title: ATEC 212 Solo
text: # 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.
  
  ## Design and development
  
  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.
  
  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.
  
  ## Specifications (212 Solo)
  
  Data from Bayerl
  
  General characteristics
  
  * Crew: one
  * Wingspan: 7.48 m (24 ft 6 in)
  * Wing area: 7.27 $m^2$ (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 $kg/m^2$ (8.87 lb/sq ft)
  