Cirrus Garmin GFC 700 Manuals
1 pdf manual(s) Cirrus Garmin GFC 700 for free download (Document Types: Maintenance manual)
Cirrus Garmin GFC 700 Maintenance manual [PDF] (42 pages)
- Identifier: id-1546681
- Brand: Cirrus
- Device: Cirrus Garmin GFC 700 Control Systems
- Type: Maintenance manual, PDF
- Key Aspects: System Connectivity and Wiring Basics, Hardware Verification Checklists, Technical Support and Resource Links
- UPD Date: 16.07.2026
- Source File: 1454594.pdf
- Pages: 42
- Description: Operational manual for the Cirrus Garmin GFC 700.
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CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 22-10: GFC 700 AUTOMATED FLIGHT CONTROL SYSTEM MODELS SR22 AND SR22T GENERAL 1 GFC 700 Automated Flight Control System 22-10: GFC 700 AUTOMATED FLIGHT CONTROL SYSTEM 1. General (See Figure 22-10-1) This section covers those systems and components which use inputs to the system to automati- cally control the flight path of the aircraft through adjustment to the pitch, roll, and yaw axes or wing lift characteristics and provide visual cues for flight path guidance. This includes the Garmin GFC 700 Autopilot system. A. GFC 700 Autopilot The Garmin GFC 700 digital Automatic Flight Control System (AFCS) Autopilot system is a fully digital, dual channel, fail-passive digital flight control system composed of multiple Line-Replaceable Units (LRUs) and servos. The GFC 700 is fully integrated within the Perspective+ Integrated Avionics System architecture and is used to stabilize aircraft pitch, roll, and yaw (optional) axes. Pitch autotrim provides trim commands to the pitch trim servo to relieve any long-term effort required by the pitch servo. The system consists of the following components: • GMC 707 Automatic Flight Control System (AFCS) Mode Controller • GCU 479 Flight Management System (FMS) Keyboard • Pitch Servo • Pitch Trim Servo • Roll Servo • Yaw Servo (Optional) • Dual GIA 63W Integrated Avionics Computers • GTA 82 Pitch Trim Adapter • 4-Way Trim Switch • Autopilot Disconnect Switch • Take-Off/Go-Around (GA) Switch The GIA 63W Integrated Avionics computer contains Autopilot/Flight Director algorithms and the MFD/PFD provides autopilot annunciation. The GSU 75 ADAHRS provides valid atti- tude, angular rate and acceleration information, and air data for flight instrumentation. The GSA 80 and GSA 81 servos are used in the pitch, roll, and yaw (optional) axes. The servos position the aircraft controls in response to commands generated by the internal GIA 63W autopilot calculations. The GTA 82 pitch trim adapter drives the pitch trim cartridge. The 23 Dec 2016
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