August 29, 2002

Revision 3 May 20, 2004 737-71A1462

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 62

ALERT ALERT

Commercial

Airplane

Group 737

ALERT ALERT

Service Bulletin

Number: 737-71A1462

Date: August 29, 2002

Revision 3 May 20, 2004

ATA System: 7121

SUBJECT: POWER PLANT - Engine Mounts - Aft Engine Mount, Link Assembly, Hanger Fitting,

Inspection, Correction and Identification of Parts

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2002 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Unpublished Work - All Rights Reserved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, BBJ, DC-8, DC-9,

DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the red-white-and-blue Boeing livery are all trademarks

owned by The Boeing Company; and no trademark license is granted in connection with this document unless

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BLANK PAGE

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

BLANK PAGE
Table of Contents

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 31

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 31

4. Process Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 32

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 33

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 34

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

FIGURE 1: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) INSTALLATION

INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

FIGURE 2: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) REMOVAL AND

INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

FIGURE 3: AFT ENGINE MOUNT, CENTER LINK (WITH POCKETS) INSTALLATION INSPECTION 45

FIGURE 4: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) REMOVAL AND

INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47

FIGURE 5: HANGER FITTING, ADD IDENTIFICATION MARKS . . . . . . . . . . . . . . . . . . . . 51

FIGURE 6: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS), ADD

IDENTIFICATION MARKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52
Table of Contents

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

FIGURE 7: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS), ADD

IDENTIFICATION MARKS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53

FIGURE 8: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) AND ENGINE

INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54

FIGURE 9: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) AND ENGINE

INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

APPENDIX A: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY REPORT FORM . . . . . . . . . . 62
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ALERT ALERT

Commercial

Airplane

Group 737

ALERT ALERT

Service Bulletin

Number: 737-71A1462 Revision Transmittal Sheet

Date: August 29, 2002

Revision 3 May 20, 2004

ATA System: 7121

SUBJECT: POWER PLANT - Engine Mounts - Aft Engine Mount, Link Assembly, Hanger Fitting,

Inspection, Correction and Identification of Parts

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-03-01, Amendment 39-13025, is related

to this service bulletin.

More work is necessary for airplanes that have not had an engine change since the new airplane was received

from Boeing, do the Part 1 Inspection procedures unless the Part 1 Inspection or the Part 2 Part Mark

procedures have been done.

No more work is necessary on airplanes that have had an engine change since the new airplane was received

from Boeing, have done the Part 1 Inspection and Part 2 Part Mark procedures.

No airplanes have been added by Revision 3 of this service bulletin. The Revision 2 of this service bulletin

included the airplanes effectivity that could be affected by this service bulletin.

REASON FOR REVISION

Revision 3 is sent to tell operators that for the airplanes that have not had an engine change since the new

airplane was received from Boeing, it is possible that some center links were incorrectly installed in an aft engine

mount before the airplane was delivered. Before this revision, inspection of the aft engine mounts was

necessary only for the airplanes that had an engine change after the new airplane was received from Boeing.

With the release of Revision 3 of this service bulletin, the Part 1 Inspection is applicable to all airplanes given in

the effectivity of this service bulletin.

1. On Summary section, Background, paragraph 1.C., Reason and paragraph 1.D., Description, more

information has been added to include the airplanes that have not had an engine change since the new

airplane was received from Boeing.

2. On Summary section, Background, paragraph 1.C., Reason and paragraph 1.J., References, a new

paragraph has been added to show the Boeing Service Related Problem information that is related to this

service bulletin.
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3. On Summary section and paragraph 1.E., Compliance information, the paragraphs about Part 1 have been

changed to include airplanes that have not had an engine change since the new airplane was received from

Boeing. The paragraphs about Part 2 have been changed to give more information. All engine installed

after 90 days has been changed to during the subsequent engine changes done after 90 days.

4. On paragraph 1.A., Planning Information, Effectivity, a group condition table has been added.

5. On paragraph 2.B., Industry Support Information, a warranty statement has been added for airplanes that

have not had an engine change since the new airplane was received from Boeing.

6. On paragraph 2.C.3., Parts Modified and Reidentified table and Figure 5 work instruction table, Step 2, the

part numbers for the hanger fitting 310A2031-23 and the hanger fitting assembly 310A2031-24 have been

added.

7. On paragraph 3.B.,Part 1,2., the work instruction step has been changed to delete information about

airplanes that have had an engine change after the airplane was delivered and during subsequent engine

installations. The changed Step 2 make the step applicable to all airplanes and the same compliance

information is already shown in the Compliance paragraphs.

8. On paragraph 3.B.,Part 1,3.e. and Part 2,1., the work instruction steps have been added for airplanes if do

or not do the Part 1 and Part 2 Work Instructions at the same time.

9. On paragraph 3.B.,Part 1,4., the work instruction step has been added for airplanes that have found the aft

engine mounts correctly installed.

10. On paragraph 3.B.,Part 2,4., the work instruction step has been added to close access. The note on the

left, right and aft markings has been changed to a Caution note.

11. Figures 1 and 3 have been changed to show the left side view to agree with the note that said the best view

is from the left side. The view was shown from the right side of the aft engine mount.

12. Figures 2 and 4 have been changed to delete the assembly and installation steps Steps 9 through 12. The

same assembly and installation steps have been moved to the new Figures 8 and 9 for airplanes that

possibly do Part 1 Correction and Part 2 part mark work instructions at the same time.

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: August 29, 2002

Revision 1: November 7, 2002

Revision 2: May 29, 2003

Revision 3: May 20, 2004
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ALERT ALERT

Commercial

Airplane

Group 737

ALERT ALERT

Service Bulletin

Number: 737-71A1462 Summary

Date: August 29, 2002

Revision 3 May 20, 2004

ATA System: 7121

SUBJECT: POWER PLANT - Engine Mounts - Aft Engine Mount, Link Assembly, Hanger Fitting,

Inspection, Correction and Identification of Parts

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

Part 1 of this service bulletin was initially prepared to give instructions for operators to do a one-time inspection

of all airplanes that have had an engine change since the airplane was delivered. It is necessary to do the

inspection on all subsequent engine changes unless Part 2 marked engine mounts are installed.

In September 2003, an operator told Boeing that an airplane was found with a center link installed incorrectly

on an aft engine mount. The operator also told Boeing that the airplane had not had an engine change since

the new airplane was received from Boeing. As a result, it is necessary for airplanes that have not had an engine

change since the new airplane was received from Boeing to do the Part 1 inspection on each of the aft engine

mounts.

In October 2001, one operator told Boeing it was necessary to get clarification of manuals related to engine

mount assembly and installation. After the initial help from Boeing, the operator reported that the aft engine

mount center link assembly, P/N 310A2034-3, could have been reversed during overhaul assembly and

subsequently installed on airplanes. The operator inspected all airplanes that had engine installations since the

airplanes were delivered. Six reversed center links were found, which were immediately corrected. No damage

was reported after visual inspection of the aft mount and local engine attachment was completed.

The operator found that no anomalies were reported during the aft engine mount installations or during the

engine installations. It was found that some increase in force was necessary to install the pawl pins that attach

the aft engine mount to the engine.
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In December 2001, a second operator told Boeing about problems they had when they tried to close the thrust

reversers after engine replacement. Visual inspection showed gap differences between the thrust reverser aft

cowl and the primary exhaust sleeve on the two sides of the engine. The engine was lowered and the

subsequent inspection found a reversed center link assembly, P/N 310A2034-7. After the center link was

removed and installed correctly, the engine installation was completed satisfactorily.

Although the center link has an apparent symmetrical shape, there is a 0.2175 inch difference in the distances

between the center bearing and each side bearing. Also, the two spherical bearings installed at each end are

not the same bore diameter. The center link can be installed 180 degrees from the correct location (reversed)

and still be attached to the engine with the pawl pins in the correct location. More force can be necessary to

install the pins.

The reversed center link condition changes the structural loading of the aft engine mount interface with the

engine. If not corrected, failure of the aft engine mount can occur. Also, the reversed center link installation

causes a 0.174 inch displacement of the engine turbine rear frame to the right. The thrust reverser cowls are

not easily closed if this condition exist.

Part 2 gives instructions to install the permanent marks on the aft engine mount, which, if installed, releases

operators from the inspection requirements given in Part 1 of this service bulletin. The permanent marks identify

the correct installation position of the hanger fitting assembly and the center link assembly of the aft engine

mount.

Boeing Service Related Problem (SRP) 737-SRP-71-0035 is related to this service bulletin.

