NOTE: Do the adjustment procedure for the applicable actuator lock
____ proximity sensor and the actuator deploy proximity sensor only. You do not need to do the adjustment procedure for the auto restow proximity sensor.
(a) Attach the proximity sensor wire (13) and clamps (14) on the hydraulic actuator bracket with the bolt (15), washers (16), and nut (17) (Fig. 402). 1) Tighten the bolt (5).
S 434-047-N00
(25)
Connect the two electrical connectors (3) for the feedback LVDT (12) of the locking hydraulic actuator.
G.
Put the Airplane Back to Its Usual Condition.
S 864-073-N00
(1)
Manually turn the actuator system through one full cycle
(AMM 78-31-00/201).
S 444-075-N00
(2)
Do the activation procedure for the thrust reverser
(AMM 78-31-00/201).
S 864-076-N00
(3)
Make sure all tube connections for the flex shafts from the lower
hydraulic actuator (7) and the top hydraulic actuator (3) to the
center hydraulic actuator (11) are correctly tightened (Fig. 402,
403, 404).
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S 714-077-N00
(4) Do the operational test for the thrust reverser (AMM 78-31-00/501).
(a) Operate the thrust reverser through three full deploy and stow cycles.
S 224-078-N00
(5)
Make sure the rod end clearance for the locking hydraulic actuator (dimension "A" in Fig. 401) is not more than 0.100 inch with the hydraulic power removed.
S 414-079-N00
(6)
Install the access panels for the hydraulic actuator with the screws (Fig. 401).
S 414-080-N00
(7)
Close the fan cowl panels (AMM 71-11-04/201).
S 864-081-N00
(8)
Remove the DO-NOT-OPERATE tags from the forward thrust lever and the reverse thrust lever.
S 444-082-N00
WARNING: MAKE SURE PERSONS AND EQUIPMENT ARE NOT NEAR THE LEADING EDGE
_______ FLAPS WHEN YOU DO THE ACTIVATION PROCEDURE. THE LEADING EDGE FLAPS MOVE VERY QUICKLY AND CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(9) Do the activation procedure for the drive circuit of the leading edge flaps (AMM 27-81-00/201).
TASK 78-31-17-004-098-N00
4. Remove the Thrust Reverser Non-Locking Hydraulic Actuator
_________________________________________________________
A. References
(1) AMM 27-62-00/201, Speed Brake Control System
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
(2)
AMM 27-81-00/201, Leading Edge Flap System
(3)
AMM 71-11-04/201, Fan Cowl Panels
(4)
AMM 78-31-00/201, Thrust Reverser System
(5)
AMM 78-36-01/401, Thrust Reverser Proximity Sensors
B.
Access
(1)
Location Zone
415 and 416 Engine 1 - Thrust Reverser Halves
425 and 426 Engine 2 - Thrust Reverser Halves
435 and 436 Engine 3 - Thrust Reverser Halves
445 and 446 Engine 4 - Thrust Reverser Halves
(2)
Access Panels
413 and 414 Fan Cowl Panels - Engine 1
423 and 424 Fan Cowl Panels - Engine 2
433 and 434 Fan Cowl Panels - Engine 3
443 and 444 Fan Cowl Panels - Engine 4
C.
Prepare to Remove the Non-Locking Hydraulic Actuator
S 044-099-N00
WARNING: DO THE DEACTIVATION PROCEDURE FOR THE SPEED BRAKE CONTROL
_______ SYSTEM. IF YOU DO NOT DO THIS THE SPOILERS CAN MOVE QUICKLY WHEN YOU MOVE THE THRUST LEVERS. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
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本文链接地址：747-400 AMM 飞机维护手册 EXHAUST 2(41)
