A320 | EFCS - Flight Controls System
In the Airbus family, in particular the A320, it was the first airliner equipped with a "fly-by-wire" flight control system. The flight control surfaces are all interpreted electrically by computers which depending on the input commands provided by the pilot or the AP, and hydraulically operated by the actuators as needed to obtain a desired response.
The introduction of the fly-by-wire system was a innovation whose objective was to increase safety (by integrating the relevant protections), reduce the Work-Load of the Pilot Flying (improving handling and comfort), and significantly reduce the total weight of the aircraft by replacing traditional cables and mechanical components, thus also improving fuel efficiency.
Furthermore, the innovative Electric Flight Control System (EFCS) also provides flight envelope protection. In fact, they do not allow flight outside the structural flight limits, set by the designers to ensure greater safety and improved control of the flight surfaces.
The A320 has a total of 11 flight computers managing the primary and secondary control surfaces.
2 ELAC [Elevator & Aileron Computer]; They control the elevators, ailerons and the horizontal stabilizer (THS).
3 SEC [Spoiler & Elevator Computer]; They control the spoilers and two of them are dedicated as backups for elevator and stabilizer control.
2 FAC [Flight Augmentation Computer]; They control rudder, rudder trim and yaw damping. It also provides wind-shear detection and low-energy aircraft status warnings.
2 SFCC [Slats & Flaps Control Computer]; They control the Flaps and Slats on the wing
2 FCDC [Flight Control Data Concentrator]; It controls and receives data from the SEC and ELAC computers and sends it directly to the ECAM.
The flight control computers process inputs from the sidestick and rudder, or the autopilot and send them to the ELACs and SECs according to flight control laws. Other inputs to the flight control computers come from the FMGC, ADIRU, radio altimeters, LGCIU and accelerometers.
If multiple failures occur in the system, the computers managing the flight surfaces reconfigure themselves with a degraded flight control law.
In the event of a complete electrical failure or a series of critical failures, the pilot can manually control the rudder and the THS (Trimmable Horizontal Stabilizer) via a mechanical link.
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CHAPTERS:
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▎00:00 - Fly-by-wire Overview
▎03:27 - Sidestick
▎05:48 - Roll Control
▎10:00 - Pitch Control
▎17:01 - Yaw Control
▎23:56 - Spoilers Control
▎31:25 - Flaps/Slats control
▎33:03 - Controls & Indications