ACTION

Part 1, open the engine thrust reversers and get access to the aft engine mount. Do an inspection of the aft

engine mount to make sure that the center link assembly is correctly installed. If the center link assembly is

incorrectly installed, correct the installation and report this to Boeing.

Part 2, get access and remove the aft engine mount. Mark the aft face of the hanger fitting with “L”, “R” and AFT”

to identify the correct position for installation. Mark the aft face of the center link assembly with “L”, “R” and “AFT”

to identify correct position for installation. Install the aft engine mount.

EFFECTIVITY

737-600/700/700C/800/900 airplanes. See Service Bulletin (SB) Paragraph 1.A.1 for effectivity.

COMPLIANCE

Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-03-01, Amendment 39-13025, is related

to this service bulletin.

Part 1, For airplanes that have had an engine change since the new airplane was received from Boeing, in 90

days or less from the initial release of SB 737-71A1462, Boeing recommends that operators do a one-time

inspection of the aft engine mount and make sure of the correct installation of the center link assembly unless

the mount is marked as given in the Part 2 of this service bulletin. If a reversed center link is found, the condition

must be corrected before the next flight. If only one engine on an airplane has been replaced, it is only

necessary to do an inspection of that engine.
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Part 1: For airplanes that have not had an engine change since the new airplane was received from Boeing, in

90 days or less from the Revision 3 release of SB 737-71A1462, Boeing recommends that operators do a

one-time inspection of the aft engine mount to make sure of the correct installation of the center link assembly.

If a reversed center link is found, the incorrect condition must be corrected before the next flight. No more new

inspection is necessary if the aft engine mounts were inspected as shown in the initial, Revision 1 or Revision

2 of this service bulletin.

Part 1: For all subsequent engine changes on all airplanes, Boeing recommends operators do the Part 1

Inspection on each aft engine mount during each subsequent engine change until the marked aft engine mount

is installed.

Part 2: For all airplanes that have had or have not had an engine change, Boeing recommends that operators

do Part 2 part mark procedures if the engine mount is removed by the Part 1 Work Instructions, or during a

subsequent usual engine maintenance task when the engine removal is necessary.

Part 2: Boeing recommends that during the subsequent engine changes done after 90 days from the release of

SB 737-71A1462, Revision 2, install permanently marked aft engine mounts. All engine changes done in 90

days or less from the release of SB 737-71A1462, Revision 2, that do not have permanently marked aft engine

mounts, must have an inspection done as given in the Part 1 Inspection.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection given in this service bulletin for airplanes that have

had an engine change since the new airplane was received from Boeing.

Boeing warranty remedies are available for airplanes in warranty as of October 9, 2003 if the airplanes have not

had an engine change since the new airplane was received from Boeing. Please refer to Paragraph 2.B.,

Industry Support Information.

MANPOWER

Manpower data for each engine position:

MATERIAL INFORMATION

None.

PART 1 Total Task Hours Elapsed Hours

Inspection 3.5 2.0

Removal and Installation 37.0 10.5

Inspection, Removal and

Installation

40.5 12.5

PART 2 Total Task Hours Elapsed Hours

Mark Aft Engine Mount 1.5 1.5
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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

FWD

FOR CORRECT INSTALLATION

INSPECT AFT ENGINE MOUNT

PART 1:

HANGER FITTING

LINK ASSEMBLY AND

MARK THE CENTER

PART 2:

V86787
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ALERT ALERT

Commercial

Airplane

Group 737

ALERT ALERT

Service Bulletin

Number: 737-71A1462

Date: August 29, 2002

Revision 3 May 20, 2004

ATA System: 7121

SUBJECT: POWER PLANT - Engine Mounts - Aft Engine Mount, Link Assembly, Hanger Fitting,

Inspection, Correction and Identification of Parts

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

PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE

BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE

BULLETIN TO THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D6-19567 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

This service bulletin is for the airplanes shown below.

Airplane models:

737-600 737-700 737-700C 737-800

737-900

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

GROUP CONDITION DESCRIPTION

1 - 737-600/-700/-700C/-800/-900 from Line 1 through

1277

1 737-600/-700/-700C/-800/-900 from Line 1 through

1277 airplanes that have had an engine change since

the new airplane was received from Boeing,

2 737-600/-700/-700C/-800/-900 from Line 1 through

1277 airplanes that have had no engine change since

the new airplane was received from Boeing,
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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

AERO CONTRACTORS LTD (YAT)

1 YG042

AIR ALGERIE (ALG)

1 YD101–YD107 YE301–YE305

AIR ASTANA (AKZ)

1 YA356–YA357 YC151

AIR BERLIN (BER)

1 YB201 YB203 YC051–YC070 YD151–YD155

AIR CHINA (BEJ)

1 YC941–YC951

AIR CHINA SOUTHWEST AIRLINES (XIN)

1 YC426–YC428 YE201–YE204

AIR EUROPA (ARE)

1 YC761–YC770 YC907 YD206–YD209

AIR MAURITANIE (MAR)

1 YA302

AIR NATIONAL GUARD (USK)

1 YG044 YG067 YG069

AIR PACIFIC (APC)

1 YA291 YC931–YC932

AIR SAHARA (SAQ)

1 YA253–YA254 YA731 YB204–YB205 YC901–YC902

AIR SENEGAL INTERNATIONAL (SNG)

1 YA683–YA684

AIR SEYCHELLES (ASY)

1 YA351

AIR SHAMROCK (SHI)

1 YG016

ALASKA AIRLINES (ASA)

1 YA841–YA858 YD501–YD507

ALOHA AIRLINES (ALO)

1 YA607–YA608 YA610 YA614–YA615 YA627–YA629

YA732–YA733

AMERICAN AIRLINES (AAL)

1 YC801–YC877
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AMIRI FLIGHT (ABD)

1 YD410 YG023–YG026

ARAMCO ASSOCIATED COMPANY (RAS)

1 YB151–YB153 YG601–YG602

ASTRAEUS, LTD. (AUA)

1 YA671–YA672 YA681–YA682

ATA AIRLINES, INC. (AAT)

1 YD301–YD330

AUSTRALIAN WEDGETAIL PROGRAM (ZVI)

1 YG089 YG201

BANCO SAFRA (BNS)

1 YG040

BB FIVE, INC (YIP)

1 YG066

BBJ ONE (BBI)

1 YG068

BEL AIR LIMITED (ULL)

1 YG022

BELAVIA (ITU)

1 YD408

BNJ SALES COMPANY (BNJ)

1 YG031 YG033 YG035–YG036 YG038

BOEING (TBC)

1 YG085

BOEING CAPITAL CORPORATION (ZMF)

1 YG002

BOEING DEMONSTRATOR JET (BCJ)

1 YG001 YG071

BRAATHENS (BRT)

1 YA311 YA543 YA545 YA547–YA552

BRITANNIA AIRWAYS (BRI)

1 YD001–YD006

BWIA WEST INDIES AIRWAYS (TTA)

1 YC136–YC141 YJ001

CHARTWELL (CHP)

1 YG017
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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

CHINA AIRLINES (CHI)

1 YC571 YC574–YC583 YC589

CHINA EASTERN AIRLINES (CEA)

1 YB206 YB561–YB566

CHINA EASTERN AIRLINES WUHAN (WUH)

1 YD171–YD172

CHINA EASTERN YUNNAN AIRLINES (YUN)

1 YA811–YA814

CHINA SOUTHERN AIRLINES (GUN)

1 YJ671–YJ676

CHINA SOUTHWEST CHONGQING A/L (CHO)

1 YC981–YC983

CHINA XINJIANG AIRLINES (XIJ)

1 YA255–YA256 YA645 YA656

COMMONWEALTH OF AUSTRALIA (GAU)

1 YG072 YG075

CONTINENTAL AIRLINES (CAL)

1 YA501–YA536 YC321–YC380 YD601–YD612 YJ501–YJ517

COPA AIRLINES (COP)

1 YA755–YA756 YA961–YA970

CYPRUS TURKISH AIRLINES (KTHY) (KHT)

1 YC467 YD021–YD022

DALLAH AL BARAKA (KAM)

1 YG063

DELTA AIR LINES (DAL)

1 YC601–YC655 YC681–YC696

DOBRO LIMITED (DOB)

1 YG008

DUBAI AIR WING (DAW)

1 YD402 YG007

EASYJET (EZY)

1 YB101–YB120 YB207

EIE EAGLE (EIE)

1 YD409

EL AL ISRAEL AIRLINES (ELA)

1 YA881–YA882 YC405 YC591–YC593
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EURALAIR HORIZONS (ERL)

1 YC701 YC703–YC704 YC707 YC727

EUROCYPRIA AIRLINES (ECY)

