A more powerful, two-seat derivation of the Sport Copter 496. The prototype featured a 4 stroke engine, 23 ft tail shaft and a MTOW of around 1300 lbs.
Assembled in New Zealand, the initial four were registered in July 1999.

A two seat partially enclosed helicopter. Composite body, main rotor and shrouded tail rotor. Useable as a trainer, either experimental or ultralight. Includes full dual controls, doors, electric start. Infinite life composite rotor blades and fuselage. High inertia blades for excellent autorotation. An 8′ wide landing gear. Floor mounted cyclic now standard. Quick build kit. Meets 51% build rule. Dual controls standard. Plans or Kits delivered within 4-6 weeks of receiving order in 2009.
The Ultrasport 496 two-seater which commenced flight testing (N496AS) in July 1995, has a wider cabin than the 331 and uses a 95hp Hirth F.30 engine. The Ultrasport helicopter kits are manufactured in Taiwan. Deliveries began in April 1997.
The Ultrasport 496RT announced in 2002 uses a 84.6kW Rotax 914 turbocharged engine with electric start and quadruple carburettors.
Prices in 2003 were: 496 US$62,900; 496RT US$77,900.
An unmanned surveillance prototype named Vigilante 496 (first flight February 1998) was developed by Science Applications International Corporation. The Vigilante 496 prototype (N496UV) evaluated as optionally piloted vehicle (OPV) by US Navy during first and second quarters of 1998.

Engine: Hirth F 30, 115 hp
Rotor span: 7.00 m
Blade area: 0.170 sq.m
MAUW: 514 kg
Empty weight: 245 kg
Fuel capacity: 60 lt
Max speed: 167 kph
Cruise speed: 112 kph
Minimum speed: 0 kph
Climb rate: 4 m/s
Seats: 2
Fuel consumption: 25 lt/hr

Engine: One 85.8kW Hirth F30 quad-carburettor / electric start
Main rotor diameter: 7.01m
Tail rotor diameter: 0.76m
Length rotor blades folded: 6.02m
Height: 2.49m
Take-off weight: 512kg
Empty weight: 256kg
Never-exceed speed: 167km/h
Max cruising speed: 113km/h
Max rate of climb: 305m/min
Hovering ceiling, IGE: 3290m
Hovering ceiling, OGE: 2135m
Range: 240km
Endurance: 3h
Fuel capacity: 61 lt

Engine: 105 hp Hirth H-30, Quad carb, Dual CDI
Transmission 11:1 helical spur (2 stage)
Rotor blades diameter: Composite 23 ft
Roror blade chord: 7 in composite
Tail rotor diameter: 30in
Cruise: 69 mph
Top Speed: 104 mph
Empty Weight: 575 lbs
Useful Load: 605 lbs
Gross Weight: 1,180 lbs
Width: 6 ft 6 in
Height 8 ft 2 in
Length (w/blades folded): 19 ft 9 in

Engine: Hirth Gober, 120 hp
Disk span: 23 ft
Seats: 2
Landing gear: skids
Endurance: 2.5 hr
Weight empty: 600 lbs
Gross: 1180 lbs
Speed max: 103 kts
Cruise: 93 kts

Engine: 75.0kW Hirth H3QE

The Ultrasport 331 is a larger version of the 254 falling within the American Experimental category (FAR Part 21.191g), with increased range and higher gross weight. Features include 10 gallon tank, doors, bigger instrument panel, electric starter. The performance as the 254, and the floor mounted cyclic is standard. Optional floats are available. Meeting the 51% rule, a quick build kit requires 80 hours assembly.
The two-blade composites construction main rotor has tip weights for momentum conservation and an 8 deg linear twist and infinite life. Equipped with a shielded two-blade tail rotor, and tailplane with tins at tip, the tail rotor drive is carried in narrow streamlined tailboom. A centrifugal sprag clutch for starting engages the rotors at 2,000 engine rpm and automatically disengages in the event of engine failure.
The flying controls are conventional collective, cyclic and yaw pedals. A floor-mounted cyclic option has been available since 1998; early models had a top-mounted stick.
The prototype 331 (N331UV) first flew December 1993.
The single seat 331 is powered by one 48.5kW Hirth 2706 dual-carburettor two-stroke engine with electric starter or Hirth H32 of same power in 331H; 12:1 planetary transmission. Fuel capacity 38 litres.
In late 2002, it was announced that Huzbou Taixing Aviation Technology of Huzhou, China was producing helicopters from kits, including examples of Ultrasports.
A single-seat ultralight helicopter, the Ultrasport 331H uses the 48.5kW Hirth H32 added to range in 2003.
The Ultrasport 331 was available for US$37,900 in 2003.

