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protection. Variable pitch artificial feel is
provided to vary the load on the elevator control wheel as a function of airspeed and horizontal trim
setting.
Yaw control is provided by means of three hydraulic PCUs to power the rudder. Rudder travel limiting
as a function of airspeed is provided to limit loads on the structure. The rudder system uses dual
cable circuits (aft fuselage) to protect the system from effects of engine rotor burst.
FLIGHT CONTROLS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−5
AILERON CONTROL
Lateral (roll) control is provided by ailerons operating in relation to control wheel displacement and
controlled via control rods, cable runs and quadrants. The ailerons are assisted by four multifunction
spoilers per wing, which are electrically controlled.
Aileron Control General Arrangement
ROLL CONTROL
ROLL DISCONNECT
MECHANISM
FORWARD
QUADRANT
TORQUE
TUBE
POWER
CONTROL
UNIT
AFT QUADRANT
AILERON
TRIM
ACTUATOR
CONTROL CABLES
AUTOPILOT
SERVO
MULTI−FUNCTION
FEEL UNIT
TRANSDUCER
SPOILER (REFERENCE)
AFT QUADRANT
FEEL UNIT
GF1010_006
Aileron Control System
Two separate lateral control systems are provided: the pilot’s side operates the lefthand
aileron
and the copilot’s side operates the righthand
aileron.
Normally, both control systems are interconnected through the forward torque tube interconnect
assembly and there is simultaneous movement of both ailerons.
FLIGHT CONTROLS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−6
AILERON CONTROL (CONT'D)
Aileron Control System Operation
The pilot and copilot roll controls are interconnected through a roll disconnect mechanism used to
maintain the control wheels connected, until a design torque is developed across the mechanism.
A jammed aileron control circuit can be isolated through automatic activation of the roll disconnect
mechanism. This procedure will allow limited lateral control using one aileron and all multifunction
spoilers through the operable control circuit.
NOTE
The Automatic Flight Control System (AFCS) should be
disconnected if a jammed aileron control circuit condition occurs.
A transducer is mounted at the outboard end of each torque tube assembly (forward quadrant).
They provide the roll command inputs to the multifunctional
spoilers system for roll assist.
Rotating either control wheel provides an input (via cables and pulleys) to the aileron forward
quadrant which directs the control cable to the aft quadrant.
Each aft quadrant has an artificial feel and centering unit. An aileron trim unit is installed with input
to each aft quadrant and provides trim input to the aileron control system.
A separate cable circuit is provided for the autopilot servo motor (controlled by the AFCS)
assembly which inputs the right aft quadrant.
Disconnecting the autopilot by the pilot overpowering the aileron servo will not cause the auto roll
disconnect system to separate the control wheels.
NOTE
Overpowering the aileron servo to disconnect the autopilot is not
recommended.
The control cables from the aft quadrant continue outboard to the hydraulically driven PCUs. There
are two PCUs for each aileron control surface.
FLIGHT CONTROLS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−7
AILERON CONTROL (CONT'D)
Aileron Surface Position Indication
Left and right aileron positions are displayed by a moving pointer on the EICAS flight controls
page. Separate pointers indicate the aileron surface position on each wing.
Scale Pointer
Unfilled triangle moves vertically
to indicate the range of travel.
The surface position pointer will
change color (green or amber)
based on hydraulic pressure
availability.
Scale
Indicates the full range available
for aileron up and down travel.
Surface Outline
The surface outline has no
movement. It will change
color, (magenta, green or
amber) based on electrical
power (ie: battery only or all
busses powered) and
hydraulic pressure availability.
GF1010_007a
FLAP
SLATIN
0
ELEV ELEV
RUDDER
AIL AIL
FLIGHT CONTROLS
SCALE LONG TICK MARKS SHORT TICK MARKS
Left side −25° (top)
+21.5° (bottom)
at top and bottom at 0°
Right side +25° (top)
　
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