The ATEC 212 Solo Czech ultralight aircraft, designed and produced by ATEC v.o.s. of Libice nad Cidlinou, was designed to comply with the Fédération Aéronautique Internationale microlight rules. It features a cantilever low-wing, a single-seat, enclosed cockpit with a bubble canopy, fixed conventional landing gear and a single engine in tractor configuration.

 

 

The 212 Solo is made from carbon fibre and was derived from the ATEC 321 Faeta and ATEC 122 Zephyr 2000 designs. Its 7.48 m (24.5 ft) span wing employs an SM701 airfoil and slotted flaps. Standard engines available are the 64 hp (48 kW) Rotax 582 two-stroke and the 80 hp (60 kW) Rotax 912UL four-stroke powerplant.

 

The aircraft was supplied as a complete ready-to-fly-aircraft.

 

Engine: 1 × Rotax 582, 48 kW (64 hp)

Propeller: 3-bladed composite

Wingspan: 7.48 m (24 ft 6 in)

Wing area: 7.27 m² (78.3 sq ft)

Empty weight: 200 kg (441 lb)

Gross weight: 315 kg (694 lb)

Fuel capacity: 50 litres (11 imp gal; 13 US gal)

VNE: 157 kt / 180 mph / 290 kmh
Maximum speed: 250 km/h (160 mph, 130 kn)

Cruise speed: 220 km/h (140 mph, 120 kn)

Stall speed: 65 km/h (40 mph, 35 kn)

Rate of climb: 7 m/s (1,400 ft/min)

Wing loading: 43.32 kg/m² (8.87 lb/sq ft)

Crew: one