Fuji T-5

The 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.

T-5
Role Basic trainer
Manufacturer Fuji Heavy Industries
First flight 28 June 1984
Introduction 1988
Primary user Japan Maritime Self-Defense Force
Developed from Fuji KM-2

Design and development

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 Mentor) as a primary trainer for the Japan Maritime Self-Defense Force. Fuji refitted a KM-2 with an Allison Model 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]).

The T-5 is an all-metal low-wing cantilever monoplane powered by an Allison 250-B17D turboprop with a three-bladed constant speed propeller. It has a retractable tricycle landing gear with the main gear retracting inwards and nose gear rearwards. The T-5 has an enclosed cabin with a sliding canopy and two side-by-side seats, and dual controls, in the aerobatic version and four seats in pairs in the utility version.

Operational history

The KM-2Kai was ordered by the JMSDF as the 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 Air Training Squadron at Ozuki Air Field.[3] The original KM-2 is no longer in service.

Operators
 Japan

Specifications (T-5)

Data from Jane's Aircraft Recognition Guide [4]

General characteristics

  • Crew: 2
  • Length: 8.4 m (27 ft 7 in)
  • Wingspan: 10 m (32 ft 10 in)
  • Height: 2.9 m (9 ft 6 in)
  • Wing area: 16.5 m2 (178 sq ft)
  • Airfoil: root: NACA 23016.5; tip: NACA 23012[5]
  • Empty weight: 1,082 kg (2,385 lb)
  • Max takeoff weight: 1,805 kg (3,979 lb)
  • Powerplant: 1 × Allison Model 250-B17D turboprop, 261 kW (350 hp)
  • Propellers: 3-bladed consytant-speed propeller

Performance

  • Maximum speed: 357 km/h (222 mph, 193 kn) at 2,440 m (8,005 ft)
  • Cruise speed: 287 km/h (178 mph, 155 kn)
  • Stall speed: 104 km/h (65 mph, 56 kn) [6]
  • Never exceed speed: 413 km/h (257 mph, 223 kn)
  • Range: 945 km (587 mi, 510 nmi)
  • Service ceiling: 7,620 m (25,000 ft)
  • Rate of climb: 8.6 m/s (1,690 ft/min)
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See also

Related development

References
  1. Taylor, JWR (Editor) (1988). Jane's All the World's Aircraft, 1988-1989. Coulsden, UK: Jane's Information Group. ISBN 0-7106-0867-5.CS1 maint: extra text: authors list (link)
  2. Donald, David; Lake, Jon, eds. (1996). Encyclopedia of World Military Aircraft. London: Aerospace Publishing. ISBN 1-874023-95-6.
  3. "Scramble". Archived from the original on 2007-04-03. Retrieved 2007-04-26.
  4. Rendall, David (1995). Jane's Aircraft Recognition Guide. Glasgow, UK: HarperCollinsPublishers. pp. 505. ISBN 0-00-4709802.
  5. Lednicer, David. "The Incomplete Guide to Airfoil Usage". m-selig.ae.illinois.edu. Retrieved 16 April 2019.
  6. Taylor, M J H (editor) (1999). Brassey's World Aircraft & Systems Directory 1999/2000 Edition. London: Brassey's. ISBN 1-85753-245-7.CS1 maint: extra text: authors list (link)
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