The 1969 W-4 Hot Canary single place open cockpit biplane was intended for pylon racing in the sport biplane class. Featuring negative stagger, the W-4 was registred N4777W.
Engine: Lycoming O-290D, 125hp
Wingspan: 14’9″
Length: 17’0″
Useful load: 314 lb
Max speed: 195 mph
The 1960 Tiny Champ single place cabin high wing monoplane was registered N3632G.
Engine: Continental A-65, 65hp
Wingspan: 20’0″
Length: 19’0″
Useful load: 250 lb
Max speed: 115 mph
Cruise speed: 105 mph
Stall: 60 mph
Range: 250 mph
Bill Warwick built his third plane, the Bantam, first flying in 1966. The first Bantam, N2258B, first flew in June 1966.
Designed for simple fabrication, the Bantam uses no compound curves and very few simple ones. The cockpit area is a steel tube structure taking all wing, gear and engine mount loads. The steerable front wheel has a spring leaf shock absorber. The remaining is wood construction with a plywood cover.
The Bantam is a single-seat, low-wing plane that can use any engine from 65 to 100 hp.
Blueprints cost US$55 in 1972.
Engine: Lycoming O-145, 65 hp
Wingspan: 18 ft 6 in
Length: 13 ft 9 in
Height: 6 ft 0 in
Gross weight: 790 lb
Empty Wt. 535 lbs
Fuel capacity 11.5 USG
Top speed: 140 mph
Cruise speed: 105 mph
Stall 52 mph
ROC: 1000 fpm
TO run: 550 ft
Ldg run: 500 ft
1972-80: Bill Warwick, 5727 W. Clearsite, Torrance, CA 90505 USA.
Airplane builder
A two seat, tandem, open cockpit design, first flown in 1970. Kits were marketed for home-builders with 80-160hp engine options.
Engine: Lycoming O-235, 100 hp
HP range: 65-150
Height: 5.4 ft
Length: 19 ft 9 in
Wing span: 28 ft
Wing area: 126 sq.ft
Speed max: 125 mph
Cruise: 115 mph
Range: 350 sm
Stall: 45 mph
ROC: 1500 fpm
Take-off dist: 500 ft
Landing dist: 600 ft
Service ceiling: 12,000 ft
Fuel cap: 18 USG
Weight empty: 700 lbs
Gross: 1400 lbs
Seats: 2 tandem
Landing gear: tail wheel
The Ward P.45 Gnome was designed and built by M. Ward at Scarle, Lincs, as the smallest aircraft in Britain.
All-wood construction, it was powered by a Douglas motor cycle engine conversion. First flown on 4 August 1967 at Wigsley, piloted by R.A.Fixter. Sold to R.A.Fixter in 1968, it was registered G-AXEI about 1968.
It later went on display at the Lincs Aviation Museum, Tattershall.
Engine: Douglas
Wingspan: 15 ft 9 in
Length: 11 ft 6 in
Mexico
Franciso J. Waltz, Mexico City, was distributor for Aero Commander. Produced in 1959 a high-altitude conversion of de Havilland Heron with 340 hp Lycoming engine for Mexican use under name Super Heron.
The Walter Minor is a family of four, six and twelve-cylinder inverted inline air-cooled engine used on light aircraft. First produced in 1929, the Minor engines have steel cylinders, aluminum heads and overhead valves, with identical bore and stroke of 105 mm (4.1 in) and 115 mm (4.5 in), respectively. Typical power ratings varied from 105 hp to 160 hp. In 2012 Avia continued to produce the Minor.
Variants:
Minor Sc.
