Mitsubishi MH2000

From Wikipedia, the free encyclopedia
Jump to navigation Jump to search
Mh2000 excel air.jpg
The Mitsubishi MH2000 of the EXCEL AIR SERVICE.
Role Utility helicopter
National origin Japan
Manufacturer Mitsubishi Heavy Industries
First flight 29 July 1996
Introduction 2000
Primary users Excel Air Service
Japan Aerospace Exploration Agency
Produced 1996-2004
Number built at least 5

The Mitsubishi MH 2000 is a 7/12 seat light utility helicopter. Low levels of interest in the aircraft forced Mitsubishi to halt sales of MH2000 in September 2004.

Design and development[edit]

The MH2000 is Japan's first indigenous helicopter with Mitsubishi Heavy Industries (MHI) having sole responsibility for developing and manufacturing the fuselage and engines.

In the development of the MH2000, MHI aimed for safety, economy and low noise levels. The program was launched in 1995 to fulfill a variety of missions, include passenger and business transport, law enforcement, search and rescue and emergency medical services.

The first of four developmental aircraft first flew on 29 July 1996, the second flying later that year and the remaining two used for ground testing. The MH2000 has its engine module and dynamic system positioned behind the cabin section to minimize sound levels in the passenger compartment. Power is provided by a pair of Mitsubishi MG5-100 turboshaft engines.

The first production model was delivered on October 1, 2000 to Excel air service in Japan. The loss of one prototype due to tail rotor blade separation led to suspension of type certificate and redesign of tail rotor. Delivered craft were modified with the new rotor and all further craft will be delivered with the new tail rotor.

JA003M on display at the Tachiarai Peace Memorial Museum.


Data from [1]

General characteristics

  • Crew: 1 or 2
  • Capacity: passengers: 6-12, 2,000 kg (4,409 lb) payload
  • Length: 12.2 m (40 ft 0 in) 14 m (46 ft) rotors turning
  • Width: 3.2 m (10 ft 6 in) (fuselage)
  • Height: 4.1 m (13 ft 5 in)
  • Empty weight: 2,500 kg (5,512 lb)
  • Max takeoff weight: 4,500 kg (9,921 lb)
  • Powerplant: 2 × Mitsubishi MG5-110 turboshaft, 597 kW (801 hp) each
  • Main rotor diameter: 12.2 m (40 ft 0 in)


  • Cruise speed: 250 km/h (155 mph; 135 kn)
  • Never exceed speed: 278 km/h (173 mph; 150 kn)
  • Range: 777 km (483 mi; 420 nmi)
  • Endurance: 4 hours
  • IGE max hovering altitude @ MTOW: 2,700 m (8,858 ft)


  1. ^ "MH-2000". 2010. Retrieved 16 August 2012. External link in |publisher= (help)

World aircraft information files brightstar publishing London sheet 34 file 901

External links[edit]