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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
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.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
FLIGHT CONTROL SYNOPTIC PAGE
SLAT POSITION
DISPLAY
MULTI-FUNCTION SPOILERS
FLAP DISPLAY
ELEVATOR POSITION INDICATION
ELEVATOR
EICAS PRIMARY PAGE
CONTROL SURFACE DISPLAYS:
FLAPS SLATS SPOILERS
TRIM DISPLAYS: AILERON RUDDER STABILIZER
Primary Page
GF1010_008 GF1010_004
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
PRIMARY FLIGHT CONTROL SCHEMATIC
Aerodynamic reaction forces at the primary controls are simulated by mechanical artificial feel units.
ELEVATORELEVATOR AFT PCUs
QUADRANT/PITCH FEEL UNITS
AILERON
PCU
RUDDER LIMITER
ELEVATOR AUTOPILOT RUDDERSERVO
PCUs RUDDER AILERON TRIM
TRIM/YAW DAMPERS
RUDDER AFTAILERON QUADRANT
AUTOPILOT
SERVO
FORWARD AILERON AFT
RUDDER
QUADRANT/
QUADRANT
ARTIFICIAL AILERONFEEL PCUs
STICK
PUSHER
ACTUATOR
FORWARD AILERON
QUADRANT
RUDDER
PEDAL
Lateral control is accomplished by a dual mechanical aileron control system hydraulically powered by two PCUs per aileron. Four multi-function spoilers per wing assist the ailerons in roll control (see SPOILER SYSTEM this Chapter). Aileron disconnect is provided for anti-jam 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 anti-jam protection. Variable pitch artificial feel is provided to vary the load on the elevator control wheel as a function of airspeed and horizontal trim setting.
Yaw control is provided by means of three hydraulic PCUs to power the rudder. Rudder travel limiting as a function of airspeed is provided to limit loads on the structure. The rudder system uses dual cable circuits (aft fuselage) to protect the system from effects of engine rotor burst.
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