Fuji T-5
| T-5 | |
|---|---|
| |
| Role | Basic trainer |
| Manufacturer | Fuji Heavy Industries |
| First flight | 28 June1984 |
| Introduction | 1988 |
| Primary user | Japan Maritime Self-Defense Force |
| Developed from | Fuji KM-2 |
TheFuji T-5orKM-2Kaiis a Japanese turboprop-driven primarytrainer aircraft,which is a development of the earlierFuji KM-2.The student and the instructor sit side-by-side.
Design and development
[edit]The Fuji T-5 was developed byFuji Heavy Industriesas a replacement for the piston-enginedFuji KM-2(itself a development of theBeechcraft T-34 Mentor) as a primary trainer for theJapan Maritime Self-Defense Force.Fuji refitted a KM-2 with anAllison Model 250turbopropengine in place of the original Lycomingpiston engine,the resultingKM-2Dfirst flying on 28 June 1984[1]and beingcertifiedon 14 February 1985.[1][2]TheKM-2Kaiis a further development of the KM-2D, with a modernised cockpit with side-by-side seating and a slidingcanopyreplacing 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
[edit]The KM-2Kai was ordered by the JMSDF as the T-5 in March1987,[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 atOzuki Air Field.[3]The original KM-2 is no longer in service.
Operators
[edit]
Specifications (T-5)
[edit]Data fromJane'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-B17Dturboprop,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)
See also
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Related development
References
[edit]
- ^abcTaylor, JWR, ed. (1988).Jane's All the World's Aircraft, 1988-1989.Coulsden, UK: Jane's Information Group.ISBN0-7106-0867-5.
- ^abcDonald, David; Lake, Jon, eds. (1996).Encyclopedia of World Military Aircraft.London: Aerospace Publishing.ISBN1-874023-95-6.
- ^"Scramble".Archived fromthe originalon 2007-04-03.Retrieved2007-04-26.
- ^Rendall, David (1995).Jane's Aircraft Recognition Guide.Glasgow, UK: HarperCollinsPublishers. pp.505.ISBN0-00-4709802.
- ^Lednicer, David."The Incomplete Guide to Airfoil Usage".m-selig.ae.illinois.edu.Retrieved16 April2019.
- ^Taylor, M J H, ed. (1999).Brassey's World Aircraft & Systems Directory 1999/2000 Edition.London: Brassey's.ISBN1-85753-245-7.