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Bell 214 Huey Plus - The prototype 214 flew in 1970. Powered by one Lycoming T53-L-702 turboshaft (1,900 shp/1,415 kW). [3] Bell 214A/C Isfahan - The 299 Bell 214As for the Imperial Iranian Army Aviation were built beginning in 1972, followed by 39 Bell 214Cs with a hoist (winch) and other search and rescue equipment for the Imperial Iranian ...
An interim twin-engine conversion of a Model 214 flew on 15 February 1977 in Texas, [4] [5] Testing was successful, and Bell decided to press forward with a definitive twin-engine Bell 214ST, with a fuselage stretched by 30 in (76 cm) and a revised main rotor of greater diameter.
The HueyTug, was a commercial version of the UH-1C with an upgraded transmission, longer main rotor, larger tailboom, strengthened fuselage, stability augmentation system, and a 2,650 shp (1,976 kW) Lycoming T-55-L-7 turboshaft engine. [12] Bell 212 15 seat twin-engined derivative of the Bell 205 Bell 214 Huey Plus Strengthened development of ...
Bell 412CF looking forward from the tail Bell 412 on approach. Development began in the late 1970s, with two Bell 212s being converted into 412 prototypes. An advanced four-blade main rotor with a smaller diameter replaced the 212's two-blade rotor. A Bell 412 prototype first flew in August 1979.
The UH-1H's dynamic components include the engine, transmission, rotor mast, main rotor blades, tail rotor driveshaft, and the 42-degree and 90-degree gearboxes of the tail rotor. The main rotor transmission consists of a 90 degree bevel gear assembly with a reduction ratio of 2.14:1, followed by a 2-stage planetary gearset with a ratio of 9.53 ...
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Civil designation for the T55-L-7 military engine; dry weight of 580 lb (260 kg) [5] also powered the original Bell 214 helicopter as a 2,930 shp (2,180 kW) engine in 1970 [6] LTC4B-8D 2,950 shp (2,200 kW) engine powering the Bell 214 A helicopter; [ 7 ] uprated from the T55-L-7C; 433 engines produced between 1973 and 1977 for this military ...
In the Bell design, Bell Model 301, the whole wingtip pod rotated between horizontal and vertical, with the engine and rotor assembly fixed together within the pod. This simplified the power transmission, but it had more complicated requirements for the engine design and was probably slightly heavier than the Boeing proposal.