TYPE: Tandem-seat ultralight/kitbuilt.

PROGRAMME: Designed and built as ultralight prototype by Peter Podešva; 80 per cent scale replica of Czechoslovak Zlin 126 Trener (member of Zlin 26 family, which was produced between late 1940s and mid-1970s). Production version built by son, Tomáš Podešva at Hranice; certified and distributed by Fläming Air; second aircraft (OK-FUD 01) exhibited at ILA, Berlin, June 2000. Type certificate awarded 18 February 2003 in Czech Republic, 18 February 2004 in Germany and 4 February 2005 in France.

CURRENT VERSIONS: Ultralight: Wooden wings; MTOW limited to 450 kg (992 lb). Also available as kit, meeting '51 per cent rule'.
Experimental: Metal wings; 520 kg (1,146 lb) MTOW; kitbuilt.
Akro: Version with all-metal wing and tailplane. Fluted aileron skins and split flaps; fabric-covered elevator. Three-piece canopy, plus windscreen, public debut (D-EETB) at Berlin, May 2004.

COSTS: Ultralight: kit EUR41,667; complete example with engine EUR59,524. Experimental: EUR52,530; with retractable landing gear EUR53,372. Akro kit EUR46,578 (all 2006).

DESIGN FEATURES: Low wing with sweptback leading-edge and unswept trailing-edge; mid-mounted, braced tailplane. Replica of Zlin 126 aerobatic trainer to 80 per cent scale, except full-scale cockpit.

FLYING CONTROLS: Conventional and manual. Split flaps. Flight-adjustable tabs on both elevators; ground-adjustable tab on rudder and port aileron.

STRUCTURE: Steel tube fuselage with fabric covering, except for sheet metal upper surface and engine cowling; fabric-covered empennage. Wings wood or metal, according to version, with aluminium leading-edge and fabric covering. Composites nose fairing.

LANDING GEAR: Tailwheel type; fixed. Wing-mounted, trousered, cantilever sprung main legs. Mainwheels 5.00-5; tailwheel 200x50. Hydraulic brakes.

POWER PLANT: One 55.1 kW (73.9 hp) Walter Mikron III four-cylinder, in-line piston engine driving a Kremen two-blade, variable-pitch (electric), wooden propeller or Woodcomp fixed-pitch propeller. (VZLÚ two-blade wooden propeller on prototype.) Option to fit LOM engines in Experimental version. Fuel capacity 35 litres (9.2 US gallons; 7.7 Imp gallons).

AVIONICS: To customer's specification.

EQUIPMENT: Optional rescue system.

DIMENSIONS, EXTERNAL:

• Wing span: 8.68 m (28 ft 5¾ in)
• Length overall: 6.52 m (21 ft 4¾ in)
• Height overall: 1.80 m (5 ft 10¾ in)

AREAS:

• Wings, gross: 10.80 m² (116.3 sq ft)

WEIGHTS AND LOADINGS (UL: Ultralight, E: Experimental):

• Weight empty: UL: 296 kg (653 lb)
• E: 380 kg (837 lb)
• Max T-O weight: UL: 450 kg (992 lb)
• where regulations permit: 472,5 kg (1,041 lb)
• E: 600 kg (1,322 lb)

PERFORMANCE (UL, E, as above):

• Never-exceed speed (V_NE):
• UL: 121 kt (225 km/h; 139 mph)
• E: 178 kt (330 km/h; 205 mph)
• Cruising speed at 75% power:
• UL: 94 kt (175 km/h; 109 mph)
• E: 124 kt (230 km/h; 143 mph)
• Stalling speed:
• UL: 36 kt (65 km/h; 41 mph)
• E: 45 kt (83 km/h; 52 mph)
• Max rate of climb at S/L: 270 m (886 ft)/min
• Max range: 432 n miles (800 km; 497 miles)
• g limits:
• UL: +4/-2
• E: +6/-3