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Toyo Aircraft Manufacturing Co T-T.10



Toyo Aircraft was established in June 1952 and their first aircraft, the T-T.10 designed by Yoshio Hashiguchi, was completed by the end of the year. It is of mixed construction; the wing is built entirely from wood and fabric around two spars, with a plywood skin enclosed within fabric. The flaps and ailerons are wood framed and fabric covered. In planform the wings are straight tapered with rounded tips; most of the taper is on the trailing edge. There is 6 degrees of dihedral. The T-T.10's tail surfaces are also straight tapered with rounded tips, generally wood framed with fabric covering. Its horizontal tail is mounted at the top of the fuselage. The elevators have a cut-out to allow rudder movement, as the latter extends down to the keel. There is a trim tab on the port elevator.




The fuselage of the T-T.10 is fabric covered over a welded chrome-molybdenum steel frame. The engine is a 140 hp (104 kW) Lycoming O-290-D2 flat four, driving a two bladed propeller. Student and instructor sit in tandem with dual controls under a multi-framed, continuous, two part sliding canopy. The rear fuselage line is raised compared with the forward section, but not to the full canopy height. The T-T.10 has conventional landing gear, with narrowly faired cantilever, coil spring damped mainlegs and a tailwheel.

The first T-T.10, registration JA3026, flew for the first time on 30 December 1952; the first production model (JA3049) followed soon after, on 11 February 1953. Production numbers are not known exactly; one report speaks of a "small batch" but only the first two T-T.10s appear in the single engine serial range JA3001 - JA3100, which covers the period August 1952 to September 1955, so they may constitute the whole batch.

One aircraft is on display at the Tokyo Metropolitan College F.A.M.E. Gallery: T-T.10 JA3026.




Engine: Lycoming O-290-D2, 100 kW (140 hp)
Propeller: 2-bladed Sensenich CSM3FM4/C374 fixed pitch
Wingspan: 8.60 m (28 ft 3 in)
Length: 7.15 m (23 ft 5 in)
Height: 2.10 m (6 ft 11 in) tail down
Wing area: 12.0 sq.m (129 sq ft)
Aspect ratio: 6.0
Airfoil: NACA 1415 at root, 2410 (modified) tip
Empty weight: 568 kg (1,252 lb)
Gross weight: 800 kg (1,764 lb)
Fuel capacity: 90 L (19.8 Imp gal; 23.8 US gal)
Maximum speed: 235 km/h (146 mph; 127 kn) at sea level
Cruising speed: 190 km/h (118 mph; 103 kn)
Stall speed: 80 km/h (50 mph; 43 kn) with 30° flaps
Service ceiling: 4,300 m (14,108 ft) service
Rate of climb: 3.8 m/s (750 ft/min) initial
Wing loading: 67 kg/sq.m (14 lb/sq ft)
Power/mass: 8.0 kg/kW (13.1 lb/hp)
Take-off distance to clear 15.25 m (50 ft): 290 m (950 ft)
Landing distance from 15.25 m (50 ft): 300 m (985 ft)
Crew: 2



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