(3)  
Install these components:

 (a)  
The bolts that connect the support bracket to the airplane (4 locations).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-11-14
 ALL  ú ú 01 Page 208 ú Jun 20/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 (b)  The bolts that connect the support fitting to the airplane (4 locations).
 (4)  S 822-031Make sure the cam roller is in the center of the feel cam.
 (5)  S 492-073Install rig pin A1 (for the feel, centering, and trim mechanism).
 (6)  S 432-032Connect the electrical connector to the trim actuator.
 (7)  S 862-033Remove the DO-NOT-CLOSE tag and close this circuit breaker on the overhead panel, P11: (a) 11J15, AILERON TRIM
 (8)  S 822-034Operate the aileron trim switches until you can easily install the bolt that connects the actuator clevis to the actuator link.
 (9)  S 492-035Install these rig pins: (a) A2 (for the lateral control override mechanism) (b) A3 (for the aileron quadrant and override mechanism)
 S 222-074

 (10)
 Make sure that the length of the ALCS control rod is correct (Fig. 201).

 S 822-075

 (11)
 If it is necessary, do these steps to adjust the ALCS control rod:

 (a)  
Adjust the rod end on the autopilot crank end of the control rod to 1.34 to 1.36 inches (34.0-34.5 mm). 1) Tighten the jamnut.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-11-14
 ALL  ú ú 01 Page 209 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 (b)  Turn the control rod body (to adjust the rod end at the autopilot servo) until the control rod is approximately
 12.51 inch (31.7 cm) long.
 S 432-038
 (12)
 Connect these components:

 (a)  
The ALCS control rod to the autopilot crank (2 locations)

 (b)  
The bus rod (for the lateral control override mechanism) to the arm

 (c)  
Body cables A1A and A1B to the feel, centering, and trim mechanism

 (d)  
Wing cables A1A and A1B to the feel, centering, and trim mechanism.

 S 092-039
 (13)
 Remove rig pins A1, A2, and A3.

 S 822-040

 (14)
 Do these steps if you installed new cables:

 (a)  
Install the control wheel rigging beam.

 (b)  
Tighten the cables to two times the value shown in Table 1.

 (c)  
Remove the rigging beam.

 (d)  
Move the control wheel through its full travel range 20 times.

 S 492-041
 (15)
 Install the control wheel rigging beam.

 (16)
 Adjust the cable tension to the value shown in Table 1.

 S 822-042
 NOTE: Before you do the adjustment, make sure the cable temperature
____
 is stable (use a tolerance of |5°F). Make sure the
 temperature was stable for at least one hour.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-11-14
 ALL  ú ú 01 Page 210 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 ~.........................................................

 |  |  BODY CABLES  |  WING CABLES  |
 |  TEMP °F  |  A1A, A1B  |  A1A, A1B  |
 |  | 5° F  |  | 10 LBS  |  | 10 LBS  |

 ........................................................... | 110 | 118 | 98 | | 90 | 109 | 89 | | 80 | 104 | 84 | | 70 | 100 | 80 | | 60 | 96 | 76 | | 50 | 92 | 72 | | 40 | 88 | 68 | | 30 | 84 | 64 | | 10 | 75 | 55 | | -10 | 67 | 47 | | -30 | 59 | 39 | | -40 | 53 | 39 | 2..................…...................…..................1
　
中國航空網(wǎng) 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 1(93)