TYPE: Side-by-side ultralight/kitbuilt.

PROGRAMME: Prototype Zephyr (OK-CUA 01). First flown 1996; production started the following year.

CURRENT VERSIONS: Zephyr: Original version, no longer available; 10.60 m (34 ft 9¼ in) wing span and 59.6 kW (79.9 hp) Rotax 912 UL engine.
Zephyr 2000: Introduced April 2001; C suffix indicates change to new shape all-carbon composites fuselage construction; shorter wing and tail spans.
Description below applies to Zephyr 2000C.
ATEC 212 Solo: Single-seat version. Prototype (OK-FUH-01) made initial flight 29 October 2000.
ATEC 321 Faeta: Maiden (OK-IUG 15) flight in February 2003; introduced at Aero '03, Friedrichshafen, April 2003. As Zephyr, but wholly of carbon fibre, including new, tapered wing with constant sweepback, differently proportioned ailerons and slotted flaps. Two-blade ground adjustable Fiti propeller and ballistic parachute. Generally as Zephyr unless otherwise indicated.

CUSTOMERS: Over 160 all versions (including some 50 kits) built and sold by April 2006. Exported to Australia, Belgium, Canada, China, Denmark, Finland, France, Germany, Greece, Ireland. Italy, Lithuania, Netherlands, New Zealand, Norway, Portugal, South Africa, Spain, Sweden, Ukraine and the US.

COSTS: Zephyr 2000: EUR44,900 with Rotax 912 UL; EUR46,900 with Rotax 912 ULS (2005); Faeta: EUR52,500 with Rotax 912 UL; EUR54,500 with Rotax 912 ULS (2005) all flyaway, excluding tax. Zephyr kit (excluding engine) EUR27,790; fast-build kit EUR22,990 extra (2006)

DESIGN FEATURES: Low-wing monoplane with T tail. Wing section UA-2 laminar flow on Zephyr 2000 and SM 701 on Faeta. Meets LSA requirements where 550 kg (1,212 lb) MTOW acceptable.

FLYING CONTROLS: Conventional and manual; spring trim. Electric flaps and elevator trim optional. Dual controls.

STRUCTURE: Zephyr 2000: Fuselage of carbon reinforced by wooden and hardened foam bulkheads; wing leading-edge of glass fibre sandwich; horizontal tail, wingtips, elevator, rudder, mainwheel legs and engine cowlings of glass fibre composites. Laminated hardwood wing main spar. Chromoly steel wing fittings; welded chromoly wing centre-section. Wing and horizontal tail trailing-edge of fabric-covered wood.
Faeta: Fuselage as Zephyr, with carbon, hardened foam and honeycomb sandwich reinforcements. Carbon sandwich wing with laminated hardwood spar; fittings and centre-section as Zephyr. Honeycomb sandwich control surfaces.

LANDING GEAR: Tricycle type, fixed. Fuselage-mounted cantilever mainwheel legs. Aerodynamic composites nosewheel leg and integral wheel fairing. Castoring nosewheel. Tyres sizes 380x100 (main), 300x100 (nose); Faeta has 350x120 main tyres. Hydraulic disc brakes. Speed fairings on all three wheels.

POWER PLANT: Zephyr 2000: One 59.6 kW (79.9 hp) Rotax 912 UL or 73.5 kW (98.6 hp) Rotax 912 ULS flat-four engine; Fiti two- or three-blade ground-adjustable pitch propeller; optional Fiti two- or three-blade in-flight-adjustable propeller with choice of mechanical or electric control. Rotax 582 UL engine optional. Fuel capacity 60 litres (15.9 US gallons; 13.2 Imp gallons) standard, 80 litres (21.1 US gallons; 17.6 Imp gallons) optional.
Faeta: Rotax 912 UL or 912 ULS. Fuel capacity 70 litres (18.4 US gallons; 15.4 Imp gallons).

ACCOMMODATION: Pilot and passenger side by side under one-piece canopy.

EQUIPMENT: Optional ballistic parachute system.


  • Wing span: 9.60 m (31 ft 6 in)
  • Length overall: 6.20 m (20 ft 4 in)
  • Height overall: 2.00 m (6 ft 6¾ in)


  • Wings, gross: 10.10 m² (108.7 sq ft)

WEIGHTS AND LOADINGS (912 ULS engine; A: Zephyr, B: Faeta):

  • Weight empty: A: 275 kg (606 lb)
    • B: 280 kg (617 lb)
  • Max T-O weight: standard: 450 kg (992 lb)
    • with ballistic parachute: 472.5 kg (1,041 lb)
    • where allowed: 550 kg (1,212 lb)


  • Max level speed: A: 132 kt (245 km/h; 152 mph)
    • B: 138 kt (255 km/h; 158 mph)
  • Max cruising speed: A: 116 kt (215 km/h; 133 mph)
    • B: 124 kt (230 km/h; 143 mph)
  • Stalling speed, flaps down: A: 36 kt (65 km/h; 41 mph)
    • B: 33 kt (60 km/h; 38 mph)
  • Max rate of climb at S/L: A: 390 m (1,280 ft)/min
    • B: 420 m (1,378 ft)/min
  • T-O run: 120 m (395 ft)
  • Landing run: 200 m (660 ft)
  • Range: standard fuel: 432 n miles (800 km; 497 miles)
    • optional fuel: 594 n miles (1,100 km; 683 miles)
  • g limits: A: +4/-2
    • B: +5/-2