(30). 2) Tighten the bolt (27) to 50-65 pound-inches. 3) Tighten the nut (30) to 10-15 pound-inches plus the run-on
torque.
NOTE: Make sure you do not change the length of the input
____ control rod during the installation of the PCM.
(e)
Apply assembly lube to all of the hydraulic fittings.
(f)
Remove the caps and connect the hydraulic lines to the PCM.
(g)
Install the hydraulic lines that you removed to get access for the removal of the PCM.
(h)
If you install the lower rudder PCM (5), connect the jumper (33) to the lower rudder PCM (5).
(i)
Connect the electrical connector DM8004 or DM8005 to the PCM.
S 092-019
(2)
Remove the rig pin R-4 from the rudder feel, centering, and trim mechanism.
S 862-021
(3)
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a)
P180 DC Power Distribution Panel
1) 180E7 ELEV/RUD VLV SYS 2
2) 180E22 ELEV/RUD VLV SYS 4
3) 180H8 ELEV/RUD VLV SYS 1
4) 180H23 ELEV/RUD VLV SYS 3
S 862-022
(4) Set the FLT CONTROL HYD POWER TAIL switches on the P461 Pilot's Overhead Maintenance Panel to NORM.
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A
747-400 MAINTENANCE MANUAL
S 092-024
(5)
Remove the rudder clamps.
G.
Do a Test of the Rudder Power Control Module
S 862-078
(1)
Make sure the rudder is in the neutral position.
S 222-026
(2)
Make sure the servo units of the rudder ratio changers are fully retracted.
NOTE: The servo units are 5.202-5.212 inches long, between the
____ centers of the mounting points, when they are retracted.
S 862-079
(3)
Supply hydraulic power to the four hydraulic systems
(Ref 29-11-00/201).
S 862-027
(4)
Push the captain's left rudder pedal fully forward and hold it there.
S 222-028
(5)
Make sure the flight controls maintenance page of EICAS shows the rudders are at 31.5 +/- 1.5 degrees.
S 792-029
(6)
Make sure there are no leaks at the hydraulic connections.
S 862-030
(7)
Push the captain's right rudder pedal fully forward and hold it there.
S 222-031
(8)
Make sure the flight controls maintenance page of EICAS shows the rudders are at 31.5 +/- 1.5 degrees.
(9)
Make sure there are no leaks at the hydraulic connections.
S 712-033
(10)
Do the operational test for the yaw damper system
(Ref 22-21-00/501).
H.
Put the Airplane Back to Its Usual Condition
(1)
Remove the rig pin, E-2, from the elevator aft torque tube.
S 792-032
S 092-034
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747-400 MAINTENANCE MANUAL
S 092-035
WARNING:_______MAKE SURE THE NOSE WHEELS POINT FORWARD. IF THE NOSE WHEELS DO NOT POINT FORWARD, THE NOSE GEAR CAN QUICKLY TURN TO THE CENTER POSITION WHEN YOU REMOVE THE TOW PIN. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(2)
Remove the TOW PIN from the nose landing gear (Ref 09-11-00/201).
S 642-036
(3)
If it is necessary, fill the hydraulic reservoirs
(Ref 12-12-01/301).
S 862-038
(4)
Remove electrical power if it is not necessary (Ref 24-22-00/201).
S 862-039
(5)
Remove the hydraulic power (Ref 29-11-00/201).
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本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(154)
