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Figure 04−10−41 Flight Control Panel (FCP) − Flight Director Vertical Modes 04−10−49
Figure 04−10−42 Cockpit Switches − Autopilot/Flight Director Function 04−10−50
Figure 04−10−43 PFD Annunciations 04−10−51
Figure 04−10−44 Autothrottle System Overview 04−10−56
Figure 04−10−45 Autothrottle Computer 04−10−57
Figure 04−10−46 Dual Servo Clutch/Servomotor 04−10−58
Figure 04−10−47 ATS Control Panel 04−10−59
Figure 04−10−48 ATS Computer Testing 04−10−62
Figure 04−10−49 ATS Takeoff Mode 04−10−63
Figure 04−10−50 ATS Takeoff 04−10−64
Figure 04−10−51 ATS Climb 04−10−65
Figure 04−10−52 ATS Cruise 04−10−66
Figure 04−10−53 Descent/Approach Modes 04−10−68
Figure 04−10−54 Landing and Go-Around Modes 04−10−70
Figure 04−10−55 ATS Disconnect 04−10−71
AUTOMATIC FLIGHT CONTROL SYSTEM
Table of Contents
Vol. 2 04−00−3
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
Page
AUTOMATIC FLIGHT CONTROL SYSTEM
Table of Contents
Vol. 2 04−00−4
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
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GENERAL
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:
• Four flight control computers;
• One flight control panel;
• Aileron and elevator servos; and
• 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:
• Flight control panel;
• Flight directors on the PFDs;
• Autopilot servomotors (elevator, aileron);
• Yaw damper actuators; and
• Pitch trim, horizontal stabilizer trim control unit (HSTCU).
Each AFCS uses the following FCCs:
• AFCS 1 – FCC 1A and 2A.
• 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 04−10−1
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
FLIGHT CONTROL COMPUTERS (CONT'D)
The AFCS SEL switch, located on the bottom right hand corner of the reversionary panel, selects
the active pair of FCCs (AFCS 1 or AFCS 2) that provide steering commands to the aileron and
elevator servos, and to the HSTCU.
The FCCs receive 28V DC power to operate the following buses:
Flight Control Computers Power Supply
FCC NORMAL POWER
1A BATT BUS
2A DC ESS BUS
1B BATT BUS
2B DC BUS 2
NOTE
FCC 2B not powered during EMER POWER ONLY conditions.
Integrated Avionics Processing System (IAPS)
　
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