78-31-13
ALL ú ú C01 Page 605 ú Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
(b)
Examine the Rulon-J surface on the auxiliary slider fitting (Fig. 601). 1) If the Rulon-J is missing or worn through, do the task to
install a new slider fitting (CMM 78-31-23).
(c)
Use a pin gauge to measure the thickness of the Rulon-J surface. 1) If the Rulon-J is worn to less than 0.010 inch (0.254 mm),
do the task to install a new slider fitting (CMM 78-31-23).
S 426-011-C00
(5)
If not already done, install the slider fitting (CMM 78-31-23).
S 946-012-C00
(6)
Do this task: Put The Airplane Back To Its Usual Condition.
TASK 78-31-13-906-013-C00
4. Put The Airplane Back To Its Usual Condition
A. References
(1)
AMM 71-11-02/201, Fan Cowl Panels
(2)
AMM 78-31-00/201, Thrust Reverser
B. Procedure
S 416-018-C00
WARNING: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
_______ REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(1)
Close the thrust reverser (AMM 78-31-00/201).
S 416-014-C00
(2)
Close the fan cowl panels (AMM 71-11-02/201).
S 446-015-C00
(3)
Do this task: Thrust Reverser Activation After Ground Maintenance (AMM 78-31-00/201).
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78-31-13
ALL ú ú C01 Page 606 ú Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
THRUST REVERSER CONTROL SYSTEM - DESCRIPTION AND OPERATION
__________________________________________________________
1. General
_______
A. The thrust reverser control system governs the functions of deploying and stowing the thrust reverser in response to commands from the reverse thrust lever in the flight compartment.
2. Thrust Reverser Hydraulic Fuse
______________________________
A. There are six hydraulic fuses installed in the thrust reverser hydraulic system. If a failure or line rupture occurs, the fuse will close to prevent a complete loss of hydraulic fluid. The fuses in the pressure lines are designed to let 175 cubic inches of fluid flow before it closes, while those in the return lines are designed to let 80 cubic inches of fluid flow before it closes. The two types of fuses will reset automatically when the hydraulic pressure on the two sides of the fuse is equalized to within 5 psi.
B. The return line hydraulic fuses are located in each air conditioning bay. The primary pressure system hydraulic fuses are located on the forward bulkhead of each main landing gear wheel well, between the landing gear system transfer valve and the thrust reverser shuttle valve. The standby pressure system hydraulic fuses are located in the main landing gear bay on the keel beam.
3. Thrust Reverser Shuttle Valve
_____________________________
A. The thrust reverser shuttle valve shifts the hydraulic pressure supply from the primary system to the standby system or vice-versa, when the pressure difference between the two systems exceeds approximately 125 psi.
B. The thrust reverser shuttle valves are located on the forward bulkhead of the main landing gear wheel well.
4. Thrust Reverser Control Valve Module
____________________________________
A. The thrust reversor control valve module, located in the air-conditioning bay, is a completely, self-contained unit, housing all of its necessary components in one manifold. The manifold provides for all hydraulic and electrical connections to the aircraft structure. The unit converts electrical signals from the aircraft thrust reverser control system into controlled hydraulic flow to the reverser actuators.
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