EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-11-03
 ALL  ú ú 05 Page 208 ú Dec 20/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL

 S 822-028
 (10) Adjust the cables to the value shown in Table 1.
 NOTE: Before the cables are adjusted, make sure that the airplane
____ temperature is stable (use a tolerance of |5°F) along the cable. Make sure that the temperature has been stable for at least one hour.
 ~..............................
 | Table 1 |
 | Aileron Cable Tension |
 ................................
 | | BODY CABLES |
 | TEMP °F | A1A, A1B, A2A, A2B |
 | | 5° | | 10 lbs |
 ................................
 | 110 | 118 |
 ................................
 | 90 | 109 |
 ................................
 | 80 | 104 |
 ................................
 | 70 | 100 |
 ................................
 | 60 | 96 |
 ................................
 | 50 | 92 |
 ................................
 | 40 | 88 |
 ................................
 | 30 | 84 |
 ................................
 | 10 | 75 |
 ................................
 | -10 | 67 |
 ................................
 | -30 | 59 |
 ................................
 | -40 | 53 |
 2.........…....................1

 S 092-029
 (11)
 Remove the rigging beam.

 S 212-030

 (12)
 Cycle the control wheel through one full travel cycle and do the checks that follow:

 (a)  
Make sure that rig pins A1 (for the lateral feel, centering, and trim mechanism) and A2 (for the lateral.control override mechanism) can be easily installed.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-11-03
 ALL  ú ú 02 Page 209 ú Sep 28/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 (b)  
Make sure that no more that two threads show at the turnbuckles when the system is rigged correctly.

 (c)  
Make sure that the cables are not bent by the fairleads, rubstrips, or grommets that are in the system.

 (d)  
Make sure that the cable gaurds are installed correctly and that the pulleys turn freely.

 (e)  
Make sure that the bottom surfaces of the control wheel touch the straight edge when rig pins A1 and A2 are installed. One bottom surface can be 0.03 inch (0.76 mm) away from the straight edge.

 (f)  
Remove the rig pins.

 S 432-031
 (13)
 Install the clip locks on the turnbuckles.

 S 422-032

 (14)
 Install the spoiler RVDT unit (Ref 27-61-04).

 S 422-033

 (15)
 Install the rudder pedal pushrods (Ref 27-21-05).

 S 862-034

 (16)
 Remove the DO-NOT-CLOSE tags and close these circuit breakers on the overhead panel, P11:

 (a)  
11E17, FLT CONT CMPTR PWR LEFT

 (b)  
11E18, FLT CONT CMPTR SERVO LEFT

 (c)  
11E19, FLT CONT CMPTR PWR CENTER

 (d)  
11E21, FLT CONT CMPTR SERVO CENTER

 (e)  
11E35, FLT CONT CMPTR PWR RIGHT

 (f)  
11E36, FLT CONT CMPTR SERVO RIGHT

 S 222-035
 (17)
 Do the test procedure below for the aileron control drums and bus force limiter.

 G.
Install Bus Force Limiter (Fig. 201)

 (1)  
Install the control wheel rigging beam.

 S 492-036
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-11-03
 ALL  ú ú 05 Page 210 ú Jan 28/02
　
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 1(88)