The ZEPHYR is an aerodynamically refined cantilever low-winged mixed-construction aircraft with a fixed tricycle undercarriage and side-by-side seating. Its flight performance places it among the latest generation of ultralight aeroplanes. Over 70 aircraft have been manufactured and succesfully operated. It is available in Europe, North America and Australia. The ZEPHYR's super-light modifications have been on offer since 2001 using hi-tec carbon fibre technology providing top flight comfort for a two-person crew not exceeding UL weight limits.

The WING has a mixed cantilever construction with a UA-2 laminar-flow . The rectangular wing plane in the root area goes over into the tapered wing ended in
a wing-tip. The main spar made of multi-layer reinforced wood is placed at a depth of 30% of the wing. The ailerons and flaps are suspended from the rear auxiliary spar. The leading edge is covered by a composite sandwich as far as the main spar. The rest of wing is covered by PES-fabric. The central framework welded from high-grade steel tubes is built in the fuselage.
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 has a mixed construction made of glasslaminate and wood 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 glass-laminated.
The UNDERCARRIAGE is a fixed three-wheeled construction with a steerable nose wheel. The main undercarriage is constructed as a pair of leaf springs of glass laminate. The front leg is made of composits and metal tubes. The main wheels are equipped with brakes. The size of main tyres: 380x100 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 performance ranges between 48 to 75 kW. The engine suitability depends on dimensions, weight and other properties. The standards recommended are the ROTAX 912 UL, 912 ULS used by the manufacturer.
The FUEL SYSTEM consists of the fuel tank integrated in the fuselage and the piping convection 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 270-280 kg   > Max. take off weight 450 kg
> Fuel capacity 60 l (altern. 80 l)
(ROTAX 912 ULS, 450 kg)
> Useful load 180-170 kg   > G limits +4g / -2g
> Stall speed 65 km/h   > Min. no-flap speed 75 km/h
> Cruising speed 180 km/h   > Max. level speed 245 km/h
> Never exceed speed 265 km/h   > Rate of climb 6,5 m/s
> Fuel consumpsion 140/180 km/h 7/12 l/h