1 YC186

EVA AIR (EVA)

1 YG083

EXCEL AIRWAYS (SBE)

1 YC111–YC113 YC903 YC906

EXCEL AIRWAYS-CYPRUS (XLC)

1 YC436–YC437

EXECUJET SWITZERLAND AG (XJT)

1 YG011

EXECUTIVE JETS LIMITED (EJL)

1 YD407

FORD AIR SERVICES (FMC)

1 YA541–YA542

FUNAIR (FUN)

1 YG027

FUTURA (FUA)

1 YC407 YC451 YC461–YC466

GAMA AVIATION LTD (GAV)

1 YG010

GE CORPORATE AIR TRANSPORT (GEB)

1 YG003 YG012

GERMANIA (GER)

1 YA231 YA233 YA235–YA240 YA571–YA572

GOL AIRLINES (GOT)

1 YA201–YA202 YA232 YA234 YA241–YA242

YA321 YA602 YA605 YA611–YA612

YA646–YA648 YA650 YA657 YB202

YB271 YD256–YD257 YJ471–YJ472

HAINAN AIRLINES (HNA)

1 YA603–YA604 YA606 YC126–YC127 YC401

YC404 YC409 YC452 YC971–YC978

YD042–YD045 YD216

HAPAG-LLOYD FLUG (HAP)

1 YC001–YC030
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HELIOS AIRWAYS (HCY)

1 YC416–YC417

HI. HAMBURG INTERNATIONAL (HAU)

1 YA574–YA578 YB276

INTER AIRLINES (IAW)

1 YJ473 YJ475

JET AIRWAYS (JPL)

1 YA609 YA621–YA622 YA734 YA751–YA754

YB181–YB183 YC402–YC403 YC731–YC741

JET AVIATION (JTA)

1 YD405 YG015 YG021

KENYA AIRWAYS (KEN)

1 YA635–YA636 YA641

KEVINAIR (KVN)

1 YG037

KLM - ROYAL DUTCH AIRLINES (KLM)

1 YC781–YC793 YD531–YD534

KOREAN AIR (KAL)

1 YC441–YC448 YD121–YD126 YD541–YD547

L-3 COMMUNICATIONS (LCS)

1 YG028

LAUDA AIR (LAL)

1 YB171–YB172 YC381–YC383 YE171–YE172

LIMITED BRAND INC. (LII)

1 YG005

LINEAS AEREAS AZTECA (AZX)

1 YA601 YB501–YB502

LOWA CORPORATION (LWA)

1 YD406

MAERSK AIR (MRS)

1 YA203–YA211 YA221

MALEV HUNGARIAN AIRLINES (HGA)

1 YA371

MANDARIN AIRLINES (MDN)

1 YC587–YC588
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MIAMI AIR (MIB)

1 YC146 YC904–YC905

MID EAST JET (SKL)

1 YG013–YG014

MONGOLIAN AIRLINES MIAT (MNG)

1 YJ476

MULTIFLIGHT (MFL)

1 YD404

NATIONAL (NJI)

1 YG032

NATIONAL AIR SERVICES (NAR)

1 YG086–YG087

NEOS (NEO)

1 YJ002 YJ631–YJ632

NEWS AMERICA INCORPORATED (NWS)

1 YG020

NOVAIR (NOO)

1 YC705

OMAN AIR (OMR)

1 YA366–YA367 YB551 YC171

OMNIFLYS (OML)

1 YG077

PEGASUS AIRLINES (PGS)

1 YC391–YC392 YC406 YC410 YC412

YC414–YC415 YC572–YC573 YD025 YD391

PICTON II (UNU)

1 YG006

POLYNESIAN AIRLINES (PLY)

1 YC147

PRIVATAIR (PTS)

1 YG018–YG019 YG064

QANTAS (QAN)

1 YC878–YC892

REPUBLIC OF CHINA AIR FORCE (CAF)

1 YC396
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ROYAL AIR MAROC (RAM)

1 YA831–YA835 YC301–YC304

ROYAL JORDANIAN AIR FORCE (RYJ)

1 YG039

ROYAL MALAYSIA AIR FORCE (MAF)

1 YG061

ROYAL SAUDI AIR FORCE (RSA)

1 YD403 YG080

RYANAIR (RYR)

1 YC471–YC499 YJ801–YJ804

SAMSUNG TECHWIN CO. (SST)

1 YG079

SAS (SAS)

1 YB001–YB006 YD041 YD046–YD055 YD081–YD084

YE001–YE020 YE051 YE101–YE109

SAS INSTITUTE INC. (SJS)

1 YG041

SAUDI OGER (SAO)

1 YD401 YG073

SHANGHAI AIRLINES (SHA)

1 YA272 YA312–YA314 YA891–YA892 YC166–YC169

YJ871

SHARE JET (SJL)

1 YG082

SHENZHEN AIRLINES (SHZ)

1 YA613 YA626 YA686–YA687 YA721–YA722

YA801–YA803 YA809 YC153–YC154 YC411

YC413

SIGAIR (SIG)

1 YG034

SILVER ARROWS (SIQ)

1 YG062

SKY AIRLINES (SYC)

1 YC730

SOUTH AFRICAN AIRFORCE (SFF)

1 YG076
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SOUTH AFRICAN AIRWAYS (SAA)

1 YC708–YC715 YC720–YC725 YD023–YD024 YD481–YD483

SOUTHERN AIRCRAFT SERVICES (HUZ)

1 YG009

SOUTHWEST AIRLINES (SWA)

1 YA001–YA099 YA101–YA128 YA271 YA301

STERLING EUROPEAN AIRLINES (STR)

1 YC101–YC104 YC751–YC752

SUN COUNTRY AIRLINES (SCA)

1 YC121 YC152 YC155–YC156

SUNEXPRESS (SNS)

1 YC453 YC455 YC702 YC706

YJ477–YJ479

SWIFLITE AIRCRAFT CORPORATION (OSF)

1 YG078

TAROM - ROMANIAN AIR TRANSPORT (TRM)

1 YB161–YB162

TBN AVIATION AVV (TBE)

1 YG029

TRACINDA CORP. (TRD)

1 YG004

TRANSAERO AIRLINES (TRX)

1 YA251–YA252

TRANSAVIA AIRLINES (TAV)

1 YB521 YC071–YC082 YC091–YC094

TRAVEL SERVIS (TSF)

1 YC408 YC454 YC459 YD203

YJ474

TUI AIRLINES BELGIUM (TLB)

1 YD217

TUNISAIR (TUN)

1 YE151–YE157 YG030

TURKISH AIRLINES (THY)

1 YC501–YC526

TUTOR-SALIBA CORPORATION (TTS)

1 YG070
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UNITED STATES NAVY (USN)

1 YG501–YG506

US AIR FORCE (USF)

1 YG074 YG081 YG084 YG088

VARIG AIRLINES (VAR)

1 YA322–YA323 YA573 YC728–YC729

VIRGIN BLUE AIRLINES (VOZ)

1 YA336–YA345 YA544 YA546 YA649

YA658–YA659 YA685 YA688–YA691 YC421–YC422

YC921–YC922 YD201–YD202 YD251–YD254

WESTJET (WJI)

1 YB301–YB310 YB601–YB605

XIAMEN AIRLINES (XIA)

1 YA701–YA708

YEMENIA (YEM)

1 YC176–YC178

YONA AVIATION II, LLC (VRH)

1 YG043

IDENTIFICATION BY VARIABLE NUMBER

Variable Group

YA001–YA099 1

YA101–YA128 1

YA201–YA211 1

YA221 1

YA231–YA242 1

YA251–YA256 1

YA271–YA272 1

YA291 1

YA301–YA302 1

YA311–YA314 1

YA321–YA323 1

YA336–YA345 1

YA351 1

YA356–YA357 1

YA366–YA367 1

YA371 1

YA501–YA536 1

YA541–YA552 1
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YA571–YA578 1

YA601–YA615 1

YA621–YA622 1

YA626–YA629 1

YA635–YA636 1

YA641 1

YA645–YA650 1

YA656–YA659 1

YA671–YA672 1

YA681–YA691 1

YA701–YA708 1

YA721–YA722 1

YA731–YA734 1

YA751–YA756 1

YA801–YA803 1

YA809 1

YA811–YA814 1

YA831–YA835 1

YA841–YA858 1

YA881–YA882 1

YA891–YA892 1

YA961–YA970 1

YB001–YB006 1

YB101–YB120 1

YB151–YB153 1

YB161–YB162 1

YB171–YB172 1

YB181–YB183 1

YB201–YB207 1

YB271 1

YB276 1

YB301–YB310 1

YB501–YB502 1

YB521 1

YB551 1

YB561–YB566 1

YB601–YB605 1

YC001–YC030 1

YC051–YC082 1

Variable Group
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YC091–YC094 1

