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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 EICAS 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 interconnecting torque tube to
FLIGHT CONTROLS
For Training Purposes Only
May 03
10-3
P I LOT T R A I N I N G GU I D E
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.
Roll Control - Schematic
Figure 10-2
1 3
3 2
FLUTTER
DAMPER
FLUTTER
DAMPER
Aileron
(Position to EICAS
Flight Controls Page)
Aileron
TRIM ACTUATOR
TRIM POSITION
TO EICAS PRIMARY
(SEE FIG 10-8)
M
ROLL
DISC
FLIGHT CONTROLS
FLAPS 30
AIL AIL
EICAS FLIGHT CONTROLS SYNOPTIC PAGE
(SECONDARY DISPLAY)
Aileron
Position
Indicator
PCU Valve
Jam Symbol
AUTOPILOT SERVO
COMMANDS
P604_10_002
I/C
OFF
R/T
NOSEDN
NOSEUP
AP
SC
SYNCI/C
OFF
R/T
NOSEDN
NOSEUP
AP
SC
SYNC
L
W
D
R
W
D
AIL TRIM
ROLL DISC
FLIGHT CONTROLS
10-4 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
Aileron Power Control Unit Protection
If a PCU is malfunctioning, a failure detection sensor 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 Damper
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.
FLIGHT CONTROLS
For Training Purposes Only
May 03
10-5
P I LOT T R A I N I N G GU I D E
Page Intentionally Left Blank
FLIGHT CONTROLS
10-6 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
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
operations). 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 on the EICAS FLIGHT CONTROLS synoptic page. If a differential of
greater than 5° between each elevator position exists, an ELEVATOR SPLIT caution
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庞巴迪挑战者604机组操作手册 CL_604-FLIGHT_CONTROLS(3)
