Toyo T-T.10

Toyo Aircraft was established in June 1952 and their first aircraft, the T-T.10, 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° 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.[1]

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.[1]

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.[1] Production numbers are not known exactly; one report speaks of a "small batch"[2] but only the first two T-T.10s appear in the single engine serial range JA3001 - JA3100,[3] which covers the period August 1952 to September 1955, so they may constitute the whole batch.

• Tokyo Metropolitan College F.A.M.E. Gallery: T-T.10 JA3026[4]

Data from Jane's All the World's Aircraft 1956/57[1]

General characteristics

• Crew: 2
• Length: 7.15 m (23 ft 5 in)
• Wingspan: 8.60 m (28 ft 3 in)
• Height: 2.10 m (6 ft 11 in) tail down
• Wing area: 12.0 m² (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)
• Powerplant: × Lycoming O-290-D2 4-cylinder horizontally opposed air cooled, 100 kW (140 hp)
• Propellers: 2-bladed Sensenich CSM3FM4/C374 fixed pitch

Performance

• Maximum speed: 235 km/h (146 mph, 127 kn) at sea level
• Cruise speed: 190 km/h (120 mph, 100 kn)
• Stall speed: 80 km/h (50 mph, 43 kn) with 30° flaps
• Service ceiling: 4,300 m (14,100 ft) service
• Rate of climb: 3.8 m/s (750 ft/min) initial
• Wing loading: 67 kg/m² (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)

• NACA 2410 airfoil
• Photo of a Toyo T-T.10