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aileron chord line. It consists of a constant length push rod hinged at both ends on brackets rigidly mounted on the wing at
one end and on the balance tab at the other end. The mechanism acts as a linkage with the aileron surface being the driving
link and the geared balance tab being the driven link. The aileron balance tab is geared to move in the opposite direction
of its corresponding ailerons movement. A roll damper is mounted on the pilot control column. Under normal operation,
the roll damper acts like a quadrant and transmits all of the crew member’s inputs. In case of any one aileron cable failure,
the roll damper limits the rate the control wheel deflects (driving the roll spoilers) to a recoverable level. To prevent damage
to the aileron surfaces from wind gusts when the aircraft is parked, a gust lock mechanism is incorporated to lock the left
drive quadrant in the neutral position. The mechanism is actuated by the crew, via a telescoping gust lock lever mounted
in the throttle quadrant. The lever moves a cable, that engages a spring loaded pawl into a quadrant mounted cam recess.
When the gust lock is engaged, the throttles are physically prevented from being moved above idle. Aileron position is displayed
on the EICAS FLIGHT CONTROL synoptic page. A full-scale deflection of the AIL position indicator corresponds
to maximum aileron deflection.
4
FLIGHT CONTROLS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 10-01-03
PRIMARY FLIGHT CONTROLS (Cont)
ROLL DISCONNECT
The roll disconnect allows the flight crew to isolate the left control wheel from the aileron control system. The roll disconnect
mechanism is mounted on the left control wheel. It is comprised of a lever, a shaft, a stud roller, a cam, and two torsion
springs. The lever and the shaft are held in axial alignment by two bushings.
During normal operation, the roller position is held into the cam detent by the torsion springs, allowing the pilot control
wheel and the input quadrant to rotate as one single unit.
In the event of a jam in the mechanical circuit, the pilot can disconnect from the aileron circuit and retain roll control
through the multifunction spoilers. However, if a jam occurs in the pilot control wheel, the pilot can disconnect from the
circuit thus permitting the copilot to retain control of the ailerons.
A pull of the roll disconnect mechanism lever retracts the roller which is held in the disconnect position by a spring-loaded
hook. This action uncouples the pilot control wheel and the pilot input quadrant and allows the control wheel to
rotate freely. This disconnect feature allows in-flight reset once the roller and the cam are realigned and the disconnect lever
is released. A microswitch senses the retraction of the roller and sends a signal of the disconnect status and a
ROLL DISCONNECT (W) CAS message will be illuminated.
RUDDER
RUDDER CONTROL SYSTEM
The rudder provides directional control about the yaw axis. The system is mechanically controlled and hydraulically powered.
The mechanical part of the system has control pedals, levers, pulleys and cables which connect to two hydraulic power
control units (PCUs) in the vertical stabilizer. The PCUs cause the rudder to move in proportion to the flight-crew’s control
pedal input. A rudder-control feel unit supplies a simulated pedal load to the flight crew.
The pilot and copilot rudder pedal assemblies are both connected to the forward quadrant assembly, with no means to disconnect
one from the other. Two cable systems beginning at the forward quadrants follow the same path in the fuselage
until they reach the engine rotor burst zone, where they are routed separately towards the rear fuselage. In the event of a
severed single cable in the rotor burst zone, the aft quadrant still receives input from the unaffected cables, thus retaining
rudder system functionality. On the ground, trapped hydraulic fluid provides rudder control surface gust lock damping
when the hydraulic systems are depressurized.
Rudder position is displayed on the EICAS FLIGHT CONTROL synoptic page. A full-scale deflection of the rudder position
indicator corresponds to maximum rudder travel.
FO1001002_014
ID
INPH
TX
ROLL DISCONNECT
HANDLE
FLIGHT CONTROLS
Volume 2 Flight Crew Operating Manual Sep 13/2004
10-01-04 CSP 100-6 REV 1
PRIMARY FLIGHT CONTROLS (Cont)
RUDDER POWER CONTROL UNIT (PCU)
There are two hydraulic rudder PCUs attached to the rear spar of the vertical stabilizer. The left hydraulic system energizes
the upper rudder PCU and the right hydraulic system energizes the lower rudder PCU. If the right hydraulic system loses
pressure, the lower rudder PCU is powered by the auxiliary hydraulic system.
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