Aerospatiale/HAL

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Aerospatiale/HAL SA315B Lama (Cheetah)

Design development of the SA 315B was initiated late in 1968, primarily to meet a requirement announced by the Indian Armed Forces for a lightweight multi-role helicopter capable of effective operations in the high mountains. During demonstration flights in the Himalayas in 1969, the SA 315B carrying a crew of two and 308 lb. (140 kgs.) of fuel made the highest landings and take-offs ever recorded—from a height of 24,600 feet (7,500 m.). In September 1970 an agreement was signed with the French company for the manufacture of the SA 315B under licence at HAL Bangalore. The first twenty SA 315Bs are to be produced from sub-assemblies obtained from France and another eighty will be manufactured at HAL’s new Helicopter Factory being established at Bangalore. The first HAL-assembled helicopter (Z 1431) initially flew on 6th October 1972 and was handed over for trials with the I.A.F. at Bangalore on 14th December being cleared for service early in 1973. A batch of six SA 315Bs had been accepted by the Indian Air Force/Army by late 1973.

The SA 315B, named the Cheetah in I.A.F. service, can be utilized for a variety of roles including liaison, rescue, training, ambulance or observation. There has been a re-thinking on the employment of fixed-wing aircraft in mountain-terrain and the fact that rotary wing aircraft have greater versatility with their VTOL/hovering capabilities will lead the Cheetah into supplanting the Krishaks for the Air O.P. role.

Notes :

The SA 315B prototype first flew on 17th March 1969 and French certification was granted on 30th September 1970. Basically the SA 315B combines the features of the Alouette II (airframe with some reinforcement) and Alouette III (dynamic components including the Artouste MB power plant and rotor system). The production SA 315B is capable of transporting 4 passengers or external sling loads of 2,204 lb. (1,000 kgs.) at an altitude of more than 8,200 feet (2,500 m.)

Image Information

Country of Orign France
Performance Max. cruising speed (with max. T.O. wt.) 75 m.p.h. (121 km./hr.)
Rate of climb (at ST) 820 ft./min. (250 m./min.)
Service ceiling 11,150 feet (3,398 m.) / Hovering ceiling (o.g.e.) 7,875 feet (2,400 m.)
Weights Empty 2,193 lb. (995 kg.)
Max. T.O. (with externally slung cargo) 4,850 lb. (2,200 kg.)
Dimensions Rotor diameter 36 ft. 1 ¾ in. (11.02 m.)
Length overall 42 ft. 4 ¾ in. (10.26 m.)
Height overall 10 ft. 1 ¾ in. (3.09 m.)

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