Twin Turboprops
Beechcraft King Air C90gti
ICAO: BE9L
Overview
The Mitsubishi MU-2 was manufactured by Mitsubishi Heavy Industries as a high-wing turboprop aircraft designed with a pressurized cabin and powered by twin engines. It first flew in September 1963 and was produced from 1963 to 1986. A total of 704 aircraft were built in Japan and Texas, United States. The MU-2 is among the most successful Japanese aircraft after the Second World War.
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Specifications
Units
- Engine
- 2 × Honeywell TPE331-6-251M
- Engine type
- Turboprop
- Power
- 2 × 776 shp · 579 kW
- Avionics
- —
- Wing tips
- No winglets
- Seats
- 12
- Crew
- —
- Cabin width
- 4 ft 11 in · 1.50 m
- Cabin height
- 4 ft 4 in · 1.32 m
- Cabin length
- 16 ft 0 in · 4.87 m
- Exterior length
- 39 ft 5 in · 12.01 m
- Tail height
- 13 ft 8 in · 4.17 m
- Fuselage diameter
- 5 ft 3 in · 1.60 m
- Wing span
- 39 ft 5 in · 12.01 m
- Baggage volume
- 42 ft³ · 1.2 m³
- Gross weight
- —
- Empty weight
- —
- Max takeoff weight
- 11,600 lb · 5,250 kg
- Max landing weight
- 11,000 lb · 5,000 kg
- Max payload
- 3,800 lb · 1,750 kg
- Fuel capacity
- 370 gal · 1,400 L · 1,100 kg (Jet A)
- Max cruise speed
- 295 kt · 339 mph · 546 km/h
- Maximum speed
- —
- Cruise speed
- —
- Approach speed
- 81 kt · 93 mph · 150 km/h
- Range
- 1,260 nm · 1,450 mi · 2,330 km
- Fuel burn
- —
- Ceiling
- 29,590 ft · 9,000 m
- Rate of climb
- 2,360 ft/min · 12 m/s
- Takeoff distance
- 2,150 ft · 660 m
- Landing distance
- 1,880 ft · 570 m
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Operational Context
In 1956, development on the Mitsubishi MU-2 started. It was the company’s first aircraft design after the Second World War. On September 14, 1963, the MU-2 took to the air for the first time. It was built as a light transport aircraft powered by twin turboprop engines intended for various civil and military uses. The aircraft was produced until 1986 with a total of 704 built.
Related Post: The Japanese Fighter Planes of World War II
The MU-2L version can accommodate one or two pilots and four to twelve passengers on board. It has an external length of 12.01 meters, an external height of 2 meters, and a fuselage diameter of 1.6 meters. It has a tail height of 4.17 meters and a wheelbase of 4.4 meters. The wingspan is 11.94 meters including tip tanks and the wing area is 16.55 square meters. It has an empty weight of 3,433 kg, a maximum payload of 1,726 kg, and a maximum usable fuel capacity of 367 US gal. The maximum takeoff and landing weights are 5,250 kg and 5,000 kg, respectively.
The aircraft is powered by two AiResearch TPE331-6-251M engines. It is a single-shaft turboprop with an integral gearbox, two-stage centrifugal compressor, reverse annular combustors and three-stage axial turbine. Each engine produces a maximum thrust of 776 hp and drives a three-bladed Hartzell HC-B3TN-5/T10178HB-11 fully-feathering reversible constant-speed propellers of 2.29 meters in diameter.
The MU-2 has a maximum cruise speed of 295 knots at 4,175 kg at 15,010 feet and an economical cruise speed of 261 knots at 4,175 kg at 25,000 feet. It has a stall speed of 100 knots with flaps down and a range of 1,260 nautical miles at 25,000 feet with full wing and tip tanks including thirty minutes reserve. It can fly up to 29,590 feet and can climb at a rate of 2,360 feet per minute at sea level. The takeoff run is 661 meters while the landing run is 573 meters.
Sources and references used for research and fact-checking.