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A
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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