SHEAR PIN
VIBRATION ISOLATOR
WASHER ASSEMBLY
(4 LOCATIONS)
NUT CONE BOLT(4 LOCATIONS)
A
Aft Vibraton Isolator Installation
Figure 201 (Sheet 1)
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54-42-11
ú ú B01 Page 203 ú Mar 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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
DIAGONAL BRACE
ACCESS DOOR AFT ENGINE
5725 (LEFT) MOUNT
5825 (RIGHT) SEE B
BOLT
(4 LOCATIONS)
COUNTERSUNK
WASHER
(4 LOCATIONS)
AFT MOUNT
BULKHEAD
PIN
SHIM 1
VIBRATION ISOLATOR ASSEMBLY
WASHER (4 LOCATIONS)
CONE BOLT NUT (4 LOCATIONS)
B
1 HOUSING TO SHIM GAP 0.10 INCH MINIMUM.
Aft Vibration Isolator Installation Figure 201 (Sheet 2)
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54-42-11
ú ú B01 Page 204 ú Nov 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
S 162-005-B00
(4) Make sure the surface where the isolator is to be installed is clean.
S 492-016-B00
CAUTION: YOU MUST INSTALL THE SHEAR PINS TO THE ENGINE MOUNT BEFORE YOU
_______ TIGHTEN THE NUTS. IF THE SHEAR PINS ARE NOT INSTALLED, DAMAGE TO THE STRUCTURE COULD OCCUR.
(5) Install the vibration isolator.
(a)
Put the bolt with the countersunk washer through the strut fitting.
(b)
Make sure the countersunk washer is adjacent to the bolt head.
(c)
Put the isolator assembly in place.
(d)
Install the washer and nut.
(e)
Tighten the nuts to 370-450 pound-inches (41.8-50.8 Newton meters).
S 412-020-B00
(6)
Install the engine (AMM 71-00-02/401).
S 412-021-B00
(7)
Install the strut access doors (AMM 54-31-01/401).
TASK 54-42-11-212-007-B00
4. Aft Engine Mount Inspection
___________________________
A. General
(1)
The vibration isolators are examined for these events:
(a)
High vibration indication (AMM 71-00-47/101)
(b)
Engine operations above the limits and high engine stress inspection after a rough landing (AMM 72-00-00/601).
(c)
Scheduled Maintenance as described in the Maintenance Planning Data Document.
(2)
You will do this examination after you remove the vibration isolator from the strut.
(3)
This examination recommends use of the Vendor Component Maintenance Manuals for the damage limits and repair information.
B. References
(1)
AMM 71-00-47/101, Power Plant - Trouble Shooting (Miscellaneous Observed Problems)
(2)
AMM 72-00-00/601, Engine
(3)
AIRPLANES WITH LORD VIBRATION ISOLATORS WITHOUT SB 71-1170; (302A005-2), CMM 54-40-01, Aft Vibration Isolation Assembly
(4)
AIRPLANES WITH LORD VIBRATION ISOLATORS WITH SB 71-1170; (S302A005-3), CMM 54-40-04, Aircraft Engine Mounting System
(5)
AIRPLANES WITHOUT SB 71-1170 WITH BARRY VIBRATION ISOLATORS; (S302A004-7), CMM 71-20-21, Engine Vibration Isolation System
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54-42-11
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