YC101–YC104 1

YC111–YC113 1

YC121 1

YC126–YC127 1

YC136–YC141 1

YC146–YC147 1

YC151–YC156 1

YC166–YC169 1

YC171 1

YC176–YC178 1

YC186 1

YC301–YC304 1

YC321–YC383 1

YC391–YC392 1

YC396 1

YC401–YC417 1

YC421–YC422 1

YC426–YC428 1

YC436–YC437 1

YC441–YC448 1

YC451–YC455 1

YC459 1

YC461–YC467 1

YC471–YC499 1

YC501–YC526 1

YC571–YC583 1

YC587–YC589 1

YC591–YC593 1

YC601–YC655 1

YC681–YC696 1

YC701–YC715 1

YC720–YC725 1

YC727–YC741 1

YC751–YC752 1

YC761–YC770 1

YC781–YC793 1

YC801–YC892 1

YC901–YC907 1

Variable Group
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YC921–YC922 1

YC931–YC932 1

YC941–YC951 1

YC971–YC978 1

YC981–YC983 1

YD001–YD006 1

YD021–YD025 1

YD041–YD055 1

YD081–YD084 1

YD101–YD107 1

YD121–YD126 1

YD151–YD155 1

YD171–YD172 1

YD201–YD203 1

YD206–YD209 1

YD216–YD217 1

YD251–YD254 1

YD256–YD257 1

YD301–YD330 1

YD391 1

YD401–YD410 1

YD481–YD483 1

YD501–YD507 1

YD531–YD534 1

YD541–YD547 1

YD601–YD612 1

YE001–YE020 1

YE051 1

YE101–YE109 1

YE151–YE157 1

YE171–YE172 1

YE201–YE204 1

YE301–YE305 1

YG001–YG044 1

YG061–YG064 1

YG066–YG089 1

YG201 1

YG501–YG506 1

YG601–YG602 1

Variable Group
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ALERT ALERT

2. Spares Affected

Add marks on the aft surface of the hanger fitting and the center link assembly with “L”, “R” and

“AFT” to identify the correct position for installation. Change the part numbers on the hanger

fitting and the center link assembly. Refer to paragraph 3.B., Work Instructions, Part 2.

YJ001–YJ002 1

YJ471–YJ479 1

YJ501–YJ517 1

YJ631–YJ632 1

YJ671–YJ676 1

YJ801–YJ804 1

YJ871 1

Variable Group
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B. Concurrent Requirements

None.

C. Reason

Part 1 of this service bulletin was initially prepared to give instructions for operators to do a one-time

inspection of all airplanes that have had an engine change since the airplane was delivered. It is

necessary to do the inspection on all subsequent engine changes unless Part 2 marked engine

mounts are installed.

In September 2003, an operator told Boeing that an airplane was found with a center link installed

incorrectly on an aft engine mount. The operator also told Boeing that the airplane had not had an

engine change since the new airplane was received from Boeing. As a result, it is necessary for

airplanes that have not had an engine changed since the new airplane was received from Boeing to

do the Part 1 inspection on each of the aft engine mounts.

In October 2001, one operator told Boeing it was necessary to get clarification of manuals related to

engine mount assembly and installation. After the initial help from Boeing, the operator reported that

the aft engine mount center link assembly, P/N 310A2034-3, could have been reversed during

overhaul assembly and subsequently installed on airplanes. The operator inspected all airplanes that

had engine installations since the airplanes were delivered. Six reversed center links were found,

which were immediately corrected. No damage was reported after visual inspection of the aft mount

and local engine attachment was completed.

The operator found that no anomalies were reported during the aft engine mount installations or during

the engine installations. It was found that some increase in force was necessary to install the pawl pins

that attach the aft engine mount to the engine.

In December 2001, a second operator told Boeing about problems they had when they tried to close

the thrust reversers after engine replacement. Visual inspection showed gap differences between the

thrust reverser aft cowl and the primary exhaust sleeve on the two sides of the engine. The engine

was lowered and the subsequent inspection found a reversed center link assembly, part number

310A2034-7. After the center link was removed and installed correctly, the engine installation was

completed satisfactorily.

Although the center link has an apparent symmetrical shape, there is a 0.2175 inch difference in the

distances between the center bearing and each side bearing. Also, the two spherical bearings

installed at each end are not the same bore diameter. The center link can be installed 180 degrees

from the correct location (reversed) and still be attached to the engine with the pawl pins in the correct

location. More force can be necessary to install the pins.

The reversed center link condition changes the structural loading of the aft engine mount interface with

the engine. If not corrected, failure of the aft engine mount can occur. Also, the reversed center link

installation causes a 0.174 inch displacement of the engine turbine rear frame to the right. The thrust

reverser cowls are not easily closed if this condition exist.

Part 2 gives instructions to install the permanent marks on the aft engine mount, which, if installed,

releases operators from the inspection requirements given in Part 1 of this service bulletin. The

permanent marks identify the correct installation position of the hanger fitting assembly and the center

link assembly of the aft engine mount.

Boeing Service Related Problem (SRP) 737-SRP-71-0035 is related to this service bulletin.
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Revision 1: This revision was sent to inform operators of the changes shown below:

The information given in the ACTION section in the Service Bulletin Summary has changed.

The information given in Paragraph 1.D., Description section of the Service Bulletin has changed.

Information has been added and the compliance time has changed in the Service Bulletin Summary

and in Paragraph 2.E. of the Service bulletin.

Paragraph 3.B.2., Work Instructions, a NOTE has been added to inform operators that the best view

of center link can be found from the left side of the engine.

More information has been added to the Steps in Figure 2.

More information has been added to the Steps in Figure 4, a new STEP 3 has been added and the

initial STEP 7 has been deleted. The initial Steps 3 through 6 have been re-numbered.

Revision 2: This revision was sent to add airplanes to the effectivity and to change the inspection given

in the initial release and in Revision 1 of this service bulletin. The inspection, identified as Part 1, is

revised from a one-time inspection to an inspection of all subsequent engine installations. Part 2 is

added to give instructions to install permanent marks on the hanger fitting and the center link. The

permanent marks identify the correct position for installation of the hanger fitting and the center link of

the aft mount of the two engines. It is not necessary to do the Part 1 inspection after marked engine

mounts are installed.

The Spares Affected information given in Paragraph 1.A.2., is changed.

Figures 5, 6 and 7 are added to give the instructions to add the marks and change the part numbers

on the hanger fitting and the center link.

FAA Airworthiness Directive (AD) information has also been added.

Revision 3: This revision is sent to tell operators that for the airplanes that have not had an engine

change since the new airplane was received from Boeing, it is possible that some center links were

incorrectly installed in an aft engine mount before the airplane was delivered. Before this revision,

inspection of the aft engine mounts was necessary only for the airplanes that had an engine change

after the new airplane was received from Boeing. With the release of Revision 3 of this service

bulletin, the Part 1 Inspection is applicable to all airplanes given in the effectivity of this service bulletin.

1. On Summary section, Background, paragraph 1.C., Reason and paragraph 1.D., Description,

more information has been added to include the airplanes that have not had an engine change

since the new airplane was received from Boeing.

2. On Summary section, Background, paragraph 1.C., Reason and paragraph 1.J., References, a

new paragraph has been added to show the Boeing Service Related Problem information that is

related to this service bulletin.

3. On Summary section and paragraph 1.E., Compliance information, the paragraphs about Part 1

have been changed to include airplanes that have not had an engine change since the new

airplane was received from Boeing. The paragraphs about Part 2 have been changed to give

more information. All engine installed after 90 days has been changed to during all subsequent

engine changes done after 90 days.
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4. On paragraph 1.A., Planning Information, Effectivity, a group condition table has been added.

5. On paragraph 2.B., Industry Support Information, a warranty statement has been added for

airplanes that have not had an engine change since the new airplane was received from Boeing.

6. On paragraph 2.C.3., Parts Modified and Reidentified table and Figure 5 work instruction table,

Step 2, the part numbers for the hanger fitting 310A2031-23 and the hanger fitting assembly

310A2031-24 have been added.

7. On paragraph 3.B.,Part 1,2., the work instruction step has been changed to delete information

about airplanes that have had an engine change after the airplane was delivered and during

subsequent engine installations. The changed Step 2 make the step applicable to all airplanes

and the same compliance information is already shown in the Compliance paragraphs.

