Pilot's Guide

190-00663-03 Rev. A
Garmin G1000 Pilot’s Guide for the Beechcraft C90A/GT/GTi
409
AUTOMATIC FLIGHT CONTROL SYSTEM
SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM
7.1 AFCS OVERVIEW
NOTE: The approved Pilot’s Operating Handbook (POH) and FAA Approved Airplane Flight Manual (AFM)
always supersedes this Pilot’s Guide.
The Garmin AFCS is a digital Automatic Flight Control System (AFCS), fully integrated within the G1000
System avionics architecture. The System Overview section provides a block diagram to support this system
description. Garmin AFCS functionality is distributed across the following Line Replaceable Units (LRUs):
• GDU 1040A Primary Flight Displays (PFDs) (2)
• GMC 710 AFCS Control Unit
• GIA 63W Integrated Avionics Units (IAUs) (2)
• GSA 81 AFCS Servos (4)
• GSM 85A Servo Mounts (4)
The Garmin AFCS can be divided into these main operating functions:
• Flight Director (FD) — The Beechcraft C90A/GT has two flight directors, each operating within an IAU and
referred to as pilot-side and copilot-side. Commands for 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
• 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
Heading Reference System (AHRS) attitude and rate information, and airspeed.
• 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.
• Manual Electric Pitch Trim (MEPT) — The pitch trim servo provides manual electric pitch trim capability
when the autopilot is not engaged.