190-00709-05 Rev. D
Garmin G1000 Pilot’s Guide for the Socata TBM 850/900
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AUTOMATIC FLIGHT CONTROL SYSTEM
SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM
NOTE: The approved Pilot’s Operating Handbook (POH) always supersedes this Pilot’s Guide.
The digital Garmin Automatic Flight Control System (AFCS) is fully integrated within the G1000 System
avionics architecture. The System Overview section provides a block diagram to support this system description.
AFCS functionality in the Socata TBM850/900 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)
• GTA 82 Trim Adapter (1)
• GSM 85 or GSM 86 servo Gearboxes (4)
The Garmin AFCS can be divided into these main operating functions:
• Flight Director (FD) — The Socata TBM850/900 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 directors provide:
– 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 and yaw trim
adapter. 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.
• Manual Electric Yaw Trim (MEYT) — The yaw trim adapter provides manual electric yaw trim capability
when the autopilot is not engaged.
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