8. On paragraph 3.B.,Part 1,3.e. and Part 2,1., the work instruction steps have been added for

airplanes if do or not do the Part 1 and Part 2 Work Instructions at the same time.

9. On paragraph 3.B.,Part 1,4., the work instruction step has been added for airplanes that have

found the aft engine mounts correctly installed.

10. On paragraph 3.B.,Part 2,4., the work instruction step has been added to close access. The note

on the left, right and aft markings has been changed to a Caution note.

11. Figures 1 and 3 have been changed to show the left side view to agree with the note that said

the best view is from the left side. The view was shown from the right side of the aft engine

mount.

12. Figures 2 and 4 have been changed to delete the assembly and installation steps Steps 9 through

12. The same assembly and installation steps have been moved to the new Figures 8 and 9 for

airplanes that possibly do Part 1 Correction and Part 2 part mark work instructions at the same

time.
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D. Description

Part 1, open the engine thrust reversers and get access to the aft engine mount. Do an inspection of

the aft engine mount to make sure that the center link assembly is correctly installed. If the center link

assembly is incorrectly installed, correct the installation and report this to Boeing. It is necessary to do

the inspection on all subsequent engine changes unless the mount that is installed is marked as given

in Part 2 of this service bulletin.

Revision 1: No more work is necessary on airplanes examined as given in the initial release of this

service bulletin.

Revision 2: More work is necessary on airplanes that had inspections done as specified in Revision 1

of this service bulletin. It is necessary to do the Part 1 inspection unless the center link and hanger

fitting were marked as specified in the Part 2 part mark procedure. Part 2, get access and remove the

aft engine mount. Mark the aft surface of the hanger fitting with “L”, “R”, and “AFT” to identify the

correct location for installation. Mark the aft surface of the center link with “L”, “R” and “AFT” to identify

the correct location for installation. Install the aft engine mount.

Revision 3: More work is necessary for airplanes that have not had an engine change since the new

airplane was received from Boeing, do the Part 1 Inspection procedures unless the Part 1 Inspection

or the Part 2 Part Mark procedures have been done.

No more work is necessary on airplanes that have had an engine change since the new airplane was

received from Boeing, have done the Part 1 Inspection and Part 2 Part Marks procedures.

No airplanes have been added by Revision 3 of this service bulletin. The Revision 2 of this service

bulletin included the airplanes effectivity that could be affected by this service bulletin.

E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-03-01, Amendment

39-13025, is related to this service bulletin.

Part 1, For airplanes that have had an engine change since the new airplane was received from

Boeing, in 90 days or less from the initial release of SB 737-71A1462, Boeing recommends that

operators do a one-time inspection of the aft engine mount and make sure of the correct installation

of the center link assembly unless the mount is marked as given in the Part 2 of this service bulletin.

If a reversed center link is found, the condition must be corrected before the next flight. If only one

engine on an airplane has been replaced, it is only necessary to do an inspection of that engine.

Part 1: For airplanes that have not had an engine change since the new airplane was received from

Boeing, in 90 days or less from the Revision 3 release of SB 737-71A1462, Boeing recommends that

operators do a one-time inspection of the aft engine mount to make sure of the correct installation of

the center link assembly. If a reversed center link is found, the incorrect condition must be corrected

before the next flight. No more new inspection is necessary if the aft engine mounts were inspected

as shown in the initial, Revision 1 or Revision 2 of this service bulletin.

Part 1: For all subsequent engine changes on all airplanes, Boeing recommends operators do the Part

1 Inspection on each aft engine mount during each subsequent engine change until the marked aft

engine mount is installed.
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Part 2: For all airplanes that have had or have not had an engine change, Boeing recommends that

operators do Part 2 part mark procedures if the engine mount is removed by the Part 1 Work

Instructions, or during a subsequent usual engine maintenance task when the engine removal is

necessary.

Part 2: Boeing recommends that during the subsequent engine changes done after 90 days from the

release of SB 737-71A1462, Revision 2, install permanently marked aft engine mounts. All engine

changes done in 90 days or less from the release of SB 737-71A1462, Revision 2, that do not have

permanently marked aft engine mounts, must have an inspection done as given in the Part 1

Inspection.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes

specified in this service bulletin comply with the applicable Federal Aviation Regulations (14 CFR Part

25) and Joint Aviation Requirements (JAR-25) and are FAA/JAA approved. This service bulletin and

FAA/JAA approval were based on the airplane in it's original Boeing delivery configuration or as

modified by other FAA/JAA 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.

Note: Joint Airworthiness Requirements (JAR) compliance status may be found in the Service Bulletin

Index, Part 1.

This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle

Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service

bulletin as an alternative method of compliance to the requirements of paragraphs (b) and (c) of

AD 2003-03-01. All provisions of AD 2003-03-01 that are not specifically referenced in the above

remain fully applicable and must be complied with.

The FAA has examined the marking, part marking and reinstallation specified in Part 2 of the work

Instructions of this service bulletin 737-71A1462. The FAA has approved the marking, partmarking

and reinstallation as an alternative method of compliance to the inspections required by

AD 2003-03-01 paragraph (f) provided future engine installations maintain all of the part marking

requirements required by Part 2 of the Work Instructions of this service bulletin.
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G. Manpower

PART 1: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY INSTALLATION INITIAL

INSPECTION

Task

Number of

Persons Task-Hours Elapsed Hours

Open Thrust Reversers 2 1.5 0.75

Inspect Center Link Assembly 1 0.50 0.50

Close Thrust Reversers 2 1.5 0.75

TOTAL FOR INITIAL INSPECTION ON EACH ENGINE 3.5 2.0

PART 1: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY INSTALLATION CORRECTION

Task

Number of

Persons Task-Hours Elapsed Hours

Remove Engine Cowl Panels 2 1.5 0.75

Change Aft Engine Mount:

— Remove Engine

— Remove and Inspect Aft Engine

Mount, Center and Right Link

Assemblies

— Install Aft Engine Mount, Center

and Right Link Assemblies

— Install Engine

4 31.0 7.5

Install Engine Cowl Panels 2 3.0 1.5

Do Thrust Reversers and Engine

Test

2 3.0 1.5

TOTAL FOR INSTALLATION CORRECTION ON EACH

ENGINE

37.0 10.5

TOTAL FOR CONCURRENT INITIAL INSPECTION AND

INSTALLATION CORRECTION ON EACH ENGINE

40.5 12.5

PART 2 : AFT ENGINE MOUNT, HANGER FITTING AND CENTER LINK ASSEMBLY, APPLY

IDENTIFICATION MARKS

Task

Number of

Persons Task-Hours Elapsed Hours

Mark Center Link Assembly and

Hangar Fitting

1 1.5 1.5

TOTAL FOR EACH ENGINE (a) 1.5 1.5

(a) Does not include engine mount removal and installation times. See Part 1 for the engine,

engine mount removal and installation times.
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ALERT ALERT

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not applicable.

J. References

1. Existing Data:

a. 737 Maintenance Manual (AMM) Subject 71-00-02, 71-11-02, 71-21-03, 78-31-00

b. 737 Structural Repair Manual (SRM) Subject 51-40-04

c. Component Maintenance Manual (CMM) 71-21-37

d. Boeing Document D6-19567, Service Bulletin Index

e. FAA Airworthiness Directive AD 2003-03-01, Amendment 39-13025

f. Boeing Service Related Problem (SRP) 737-SRP-71-0035

2. Data supplied with this Service Bulletin:

None.

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

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.

4. Process Data:

Boeing Process specifications referred to on the drawings are not given in this service bulletin

since these procedures are frequently used as standard shop practices.

Drawing Number Title

310A2030 AFT ENGINE MOUNT INSTL, CFM56-7

310A2031 HANGER ASSY - AFT ENGINE MOUNT, CFM56-7

310A2034 LINK ASSY - CENTER, AFT ENGINE MOUNT, CFM56-7
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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

K. Publications Affected

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermix ability of parts.

Publication Chapter-Section

737 Maintenance Manual 71-21

737 Power Plant Build-Up Manual 71-00

737 Illustrated Parts Catalog 71-21

Component Maintenance Manual 71-21
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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

For operators of airplanes that have not had an engine change since the new airplane was received

from Boeing:

Boeing warranty remedies are available for 737 airplanes in warranty as of October 9, 2003. For

inspection man-hour reimbursement for airplanes in warranty as of that date, send a warranty claim

to Boeing Commercial Airplanes Group - Warranties. If the condition described in this service bulletin

is found during the inspection for airplanes in warranty as of that date and additional man-hours are

required, send a warranty claim to Boeing Commercial Airplanes Group - Warranties.

