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FLIGHT CONTROL POSITION INDICATORS

STABILIZER TRIM AILERON TRIM POSITION INDICATORS POSITION INDICATOR
(2) (P10) (CONTROL WHEEL)
Flight Deck Flight Control Indicators
Figure 13

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 (b)  
Rudder trim position is on the aft electronic control panel P8. The indicator is electrically driven by position transmitters at the rudder.

 (c)  
Aileron trim is indicated on top of the hub of each control wheel. Trim is indicated by the physical offset of the control wheel.

 (2)  
Aileron and Rudder Trim Switches

 (a)  
Aileron and rudder trim switches are on the aft section of the control stand (P8). The aileron trim switches (2) are spring loaded to the center position. When both are held toward LEFT WING DOWN or RIGHT WING DOWN, they activate arm and control signals that cause the ailerons to be trimmed.

 (b)  
The rudder trim switch is a single rotary switch spring loaded to the center position. When held toward NOSE LEFT or NOSE RIGHT, it activates signals that cause the rudder to be trimmed.

 (c)  
The switches cause trim motors to move cam/roller mechanisms. These change the center position of the control system.

 (3)  
Flight Control Position Indicators

 (a)  The flight control position indicators are on the lower EICAS display unit when the status page is selected (Ref 31-41-00). The pointers indicate the position of each aileron (2), elevator (2), and rudder (1). A position transmitter at each of the following control surfaces drives the corresponding pointer on the indicators: 1) Left aileron 2) Right aileron 3) Left elevator 4) Right elevator 5) Rudder
 O. Flight Control System Electronics (Fig. 14)
 (1)  The two Control System Electronic Units (CSEU) consist of 8 separate modules in the left system and 8 separate modules in the right system (Ref Chapter 27). The modules are on the electronic equipment racks in the main electrical/electronics equipment compartment.
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MAINTENANCE MANUAL

Flight Control System Electronics
Figure 14

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 (2)  
The modules drive flight control actuators and stabilizer trim control modules. Sensor inputs are from electrical, mechanical, and information (as shown) systems. The CSEU modules act as buffers for inputs, define required control movements, and then modify and program the inputs to provide the output command signal.

 (3)  
The two power supplies provide power monitoring and necessary voltages for each module.

 (4)  
The stabilizer trim and elevator asymmetry limit module (SAM) processes autopilot automatic trim signals, manual electric trim signals, and drives the stabilizer to relieve elevator loads and maintain pitch authority.

 (5)  
The rudder ratio changer module increases rudder travel limits as airspeed is reduced. This maintains rudder authority at low airspeeds.
　
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