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Commercial Airplanes DC10 Service Bulletin ALERT Number: DC10-32A260 Original Issue: September 30, 2011 ATA System: 3200 SUBJECT: LANDING GEAR - Landing Gear - Replaces Left and Right Main Landing Gear Upper Torque Link Bolt 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.

9E991ECCN:

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: September 30, 2011 DC10-32A260 1 of 16

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Original Issue: September 30, 2011 DC10-32A260 2 of 16 BOEING SERVICE BULLETIN DC10-32A260

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Table of Contents

Summary5

1. PLANNING INFORMATION7

A. Effectivity7

1. Airplanes7

2. Spares Affected8

B. Concurrent Requirements8

C. Reason8

D. Description9

E. Compliance9

F. Approval ............................................... 1 0 G. Manpower .............................................. 1 0 H. Weight and Balance Changes .................................... 1 1 I. Electrical Load Data ......................................... 1 1 J. References .............................................. 1 1

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

2. Data supplied with this Service Bulletin ............................ 1 1

3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 1 K. Publications Affected ........................................ 1 1 L. Interchangeability and Intermixability of Parts ........................... 1 1

2. MATERIAL INFORMATION ........................................ 1 3 A. Material - Price and Availability ................................... 1 3 B. Industry Support Information .................................... 1 3 C. Parts Necessary For Each Airplane ................................. 1 3

1. Kits/Parts ............................................ 1 3

2. Parts and Materials Supplied by the Operator ........................ 1 3

3. Parts Modified and Reidentified ................................ 1 4

4. Parts Removed and Not Replaced .............................. 1 4 D. Parts Necessary to Change Spares ................................. 1 4 E. Special Tooling - Price and Availability ............................... 1 4 F. Special Tooling Necessary to do this Service Bulletin ....................... 1 4

3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 5 A. GENERAL INFORMATION ..................................... 1 5 B. WORK INSTRUCTIONS ....................................... 1 5

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Original Issue: September 30, 2011 DC10-32A260 4 of 16 BOEING SERVICE BULLETIN DC10-32A260

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Commercial Airplanes DC10 Service Bulletin ALERT SummaryNumber: DC10-32A260Original Issue: September 30, 2011 ATA System: 3200 SUBJECT: LANDING GEAR - Landing Gear - Replaces Left and Right Main Landing Gear Upper Torque Link Bolt

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER.

CONCURRENT REQUIREMENTS None.

BACKGROUND In 1999, Boeing approved the fabrication of part number ARG7063-503 Main Landing Gear (MLG) Upper Torque Link Bolt from bar stock with a machined head in lieu of an upset forged head. Between 2000 and 2006 Boeing received 28 bolts that were fabricated from bar stock and a machined head. The bolts are a Safe Life Limit (SLL) item and are required to be serialized for traceability. Boeing has determined that this substitution reduces the SLL of the bolt from 47,300 flight cycles to 6,590 flight cycles. As a result of the reduced SLL, Boeing has ceased allowing the manufacture of the bolt from bar stock and a machined head. This service bulletin is being issued to advise affected operators of the bolt SLL reduction and allow their processes to monitor and replace the bolts prior to reaching the SLL. If not corrected, a bolt fabricated from bar stock and a machined head exceeding 6,590 flight cycle SLL could fail resulting in MLG damage and potentially cause significant damage to the airplane.

ACTION Refer to Paragraph 1.D., Description.

EFFECTIVITY DC-10 and MD-10 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.

Refer to Paragraph 1.E., Compliance.

Original Issue: September 30, 2011 DC10-32A260 5 of 16

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INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the information provided in this service bulletin.

MANPOWER Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION None.

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THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER.