For operators of airplanes that have had an engine change since the new airplane was received from

Boeing:

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

C. Parts Necessary For Each Airplane

1. Kits/Parts:

None.

2. Parts and Materials Supplied by the Operator:

None.

3. Parts Modified and Reidentified:

The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the

number of parts changed on each airplane. Components or subassembly parts are indented. The

quantity of the indented part is the number of parts used on the next higher assembly.

Existing Part

Number QTY Name New Part Number Notes

310A2031-22 1 Hanger Fitting Assembly 310A2031-24 (a) (b) (c)

310A2031-23 1 Hanger Fitting 310A2031-25 (a) (b) (c)

310A2034-3 1 Center Link Assembly 310A2034-14 (a) (b) (c)

310A2034-7 1 Center Link Assembly 310A2034-13 (a) (b) (c)

310A2034-8 1 Center Link Assembly 310A2034-14 (a) (b) (c)

(a) Make the change given in this service bulletin.

(b) This is the part number after the change given in this service bulletin.

(c) This part is used in production.
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ALERT ALERT

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 737-71A1462

ALERT ALERT

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED

MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES

CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE

SPARKS OR OTHER ELECTRICAL DAMAGE.

Note:

1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. The work instructions are divided into two parts. Part 1 gives instructions to do an

inspection and if necessary, correct the installation of the aft engine mounts. Part 2 gives

instructions to mark the hanger fitting and the center link assembly of the aft mounts of the

two engines.

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.

— Angular tolerance is plus or minus 2 degrees

— Torque limits to tighten nuts and bolts are given in 737 Structural Repair Manual

(SRM) 51-40-04.
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ALERT ALERT

B. WORK INSTRUCTIONS

PART 1: Inspection and correction of aft engine mounts

1. Open the thrust reversers. Refer to 737 AMM 78-31-00/201.

2. Do a detailed inspection of the aft engine mount on each engine position. Make sure that the

center link assembly is correctly installed. See Figure 1 for Center Link Assembly, part number

310A2034-3 (without pockets) and Figure 3 for Center Link Assembly, part numbers

310A2034-7 or -8 (with pockets).

Note:

1. Airplanes can have two different types of center links installed. Refer to Figure 1 or

Figure 3.

2. The best view of the center link assembly is from left side of the engine.

3. If an incorrectly installed center link assembly is found, remove and install it correctly and do the

items below before the next flight. See Figure 2 for Center Link Assembly, part number

310A2034-3 (without pockets) or Figure 4 for Center Link Assembly, part numbers 310A2034-7

or -8 (with pockets).

a. Do a detailed inspection on the mount lugs of the engine turbine rear frame.

Do an inspection of the engine mounting lugs and the adjacent engine turbine rear frame

area for cracks, yielding, buckling, and wear damage. Contact CFMI for more instructions

if damaged hardware is found.

b. Do a detailed inspection of the aft engine mount hardware.

(1) Do an inspection of the parts specified below for cracks, yielding, buckling and wear

damage. See Figure 2 or Figure 4.

(a) Center link Assembly 310A2034-( ).

(b) Right link Assembly 310A2035-( ).

(c) Aft mount hanger assembly 310A2031-( ), at the interfaces with the center link and

right link.

(d) 310A2037-( ) link pins that are removed during disassembly.

(2) If any damage is found, contact the Boeing Field Service Representative for more

instructions.

c. Record the installed engine information on the form that is supplied in Appendix A of this

service bulletin. See Appendix A.

d. Give the completed Appendix A form to your Boeing Field Service Representative and your

CFMI Representative.
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ALERT ALERT

e. Do steps (1) or (2) shown below.

(1) Do the Part 2 work instructions to add the permanent part marks on the center link

assembly and the hanger fitting before the engine installation. See the Part 2 Work

Instructions.

(2) If the Part 2 Work Instructions is not done, do these steps shown below.

Note: The Part 2 part mark procedures can be done at the same time during a

subsequent usual engine maintenance task that makes the engine removal

necessary.

(a) Assemble and install the aft engine mounts and install the engines. Refer to

Figure 8 for Center Link Assembly, part number 310A2034-3 (without pockets) or

Figure 9 for Center Link Assembly, part numbers 310A2034-7 or -8 (with pockets).

(b) Close the thrust reversers. Refer to 737 AMM 78-31-00/201.

(c) Install the fan cowl panels. Refer to 737 AMM 71-11-02/401.

(d) Do the operational test of the thrust reversers. Refer to 737 AMM 78-31-00/501.

(e) Do the tests of the installed engine. Refer to 737 AMM 71-00-02/401.

(f) Put the airplane back to a serviceable condition.

4. If a correctly installed center link assembly is found, do these steps shown below.

a. Close the thrust reversers. Refer to 737 AMM 78-31-00/201.

b. Do the operational test of the thrust reversers. Refer to 737 AMM 78-31-00/501.

c. Put the airplane back to a serviceable condition.
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ALERT ALERT

PART 2: Mark the hanger fitting and center link

1. If the Part 2 is not done at the same time with Part 1 or with other usual engine maintenance tasks

that make the engine removal necessary, do these steps below at each engine position.

a. Open the thrust reversers. Refer to 737 AMM 78-31-00/201.

b. Remove and keep the fan cowl panels. Refer to 737 AMM 71-11-02/401.

c. Remove and keep the engine. Refer to 737 AMM 71-00-02/401.

d. Remove and disassemble the aft engine mount. Refer to 737 AMM 71-00-02/401,

737 AMM 71-21-03 and 737 CMM 71-21-37.

2. Add marks on the aft face of the hanger fitting and change the part number. See Figure 5.

3. Add marks on the aft face of the center link assembly and change the part number. See Figure

6 or Figure 7.

Note: Airplanes can have two different types of center links installed.

4. Do these steps below to install the aft engine mounts, engines and close access.

CAUTION: MAKE SURE THAT THE “L”, “R”, AND “AFT” MARKINGS ARE ON THE NEAR

SIDE WHEN SEE FROM THE AFT SIDE OF THE ENGINE MOUNT. MAKE SURE

THAT THE MARKINGS ON THE CENTER LINK ASSEMBLY AGREE WITH THE

“L”, “R”, AND “AFT” MARKINGS THAT ARE ON THE HANGER FITTING WHEN

THE CENTER LINK ASSEMBLY IS INSTALLED ON THE HANGER FITTING.

a. Assemble and install the aft engine mounts and install the engines. Refer to Figure 8 for

Center Link Assembly, part number 310A2034-3 (without pockets) or Figure 9 for Center

Link Assembly, part numbers 310A2034-7 or -8 (with pockets).

b. Close the thrust reversers. Refer to 737 AMM 78-31-00/201.

c. Install the kept fan cowl panels. Refer to 737 AMM 71-11-02/401.

d. Do the tests of the installed engine. Refer to 737 AMM 71-00-02/401.

e. Do the operational test of the thrust reversers. Refer to 737 AMM 78-31-00/501.

5. Put the airplane back to a serviceable condition.
FIGURE 1: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) INSTALLATION

INSPECTION

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

FIGURE 1: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) INSTALLATION

INSPECTION

ASSEMBLY

CENTER LINK

AFT ENGINE MOUNT

LEFT THRUST

LINK

FWD

SEE B

A

SEE A

V88902

(SHEET 1 OF 2)
FIGURE 1: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) INSTALLATION

INSPECTION

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below is for each engine.

STEP TASK NAME PART NUMBER QTY NOTE

1 Inspect Center Link

Assembly

310A2034-3 1 Make sure that the loader

relief slots are seen on the

aft face of link. Center Bearing S302T001-822 1

Note:

1. The best view of the center link assembly is from the left side of the engine.

2. The loader relief slots are located 180 degrees apart and are used to install the

spherical bearing in the bearing race.

RELIEF SLOTS

LOADER

A-A

FWD

1

B

V88891

(SHEET 2 OF 2)
FIGURE 2: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) REMOVAL AND

INSPECTION

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ALERT ALERT

FIGURE 2: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) REMOVAL AND

INSPECTION

CENTER LINK

ASSEMBLY

AFT ENGINE MOUNT

FRAME LUGS

TURBINE REAR

LEFT THRUST LINK

FWD

SEE A

A

1

SEE B

V88901

(SHEET 1 OF 4)
FIGURE 2: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) REMOVAL AND

INSPECTION

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ALERT ALERT

LINK PINS

TURBINE

REAR FRAME

FWD

B

3

8

2 SEE C

2

V88889

(SHEET 2 OF 4)
FIGURE 2: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) REMOVAL AND

INSPECTION

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

LINK PIN

LINK PIN

ASSEMBLY

CENTER LINK

ASSEMBLY

RIGHT LINK

FWD

6 7

6 7

4 5

C

4 5

8

N45757

(SHEET 3 OF 4)
FIGURE 2: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) REMOVAL AND

INSPECTION

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below is for each engine.

