DINFIA IA-50 Guarani 2

IA-50 GUARANI 2
The original FA-1 Guarani 1 was a twin-turboprop light transport designed and built under the direction of Military Aircraft Engineer Captain Hector Eduardo Ruiz, head of the design team of the Fabrica Militar de Aviones (Aircraft Factory). It utilised about 20% of the structural components of the earlier IA-35 Huanquero and flew for the first time on February 6, 1962. Full details of the Guarani I can be found in the 1962-1963 Jane's.
From it has been developed the IA 50 (formerly FA-2) Guarani 2, the first prototype of which flew for the first time on April 23, 1903 and introduced more powerful engines, de-icing equipment, a single swept fin and rudder and a shorter rear fuselage to save weight. A second prototype has been built, followed by a single pre-production machine.
The Guarani 2 is now in production for the Argentine Air Force (FAA). Current contracts cover the manufacture of 18 standard models for communications duties, two for photographic work and one furnished as an executive transport for use by the President of Argentina. Thus, with the prototypes and pre-series aircraft, a total of 24 Guarani 2's is being produced.
The pre-series machine is fitted with a Bendix M-4 autopilot, to evaluate this equipment. Production aircraft will have flight deck windows of modified size and shape, to meet the US Federal Aviation Agency's CAM-4B requirements.
Type: Twin-engined light transport.
Wings: Cantilever low-wing monoplane. Wing section NACA-63(3)218. Aspect ratio 9. Centre-section chord 9 ft 1 in (2-75 m). Dihedral 7° on outer wings only. Incidence 3° at root, 1° at tip. All-metal single-spar structure. Fabric-covered metal ailerons. All-metal split flaps. Automatic trim-tab in each aileron. Kleber-Colombes de-icing system optional.
Fuselage: Duralumin semi-monocoque structure.
Tail Unit: Cantilever all-metal structure with 52° 30' sweepback on fin. Variable-incidence tailplane. Trim-tab in rudder and each elevator. Kleber-Colombes leading-edge deicing system optional.
Landing Gear: Retractable tricycle type. Hydraulic actuation, all wheels retracting forward. Oleo-pneumatic shock-absorbers of Argentine manufacture. Each main unit fitted with two Dunlop wheels and tubeless tyres size 750 x 10. Singlo Dunlop nose-wheel with tubeless tyre size 650 x 10. Tyre pressure 45 lb/sq in (3-16 kg/cm2). Dunlop hydraulic brakes.
Power Plant: Two Turbomeca Bastan VI-A turboprop engines each rated at 930 slip plus 165 lb (75 kg) st. Ratier-Figeac FH-86 metal variable-pitch propellers, diameter 9 ft 0.25 in (2-75 m). Water-alcohol injection. Total internal fuel capacity 420 Imp gallons (1,910 litres) in integral tanks in wings. Provision for two wingtip fuel tanks, each with capacity of 75 Imp gallons (340 litres). Oil capacity 4-2 Imp gallons (19 litres) for each engine.
Accommodation: Crew of two side-by-side on flight deck. Standard seating in main cabin for 10, 12 or 15 passengers. Door with built-in steps at rear of cabin on port side. The 10-passenger executive version has a baggage compartment (port) and bar (starboard) immediately aft of flight deck; two rows of three inward-facing seats at front of main cabin and two pairs of armchair seats facing each other fore and aft with table between; toilet opposite entry door. The utility and paratroop transport has seven inward-facing seats on the port side of the cabin and eight on the starboard side. A navigation and radar training version has six seats and comprehensive equipment in the cabin. An ambulance version carries two pairs of stretchers on the port side of the cabin and one pair on the starboard side, with two seats for attendents. All versions have a forward baggage hold and galley, and a toilet at the rear.
Systems: SEMCA Type EQ-2 air-conditioning equipment. Navigation and landing lights and rotating beacon standard.
Electronics and Equipment: Radio and radar to operator's requirements. Normally two RA-21A VHF receivers, two TA-21A VHF transmitters, one RA-21A(MNA-21B) navigation system, one GSA-8A-1 glide slope receiver, one FKA-23A marker receiver, two DFA-22A ADF installations and two ASA-31A audio panels, all manufactured by Bendix; and one Eldeco 20A HF transceiver. Full blind-flying instrumentation standard. Optional equipment includes Bendix VOR ILS, automatic pilot, automatic navigation system, weather radar and oxygen equipment.
