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trim actuator at the summing unit in the vertical fin. Directional trim is summed into the pilot pedal
command and no pedal displacement occurs.
Longitudinal trim is achieved by inputs from autopilot, mach trim and switches on the pilot’s control
wheels. Trim is operated by a dual electric motor and screw jack assembly at the horizontal
stabilizer. Mach trim is provided by the two FCUs to correct for inherent airplane trim changes, with
changing mach number.
Aileron, elevator and pitch trim indication is shown full time on the EICAS primary display.
FLIGHT CONTROLS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−2
HIGH LIFT DEVICES
The high lift devices consist of leading edge slats and trailing edge flaps. The flap/slat systems are
mechanically independent. Each system contains ballscrew actuators, linked through a rigid drive
line to dual electric motors contained within a central powerdrive
unit.
An integrated flap/slat selector lever is located in the flight compartment, in the centre pedestal.
Electrically, there are two independent channels for both flap and slat systems. Two Slat/Flap Control
Units (SFCUs) control the operation of the slats and the flaps.
System control provides protection against asymmetry and uncommanded movement. Interface to
EICAS and central maintenance are provided for system failure detection and isolation.
STALL PROTECTION
Two subsystems, stall warning and a stick pusher system comprise the stall protection system.
HYDRAULIC POWER DISTRIBUTION
The primary and secondary flight controls are hydraulically powered by the following services:
NO. 1 SYSTEM NO. 3 SYSTEM NO. 2 SYSTEM
RUDDER RUDDER
LEFT AND
RIGHT AILERON
RIGHT
LEFT AND RIGHT
RIGHT ELEVATOR
LEFT AND RIGHT
LEFT AND RIGHT
GROUND SPOILERS
AILERON
ELEVATOR
MULTIFUNCTION
LEFT AND RIGHT
MULTIFUNCTION
RUDDER
LEFT
AILERON
LEFT
ELEVATOR
LEFT AND RIGHT
GROUND SPOILERS
SPOILERS SPOILERS
GF1010_003
INDICATING SYSTEM
The flight control synoptic page provides position indications of the primary control surface, flap/slats
and spoiler system. The roll, pitch and yaw trim indications are displayed on the EICAS primary
page.
FLIGHT CONTROLS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−3
FLIGHT CONTROL SYNOPTIC PAGE
SLAT DISPLAY
MULTIFUNCTION
SPOILERS
FLAP DISPLAY
ELEVATOR
AILERON POSITION
INDICATION
RUDDER POSITION
INDICATION
ELEVATOR POSITION
INDICATION
GROUND SPOILER
DISPLAY
AILERON
FLAP DIGITAL
DISPLAY
SLAT POSITION
DISPLAY
FLIGHT CONTROLS
SLAT OUT
FLAP 30
AIL
ELEV
RUDDER
AIL
ELEV
GF1010_004
EICAS PRIMARY PAGE
Primary Page
TRIM DISPLAYS:
AILERON
RUDDER
STABILIZER
CONTROL SURFACE
DISPLAYS:
FLAPS
SLATS
SPOILERS
GEAR
OUT
30
DN DN DN
ND
STAB
NU
NL RUDDER
LWD RWD
NR
TRIMS
7.2
AIL
GF1010_008
FLIGHT CONTROLS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−4
PRIMARY FLIGHT CONTROL SCHEMATIC
Aerodynamic reaction forces at the primary controls are simulated by mechanical artificial feel units.
FORWARD
RUDDER
QUADRANT
FORWARD AILERON
QUADRANT
AILERON
AUTOPILOT
SERVO
AILERON AFT
QUADRANT/
ARTIFICIAL
FEEL
AILERON
PCU
AILERON TRIM
RUDDER
PCUs
ELEVATOR
PCUs
RUDDER AFT
QUADRANT
RUDDER
TRIM/YAW
DAMPERS
ELEVATOR
AUTOPILOT
SERVO
ELEVATOR AFT
QUADRANT/PITCH
FEEL UNITS
STICK
PUSHER
ACTUATOR
AILERON
PCUs
RUDDER
PEDAL
RUDDER
LIMITER
GF0910_005
Lateral control is accomplished by a dual mechanical aileron control system hydraulically powered by
two PCUs per aileron. Four multifunction
spoilers per wing assist the ailerons in roll control (see
SPOILER SYSTEM this Chapter). Aileron disconnect is provided for antijam
protection. Artificial feel
and centering is provided to lighten the load on the aileron control system.
Pitch control is provided by a dual mechanical elevator control system hydraulically powered by two
PCUs per elevator. Pitch disconnect is provided for antijam
　
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