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Pitch disconnect allows the flight crew to isolate the left and right control column and cable system from each other. Pitch disconnect separates the control column interconnect (torque tube) system. Single side pitch control is then available (either left or right elevator) using the operable control column path.
The rudder uses cable split quadrants to dualize the cable paths in the engine turbine burst zone. This method protects the system from loss of pedal commanded rudder control, during a rotor burst event.
Flutter damping for the primary flight controls is provided through the PCUs internal operation. Ground gust damping (gust locks) are provided through PCUs on the elevators, ailerons and rudder. The PCUs provide a hydraulic lock for gust damping, when the hydraulic systems are depressurized.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
SECONDARY FLIGHT CONTROLS
The secondary flight controls consist of the flap/slat system, multi-function spoilers, ground spoilers and various trim systems.
The electrical flight control system is built around two identical digital computer units referred to as Flight Control Units (FCUs). The FCUs control and monitor the following systems: multi-functional spoilers, ground spoilers, horizontal stabilizer trim, pitch feel and rudder travel limiting.
SPOILER SYSTEM
Eight multi-functional spoiler panels are electrically controlled and hydraulically actuated by a single PCU on each surface. The multi-function spoilers are used for in flight operation as roll assistance, symmetrically for proportional lift dump and on ground for ground lift dumping.
Four ground spoiler panels are electrically controlled and hydraulically actuated by a single actuator on each surface and are used for ground lift dumping only.
TRIM CONTROL
Lateral trim is accomplished by a dual position switch in the centre pedestal that operates an electric trim actuator at the aft quadrant/aileron artificial feel units. The lateral trim will cause rotation of the control wheel neutral position.
Directional trim is achieved by a single rotary switch in the centre pedestal that operates an electric 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.
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
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 power-drive unit.
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