Photograph:
IAC MA-2 Mamba VH-FCX (c/n AA1-001) at Avalon, VIC in 1999 (David C Eyre)
Country of origin:
Australia
Description:
Two-seat utility aircraft
Power Plant:
(MA-2A)
One 119 kw (160 hp) Textron Lycoming O-320-D1A four-cylinder horizontally-opposed air-cooled engine
Specifications:
- Wingspan: 8.36 m (27 ft 5 in)
- Length: 7.47 m (24 ft 6 in)
- Height: 2.74 m (9 ft)
- Wing area: 9.29 m² (100 sq ft)
- Max speed at sea level: 232 k/h (144 mph)
- Max cruising speed at 70% power: 213 km/h (132 mph)
- Max cruising speed at 2,440 m (8,000 ft): 222 km/h (138 mph)
- Max rate of climb at sea level: 335 m/min (1,100 ft/min)
- Stalling speed flaps down: 84 km/h (52 mph)
- Range at 2,440 m (8,000 ft) at max cruising speed, no reserve: 1,262 km (787 miles)
- Empty weight: 635 kg (1,400 lb)
- Loaded weight: 967 kg (2,000 lb)
History:
The MA-2 Mamba was named after the company which conceived the design, the Melbourne Aircraft Manufacturing Basic Aircraft Project, and the prototype VH-JSA (c/n P-001) first flew on 25 January 1989 fitted with an 87 kw (116 hp) Textron Lycoming O-235 engine. Designed as a high-wing, tandem, two-seat, utility aircraft aimed at the civil and military markets, it was built to meet requirements of ANO 101.22, US FAR 23, and UK BCAR section K.
The prototype was constructed and test flown at Essendon, VIC and production was initially planned to take place at Echuca, VIC but this did not eventuate. Later plans were announced for production to take place at Essendon. In 1990 the company changed its name to the International Aircraft Corporation, and later Aviation Industries of Australia Pty Ltd became responsible for the program.
Construction was conventional, with a welded steel tube frame, plywood underbelly, and aluminium covering overall. The engine cowling was carbon fibre. Wings were all aluminium, with two tubular aluminium spars, ribs of similar material channel section, flat sheeting and riveted together. Fuel to a total of 327 litres (72 Imp gals) was carried internally and provision was made for two auxiliary slipper tanks under each wing, these being constructed of carbon fibre. No flaps were fitted but the prototype had an electrically-operated speed brake under the fuselage. The undercarriage was of tricycle configuration and large wheels were fitted to permit rough field operation. Dual controls were standard and the undercarriage legs were long to permit a 1.8 m (5 ft 9 in) diameter propeller.
Further models were proposed: the MA-2C civil variant of the MA-2A and the MA-2M, a strengthened military aircraft with a 149 kw (200 hp) Avco Lycoming IO-360 engine and armour plating, able to carry 272 kg (600 lb) of ordinance, aimed at performing roles such as forward area control, border patrol, counter-insurgency, and armament training. Also proposed was a four-seat utility or training variant, a mock-up of which was constructed in 1992. Production two-seat models were planned to incorporate a number of refinements, including moving the tailplane to a higher position, altering the angle of the lower rear fuselage to improve clearance during rotation, and installation of a 119 kw (160 hp) Lycoming O-320 engine, this engine to be standardised on civil variants.
Sales were announced for nine aircraft for the West Australian Department of Conservation and Land Management for fire spotting; and three aircraft for Professional Pilot Training based at Cessnock, NSW. Some foreign interest was also shown in the design.
In February 1999, at the Australian International Air Show at Avalon, VIC, a new variant VH-FCX (c/n AA1-001) was placed on static display, aimed at the military market, and registered to Australian Industrial Corporation of Shepparton, VIC. However, no production aircraft are known to have been completed.