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−21.5° (bottom)
at top and bottom at 0°
FLIGHT CONTROLS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−8
AILERON CONTROL (CONT'D)
Aileron Trim
Aileron trim is accomplished by selecting the AIL TRIM switches on the trim control panel
(pedestal) in the desired direction. Actuating both switches provides arming and direction signals
to reposition the ailerons through the use of a trim actuator. Hydraulic power is necessary to set
aileron trim. Aileron trim position is displayed on PRIMARY page, along with the allowable takeoff
green band.
A “CONFIG AIL TRIM” red warning message is accompanied by a “NO TAKEOFF”
aural warning.
It is displayed during the takeoff
roll if the aileron trim is set outside the allowable takeoff
range.
LWD RWD
TRIMS
AIL
Trim Scales
Aileron trim range for left wing down,
centre and right wing down indications.
− Left wing down.
− Right wing down.
Pointer
Pivots about the centre dot and
indicates the trim setting.
Green Band (takeoff)
Replaces the centre tick mark.
White if it is not in the green
band.
Aileron Trim Switch
Located on the trim control
panel (centre pedestal).
Spring loaded split switches
requires both to be selected
in the same direction. Push
both switches full left or right
to activate the trim.
GF1010_009
LWD
RWD
TRIMS
L
AIL
WD
RWD
SCALE LONG TICK MARKS SHORT TICK
MARKS
Left side + 100% (bottom)
− 100% (top)
± 100% ± 50% and 0%
Right side + 100% (top)
− 100% (bottom)
± 100% ± 50% and 0%
Centre
position
− 0%
GREEN BAND CENTRE TICK MARK
± 14% Replaced by the green band −
FLIGHT CONTROLS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−9
AILERON CONTROL (CONT'D)
Aileron Control Schematic
TRIM ACTUATOR
TRIM POSITION
TO EICAS
ROLL
COMMANDS
LEFT AILERON
(POSITION TO EICAS
FLIGHT CONTROLS PAGE)
1
2
3
4
1
2
3
4
Trim motor
ROLL DISCONNECT SWITCH
ROLL
COMMANDS
POWER
UNIT
CONTROL
NO TAKEOFF
CONFIGURATION WARNING
CONFIG AIL TRIM
AIL
RIGHT AILERON
(POSITION TO
AFCS)
LEGEND
Electrical input
Cable input
Mechanical input
GF1010_011
FCUs
GEAR
OUT
30
DN DN DN
ND
STAB
NU
NL RUDDER
LWD RWD
NR
TRIMS
7.2
AIL
TRIMS
L
AIL
WD
RWD
MULTIFUNCTION
SPOILERS
AUTOPILOT
INPUT
FLIGHT CONTROLS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−10
RUDDER CONTROL
Directional control about the yaw axis is provided by the rudder control system. The rudder is
hydraulically powered through displacement of either pilot’s rudder pedals and controlled via control
rods, cable runs and quadrants.
Rudder Control General Arrangement
DUAL PATH SPLIT
QUADRANTS
CABLE
CIRCUIT
AFT
QUADRANT
YAW
DAMPER
RUDDER
TRIM
ACTUATOR
POWER CONTROL UNIT (PCU)
FORWARD
QUADRANT
SHAFT
ASSEMBLY
RUDDER
PEDAL
PEDAL
ASSEMBLY
RUDDER TRAVEL
LIMITER ACTUATOR
RUDDER FEEL
UNIT
ARTIFICIAL FEEL
LOAD
LIMITER
SUMMING
MECHANISM GF1010_012
Rudder Control System Operation
Each rudder pedal assembly uses an artificial feel unit and pedal input is transmitted via control
rods to the forward quadrant and shaft assembly. The cable system has a single path in the
fuselage and dualized in the rotor burst zone. The forward cable quadrant (one in each control
circuit) transmits the cable circuit to the aft quadrant. Artificial feel is provided by a linear spring
unit (rudder feel unit), connected to the aft quadrant.
Rudder input from the aft quadrant is received by a load limiting bungee (telescopic rod) which
protects the system from rapid inputs. The load limiter delivers pilot input to a summing
mechanism which adds the trim and yaw damping commands to the pilot commanded rudder
input.
Yaw dampers are used to improve the airplane’s lateral/directional stability and turn coordination.
　
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