The IAR-46 is a very light two-seater airplane for flight school, training and tourism, developed from the ICA IS-28. Construction is conventional riveted joints. Seats are arranged side by side, the left seat as the main, low trepezoidal wing, empennage in “T” semi-retractable landing gear, with skid wheel connected with the rudder.
Definition phase and marketing studies started early 1991 and detail design began late 1991.
DESIGN FEATURES: Low-wing monoplane; GA(W)-1 aerofoil section) with high aspect ratio; raked tips; T tail. Dihedral 2° from centre-section; incidence 4° at root; no twist. Foldable horizontal tail surfaces.
FLYING CONTROLS: Conventional and manual. Actuation by pushrods and cables; trim tab in each elevator. Manually operated plain trailing-edge flaps.
STRUCTURE: All-metal except fabric covering on elevators and rudder and GFRP for non-stressed fairings. Wing has main and auxiliary spars. Fluted aluminium skins on ailerons and flaps.
LANDING GEAR: Retractable (manual/mechanical) single mainwheels with hydraulic shock-absorbers and hydraulic, toe-operated disc brakes; steerable, non-retractable tailwheel rubber-in-compression shock-absorption. Rearward-retracting 5.00×5 Matco or Cleveland mainwheels, with 360×110 tyres, pressure 3.00 bar (43.5 lb/sq in). Tost 210×65 tailwheel and tyre, pressure 2.50 bar (36 lb/sq in).
POWER PLANT: One 59.6 kW (79.9 hp) Rotax 912 F3 (IAR-46) or 73.5 kW (98.6 hp) Rotax 912 S3 (IAR-46S) flat-four engine, with 2.43:1 reduction gearing to a Hoffmann HO-V352F/170FQ two-blade variable-pitch propeller (‘170FQ+6 in IAR-46S). Fuel in single tank in fuselage, capacity 70 litres (18.5 US gallons; 15.4 Imp gallons).
ACCOMMODATION: Two adjustable backrest seats side by side; dual controls standard; adjustable rudder pedals. Fixed windscreen and rearward-sliding jettisonable canopy. Baggage compartment aft of seats. Cockpit heated and ventilated.
SYSTEMS: Electrical power supplied by 250 W 14 V DC alternator and 12 V 25 Ah battery. Hydraulic system for mainwheel brakes only, with parking brake valve.
AVIONICS: Instrumentation: Standard VFR instrumentation to JAR 22.1303 and JAR 22.1305. Options include horizon and directional gyros, turn co-ordinator and Becker nav/com and transponder avionics package.
EQUIPMENT: Anti-collision and position lights standard; ground power receptacle optional.
A development phase was initiated mid-1992 with the first of two prototypes (YR-1037) shown at the Paris Air Show June 1993 and made first flight November that year.
Following flight test evaluation, static test and ground testing for JAR-VLA compliance, development of 02 second prototype began at end of 1995. This aircraft (YR-BVC) made first flight in April 1997.
The manufacturer’s preliminary flight test programme was completed in August 1999 and JAR-VLA certification (Utility category) by Romanian CAA, began mid-1998, was received November 1999, with YR-BVC registered to Airclub Romania in August 2000.
FAA certification was expected in September 2000 but apparently still awaited in mid-2003. Three further production aircraft were built and stored by late 1998, eventually registered in April 2001. The first three (c/n 03 to 05) were registered to Airclub of Romania in April 2001.
IAR-46
Engine: Rotax 912 F3/A3, 58 kW (78 hp)
Propeller: 2-bladed Hoffmann HO-V352F/170FQ, 1.7 m (5 ft 7 in) diameter
Wingspan: 11.42 m (37 ft 6 in)
Wing area: 13.87 sq.m (149.3 sq ft)
Aspect ratio: 9.403:1
Airfoil: GA(W)-1
Height: 2.15 m (7 ft 1 in)
Length: 7.85 m (25 ft 9 in)
Empty weight: 530 kg (1,168 lb)
Max takeoff weight: 750 kg (1,653 lb)
Fuel capacity: 78 L (21 US gal; 17 imp gal)
G limits: +4.4, -2.2
Cruise speed: 150 km/h (93 mph, 81 kn) (econ cruise)
Stall speed: 78 km/h (48 mph, 42 kn)
Never exceed speed: 270 km/h (170 mph, 150 kn)
Range: 800 km (500 mi, 430 nmi) (no reserve)
Service ceiling: 5,000 m (16,000 ft)
Rate of climb: 4.30 m/s (846 ft/min)
Wing loading: 54.1 kg/m2 (11.1 lb/sq ft)
Power/mass: 12.58 kg/kW (20.67 lb/hp)
Rate of climb: 4.30 m/s (846 ft/min)
Crew: 2
IAR-46S
Engine: Rotax 912 S3, 73.5 kW (98.6 hp)
Wingspan: 11.42 m (37 ft 6 in)
Wing area: 13.87 sq.m (149.3 sq ft)
Aspect ratio: 9.403:1
Airfoil: GA(W)-1
Height: 2.15 m (7 ft 1 in)
Length: 7.85 m (25 ft 9 in)
Empty weight: 530 kg (1,168 lb)
Max takeoff weight: 750 kg (1,653 lb)
Fuel capacity: 78 L
Maximum speed: 215 km/h (134 mph; 116 kn)
Cruising speed: 170 km/h (110 mph; 92 kn) (econ cruise)
Stall speed: 78 km/h (48 mph; 42 kn)
Never exceed speed: 280 km/h (170 mph; 150 kn)
Range: 800 km (497 mi; 432 nmi) (no reserve)
Service ceiling: 5,000 m (16,404 ft)
Crew: 2
All Aero 