MAGIC Avionics

Source: Meggitt Avionics, Inc.

MAGIC Avionics
The Meggitt Avionics new generation integrated cockpit (MAGIC) features solid-state sensors and LCD displays and is designed for smaller aircraft
Meggitt Avionics, Inc. Avionics new generation integrated cockpit (MAGIC) features solid-state sensors and LCD displays and is designed for smaller aircraft. The suite is flying on the Piper Malibu Meridian and has been selected for the Century Aerospace CA-100, American Utilicraft FF-1080-200 and Visionair VantageVA-10.

The suite includes the following components:

  • Primary Flight Display (PFD) displays all information needed to fly the aircraft. It receives data from various external sensors to display pitch and roll attitude, rate of climb, airspeed, heading, ILS (LOG/GS), sideslip and baro set. (In the unlikely event that the PFD fails all of this data will be presented on the Navigation Display (ND).
  • Navigation Display (ND) shows all required navigation modes; compass rose (HSI), MAP and ARC. Data is received from a number of systems including the GPS, radio receivers (VOR and ADF) and the Heading System. Outputs for an autopilot are provided. Mode, heading and course selection controls are on the bezel of the ND.
  • Two redundant Engine Display Units (EDU) show all necessary information for operation of turbine engines including fuel quantity and usage calculations. Engine parameters are normally displayed in both analog and digital format using color to highlight exceedance conditions. Displayed parameters include Torque (TQ), Inter Turbine Temp (ITT), Power Turbine RPM (NP), Gas generator RPM % of maximum (NG), Vacuum Suction (VAC), Oil Temp/Pressure, Fuel Quantity, Fuel Flow (FF), Fuel At Destination (FAD), Time To Destination (TTD), and Outside Air Temperature (OAT). Each EDU also has a selectable reversionary mode where all the data from both screens is compressed and displayed on one screen.
  • A separate Data Acquisition Unit (DAU) converts all analog signals from the engine sensors and fuel probes to digital format, which it transmits via ARINC 429 buses to the EDUs for display. In all ADAHRS equipped aircraft the DAU can automatically record data necessary for engine condition trend monitoring.
  • The Air Data Attitude Heading Reference System is an all-solid state-sensing unit (no rotating parts). Electric signals are taken from the fluxgate to provide a total sensing package which outputs pitch and roll attitude; pitch, roll and yaw rates; altitude; rate of change of altitude (IVSI); airspeed and heading on digital data buses (ARINC 429).

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