BOMBARDIER BD-100-1A10, Руководство по эксплуатации

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AUTOMATIC FLIGHT CONTROL SYSTEM
May 06/2005 Flight Crew Operating Manual Volume 2
REV 2 CSP 100-6
04-01-21
AUTOPILOT
DESCRIPTION
The Challenger 300 his equipped with a three axis digital fail-passive autopilot. Autopilot servos provide command inputs
to the ailerons and elevators. The rudder is controlled by the yaw damper system. The coupled flight guidance computer
provides the flight guidance signals to drive the servos. Both flight guidance computers must be operational for the auto-
pilot to function.
Upon occurrence of any single failure, the autopilot will not:
- Cause significant displacement of the aircraft from its approach path or altitude loss below the nominal glide path
- (Upon system disconnection) Involve any out-of-trim condition not easily controlled by the pilot
- Cause any action to occur with the flight control system that is not readily apparent to the pilot, either by control
column movement or advisory display
The automatic flight-control system (AFCS) consists of dual-independent flight directors, a three axis autopilot, and auto-
matic pitch trim and yaw damper system.
The AFCS operates with the integrated-avionics processor system (IAPS). The IAPS collects the data for the avionics sys-
tems. The AFCS gives the course, heading, and preselected altitude data to the electronic flight instrument system (EFIS).
The AFCS calculates the vertical and lateral flight-guidance commands to keep the aircraft on the correct pitch/roll attitude.
The flight directors show the flight-guidance commands on the primary flight displays.
ENGAGEMENT PARAMETERS
The autopilot can be engaged using the AP switch on the FGP, if the following conditions exist:
- Yaw damper is operable
- Both flight guidance computers (FGCs) are serviceable
- At least one channel of the horizontal stabilizer trim is engaged and the FCCs detect no faults with the horizontal
stabilizer trim system
- No significant instability of the aircraft exists
COMPONENTS AND OPERATION
AUTOPILOT ENGAGEMENT
The autopilot is engaged by pressing the AP switch located on the flight guidance panel. When the autopilot is engaged,
both channels of the autopilot are coupled to the onside flight guidance computer. Autopilot engagement is indicated on the
PFD by a green AP indication.
Pressing the AP switch on the FGP when the autopilot is engaged will cause the autopilot to disengage.
AUTOPILOT SERVO MOTORS
When the autopilot is engaged, the controlling FGC directs pitch and roll commands to the aileron and elevator servos.
When a change in roll or pitch attitude is required, the FGC signals the aileron servo or elevator servo to bias the control
cables to move 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 in-
terconnected, the servo is capable of moving both ailerons. The elevator servo is located in the left elevator cable run. The
servo moves both elevators when the elevators are interconnected.
When an out-of-trim condition is sensed in the pitch axis, the FGC signals the horizontal stabilizer trim control unit to re-
position the horizontal stabilizer.