK PAGE
Table of Contents

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

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

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

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

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

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

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

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

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

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

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

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

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

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

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

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

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

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

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

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

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

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

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

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

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

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 16

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

FIGURE 1: TURBINE GEARBOX ASSEMBLY (TGA) - AIRPLANE SKIN INTERFACE - BOTTOM AND TOP

AFT TIE ROD ASSEMBLY - DISCONNECT [Group 1, Configuration 1] . . . . . . . . . . 19

FIGURE 2: TURBINE GEARBOX ASSEMBLY (TGA) - TGA INTERFACE - BOTTOM AND TOP AFT TIE

ROD ASSEMBLY - REMOVAL [Group 1, Configuration 1] . . . . . . . . . . . . . . . . . . 22

FIGURE 3: TURBINE GEARBOX ASSEMBLY (TGA) - AIRPLANE SKIN INTERFACE - BOTTOM AND TOP

AFT TIE ROD ASSEMBLY - INSTALLATION [Group 1, Configuration 1] . . . . . . . . . . 24

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BOEING SERVICE BULLETIN 767-29-0113

BLANK PAGE
Commercial 

Airplanes 767

Service Bulletin

SPECIAL ATTENTION

Summary Number: 767-29-0113

Original Issue: May 29, 2013

ATA System: 2911

SUBJECT: MAIN HYDRAULIC SYSTEMS - Center Hydraulic System Air Driven Pump (ADP) -

Turbine Gearbox Assembly (TGA) Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Accomplishment of this service bulletin will make sure that the existing Air Driven Pump (ADP) Turbine Gearbox

Assembly (TGA) of the Center Hydraulic System is replaced with an improved ADP TGA. The improved ADP

TGA includes significant changes of the containment capabilities over the existing design. The new design

minimizes the risk of external damage associated with fractures to the ADP TGA and the release of high energy

fragments during an ADP TGA turbine wheel burst. If the existing ADP TGA is not replaced, and an uncontained

turbine wheel burst occurs, high energy fragments could cause damage to the airplane and hazards to persons

or property on the ground.

Analysis by Boeing finds that the existing ADP TGA design cannot adequately contain fragments caused by a

ADP TGA turbine wheel burst.

Operators have reported uncontained failures of the ADP TGA turbine wheel when flight crews noticed a reduction

in center hydraulic system pressure, and upon landing, found damage to the ADP TGA, left aft wing-to-body

fairing, and airplane skin.

This service bulletin gives instructions to replace the existing ADP TGA with an improved ADP TGA that can

adequately contain a turbine burst event should one occur.

Boeing Service Related Problem (SRP) 767-SRP-29-0083 is related to this service bulletin.

Service History

Cycles/Years/Hours Report

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 41,004

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 8,522

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Service History

Cycles/Years/Hours Report

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 2,021

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 29,189

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 31,827

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 33,968

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 35,743

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change Yes Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required No Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION (PRR B12901-104S)

Remove the existing ADP TGA.

Install a new ADP TGA.

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BOEING SERVICE BULLETIN 767-29-0113
EFFECTIVITY

767-400ER Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

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 36 months after the original

issue date of this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the repair procedures given in this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

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

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BOEING SERVICE BULLETIN 767-29-0113
Commercial 

Airplanes 767

Service Bulletin

SPECIAL ATTENTION

Number: 767-29-0113

Original Issue: May 29, 2013

ATA System: 2911

SUBJECT: MAIN HYDRAULIC SYSTEMS - Center Hydraulic System Air Driven Pump (ADP) -

Turbine Gearbox Assembly (TGA) Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent

production airplanes. Refer to PRR B12901-104S for data about this change.

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

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

1 - 767-400ER Airplanes.

Airplanes with Protective Blanket installed on the Turbine Gearbox

Assembly.

1

Airplanes without Protective Blanket installed on Turbine Gearbox

Assembly.

2

Airplane Models:

767-400ER

Variable Number Group

VQ001 - VQ021 1

VQ071 - VQ086 1

VQ111 1

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2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

Accomplishment of this service bulletin will make sure that the existing Air Driven Pump (ADP) Turbine

Gearbox Assembly (TGA) of the Center Hydraulic System is replaced with an improved ADP TGA. The

improved ADP TGA includes significant changes of the containment capabilities over the existing

design. The new design minimizes the risk of external damage associated with fractures to the ADP

TGA and the release of high energy fragments during an ADP TGA turbine wheel burst. If the existing

ADP TGA is not replaced, and an uncontained turbine wheel burst occurs, high energy fragments could

cause damage to the airplane and hazards to persons or property on the ground.

Analysis by Boeing finds that the existing ADP TGA design cannot adequately contain fragments caused

by a ADP TGA turbine wheel burst.

