(2)
Cowling for transmission of vibration to airplane structure.
(3)
Tightness of engine mounts (Ref 71-00 R/I).
(4)
Inlet cowl for looseness or damage.
(5)
Thrust reverser doors for operation or damage.
(6)
Mounting of hydraulic pump for looseness (Ref Chapter 29).
(7)
Quad-ring of fuel control unit for looseness (Ref Chapter 73).
(8)
Contact of start lever on control stand bumper seal.
(9)
Thrust reverser levers on aisle stand for looseness.
(10)
Aisle stand for proper clearance between the thrust levers and the nylon strips, rework as required to obtain .000 to .005 total clearance, throughout lever travel.
B. If none of the above components are cause of vibration,
(1)
Install cork tape over the floor beams and/or add doublers and stiffeners on loose floor panels in the cockpit.
(2)
Inspect and repair engine per P&WA Maintenance Manual if engine reported vibration level is above limits.
500
Oct 20/87 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 71-00 Page 101
POWER PLANT (JT8D) - REMOVAL/INSTALLATION
1. General
A. The 737 airplane is equipped with integral engine change provisions, which are designed to permit rapid engine changes. These provisions include engine change hoist support fittings in the wing, low level accessibility, and a power plant with simple disconnects.
B. The engines will be removed or installed by using a hoist incorporating a load indicating system which provides a visible readout.
C. Many of the engine change disconnects are readily accessible from the ground. Others, such as firewall disconnects and access to the cone bolt nuts, will require the use of a six-foot stepladder or low workstand.
D. The power plant weighs approximately 5000 pounds with handling beams. The hoisting equipment shall be capable of supporting this weight and, because of the considerable weight involved, caution shall be used at all times when handling the engine to prevent injury to personnel, damage to equipment, and/or engine/airframe damage during engine removal/installation.
E. Before a power plant is removed or installed, check all openings and disconnected hose and tubing. During removal, all openings, tube ends, and electrical connectors shall be capped as soon as possible after disconnection. During installation, caps should be left in place until the connections are to be made. Use external caps on all openings; do not use internal plugs.
F. Engine compartment cleanliness is important because the intensive mass airflow tends to draw foreign objects into the engine. Thoroughly clean and check area after completion of any work. Keep the inlet area free of dirt, oil, and grease and remove all unused parts such as nuts, washers, and pieces of lockwire.
G. The service life of flexible metal hose assemblies will be extended if the following procedures are used.
(1)
Do not twist or kink the hose during installation.
(2)
Use two wrenches when attaching swivel nuts to mating fittings.
(3)
When one end of the hose is disconnected to permit engine change, do not twist the hose out of the way, distort it during handling, use it as a hand hold, or otherwise mistreat it.
500
May 01/00 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 71-00 Page 401
2. Equipment and Materials
A. Engine Support Beams - Boeing F72714 or F72988 (two required)
B. Load Indicating System Boeing F80219-45, -46, -47, -48, -68 and -69 consists of three loadcell assemblies and three hoist assemblies. The loadcell assemblies are identified as INBD FWD, INBD AFT and OUTBD.
C. Engine Cone Bolt Thread Protector - Boeing F70266-305 (one set required)
D. Engine Aft Cone Bolt Nut Adapter - Boeing F80257 or F80254
E. Engine Transportation Dolly - P/N 428 with adapters P/N 1843, (Ground Support Engineering, Miami, Florida); or P/N STC 90448-1, (Spec Tool Co., Pico Rivera, Ca 90660)
F. Engine Inlet Cover - Boeing F72717
G. Engine Exhaust Cover - Boeing F80093
H. Antiseize Compound - Ease-Off 990
I. Container for drained fuel - at least 5-gallon capacity
3. Prepare to Remove Power Plant
A. Ground airplane to an approved grounding lug.
B. Connect electrical power to airplane.
C. Position ground power switch to ON and battery switch to ON.
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