F. Electrical power must not be on during the time the fuel, hydraulic, and electrical lines are being disconnected from or connected to the strut. If being provided, remove electrical power (Ref 24-22-0 MP).
WARNING: KEEP ELECTRICAL POWER OFF DURING DISCONNECTION OR CONNECTION OF FUEL, HYDRAULIC, AND ELECTRICAL LINES TO PREVENT INJURY TO PERSONNEL THAT COULD RESULT FROM ACCIDENTAL APPLICATION OF PRESSURIZED FLUIDS, ENERGIZING OF ELECTRICAL CIRCUITS OR FIRE.
G. Pull (open) FUEL FLOW circuit breakers to prevent fuel flow transmitter damage resulting from dry operation.
H. Place thrust levers in fully retarded position and start levers in CUTOFF.
I. Depressurize hydraulic system A.
J. Check all three hoist attach fittings and related wing support structure for evidence of loose fasteners, nicks, cracks, gauges, chipped finish and/or signs of visible damage.
K. Remove electrical power if no longer required (Ref 24-22-0 MP).
4. Remove Power Plant
WARNING: ENGINE WEIGHS APPROXIMATELY 5000 POUNDS WITH BEAMS. MAKE CERTAIN ENGINE SUPPORT ASSEMBLY IS ADJUSTED TO GIVE EVEN FORE AND AFT SUPPORT TO ENGINE. UNEVEN SUPPORT CAN CAUSE ENGINE TO SHIFT RESULTING IN INJURY TO PERSONNEL AND/OR DAMAGE TO ENGINE AND AIRPLANE STRUCTURE.
A. Remove engine side removable cowl panels (Ref 71-11-11).
B. Remove forward, mid, and aft access panels on both sides of the midfairing. Remove the cone bolt access door on each side of the fixed fairing.
C. Remove fixed fairing (Ref 71-11-21).
D. If being provided, remove electrical power (Ref 24-22-0 MP). Drain engine fuel supply line by opening drain port below the fuel filter. Provide 5-gallon container for drained fuel. Loosen fuel supply line at disconnect point to hasten draining. Close drain port after draining and lockwire (Fig. 401).
E. Following draining, uncouple fuel supply flex hose (11) at the disconnect bracket on the engine (Fig. 402).
F. Disconnect the pneumatic duct from the flanged coupling on the horizontal firewall (4).
G. Disconnect electrical connectors (1) at the forward end of the firewall, and electrical connectors
(13) on the forward horizontal firewall (Fig. 402).
H. Disconnect engine pressure ratio sensing lines (2) and the high pressure sensing line (9) at their disconnect brackets.
May 01/00 71-00 Page 403 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G42795
Fuel Line Draining 544
71-00 Figure 401 May 15/80
Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
I. On No. 1 engine, disconnect water pressurizing line (10) at disconnect bracket.
J. Uncouple the hydraulic supply, pressure, and return lines (7) at their disconnect bracket.
WARNING: A SMALL QUANTITY OF HYDRAULIC FLUID MAY SPILL FROM THE LINES. MAKE CERTAIN THAT ANY SPILLED HYDRAULIC FLUID IS CLEANED UP IMMEDIATELY.
K. Disconnect hydraulic reservoir pneumatic pressurizing line (5) at disconnect bracket.
L. Disconnect the engine bonding lead(s) at the grounding lug (3) near the forward end of the firewall.
M. Disconnect the aft strut drain line (6), at the disconnect bracket. If required for other maintenance, provide electrical power (Ref 24-22-0 MP).
N. Disconnect the engine start and thrust control push-pull cables (8) at engine cross-shaft (Fig. 403).
O. Remove the two locknuts and washers securing the engine controls support brackets at approximately the 8 o'clock position on the engine. Pull the two support brackets away from fixed bracket.
P. Remove locknut, washer, and bolt attaching engine start push-pull cable support clamp to bracket on engine flange at the 9 o'clock position on the engine.
Q. Remove the two locknuts and washers securing the engine control cables to the spacer block at approximately the 10 o'clock position on the engine. Remove the top spacer block and swing the cables free.
NOTE: Possible interference between the push-pull cables and the engine during removal and installation of the power plant will be minimized if the cables are swung up and secured to airplane structure.
R. With thrust reverser in forward thrust position, uncouple thrust reverser push-pull cable at quick-disconnect (Fig. 404).
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本文鏈接地址：737 AMM 飛機維護手冊 動力裝置 POWER PLANT(5)
