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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.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−4
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AUTOPILOT
Description
The Challenger 604 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.
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. Any significant
elevator or aileron mistrim condition causes an amber E (elevator) or A (aileron) to be displayed
on the upper left of the PFD. In conjunction with the PFD annunciations, the EICAS will display
an AP TRIM IS NU or AP TRIM IS ND caution EICAS message (autopilot is counteracting a
significant nose-up or nose-down mistrim) for a significant elevator mistrim condition, or an AP
TRIM IS LWD or AP TRIM IS RWD caution EICAS message (indicating left or right wing down) for
an aileron mistrim.
NOTE
When the autopilot is disengaged during a mistrim condition, expect
an abrupt change in control force.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−5
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AUTOPILOT (CONT'D)
Autopilot Elevator and Aileron Mistrim Annunciation
Figure 04−10−3
NOTE
Autopilot monitors aileron mistrim conditions but cannot change
aileron trim settings
Autopilot Servomotors
When the autopilot is engaged, the active pair of FCCs direct roll and pitch commands to the
aileron and elevator servos, and stabilizer trim commands through the HSTCU. When a change
in roll or pitch is required, the FCCs signal the aileron servo or elevator servo to bias the control
cables and displace the associated control surface.
The aileron servo is located on the control cable run for the right aileron. Since the left and right
ailerons are normally interconnected, the servo is capable of moving both ailerons.
The elevator servo is located on the left elevator cable run. Both elevators move unless
disconnected.
Autopilot Engagement
The autopilot is engaged by pressing the AP ENG button located on the flight control panel (see
Figure 04−10−4). Autopilot engagement is indicated by the illumination of a green indicator
light along each side of the AP button. In addition, an AP engage annunciation is provided on
　
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