### 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 CFR 300-774). 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. 9E991 ECCN: 

## 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 Unpublished Work.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 are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries 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.

Original Issue: May 29, 2013 767-29-0113 1 of 26 3.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 2 of 26 **BOEING SERVICE BULLETIN 767-29-0113**

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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 3 of 26 **BOEING SERVICE BULLETIN 767-29-0113**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 4 of 26 **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 Report**  **Cycles/Years/Hours** 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 5 of 26**Service History Report**  **Cycles/Years/Hours** 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.
**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected No Spares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes Yes Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected Yes Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts No Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required
**ACTION (PRR B12901-104S)** Remove the existing ADP TGA. Install a new ADP TGA.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 6 of 26 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 7 of 26 **BOEING SERVICE BULLETIN 767-29-0113**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 8 of 26 **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.
**DESCRIPTION CONFIGURATION**  **GROUP** 767-400ER Airplanes.

- 1 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 **Group Variable Number**  1 VQ001 - VQ021 1 VQ071 - VQ086 1 VQ111

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 9 of 262. 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 Report**  **Cycles/Years/Hours** 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 10 of 26 **BOEING SERVICE BULLETIN 767-29-0113 Service History**  **Report Cycles/Years/Hours**  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 Zone**  **Model** 197 767-400ER **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:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 11 of 26 **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: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 1.625 3.25 2 Remove Existing ADP TGA

- - 1 FIGURE 1 0.25 0.25 1 FIGURE 2

- - 1 FIGURE 3 1.625 3.25 2 Install New ADP TGA 3.50 6.75 TOTAL FOR EACH AIRPLANE **Group 1, Configuration 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 1.625 3.25 2 Remove Existing ADP TGA 1.625 3.25 2 Install New ADP TGA 3.25 6.50 TOTAL FOR EACH AIRPLANE 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 (Pounds)**  **Airplane** +5350.7 lb.-in. +4.6 lb. 767-400ER

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 12 of 26 **BOEING SERVICE BULLETIN 767-29-0113 Group 1, Configuration 2:**  **Change in Moment (Pound-Inches)**  **Change in Weight (Pounds)**  **Airplane** +19309.0 lb.-in. +16.6 lb. 767-400ER
**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:
**Title Drawing Number**  AIR DRIVE UNIT INSTALLATION - SECTION 46 271T4606 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: **Chapter-Section Publication**  29-11 767 Illustrated Parts Catalog 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 13 of 26 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 14 of 26 **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.
**Notes Existing Part Number**  **Name QTY**  **Part Number / Specification**  (a) (b) (c) (d) N012000000 Turbine Gearbox Assembly (TGA) 1 N012000000-2 or or N012000000-1 N012000000-3 (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:**
**Notes Name**  **QTY Part Number /**  **Specification** Cotter Pin 4 BACP18BC02A06P

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 15 of 26 **BOEING SERVICE BULLETIN 767-29-0113 Group 1, Configuration 2:** 
**Notes Name**  **QTY Part Number /**  **Specification** Cotter Pin 2 BACP18BC02A06P
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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 16 of 26 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 17 of 26 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 18 of 26 **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)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 19 of 26 **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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 20 of 26 **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.
**More Data Qty**  **Identification Name**  **Task Step**  2
- Cotter Pin Remove 1 2
- Nut Remove / Keep 4
- Washer Remove / Keep 2
- Bolt Remove / Keep 2
- Bushing Remove / Keep 2
- Tie Rod Assembly Disconnect

**FIGURE 1: TURBINE GEARBOX ASSEMBLY (TGA) - AIRPLANE SKIN INTERFACE - BOTTOM AND TOP AFT TIE ROD ASSEMBLY - DISCONNECT**  **(SHEET 3 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 21 of 26 **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)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 22 of 26 **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.
**More Data Qty**  **Identification Name**  **Task Step**  2
- Cotter Pin Remove 1 2
- Nut Remove / Keep 4
- Washer Remove / Keep 2
- Bolt Remove / Keep 2
- Bushing Remove / Keep Disconnect at ClevisBracket/TGA interface. 2
- Tie Rod Assembly Remove / Keep

**FIGURE 2: TURBINE GEARBOX ASSEMBLY (TGA) - TGA INTERFACE - BOTTOM AND TOP AFT TIE ROD ASSEMBLY - REMOVAL**  **(SHEET 2 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 23 of 26 **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)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 24 of 26 **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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 25 of 26 **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.
**More Data Qty**  **Identification Name**  **Task Step**  2
- Tie Rod Assembly Install (Kept) 1 2
- Bushing Install (Kept) 4
- Washer Install (Kept) 2
- Bolt Install (Kept) Tighten the nut to 65 +/- 2 Inch Pounds. 2
- Nut Install (Kept)

2 BACP18BC02A06P Cotter Pin Install (New)

**FIGURE 3: TURBINE GEARBOX ASSEMBLY (TGA) - AIRPLANE SKIN INTERFACE - BOTTOM AND TOP AFT TIE ROD ASSEMBLY - INSTALLATION**  **(SHEET 3 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 29, 2013 767-29-0113 26 of 26 **BOEING SERVICE BULLETIN 767-29-0113**