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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
SEE E
UPPER RUDDER
UPPER RUDDER FRONT SPAR
POWER CONTROL
UPPER ACTUATOR
UPPER RUDDER
POWER CONTROL
CENTER ACTUATOR
UPPER RUDDER
UPPER RUDDER POWER CONTROL
RATIO CHANGER MODULE
SEE F
UPPER RUDDER
POWER CONTROL
LOWER ACTUATOR
INPUT CONTROL ROD
RUDDER TRIM
ACTUATOR
FEEL,TRIM,AND
RUDDER AFT CENTERING MECHANISM
QUADRANT
RB CABLE
SERVO
UNIT
TO POWER RA CABLE
CONTROL MODULE CHANGER RATIO RUDDER LOWER RUDDER LOWER RUDDER FRONT SPAR
POWER CONTROL
UPPER ACTUATOR
LOWER RUDDER
POWER CONTROL
LOWER RUDDER MODULE
INPUT RATIO CHANGER
OUTPUT CRANK SEE F
CRANK RATIO CHANGER TRUNNION LOWER ACTUATOR POWER CONTROL LOWER RUDDER
F E
Rudder Control System Component Location
Figure 2 (Sheet 3)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
FIBERGLASS HONEYCOMB
VERTICAL STABILIZER
SEE B
RUDDER HINGE NO. 11
RUDDER HINGE NO. 10 UPPER RUDDER
SEE A
POWER CONTROL PACKAGE RUDDER HINGE NO. 9
SEE C
RUDDER HINGE POSITION UPPER RUDDER
NO. 8 TRANSMITTER RUDDER HINGE NO. 7
6.5`-7.7` UPPER AND LOWER RUDDER FULL PEDAL HIGH RUDDER HINGE SPEED 367 KNOTS NO. 6
RUDDER HINGE NO. 5
A
31`-32` UPPER
AND LOWER RUDDER
LOWER RUDDER
FULL PEDAL
POSITION
25.2` TRANSMITTER
LOW SPEED FIBERGLASS
FULL RUDDER TRIM HONEYCOMB
RUDDER HINGE NO. 4
RUDDER HINGE NO. 3LOWER RUDDER POWER CONTROL PACKAGE RUDDER HINGE NO. 2
RUDDER HINGE NO. 1
LEFT HAND TRAVEL SHOWN RIGHT HAND TRAVEL OPPOSITE CB
Rudders - Mechanism Components
Figure 3
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
B. The adjustment crank is located on the instrument panel forward of the control wheel. It is connected to a flexshaft routed forward under the instrument panel, then down under the floor, to the rudder control jackshaft assembly. Rotation of the rudder pedal adjustment crank, actuates the jackscrew containing the pedal adjustment nut, which causes the yoke to move fore and aft.
5. Rudder Forward Quadrant
_______________________
A. The forward quadrant transmits motion from the captain's and first officer's rudder pedals to the rudder control cables. Captain's and first officer's forward quadrants are linked together at the forward end by a bus rod.
6. Rudder Aft Control Quadrant
___________________________
A. The rudder aft control quadrant conveys the motion of the rudder control cables to the feel and centering mechanism. The assembly consists of a quadrant and control crank which are bolted to a shaft. The shaft is mounted horizontally in the vertical stabilizer.
B. Quadrant shaft rotation transmits motion to the control crank. The control crank pushes or pulls the input rod to the feel and centering mechanism. The centering springs, attached to the rudder centering and feel assembly, positions the quadrant back to the trimmed position when there is no pressure on the rudder pedal.
7. Rudder Trim Control Mechanism
_____________________________
A. The rudder trim control mechanism provides a means for controlling the directional trim of the airplane and indicates the units of rudder trim. The control mechanism consists of rudder trim switch and indicator on the aft end of the control stand.
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