747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(149)

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 a)  Place FLT CONTROLS HYD POWER TAIL system switches No. 2
 and 4 on panel P461 to SHUTOFF position.
 b)  Open ELEV RUD circuit breakers SYS 2 and 4 on panel
 P180.
 c)  Loosen the check nuts on both end of the input rod for
 the power control module and remove the bolt that
 connect the aft end of the rod to the power control
 package.
 d)  Rotate the input rod until the rudder trailing edge
 falls within the width of the index tab.
 NOTE: One half turn of the rod and the free rod end is____
 equivalent to 1.56 inches (39.62 mm) of travel
 at the rudder trailing edge. Lengthen the rod
 to move rudder right and shorten to move rudder
 left.
 e)  Re-connect the input rod and tighten the outer bolt
 first to 50-65 pound-inches (5.67 nm - 7.37 nm) plus
 run-on torgue. Tighten the inner nut to 12 to 15
 pound-inches (1.36 nm - 1.70 nm) plus run-on torque.
 Do not reset outer bolt.
 NOTE: Run-on torque is torque measured prior to actual____
 outer bolt contact with clevis or inner nut
 contact with end of outer bolt.
 f)  Close circuit breakers for ELEV RUD systems No. 2 and 4
 on panel P180.
 g)  Place FLT CONTROLS HYD POWER TAIL switches No. 2 and 4
 on panel P461 to NORM position.
 h)  Recheck rudder neutral position and re-adjust as
 necessary.
 i)  Tighten both check nuts on the input rod.

Inspect both rod ends for proper thread engagement. Rod end threads must be visible through inspection holes in rod. No more than 10 threads at each end may be visible beyond checknut.
 NOTE: INCORRECT THREAD ENGAGEMENT MAY EFFECT SECURITY OF
____ ROD
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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747-400
MAINTENANCE MANUAL

 S 225-053
 (5)
Remove the DO-NOT-CLOSE tag and close this circuit breaker:

 (a)  
P180 DC Power Distribution Panel
 1) 180J12 GND PWR SENSE

 

 S 095-012
 (6)  
Remove the rig pins, R-4, and E-2.

 S 865-034

 (7)  
Use the rudder pedals to move the rudder to its fully left position.

 CAUTION:_______MAKE SURE THE ROD ENDS ARE ALIGNED CORRECTLY. IF THE ROD ENDS ARE NOT ALIGNED CORRECTLY, THE BEARINGS IN THEM WILL NOT HAVE SUFFICIENT TRAVEL. THIS CAN CAUSE DAMAGE TO THE ROD AND OTHER PARTS.
 (a)  Make sure the rod end bearings move as freely as possible.
 S 095-014
 WARNING:_______MAKE SURE THE NOSE LANDING GEAR IS POINTED FORWARD. IF THE TIRES ARE NOT PARALLEL WITH THE AIRPLANE, THEY CAN TURN QUICKLY WHEN YOU REMOVE THE TOW PIN. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
 (8)  
Remove the TOW PIN from the nose landing gear (Ref 09-11-00/201).

 S 715-015

 (9)  
Do the task to do a test of the power control actuator for the lower rudder.

 TASK 27-21-16-715-016
 3.  Lower Rudder Power Control Actuator Test________________________________________
 A. References
 (1)  
06-09-05/201, Body Section 48 Access Doors and Panels

 (2)  
06-09-07/201, Fin and Rudder Access Doors and Panels

 (3)  
09-11-00/201, Towing

 (4)  
12-12-01/301, Hydraulic Systems

 (5)  
24-22-00/201, Manual Control

 (6)  
29-11-00/201, Main Hydraulic Supply System

 (7)  
31-61-00/201, Integrated Display System

 B.
Access

 (1)  
Location Zone 324 Vertical Fin, Rear Spar to Trailing Edge 325 Lower Rudder

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 ALL  ú ú 02 Page 508 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

　
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