(f)  
Install the sync lock on the lower hydraulic actuator
 (AMM 78-34-13/401).

 S 844-029-N00
 (5)  Remove the hydraulic pressure after you install the rotary flex shafts.
 (a)  If you used hydraulic power from the airplane, do the steps that follow: 1) Make sure the applicable circuit breaker is open to remove
 the electrical power to the isolation valve: a) P6 Circuit Breaker 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

_ 2) Remove the hydraulic power from the airplane (AMM 29-11-00/201). 3) Remove the electrical power from the airplane (AMM24-22-00/201). 4) Push the deactivation slide into the isolation valve housing.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
5)  Install the streamered pin to hold the deactivation slide in the ground deactivation position. a) Install a hitch pin in the streamered pin.
 6)  Connect the engine-to-strut electrical connector, D4180 (LH sleeve) or D4182 (RH sleeve).
 (b)  If you used the hydraulic power from a hydraulic ground service cart, do the steps that follow: 1) Decrease the pressure in the hydraulic service cart to
 zero. 2) Disconnect the hydraulic service cart from the retract line flexhose on the top non-locking actuator. 3) Connect the retract line flexhose to the hydraulic connection at the strut.
 S 714-031-N00
 (6)  
Manually turn the actuator system through one full open and close cycle (AMM 78-31-00/201).

 S 864-032-N00

 (7)  
Do the activation procedure for the thrust reverser (AMM 78-31-00/201).

 S 864-033-N00

 (8)  
Remove the DO-NOT-OPERATE tags from the thrust levers.

 S 714-034-N00

 (9)  
Operate the thrust reverser through a minimum of three full open and close cycles (AMM 78-31-00/201).

 S 794-035-N00

 (10)
 Look for hydraulic fluid leaks.

 S 414-036-N00

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

 S 864-037-N00
 WARNING: MAKE SURE EQUIPMENT AND PERSONS ARE NOT NEAR THE LEADING EDGE
_______ FLAPS. THE LEADING EDGE FLAPS MOVE VERY QUICKLY AND CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (12) Do the activation procedure for the drive circuit of the leading edge flaps (AMM 27-81-00/201).
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THRUST REVERSER CONTROL SYSTEM - DESCRIPTION AND OPERATION
__________________________________________________________
 1.  General
_______
 A.  The system for the thrust reverser control governs the functions of deploying and stowing the thrust reverser in response to commands from the reverse thrust lever in the flight compartment. The thrust control system used for controlling forward thrust is also used for controlling reverse thrust (Ref 76-11-00/1).
 B.  The system for the thrust reverser control for each engine consists of the following:
 (1)  
An engine power control system consisting of forward/reverse thrust lever connected via the transducer for the thrust lever angle (TLA) to the electronic engine control (EEC) which commands the engine fuel control unit (Ref 76-11-00/1).

 (2)  
An electrical circuit to operate the isolation valve for the thrust reverser to port hydraulic fluid to the reverser actuation system, and to prevent reverser operation unless all the following required operating conditions are met.

 (a)  
Air/gnd relays are in the ground position.

 (b)  
Fire switch is in the normal position.

 (c)  
Electrical power bus provides 28v dc.

 (3)  
An electrical circuit to operate the directional control valve which ports hydraulic fluid to the extend or retract side of the reverser actuators.
　
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