engaged in the fin structure.

 (b)  
Install the top bolt assembly, bushings, and the washer.

 (c)  
Install the inner nut and tighten it to 50-60 pound-inches (5.7-6.7 newton-meters).

 (d)  
Install the outer nut and tighten it to 10 pound-inches

 (1.13 newton-meters).
 NOTE: Do not change the torque valve for the inner nut.
____
 S 432-052
 (2)  
Do these steps to connect the trim actuator to the spring arm assembly:

 (a)  
Install the bolt assembly and the bushings.

 (b)  
Install the inner nut and tighten it to 50-60 pound-inches (5.7-6.7 newton-meters).

 (c)  
Install the outer nut and tighten it to 10 pound-inches

 (1.13 newtons).
 NOTE: Do not change the torque valve for the inner nut.
____
 S 432-031
 (3)  
Connect the electrical connector to the trim actuator.

 I.
Install the Roller Bearing to the Cam Roller Arm Assembly (Fig. 202)

 S 622-056
 (1)  
Apply the corrosion preventive compound to the bolt before
 installation.

 S 422-055

 (2)  
Do these steps to install the roller bearing:

 (a)  
Install the roller bearing with the bolt and washers.

 (b)  
Install the inner nut and tighten it to 60 - 80 pound-inches (6.8-9.0 newton-meters).

 (c)  
Install the outer nut and tighten it to 15 - 20 pound-inches (1.7-2.2 newton-meters).

 NOTE: Do not change the torque value for the inner nut.
____
 S 432-058
 (3)  
Install the two feel and centering springs.

 J.
Feel, Centering, and Trim Mechanism - Test

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-21-06
 ALL  ú ú 01 Page 213 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 S 862-047

 WARNING:_______ KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES WHEN
 HYDRAULIC POWER IS SUPPLIED.  AILERONS, ELEVATORS, RUDDER,
 FLAPS, SLATS.  SPOILERS, AND STABILIZER ARE FULLY POWERED
 SURFACES.  INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR

 WHEN HYDRAULIC POWER IS SUPPLIED.
 (1)  
Supply pressure to the left, right, and center hydraulic systems (Ref 29-11-00).

 S 862-032

 (2)  
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P11 panel:

 (a)  
11H17, FLT CONT SHUTOFF TAIL LEFT

 (b)  
11H18, FLT CONT SHUTOFF TAIL CTR

 (c)  
11H28, FLT CONT SHUTOFF TAIL RIGHT

 S 862-033
 (3)  
Remove the DO-NOT-OPERATE tags and move the FLT CONTROL SHUTOFF switches L, C, and R on the right side panel, P61, to ON.

 S 862-034

 (4)  
Make sure these circuit breakers on the P11 panel are closed:

 (a)  
EICAS (6 locations)

 (b)  
11C10, RUD TRIM

 S 862-035
 (5)  
Push the STATUS switch on the pilot's display select panel, P9, to show the rudder position indicator on the bottom EICAS display.

 S 212-036

 (6)  
Move the captain's right rudder pedal to its full forward position and do this check:

 (a)  
Make sure the rudder trailing edge moves smoothly to its full right position.

 (b)  
Make sure the rudder position indicator moves to its full right position.

 S 212-037
 (7)  
Move the captain's left rudder pedal to its full forward position and do these checks:

 (a)  
Make sure the rudder trailing edge moves smoothly to its full left position.

 (b)  
Make sure the rudder position indicator moves to its full left position.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-21-06
 ALL  ú ú 01 Page 214 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：757 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(51)