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747-400 MAINTENANCE MANUAL
2) Make sure the flight controls maintenance page of EICAS shows that the rudders are at 31.5 +/-1.5 degrees.
(b) Push the captain's right rudder pedal fully forward and hold it. 1) Make sure the rudder position indicators on the status page
of EICAS show the rudders are fully right (the pointers are right of the third ten degree mark). 2) Make sure the flight controls maintenance page of EICAS shows that the rudders are at 31.5 +/-1.5 degrees.
S 715-052
(4)
(High speed test) do one of the two subsequent procedures, to give high-speed rudder ratio changer position (extend).
(a)
Procedure 1 (for airplanes with two SRM's P/N 285U0015-108 or later), see procedure 1 (Ref 27-21-00/524).
WARNING:_______MAKE SURE THE FLAPS ARE RETRACTED. IF THE FLAPS ARE NOT RETRACTED, THEY CAN MOVE WHEN YOU PRESSURIZE THE PITOT-STATIC SYSTEM. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(b)
Procedure 2 (airplanes with any combination of SRM part numbers installed), supply a 3.37-3.52 psig pressure (363-371 knots) to the pitot port of the top right and the top left pitot probes (Ref 34-11-00/201).
(c)
Push the captain's left rudder pedal fully forward and hold it. 1) Make sure the rudder position indicators on the status page of EICAS shows the rudders moved left.
2) Make sure the flight controls maintenance page of EICAS shows that the rudders are at 6-8 degrees.
(d)
Push the captain's right rudder pedal fully forward and hold it. 1) Make sure the rudder position indicators on the status page
of EICAS show the rudders moved right. 2) Make sure the flight controls maintenance page of EICAS shows that the rudders are at 6-8 degrees.
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(e)
If procedure 1 was used to extend the actuator, push the LSK that is adjacent to END TEST> on the CDU.
(f)
If procedure 2 was used to extend the actuator, slowly release the pressure from the pitot static system (Ref 34-11-00/201).
(g)
Do the procedure to reactivate the trailing edge flaps (Ref 27-51-00/201).
G.
Put the Airplane Back to Its Usual Condition
S 095-059
(1) Remove rig pin E-2 from the bottom of the elevator aft quadrant.
S 095-069
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.
(2)
Remove the TOW PIN from the nose landing gear (Ref 32-50-00/201).
S 865-061
(3)
Remove hydraulic power (Ref 29-11-00/201).
(4)
Close the access doors and the access panels.
(5)
Remove electrical power if it is not necessary (Ref 24-22-00/201).
S 415-063
S 865-064
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747-400 MAINTENANCE MANUAL
UPPER RUDDER POWER CONTROL ACTUATOR - REMOVAL/INSTALLATION
__________________________________________________________
1. General_______
A. There are eight tasks in this procedure. There is a task for the removal and a task for the installation of the upper, center and lower power control actuators (referred to as the actuators or as the PCAs) of the power control package (PCP) for the upper rudder. The other two tasks are to prepare for the removal, and to put the airplane back to its usual condition.
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