Full Authority Digital Engine Control (FADEC)

 

Full Authority Digital Engine Control (FADEC) 

 

FADEC is an electronic system consisting of a digital computer and ancillary components that control an aircraft’s engine and propeller. FADEC was first used in turbine-powered aircraft, and referred to as Full Authority Digital Electronic Control, these sophisticated control systems are increasingly being used in piston powered aircraft. 

 

In a spark-ignition reciprocating engine speed, temperature, and pressure sensors are used by FADEC to monitor the status of each cylinder. The ideal pulse for each injector is calculated by a digital computer and this adjusts the ignition timing as necessary to achieve optimal performance. FADEC operates similarly and performs all of the same functions, excluding those specifically related to the spark ignition process in a compression-ignition engine.

Aircraft Equipped With FADEC

 

 

The need for magnetos, carburetor heat, mixture controls, and engine priming is eliminated by FADEC system. FADEC system equipped aircraft is characterized by a single throttle lever. The pilot simply changes the positions of throttle lever to a desired detent, such as start, idle, cruise power, or max power, and there is no need for the pilot to monitor or control the fuel-air mixture is not necessary to monitor for the aircrafts equipped with FADEC system adjusts the engine and propeller automatically for the mode selected as per situation. 

 

During the starting of an aircraft, the cylinders, adjustment of mixture, and positions the throttle based on engine temperature and ambient pressures are primed by FADEC. The FADEC constantly monitors the engine and adjusts fuel flow and ignition timing individually in each cylinder during the cruise flight. The combustion process is precisely controlled by FADEC and thus results in increased horsepower and decreased fuel consumption. 

 

In modern flights FADEC systems are considered an essential part of the propeller and engine control and can be powered by the aircraft’s main electrical system. FADEC uses power from a separate generator connected to the engine in many aircraft. There must be a backup electrical source available because failure of a FADEC system could result in a complete loss of engine thrust and to prevent this there must be a separate power source for FADEC. Two separate and identical digital channels are incorporated for redundancy to prevent loss of thrust. 

 

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