TYPE: Three-seat helicopter. PROGRAMME: Announced July 2000, when mockup under construction at Kazan helicopter factory; this exhibited at Moscow Salon in August 2001, promoted by Rostvertol, which considering establishing production line. Building of prototype was to have begun in 2001; development cost US$30 million, including US$2.58 million for scientific research and US$15.77 million for prototypes and preparation for series production; estimated unit cost US$140,000 to US$150,000. Programme included in Russian federal aviation plan for 2002-10, but no further announcements made by early 2004. Development under leadership of M.N.Tishchenko of Moscow Aviation Institute, thus designated Mi-60 MAI; financed by Ministry of Education. Maintenance-free rotor hub; airframe TBO of 2,000 hours. LANDING GEAR: Skid type. POWER PLANT: One or two pston engine driving main gearbox via a belt; option of one 195hp Textron Lycoming HIO-360-F1AD, one 237hp VAZ-426 or two 113hp Rotax 914Fs.

Jane's All the World's Aircraft, 2005-2006

Technical data for Mi-60MAI with Textron Lycoming engine Main rotor diameter: 10.0m, normal take-off weight: 800kg, max take-off weight: 1115kg, max level speed: 200km/h, max cruising speed: 175km/h, economic cruising speed: 85km/h, max vertical rate of climb at S/L: 228m/min, hovering ceiling, IGE: 1800m, service ceiling: 4900m, range: 400km, endurance: 3h 40min

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