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trim, the clacker will alert the crew. Unusual long periods of autopilot
trimming may indicate trim runaway. There is no trim-in-motion
clacker for any trim operation other than autopilot trim.
CAS Color Description
AP ELEV MISTRIM Amber Autopilot elevator servo holding excessive
torque.
Pilot’s Manual
5-20 PM-132A
PITCH TRIM BIAS
The pitch trim bias system works in conjunction with the up/down
spring assembly. Its function is to assist the pilot by providing added
spring pressure against the elevator in the event the horizontal stabilizer
is jammed in an out-of-trim position. Pitch trim bias is actuated by
the crew using the three-position (spring loaded to the center position)
PIT TRIM BIAS switch located at the front of the throttle quadrant.
Power for the system is provided through the PIT TRIM BIAS circuit
breaker on the copilot’s circuit breaker panel (FLIGHT group).
The following CAS illuminations are specific to the pitch trim bias.
CONFIGURATION TRIM
The configuration trim functions aid the pilot by providing automatic
relief of control column loads via the #1 IC control of horizontal stabilizer
position. The configuration trim system control and monitoring
functions are provided by software contained in the #1 IC using inputs
from spoiler lever position sensors. Through these interfaces, the configuration
trim provides automatic pitch control for changes in airplane
configuration. This mode is only functional when the trim selector
switch is in the PRI position and the autopilot is not engaged. Trim
commands from either control wheel trim switch will have priority
over the configuration trim commands.
CAS Color Description
PIT TRIM BIAS Red Abnormal PIT TRIM BIAS configuration with
the aircraft on the ground and either thrust
lever is advanced to MCR or above.
PIT TRIM BIAS White The pitch trim bias system is moved from the
normal position. PIT TRIM BIAS should only
be used for jammed stabilizer conditions in
flight.
Pilot’s Manual
PM-132A 5-21
AILERON TRIM
The aileron trim system provides manual aileron trim tab control. The
manual trim tab control system enables the pilot, with authority, and
the copilot to eliminate out-of-trim forces which may be present in the
aileron control circuit, preventing smooth operation of the control column.
This enables the airplane to be flown without either pilot having
to apply constant forces to the hand wheel to maintain the wing level.
The aileron trim system is controlled by a control wheel trim switch
mounted on the pilot and copilot’s control wheels (Figure 5-1) and incorporates
two switches, trim, and trim arm. To manually trim, the pilot
or copilot must press and hold the ARM button while pushing the
trim switch to the LWD or RWD position. The control wheel trim
switch induce inputs into the roll trim control electrical system which
translates commands to a rotary actuator mounted in the left aileron.
The actuator moves the aileron trim tab through dual push rods to the
command position. A trim tab position sensor is attached to the rotary
actuator shaft and provides input to the Data Acquisition Units (DAUs)
for display of aileron trim position on the cockpit Engine Indicating
and Crew Alerting System (EICAS). Driving the actuator clockwise
causes the trim tab to rise. This results in left aileron moving down and
the right aileron moving up. This results in the airplane performing a
Right Wing Down (RWD) movement. Conversely, driving the actuator
counterclockwise causes the trim tab to lower. This causes the left aileron
to move up and the right aileron to move down, resulting in the airplane
performing a Left Wing Down (LWD) movement.
Aileron trim is powered from the L ESS BUS and is protected by TRIMAIL
5-amp circuit breaker on the pilot’s circuit breaker panel (FLIGHT
group).
Pilot’s Manual
5-22 PM-132A
RUDDER TRIM
The rudder trim system provides manual rudder trim tab control. The
manual trim control system enables the pilot and copilot to eliminate
out-of trim forces which may be present in the rudder control circuit.
This enables the airplane to be flown without either pilot having to
apply a constant force to the rudder pedals.
Rudder trim changes are effected through an electronically driven rotary
actuator mounted in the rudder and connected to the rudder trim tab
with dual pushrods. The actuator is controlled manually by a doublepole,
double-throw, center-off, momentary-action, rotary switch located
on the trim switch panel (Figure 5-4) in the center pedestal. This
switch is constructed in two sections with poles that are not mechanically
　
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