2023 Atec 212 Solo

Technical details

Spacious monocoque fuselage is made of carbon composite, reinforced with carbon bars and honeycomb sandwich bulkheads. The aircraft is equipped with ROTAX 582 DCDI engine of 65 HP mounted on front fireproof bulkhead. Also four stroke ROTAX 912 UL 80 HP engine can be optionally installed. The fuel tank capacity is 50L. It is inbuilt under pilot’s legs in the cabine. The dashboard is equipped with a complete set of standard flight and engine control instruments. Upholstered pilot seat is made of ergonomically shaped PU foam.

Tailplanes of classical arrangement are integral part of the fuselage. The rigid construction of carbon sandwich with NOMEX honeycomb is applied. The elevator is controlled by push-rods and can be electrically trimmed. The rudder is controlled by steel wire ropes.

The trapezoidal wings are fixed together in the area of mainspar of CrMo steel. Ailerons and flaps are controlled by push-rods. The flaps are electrically controlled by neutral down to three deflected positions.

The landing gear is in classical configuration with steerable tail wheel. The main gear is designed as a pair of leaf composite springs. The size of main gear wheels is 350 x 120 mm. The wheels are equipped with brake discs and aerodynamic cowlings.

By its performance, manoeuvrability and rigidity, the ATEC 212 SOLO exceeds usual design standards applied within its microlight category.

Basic characteristics

Specification

Wing span 7,48 m

Length 5,2 m

Height 1,55 m

Wing area 7,27 m2

Tail span 2,18 m

Empty weight 200 kg

Max. take-off weight 300 kg

Fuel capacity 2 x 35 L

Performance (ROTAX 912, 100 HP)

Cruising speed VC 260 km/h / 140 kt

Never exceed speed VNE 310 km/h / 167 kt

Stall speed (flaps extended) VS0 50 km/h / 27 kt

Stall speed (flaps retracted) VS1 70 km/h / 38 kt

Max. horizontal speed VH 290 km/h / 157 kt

Rate of climb 8,5 m/s / 1680 FPM

G-load limit +6 / -4

Flight range 900 km

Fuel consumption (140/180 km/h) 12 L/h