Minor M 337
Minor 4-I
Minor 4-II
Minor 4-III
Minor 6-I
Minor 6-II
Minor 6-III
Minor 12 1-MR
Applications:
Aero Ae 45
Aero Ae 50
Aviator Shershen’
Beneš-Mráz Beta-Minor
Fry Esprit VFII
Let L-200 Morava
LIBIS KB-6
LWD Zuch
Manzolini Libellula II
Nord NC.856
Nord NC.859
Nord NC-860
Oeffag O.K.15
Orličan L-40 Meta Sokol
Pasotti Airone
Praga E-210
Praga E-211
Starck AS-57
Zlin 22
Zlin Trener
Specifications:
Minor 4-cylinder
Type: 4-cylinder inverted inline air-cooled
Bore: 105mm (4.14 in)
Stroke: 115mm (4.53 in)
Displacement: 4 Liter (244 cu in)
Length: 1,119mm (44.09 in)
Width: 440mm (17.32 in)
Height: 630mm (24.80 in)
Dry weight: 93kg (205 lb)
Valvetrain: 1 inlet and 1 exhaust valve per cyclinder
Fuel system: 1 claudel carburetor
Fuel type: 68 octane
Cooling system: air-cooled
Power output: 95 hp at 2,550 rpm
Compression ratio: 5.3:1
Power-to-weight ratio: 2.41lb/hp at cruise power
Originally the Walter turbo prop was designed for the harsh Russian environment with limited field maintenance. The engine does not require a hot section inspection, and requires only an inspection every 300 hours.
First run in 1967, the Walter M601 is a turboprop aircraft engine produced by Walter Aircraft Engines of the Czech Republic. The company’s first turboprop, the M601 is used in business, agricultural and military training aircraft.
The turboprop was designed for use on the Let L-410 and the M601 first ran in 1967. It was not suitable for the prototype L-410 and the company developed an upgraded version, the M601A, with a slightly wider diameter.
Variants:
M601A
Initial production variant for early version of the Let L410.
M601B
Production variant for the Let L410UVP.
M601D
Developed for the Let L410UVP.
M601D-1
Agricultural variant for high-cycle operation, used on the PZL Kruk and Ayres Thrush.
M601D-2
Special variant for paradrop aircraft, used on the Do 28 and some Finist conversions.
M601D-11
Agricultural and paradrop variant with a higher Time Between Overhaul of up to 1800 hours.
M601D-11NZ
Downrated variant for use in the FU-24 Fletcher.
M601E
Developed for the Let L410UVP-E.
M601E-11
General use engine with sub-variants of differing TBO.
M601E-11A
Variant of the 11 for use at higher operating altitudes and modified with a low pressure bleed air system for pressurised aircraft.
M601E-21
Variant for the L410-UVP-E used for hot and high operations.
M601F
Variant intended for use on the L420-UVP.
M601FS
M601F-11
M601F-22
M601F-32
M601FS
M601T
Aerobatic variant for use on the PZL Orlik.
M601H-80
now the GE Aviation Czech H80
M601Z
Agricultural variant for use on the Z-37T.
Applications:
Aerocomp Comp Air 10 XL
Aerocomp Comp Air 7
Ayres Thrush
Dornier Do 28
Lancair Propjet
Let Z-37T – TurboČmelák (AgroTurbo)
Let L-410 Turbolet
Let L-420
Myasishchev/SOKOL M-101T
PAC FU-24 Fletcher
Progress Rysachok
PZL-106 Kruk
PZL-130 Orlik
Specifications:
Take off rating: 690 shp / 515 kW
Prop speed: 2080 rpm
Interturbine temp: 710 deg C
Max continuous: 606 shp / 452 kW
Gas generator speed: 36,080 rpm
Prop speed: 1800-2000 rpm
Interturbine temp: 690 deg C
Max reversing rating: 413 shp / 308 kW
Weight: 420 lb / 190.5 kg
M601D-1
Type: Turboprop
Length: 1675 mm
Diameter: 590 mm
Dry weight: 197 kg
Compressor: 2-stage axial compressor and 1-stage centrifugal compressor
Combustors: annular
Turbine: 1-stage high-pressure and 1-stage free
Maximum power output: 544 kW, 490 kW continuous (740 hp, 657 hp continuous)
Turbine inlet temperature: 690°C
Specific fuel consumption: 0.62 lbs/shph
Power-to-weight ratio: 2.76:1 (kW:kg)
Circa 1975 Fred W Wallman Jr built the two-place, open cockpit, high-wing monoplane, Sportplane, registered N4FW. The fuselage and tail were steel tube, and wing was all wood.
The Sorrtplans was first flown on 24 September 1975, piloted by Bert Sissler. Only the one was ever built.
Engine: 115hp Lycoming O-235-C1
Wingspan: 30’0″
Length: 21’6″
Useful load: 566 lb
Cruise speed: 100 mph
Stall: 35 mph
All Aero 