Our Fleet - Bell 222

Country of origin: Canada & USA

Type: Twin engine ten seater helicopter

Powerplant: Two 505kW (680shp) Avco (Textron) Lycoming LTS 101750C turboshafts driving a two blade main rotor and two blade tail rotor.

Performance: Max cruising speed 240km/h (130kt). Initial rate of climb 1730ft/min. Hovering ceiling in ground effect 10,300ft. Range with no reserves 724km (390nm). Service ceiling 15,500ft. Hovering ceiling in ground effect 12,400ft. Range at economical cruising speed, with standard fuel, wheels and no reserves 558km (301nm), or 713km (385nm) with skids; range with wheels and auxiliary fuel, no reserves 702km (380nm).

Weights: Empty equipped 2076kg (4577lb), max takeoff 3472kg (8250lb).

Dimensions: Main rotor diameter 12.80m (42ft 0in), fuselage length 12.85m (42ft 2in), height 3.51m (11ft 6in). Main rotor disc area 128.7m2 (1385.4sq ft).

Capacity: Seating for ten, including pilot, in four rows.

Production: 184 Bell 222s built.

History: Bell announced development of the all new 222 twin in 1974, following the positive response generated by a mockup proposal displayed at that year's Helicopter Association of America convention.

Having taken note of potential customers' preferences and suggestions, Bell modified its design accordingly, and the subsequent development effort led to the Model 222's first flight in August 1976. A number of advanced features were designed into the 222, including the Noda Matic vibration reduction system developed for the 214ST, stub wings housing the retractable undercarriage, provision for IFR avionics, and dual hydraulic and electrical systems.

The 222 was awarded FAA certification in December 1979. Production deliveries commenced in early 1980. Subsequent development led to the more powerful 222B with a larger diameter main rotor, introduced in 1982, and the essentially similar 222UT Utility Twin, which features skid landing gear in place of wheels.