04/30/2011. Remarks by Johan Visschedijk: "Christopher Turner of Newcastle-upon-Tyne, UK, started design of this homebuilt aircraft in June 1974, while construction started in May 1975. The aircraft was registered G-BEBO (c/n PFA 046-10127) on June 30, 1976, under the designation Pheonix Currie Wot. Reportedly the design was developed from that pre-WW II type, but did bears no resemblance to it whatsoever, and the 125 hp Avco Lycoming O-290-3 engine had much more power than the original 40 hp JAP J-99 two-cylinder engine.

By the time of the first flight on October 14, 1979, Turner had moved to York and the designation had officially been altered to Turner TSW, which stood for Turner Special Wot. The aircraft was destroyed in a hangar fire at High Flatts Farm on October 19, 2002, by which time it was designated Turner TSW-2.

Pictured here is the second and last example of the type, produced by James Richard Woolford and Kingsly Maxwell Thomas, both of Helston, UK. The aircraft was registered G-BLPB (c/n TA-001) on October 19, 1984 as a Turner TSW Hot Two Wot.

First flown in 1986, powered by an 150 hp Lycoming O-320, the aircraft is still registered as of this day although reregistered to four subsequent new owners, while the designation has also changed to Turner TSW-2, and the PFA c/n 046-10606 has replaced the original TA-001."

Type: Two-seat lightweight biplane.
Wings: Braced single-bay biplane. Wing section NACA M6. Thickness/chord ratio 12%. Dihedral on upper wings 0°; lower wings 3° 30'. Incidence on upper wings 3° 30'; lower wings 4°. Conventionally staggered wings, with N-type inter plane and center section struts. Streamline section flying and landing wires. Conventional wooden structure of spruce, with plywood leading edge and fabric covering. Plain ailerons, of similar construction, on all four wings. No flaps. No trim tabs. Cut-out in trailing edge of upper wing center section.
Fuselage: Conventional structure of wood with plywood skins.
Tail unit: Cantilever wooden structure of spruce, with all surfaces fabric covered. Fixed incidence tail plane. No trim tabs.
Landing gear: Non-retractable tail skid type. Two side Vs and half-axles hinged to lower fuselage. Shock-absorption by rubber bungee. Goodyear main wheel tires size 6.00-6, pressure 1.38 bar (20 lb/sq.in).
Power plant: One 125 hp Avco Lycoming O-290-3 flat-four engine, driving a two-blade fixed-pitch wooden propeller with spinner. Fuel tank in fuselage, aft of firewall, capacity 16.81 gal (63.6 l). Refueling point on upper surface of fuselage. Oil capacity 2.04 gal (7.6 l).
Accommodation: Pilot and passenger in tandem open cockpits. Removable cover for forward cockpit when flown solo. Baggage locker aft of pilot's cockpit.

Wing span (both): 20 ft 0 in (6.10 m)
Wing chord, constant (both): 3 ft 6 in (1.07 m)
Wing area, gross: 140 sq.ft (13.01 sq.m)
Wing aspect ratio: 5.7
Length overall: 19 ft 0 in (5.79 m)
Height overall: 6 ft 9 in (2.06 m)
Tail plane span: 7 ft 0 in (2.13 m)
Wheel track: 5 ft 0 in (1.52 m)
Wheel base: 12 ft 11 in (3.94 m)
Propeller diameter: 6 ft 0 in (1.83 m)
Empty: 770 lb (349 kg)
Fuel max: 100 lb (45 kg)
Take off and landing max: 1,250 lb (567 kg)
Max level speed at sea level: 150 mph (241 kmh)
Max cruising speed at sea level: 100 mph (161 kmh)
Econ cruising speed at sea level: 85 mph (137 kmh)
Stall speed, engine idling: 54 mph (87 kmh)
Max rate of climb at sea level: 1,100 ft (335 m)/min
Range with max fuel, 2.4 gal (9 l) reserves: 200 mls (322 km)