BOMBARDIER BD-100-1A10, Operating Manual

Page: 275 / 544

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 discon-
nect 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 pow-
ered. 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 dis-
connect 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 posi-
tion indicator corresponds to maximum rudder travel.
F
O
10
010
02_0
14
ID
INPH
TX
ROLL DISCONNECT
HANDLE