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Gardan GY-20 Minicab / GY-201



M. Yves Gardan designed the GY 201 Minicab in 1949 as a two seater with side by side seating and dual control, which first flew in 1949. The fuselage is a wooden open girder structure; the forward part around the cockpit being plywood lined, the remainder fabric covered. The fin is built integral with the fuselage. The tailplane is a single piece plywood covered structure, and the elevator and rudder have fabric covered wooden frames. The wing section is NACA 23015 at the root and 23010 at the tip. The wing structure consists of a laminated spruce and plywood main box spar, a diagonal drag spar and a rear false spar, with lattice type ribs. Forward of the main spar is plywood covered to form a torsion box, the remainder of the wing being fabric covered. Split flaps are installed. The two main undercarriage legs are mounted on the main spar with rubber in compression springing. An 11 Imp. gallon fuel tank is fitted just behind the firewall.

In 1949 his GY-20 Minicab won the world record for speed and distance in a straight line for an aircraft of less than 1102 lb (500kg) maximum gross weight, flying from Paris to Rabat in 10h of flight, 1135 mile being covered at 109mph average (1826km at 185kph) with a Continental 65hp motor. More than 100 Minicabs were made and it is still being built by US homebuilders under the name of Cavalier in 1983.

In 1952, the 90hp version of the Minicab appeared, with retractable undercarriage and called the Super-Cab. Continental engines from 65 to 100 h.p. may be installed.



Production was entrusted to the Constructions Aernautiques du Bearn, which delivered the first aircraft in 1952, and support for this light type subsequently passed to SIPA (the Société Industrielle Pour l’Aeronautique). There were two production variants of the Minicab, the GY.20 and GY.201, these differing from each other only in details of equipment and other small features.


One of the French G.A.B. Supercabs undergoing fully-instrumented
test flying at Villacoublay; Jacques Noetinger is the pilot.

Produced in limited numbers between 1952 and 1958, the design was acquired by A.W. Ord-Hume in Britain, who anglicised the plans. Adjusted them for home builders, the aircraft has subesequently proved extremely popular. The aircraft is marketed in North America as the Hawk BM.4 by Miranda Aircraft of Canada.



Engine: l x Continental A65-8, 48.5kW (65hp).
Span: 7.59m (24ft 11 in).
Length: 5.45m (17 ft 10.5 in).
Max T/O weight: 485 kg (1,069 lb).
Max speed: 124 mph at sea level.
Operational range: 466 miles.
Seats: 2

Engine: Continental, 90 h.p.
Span: 25 ft 0 in.
Length: 17 ft 0 in.
Wing Area: 107 sq. ft.
Empty Weight: 750 lb.
Loaded Weight: 1235 lb.
Wing Loading: 11.5 lb/sq. ft.
Max. Speed: 124 mph.
Cruise Speed: 110 mph.
Stall Speed: 50mph.
Initial Climb: 680 fpm.
Range: 360 miles.

Engine: Continental O-200A, 100 h.p.
Cruise: 120 mph
ROC: 1000 fpm.
Span: 25ft
Length: l7ft l0in
Empty weight: 800lb
Gross weight: 1234 lb

Engine: Revmaster VW, 65 hp. Stall: 38 kt / 43 mph / 70 kmh
Cruise: 97 kt / 112 mph / 180 kmh
VNE: 107 kt / 123 mph / 198 kmh
Empty Weight: 270 kg / 595 lbs
MTOW Weight: 485 kg / 1069 lbs
Climb Ratio: 600 ft/min / 3 m/s
Take-off distance (50ft obstacle): 1150 ft / 350 m
Landing distance (50ft obstacle): 1080 ft / 330 m



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