For Training Purposes Only
Sept 04
2-1
P I L O T T R A I N I N G G U I D E
AUTOMATIC FLIGHT CONTROL SYSTEM
INTRODUCTION
The Primus 2000XP includes an Automatic Flight Control System (AFCS) that
provides dual channel autopilots, dual yaw dampers, dual flight directors and
automatic pitch trim. The autopilot and yaw damper functions operate in an active
standby mode, with only one channel active at a time. All computations are performed
by two Flight Guidance Computers (FGC), located in the Integrated Avionics
Computer (IAC). The FGC receives inputs from the Electronic Flight Instrument
System (EFIS), the Air Data Computers (ADC), the Inertial Reference System (IRS),
the Flight Management System (FMS), the Fault Warning Computer (FWC) and the
Data Acquisition Unit (DAU).
DESCRIPTION
All computations are performed by the FGCs which are located in IAC1 and IAC2.
The FGCs receive inputs from the following through the Avionics Standard
Communications Bus:
•
Flight Management System
•
Electronic Flight Instrument System
•
Inertial Reference System
•
Fault Warning Computer
•
Data Acquisition Units
•
Micro Air Data Computers
GUIDANCE PANEL
The AFCS functions controlled by the FGC include:
•
Flight director modes
•
Pitch wheel references
•
Engagement of the autopilot and yaw damper functions
•
Selection of left or right Primary Flight Display (PFD) data to be used by FGC
