The design of the Parandeh Abi, Blue Bird in English, recreational and training aircraft was begun in 1994 and the first flight was on 27 July 1998. The designer was Mohammad Hassan Karami.

 

It is a conventionally laid out low wing single-engine monoplane, built entirely from composite materials and seating two side-by-side. Its two spar wings and single spar horizontal tail are rectangular in plan. The wing carries 2.5° of dihedral and the tips are slightly upturned. Plain flaps fill the trailing edges inboard of the ailerons. The elevators are horn balanced, as is the rudder. Together, the fin and rudder are straight tapered, with a small dorsal fillet.

 

 

The Parandeh Abi is powered by a Rotax 914 F3 horizontally opposed four-cylinder engine driving a thee-bladed propeller. Its fixed, self-sprung steel cantilever tricycle undercarriage is attached to the fuselage. All wheels have speed fairings. In early production aircraft, access to the cabin was via the top hinged, upward opening canopy, but later examples have forward hinged doors reaching down almost to the wing. The doors contain a framed window, though the total cabin transparency is noticeably reduced. All models have a pair of small, fixed windows in the tapering fuselage behind the seats, where there is a baggage compartment. The aircraft can be equipped with either a stick or yoke for primary control. Other differences between early and later production models include improved engine cooling with the addition of chin and cheek air intakes, enlarged rudder horn balances, tailplane root fillets and fluted skinning on the ailerons and rudder.

 

The design was type certified to JAR-VLA standards.

 

Production of the Parandeh Abi began in 2001 with orders for 5 from Iranian flying clubs. By March 2006 Dorna had orders for 14 and options on another 30 and by November 2008 28 had been built at a unit cost of €120,000. As well as supplying clubs and training centres, Parandeh Albis also went to the Iranian Police and to the Civil Aviation Organisation.

 

By the end of 2012 the company's website was gone and the domain was for sale. The company may no longer be in business.

 

Engine: 1 × Rotax 914 F3

Propeller: 3-bladed MT-Propeller MTV-6-A/172-8, 1.72 m (5 ft 8 in) diameter

Wingspan: 9.45 m (31 ft 0 in).

Wing area: 11.06 m² (119.0 sq ft) gross

Airfoil: NACA 63-215

Length: 6.17 m (20 ft 3 in)

Height: 2.70 m (8 ft 10 in)

Empty weight: 490 kg (1,080 lb)

Max takeoff weight: 750 kg (1,653 lb)

Fuel capacity: 120 L (26.4 Imp gal, 31.7 US gal)

Maximum speed: 282 km/h (175 mph; 152 kn) at 4,267 m (14,000 ft)

Cruise speed: 161 km/h (100 mph; 87 kn) economical, at 3,658 m (12,000 ft)

Stall speed: 83 km/h (52 mph; 45 kn) sea level, flaps down

Never exceed speed: 321 km/h (199 mph; 173 kn)

Range: 1,094 km (680 mi; 591 nmi) with maximum fuel

Service ceiling: 4,265 m (13,993 ft)

Rate of climb: 3.8 m/s (750 ft/min) at sea level

Crew: one

Capacity: one passenger