TYPE: Primary prop trainer/sportplane.

PROGRAMME: Intended for domestic market to avoid dependence on foreign imports; prototype (originally known as IR-02) made first flight on 3 June 1997; second had been built by 3 January 1999 when one was lost in a fatal accident while testing an emergency parachute. Series production launched in 2000. Iranian certification to JAR-VLA (Normal category) standard was awarded on 16 August 2000. Made its public debut (fourth aircraft shown) at the Iran International Air Show in October/November 2002. Four completed by early 2003; no later total provided by mid-2006.

CUSTOMERS: Four ordered by a flying school in Iran. 10 on option for a government institute.

DESIGN FEATURES: Similar configuration to US Van's RV-6A, but with greater wing span; meets JAR 22 and JAR-VLA standards. Intended for pilot training, general aviation, surveillance and recreational flying.
NASA aerofoil sections: 632-215 (wing), 632-015 (horizontal tail) and 63-010 (vertical tail).

FLYING CONTROLS: Conventional and manual. Balanced ailerons; horn-balanced elevators. Trim tab in port elevator. Electrically actuated single-slotted flaps.

STRUCTURE: Mainly aluminium alloy; steel alloys in some areas. Single-spar wings. Glass fibre engine cowling and wingtip fairings.

LANDING GEAR: Tricycle type; fixed. Fuselage-mounted spring steel tube cantilever mainwheel legs with 5.00-5 tyres; trailing link, castoring nosewheel on spring steel tube cantilever leg with shimmy damper; tyre size 10X3.50-4. Hydraulic mainwheel disc brakes. Streamlined composites fairings over all three wheels.

POWER PLANT: One Textron Lycoming O-320-B2B flat-four engine (119 kW; 160 hp at 2.700 rpm), driving a Sensenich M 74 DM two-blade, fixed-pitch metal propeller. Optional 112 KW (150 hp) Lycoming O-320-E2D. Integral fuel tank in each wing, combined capacity 120 litres (31.7 US gallons; 26.4 Imp gallons).

ACCOMMODATION: Two seats side by side. Dual controls. Wraparound windscreen; one-piece rearward-sliding canopy. Cabin heated and ventilated. Rear baggage compartment with internal access.

SYSTEMS: 12 V electrical system.

AVIONICS: To customer requirements: can include Bendix/King KX 155 VHF nav/com radio, ELT, and ADF/VOR/GPS.


  • Wing span: 8,74 m (28 ft 8 in)
  • Wing chord, constant: 1,24 m (4 ft 0¾ in)
  • Wing aspect ratio: 7.0
  • Length overall: 6,02 m (19 ft 9 in)
  • Height overall: 2,04 m (6 ft 8¼ in)
  • Propeller diameter: 1,88 m (6 ft 2 in)


  • Wings, gross: 10.87 m² (117.0 sq ft)
  • Vertical tail surfaces (total): 1.04 m² (11.19 sq ft)
  • Horizontal tail surfaces (tatal): 2.40 m² (25.83 sq ft)


  • Weight empty: 500 kg (1,102 lb)
  • Max T-O and landing weight: 750 kg (1,653 lb)
  • Max wing loading: 69,0 kg/m² (14,13 lb/sq ft)
  • Max power loading: 6,29 kg/kW (10,33 lb/hp)


  • Max level speed at S/L: 140 kt (259 km/h; 161 mph)
  • Max cruising speed, 75% power: 135 kt (250 km/h; 155 mph)
  • Stalling speed, flaps down: 45 kt (84 km/h; 52 mph)
  • Max rate of climb at S/L: 457 m (1,500 ft)/min
  • Service ceiling: 6.400 m (21.000 ft)
  • T-O run: 250 m (820 ft)
  • Range with max fuel: 540 n miles (1.000 km; 621 miles)