Schweizer 300C
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| Schweizer 300C/330/333 | |
|---|---|
| Schweizer 300CB | |
| Type | Light utility and trainer helicopter |
| Manufacturer | Schweizer Aircraft Corporation |
| Developed from | Hughes 300 |
The Schweizer 300C is a piston-powered light utility helicopter produced by the Schweizer Aircraft Corporation. Mostly used for training and agriculture, it is a very cost effective platform. The Schweizer 330 and 333 are turbine-powered developments of the 300C
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[edit] Schweizer 300C
[edit] Background
The Schweizer 300C design is based upon the older Hughes Model 269 helicopter series, which first flew in October 1956 and began civil production in 1961. Under Hughes, the Model 269 was marketed as the Hughes 300, and for a few years after Schweizer acquired the FAA Type Certificate it was known as the Schweizer-Hughes 300.
[edit] Description
The 300C is powered by a four-cylinder, fuel injected Bell-Lycoming HIO-360-D1A 190 shaft-horsepower (141 kw) piston engine. It uses a fully articulated, counter-clockwise rotating, three-bladed main rotor, and a two-bladed tail rotor. It is of the conventional pod and boom design with shock absorber damped, skid type landing gear. The 300C normally seats two adults. It is capable of seating a third passenger between the two main seats if the middle collective control stick is removed and a seat cushion is put in its place. The flight controls are directly linked to the control surfaces of the helicopter. There are no hydraulics in the 300C. There are generally two sets of controls. The controls on the right side of the cockpit are removable.
Schweizer Aircraft has been a subsidiary of Sikorsky Aircraft since 2004.
[edit] Performance
The 300C has a 950 lb (430 kg) payload. The 300C has a cruising speed of 99 mph (159 km/h or 86 knots) and a maximum speed (VNE) of 109 mph (176 km/h or 95 knots). Its maximum endurance with two 32 gallon (121 liter) fuel tanks is 5.5 hours and has a range of 365 miles (587 km). It has an in-ground effect (IGE) hover ceiling of 10800 ft (3300 m) and an out-of-ground effect (OGE) hover ceiling of 8600 ft (2600 m).
[edit] Derivatives
[edit] Schweizer 330
In 1987, Schweizer announced development of the Schweizer 330 using the dynamic components, rotors, controls and systems of the 300C.<ref name="Frawley Civil">Frawley, Gerard: The International Directiory of Civil Aircraft, 2003-2004, page 190. Aerospace Publications Pty Ltd, 2003. ISBN 1-875671-58-7</ref> The Allison (later Rolls-Royce) 250-C20 truboshaft was derated to 165kW (220hp), giving the 330 excellent hot and high performance, maintaining power output to 18,000 feet. The 330 also received all-new fuselage, vertical tail surfaces, and tail fairing.
The first 330, converted from a 300C, flew on June 14 1988. The type received FAA certification in september 1992, with deliveries beginning in mid-1993.
The improved 330SP, announced in May 1997, featured an improved rotor and raised skids, which can be retrofitted to 330s.
[edit] Schweizer 333
The further improved 333 was announced in 2000, featuring upgraded dynamic system components, new rotor blades, and standard high skids. It has 30% greater useful load than the 330SP.
[edit] RQ-8 Fire Scout
The RQ-8 Fire Scout is a derivative of the Schweizer 330SP helicopter, with a new fuselage, new fuel system, and UAV electronics and sensors.
[edit] Specifications
This aircraft article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them.[edit] Schweizer 300C
Source: International Directiory of Civil Aircraft<ref name="Frawley Civil"/>
General characteristics<h3>
- Crew: 2
- Payload: lb (kg)
- Length: (overall) 28 ft 11 in (8.8 m)
- Rotor diameter: 25 ft 3 in (7.7 m)
- Height: 8 ft 3 in (2.5 m)
- Empty weight: 1008 lb (457 kg)
- Loaded weight: 1850 lb (839 kg)
- Powerplant: 1× Lycoming HIO-360-B1A 6 cylinder, horizontally opposed, 180 hp ()
<h3>Performance<h3>
- Never exceed speed: kts (mph)
- Maximum speed: kts (mph)
- Cruise speed: kts (75 mph)
- Range: nm (204 miles)
[edit] Technical details
Performance
Maximum Speed Vne (Kias) Sea Level: 95 knots (176 km/h)
Cruise Speed: 86 knots (159 km/h)
Maximum Endurance: 3.8 h (5.5 h with auxiliary fuel tank)
Hover Ceiling IGE: 10800 ft (3300 m)
Hover Ceiling OGE: 8600 ft (2600 m)
Dimensions
Height (overall): 8.72 ft (2.65 m)
Length (overall): 30.83 ft (9.40 m)
Fuselage length: 22.19 ft (6.76 m)
Landing gear tread width: 6.54 ft (1.99 m)
Weight
Empty weight: 1100 lb (499 kg)
Gross weight: 2050 lb (930 kg)
Useful load: 950 lb (431 kg)
Power Plant
Engine: Textron Lycoming H10-360 D1A
Maximum Take Off: 190 shp (141 kW)
Maximum Continuous: 190 shp (141 kW)
Rotor System
Main rotor diameter: 26.83 ft (8.18 m)
Main rotor disk area: 565 ft2 (52.49 m2)
Main rotor RPM: 471
Tail rotor diameter: 4.25 ft (1.30 m)
Fuel
Type: AVGAS (100LL)
Standard capacity: 32 US gal, 192 lb (121 L, 87 kg)
Auxiliary capacity: 32 US gal, 192 lb (121 L, 87 kg)
Seating capacity
Training: 2
Utility: 3
[edit] References
<references/>
[edit] External links
[edit] Related content
Related development<h3>
<h3>Comparable aircraft<h3> <h3>Designation sequence<h3>- 300 - 330 - 333