Jane's All The World's Aircraft / 1965/1966 EDITION - Edited by John W. R. Taylor
Dimensions, external:
Wing span - 64 ft 1 in (19-53 m)
Length overall - 48 ft 9 in (14-86 m)
Length of fuselage - 46 ft 10.5 in (14-29 m)
Height over tail - 19 ft 0.75 in (5-81 m)
Tailplane span - 21 ft 4 in (6-50 m)
Wheel track - 15 ft 9.5 in (4-82 m)
Wheelbase - 11 ft 1.75 in (3-40 m)
Passenger door:
Height - 4 ft 9.5 in (1-46 m)
Width - 2 ft 5 in (0-74 m)
Areas:
Wings, gross - 450 sq ft (41-81 m2)
Ailerons (total) - 38-2 sq ft (3-55 m2)
Trailing-edge flaps (total) - 51-73 sq ft (4-81 m2)
Vertical tail surfaces (total) - 60-5 sq ft (5-62 m2)
Horizontal tail surfaces (total) - 79-0 sq ft (7-34 m2)
Weights and Loading:
Weight empty, equipped - 8,650 lb (3,924 kg)
Max payload - 2,600 lb (1,180 kg)
Max T-O weight - 15,700 lb (7,120 kg)
Max landing weight - 13,800 lb (6,260 kg)
Max power loading - 7-72 lb/hp (3-5 kg/hp)
Performance (at max T-O weight):
Max level speed - 310 mph (500 kmh)
Max permissible diving speed - 320 mph (515 kmh)
Max cruising speed - 305 mph (491 kmh)
Econ cruising speed - 280 mph (450 kmh)
Stalling speed - 90 mph (145 kmh)
Rate of climb at S/L - 2,640 ft (805 m) min
Service ceiling - 41,000 ft (12,500 m)
Service ceiling, one engine out - 11,000 ft (3,350 m)
T-O run - 1,380 ft (420 m)
T-O to 50 ft (15 m) - 2,200 ft (640 m)
Landing from 50 ft (15 m) - 1,970 ft (600 m)
Landing run - 820 ft (250 m)
Range with max fuel - 1,600 miles (2,575 km)
Range with max payload - 1,240 miles (1,995 km)
Jane's All The World's Aircraft / 1965/1966 EDITION - Edited by John W. R. Taylor
DINFIA - DIRECCION NACIONAL DE FABRICACIONES E INVESTIGACIONES AERONAUTICAS (National Directorate of Aeronautical Manufacture and Research)
Address: Camino a San Boque km 5.5, Cordoba
Director: Brigadier Cesar Paradello Malcom
The original Fabrica Militar de Aviones (Military Aircraft Factory) was founded in 1927 as a central organisation for aeronautical research and production in the Argentine. Its name was changed to Instituto Aerotecnico in 1943 and then to Industrias Aeronauticas y Mecanicas del Estado (IAME) in 1952. In 1957 it became a State enterprise under its present title of Direccion Nacional de Fabricaciones e Investigaciones Aeronauticas (DINFIA).
DINFIA comprises two large divisions: The Instituto de Investigacion Aeronautica y Espacial (IIAE), with nine technical departments, is responsible for aeronautical planning, research and the manufacture of prototype and preproduction aircraft. The Directorate of Production has nine factories in which it manufactures aircraft and, since 1952, motor vehicles in quantity. The laboratories, factories and other buildings belonging to these two divisions of DINFIA occupy a total covered area of 2,475,700 sq ft (230,000 sq m), and a total of 9,500 people is employed.
Current production in series is centred on the turboprop-powered IA-50 Guarani 2 twin-engined general-purpose monoplane and the IA-46 Ranquel and IA-51 single-engined lightplanes of national design.
Manufacture of the piston-engined IA-35 Huanquero general-purpose aircraft has been completed, as has the assembly of 48 Morane-Saulnier MS-760 Paris twin-jet liaison aircraft under licence from the Potez company of France.
Development of the IA-52 twin-turboprop transport and IA-55 counter-insurgency aircraft, described in the 1964-1965 Jane's, has been suspended, but work is under way at the IIAE on a new agricultural aircraft designated IA-53.
Descriptions of all types currently under development or in production follow.