Hummingbird
Role	Helicopter Type of aircraft
National origin	United States
Manufacturer	Vertical Aviation Technologies
Introduction	1991
Status	In production (2013)
Developed from	Sikorsky S-52

The Vertical Hummingbird is an American helicopter, produced by Vertical Aviation Technologies of Sanford, Florida that was introduced in 1991. The aircraft is supplied as a kit for amateur construction.^[1][2]

Design and development

The Hummingbird is a development of the certified Sikorsky S-52 that first flew in 1947, adapted to kit form. The aircraft features a single main rotor, a four-seat enclosed cabin, quadracycle landing gear and an option for skids.^[1] The prototype was converted by Vertical Aviation Technologies from a Sikorsky S-52-3.^[3]

The Hummingbird fuselage is made from riveted aluminum sheet. The nose section is adapted from the Bell 206. Its 33 ft (10.1 m) diameter fully articulated three-bladed main rotor employs a NACA 0015 airfoil.^[4] The two-bladed tail rotor has a diameter of 5.75 ft (1.8 m). The aircraft has an empty weight of 1,790 lb (812 kg) and a gross weight of 2,800 lb (1,270 kg), giving a useful load of 1,010 lb (458 kg). With full fuel of 57 U.S. gallons (220 L; 47 imp gal) the payload is 668 lb (303 kg).^[1][5]

Variants

VAT S-52-3

Prototype of the Hummingbird family, converted from an original Sikorsky S-52-3.^[3]

Hummingbird 260L

Version powered by a six cylinder, air-cooled, four-stroke, dual-ignition 265 hp (198 kW) Lycoming IVO-435 engine^[6]

Hummingbird 300LS

Version powered by an eight cylinder, liquid-cooled, four-stroke, single-ignition 325 hp (242 kW) General Motors LS7 V-8 automotive conversion engine, derated to 280 hp (209 kW)^[7]

Hummingbird 300L

Version powered by a six cylinder, air-cooled, fuel injected IO-540 derated to 280 hp (209 kW)^[5]

Specifications (Hummingbird 300L)

Data from Vertical Aviation^[5]

General characteristics

• Crew: one
• Capacity: three passengers
• Width: 5 ft 0 in (1.52 m)
• Height: 8 ft 7 in (2.62 m)
• Airfoil: NACA 0015
• Empty weight: 1,790 lb (812 kg)
• Gross weight: 2,800 lb (1,270 kg)
• Fuel capacity: 57 US gallons (47 imp gal; 220 L)
• Powerplant: 1 × IO-540 six cylinder, air-cooled, four stroke fuel injected aircraft engine, 280 hp (210 kW)
• Main rotor diameter: 33 ft 0 in (10.06 m)

Performance

• Maximum speed: 110 mph (180 km/h, 96 kn)
• Never exceed speed: 110 mph (180 km/h, 96 kn)
• Range: 380 mi (610 km, 330 nmi)
• Service ceiling: 14,000 ft (4,300 m)
• Rate of climb: 950 ft/min (4.8 m/s) at 2,800 lb (1,270 kg)