Mitsubishi MU-2

https://en.wikipedia.org/wiki/Mitsubishi_MU-2

The Mitsubishi MU-2 is a Japanese high-wing, twin-engine turboprop aircraft with
a pressurized cabin manufactured by Mitsubishi Heavy Industries. It made its
maiden flight in September 1963 and was produced until 1986. It is one of
postwar Japan's most successful aircraft, with 704 manufactured in Japan and San
Angelo, Texas, in the United States.

Work on the MU-2, Mitsubishi's first postwar aircraft design, began in 1956.
Designed as a light twin turboprop transport suitable for a variety of civil and
military roles, the MU-2 first flew on 14 September 1963. This first MU-2, and
the three MU-2As built, were powered by the Turbomeca Astazou turboprop.

Civil MU-2s powered by Garrett engines were certified as variants of the MU-2B,
using the MU-2B type followed by a number. For marketing purposes, each variant
was given a suffix letter; the MU-2B-10, for example, was sold as the MU-2D,
while the MU-2B-36A was marketed as the MU-2N.

The MU-2 has a high cruise speed coupled with a low landing speed. This is
accomplished by using over-wing spoilers instead of conventional ailerons for
roll control, allowing the use of full-span double-slotted flaps on the trailing
edge of the wing; the very large flaps give the MU-2 wing loading comparable to
a Beechcraft King Air in landing configuration, while having wing loading
comparable to a light jet in cruise. The spoilers are highly effective, even
when the MU-2 wing is stalled, and the lack of ailerons completely eliminates
adverse yaw.

Production

In 1963, Mitsubishi granted Mooney Aircraft rights in North America to assemble,
sell, and support the MU-2. In 1965, Mooney established a facility to assemble
MU-2s at its new factory in San Angelo, Texas. Major components were shipped
from Japan, and the San Angelo factory installed engines, avionics, and
interiors, then painted, flight tested, and delivered the completed aircraft to
customers. By 1969, Mooney was in financial difficulty, and the San Angelo
facility was taken over by Mitsubishi. Production in the United States ended in
1986. The last Japanese-built aircraft was completed in January 1987.

The subsequent production aircraft, designated MU-2B, were delivered with the
Garrett TPE331 engines that remained standard on all later models. Thirty-four
MU-2Bs were built, followed by 18 examples of the similar MU-2D. The Japanese
armed forces purchased four unpressurized MU-2Cs and 16 search and rescue
variants designated MU-2E. Featuring slightly more powerful upgraded TPE331
engines, 95 examples of the MU-2F were sold.

Beginning with the MU-2G, the fuselage was stretched. The MU-2M, of which only
28 were built, is regarded as the toughest and most desired of all short-bodied
MU-2s, especially with a -10 engine conversion. It had a short fuselage and the
same engines as the MU-2K and stretched MU-2J, and had an increase in cabin
pressurization to 6.0 psi; it was followed by the MU-2P, which had newer,
four-blade propellers. The final short-fuselage MU-2s produced were known as
Solitaires and were fitted with 496 kW (665 shp) Garrett TPE331-10-501M engines.

The first significant change to the airframe came with the stretched MU-2G,
first flying 10 January 1969, which featured a 1.91 m (6 ft 3 in) longer
fuselage than earlier models; 46 were built before being succeeded by the more
powerful MU-2J (108 constructed). The MU-2L (29 built) was a higher-gross-weight
variant, followed by the MU-2N (39 built) with uprated engines and four-blade
propellers. The final stretched-fuselage MU-2 was named the Marquise, and like
the Solitaire, used 533 kW (715 shp) TPE331 engines.

As of 2005, 397 MU-2 aircraft are registered in the United States


Role
Utility transport aircraft

National origin
Japan

Manufacturer
Mitsubishi Heavy Industries

First flight
14 September 1963

Status
In service

Produced
1963–1986

Number built
704

Operational history

United States

Since 1987 MU-2s have been flown by retired United States Air Force pilots
working for Air 1st Aviation Companies, Inc. under government contract at
Tyndall Air Force Base, Florida, where they provide U.S. Air Force undergraduate
Air Battle Manager students of the U.S. Air Force Weapons Controller School with
their initial experience controlling live aircraft. In the tactical simulations,
the aircraft usually represent F-15s and Mikoyan MiG-29s. Students must control
eight MU-2 missions before they can progress to controlling high-performance
aircraft such as F-15s or F-22s.

Flight around the world

On 25 August 2013 Mike Laver, owner and pilot of N50ET (a -10 engine converted
1974 K-model equipped with 5-blade MT-composite propellers, which had just
received a Supplemental Type Certificate (STC) under Air 1st of Aiken, South
Carolina), along with AOPA Pilot technical editor Mike Collins, embarked on an
around-the-world journey in the MU-2B-25. The voyage commenced at Aiken
Municipal Airport and visited Nagoya, Japan on 14 September 2013, the 50th
anniversary of the MU-2.

Specifications (MU-2L)

General characteristics
Crew: 1 or 2 pilots
Capacity: 4–12 passengers
Length: 12.01 m (39 ft 5 in)
Wingspan: 11.94 m (39 ft 2 in) including tip tanks
Height: 4.17 m (13 ft 8 in)
Wing area: 16.55 m2 (178.1 sq ft)
Aspect ratio: 7.71:1
Airfoil: root: NACA 64A415; tip: NACA 63A212
Empty weight: 3,433 kg (7,568 lb)
Max takeoff weight: 5,250 kg (11,574 lb)
Fuel capacity: 1,388 L (367 US gal; 305 imp gal) maximum usable fuel
Powerplant: 2 × AiResearch TPE331-6-251M turboprop engines, 579 kW (776 hp) each
Propellers: 3-bladed Hartzell HC-B3TN-5/T10178HB-11 fully feathering reversible
constant-speed propellers, 2.29 m (7 ft 6 in) diameter

Performance
Cruise speed: 547 km/h (340 mph, 295 kn) at 4,175 kg (9,204 lb) at 4,575 m
(15,010 ft) maximum
Economical cruise speed: 483 km/h (300 mph; 261 kn) at 4,175 kg (9,204 lb) at
7,620 m (25,000 ft)
Stall speed: 185 km/h (115 mph, 100 kn) flaps down (Calibrated airspeed)
Range: 2,334 km (1,450 mi, 1,260 nmi) at 7,620 m (25,000 ft) with full wing and
tip tanks including 30 minutes reserve
Service ceiling: 9,020 m (29,590 ft)
Rate of climb: 12.0 m/s (2,360 ft/min) at sea level

Take-off run to 15 m (50 ft): 661 m (2,169 ft)
Landing run from 15 m (50 ft): 573 m (1,880 ft)




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