STEP TASK NAME PART NUMBER QTY NOTE

1 Remove/

Lower

Engine - 1 Refer to 737 AMM

71-00-02/401.

2 Remove/

Keep

Aft Engine mount 310A2030-6 or -11 1 Refer to 737 AMM

71-21-03/401.

Link Pins 310A2037-( ) 4

3 Inspect Link Pins 310A2037-( ) 4 Check for cracks, yielding,

buckling and wear damage.

4 Remove/

Keep

Center Link

Assembly

310A2034-3 1 Refer to 737 CMM

71-21-37/301.

Link Pin 310A2037-( ) 1

5 Inspect Center Link

Assembly

310A2034-3 1 Check for cracks, yielding,

buckling and wear damage.

Link Pin 310A2037-( ) 1

6 Remove/

Keep

Right Link

Assembly

310A2035-5, -7 or -8 1 Refer to 737 CMM

71-21-37/301.

Link Pin 310A2037-( ) 1

7 Inspect Right Link

Assembly

310A2035-5, -7 or -8 1 Check for cracks, yielding,

buckling and wear damage.

Link Pin 310A2037-( ) 1

8 Inspect Aft Engine Mount 310A2030-6 or -11 1 Check for cracks, yielding,

buckling and wear damage.

Engine Rear

Frame

- -

Note: Do a detailed inspection of the aft engine mount and engine turbine rear frame

interface for damage before the center link and right link assemblies are installed.

(SHEET 4 OF 4)
FIGURE 3: AFT ENGINE MOUNT, CENTER LINK (WITH POCKETS) INSTALLATION INSPECTION

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ALERT ALERT

FIGURE 3: AFT ENGINE MOUNT, CENTER LINK (WITH POCKETS) INSTALLATION INSPECTION

ASSEMBLY

CENTER LINK

AFT ENGINE MOUNT

LEFT THRUST

LINK

FWD

SEE B

A

SEE A

V88902

(SHEET 1 OF 2)
FIGURE 3: AFT ENGINE MOUNT, CENTER LINK (WITH POCKETS) INSTALLATION INSPECTION

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below is for each engine.

STEP TASK NAME PART NUMBER QTY NOTE

1 Inspect Center Link

Assembly

310A2034-7 or -8 1 Make sure that the loader

relief slots are at the aft

face of the center link

assembly. Center Bearing S302T001-702 or -822 1

Note:

1. The best view of the center link is from the left side of the engine.

2. The center link assembly 310A2034-7 has the center bearing part numbers

S302T001-702 or S302T001-822 installed.

3. The center link assembly 310A2034-8 has the center bearing part number

S302T001-822 installed.

2 Inspect Center Link

Assembly

310A2034-7 or -8 1 Make sure that the larger

of the two pockets is on

the left side.

A-A

FWD

POCKET

SMALL

RELIEF SLOTS

LOADER

LARGE

POCKET

1

2

B

V86799

(SHEET 2 OF 2)
FIGURE 4: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) REMOVAL AND

INSPECTION

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

FIGURE 4: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) REMOVAL AND

INSPECTION

LEFT THRUST LINK

TURBINE REAR

FRAME LUGS

AFT ENGINE MOUNT

ASSEMBLY

CENTER LINK

FWD

SEE B

1

A

SEE A

V86781

(SHEET 1 OF 4)
FIGURE 4: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) REMOVAL AND

INSPECTION

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ALERT ALERT

REAR FRAME

TURBINE

LINK PINS

FWD

2 3

2 SEE C

8

B

V86800

(SHEET 2 OF 4)
FIGURE 4: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) REMOVAL AND

INSPECTION

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ALERT ALERT

LINK PIN

LINK PIN

ASSEMBLY

CENTER LINK

ASSEMBLY

RIGHT LINK

FWD

6 7

6 7

4 5

4 5

C

8

N45582

(SHEET 3 OF 4)
FIGURE 4: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) REMOVAL AND

INSPECTION

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ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below is for each engine.

STEP TASK NAME PART NUMBER QTY NOTE

1 Remove/

Lower

Engine - 1 Refer to 737 AMM

71-00-02/401.

2 Remove/

Keep

Aft Engine mount 310A2030-11 or -12 1 Refer to 737 AMM

71-21-03/401.

Link Pins 310A2037-( ) 4

3 Inspect Link Pins 310A2037-( ) 4 Check for cracks, yielding,

buckling and wear damage.

4 Remove/

Keep

Center Link

Assembly

310A2034-7 or -8 1 Refer to 737 CMM

71-21-37/301.

Link Pin 310A2037-( ) 1

5 Inspect Center Link

Assembly

310A2034-7 or -8 1 Check for cracks, yielding,

buckling and wear damage.

Link Pin 310A2037-( ) 1

6 Remove/

Keep

Right Link

Assembly

310A2035-5, -7 or -8 1 Refer to 737 CMM

71-21-37/301.

Link Pin 310A2037-( ) 1

7 Inspect Right Link

Assembly

310A2035-5, -7 or -8 1 Check for cracks, yielding,

buckling and wear damage.

Link Pin 310A2037-( ) 1

8 Inspect Aft Engine Mount 310A2030-11 or -12 1 Check for cracks, yielding,

buckling and wear damage.

Engine Turbine

Rear Frame

- -

Note: Do a detailed inspection of the aft engine mount and engine turbine rear frame

interface for damage before the center link and right link assemblies are installed.

(SHEET 4 OF 4)
FIGURE 5: HANGER FITTING, ADD IDENTIFICATION MARKS

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ALERT ALERT

FIGURE 5: HANGER FITTING, ADD IDENTIFICATION MARKS

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below is for each engine mount.

STEP TASK NAME PART NUMBER QTY NOTE

1 Mark Hanger

Fitting

310A2031-23 1 Mark aft face with “L”, “R” and “AFT”.

Use the vibro-engraving method.

Refer to BSOPM 20-50-10

Note:

1. The left “L” and right “R” letters height are 0.375 inch high.

2. The “AFT” letters height: are 1.0 inch high.

2 Identify Hanger

Fitting

Assembly

310A2031-24 1 Change the part number from the

310A2031-22 to 310A2031-24.

Recommend to use a rubber stamp

method and the part number location is

optional. Refer to BSOPM 20-50-10.

Hanger

Fitting

310A2031-25 1 Change the part number from the

310A2031-23 to 310A2031-25. Use

the vibro-engraving method. Refer to

BSOPM 20-50-10.

0.85

1.35 (2 PLACES)

1.95

2.45

(2 PLACES)

0.25

0.55

0.85

1.35

HANGER FITTING

2

1

(SHEET 1 OF 1)
FIGURE 6: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS), ADD IDENTIFICATION MARKS

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

FIGURE 6: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS), ADD

IDENTIFICATION MARKS

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below is for each engine.

STEP TASK NAME PART NUMBER QTY NOTE

1 Mark Center Link

Assembly

310A2034-3 1 Mark aft face with “L”, “R” and “AFT”.

Use the vibro-engraving method.

Refer to BSOPM 20-50-10

Note: Make the left “L”, right ”R” and “AFT” letters 0.375 inch high.

2 Identify Center Link

Assembly

310A2034-14 1 Change the part number from

310A2034-3 to 310A2034-14.

Use the vibro-engraving method or

electrochemical etching method.

Refer to BSOPM 20-50-10.

BEARING

DIAMETER

1.00

0.39

0.69

0.05

0.25

0.05

0.25

0.56

0.86

1

WITHOUT POCKETS

CENTER LINK ASSEMBLY

2

0.10 MINIMUM

BEARING

DIAMETER

1.18

0.10 MINIMUM

MINIMUM

0.10

1

W21580

(SHEET 1 OF 1)
FIGURE 7: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS), ADD IDENTIFICATION

MARKS

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ALERT ALERT

FIGURE 7: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS), ADD IDENTIFICATION

MARKS

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below is for each engine.

STEP TASK NAME PART NUMBER QTY NOTE

1 Mark Center Link

Assembly

310A2034-7 or -8 1 Mark aft face with “L”, “R” and “AFT”. Use

the vibro-engraving method. Refer to

BSOPM 20-50-10

Note: 1. Make sure that the 1.00 inch inside diameter bearing and the larger of the two pockets

located on the left side.

