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(PCUs), which hydraulically move the control surfaces. Artificial control loading provides tactile
feedback to the pilots at the individual control columns, control wheels and rudder pedals.
FLIGHT CONTROLS
Description
Vol. 2 10−10−1
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
PRIMARY FLIGHT CONTROLS (CONT'D)
Position indicators are located on the FLIGHT CONTROLS synoptic page. White triangles and
position scales indicate relative deflection of the ailerons, elevators and rudder.
Aileron and elevator flight control surfaces are each powered by two hydraulic systems, and the
rudder is powered by all three systems. Flight control system design ensures that the loss of one
hydraulic system will not prevent the operation of any control surface. Furthermore, should two
hydraulic systems be lost, the remaining hydraulic system is sufficient to maintain safe aircraft
control. Protection against cable jam/failure or PCU jam/failure is also provided for each axis.
Gust damping is provided for all three sets of primary flight controls. When the aircraft is parked
and the hydraulic systems are unpressurized, built-in valves in the aileron, elevator and rudder
PCUs protect against rapid flight control surface movement.
Components and Operation
Ailerons
Lateral (roll) control is provided by ailerons. Two separate control paths are provided from the
pilot’s and copilot’s control wheels. The pilot’s side controls the left aileron and the copilot’s side
controls the right aileron. Movement of both pilot’s and copilot’s controls is simultaneous when
the controls are interconnected (normal operation). Rotating either control wheel activates, via
cables and pulleys, the PCUs (actuators) for the ailerons. Two actuators are used for each
aileron. The left aileron PCUs use hydraulic pressure from systems 1 and 3, and the right
aileron PCUs use hydraulic systems 2 and 3. A position transmitter, linked to each aileron,
provides visual indication of the aileron deflection on the FLIGHT CONTROLS synoptic page
Aileron Disconnect
In the event of a control cable jam or PCU malfunction, the left and right sides of the aileron
control circuit can be isolated by pulling the ROLL DISCONNECT handle on the center
pedestal. This disengages a locking pin on the interconnect torque tube to isolate the failed
circuit. The aileron on the operable circuit provides roll control at a reduced roll rate. The ROLL
DISCONNECT handle can be reset at any time, locking the two control circuits together again.
FLIGHT CONTROLS
Description
Vol. 2 10−10−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
PRIMARY FLIGHT CONTROLS (CONT'D)
Roll Control − Schematic
Figure 10−10−2
FLIGHT CONTROLS
Description
Vol. 2 10−10−3
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
PRIMARY FLIGHT CONTROLS (CONT'D)
Aileron Power Control Unit Protection
If a PCU is malfunctioning, a failure detection will cause the EICAS to display a PCU valve jam
symbol on the FLIGHT CONTROLS synoptic page (an amber half-circle above the aileron
outline), and an amber AILERON PCU caution EICAS message to appear. Two sets of shear
rivets on each aileron PCU provide additional protection against internal PCU linkage jams. If
the linkage to one cylinder jams, the pilot can overpower the jammed condition, which will
shear the rivets on that side and allow the other cylinder to operate the aileron.
Flutter Dampers
A flutter damper is installed on each aileron. This prevents control surface flutter in flight, in the
event of a complete loss of hydraulic fluid at the PCU. A breakaway link provides jam
protection in the case of flutter damper seizure.
Elevators
Longitudinal (pitch) control is provided by elevators, and supplemented by a movable horizontal
stabilizer. Two separate control paths are provided through the pilot’s and copilot’s control
columns. The pilot’s control column controls the left elevator, and the copilot’s control column
controls the right elevator. Movement of both pilot’s and copilot’s controls is simultaneous when
the systems are interconnected (normal operation). Moving either control column activates, via
cables and pulleys, the PCUs (hydraulic actuators) for the elevators. Two actuators are used for
each elevator. The left elevator PCUs use hydraulic pressure from systems 1 and 3, and the
right PCUs use systems 2 and 3.
A position transmitter linked to each elevator provides visual indication of the elevator deflection
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庞巴迪挑战者605机组操作手册 CL605-FLIGHT_CONTROLS(2)
