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If the navigation source is VOR or localizer or OBS Mode has been enabled when using GPS, the Selected Course is controlled using the CRS Knob corresponding to the selected flight director (CRS1 for the pilot side, CRS2 for the copilot side).
Pressing the CWS Button and hand-flying the aircraft does not change the Selected Course while in Approach Mode. The autopilot guides the aircraft back to the Selected Course (or GPS flight plan) when the CWS Button is released.
394 Garmin G1000 Pilot’s Guide for the Cessna Citation Mustang 190-00494-02 Rev. B
Automatic utomatic utomatic Flight Control System ystem
SYSTEM
OVERVIEW
FLIGHT
AUDIO PANEL EICAS INSTRUMENTS
& CNS
FLIGHT
MANAGEMENT
HAZARD
ADDITIONAL AFCS AVOIDANCE
INDEX APPENDICES FEATURES
kcourse Mode (BC) NOTE: When making a backcourse approach, set the Selected Course to the localizer front course.
Backcourse Mode captures and tracks a localizer signal in the backcourse direction. The mode may be selected by pressing the BC Key. Backcourse Mode is armed if the CDI is greater than one dot when the mode is selected. If the CDI is less than one dot, Backcourse Mode is automatically captured when the BC Key is pressed. The flight director creates roll steering commands from the Selected Course and deviation when in Backcourse Mode.
Pitch Hold Mode ActiveBackcourse Mode ActiveFigure 7-30 Backcourse ModeLOC2 is Selected Navigation SourceCommand Bars Hold Pitch Attitude
Changing the Selected Course
If the navigation source is VOR or localizer or OBS Mode has been enabled when using GPS, the Selected Course is controlled using the CRS Knob corresponding to the selected flight director (CRS1 for the pilot side, CRS2 for the copilot side).
Pressing the CWS Button and hand-flying the aircraft does not reset any reference data while in Backcourse Mode. The autopilot guides the aircraft back to the Selected Course when the CWS Button is released.
190-00494-02 Rev. B Garmin G1000 Pilot’s Guide for the Cessna Citation Mustang 395
Automatic utomatic utomatic Flight Control System ystem
SYSTEM
OVERVIEW
FLIGHT
INSTRUMENTS EICAS AUDIO PANEL
& CNS
FLIGHT
MANAGEMENT
HAZARD
AVOIDANCE AFCS ADDITIONAL
FEATURES APPENDICES INDEX
7.5 Autopilotutopilotutopilot and Yawaw Damper Operationperation NOTE: Refer to the AFM for specific instructions regarding emergency procedures.
The Cessna Citation Mustang’s autopilot and yaw damper operate the flight control surface servos to provide automatic flight control. The autopilot controls the aircraft pitch and roll attitudes following commands received from the flight director. Pitch autotrim provides trim commands to the pitch trim servo to relieve any sustained effort required by the pitch servo. Autopilot operation is not independent of the yaw damper for the Cessna Citation Mustang.
The yaw damper reduces Dutch roll tendencies and coordinates turns. It can operate independently of the autopilot and may be used during normal hand-flight maneuvers. Yaw rate commands are limited to 6 deg/sec by the yaw damper.
Flight Control
Pitch and roll commands are provided to the servos based on the active flight director modes. Yaw damping is provided by the yaw servo. Servo motor control limits the maximum servo speed and torque. The servo gearboxes are equipped with slip-clutches set to certain values. This allows the servos to be overridden in case of an emergency.
Pitch Axis and Trim
The autopilot pitch axis uses pitch rate to stabilize the aircraft pitch attitude during upsets and flight director maneuvers. Flight director pitch commands are rate- and attitude-limited, combined with pitch damper control, and sent to the pitch servo motor. The pitch servo measures the output effort (torque) and provides this signal to the pitch trim servo. The pitch trim servo commands the motor to reduce the average pitch servo effort.
When the autopilot is not engaged, the pitch trim servo may be used to provide manual electric pitch trim (MEPT). This allows the aircraft to be trimmed using a control wheel switch rather than the trim wheel. Manual trim commands are generated only when both halves of the MEPT Switch are operated simultaneously. Trim speeds are scheduled with airspeed to provide more consistent response.
Roll Axis
The autopilot roll axis uses roll rate to stabilize aircraft roll attitude during upsets and flight director maneuvers. The flight director roll commands are rate- and attitude-limited, combined with roll damper control, and sent to the roll servo motor.
Yawaw Axis
The yaw damper uses yaw rate and roll attitude to dampen the aircraft’s natural Dutch roll response. It also uses lateral acceleration to coordinate turns. Yaw damper operation is independent of autopilot engagement.
396 Garmin G1000 Pilot’s Guide for the Cessna Citation Mustang 190-00494-02 Rev. B
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Cessna Citation Mustang G1000 Integrated Flight Dec(140)
