ATEC 212 Solo

The ATEC 212 Solo is a Czech ultralight aircraft, designed and produced by ATEC v.o.s. of Libice nad Cidlinou. The aircraft is supplied as a complete ready-to-fly-aircraft.^[1]^[2]

Design and development[edit]

The aircraft 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.^[1]^[2]

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.^[1]^[2]

Data from Bayerl^[1]^[2]

General characteristics

Crew: one
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)
Powerplant: 1 × Rotax 582 twin cylinder, liquid-cooled, two stroke, 48 kW (64 hp)
Propellers: 3-bladed composite

Performance

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)

^ ^a ^b ^c ^d Bayerl, Robby; Martin Berkemeier; et al: World Directory of Leisure Aviation 2011-12, page 28. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X
^ ^a ^b ^c ^d Tacke, Willi; Marino Boric; et al: World Directory of Light Aviation 2015-16, page 29. Flying Pages Europe SARL, 2015. ISSN 1368-485X