• S1
  • S2
  • S3
  • Solo dashboard
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  • S8

Is a single-seater, cantilever low-wing aircraft of all composite construction.
High volume of carbon together with honeycomb sandwich reinforcement provide a very low weight, but high strength and rigidity.
It’s design is derived from well-proven ZEPHYR 2000 and ATEC 321 FAETA.
Especially, there are Faeta shortened wings of SM 701 profile with high-efficient slotted flaps applied.

(ROTAX 582 DCDI, 65 HP)

Useful load 100 kg
G-limits +6 / -4
Stall speed 65 km/h / 35 kt
Min. no-flap speed 77 km/h / 42 kt
Cruising speed 220 km/h / 120 kt
Never exceed speed 290 km/h / 159 kt
Rate of climb 7 m/s / 1380 ft/min
Fuel consumption (140/180 km/h) 15 L/h


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 50 L


  • 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 / 100 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.
The new wild "american super-eagle" ATEC 212 SOLO is heading to USA.
  • This plane is equipped with classical analogue instruments, but fitted with 100HP Rotax 912 S and 2-blades FITI Eco
  • Competition propeller. 
  • This configuration provides SOLO with exceptional high performance.
  • This single-seater plane has no competitors within its category by its streamlined, very manoeuvrable airframe and high-performanced propulsion.
  • Comparing previous SOLO version, the new "eagle" has two wingtanks of 70L total capacity, spacious upholstered cockpit and new comfortable seat made of memory 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.