Airmaster H2-B1

The H2-B1 was designed with the co-operation of the builders of the American Helicom helicopter.[2] Construction of the prototype, registered G-AYNS, was started in September 1970 and it was first flown from Redhill Aerodrome on 12 September 1972.[1][2] It was intended that an improved H2-B2 variant would enter production but only the prototype H2-B1 was built.[1]

The H2-B1 is a two-seat ultralight helicopter with a single two-bladed main rotor and a two-bladed tail rotor.[1] The fuselage is a welded tubular structure skinned with aluminium and had two side-by-side configuration seats for the pilot and a passenger, it is also fitted with a skid landing gear, small wheels are fitted to allow the helicopter to be moved on the ground.[1] The engine is a 100 hp (75 kW) Rolls-Royce Continental O-200-A air-cooled engine driving the main and tail rotors through a simple gearbox.[1]

H2-B1

Prototype, one built[1]

H2-B2

Proposed production variant with streamlined fuselage and a monocoque tailboom, not built.[1]

Data from Jane's All the World's Aircraft 1973-74[1]

General characteristics

• Crew: 2
• Length: 7.70 m (25 ft 3 in)
• Height: 2.46 m (8 ft 1 in)
• Empty weight: 334 kg (738 lb)
• Gross weight: 544 kg (1,200 lb)
• Powerplant: 1 × Rolls-Royce Continental O-200-A four-cylinder, horizontally-opposed, air-cooled piston , 67 kW (100 hp)
• Main rotor diameter: 7.01 m (23 ft 0 in)
• Main rotor area: 104.0 m² (1,120 sq ft)

Performance

• Maximum speed: 153 km/h (99.5 mph, 86.5 kn)
• Cruise speed: 137 km/h (85 mph, 74 kn)
• Range: 370 km (230 mi, 200 nmi)
• Service ceiling: 3,050 m (10,000 ft)
• Rate of climb: 9.1 m/s (1,800 ft/min)

Related lists

• List of rotorcraft