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747-400 FAULT ISOLATION/MAINT MANUAL
UPPER RUDDER UPPER ACTUATOR UPPER RUDDER
FRONT SPAR
UPPER RUDDER CENTER ACTUATOR
UPPER RUDDER UPPER RUDDER
RATIO CHANGER POWER CONTROL
M560 MODULE
SEE F SHT 4
UPPER RUDDER
LOWER ACTUATOR
RUDDER TRIM ACTUATOR, M7878
FEEL,TRIM,AND RUDDER AFT
CENTERING MECHANISM QUADRANT
RB CABLE
RA CABLE
LOWER RUDDER UPPER ACTUATOR LOWER RUDDER FRONT SPAR
LOWER RUDDER POWER CONTROL MODULE
LOWER RUDDER RATIO CHANGER M258
SEE F SHT 4
LOWER RUDDER LOWER ACTUATOR
E FROM SHEET 2
Rudder - Component Location Figure 102 (Sheet 3)
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747-400
FAULT ISOLATION/MAINT MANUAL
SERVO UNIT
M258 LOWER
M560 UPPER
UPPER, LOWER
RUDDER RATIO
CHANGER
M258, M560
TO POWER INPUT CRANK
CONTROL
MODULE
OUTPUT
CRANK
RATIO
CHANGER UPPER RUDDER
TRUNNION
F FROM SHT 3
UPPER, LOWER
RUDDER POSITION
TRANSMITTERS,
T490, T491
SEE G
RUDDER
POSITION
TRANSMITTERS
T490, T491
B
LOWER RUDDER
Rudder - Component Location Figure 102 (Sheet 4)
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747-400
FAULT ISOLATION/MAINT MANUAL
RUDDER & ELEVATOR HYDRAULIC SYSTEM 4 SHUTOFF VALVE, V150
SEE H
RUDDER & ELEVATOR HYDRAULIC SYSTEM 3 SHUTOFF VALVE, V147
SEE H RUDDER & ELEVATOR HYDRAULIC SYSTEM 1 SHUTOFF VALVE, V142
SEE H
RUDDER & ELEVATOR HYDRAULIC SYSTEM 2 SHUTOFF VALVE, V143
SEE H
HYDRAULIC LINES (REF)
RUDDER & ELEVATOR HYDRAULIC SHUTOFF VALVE
(4 PLACES TYPICAL)
V142 (SYSTEM 1)
V143 (SYSTEM 2)
V147 (SYSTEM 3)
V150 (SYSTEM 4)
H
Rudder - Component Location
Figure 102 (Sheet 5)
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747-400 MAINTENANCE MANUAL
RUDDER AND RUDDER TRIM CONTROL SYSTEM - DESCRIPTION AND OPERATION
_________________________________________________________________
1. General_______
A. Two independently supported and operated rudders without tabs provide yaw control of the airplane. Each rudder is positioned by a hydraulically operated power control package (PCP). The upper PCP consists of three power control actuators (PCAs) and a power control module (PCM). The lower PCP consists of two PCAs, and a PCM. Hydraulic power for the two PCP is provided by No. 1, 2, 3 and 4 airplane hydraulic systems. Systems No. 1 and 3 supply the upper rudder PCP; systems No. 2 and 4 supply the lower rudder PCP.
B. The rudder control system is operated by rudder pedal inputs at the captain and first officer positions. The rudder pedals operate a forward quadrant through linkage. The forward quadrant is connected by cables to the aft quadrant, which is linked to a feel and centering mechanism. The feel and centering mechanism is connected by linkage to two rudder ratio changers (RRCs). Each RRC is linked to the summing lever of a hydraulically operated PCM.
C. Rudder trim is provided by means of a rudder trim control switch located in the rear portion of the control stand. The rudder control switch is connected electrically to the rudder trim actuator. The rudder trim actuator controls the feel and centering mechanism null position. Linkage common to the rudder control system connects the rudder trim system to the power control module.
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