The P92 is a two- seater, single strut braced high wing ultra-light aircraft. The main features of the design and construction are direct towards the aim of low weight and low cost. An extensive program of static and dynamic tests has been performed on all the main structural component. The wing box, as the fuselage and the empennages was submitted to the ultimate loads. After a brilliant debut in the European market, the P92 is presented to the North American market. It is a real aircraft, that operates within the limits of costs and weight of an ultra-light plane. Designed and manufactured according. to the international airworthiness standards, the P92 is a true aeronautical product. Like the most well known successful "kit planes", it adopts the high wing design, but depart from the construction of "Welded Tubes and Cloth" for a metallic structure made up of Frames, Spars, Ribs, Skins... This has been accomplished by one of the most known European Designers in the general aviation field, with the aid of modern planning instruments. The P92's performances and flying qualities are so superior that it compares to those planes certified under FAR 23.The wing structure consists of a single spar metal torsion box, with an aluminum leading edge. The latter feature, in providing an aerodynamically clean surface in the relevant portion of the airfoil, increases performances and, being easily detachable, helps to reducing the maintenance and repair costs. The forward fuselage section, which includes the cabin, is formed by welded steel-tubes framework, covered with aluminum panels. A rugged central member collects the wing strut and landing gear loads. The high deformation energy of the steel-tubes framework offers a good protection of the crew in the event of an emergency landing. The light alloy stressed skin tail cone supports the empennage.The all-moving tailplane provides remarkable longitudinal hands-off stability and control power with the minimum drag and weight penalty. Behind the light-alloy tube spar, the metal structure is Dracon covered to minimize the mass-balancing. A wide trim-tab accomplishes also the anti-tab, function. The two stabilator halves are quick detachable The fin has a cantilever structure of light alloy, except for glassfiber tip. Fin and rudder have ribbed light alloy skins. The half-span flaps, electrically activated, allows stall speed under 37 m.p.h. (32 kts, 60 Km/h). With flaps deployed, a steep approach is possible and a very short flare and roll out will result.The ailerons, nearly interchangeable with the flaps, are very effective, which results in an aggressive roll rate. The differential control allows limited use of the rudder in the turns. The flaps and ailerons are made of light alloy structure, Dracon covered. The steel leaf main gear legs provide excellent shock absorption characteristics, are trouble free and require no maintenance. To facilitate inspection, the leg fitting are on the external fuselage bottom wall. Wheels and hydraulic disc brakes are of aircraft type. The brake lever control is located forward between the seats. An hydraulic valve provides the parking brake control. The levered suspension nose gear with rubber shock absorber has been designed to resist to high impact loading in basic training use. The nose gear is directly steerable by the rudder pedals.The leading edge tapering near the wing root allows visibility, also in a steep turn. The engine is set low and the cowling slopes down from the windshields, so forward visibility is excellent. A rear window completes the 360° vision. The cabin, which features extra-large doors, is 41 inches wide and this, combined with all surrounding windows, makes the airplane seem very roomy. Behind the seats there is a large luggage area. The dual control sticks come up forward, between pilots legs, in the conventional manner and there are two throttles, each on the left of the pilot. The dual rudder pedals, of conventional type, control also the nose wheel steering. The flight controls are smooth throughout the range of travel, being all control linkages of aircraft-type. A rocker switch, between the seats, controls the pitch trim. The position indicator is on the instruments panel.Three engine options are available: - ROTAX 582 64HP, two cylinders, two strokes, liquid cooled - ROTAX 912 80HP, four strokes, liquid cooled - LIMBACH L 2000 80HP, four cylinders, four strokes, air cooled. The propeller can be two or three blades. The engine is connected to airframe through the Cr-Mo steel-tube engine mount and the vibration isolating suspensions. The firewall is soundproofing. The fast opening of the cowling allows the complete and easy access to the engine and equipments. The two fuel tanks are built into the composite wing leading edge near the root. Total standard capacity 60 Lt. (16 gal.). Indipendent fuel valves are located in the each side of the cockpit. The Gascolator is installed in the engine vane. Gravity fuel feed when mechanical fuel pump is out. All engines are equipped with a 14 V, 8 to 55. A generator with a 12 V, 18 Ah backup battery. All the circuits are fuses protected.

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