Fuji KM-2
From Wikipedia, the free encyclopedia
| KM-2 | |
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| Type | Primary trainer |
| Manufacturer | Fuji |
| Maiden flight | 16 January 1962 |
| Introduced | 1962 |
| Primary users | Japan Air SDF Japan Maritime SDF Japan Ground SDF |
| Number built | 64 |
| Developed from | Beech T-34 |
| Variants | Fuji T-3 Fuji T-5 |
The Fuji KM-2 is a Japanese propeller-driven light aircraft, which was developed by Fuji Heavy Industries from the Beech T-34 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
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[edit] Design and development
Fuji Heavy Industries was established in July 1952 as a successor to Nakajima, and undertook licenced 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 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].
[edit] Operators
[edit] Specifications (KM-2)
Data from Jane's Aircraft Recognition Guide [3]
General characteristics
- Crew: 2: student, instructor
- Length: 26 ft 4 in (8 m)
- Wingspan: 32 ft 10 in (10 m)
- Height: 9 ft 11 in (3 m)
- Wing area: ()
- Empty weight: 2,469 lb (1,120 kg)
- Max takeoff weight: 3,329 lb (1,510 kg)
- Powerplant: 1× Lycoming IGSO-480-A1A6 piston engine, 340 hp (254 kW)
Performance
- Maximum speed: 234 mph (377 km/h)
- Range: 520 nm (965 km)
[edit] See also
Related development
[edit] References
- ^ a b c Donald, David (Editor) (1997). The Encyclopedia of World Aircraft. London: Aerospace Publishing. ISBN 1-85605-375-X.
- ^ a b c Donald, David; Lake, Jon (editors) (1996). Encyclopedia of World Military Aircraft. London: Aerospace Publishing. ISBN 1 874023 95 6.
- ^ Rendall, David (1995). Jane's Aircraft Recognition Guide. Glasgow, UK: HarperCollinsPublishers, 505. ISBN 0-00-4709802.
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