The Fuji LM-1 Nikko is a four-seat liaison aircraft adapted from the design of the Beech T-34 Mentor which was built under licence by Fuji for the Japanese Self-Defense Force.
Flown for the first time on 6 June 1955, the LM-1 employs the wing, undercarriage and tail assembly of the Mentor, and a new centre fuselage.
Engine: 225 hp Continental O-470-13 Wing span: 32 ft 9.5 in Wing area: 177.6 sq.ft Length: 25 ft 11 in Height: 9 ft 7 in Empty weight: 2234 lb Loaded weight: 3375 lb Max speed: 185 mph Cruise: 157 mph Service ceiling: 17,399 ft
The original LM/KM series aircraft were four-seat developments of the Beech T-34A Mentor, the first flying in 1955, and large numbers were delivered to the JMSDF and JGSDF for liaison and training. A tandem two-seat derivative of the Beech T-34 with a Lycoming IGSO-480-AIA6 piston engine entered production in the mid¬1970s as the KM-2B for the JMSDF, and later as the T-3 for the JASDF. Fuji in Japan flew the prototype (JA3725) of the KM-2B two-seat primary trainer on 26 September 1974; this development of the earlier KM-2 combined the airframe and powerplant of that aircraft with the tandem-seat cockpit arrangement of the Beech T-34A Mentor.
Ten KM-2 were ordered for the JMSDF, for delivery by February 1963. Further contracts were to follow, to replace the 45 North American SNJs (Harvards) then in naval service. The prototype KM-2 received its certificate of airworthiness February 1961.
T-5
Fuji has tested a company owned four-seat KM-2 utility aircraft with an Allison 250-B17 turboprop, under the designation KM-2D.
The first KM-2D, flown on 28 June 1984, was a straight conversion of a company-owned piston KM-2 retaining the original four-seat cabin structure.
The JMSDF considered re-engining its fleet of tandem-seat KM-2B trainers, but has now elected to purchase new-build KM¬2Kais, with the first funded in 1986/87. These will be turboprop powered, and will retain the tandem seating of the KM-2B. Deliveries are scheduled for 1988, to begin replacement of the oldest KM-2Bs.
The Japanese Maritime Self-Defence Force took delivery of the definitive turbo-prop powered KM-2D prototype (first flown on 27 April 1988) in August 1988 which was to be tested by the service until March 1989. This prototype, a conversion of a MSDF KM-2B, embodied extensive cabin redesign.
KM 2 Engine: Lycoming IGSO-480 A1A6, 340 hp. Max speed: 227 mph (365 kph) at 16,400ft (5000 m) Cruise, 183 mph (295 kph) Initial climb, 1,560 fpm (7.92 m/sec) Service ceiling, 29,200ft (8900 m) Range, 765 mls (1235 km). Empty weight, 2387 lb (1083 kg) Loaded weight, 3,296 lb (1495 kg). Span, 32 ft 9.75 in (10 m) Length, 26 ft 0.75 in (7.95 m) Wing area, 177.6 sq.ft (16.49 sq.m).
First post-war jet aircraft of Japanese design, the prototype T1F2 flew for the first time on January 19, 1958, powered by a 4,000 lb thrust Bristol Siddeley Orpheus 805 turbo-jet. Two production batches of 20 of this version were built as standard two-seat intermediate jet trainers for the Japanese Air Self-Defence Force, under the designation T1A.
They were followed by the all-Japanese T1F1 (JASDF designation TIB) with a 2,645 lb thrust J3 IHI 3 turbojet produced by Ishikawajima-Harima. The prototype of this version flew on May 17, 1960, and 20 production models were ordered by the JASDF for delivery between August 1962 and March 1963.
Fuji T1F2 (T1A)
T1A / T1F2 Engine: 1 x 4,000 lbs.t. (1814 kgp) Bristol Siddeley Orpheus 80506. Span: 34 ft 5.5 in (10.5 m) Length: 39 ft 9.25 in (12.12 m) Wing area: 239 sq.ft (22.22 sq.m) Height: 13ft 3in Empty weight: 5,335 lb (2 420 kg) Loaded weight: 9,150 lb (4 238 kg) Gross weight: 10,6701b Max speed: 576 mph (921 kph) at 20,000ft (6100 m) Cruise: 397 mph (640 kph) Initial climb: 3,460 fpm (17.3 m/sec) Ceiling: 52,490 ft (16000 m) Range: 806 mls (1297 km). Max rate of climb at SL: 6,100 ft/min
1961: So 18, 2-chrome, Marunouchi, Chiyoda-ku, Tokyo
Successor to Nakajima Aircraft Company, established 15 July 1953 with factory at Utsunomiya City. Built Cessna L-19E Bird Dog observation aircraft under license. Concluded agreement with Beech in November 1953 to manufacture Beech B45 Mentor trainers; total of 124 built, deliveries commencing August 1954. From Mentor Fuji developed LM-1 Nikko four-seat liaison aircraft, first flown June 1955. Similar two-seat KM-2 developed. KM-2B with widened fuselage and tandem seating for two selected as JASDF primary trainer in August 1975. Fuji assembled or built more than 120 Bell 204B/B2 helicopters from 1962. Fuji T-1 two-seat jet trainer was first postwar Japanese jet aircraft. Forty T-1 As built with Bristol Orpheus engines, and 20 T-1 Bs with Japanese engines. FA-200 Aero Subaru four-seat light aircraft first flown August 31,1965 (nearly 300 built). Work on FA-300 twin-engined light transport began 1971, continued as joint venture with Rockwell International, U.S.A., following agreement signed June 28,1974, as Rockwell Commander 700; prototype first flown in Japan on November 13,1974 and 30 delivered before cooperation ended in 1980 (also development of the higher-powered FA-300/Commander 710 then ended). Current programs include production of the T-5 primary/basic trainer for the JMSDF (as turboprop development of the KM-2, with KM-2Kai prototype flying in April 1988) AH-1S attack helicopter, 205B/UH-1J general purpose helicopters (205Bs from 1995, military UH-1s from 1993), participation in the Mitsubishi F-2 program, subcontract work on the Mitsubishi F-15J and Kawasaki P-3C and T-4, manufacture of assemblies for a range of Boeing airliners, production of UAVs, and participation in space programs.
