August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 62 ALERT ALERT 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2002 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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 provided in writing by Boeing.BLANK PAGE August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

BLANK PAGETable of Contents August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 62 

### 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52Table of Contents August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 62 

### 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 . . . . . . . . . . 62August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 62 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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 62 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, 2004August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 62 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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 8 of 62 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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 62 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 1.5August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 62 

### 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:V86787August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 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

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,August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 62 

### 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–YC877August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 62 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 YG017August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 62 

### 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–YC593August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT 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–YC030August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 62 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–YC588August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT 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 YC396August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 18 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT 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 YG076August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT 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 YG070August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 20 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT 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 1August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

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 GroupAugust 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

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 GroupAugust 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

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 GroupAugust 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 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 GroupAugust 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT 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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 28 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT 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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 30 of 62 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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 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, CFM56-7August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 62 

### 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 71-21August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 62 

### 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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 34 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 62 

### 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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 36 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 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.August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 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 August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 62 

### 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 A SEEV88902

(SHEET 1 OF 2)FIGURE 1: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) INSTALLATION INSPECTION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 62 

### 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



### BV88891

(SHEET 2 OF 2)FIGURE 2: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) REMOVAL AND INSPECTION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 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 A SEE



### A

1
SEE BV88901

(SHEET 1 OF 4)FIGURE 2: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) REMOVAL AND INSPECTION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 42 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

LINK PINS TURBINE REAR FRAME FWD 

### B 3 8 2 C SEE

2V88889

(SHEET 2 OF 4)FIGURE 2: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) REMOVAL AND INSPECTION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 62 

### 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 8N45757

(SHEET 3 OF 4)FIGURE 2: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) REMOVAL AND INSPECTION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 62 

### 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 August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 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 A SEEV88902

(SHEET 1 OF 2)FIGURE 3: AFT ENGINE MOUNT, CENTER LINK (WITH POCKETS) INSTALLATION INSPECTION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 62 

### 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



### BV86799

(SHEET 2 OF 2)FIGURE 4: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) REMOVAL AND INSPECTION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 47 of 62 

### 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 A SEEV86781

(SHEET 1 OF 4)FIGURE 4: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) REMOVAL AND INSPECTION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 48 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

REAR FRAME TURBINE LINK PINS FWD 2 3 C SEE 2

8



### BV86800

(SHEET 2 OF 4)FIGURE 4: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) REMOVAL AND INSPECTION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

LINK PIN LINK PIN

ASSEMBLY CENTER LINK ASSEMBLY RIGHT LINK FWD 6 7

6 7 4 5

4 5


### C 8N45582

(SHEET 3 OF 4)FIGURE 4: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) REMOVAL AND INSPECTION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 50 of 62 

### 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 310A2030-11 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 August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 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 August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 62 

### 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

1W21580

(SHEET 1 OF 1)FIGURE 7: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS), ADD IDENTIFICATION MARKS August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 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 August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 54 of 62 

### 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

A SEE385917 AFT ENGINE MOUNT

(SHEET 1 OF 4)FIGURE 8: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) AND ENGINE INSTALLATION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

LINK PINS FWD 

### A 3 3 B SEE AFT ENGINE MOUNT385918

(SHEET 2 OF 4)FIGURE 8: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) AND ENGINE INSTALLATION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 56 of 62 

### 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



### C385869

(SHEET 3 OF 4)FIGURE 8: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITHOUT POCKETS) AND ENGINE INSTALLATION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 62 

### 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 August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 62 

### 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

A SEE385931

(SHEET 1 OF 4)FIGURE 9: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) AND ENGINE INSTALLATION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 ALERT ALERT

LINK PINS AFT ENGINE MOUNT

FWD 3 3



### A B SEE385934

(SHEET 2 OF 4)FIGURE 9: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) AND ENGINE INSTALLATION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 60 of 62 

### 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



### C385936

(SHEET 3 OF 4)FIGURE 9: AFT ENGINE MOUNT, CENTER LINK ASSEMBLY (WITH POCKETS) AND ENGINE INSTALLATION August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 61 of 62 

### 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 August 29, 2002 Revision 3 May 20, 2004 737-71A1462 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 62 of 62 

### BOEING SERVICE BULLETIN 737-71A1462 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 ___________________