Engine: Hirth 2706, 65 hp
Rotor span: 6.40 m
Blade area: 0.170 sq.m
MAUW: 295 kg
Empty weight: 150 kg
Fuel capacity: 38 lt
Max speed: 167 kph
Cruise speed: 105 kph
Minimum speed: 0 kph
Climb rate: 4 m/s
Seats: 1
Fuel consumption: 14 lt/hr

Engine: Hirth 2703, 55 hp.
Disk span: 21 ft.
Length: 16.67 ft.
Height: 7.5 ft.
Weight empty: 330 lbs.
Gross: 680 lbs.
Fuel cap: 10 USG.
Speed max: 104 mph.
Cruise: 63 mph.
Range: 150 sm.
ROC: 1000 fpm.
Service ceiling: 12,000 ft.
Endurance: 2.5 hr.
Seats: 1.
Landing gear: skids.

Engine: 65hp Hirth 2706 Dual carb, Dual CDI.
Transmission 12:1 Planetary
Rotor Blades: Composite 21′ diameter, 7″ chord,
Tail rotor: composite 30′ diameter.
Empty Weight: 330 lbs
Useful Load 320 lbs
Gross Weight: 650 lbs
Fuel capacity: 10 USG
Width 6 ft 6 in
Height 8 ft 2 in
Length 19 ft 2 in (w/blades off)
Cruise: 65mph
Top Speed: 104 mph
Range: 150 sm
ROC: 1000 fpm
Service ceiling: 12,000 ft
Kit price: US$34,850 (2008)

Ultrasport 331
Main rotor diameter: 6.4m
Tail rotor diameter: 0.76m
Length with rotor blades folded: 5.84m
Height: 2.39m
Take-off weight: 294kg
Empty weight: 150kg
Max level speed: 167km/h
Cruising speed: 101km/h
Max rate of climb: 305m/min
Hovering ceiling, IGE: 3290m
Hovering ceiling, OGE: 2135m
Range with normal fuel at 100km/h: 241km

Ultrasport 331H
Engine: 48.5kW Hirth H32

American Sportscopter (ASI) was formed in 1990 to produce an ultralight helicopter to FAR Part 103, which was designated Ultrasport 254. Design objective of 254 was basic weight not to exceed 115kg (254 lb) in order to comply with FAR Pt 103.
First flown on 24 July 1993 and publicly displayed at Oshkosh that year, it is a single-seater with a semi-enclosed composite fuselage structure, skid undercarriage and a tubular tailboom with tailplane and twin fins and a tail rotor enclosed in a large circular shroud. Two prototypes were built and tested.
The two-blade composites construction main rotor has tip weights for momentum conservation in the event of an engine failure, an 8 deg linear twist and infinite life. The tail rotor drive is carried in a narrow streamlined tailboom. A centrifugal sprag clutch for starting engages rotors at 2,000 engine rpm and automatically disengages in the event of engine failure.
Fitted with a 5 US gallon tank, and the 8 foot wide landing gear stressed for landings at up to 2.5g, and has optional floats (weight 18kg). A quick build kit requires 80 hours to assembly. An overhead control stick operates with same movements as joysticks. A floor-mounted cyclic option has available since 1998.
It is powered by a 55hp Hirth 2703 engine mounted behind the cockpit rear bulkhead. In 2003 the engine used was the 41.0kW Hirth 27G3 dual-carburettor two-stroke engine with pull starter and 12:1 planetary transmission. Normal fuel capacity 19 litres.
The Ultrasport 254 was available in 2003 for US$34,900.

Engine: 55 hp Hirth 2703 522cc.
Transmission: 12:1 planetary.
Speed max: 63 mph.
Cruise: 63 mph.
Range: 70 sm.
ROC: 1000 fpm.
Rotor blades: Composite 21’, 6.7” chord, metal tail rotor 40”.
Fuel cap: 5 USG.
Weight empty: 252 lbs.
Gross: 525 lbs.
Height: 7.5 ft.
Length: 16.67 ft.
Seats: 1.
Landing gear: skids.

Engines: 55hp Hirth 2703, 65hp Hirth 2706 is optional. Dual carb,Dual CDI.
Transmission 12:1 Planetary
Rotor Blades: Composite 21′ diameter, 7″ chord
Composite tail rotor 30′ diameter.
Cruise 63 mph
Top Speed 63 mph
Empty Weight 252 lbs
Useful Load 273 lbs
Gross Weight 525 lbs
Width 8′
Height 7’10”
Length 19’2″

Ultrasport 254
Main rotor diameter: 6.4m
Tail rotor diameter: 0.76m
Length with rotor blades folded: 5.84m
Height: 2.39m
Take-off weight: 238kg
Empty weight: 114kg
Max level speed: 101km/h
Max rate of climb: 305m/min
Hovering ceiling, IGE: 3290m
Hovering ceiling, OGE: 2135m
Range with normal fuel at 100km/h: 120km