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3) Press the APR Key.
Figure 7-29 GPS Approach Mode Armed
190-00494-02 Rev. B Garmin G1000 Pilot’s Guide for the Cessna Citation Mustang 393
Automatic utomatic utomatic Flight Control System ystem
SYSTEM
OVERVIEW
FLIGHT
INSTRUMENTS EICAS AUDIO PANEL
& CNS
FLIGHT
MANAGEMENT
HAZARD
AVOIDANCE AFCS ADDITIONAL
FEATURES APPENDICES INDEX
LOC Approach Mode allows the autopilot to fly a LOC/ILS approach with a glideslope. When LOC Approach Mode is armed, Glideslope Mode is also armed automatically. LOC captures are inhibited if the difference between aircraft heading and localizer course exceeds 105°.
Selecting LOC Approach Mode:
1) Ensure a valid localizer frequency is tuned.
2) Ensure that LOC is the selected navigation source (use the CDI Softkey to cycle through navigation sources if necessary).
3) Press the APR Key.
Or:
1) Ensure that GPS is the selected navigation source (use the CDI Softkey to cycle through navigation sources if necessary).
2) Ensure a LOC/ILS approach is loaded into the active flight plan.
3) Ensure the corresponding LOC frequency is tuned.
4) Press the APR Key.
If the following occurs, the flight director reverts to Roll Hold Mode (wings rolled level):
• Approach Mode is active and a Vectors-To-Final is activated
• Approach Mode is active and Navigation source is manually switched
• During a LOC/ILS approach, GPS Navigation Mode is active and the FAF is crossed after the automatic navigation source switch from GPS to LOC
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 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.
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Cessna Citation Mustang Pilot’Guide 2(39)
