(3)  
AMM 51-31-00/201, Seals and Sealing

 (4)  
AMM 54-31-01/401, Nacelle Strut Access Panels

 (5)  
AMM 54-32-01/401, Forward Fairings

 (6)  
AMM 54-32-02/401, Aft Fairing

 (7)  
AMM 71-00-02/401, Power Plant

 (8)  
AMM 71-11-02/401, Fan Cowl Panels

 (9)  
AMM 78-31-00/201, Thrust Reverser System

 (10)
 CPM 54-40-37, Part 3

 (11)
 OHM 54-50-01

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 54-10-01
 ALL  ú ú B03 Page 418 ú Mar 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 D.  Access
 (1)  Location Zone
 500 Left Nacelle
 600 Right Nacelle

 E.  Prepare for the Pin/Bolt Installation.
 S 214-033-B00
 (1)  Do a check that all pins, bolts, caps, and washers at the
 installation points are free from corrosion.

 (a)  
Include the interior of the fuse pins or bolts, and the inner diameter of the fitting bushings.

 (b)  
Do these steps if you find corrosion: 1) To remove the corrosion, refer to CPM 54-40-37, Part 3. 2) To repair or replace the corroded part, refer to

 OHM 54-50-01. 3) Apply a 0.05 inch (1.3 mm) thick layer of corrosion-preventive compound to the inner surface of the pin/bolt.
 S 214-034-B00
 (2)  Make sure all bushings at the installation points are sealed from corrosion.
 (a)  If some of the bushings are not sealed, apply sealant to the bushings (AMM 51-31-00/201). 1) Apply a fillet seal to the flanged end of all bushings. 2) Apply sealant (maximum thickness 0.010 inch) to all
 unflanged bushing ends which are open to corrosion after the pins/bolts are assembled.
 NOTE: No seal is necessary for unflanged bushing ends
____ which are closed to corrosion after the pins/bolts are installed.
 a) Do not include the upper link or the diagonal brace. 3) Apply sealant to the bushing ends, that do not have flanges, at the diagonal brace wing fitting.
 F.  Install the applicable pin/bolt.
 S 424-035-B00
 (1)  Install the fuse bolt in the midspar fitting (Figure 402, Detail C).
 (a)  
Make sure corrosion-preventive compound is applied to all of the inner surface of the fuse bolt.

 (b)  
Apply a thin layer of grease to the OD of the fuse bolt.

 (c)  
Push out the brass slug with the greased fuse bolt. 1) Make sure the clevis and the lug stay aligned. 2) Make sure the head of the fuse bolt is installed on the

 outboard side of the strut.

 (d)
Install the washer and locknut on the end of the fuse bolt.

 1)  Apply a thin layer of grease between the washer and the fuse bolt.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 54-10-01
 ALL  ú ú B02 Page 419 ú Mar 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
 (e)

(f)

(g)

(h)

A
737-300/400/500MAINTENANCE MANUAL
Do a check of the self-locking torque of the locknut.
 1)  If the self-locking torque is not 90-800 pound-inches (10.3-91.2 N.m), replace the locknut and do the check again.
 NOTE: The torque wrench must be installed on the nut
____ and not the head of the bolt. The C54003 socket can be used to hold the fuse pin while tightening the nut.
Tighten the locknut to 1000-1200 pound-inches (114.0-136.8
 N.m).
Install the cap, bolt, nut, and two washers:
 1) Apply a thin layer of grease on the contact surfaces of the

 cap, two washers, and bolt. 2) Assemble the cap, two washers, bolt, and nut. 3) Tighten the nut to 150-350 pound-inches (17.1-39.9 N.m). 4) Install the cotter pin.
 a)  If it is necessary, you can loosen the nut a minimum quantity to install the cotter pin.
 5)  Apply sealant approximately 0.10 inch (2.54 mm) thick, to the two ends of the cotter pin, to prevent movement of the cotter pin.
Install the side link assembly (Figure 402, Detail H).
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 NACELLES/PYLONS(18)