The ATEC 321 FAETA is an aerodynamically refined cantilever low-winged all composit aircraft with a high content of carbon fibre. The ultralight modification is a basic one of the project series of very light sport planes of a derived design. Swift and manoeuvrable aircraft providing over standard comfort for a two-person crew and a safe sensation in the spacious cockpit. The low-weight but rigid airframe makes possibility equipe aircraft with a high-speed parachute rescue system without a drastic loss of payload. The adequate wing area together with an efficient slotted flap give the plane be able fly with an extremely low speed.

The WING is a reinforced shell of a carbon-fibre sandwich. The tapered backswept wing of a SM 701 airfoil along the all span. The all composite main wing spar is equipped with carbon flanges designed for a high safety factor. The high efficient slotted flap has been developed using latest methods of computer design engineering. All external details of wing like flap hinges, slots, Pitot tube attachement, wing tips have been shaped with respect for minimum air drag.

The FUSELAGE is a carbon-fibre shell braced by multi-layer wooden bulkheads. The cross-section is elliptic with pure wing fillets and a spacious cabin. The hinged perspex canopy can swing upwards and backwards. The engine which is in the front part of the fuselage is separated by the firewall, to which the engine bearer attachment and the steerable nosewheel are attached.

The TAIL UNIT all composite arranged in T-shape. The tapered horizontal tail surface with an elevator is constructed in a way similar to that of a wing. The tapered vertical tail surface is a monolithic part of the fuselage shell. The rudder suspended from the last fuselage bulkhead is completely of composites.

The LANDING GEAR is a fixed three-wheeled construction with a steerable nose wheel. The main gear is constructed as a pair of leaf springs of composites. The front leg is made of composites and metal tubes. The main wheels are equipped with disc brakes. The size of main tyres: 350x120 mm, while that of front tyre is 300x100 mm. All wheels have aerodynamic fairing.

The CONTROL. Dual control of all the rudders. The ailerons, flaps and elevator are controlled through the control rods and levers, the rudder through the steel wire ropes. All the control attachments are situated within the airframe. The important checking points in the wings are equipped with inspection holes with a perspex covering.

The ENGINE of standard option is ROTAX 912 UL 80 HP or ROTAX 912 SUL 100 HP that drives a FITI three or two blade propeller ground adjustable. The engine bed attachment is welded of the first-rate-quality CrMo steel tubes.

The FUEL SYSTEM consists of the fuel tank integrated in the fuselage and the piping connection equipped with a sediment bowl and a drain plug. The pressure of the fuel is measured by a fuel-pressure gauge.

The ISTRUMENTATION consists of basic flight, engine and navigation checking instruments. The static and dynamic pressure is taken from the Pitot tube attached below the port wing.
> Wing span 9,6 m   > Length 6,2 m
> Height 2,0 m   > Wing area 10,1 m2
> Tail span 2,4 m   > Wheel spacing 2,0 m
> Empty weight 275 kg   > Max. take off weight 450 / 472,5 kg
> Fuel capacity 70 l
(ROTAX 912 ULS, 450 kg)
> Useful load 175 kg   > G limits +5g / -2g
> Stall speed 60 km/h 34 kt   > Min. no-flap speed 75 km/h 40 kt
> Cruising speed 230 km/h 124 kt   > Max. level speed 255 km/h 138 kt
> Never exceed speed 275 km/h 148 kt   > Rate of climb 7 m/s 1375 FPM
> Fuel consumpsion
140/180 km/h