(c)  
Make sure the rudder is no more than 0.10 inch (2.5 mm) away from its neutral position.

 S 222-062
 (6)  
Move the RRCM test switch to NORMAL. Stop for 30 seconds to let the ratio-changer actuator retract and do the checks that follow:

 (a)  
Make sure the IN TEST light on each RRCM is ON no more than 18 seconds.

 (b)  
Make sure the RRCM faultballs are black.

 (c)  
Make sure the rudder is no more than 0.15 inch (3.8 mm) away from its neutral position.

 (d)  
Make sure that rig pin R9 can be easily pushed through the shear pin.

 S 862-086
 (7)  
Remove the power from the left, right, and center hydraulic systems (Ref 29-11-00).

 J.
Put the Airplane Back to its Usual Condition

 (1)  
Make sure that all the rig pins are removed.

 S 862-064

 (2)  
Remove the DO-NOT-CLOSE tags and close the P11 panel circuit breakers shown in Table 201.

 S 212-063
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-21-12
 ALL  ú ú 04 Page 217 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
 S 092-007
 WARNING: STAY AWAY FROM THE NOSE WHEELS WHEN THE LOCKPIN IS REMOVED.
_______ THE WHEELS CAN TURN TO THE CENTER POSITION QUICKLY, AND CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
 (3)  Make sure that the nose wheels are in their center position and remove the towing lever lockpin from the nose gear (Fig. 203).
 S 212-004
 CAUTION: IF THE RRCM TEST SWITCH IS NOT IN ITS "NORMAL" POSITION, THE
_______ AMBER "RUDDER RATIO" LIGHT WILL COME ON. THIS WILL PREVENT AIRPLANE DISPATCH.
 (4)
Make sure that the RRCM test switch is in its NORMAL position.

 S 862-067

 (5)
Remove electrical power if it is not necessary (Ref 24-22-00).

 S 412-068

 (6)
Close access panels 324AL, 324BL, and 324CL (Ref 06-42-00).

 TASK 27-21-12-022-088
 4. Remove the Rudder Ratio-Changer Linear Variable Differential
____________________________________________________________
 Transducer (LVDT)

_________________
 A. References
 (1)  
06-42-00/201, Empennage Access Doors and Panels

 (2)  
24-22-00/201, Electrical Power - Control

 (3)  
29-11-00/201, Pressurize/Depressurize Main Hydraulic System

 B.
Access

 (1)  
Location Zone 324 Vertical Stabilizer - Rear Spar to Trailing Edge

 (2)  
Access Panels 324AL Body to Fin Seal 324BL Aft Side of Rear Spar and Rudder Hinge 324CL Rudder Hinge and PCU's

 C.
Prepare for Removal

 (1)  
Supply electrical power (Ref 24-22-00).

 S 862-070

 (2)  
Remove the power from the left, right, and center hydraulic systems (Ref 29-11-00).

 S 862-069
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-21-12
 ALL  ú ú 05 Page 218 ú Mar 20/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757 MAINTENANCE MANUAL
 S 862-071
 (3)  
Move the FLT CONTROL SHUTOFF L, C, and R switches on the right side panel, P61, to OFF. Attach DO-NOT-OPERATE tags and make sure that the amber switch-position legend lights come ON.

 S 862-072

 (4)  
Open these circuit breakers on the overhead panel, P11, and attach DO-NOT-CLOSE tags:

 (a)  
11D18 or 11G10, RUD RATIO

 (b)  
11H17, FLT CONT SHUTOFF TAIL LEFT

 (c)  
11H18, FLT CONT SHUTOFF TAIL CTR

 (d)  
11H28, FLT CONT SHUTOFF TAIL RIGHT

 (e)  
11C6, CSEU 1L AC
 or FLT CONT ELEC 1L AC

 (f)  
11C7, CSEU 1L DC
 or FLT CONT ELEC 1L DC

 (g)  
11C8, CSEU 2L AC
 or FLT CONT ELEC 2L AC
　
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(59)