THE P-92J IS CERTIFIED UNDER JAR-VLA
INTERNATIONAL AIRWORTHINESS REGULATIONS.

The P92-J is a single strut braced high wing aircraft, and carries a useful load of two occupants plus luggage and fuel for more than four hours with a Take-Off Weight of only 1146 Ibs.
This was made possible by accurate engineering and design of the structure and systems and by the adoption of a light and compact power unit of modern conception.
Since the performance as well as the direct and indirect costs depend on the weight and power of the machine, a remarkable advantage is gained from both these point of view.
In other words, the P92-J does the same things and better (private or commercial use) with less weight and power than the older generation aircrafts. Therefore:

MAIN FEATURES:

- A welded steel tube framework encloses the cabin, covered with aluminum panels. This strong structure is highly resistant to the heavy loads imposed on basic training aircraft and provides good protection for the crew in case of an emergency landing.
- The wing structure consist of a single spar metal torsion box with a one-piece molded reinforced fiberglass leading edge. The latter feature in providing an aerodynamically clean surface , increases performance and being easily detachable, helps to reduce maintenance and repair costs.
- The light alloy stressed-skin tail cone supports the empennage.
- The electrically activated half-span flaps, allow stall speeds under 35 Kts. With flaps deployed, a steep approach is possible resulting in a very short flare and roll out. - The ailerons, almost interchangeable with flaps, are very effective, resulting in an aggressive roll rate. - The all-moving tailplane provides excellent longitudinal stick-free stability and control power with the minimum drag and weight penalty.
- The instrument panel is designed to accommodate optional instrumentation up to an IFR configuration.
- A rocker switch located between the seats, controls the pitch trim. The position indicator is installed on the instrument panel.
- The wide windshield not interested by any structural element is carried up over the pilot's head.
- The leading edge tapering near the wing root allows visibility even in a steep turn.
- The engine is mounted low and the cowling slopes down away from the windshield, so forward visibility is excellent.
- A rear window completes the 360° vision.
- The 3 ft. 8 in., wide cabin has extra large doors and this feature together with the side windows make the aircraft seem very spacious. A large luggage area is located behind the seats. The cabin is provided of: two adjustable seats; safety belt system; fresh air inlet doors; cabin heating system; cabin overhead loudspeakers.
- The particular shape of the door provides extra elbow room and comfort for the pilot.
- The dual control sticks come up forward between the pilot's legs. The stick grip allows the installation of trim switch and mike switch.
- The conventional type dual rudder pedals also control the nose wheel steering.
- The brake control lever is located between the two seats. The parking brake function is obtained through an hydraulic valve.
- A 59,6 KW (81 HP) ROTAX 912A2, four opposed cylinders, four stroke liquid/air cooled engine and integrated reduction gear (1:2.273) drives a high efficiency two-bladed propeller with spinner.
- The fuel consumption in cruise condition is below 3,5 Gal/hr (13 IVh) of automotive gasoline. The TBO spans to 1200 hours.
- The engine firewall is soundproofed. The upper and lower engine cowlings are quickly removable permitting inspection and easy access to the engine and its accessories.
- The forward section of each wing in the proximity of the root, incorporates a 9,3 Gallons (35 It) capacity fuel tank.
- Independent fuel flow valves are located on either side of the cockpit and are easily accessible by the pilot.
- Gravity fuel feed backup if the mechanical pump fails.
- The battery has a capacity of 18Ah.
- A 14 V, 21A generator is an integral part of the engine.
- The spring steel undercarriage legs provides excellent shock absorption characteristics are trouble free and require no maintenance. To facilitate inspection, the leg fittings are externally mounted on the under section of the fuselage.
- The levered suspension nose gear with a rubber shock absorber has been designed to resist high impact loads during basic training programs.