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The aileron trim tab has ±20 degrees of travel with respect to the aileron surface. The aileron trim switches consist of a single unit containing a split-pole-four throw toggle button (left and right for aileron trim and up and down for horizontal stabilizer trim) and a single-pole single-throw push button to arm. To activate aileron trim, the button must be pressed down and simultaneously pushed left or right.
The CONFIG AILERON TRIM (W) CAS message illuminates if takeoff is attempted with the aileron trim not within the takeoff trim band.
RUDDER TRIM
Rudder trim is provided through an electromechanical rudder trim actuator. Rudder trim is activated by the flight crew by means of a RUD TRIM switch on the pedestal. Trimming of the rudder is done directly with the rudder surface. There are no trim tabs on the rudder. Activation of the RUD TRIM switch causes electrical inputs to the rudder power control units that move the rudder to the position selected by the pilot. A CONFIG RUDDER TRIM (W) CAS will also be illuminated if not properly configured for takeoff.
CFO1002002_006
HORIZONTAL STABILIZER TRIM
The stabilizer trim controls pitch trim by varying the horizontal stabilizers angle of incidence. The stabilizers are positioned by a jack screw driven by electric motors and controlled by the horizontal stabilizer trim control unit. Each trim motor has a brake to prevent trim runaway. The trim control unit receives inputs from the control wheel trim switches, the autopilot (AFCS), flaps (FCU) and Mach (ADC).
The stabilizer trim position indicator and readout is displayed on the EICAS and the FLIGHT CONTROLS synoptic page. The digital readout indicates the stabilizer position in units of trim, which corresponds to horizontal stabilizer angle of in-cidence. The stab trim range of movement is 0 to 15 degrees, with the normal takeoff range of 2.5 to 8.0 units (green).
A CONFIG STAB TRIM (W) CAS will be displayed if the stabilizer trim is not in normal takeoff range.
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
10-02-02 SECONDARY FLIGHT CONTROLS (Cont) HORIZONTAL STABILIZER TRIM
The stabilizer trim can be moved manually by control wheel trim switches or automatically via computer-controlled inputs from the autopilot, spoilers, or flaps.
Manual trim rates differ, depending on which channel is engaged. When the primary channel is engaged, the trim rate is a function of airspeed (mach). When the pitch trim secondary channel is engaged, the trim rate is a constant 0.2 degrees per second.
The primary channel trim rate limit is 0.4 degrees/second at airspeeds up to Mach 0.4, decreasing linearly to 0.1 degrees/ second at Mach 0.8, and 0.1 degrees/second above Mach 0.8. If Mach data is not available, the trim rate limit defaults to
0.2 degrees/second.
CONFIGURATION TRIM
The aircraft has configuration trim, which is automatic trim movement when the flaps are extended or retracted and the spoilers are extended or retracted. The aircraft has a nose down pitching moment with flap extension and nose up pitching moment with spoiler extension. When these control surfaces are deflected, the horizontal stabilizer trim moves so as to reduce the control column forces.
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