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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 04.10.5
Oct 05/06
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 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 04.10.6
Oct 05/06
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本文链接地址：庞巴迪挑战者605公务机机组操作手册 CL605-AUTOMATIC_FLIGHT_CONTROL_SYSTEM(5)
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