2. Make the right ”R” and “AFT” letters 0.375 inch high.

3. Make the left “L” letter 0.20 inch high.

2 Change Center Link

Assembly

310A2034-13 or -14 1 Change the part number by a vibroengraving method or electrochemical

etching method. Refer to BSOPM 20-50-10

Note: 1. Change the part number on either location.

2. Change the part number from 310A2034-7 to 310A2034-13. Change the part

number from 310A2034-8 to 310A2034-14.

BEARING

1.00 DIAMETER

1

WITH POCKETS

CENTER LINK ASSEMBLY

2 0.10 MINIMUM

BEARING

DIAMETER

1.18

0.10 MINIMUM

MINIMUM

0.10

1

SMALL POCKET

LARGE POCKET

0.03 MINIMUM

0.03 MINIMUM

0.03 MINIMUM POCKET RADIUS

MINIMUM FROM

LOCATE 0.05

(SHEET 1 OF 1)
FIGURE 8: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) AND ENGINE

INSTALLATION

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

FIGURE 8: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) AND ENGINE

INSTALLATION

LINK PIN

LINK PIN

ASSEMBLY

CENTER LINK

RELIEF SLOTS

LOADER

ASSEMBLY

RIGHT LINK

1.00 BEARING

A-A

A

A

FWD

2

2

1

1

SEE A

385917

AFT ENGINE MOUNT

(SHEET 1 OF 4)
FIGURE 8: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) AND ENGINE

INSTALLATION

August 29, 2002

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

LINK PINS

FWD

A

3

3 SEE B

AFT ENGINE MOUNT

385918

(SHEET 2 OF 4)
FIGURE 8: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) AND ENGINE

INSTALLATION

August 29, 2002

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

CENTER LINK

ASSEMBLY

AFT ENGINE MOUNT

FRAME LUGS

TURBINE REAR

LEFT THRUST LINK

FWD

B

4

SEE C

C

385869

(SHEET 3 OF 4)
FIGURE 8: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) AND ENGINE

INSTALLATION

August 29, 2002

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below is for each engine.

STEP TASK NAME PART NUMBER QTY NOTE

CAUTION: MAKE SURE THAT THE 1.00 INCH INSIDE DIAMETER BEARING IS LOCATED ON THE

LEFT SIDE AND THE LOADER RELIEF SLOTS ARE LOCATED ON THE AFT FACE OF

THE CENTER LINK WHEN SEE FROM THE AFT SIDE OF THE CENTER LINK

DURING INSTALLATION.

CAUTION: IF THE PARTS ARE MARKED, MAKE SURE THAT THE “L”, “R”, AND “AFT” MARKINGS

ARE ON THE NEAR SIDE WHEN SEE FROM THE AFT SIDE OF THE ENGINE MOUNT.

MAKE SURE THAT THE MARKINGS ON THE CENTER LINK ASSEMBLY AGREE WITH

THE “L”, “R”, AND “AFT” MARKINGS THAT ARE ON THE HANGER FITTING WHEN THE

CENTER LINK ASSEMBLY IS INSTALLED ON THE HANGER FITTING.

1 Install

(Kept)

Center Link

Assembly

310A2034-3 1 Refer to 737 CMM

71-21-37/701.

Link Pin 310A2037-( ) 1

2 Install

(Kept)

Right Link

Assembly

310A2035-5, -7 or -8 1 Refer to 737 CMM

71-21-37/701.

Link Pin 310A2037-( ) 1

3 Install

(Kept)

Aft Engine Mount 310A2030-6 or -11 1 Refer to 737 AMM

71-21-03/401.

Link Pins 310A2037-( ) 4

4 Install

(Kept)

Engine - 1 Refer to 737 AMM

71-00-02/401.

(SHEET 4 OF 4)
FIGURE 9: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) AND ENGINE INSTALLATION

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

FIGURE 9: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) AND ENGINE

INSTALLATION

SMALL POCKET

LINK PIN

LINK PIN

ASSEMBLY

CENTER LINK

RELIEF SLOTS

LOADER

ASSEMBLY

RIGHT LINK

LARGE POCKET

1.00 BEARING

A-A

AFT ENGINE MOUNT

A

A

FWD

2

2

1

1

SEE A

385931

(SHEET 1 OF 4)
FIGURE 9: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) AND ENGINE INSTALLATION

August 29, 2002

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

LINK PINS

AFT ENGINE MOUNT

FWD

3

3

A

SEE B

385934

(SHEET 2 OF 4)
FIGURE 9: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) AND ENGINE INSTALLATION

August 29, 2002

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

CENTER LINK

ASSEMBLY

AFT ENGINE MOUNT

FRAME LUGS

TURBINE REAR

LEFT THRUST LINK

FWD

B

4

SEE C

C

385936

(SHEET 3 OF 4)
FIGURE 9: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) AND ENGINE INSTALLATION

August 29, 2002

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BOEING SERVICE BULLETIN 737-71A1462

ALERT ALERT

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below is for each engine.

STEP TASK NAME PART NUMBER QTY NOTE

CAUTION: MAKE SURE THAT THE 1.00 INCH INSIDE DIAMETER BEARING AND THE LARGE

POCKET ARE LOCATED ON THE LEFT SIDE, THE LOADER RELIEF SLOTS ARE

LOCATED ON THE AFT FACE OF THE CENTER LINK WHEN SEE FROM THE AFT

SIDE OF THE CENTER LINK DURING INSTALLATION.

CAUTION: IF THE PARTS ARE MARKED, MAKE SURE THAT THE “L”, “R”, AND “AFT”

MARKINGS ARE ON THE NEAR SIDE WHEN SEE FROM THE AFT SIDE OF THE

ENGINE MOUNT. MAKE SURE THAT THE MARKINGS ON THE CENTER LINK

ASSEMBLY AGREE WITH THE “L”, “R”, AND “AFT” MARKINGS THAT ARE ON THE

HANGER FITTING WHEN THE CENTER LINK ASSEMBLY IS INSTALLED ON THE

HANGER FITTING.

1 Install

(Kept)

Center Link

Assembly

310A2034-7 or -8 1 Refer to 737 CMM

71-21-37/701.

Link Pin 310A2037-( ) 1

2 Install

(Kept)

Right Link

Assembly

310A2035-5, -7 or -8 1 Refer to 737 CMM

71-21-37/701.

Link Pin 310A2037-( ) 1

3 Install

(Kept)

Aft Engine Mount 310A2030-11 or -12 1 Refer to 737 AMM

71-21-03/401.

Link Pins 310A2037-( ) 4

4 Install

(Kept)

Engine - 1 Refer to 737 AMM

71-00-02/401.

(SHEET 4 OF 4)
APPENDIX A: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY REPORT FORM

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ALERT ALERT

APPENDIX A: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY REPORT FORM

Use this form if, after the inspection as specified in this Service Bulletin, a reversed aft engine mount, center link

assembly is found. The data below is necessary and will be used by Boeing and CFM International (CFMI) to

monitor and to calculate life-limits for the CFM56-7B turbine rear frame (TRF).

After the form is completed, please give a copy to your local Boeing Field Service Representative and your CFMI

Representative for routing.

AFT ENGINE MOUNT, CENTER LINK ASSEMBLY REPORT FORM

AIRPLANE DATA

Model ______________________ Series _____________________

Serial Number _______________________ Flight Hours _____________________________

Airline 3 -Letter Code ________________________ Flight Cycles __________________

Date Inspected _______________

ENGINE DATA

Supply data for the engine or engines as applicable where the reversed center link was found.

Engine 1 Engine 2

Engine Serial Number (ESN)____________ Engine Serial Number (ESN)_______________

Time Since New (TSN) _________________ Time Since New (TSN) ____________________

Cycles Since New (CSN) _______________ Cycles Since New (CSN) __________________

Time Since Overhaul (TSO)_____________ Time Since Overhaul (TSO)________________

Cycles Since Overhaul (CSO) ___________ Cycles Since Overhaul (CSO) ______________

Time Since Installation (TSI) ____________ Time Since Installation (TSI) _______________

Cycles Since Installation (CSI) __________ Cycles Since Installation (CSI) _____________

Turbine Rear Frame (TRF) Turbine Rear Frame (TRF)

Part Number _____________ Part Number __________________

Turbine Rear Frame (TRF) Turbine Rear Frame (TRF)

Serial Number ______________ Serial Number __________________

Aft Mount Part Number ________________ Aft Mount Part Number ___________________