54-42-00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 AFT ENGINE MOUNT - MAINTENANCE PRACTICES
________________________________________
 1.  General_______
 A.  There are three tasks in this procedure:
 (1)  
The first task removes the aft engine mount

 (2)  
The second task installs the aft engine mounts

 (3)  
The third task is the inspection of the aft engine mount.

 B.  The vibration isolator stays with the strut during an engine change. To do an inspection of the engine mounts and shear pins, you must remove the engine.
 C.  This procedure gives the wear limits for the shear pin, the fitting, and the strut fitting to bushing.
 D.  This procedure is for the left and right engines.
 TASK 54-42-11-002-001-B00
 2.  Aft Engine Mount Removal________________________
 A.  Equipment
 (1)  C71006 - Thread Protector
 B.  References
 (1)  
AMM 54-31-01/401, Nacelle Strut Access Panels

 (2)  
AMM 71-00-02/401, Power Plant

 C.  Access
 (1)  
Location Zones
 500 Left Nacelle
 600 Right Nacelle

 (2)  
Access Panels
 5725 Strut Access Door - Left Nacelle
 5825 Strut Access Door - Right Nacelle

 D.  Procedure
 S 012-002-B00
 (1)  
Remove the engine (AMM 71-00-02/401).

 (2)  
Remove the strut access doors (AMM 54-31-01/401).

 S 532-004-B00

 (3)  
Install the thread protector to prevent damage to the threads on the cone bolt.

 S 022-005-B00

 (4)  
Remove the bolts, nuts, and the washers that attach the vibration isolator to the strut (Fig. 201).

 S 012-003-B00
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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 ALL  ú ú B01 Page 201 ú Jul 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 S 022-006-B00
 (5)  
Remove the vibration isolator from the strut.

 S 222-009-B00

 (6)  
Do the inspection procedure for the aft engine mount.

 TASK 54-42-11-402-014-B00
 3. Aft Engine Mount Installation
_____________________________
 A. References
 (1)  
AMM 54-31-01/401, Nacelle Strut Access Panels

 (2)  
AMM 70-20-02/201, Tightening Practices and Torque Values

 (3)  
AMM 71-00-02/401, Power Plant

 B. Access
 (1)  
Location Zones
 500 Left Nacelle
 600 Right Nacelle

 (2)  
Access Panels
 5725 Access Door Strut - left Nacelle
 5825 Access Door Strut - Right Nacelle

 C. Procedure
 S 912-015-B00
 (1) Do a torque check for the self-locking nuts (AMM 70-20-02/201).
 NOTE: The break away torque for the BACN10HR6CS nuts is 9.5
____
 pound-inches.

 S 282-010-B00
 CAUTION: DO NOT INSTALL THE BARRY CONTROLS VIBRATION ISOLATOR
_______ P/N 93853-07 (BOEING SPECIFICATION S302A004-7) ON AIRPLANES WITH FORWARD ENGINE MOUNTS WHICH ARE ISOLATED. DAMAGE TO EQUIPMENT CAN OCCUR.
 (2)  
Do a check of the part number of the isolator to make sure it is correct.

 S 532-024-B00

 (3)  
Make sure the thread protector is on the conical surface of the cone bolt.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 54-42-11
 ALL  ú ú B01 Page 202 ú Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
UPPER LINK
WING
NACELLE STRUT
FORWARD ENGINE 
MOUNT  STRUT-TO-WING 
AFT ENGINE  DIAGONAL BRACE 
　
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