BOMBARDIER BD-100-1A10, Operating Manual

Page: 284 / 544

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 electro-
mechanical 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 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.
OFF
SEC
OFF
SEC
TRIM
RUD
TRIM
L L
PRI
R
PRI
R
STAB STAB
C
FO
100
20
02
_0
06
CAS
CKLST
SKIP
FRMT
TFC
TR/WX ENTER SUMRY
A/ICE FUEL HYD
L R
ECS
ABV
ELEC FLT
COM1 NAV1 ATC1/TCAS ADF1
HF1
COM3
COM2
118.000 108.00
1799.5 118.000 118.000
118.000
118.000 2.0000
190.0 108.00 118.000
STBY
TX 2.0000 AM
25 25
1200
MFD CONTROL
FLIGHT CONTROLS
AILERON AILERON
ELEVATOR ELEVATOR
RUDDER
AUTO PLAN
SHLDR SIDE