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control switches A and B are in the standby rudder position, and
the yaw damper switch is on. When the WTRIS engages, the
solenoid valve moves. This sends pressure to the EHSV. When
the EHSV moves, it sends pressure to the yaw damper actuator.
The yaw damper actuator moves and applies pressure to one
chamber and opens the other to return. The standby rudder
PCU piston moves and moves the rudder.
See the wheel-to-rudder interconnect section for more
information. (SECTION 27-24)
RUDDER AND RUDDER TRIM CONTROL SYSTEM - STANDBY RUDDER PCU - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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RUDDER AND RUDDER TRIM CONTROL SYSTEM - STANDBY RUDDER PCU - FUNCTIONAL DESCRIPTION
RUDDER AND RUDDER TRIM CONTROL SYSTEM - STANDBY RUDDER PCU - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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Purpose
The rudder controls the flight attitude of the airplane about the
vertical axis.
Location
The rudder attaches at the trailing edge of the vertical stabilizer.
Physical Description
The rudder attaches to the vertical stabilizer with hinges. Two
PCUs attach to the rudder and move it.
Functional Description
The rudder has a maximum deflection of 29 degrees left and 29
degres right. Stops on the forward quadrant limit the input to the
rudder PCUs.
When the rudder moves, the rudder position transmitter sends
and signal to the flight data acquisition unit (FDAU).
See the flight data recorder system section for more
information. (SECTION 31-31)
RUDDER AND RUDDER TRIM CONTROL SYSTEM - RUDDER
EFFECTIVITY
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RUDDER AND RUDDER TRIM CONTROL SYSTEM - RUDDER
RUDDER AND RUDDER TRIM CONTROL SYSTEM - RUDDER
EFFECTIVITY
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27-21-00-009
General
The rudder control system uses cable input from the rudder
pedals.
Physical Description
The yaw control system has these components:
* Rudder pedals and forward quadrant
* RA and RB rudder control cables
* Aft quadrant and trim, feel and centering
* Hydraulic PCUs (2)
* Rudder.
Functional Description - Normal
When the pedals move, they move the rudder forward control
quadrants. This moves the RA and RB rudder control cables.
The cables move the rudder aft control quadrant and the PCUs.
The rudder PCUs pistons move and control the rudder position.
Functional Description - Electric Trim
During electric trim, the pilots move the rudder trim knob on the
aisle stand, this sends a signal to the rudder trim actuator. The
trim actuator moves the rudder feel and centering unit. This
moves the rudder PCU and the rudder pedals. The rudder PCUs
pistons move and control the rudder position.
RUDDER AND RUDDER TRIM CONTROL SYSTEM - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
27-21-00-010
RUDDER AND RUDDER TRIM CONTROL SYSTEM - FUNCTIONAL DESCRIPTION
RUDDER AND RUDDER TRIM CONTROL SYSTEM - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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27-21-00-010
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27-24-00
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
Purpose
The wheel to rudder interconnect system (WTRIS) assists turns
during flight control manual reversion operations when both
flight control A and B hydraulics are OFF, and the standby
system is ON. The WTRIS commands a small amount of rudder
movement as a function of the captain control wheel aileron
input to help turns.
　
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