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Figure 10.10.21 EICAS Flight Controls Indications (Aileron, Elevator,
Rudder) 10.10.28
FLIGHT CONTROLS Description Vol. 2 10.10.1
Oct 05/06
The Challenger 605 has conventional flight controls organized on an advanced technology airfoil, and a T-tail configuration empennage. The flight control surfaces are actuated by crew or autopilot inputs via mechanical connections to hydraulic power control units (PCUs). Artificial control loading is provided at the individual control columns, control wheels and rudder pedals.
The flight controls may be divided functionally into two categories: Primary and secondary flight controls.
Primary Flight Controls
The primary flight controls are the ailerons, elevators and rudder. Each aileron and elevator is powered by two hydraulic systems. The rudder is powered by all three hydraulic systems.
In the unlikely case of total electrical failure or double-engine failure, ACMP 3B can be electrically energized directly from the air-driven generator (ADG). This ensures hydraulic power is available to the flight controls.
Secondary Flight Controls
The secondary flight controls include the trim systems (aileron, rudder and horizontal stabilizer), flaps, flight spoilers and ground spoilers. The stall protection system (SPS) is also considered a function of the secondary flight control system.
Flight Control Surfaces
Figure 10.10.1
PRIMARY FLIGHT CONTROLS
Description
The primary flight controls are arranged conventionally, with rudder pedals and a control wheel and column for both the pilot and copilot. Movement of the cockpit controls is transmitted mechanically via cable and/or pushrods to the aileron, elevator and rudder power control units (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 10.10.2
Oct 05/06
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.
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