Operators have reported uncontained failures of the ADP TGA turbine wheel when flight crews noticed

a reduction in center hydraulic system pressure, and upon landing, found damage to the ADP TGA,

left aft wing-to-body fairing, and airplane skin.

This service bulletin gives instructions to replace the existing ADP TGA with an improved ADP TGA

that can adequately contain a turbine burst event should one occur.

Boeing Service Related Problem (SRP) 767-SRP-29-0083 is related to this service bulletin.

Service History

Cycles/Years/Hours Report

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 41,004

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 8,522

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 2,021

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 29,189

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 31,827

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Service History

Cycles/Years/Hours Report

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 33,968

ADP TGA Turbine wheel burst resulted in fractures to the ADP

TGA and release of high energy fragments. Release of the high

energy fragments resulted in airplane damage.

TGA Service Hours 35,743

D. Description

Remove the existing ADP TGA.

Install a new ADP TGA.

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

Affected Maintenance Zones

Model Zone

767-400ER 197

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 36 months after the

original issue date of 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:

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BOEING SERVICE BULLETIN 767-29-0113
• 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.

Group 1, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Remove Existing 2 3.25 1.625

ADP TGA

FIGURE 1 1 - -

FIGURE 2 1 0.25 0.25

FIGURE 3 1 - -

Install New ADP 2 3.25 1.625

TGA

TOTAL FOR EACH AIRPLANE 6.75 3.50

Group 1, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Remove Existing 2 3.25 1.625

ADP TGA

Install New ADP 2 3.25 1.625

TGA

TOTAL FOR EACH AIRPLANE 6.50 3.25

The time to make the change to the Air Driven Pump (ADP) Turbine Gearbox Assembly (TGA) in

accordance with Fairchild Controls SB N012000000-29-03 R2 Service Bulletin is not included.

Group 1, Configuration 1:

The time to do the task in Figure 1 and Figure 3 is already given in the Removal and Installation of the

ADP TGA.

H. Weight and Balance Changes

Group 1, Configuration 1:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

767-400ER +4.6 lb. +5350.7 lb.-in.

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BOEING SERVICE BULLETIN 767-29-0113
Group 1, Configuration 2:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

767-400ER +16.6 lb. +19309.0 lb.-in.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR B12901-104S

b. Boeing Service Related Problem (SRP) 767-SRP-29-0083

c. Service Bulletin Index D624T001

d. 767 Aircraft Maintenance Manual (AMM) 29-11-03

e. Fairchild Controls Service Bulletin Fairchild Controls SB N012000000-29-03 R2

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

271T4606 AIR DRIVE UNIT INSTALLATION - SECTION 46

The table above lists a applicable drawing used to prepare this service bulletin. The drawing is

not necessary to make the specified changes, and is not supplied with this service bulletin. The

drawing may not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

767 Illustrated Parts Catalog 29-11

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.

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BOEING SERVICE BULLETIN 767-29-0113
L. Interchangeability and Intermixability of Parts

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

information.

M. Software Accomplishment Summary

Not affected.

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BOEING SERVICE BULLETIN 767-29-0113
2. MATERIAL INFORMATION

A. Material - Price and Availability

The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each

Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin

does not show the Boeing price and supply data.

B. Industry Support Information

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

this service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

The following parts or materials are necessary to do the change in this service bulletin. Parts and

materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine

operator part and material supply to make sure all necessary parts and materials are available.

Part Number / QTY Name Existing Part Number Notes

Specification

N012000000-2 1 Turbine Gearbox Assembly (TGA) N012000000 (a) (b) (c) (d)

or or

N012000000-3 N012000000-1

(a) You cannot use the existing part to replace the new or changed part.

(b) Fairchild Controls SB N012000000-29-03 R2 gives instructions to change the existing part to the

new/changed part.

(c) Boeing Specification Number S271T401-11 corresponds to Fairchild Controls Part Numbers N012000000-

2 or N012000000-3.

(d) Boeing Specification Number S271T401-1 corresponds to Fairchild Controls Part Numbers N012000000

or N012000000-1.

Group 1, Configuration 1:

Part Number / QTY Name Notes

Specification

BACP18BC02A06P 4 Cotter Pin

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BOEING SERVICE BULLETIN 767-29-0113
Group 1, Configuration 2:

Part Number / QTY Name Notes

Specification

BACP18BC02A06P 2 Cotter Pin

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

None.

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BOEING SERVICE BULLETIN 767-29-0113
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. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

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

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

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

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

SRM Chapter 51.

5. If the length of any fastener specified in this service bulletin does not meet 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. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51.

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.

