曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

NOTE:  On airplanes with non-energy absorbing secondary supports or with energy absorbing secondary support without retainer bushing the rub strip on the No. 1 engine can be installed facing inboard or outboard
NOTE:  The asbestos fiber (HEX) washer is manufactured thicker than the bushing head to arranged as shown in Fig. 401.
D.  Check for gap between nomex paper or thermosetting sheet washer or shims (if installed) and aft vibration isolator lug on both sides of installation. If a gap exist it shall be no greater than
0.002 inch maximum gap limitation. Ensure that isolator installation is as shown on Fig. 401.
NOTE:  Polyimide coated nomex paper washers are supplied as three separate washers each 0.015-inch thick. Laminated thermosetting sheet washer is supplied as a single washer 0.045-inch thick. Regardless of material type, the total thickness is 0.045 inch. Ensure complete coverage of bushing head in the event of adverse tolerance stack up at installation. This washer may be trimmed back to facilitate installation; however, do not trim past a point flush with the top of the bushing heads. Any damaged asbestos fiber (HEX) washer should be replaced and cemented to firewall (AMM 54-41-21/401).
501 
May 01/00  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  71-21-11 Page 401 

G42833 F96251 F96321
Aft Vibration Isolator Installation  5E4 
71-21-11 Page 402  Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/03 

501  Aft Vibration Isolator Installation 
May 01/03  Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  71-21-11 Page 402A 

Aft Vibration Isolator Installation  501 
71-21-11 Page 402B  Figure 401 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/03 

E.  AIRPLANES WITHOUT RETAINER BUSHING; Position shim(s) and retainer on the bolt.
F.  AIRPLANES WITH RETAINER BUSHING; Position washer, bushing and retainer on the bolt.
G.  Install flat washer and nut, and tighten the bolt to 250-300 pound-inches. Back the nut off to line up the next adjacent slot with hole in bolt.
H.  AIRPLANES WITHOUT RETAINER BUSHING; Adjust shim(s) to achieve a gap between 0.005 and 0.025 inch at the highest area on aft vibration isolator and retainer.
I.  Install a new cotter pin.
J.  Install the power plant (AMM 71-00/401).
501 
Aug 01/94  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  71-21-11 Page 403 

AFT CONE BOLT - REMOVAL/INSTALLATION
1. General
A.  For aft engine mount with secondary support assembly; the removal/installation is identical, except for the position of the secondary support assembly. The secondary support assembly is positioned outboard of each engine.
2.  Equipment and Materials
A.  Grease - MIL-G-23827
3.  Remove Aft Cone Bolt (Fig. 401)
A.  Remove power plant (Ref 71-00).
B.  Remove nut retainer, cotter pin, bolt retainer, nut, washers, and bolt securing aft cone bolt between flanges of engine aft mount ring. Remove cone bolt.
4.  Install Aft Cone Bolt (Fig. 401)
A.  Ensure that cone bolt to be installed is approved for 737 use. The preferred aft cone bolt is BAC10-60517-50 (shot peened). Cone bolts BAC10-60157-44 (uncoated) and BAC10-60517-40 (coated) are also used. Cone bolt BAC10-60517-40 (coated) should be reworked to BAC10-60517-44 by removing Dri-Lube coating.
CAUTION:  ONLY APPROVED CONE BOLTS HAVE THE CORRECT STRUCTURAL FUSE CHARACTERISTICS.
B.  Coat the shank of aft cone bolt attach bolts and mating holes with grease.
C.  Position cone bolt between flanges of engine aft mount ring.
D.  For aft cone bolt assembly.
(1)  
Insert bolt with bolthead forward through engine secondary support side fitting, holes in engine aft mount ring and hole in cone bolt.

NOTE: No washers are allowed under the head of the bolt.

(2)  
Install from zero to three thinner washers as needed to obtain the correct clearance.

(3)  
Install the thicker washer (required) next to the nut and install the nut.

(4)  
Tighten nut as required to allow 0.005 - 0.010 inch total end play between attach bolthead and engine mount flanges.

(5)  
Install new cotter pin.

(6)  
Install bolt and nut retainers.

E.  For secondary support assembly.
(1)  
Insert bolt with bolthead forward through engine secondary support side fitting, holes in engine aft mount ring, spacers, adjust shims to obtain 0.005 max. gap between spacer and engine flanges; and (for engine No. 1 only) rub strip.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 動力裝置 POWER PLANT(59)