SOCATA Gardan GY-80 Horizon

The French company Sud Aviation produces, in addition to the well-known jet transport "Caravelle", also the modern and successful four-seater sports aircraft "Horizon". Although there is considerable competition in this class, mainly American aircraft, "Horizon" is produced not only for the domestic market, but also exports, mainly to Switzerland. Designer Yves Gardan created the "Horizon" under the assumption that it had to compete both in flight and price between the Cessna 172, Piper "Cherokee" and Beech "Musketeer" types. He succeeded in both.

The first flight of the prototype took place in July 1960, but the aircraft entered serial production only after thorough practical tests in the summer of 1963. In order to fully satisfy the various and demanding requirements, the "Horizon" is delivered in four versions - with an engine of 150 or 160 к and with a fixed or automatically adjustable propeller. This changes the performance significantly. In addition, the aircraft is optionally equipped with various instruments, up to equipment for flight without vision (IFR conditions).

TECHNICAL DESCRIPTION
The GY.80 "Horizon" is a four-seater low-wing all-metal aircraft with a retractable undercarriage.
The trapezoidal wing is characterized by a leading edge that is bent forward at the fuselage. The entire trailing edge is occupied by split landing flaps and ailerons. The construction of the wing and flaps is all-metal. The landing flaps are electrically operated. The wing profiling is very interesting - at the fuselage it is a modified NACA 4413.6 profile and at the end it is a modification of NACA 63517.
The square-section hull with rounded corners is an all-metal shell construction. The spacious four-seater cabin is equipped with entrance doors on both sides. The front seats are adjustable. The luggage compartment is behind the rear undivided backrest. Steering is a double steering wheel, the dashboard is equipped with very clear basic instruments and can be supplemented with instruments for flight under IFR.

The tail surfaces are also all metal. The floating elevator is complete and has a large balancing surface. The relatively large rudder is arrow-shaped, while the keel surface extends further forward, similar to a wing. The symmetrical profile of the tail surfaces is very thin.

The landing gear consists of a three-wheel retractable undercarriage with mechanical control. Chassis shock absorbers are oil-pneumatic. Wheels with low-pressure tires measuring 380x150 have hydraulic disc brakes and a manual parking brake. When the landing gear is retracted, half of the wheels protrude from the outline of the aircraft. The end of the hull is equipped with an auxiliary spur.

Engine group. The aircraft is powered by a 4-cylinder American Lycoming engine, either type 0-320-A2C and 150 hp at 2700 rpm or type 0-320-B2B with 160 hp at 2700 rpm. The propeller is either fixed metal or adjustable Hartzell type with constant speed. The two fuel tanks have a total capacity of 160 1.
Coloring. The basic one, supplied as standard and drawn on the drawing, is white-red. Any other combinations are also supplied.
Technical data and performance (for version with 160 к engine in parenthesis): span 9.70, length 6.57, height 2.60 m, bearing area 13 m², surface load 87 kg/m², empty weight 590 kg (608 kg ), take-off weight 1,020 kg (1,100 kg).
Top horizontal speed 229 to 245 km/h - depending on engine and propeller type, cruising speed at 66% power at 2000 m is 205 to 213 km/h. Max. permissible speed 300 km/h. Climb rate at the ground 3.2 to 3.5 m/s, practical reach 4200 to 4700 m. Range at 66% engine power 1260 km, take-off length over a 15 m obstacle 450 m, landing length over a 15 m obstacle 450 m.

Klemm L-25