Fuji T-5
From Wikipedia, the free encyclopedia
| T-5 | |
|---|---|
| Type | Basic trainer |
| Manufacturer | Fuji |
| Maiden flight | 1988 |
| Introduced | 1988 |
| Primary user | Japanese Air Force |
| Developed from | Fuji KM-2 |
| Variants | none |
Fuji T-5 or KM-2Kai is a Japanese turboprop-driven primary trainer aircraft, which is a development of the earlier Fuji KM-2. The student and the instructor sit side-by-side.
Contents |
[edit] History
The Fuji T-5 was developed by Fuji Heavy Industries as a replacement for the piston-engined Fuji KM-2 (itself a development of the Beechcraft T-34) as a primary trainer for the Japan Maritime Self-Defense Force. Fuji refitted a KM-2 with an Allison 250 turboprop engine in place of the original Lycoming piston engine, the resulting KM-2D first flying on 28 June 1984 [1] and being certified on 14 February 1985 [1] [2]. The KM-2Kai is a further development of the KM-2D, with a modernised cockpit with side-by-side seating and a sliding canopy replacing the original KM-2's car type side doors [2] (which were retained by the KM-2D[1]).
[edit] Operational history
The KM-2Kai was ordered by the JMSDF as the Fuji T-5 in March 1987[2], with deliveries of the KM2-Kai to the Japanese Self Defence Forces beginning in 1988, with a total of 40 being built. The T-5 serves with the 201 Kyoiku Kokutai at Ozuki in Japan [3]. The original KM-2 is no longer in service.
[edit] Operators
[edit] Specifications (T-5)
Data from Jane's Aircraft Recognition Guide [4]
General characteristics
- Crew: 2: student, instructor
- Length: 8.4 m (27 ft 8 in)
- Wingspan: 10 m (32 ft 11 in)
- Height: 2.9 m (9 ft 8 in)
- Wing area: 16.5 m² [2] (178 ft²)
- Airfoil: NACA 23016.5/23012 (root/tip) [5]
- Empty weight: 1,082 kg (2,385 lb)
- Max takeoff weight: 1,805 kg (3,979 lb)
- Powerplant: 1× Allison 250-B17D turboprop, 261 kW (350 hp)
Performance
- Never exceed speed: 413 km/h (223 knots, 256 mph)
- Maximum speed: 357 km/h (193 knots, 222 mph) at 2,440 m (8,000 ft)
- Cruise speed: 287 km/h (155 knots, 178 km/h)
- Stall speed: 104 km/h [5] (56 knots, 65 mph) (flaps down)
- Range: 945 km (510 nm, 587 mi)
- Service ceiling 7,620 m (25,000 ft)
- Rate of climb: 8.6 m/s (1,700 ft/min)
Armament
- None fitted as standard
[edit] References
- ^ a b c Taylor, JWR (Editor) (1988). Jane's All the World's Aircraft, 1988-1989. Coulsden, UK: Jane's Information Group. ISBN 0 7106-0867-5.
- ^ a b c d Donald, David; Lake, Jon (editors) (1996). Encyclopedia of World Military Aircraft. London: Aerospace Publishing. ISBN 1 874023 95 6.
- ^ Scramble. Retrieved on 2007-04-26.
- ^ Rendall, David (1995). Jane's Aircraft Recognition Guide. Glasgow, UK: HarperCollinsPublishers, 505. ISBN 0-00-4709802.
- ^ a b Taylor, M J H (editor) (1999). Brassey's World Aircraft & Systems Directory 1999/2000 Edition. London: Brassey's. ISBN 1 85753 245 7.
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