The Valentino Fry Esprit VFII has flaps on rear fuselage, both sides, mechanically actuated. The Al 6061 landing gear has hydraulically actuated brakes, with 500×5 Celeveland units.
The VF-II SC is the supercharged version of the VF-II. It is equipped with a LOM Praha M-332 AK Engine and a MTV 175-7 3 blade propeller.
Esprit VFII Engine: Rolls-Royce O-200A Wing Span: 6.090 m Length: 5.600 m Height @ Cockpit: 1.200 m Height @ Tail: 1.750 m Wing Area: 6.056 sq.m Elevator Area: 0.79 sq.m Empty Weight: 358 kg MTOW: 490 kg Wing Load: 81 kg/sq.m Fuel capacity: 65 lt AVAGAS 100 LL Propeller: MTV-1F / 170-08 VF II (Mühlbauer) Electrical Constant Speed Propeller Prop Diameter: 1700mm Top level speed @ 500ft MSL: 185 kt Design speed vd: 230 kt Never exceed speed vne: 206 kt Manouver speed va: 133 kt Stall speed, power off vso: 54 kt Best rate of climb speed vy: 74 kt Practical climb speed: 100 kt Best rate of climb: 1800 ft/min max. positive load: 6g max negative load: 3g
Esprit VFII SC Engine: LOM Praha M-332 AK Propeller: MTV 175-7 (Mühlbauer) Constant Speed Propeller (electrical) 3 blade Prop Diameter: 1750mm Wing Span: 6.090 m Length: 6.000 m Height @ Cockpit: 1.200 m Height @ Tail: 1.750 m Wing Area: 6.056 sq.m Elevator Area: 0.79 sq.m Empty Weight: 365 kg MTOW: 490 kg Wing Load: 81 kg/sq.m Fuel 65 lt, 78-98 oct Automotive Max speed: 205 kt (IAS) Max speed @ 7000 ft: 195 kts (TAS) Max speed @ 12000 ft: 210 kts (TAS) Design speed vd: 230 kt Manouver speed va: 133 kt Stall speed, power off vso: 54 kt Best rate of climb speed vy: 74 kt Practical climb speed: 100 kt Best rate of climb: 2700 ft/min max. positive load: 6g max negative load: 3g
This small biplane of generally Farman-like configuration was built in Pressburg, Austria-Hungary (today Bratislava, Slovakia). The elevators and the ailerons were operated by a lever, while the rudder was operated by a separate lever. It was powered by a German-built 25 hp 3-cylinder engine, driving a propeller of 1.8 m diameter.
Engine: 25 hp Prop diameter: 1.8 m Span: 6.5 m Length: 7.5 m Wing area: 25 sq.m Take-off weight: 250 kg
A metal monocoque aircraft kit with 2 seats side by side. The MD-11 can accommodate engines up to 200hp. Built with 2024 T-3 aluminium. First flown in 1993. The standard kit price in 1996 was US$19,500.
Engine: Franklin, 120 hp. HP range: 100-180. Height: 6 ft. Length: 24.5 ft. Wing span: 29.5 ft. Wing area: 155.9 sq.ft. Weight empty: 925 lbs. Gross: 1800 lbs. Speed max: 180 mph. Cruise: 125 mph. Range: 875 sm. Stall: 40 mph. ROC: 1000 fpm. Take-off dist: 500 ft. Landing dist: 400 ft. Service ceiling: 16,000 ft. Seats: 2. Landing gear: tail wheel. Cabin width: 43 in
Engine: Walter Lom, 140 hp HP range: 100-200 Fuel capacity: 43 USG Height: 6.5 ft Length: 27.5 ft Wing span: 29.5 ft Wing area: 177 sq.ft Empty weight: 1150 lb Gross weight: 2000 lb Top speed: 200 mph Cruise: 150 mph Stall: 35 mph Range: 700 sm Rate of climb: 1000 fpm Takeoff dist: 500 ft Landing dist: 400 ft Service ceiling: 16,000 ft Seats: 2 Landing gear: tail Cabin width: 43 in
Engine: Lycoming HP range: 150-180 Height: 6.5 ft Length: 27.5 ft Wing span: 29.5 ft Wing area: 177 sq.ft Fuel capacity: 43 USG Empty weight: 1150 lb Gross weight: 2000 lb Top speed: 200 mph Cruise: 150 mph Stall: 35 mph Range: 700 sm Rate of climb: 1000 fpm Takeoff dist: 500 ft Landing dist: 400 ft Service ceiling: 16,000 ft Seats: 2 Landing gear: tail Cabin width: 43 in
USA Friesley Aircraft Corp., Gridley, CA, built single Falcon, large transport biplane, 12 passengers, 2 x 400hp Liberty, finished mid-1920, not flown until 1921.
