Bell 400
From Wikipedia, the free encyclopedia
| Bell 400/440 TwinRanger | |
|---|---|
 A Bell 400 prototype |
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| Type | Multipurpose utility helicopter |
| Manufacturer | Bell Helicopter Textron |
| Maiden flight | 1984 |
| Status | Active service |
| Developed from | Bell 206L |
The Bell 400/440 TwinRanger were twin-engine developments of the Model 206L LongRanger, while the Bell 400A was a single-engine version of the 400.
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[edit] Development
Bell has tried several incarnations of a twin version of its successful Bell 206 series. The TwinRanger name dates back to the mid 1980s when Bell first considered developing a twin engine version of the LongRanger.
The Bell 400 TwinRanger featured a reprofiled fuselage, two Allison 250 turboshafts, the OH-58D Kiowa's four blade main rotor, and a new shrouded tail rotor.[1] Bell also planned the single-engined 400A, and the 440 twin with a larger fuselage made possible by a high degree of composites.[2] The Bell 400 first flew on April 4 1984. Bell suspended development of the 400/440 family in the late 1980s as it felt unable to achieve a protifable production rate of 120 units a year.[1]
[edit] Successors
After the success of Tridair's Gemini ST twin engine conversions of the 206L in the early 1990s, Bell produced the equivalent Bell 206LT TwinRanger based on the 206L-4. Only 13 206LTs were built between 1994 and 1997. The 206LT was replaced in Bell's line-up by the Bell 427, a mostly-new development of the Bell 407, itself a four-bladed single-engine derivative of the 206L.[1]
[edit] Variants
- Bell 400
- Bell 400A
- Projected model to be powered by one PW209T turboshaft of 937 shp.[2]
- Bell 440
[edit] Specifications (Bell 400)
Data from The Illustrated Encyclopedia of Helicopters[2]
General characteristics
- Crew: 1 pilot
- Capacity: 5 passengers
- Length: ft in (m)
- Rotor diameter: 35 ft 0 in (10.60 m)
- Height: ft in (m)
- Disc area: 2 ft² (m²)
- Empty weight: 3,075 lb (1,400kg)
- Loaded weight: lb (kg)
- Useful load: lb (kg)
- Max takeoff weight: 5,500lb (2,495 kg)
- Powerplant: 2× Rolls-Royce plc Allison 250-C20P turboshaft, 420 hp (kW) each
Performance
- Never exceed speed: knots (mph, km/h)
- Maximum speed: knots (172 mph, 278 km/h)
- Cruise speed: knots (mph, 259 km/h)
- Stall speed: knots (mph, km/h)
- Range: 394 nm (mi, 730 km)
- Service ceiling 10,000 ft (3,048 m)
- Rate of climb: 2,000 ft/min (m/s)
- Disc loading: lb/ft² (kg/m²)
- Power/mass: hp/lb (W/kg)
[edit] References
- ^ a b c Frawley, Gerard: The International Directiory of Civil Aircraft, 2003-2004, page 43. Aerospace Publications Pty Ltd, 2003. ISBN 1-875671-58-7
- ^ a b c Apostolo, Giorgio; Elfan ap Rees (1984). The Illustrated Encyclopedia of Helicopters. New York, NY, USA: Bonanza Books, 50. ISBN 0-517-439352.
[edit] See also
Related development
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[edit] External links
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