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Mi-38
Mi-38 at HeliRussia 2011
Role Medium transport helicopter
Design group Mil Moscow Helicopter Plant
Built by Kazan Helicopter Plant
First flight 22 December 2003
Number built 3

The Mil Mi-38 is a transport helicopter designed by Mil Moscow Helicopter Plant. Originally intended as a replacement for the Mil Mi-8 and the Mi-17, it is being marketed in both military and civil versions.[1] It flew for the first time on 22 December 2003.[2]

Design and development

Mi-38 in MAKS Airshow 2013

The manufacturer plans to provide the Mi-38 with a new Tranzas "glass cockpit" avionics system and new composite main rotor blades. The helicopter is offered with a choice of either Klimov TV7-117V or Pratt & Whitney Canada PW127/TS turboshaft engines. The second prototype, powered by the PW127TS, made its first flight in December 2010.[3] In 2013, the third prototype has been assembled at the Kazan Helicopter Plant.[4]

The Mil Mi-38 prototypes have already set five records in the E1h class. The second prototype aircraft set an altitude record by reaching 8,620 meters (28,280 feet) without a payload. The second and third records were for climbing speed; the Mi-38 reached a height of 3,000 meters (9,843 feet) in six minutes, then followed this to reach 6,000 meters (19,685 feet) in 10 minutes and 52 seconds. Two further records were altitude records: the first was set at 7,895 meters (25,902 feet) with a 1,000-kg (2,205-lb) payload, the second at 7,020 meters (23,031 feet) with a 2,000-kg (4,409-lb) payload.[5]

Specifications (Mi-38)

General characteristics

  • Crew: 1/2 – one or two (for passenger transportation) pilots
  • Capacity: 30 passengers ( under the AP-29 airworthiness regulations )
  • Length: 19.70 m ()
  • Rotor diameter: 21.10 m ()
  • Height: 5.13 m ()
  • Disc area: 349.5 m² ()
  • Empty weight: 8,300 kg ()
  • Loaded weight: 14,200 kg ()
  • Powerplant: 2 × Klimov TV7-117V or Pratt & Whitney Canada PW127/TS turboshaft, 1,864 kW (2,800 shp) each

Performance

  • Rate of climb: ? m/s (? ft/min)
  • Disc loading: 41 kg/m² (8.3 lb/ft²)
  • Power/mass: 260 W/kg (0.16 hp/lb) [6]

See also

References

The initial version of this article was based on material from aviation.ru. It has been released under the GFDL by the copyright holder.

External links

This page uses Creative Commons Licensed content from Wikipedia (view authors).
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