S 434-072-N00

 (16)
 Install the extend port cap (4) on the upper non-locking hydraulic actuator (3) if the upper non-locking hydraulic actuator was installed.

 G.
Put the Airplane Back to Its Usual Condition.

 S 864-107-N00
 (1)  
Manually turn the actuator system through one full cycle
 (AMM 78-31-00/201).

 S 864-108-N00

 (2)  
For the applicable engine, remove the DO-NOT-CLOSE tags and close this circuit breaker that follows:

 (a)  P6 Main Power Distribution Panel
 1) 6F13 T/R CONT ENG 1
 2) 6E13 T/R CONT ENG 2
 3) 6D13 T/R CONT ENG 3
 4) 6C13 T/R CONT ENG 4

 S 864-109-N00
 (3)  
Do the activation procedure for the thrust reverser
 (AMM 78-31-00/201).

 S 434-110-N00

 (4)  
Make sure all tube connections for the flex shafts from the lower hydraulic actuator (7) and the upper hydraulic actuator (3) to the center hydraulic actuator (11) are correctly tightened (Fig. 402, 403, 404).

 S 714-111-N00

 (5)  
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.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 78-31-17
 ALL  ú ú N02 Page 435 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 414-113-N00
 (6)  
Install the access panels for the hydraulic actuator with the screws (Fig. 401).

 S 414-114-N00

 (7)  
Close the fan cowl panels (AMM 71-11-04/201).

 S 864-115-N00

 (8)  
Remove the DO-NOT-OPERATE tags from the forward thrust lever and the reverse thrust lever.

 S 444-116-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).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 78-31-17
 ALL  ú ú N02 Page 436 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
THRUST REVERSER HYDRAULIC ACTUATORS - ADJUSTMENT / TEST
_______________________________________________________
 1.  General
_______
 A.  This procedure gives the instructions to adjust the feedback rod
 posistional reference for the rod end to the hydraulic actuator.

 B.  There are two types of thrust reverser hydraulic actuators: locking and non-locking. Both types of actuator have a initial requirement for a 0.010-0.018 inch gap between the rod end collar and the actuator cylinder when the actuator is fully retracted. The gap on the locking actuators is adjusted by rotating the rod end of the actuator. The gap on the non-locking actuator is not adjustable and is set at the time of manufacture.
 TASK 78-31-17-605-003-N00
 2.  Adjust the Center Locking Hydraulic Actuator (Fig. 501)
_______________________________________________________
 A.  References
 (1)
AMM 27-62-00/201, Speed Brake Control System

 (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 78-31-17/401, Thrust Reverser Hydraulic Actuators

 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)  
　
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