US marketing name: Vulcan

TYPE: Tandem-seat ultralight twin/kitbuilt.

PROGRAMME: Development of A-20 with two engines; commissioned by Gulf Aviation Technologies; prototype construction began March 1996; first flight 18 November 1997.

CURRENT VERSIONS: SA-26 Vulcan: Lower-powered variant; Rotax 503 engines. Marketed in US by Spectrum Aircraft.
Vulcan SS: With Rotax 582 engines.
Super Vulcan: Aeroprakt-36; described separately.

CUSTOMERS: More than 15 sold by late 2002 to customers in Guatemala, Panama, UAE and USA.

Description of A-20 applies generally, except as below.

DESIGN FEATURES: Introduces twin-engine safety margins to A-20 design; able to take off on one engine. Sweepback increased to 3°; tailfin height and rudder chord both increased.

POWER PLANT: Two 47.8 kW (64.1 hp) Rotax 582 UL two-cylinder two-stroke engines, each driving a three-blade, ground-adjustable pitch Ivoprop propeller. Alternatively, two 38.3 kW (51.6 hp) Rotax 462 or 34.0 kW (45.6 hp) Rotax 503 twin-piston engines. Fuel capacity 38 litres (10.0 US gallons; 8.4 Imp gallons) in SA-26 or 90 litres (23.8 US gallons; 19.8 Imp gallons) standard in Vulcan SS; 180 litres (47.5 US gallons; 39.6 Imp gallons) optional.

SYSTEMS: Electrical system with 12 V DC, 14 Ah battery for electric starter.