cap to elastomer (Barry Controls 71-20-03).

(e)  
Inspect for separations in the bond between elastomer and metal. If separations are greater than 0.375 inch depth or 1.00 inch length, or if there are more than two separations on either end, replace vibration isolator.

501 
May 01/01  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  71-20-0 Page 604A 

7.  Examine Engine Aft Mount Secondary Support Assembly
A.  Check the crushable honeycomb energy absorber of the load limiter (Fig. 603).
(1)  Push softly on the honeycomb energy absorber on either side of the through bolt and check for movement. If the honeycomb energy absorber is not bonded at the top or bottom, replace the load limiter assembly.
NOTE:  The honeycomb energy absorber is bonded to the end plate at the lower end and to the top of the housing at the upper end. The sides of the honeycomb energy absorber are not bonded to the sides of the housing. There is a small clearance on both sides of the housing.
B.  Check the self-locking nut of the load limiter through bolt.
(1)  If the nut is missing or loosen, replace the nut. If the spacer is new or if the existing spacer is at least 0.67 inch thick, tighten the nut down on the crushable spacer. If the existing spacer is less than 0.67 inch thick, tighten the nut until two or three complete threads are above the nut. Make sure the self-looking torque of the nut is 12-60 pound-inches.
NOTE:  The crushable space is not critical to the operation of the secondary support. The crushable spacer does not need to be replaced if the soft honeycomb core is crushed or split. The purpose of the spacer is to allow the engine to drop down slightly in case of a cone bolt fracture on the ground with the engine at zero or idle thrust. This puts the cone bolt indicator on the nacelle fairing out of the green band. The minimum thickness of the spacer is based on the minimum distance required at the secondary support to move the indicator out of the green band
C.  Check the load limiter through bolt for grooves or wear patterns at the lower edge of the retainer.
(1)  Make sure that any wear grooves do to exceed the thread depth for the bolt. Minimum acceptable bolt diameter is 0.27 inch. If there is excessive wear, replace the bolt.
501 
71-20-0 Page 604B  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/00 

L17586 F95401 L17776
501  Forward Vibration Isolator Assembly Dimensions 
May 01/00  Figure 602 (Sheet 1)  71-20-0 
Page 605 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Aft Vibration Isolator  501 
71-20-0 Page 606  Figure 602 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/00 

500  Energy Absorbing Secondary Support Assembly 
May 01/00  with Crushable Spacer  71-20-0 
 Figure 603  Page 607 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

AFT VIBRATION ISOLATOR - REMOVAL/INSTALLATION
1.  Equipment and Materials
A.  Grease - MIL-G-23827
B.  Shims, Corrosion Resistant Steel - BAC66-23590-1, -2, -3, -4, -5, -6; as required
2.  Remove Aft Vibration Isolator (Fig. 401)
A.  Remove power plant (AMM 71-00/401).
B.  Remove isolator.
(1)  
AIRPLANES WITH NON-ENERGY ABSORBING SECONDARY SUPPORT; Remove cotter pin, nut, washers, cable retainer, shims (if installed), and bolt attaching aft vibration isolator to inboard flap outboard flap track, and remove isolator.

(2)  
AIRPLANES WITH ENERGY ABSORBING SECONDARY SUPPORT WITHOUT RETAINER BUSHING; Remove cotter pin, nut, washers, retainer, shims (if installed), and bolt attaching aft vibration isolator to inboard flap track outboard flap and remove isolator.

(3)  
AIRPLANES WITH ENERGY ABSORBING SECONDARY SUPPORT WITH RETAINER BUSHING; Remove the cotter pin, nut, washers, retainer and bushing, and bolt attaching aft vibration isolator to the inboard flap outboard flap track, and remove isolator.

3.  Install Aft Vibration Isolator (Fig. 401)
A.  Before installing vibration isolator, check that overall dimension across flanges of flap track bushings is 4.72 +0.02 inches. Adjust bushings (using a wrench on each bushing) as required (AMM 54-41-21/401).
B.  Coat aft vibration isolator mounting bolt and mating holes in isolator lugs and flap track with grease.
C.  Loosely install aft vibration isolator, with phenolic rub strip inboard, on inboard flap outboard flap track using bolt, (asbestos fiber [HEX] and [nomex paper or thermosetting sheet]) washers arranged as shown in Fig. 401.
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) 動(dòng)力裝置 POWER PLANT(58)