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The pilot moves the control wheels to operate these surfaces.
Below is a typical right turn input and how the lateral system
operates.
Neutral Position
When the aileron control wheels are in the neutral position, the
aileron trim indicator on top of the control wheel shows the
amount of aileron trim.
The feel and centering unit is balanced. The roller stays in the
bottom of the cam and the springs are not extended.
The aileron PCUs input cranks are at neutral. There is no
hydraulic input to the PCU.
Right Roll Control Input
To roll right, the captain turns the control wheel clockwise. This
will also move the bus drum at the first officer’s column within
the limit of the lost motion device.
The aileron control cables move the roller to roll up on the cam
of the feel and centering unit. The springs extend and resist the
input force to supply the feel force.
The cables also move the input rod. This moves the input
cranks in the aileron PCUs. Now hydraulic pressure goes to the
PCU.
Control Input Complete
Hydraulic pressure pushes the PCU housing to move left. This
moves the aileron body quadrants counterclockwise. Wing
cable tension moves the ailerons.
When the aileron PCU housing moves, it also causes the aileron
spring cartridge to move left. This moves the spoiler input rod
and the right body cables. This centers the lost motion device in
the transfer mechanism.
When the spoiler input rod moves, it gives an input to the spoiler
mixer to control the position of the flight spoilers.
Manual Operation
If hydraulic pressure is OFF, the control sequence is the same
as described above.
AILERON AND AILERON TRIM CONTROL SYSTEM - AILERON OPERATION
EFFECTIVITY
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AILERON AND AILERON TRIM CONTROL SYSTEM - AILERON OPERATION
AILERON AND AILERON TRIM CONTROL SYSTEM - AILERON OPERATION
EFFECTIVITY
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
Purpose
The rudder controls the flight attitude of the airplane about the
vertical axis.
Location
The rudder hinges aft of the rear spar of the vertical stabilizer.
Yaw control
The pilots manually command a yaw input with the rudder
pedals. When engaged, the yaw damper automatically makes
small yaw corrections. During yaw damper operation, there is
no feedback to the rudder pedals.
Abbreviations and Acronyms
* ac - alternating current
* auth - authority
* FDAU - flight data acquisition unit
* EHSV - electrohydraulic servo valve
* FSEU - flap/slat electronic unit
* Hz - Hertz
* LVDT - linear variable differential transformer
* PCU - power control unit
* SMYD - stall management yaw damper
* soln - solenoid
* v - Volt
* vlv - valve
* WTRIS - wheel-to-rudder interconnect system
RUDDER AND RUDDER TRIM CONTROL SYSTEM - INTRODUCTION
EFFECTIVITY
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RUDDER AND RUDDER TRIM CONTROL SYSTEM - INTRODUCTION
RUDDER AND RUDDER TRIM CONTROL SYSTEM - INTRODUCTION
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RUDDER AND RUDDER TRIM CONTROL SYSTEM - INTRODUCTION
RUDDER AND RUDDER TRIM CONTROL SYSTEM - INTRODUCTION
EFFECTIVITY
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General
The pilot uses the rudder pedals or the rudder trim control knob
to control the rudder. The yaw damper and wheel-to-rudder
interconnect system automatically control the rudder.
Manual Operation - Rudder Pedals
The flight crew uses the rudder pedals to control the rudder
　
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