FLIGHT CONTROLS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 10-02-01
SECONDARY FLIGHT CONTROLS
DESCRIPTION
Secondary flight controls include flaps, multifunction spoilers, ground spoilers, aileron, rudder, and horizontal stabilizer
trims. Flaps are electrically controlled and hydraulically actuated. Horizontal stabilizer, aileron, and rudder trims are electrically
operated. The multifunction spoilers and ground spoilers are operated hydraulically but controlled via electrical signals
generated by the SECU. Position indicators for the secondary control surfaces are located on the MFD and the FLIGHT
CONTROLS synoptic page.
CFO1001002_004
MULTI-FUNCTION
SPOILERS
GROUND
SPOILERS
SINGLE
FOWLER
FLAP
AILERON
TRIM
HORIZONTAL
STABILIZER
REV 1
FLIGHT CONTROLS
Volume 2 Flight Crew Operating Manual Sep 13/2004
10-02-02 CSP 100-6 REV 1
SECONDARY FLIGHT CONTROLS (Cont)
COMPONENTS AND OPERATION
AILERON TRIM
Aileron trim is achieved by means of an aileron trim tab located on the left aileron. The trim tab is moved by an electromechanical
actuator located in the left aileron. The trim actuator is activated by movement of the aileron trim switches on
the pilot and copilot’s control wheels.
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.
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 incidence.
The stab trim range of movement is 0 to 15 degrees, with the normal takeoff range of 2.5 to 8.0 units (green).
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