TYPE: Two-seat lightplane.

PROGRAMME: Launched 1994; prototype manufacture started mid-1994; first flight was made on 27 July 1998; prototype had accumulated 600 hours’ flying in 800 flights by end of November 2005. Certification to JAR 21 standards by the Iranian CAO was awarded on 2 December 2001, and initial production is under way. Improved version, characterised by forward-hinged doors, was scheduled for certification in early 2005; received amendment to Type Certificate for yoke or stick type control system.

CUSTOMERS: First five production aircraft sold to Iranian civil aeroclubs for pilot training; manufacture of these began in 2001. Stated orders for 14 and options for 30 more as at March 2006.

COSTS: Programme cost by November 1998 estimated at USD1.5 million excluding R&D; basic aircraft quoted at USD137.500 for new version (2006).

DESIGN FEATURES: Conventional low-wing, fixed-gear lightplane, designed for low-cost, easy-to-fly/maintain operation.
Several revisions of detail during early production including enlarged engine cowling for improved cooling (achieved in at least two stages of modification); tailplane leading-edge root extensions; enlarged rudder horn balance; fluted (bead) skin on rudder and ailerons. By 2004, all these features applied to new version having forward-hinged doors in place of previous ‘gull wing’ type. At least one aircraft of earlier version noted with flaps of reduced span.
Wings have constant chord, NACA 63-215 aerofoil section, 2° 30' dihedral from roots, 2° incidence and -2° twist.

FLYING CONTROLS: Conventional and manual; yoke or stick available optionally. Ailerons and elevators actuated by pushrods; rudder by cables; elevators have electric trim. Electrically actuated plain flaps.

STRUCTURE: All-composites. Two-spar wing, single-spar horizontal tail, monocoque fuselage.

LANDING GEAR: Non-retractable tricycle type, with Goodyear 5.00-5 tyres (6 ply on mainwheels, 4 ply on nosewheel). Fuselage-mounted cantilever self-sprung steel leg on each unit. Cleveland mainwheel brakes. Composites speed fairings on all three wheels.

POWER PLANT: One 84.6 kW (113.4 hp) Rotax 914 F3 flat-four engine driving an MT Propeller; three-blade MTV-6-A/172-08 variable-pitch propeller at 5.800 rpm. Fuel tank in each wing, combined capacity 120 litres (31.7 US gallons; 26.4 Imp gallons); gravity filling point on each tank. Oil capaciiy 3.0 litres (0.8 US gallon; 0.7 Imp gallon).

ACCOMMODATION: Two seats side by side, with baggage compartment aft of seats. Initially with narrow hardtop roof to cabin; access via upward-opening window each side, each with smaller non-opening window to rear. Later aircraft have full-height, forward-hinged door each side.

SYSTEMS: Electrical system: 12 V 20 A integral AC generator, 12 V 40 A external alternator and 34 Ah battery.

AVIONICS: Comms: Bendix/King KX 125 nav/com; KT 76A transponder.
Instrumentation: Conventional VFR.

DIMENSIONS, EXTERNAL:

• Wing span: 9.45 m (31 ft 0 in)
• Wing chord, constant: 1.17 m (3 ft 10 in)
• Wing aspect ratio: 8.1
• Length overall: 6.17 m (20 ft 3 in)
• Fuselage max width: 1.12 m (3 ft 8 in)
• Height overall: 2.17 m (7 ft 1½ in)
• Tailplane span: 2.70 m (8 ft 10¼ in)
• Wheel track: 1.94 m (6 ft 4½ in)
• Wheelbase: 1.51 m (4 ft 11½ in)
• Propeller diameter: 1.72 m (5 ft 7¾ in)
• Propeller ground clearance: 0.18 m (7 in)

DIMENSIONS, INTERNAL:

• Cockpit: Length: 1.09 m (3 ft 7 in)
• Max width: 1.02 m (3 ft 4¼ in)

AREAS:

• Wings, gross: 11.06 m² (119.0 sq ft)
• Ailerons (total): 0.95 m² (10.23 sq ft)
• Trailing-edge flaps (total): 1.54 m² (16.58 sq ft)
• Fin: 0.42 m² (4.52 sq ft)
• Rudder: 0.37 m² (3.98 sq ft)
• Tailplane: 0.84 m² (9.04 sq ft)
• Elevators (total): 0.515 m² (5.54 sq ft)

WEIGHTS AND LOADINGS:

• Weight empty, equipped: 490 kg (1.080 lb)
• Max fuel weight: 90 kg (198 lb)
• Max T-O and landing weight: 750 kg (1.653 lb)
• Max wing loading: 67.8 kg/m² (13.89 lb/sq ft)
• Max power loading: 8.87 kg/kW (14.58 lb/hp)

PERFORMANCE:

• Never-exceed speed (V_NE): 173 kt (321 km/h; 200 mph)
• Max level speed at FL140: 152 kt (282 km/h; 175 mph)
• Max cruising speed at FL100: 130 kt (241 km/h; 150 mph)
• Econ cruising speed at FL120: 87 kt (161 km/h; 100 mph)
• Stalling speed at S/L, flaps down: 45 kt (83 km/h; 51 mph)
• Max rate of climb at S/L: 229 m (730 ft)/min
• Service ceiling: 4.265 m (14.000 ft)
• T-O run: 275 m (900 ft)
• Landing run: 244 m (800 ft)
• Range with max fuel: 590 n miles (1.094 km; 680 miles)