Kawasaki KH-4 / KHR-1
At the beginning of the sixties, Kawasaki began to develop a version of the three-seat Bell Model 47G-3B, with a stretched cabin to make room for two rows of seats.
Powered by a 201kW Lycoming TVO-435-B1A air-cooled engine, the first KH-4 flew in August 1962 and received Japanese type approval on 9 November of that year.
Apart from changes to the cabin to accommodate extra passenger, and new supercharged engine, the KH-4 had a new instrument layout, modified control system and larger fuel capacity.
The engine retained was a 270hp Lycoming TVO-435-B1A or -D1A.
By the beginning of 1972, 193 of the Kawasaki KH-4 had been built, 19 of which were assigned to the Japanese Army, 23 to the Thai armed forces, four to the South Korean armed forces and one to the Philippines.
A total of 338 built for civil and military customers between 1960 and 1975.
An experimental variant of the KH-4 was the KHR-1 which was modified to test a three-blade rigid rotor system. This aircraft flew for the first time on 26 April, 1968.
Rotor diameter: 11.32m
Length overall: 13.30m
Length of fuselage: 9.93m
Height overall: 2.84m
Empty weight: 816kg
Maximum take-off weight weight: 1293kg
Maximum level speed: 169km/h
Cruising speed: 140km/h
Service ceiling: 5640m
Hover ceiling in ground effect: 5485m
Maximum range: 400km