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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.
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 the centre of the FMA
display of each PFD (see Figure 04−10−4).
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−5
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AUTOPILOT (CONT'D)
AP Engage Button
Figure 04−10−3
Once engaged, the autopilot will couple to, and follow the guidance commands from, the
selected flight director. If no FD modes are commanded prior to autopilot engagement, the
autopilot automatically activates, and follows guidance from the basic lateral (ROLL) and vertical
(PITCH) modes.
When the autopilot is not engaged, a left- or right-pointing arrow, in white, indicates which flight
director the autopilot will couple to upon engagement.
Autopilot Engagement Criteria
The autopilot can be engaged provided the following conditions exist:
• At least one yaw damper is engaged (normally, both YDs are engaged);
• No faults detected in the active pair of flight control computers (FCCs); and
• No significant instability exists, including:
• Adverse pitch/roll/yaw rates;
• G-loads exceeding predetermined values; or
• Adverse pitch/roll attitudes exceeding predetermined values.
Autopilot Engagement
Figure 04−10−4
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−6
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AUTOPILOT (CONT'D)
Autopilot Disengagement
Manual (Pilots Action) Disengagement
The autopilot is normally disengaged by pressing the red autopilot/stick pusher (AP/SP DISC)
disconnect button on the outboard horn of either control wheel.
The autopilot may also be manually disengaged by any one of the following actions:
• Operating either stabilizer trim switch;
• Pushing the AP ENG button on the FCP;
• Selecting takeoff or go-around (TOGA) button;
• Switching the AFCS SEL selector to the other AFCS (1 or 2); or
• Pressing the yaw damper DISC switch.
Whenever the autopilot is manually disengaged (by pilot action), the PFD green engage
annunciation turns red and flashes for 5 seconds, the green status indicator lights beside the
AP button extinguish, and the autopilot disconnect (cavalry charge) aural sounds. The autopilot
disconnect warning will automatically cancel after a few repetitions of the cavalry charge.
Monitored Disengagement
The FCCs continually monitor aircraft sensors, servo data, the automatic pitch trim system and
internal parameters for faults. The autopilot will automatically disengage if any of the following
conditions occur:
• Internal FCC monitors detect a failure in any axis;
• Any power source to an FCC of the active pair is lost;
• Loss of either inertial reference system (IRS) system input;
• Dual yaw damper failure;
• Aircraft is at an excessive attitude (pitch angle beyond +25° or −17°, roll angle beyond
±45°);
• Either stick shaker activates; or
• Switch from one AFCS to the other.
A monitored disengagement is annunciated in the same manner as a manual disengagement,
with the exception that the flashing on the PFD and the aural warning will continue until
cancelled by the flight crew. Pressing either pilot’s AP/SP DISC switch or TOGA button, or
reengaging the autopilot, will cancel the flashing on the PFD and the aural warning.
YAW DAMPER SYSTEM
Description
Each yaw damper is a dual-channel, fully independent yaw damper system, providing yaw
damping, turn entry, steady-state turn coordination, and turn exit for the full flight envelope.
The yaw dampers operate independently of the autopilot.
　
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