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Bell 214ST

The Bell 214ST is a medium-lift, twin-engine helicopter descended from Bell Helicopter's ubiquitous UH-1 Huey series. Though it shares a type number with the somewhat-related Bell 214, the 214ST is larger and of quite different appearance.


Design and development

The 214ST was originally developed as a military project from the Bell 214B BigLifter, specifically for production in Iran and the development by Bell was funded by the Iranian government. The interim prototype was first flown in February 1977 in Texas, with three conforming prototypes following in 1978.

The overthrow of the Shah in 1979, lead Bell to change production plans and build the 214ST at their Dallas-Fort Worth facility instead and launch it as a civil helicopter, rather than a military one. Manufacturing of production 214STs began is 1981. Type certification from the FAA and CAA for visual and instrument flight rules was awarded in 1982. The military variant followed the civil one into production with helicopter deliveries commencing in 1982.

The Bell 214ST included major design changes from the Bell 214. The Bell 214ST has a larger, stretched fuselage with seating for 16-18 passengers, and two 1,625 shp (1,212 kW) GE CT7-2A engines. The helicopter introduced some ground-breaking innovations for Bell, including, a one-hour run-dry transmission, fiberglass rotor blades, elastomeric rotorhead bearings and the option of either skid or wheeled landing gear. The helicopter has a cockpit door and a large cabin door on each side. The 214ST has a capacity for fuel of 435 US gallons (1,650 L). An auxiliary fuel system could be added.

The Model 214ST is the largest helicopter that has been built by Bell.[5] The ST was originally an acronym for "Stretched Twin", but was later changed to "Super Transporter". Bell built a total of 100 214STs. with production ending in 1991.


General characteristics

Crew: 1 or 2

Capacity: Internal: 16 or 17 passengers or equivalent cargo; External: 8,000 lb (3,630 kg) sling load

Length: 49 ft 4 in (15.03 m)

Rotor diameter: 52 ft 0 in (15.85 m)

Height: 15 ft 11 in (4.84 m)

Disc area: 2,124 ft² (107.3 m²)

Empty weight: 9,481 lb (4,300 kg)

Max takeoff weight: 17,500 lb (7,938 kg)

Powerplant: 2 × General Electric CT7-2A turboshaft, 1,625 shp (1,215 kW) each



Maximum speed: 143 knots (165 mph, 264 km/h)

Cruise speed: 140 knots (161 mph, 259 km/h)

Range: 435 nmi (500 mi, 858 km)

Service ceiling: 10,400 ft (3,170 m; ceiling for hover in ground effect)

Rate of climb: 1,780 ft/min (9.04 m/s)