7. The instructions in Paragraph 3.B., Work Instructions and the figures can include

operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated

Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing

Index contain data on versions of the tools or test equipment that you can use. It is

permitted to use replaced tools. It is not permitted to use superseded tools.

8. 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.

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.

10. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

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BOEING SERVICE BULLETIN 767-29-0113
B. WORK INSTRUCTIONS

1. Remove the existing Air Driven Pump (ADP) Turbine Gearbox Assembly (TGA) part number

N012000000 or N012000000-1. Refer to 767 AMM 29-11-03 as an accepted procedure.

Group 1, Configuration 1:

NOTE: When the ADP TGA of the Center Hydraulic System is removed from the airplane, it can

be difficult to disconnect the bottom and top aft tie rod assemblies from the ADP TGA

because of interference with the protective blanket. Figures 1 - 3, as referred to below,

provide an alternative method to disconnect/connect these tie rod assemblies from/to the

bottom and top aft ADP TGA airplane skin interface.

Group 1, Configuration 1:

a. You can do the following steps as an alternative to the tie rod disconnection instructions given

in 767 AMM 29-11-03.

(1) Disconnect the bottom and top aft tie rod assemblies in accordance with FIGURE 1

(2) Remove and keep the bottom and top aft tie rod assemblies from the ADP TGA in

accordance with FIGURE 2.

(3) Install the kept bottom and top aft tie rod assemblies at the airplane skin interface in

accordance with FIGURE 3.

2. Install the new ADP TGA part number N012000000-2 or N012000000-3. Refer to 767 AMM

29-11-03 as an accepted procedure.

3. Put the airplane back to a serviceable condition.

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767-29-0113

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BOEING SERVICE BULLETIN 767-29-0113
This Figure applies only to: Group 1, Configuration 1.

FIGURE 1: TURBINE GEARBOX ASSEMBLY (TGA) - AIRPLANE SKIN INTERFACE - BOTTOM AND TOP

AFT TIE ROD ASSEMBLY - DISCONNECT

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-29-0113
FIGURE 1: TURBINE GEARBOX ASSEMBLY (TGA) - AIRPLANE SKIN INTERFACE - BOTTOM AND TOP

AFT TIE ROD ASSEMBLY - DISCONNECT

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-29-0113
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 each airplane.

Step Task Name Identification Qty More Data

1 Remove Cotter Pin - 2

Remove / Keep Nut - 2

Remove / Keep Washer - 4

Remove / Keep Bolt - 2

Remove / Keep Bushing - 2

Disconnect Tie Rod Assembly - 2

FIGURE 1: TURBINE GEARBOX ASSEMBLY (TGA) - AIRPLANE SKIN INTERFACE - BOTTOM AND TOP

AFT TIE ROD ASSEMBLY - DISCONNECT

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-29-0113
This Figure applies only to: Group 1, Configuration 1.

FIGURE 2: TURBINE GEARBOX ASSEMBLY (TGA) - TGA INTERFACE - BOTTOM AND TOP AFT TIE ROD

ASSEMBLY - REMOVAL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-29-0113
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 each airplane.

Step Task Name Identification Qty More Data

1 Remove Cotter Pin - 2

Remove / Keep Nut - 2

Remove / Keep Washer - 4

Remove / Keep Bolt - 2

Remove / Keep Bushing - 2

Disconnect at Clevis

Bracket/TGA interface.

Remove / Keep Tie Rod Assembly - 2

FIGURE 2: TURBINE GEARBOX ASSEMBLY (TGA) - TGA INTERFACE - BOTTOM AND TOP AFT TIE ROD

ASSEMBLY - REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-29-0113
This Figure applies only to: Group 1, Configuration 1.

FIGURE 3: TURBINE GEARBOX ASSEMBLY (TGA) - AIRPLANE SKIN INTERFACE - BOTTOM AND TOP

AFT TIE ROD ASSEMBLY - INSTALLATION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-29-0113
FIGURE 3: TURBINE GEARBOX ASSEMBLY (TGA) - AIRPLANE SKIN INTERFACE - BOTTOM AND TOP

AFT TIE ROD ASSEMBLY - INSTALLATION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-29-0113
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 each airplane.

Step Task Name Identification Qty More Data

1 Install (Kept) Tie Rod Assembly - 2

Install (Kept) Bushing - 2

Install (Kept) Washer - 4

Install (Kept) Bolt - 2

Tighten the nut to 65

+/- 2 Inch Pounds.

Install (Kept) Nut - 2

Install (New) Cotter Pin BACP18BC02A06P 2

FIGURE 3: TURBINE GEARBOX ASSEMBLY (TGA) - AIRPLANE SKIN INTERFACE - BOTTOM AND TOP

AFT TIE ROD ASSEMBLY - INSTALLATION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-29-0113