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AUTOMATIC FLIGHT CONTROL SYSTEM Table of Contents Vol. 2 04.00.4
Oct 05/06
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CL.605 Flight Crew Operating Manual
PSP 605.6
AUTOMATIC FLIGHT CONTROL SYSTEM Description Vol. 2 04.10.1
Oct 05/06
The automatic flight control system (AFCS) on the Challenger 605 is a subsystem of the Collins Pro Line 21 Avionics System. It is a fully integrated flight control system that includes a dual channel two-axis autopilot, each with integrated dual flight directors, dual yaw dampers, and automatic pitch trim control. The flight control system consists primarily of the following equipment:
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Four flight control computers;
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One flight control panel;
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Aileron and elevator servos; and
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Two linear actuators for the rudder (yaw damping).
The flight control computers (FCCs) receive pilots’ input from the selections made on the flight control panel (FCP). Electronic signals from the FCCs send guidance commands to the aileron and elevator servos, the yaw damper linear actuators, and the horizontal stabilizer trim control unit (HSTCU).
When the autopilot is engaged, the AFCS maneuvers the aircraft, while the pilot monitors the flight path by observing the flight guidance information presented on the EFIS primary flight display (PFD).
When the autopilot is disengaged, the pilot manually flies the aircraft in response to guidance provided by the flight director (FD) command bars on the PFD.
The Safe Flight enhanced autothrottle system (ATS) incorporates dual.servo control of the thrust levers to enable thrust and speed control for all phases of flight, including a go.around mode. The ATS will be explained in detail at the end of this chapter.
FLIGHT CONTROL COMPUTERS
Description
The flight control computers (FCCs) process information from the inertial reference system (IRS), air data computers (ADCs), navigational (NAV) systems and various cockpit control panels, to calculate flight path and flight guidance parameters.
Components and Operation
Each FCC is capable of generating independent flight director commands.
The FCCs provide output data to the following:
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Flight control panel;
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Flight directors on the PFDs;
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Autopilot servomotors (elevator, aileron);
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Yaw damper actuators; and
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Pitch trim, horizontal stabilizer trim control unit (HSTCU).
Each AFCS uses the following FCCs:
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AFCS 1 – FCC 1A and 2A.
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AFCS 2 – FCC 1B and 2B.
Only one system of FCC pairs (AFCS 1 or AFCS 2) can be active at any time. The inactive system is on standby, and a manual selection is required to switch from AFCS 1 to AFCS 2, or vice versa.
AUTOMATIC FLIGHT CONTROL SYSTEM Description Vol. 2 04.10.2
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