1. PLANNING INFORMATION A. Effectivity

1. Airplanes This service bulletin is for the airplanes shown below.

DESCRIPTIONCONFIGURATIONGROUP Inspect Left and Right Main Landing Gear Upper Torque Link Bolt-1 Airplane Models:

DC-10-10, MD-10-10F GroupFuselage Number 132 139 155 186 189 1119 1139

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GroupFuselage Number 1142 1198 1207 - 209 1250 1273 1285 1319 1353 1379

2. Spares Affected Examine your spares supply for part number ARG7063-503 Main Landing Gear (MLG) Upper Torque Link Bolt with the serial numbers that follow. If any parts are found, a reduced Safe Life Limit threshold of 6,590 flight cycle applies if installed.

Serial NumberManufacturer CPI0001, CPI0002, CPI0003, CPI0004, CPI0005, CPI0006, CPI0007, CPI0008, CPI0009, CPI0010, CPI0011, CPI0012, CPI0013, CPI0014, and CPI0015 Castle Precision Industries 0001, 0002, 0003, 0004, 0005, 0006, 0007, 0008, 0010, 0011, 0012, 0013 and 0014 Tuffer Manufacturing B. Concurrent Requirements None.

C. Reason In 1999, Boeing approved the fabrication of part number ARG7063-503 Main Landing Gear (MLG) Upper Torque Link Bolt from bar stock with a machined head in lieu of an upset forged head. Between 2000 and 2006 Boeing received 28 bolts that were fabricated from bar stock and a machined head.

The bolts are a Safe Life Limit (SLL) item and are required to be serialized for traceability. Boeing has determined that this substitution reduces the SLL of the bolt from 47,300 flight cycles to 6,590 flight cycles. As a result of the reduced SLL, Boeing has ceased allowing the manufacture of the bolt from bar stock and a machined head. This service bulletin is being issued to advise affected operators of the bolt SLL reduction and allow their processes to monitor and replace the bolts prior to reaching the SLL. If not corrected, a bolt fabricated from bar stock and a machined head exceeding 6,590 flight cycle SLL could fail resulting in MLG damage and potentially cause significant damage to the airplane.

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D. Description This service bulletin replaces Castle Precision Industries and Tuffer Manufacturing Main Landing Gear (MLG) Upper Torque Link Bolt part number ARG7063-503 on the left and right MLG fabricated from bar stock and a machined head as follows:

1. Replaces bolt(s) with new or serviceable part number ARG7063-503.

NOTE: Serviceable part number must be within its Safe Life Limit (SLL) and can not have one of the aforementioned serial numbers.

Option 2

1. Replaces bolt(s) with new or serviceable part number ARG7323-1 and related hardware.

Option 3

1. Monitors bolt(s) SLL and does Option 1 or Option 2 at threshold specified in Paragraph 1.E., Compliance.

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

Affected Maintenance Zones ZoneModel 734, 744DC-10-10, MD-10-10F 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.

Accomplish the required action(s), based on the applicable condition(s), in Table(s) 1, in accordance with Paragraph 3. Accomplishment Instructions.

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Table 1: Replace Upper MLG Torque Link Bolts fabricated from bar stock and a machined head.

Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before 6,590 flight cycles from installation.

Before further flight.

Replace bolt fabricated from bar stock and a machined head.

All Airplanes F. Approval MD-10 Airplanes:

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. 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.

DC-10 Airplanes:

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.

G. Manpower The table below shows an estimate of the task hours necessary to do this service bulletin for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time:

Time to adjust to the workplace Time to schedule the work Time to inspect the work Time to cure the materials Time to make the parts Time to find the tools.

Elapsed HoursTask HoursNumber of PersonsTask

1.02.02Replace

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Elapsed HoursTask HoursNumber of PersonsTask

1.02.0TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes Option 1 None.

Option 2 Moment Change (MEW) IN.-LBS Mfr's Empty Weight (MEW) LBS Approximate Station (Inches)Airplane +12833.8+8.9+1442.0DC-10-10, MD-10- 10F I. Electrical Load Data Not changed.

J. References

1. Existing Data

a. DC-10, MD-10 Aircraft Maintenance Manual (AMM) 32-00-00, 32-11-02.

2. Data supplied with this Service Bulletin None.

3. Installation Drawings Used in the Preparation of this Service Bulletin None.

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

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