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The integrated avionics processing system (IAPS) is a physical housing (card cage) containing
the four flight control computers (FCCs) and other avionics systems computers and modules.
The IAPS provides power to the avionics components, and enables these components to
communicate with each other and with aircraft systems.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
FLIGHT CONTROL COMPUTERS (CONT'D)
Automatic Flight Control System Configuration
Figure 04−10−1
Flight Control Panel (FCP)
The flight control panel (FCP) is the mode selection panel that controls the flight director and
autopilot functions. The FCP is located on the glareshield, and is accessible to both pilots.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−3
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
FLIGHT CONTROL COMPUTERS (CONT'D)
Flight Control Panel
Figure 04−10−2
FCC Status Indicator Lights
There are two green status indicator lights, one on either side of each mode button. When a
pilot selects an FCP button, the request is sent to both active FCCs (1A and 2A, or 1B and 2B).
When the FCCs determine that conditions are correct for the selected mode, they send
acknowledgement signals back to the FCP, and illuminate the green lights on either side of the
selected button.
The left light indicates that FCC 1 (A or B) has acknowledged the request. The right light
indicates that FCC 2 (A or B) has acknowledged the request.
NOTE
Illumination of the status indicator lights does not provide the flight
crew with a complete representation of active or armed flight
director modes. The flight mode annunciator must always be
cross-checked to confirm current lateral and vertical FD mode
status.
FD Buttons
The FD buttons are used to turn on or turn off the flight directors. When the autopilot is not
engaged, pressing the FD button, associated with the active flight director, will remove the
command bars and vertical and lateral guidance information from both PFDs. The inactive side
FD button can be used to alternately display or remove the flight director command bar from
the associated PFD.
Course Select Knob
The course select knobs are used to set the course arrow when navigating with a VOR or
localizer. CRS1, when rotated, changes the selected course as displayed on the left primary
flight display. A course arrow and digital course readout on PFD 1 indicate the course setting.
The button in the center of the knob (PUSH DIRECT button), when pressed, causes the course
pointer and digital readout to indicate a “direct-to” course to the tuned VOR station.
The CRS2 course select knob operates in an identical manner for the right PFD.
AUTOPILOT
Description
The Challenger 605 is equipped with a dual-channel, two-axis, fail-passive autopilot system. The
autopilot provides an interface between the AFCS and flight controls for roll and pitch commands.
Yaw dampers provide turn coordination and yaw damping.
The autopilot is integrated with the flight director to automatically control and direct the flight path
of the aircraft. When engaged, the autopilot controls the aircraft’s pitch and roll axes in accordance
with the coupled flight director commands.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−4
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AUTOPILOT (CONT'D)
Operation
Autopilot Pitch Trim
Automatic pitch trim is enabled whenever the autopilot is engaged. The autopilot issues
commands to the horizontal stabilizer trim control unit (HSTCU) to remove continuous loads
from the elevator servomotor.
Protracted trim operation causes the trim clacker aural to sound. Autopilot pitch trim failure is
annunciated by an AP PITCH TRIM caution EICAS message.
Autopilot Mistrim Conditions
The AFCS continuously monitors both axes of the autopilot when it is engaged. A significant
elevator mistrim condition causes the EICAS to display an AP HOLDING NOSE UP or AP
HOLDING NOSE DOWN caution EICAS message (autopilot is counteracting a significant nose-up
or nose-down mistrim). For a significant aileron mistrim condition, an AP HOLDING LWD or AP
HOLDING RWD caution EICAS message (indicating left or right wing down) is displayed.
NOTE
When the autopilot is disengaged during a mistrim condition, expect
an abrupt change in control force.
NOTE
Autopilot monitors aileron mistrim conditions but cannot change
　
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