Automatic Flight Control System; Afcs: Autopilot And Flight Director - Garmin G5000 Airplane Flight Manual Supplement

Model 560XL

Automatic Flight Control System

AFCS: Autopilot and Flight Director

The Automatic Flight Control System (AFCS) is fully integrated within the G5000 System avionics
architecture. The G5000 includes a three-axis autopilot and flight director system which provides the
pilot with the following features:
Autopilot (AP) — Autopilot operation occurs within the pitch, roll, and pitch trim servos. It also provides
servo monitoring and automatic flight control in response to flight director steering commands, AHRS
attitude and rate information, and airspeed.
Flight Director (FD) - Two flight directors, each operating within their respective GIA and referred to as
pilot-side and copilot-side. Commands for only the selected flight director are displayed on both PFDs.
The flight director provides:

Command Bars showing pitch/roll guidance

Vertical/lateral mode selection and processing

Autopilot communication
Yaw Damper (YD) — The yaw servo is self-monitoring and provides Dutch Roll damping and turn
coordination in response to yaw rate, roll angle, roll rate, lateral acceleration, and airspeed.
Electric Pitch Trim – The pitch trim servo provides manual electric pitch trim capability when the autopilot
is not engaged.
Pilot commands to the AFCS are entered through the GMC 7200 Autopilot Mode Controller mounted in
the center of the cockpit under the airplane's glareshield. The GMC 7200 controller also controls the
heading bug, navigation course selector on each PFD, and the altitude preselect.
Other components of the autopilot include four servos that also contain autopilot processors, control
wheel-mounted elevator trim switches, control wheel-mounted autopilot/yaw damper disconnect and trim
interrupt switch (AP YD DISC/TRIM INT), control wheel-mounted Control Wheel Steering (CWS) switch,
and a Go-Around (GA) switch mounted in both throttle knobs.
The autopilot and electric trim may be manually disconnected using any one of the following methods:
1. AP YD DISC/TRIM INT button (Pilot's or Copilot's control wheel) – PRESS and RELEASE.
2. AP button (Autopilot mode control panel) – PRESS (Yaw damper remains engaged).
3. Pitch Trim Switch (Pilot's or Copilot's control wheel) – PRESS either portion of the split switch
(Yaw damper remains engaged).
4. Go-Around (GA) switch (Left or Right Throttle) – PRESS (Yaw damper remains engaged).
NOTE: Autopilot will not disengage with GA switch in flight if USP option is installed
5. A/P SERVO Circuit Breaker (Left and/or Right Circuit Breaker Panel – AVIONICS) – PULL.
The following conditions will cause the autopilot to disconnect:

Electrical power failure, including pulling either A/P SERVO circuit breaker

Internal autopilot system failure

Malfunction of either AHRS (two fully functional AHRS are required for the autopilot to function)

Failure of the on-side PFD

Setting the battery switch to EMER with dual generator failure or both generators set to OFF.
Textron Aviation Citation 560XL
A-8
Appendix – Systems Description
190-02313-03 Rev. 8