Tailplane The classical empennage consists of a vertical tail surface and a horizontal tail surface with right and left elevators interconnected by the control transmission. The vertical tail surface of a trapeze shape consists of a vertical stabilizer and a rudder. Flight surfaces and controls The flight surfaces consist of conventional ailerons, elevator, and rudder. Ailerons and elevator are deflected through push rods, while the rudder is controlled by steel cables. There is only one elevator trim. The elevator trim and wing flaps are electrically actuated. Landing gear and brakes The nose gear is of castoring type (not steerable), and consists of a tubular steel leg connected to the lower engine mount attachments and is fitted with a hydraulic shock absorber. The main landing gear system consists of two leaf spring steel struts, wheels with disk brakes, and the wheel fairings which are part of the standard equipment. The struts absorb the landing shocks and are made of quenched and tempered steel. Two wheels 6.00-6 for main landing gear and 5.00-5 wheel for nose are installed. Hydraulic operated brake discs are installed on the aluminum wheels. Wheel brakes are operated individually using the brake pedals either on the pilot or the co-pilot’s side. The parking-brake lever is located on the centre panel, and closes the return valve of the brake lines. Engine and propeller The aircraft is equipped with a Rotax 912 ULS 2 engine (not type certificated), which is of a four cycle, four cylinder horizontally opposed configuration. The cylinder heads are cooled by liquid while the cylinders are cooled by ram air flow. Engine rotation is clockwise, looking from the pilot’s seat. The performance of the engine is 100 HP at maximum take-off power (limited to 5 min.), maximum continuous power is 90 HP, at 2400 RPM. Engine output is transferred to the fixed pitch, 1700 mm diameters two-bladed composite propeller (model with TC EASA. EASA.P.XXX) using a reduction gearbox (with integrated overload clutch). The reduction ratio is 1:2.43. The engine is controlled with a single lever, located between the two seats. The basic particulars of the engine are shown here: Discipline Value Maximum power rating 73.5 kW RPM @ max power 2500 Cruise power rating 69.0 kW @ 2400 rpm Bore 84 mm Stroke 61 mm Displacement 1352 cm3 Compression ratio 10.5: 1
Tailplane The classical empennage consists of a vertical tail surface and a horizontal tail surface with right and left elevators interconnected by the control transmission. The vertical tail surface of a trapeze shape consists of a vertical stabilizer and a rudder. Flight surfaces and controls The flight surfaces consist of conventional ailerons, elevator, and rudder. Ailerons and elevator are deflected through push rods, while the rudder is controlled by steel cables. There is only one elevator trim. The elevator trim and wing flaps are electrically actuated. Landing gear and brakes The nose gear is of castoring type (not steerable), and consists of a tubular steel leg connected to the lower engine mount attachments and is fitted with a hydraulic shock absorber. The main landing gear system consists of two leaf spring steel struts, wheels with disk brakes, and the wheel fairings which are part of the standard equipment. The struts absorb the landing shocks and are made of quenched and tempered steel. Two wheels 6.00-6 for main landing gear and 5.00-5 wheel for nose are installed. Hydraulic operated brake discs are installed on the aluminum wheels. Wheel brakes are operated individually using the brake pedals either on the pilot or the co-pilot’s side. The parking-brake lever is located on the centre panel, and closes the return valve of the brake lines. Engine and propeller The aircraft is equipped with a Rotax 912 ULS 2 engine (not type certificated), which is of a four cycle, four cylinder horizontally opposed configuration. The cylinder heads are cooled by liquid while the cylinders are cooled by ram air flow. Engine rotation is clockwise, looking from the pilot’s seat. The performance of the engine is 100 HP at maximum take-off power (limited to 5 min.), maximum continuous power is 90 HP, at 2400 RPM. Engine output is transferred to the fixed pitch, 1700 mm diameters two-bladed composite propeller (model with TC EASA. EASA.P.XXX) using a reduction gearbox (with integrated overload clutch). The reduction ratio is 1:2.43. The engine is controlled with a single lever, located between the two seats. The basic particulars of the engine are shown here: Discipline Value Maximum power rating 73.5 kW RPM @ max power 2500 Cruise power rating 69.0 kW @ 2400 rpm Bore 84 mm Stroke 61 mm Displacement 1352 cm3 Compression ratio 10.5: 1
ABCD-GD-01-00%20-%20Aeroplane%20General%20Description%20-%2017.02.16%20-%20v1.docx