Garmin GFC 600 Manual - Página 39

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AFCS OVERVIEW

The Garmin GFC 600 Pilot's Guide, part number 190-01488-00, may be referenced for a detailed system

description.

The GFC 600 is a digital Automatic Flight Control System (AFCS). It is a two-axis autopilot (with optional

axis yaw damper) and flight director system which provides the pilot with the following features:

Flight Director (FD) — The flight director processing occurs in the GMC 605 mode panel. Selected

modes for the flight director are displayed on the GMC 605 display and the GI 285 annunciator panel (if

installed).

The flight director provides:



Command Bars showing pitch/roll guidance



Vertical / lateral mode selection and processing

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, attitude

and rate information, and airspeed.

Optional Yaw Damper (YD) — The yaw servo is self-monitoring and provides Dutch roll damping and

turn coordination in response to yaw rate, roll angle, lateral acceleration, and airspeed.

Electric Pitch Trim — The pitch trim servo provides manual electric pitch trim capability when the

autopilot is not engaged. It provides automatic electric pitch trim capability when the autopilot is engaged.

Internal Attitude Source – The GMC 605 contains internal sensors which calculate the aircraft attitude,

allowing the GFC 600 to operate without relying on any external source of attitude. Internal monitoring

detects attitude errors and will automatically disconnect the autopilot in the unlikely event of internal

attitude failure. The GMC 605 attitude source requires either air data or GPS data for calculation of the

aircraft attitude.

Airspeed and Altitude Information – The GFC 600 requires airspeed and altitude information. It may be

interfaced to an external air data computer. If an external air data computer is not available, a small Air

Data Module will be attached to the back of the GMC 605 rack to provide basic air data information to the

GFC 600.

Pilot commands to the AFCS are entered through the GMC 605 autopilot mode panel.

Other components of the AFCS include the GSA 87 pitch, roll, pitch trim, and optional yaw servos that

also contain autopilot processors, control wheel mounted elevator trim switch, control wheel mounted

autopilot / yaw damper disconnect and trim interrupt switch (AP DISC / TRIM INT), Control Wheel

Steering switch (CWS), and a Go-Around (GA) switch.

The following conditions will cause the autopilot to automatically disconnect:



Electrical power failure, including pulling the AUTOPILOT circuit breaker.

190-02011-11 Rev. 2

Section 7 – System Description

GFC 600 Autopilot Installed in Piper PA-46-310P/350P

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