(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.
Install the Sync Lock (Fig. 401)

 S 434-010-N00
 (1)  
Remove the protection covers from all openings.

 S 424-011-N00

 (2)  
Install the sync lock (3) as follows:

 (a)  
Install the sync lock (3) on the lower non-locking hydraulic actuator (7) with the electrical connector (5) in the aft direction.

 (b)  
Tighten the torque nut (9) on the sync lock (3) with your hand.

 S 434-012-N00
 (3)  Put the gasket around the lower non-locking hydraulic actuator (7) as follows:
 (a)  Put the gasket in position to be below the band clamp (8). 1) Put the gasket in position so the ends of the gasket will
 be below the sync lock bracket (6). 2) The ends of the gasket must not make an overlap.
 NOTE: You can cut the gasket if it is necessary.
____
 S 434-013-N00
 (4)  Install the sync lock bracket (6) as follows:
 (a)  
Attach the sync lock bracket (6) to the sync lock (3) with the two bolts (1).

 (b)  
Tighten the bolts (1) loosely to make sure the sync lock bracket (6) can move in the slots.

 (c)  
Install the band clamp (8) on the tang of the sync lock bracket

 (6) and around the lower non-locking hydraulic actuator (7).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
(d)  Tighten the nut of the band clamp (8) to 30-35 pound-inches (3.4-4.0 newton-meters).
 S 424-014-N00
 (5)  Install the sync lock (3) as follows:
 (a)  
Hold the sync lock (3) with a 2-7/16 wrench on the wrench flats (4).

 (b)  
Tighten the torque nut (9) to 855-945 pound-inches (96.6-106.8 newton-meters).

 (c)  
Fully tighten the two bolts (1) that attach the sync lcok bracket (6) to the lower non-locking hydraulic actuator (7).

 S 434-015-N00
 (6)  
Connect the electrical connector DV170 (DV171) to the electrical connector (5) on the sync lock.

 D.
Put the Airplane Back to Its Usual Condition.

 S 414-017-N00
 (1)  
Close the applicable fan cowl panel (AMM 71-11-04/201).

 S 444-018-N00

 (2)  
Do the activation procedure for the thrust reverser
 (AMM 78-31-00/201).

 S 714-019-N00

 (3)  
Do the operational test of the thrust reverser system
 (AMM 78-31-00/501).

 (4)  
Remove electrical power (AMM 24-22-00/201).

 S 864-020-N00
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
THRUST REVERSER SYNC LOCK - ADJUSTMENT/TEST
___________________________________________
 1.  General
_______
 A.  There are two sync locks for each engine thrust reverser. The sync lock is installed on the lower non-locking hydraulic actuator of each thrust reverser sleeve.
 B.  The Thrust Reverser Sync Lock Integrity Test has two tasks:
 (1)  
The first task does a test of the electrical circuit which controls the operation of the sync lock on each thrust reverser sleeve.

 (2)  
The second task does a test of the the mechanical function of the sync lock on each thrust reverser sleeve.

 C.  
The thrust reverser sync lock is referred to as the sync lock in this procedure.

 TASK 78-34-13-285-001-N00
　
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