BOEING 737
MAINTENANCE MANUAL
CHAPTER 54 TAB EFFECTIVE PAGES SEE LAST PAGE OF LIST FOR NUMBER OF PAGES CONTENTS 54 1 OCT 20/89 5062 BLANK 54- 00 1 MAY 15/67 5002 BLANK 54- 10- 02 601 OCT 20/89 500602 OCT 20/89 500603 OCT 20/89 500604 BLANK 54- 11-0 1 FEB 15/68 5002 BLANK 54- 31-0 1 AUG 15/73 5382 NOV 01/74 540 54- 41-0 1 OCT 20/92 5052 FEB 20/87 500 54- 41-0 601 OCT 20/92 505602 FEB 20/87 500603 FEB 20/87 500* 604 MAY 01/03 500605 MAY 20/82 500606 FEB 20/86 500 54- 41- 11 401 MAY 01/01 574402 MAY 01/99 518403 MAY 01/01 501404 MAY 01/99 500 54- 41- 21 401 SEP 20/81 500402 AUG 01/94 501403 AUG 01/94 501404 AUG 01/94 501 54- 51-0 1 OCT 20/91 5E42 BLANK 54- 51- 11 401 FEB 15/77 563402 FEB 15/77 563 PAGE DATE CODE 54- 51- 11 501 FEB 20/84 563502 NOV 15/68 500 54- 51- 32 401 FEB 15/69 506402 FEB 15/69 501 54- 51- 41 401 MAY 15/68 500402 MAY 15/71 500 PAGE DATE CODE PAGE DATE CODE PAGE DATE CODE
* = REVISED, ADDED OR DELETED PAGE F = FOLDOUT PAGE
C8 CHAPTER 54 EFFECTIVE PAGES
MAY 01/03 PAGE 1
LAST PAGE
D6-37115
Description and Operation STRUT DRAINS.......................................................................................................... 54-10-02 Inspection/Check MAIN FRAME ENGINE FIREWALL ................................................................................................... 54-11-0 Description and Operation PLATES AND SKIN ENGINE COWLING .................................................................................................... 54-31-0 Description and Operation Movable Cowls and Fixed Cowls Nose Dome and Nose Cowl Thrust Reverser Fairing ATTACH FITTINGS ENGINE ATTACH FITTINGS ..................................................................................... 54-41-0 Description and Operation Inspection/Check Forward Engine Mount................................................................................................ 54-41-11 Removal/Installation Fiber Washer............................................................................................................... 54-41-21 Removal/Installation FILLETS/FAIRINGS ENGINE-TO-WING FAIRING ..................................................................................... 54-51-0 Description and Operation Engine-To-Wing Forward Fairing................................................................................ 54-51-11 Removal/Installation Adjustment/Test Engine-To-Wing Aft Fairing......................................................................................... 54-51-32 Removal/Installation Engine-To-Wing Midfairing ......................................................................................... 54-51-41 Removal/Installation
506 Oct 20/89 Contents 54 Page 1 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
NACELLES/PYLONS - DESCRIPTION AND OPERATION
1. General
A. Two engines are installed on the airplane, one on each wing. (See figure 1.) Each engine is mounted at three points directly from the wing. The cowling and supporting structure of the engines is generally constructed of aluminum alloy. Steel, stainless steel or titanium is used in areas where high structural strength and fire or heat resistance is required. The engine-to-wing fairing is supported by the wing. The fixed cowl is attached to the engine and the movable cowl is supported by hinges from the fixed cowl.
B. The engines are mounted by cone bolts at two points forward and at a single point aft. The forward mounting, with thrust links, takes all thrust loads plus vertical and side loads. Engine vibration isolators are installed at the structural engine attachment points. The engine support fittings are designed to allow for thermal expansion of the engines.
C. The forward attachment fittings consist of a steel forging suspended from fittings attached to wing structure. The aft attachment fitting is suspended from the outboard track of the inboard flap.
D. Engine hoist fittings, with protective covers are installed on the surface of the wing.
500 Engine Nacelles
May 15/67 Figure 1 54-00
Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
MIDFAIRING DRAINS - INSPECTION/CHECK
1. General
A. The midfairing drain system disposes of accumulated fluids leaking from system plumbing routed through the midfairing. The midfairing clearing procedure gives the instructions for clearing a midfairing drain system blockage using compressed air.
2. Clear Midfairing Drains
A. Equipment and Materials
(1)
Air supply 25-35 psig regulated, hose and nozzle
(2)
Plugs - suitable for air-tight sealing of drain tube openings
B. Prepare to Clear Drains
(1)
Remove forward, mid and aft access doors and panels from both sides of the midfairing.
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 NACELLES/PYLONS
