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the upper left of the attitude display portion of each PFD (see Figure 04−10−5).
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−6
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AUTOPILOT (CONT'D)
AP Engage Button
Figure 04−10−4
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)
• AP DISC switch-bar (if installed) on the FCP is in the normal position
• No faults detected in the active pair of flight control computers (FCCs)
• No significant instability exists, including:
• Adverse pitch/roll/yaw rates
• G−loads exceeding predetermined values
• Adverse pitch/roll attitudes exceeding predetermined values
Autopilot Engagement
Figure 04−10−5
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−7
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
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
• Lowering the AP DISC switch-bar (if installed) 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
canceled 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.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−8
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
YAW DAMPER SYSTEM (CONT'D)
The yaw dampers operate independently of the autopilot.
NOTE
The yaw damper will not compensate for a sustained adverse yaw
created by an engine power asymmetry or improper rudder inputs.
Operation
Yaw Damper Engagement
The yaw dampers are engaged by pushing both YD 1 and YD 2 switch/lights on the YAW
DAMPER panel. Selective engagement of the switch/lights activates the corresponding yaw
damper channel. Yaw damper engagement is indicated by the absence of yaw damper (status
and caution) EICAS messages and PFD indications.
Normally, both yaw dampers are engaged for all phases of flight. One yaw damper channel will
provide adequate yaw damping and turn coordination during flight. At speeds greater than 256
　
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