Fuji KM-2

The Fuji KM-2 is a Japanese propeller-driven light aircraft, which was developed by Fuji Heavy Industries from the Beech T-34 Mentor which Fuji built under licence. Various versions have been used as primary trainers by the Japan Self-Defense Forces, with the KM-2B remaining in service with the Japan Air Self-Defense Force.

KM-2
Role Primary trainer
Manufacturer Fuji
First flight 16 January 1962
Introduction 1962
Primary users Japan Air Self-Defense Force
Japan Maritime Self-Defense Force
Japan Ground Self-Defense Force
Number built 64
Developed from Beech T-34 Mentor
Variants Fuji T-3

Design and development

Fuji Heavy Industries was established in July 1952 as a successor to Nakajima, and undertook licensed production of the Beech T-34 trainer aircraft as its first product.[1] This was used by Fuji for the development of the Fuji LM-1 Nikko which was a four-seat liaison aircraft powered by a 225 hp Continental O-470 engine, with introduction of a more powerful 340 hp Lycoming O-480 engine resulting in redesignation as the LM-2, with both the LM-1 and LM-2 being used by the Japan Ground Self-Defense Force.[1]

The KM was a four-seat civil version of the LM-1, fitted with the more powerful Lycoming engine that was later used by the LM-2. After the KM was used by the Japanese government for civil pilot training, the KM-2 was developed as a side-by-side two-seat trainer, first flying on 16 January 1962.[1] Sixty-two were purchased by the Japan Maritime Self-Defense Force as primary trainers, with a further two purchased by the Japan Ground Self-Defense Force as the TL-1.[2]

The KM-2B was a further development of the KM-2 for use as a primary trainer for the Japan Air Self-Defense Force. It combined the structure and engine of the KM-2 with the tandem cockpit of the T-34 Mentor, first flying on 17 January 1978.[2] Fifty were purchased by the JASDF as the Fuji T-3, production continuing until 1992.[2]

Operators
 Japan

Specifications (KM-2)

Data from Jane's All The World's Aircraft 1966–1967[3]

General characteristics

  • Crew: 2
  • Length: 7.94 m (26 ft 1 in)
  • Wingspan: 10.0 m (32 ft 10 in)
  • Height: 2.92 m (9 ft 7 in)
  • Wing area: 16.49 m2 (177.5 sq ft)
  • Empty weight: 1,134 kg (2,500 lb)
  • Max takeoff weight: 1,750 kg (3,858 lb)
  • Fuel capacity: 189 L (50 US gal; 42 imp gal) normal, provision for further 76 L (20 US gal; 17 imp gal) in auxiliary tanks
  • Powerplant: 1 × Lycoming IGSO-480-A1A6 air-cooled flat-six engine, 250 kW (340 hp)
  • Propellers: 3-bladed Hartzell HC-83X20-1B/9333C-3 constant-speed propeller, 2.29 m (7 ft 6 in) diameter

Performance

  • Maximum speed: 378 km/h (235 mph, 204 kn) at 4,880 m (16,000 ft)
  • Cruise speed: 304 km/h (189 mph, 164 kn) at 3,050 m (10,000 ft)
  • Stall speed: 100 km/h (62 mph, 54 kn) (flaps down)
  • Range: 975 km (606 mi, 526 nmi)
  • Service ceiling: 8,170 m (26,800 ft)
  • Rate of climb: 7.7 m/s (1,520 ft/min)
  • Takeoff distance to 15 m (50 ft): 440 m (1,444 ft)
  • Landing distance from 15 m (50 ft): 375 m (1,230 ft)
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See also

Related development

References
  1. Donald, David, ed. (1997). The Encyclopedia of World Aircraft. London: Aerospace Publishing. ISBN 1-85605-375-X.
  2. Donald, David; Lake, Jon, eds. (1996). Encyclopedia of World Military Aircraft. London: Aerospace Publishing. ISBN 1-874023-95-6.
  3. Taylor 1966, p. 102.
  • Taylor, John W. R. (1966). Jane's All The World's Aircraft 1966–67. London: Sampson Low, Marston & Co. Ltd.
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