The P2004 Bravo is a cantilevered high wing, twin side by side seat aeroplane, powered by a Rotax 912 73 kW (100hp) engine. Ideal for tourism and flying schools, the P2004 Bravo widens the large family of Tecnam Ultralight Aircraft. The “Bravo” features a refined aerodynamic with a tapered cantilevered wing. Laminar airfoils, large slotted flaps with up-turned wing tips lead, together with a streamlined fuselage, to a high performance aeroplane with increased cruise speed and range. P2004 Bravo is the result of Tecnam’s continuous improvement arising from the experiences of a varied and prolonged use overtime of hundred of planes in the most different conditions. Furthermore, the continuous research and development in the aerodynamics, structures, and system, has been the key to the success. The plane outstanding performance and flying qualities together with low operating costs, easy piloting and maintenance, make of this aircraft an excellent solution for the flying-schools and training activity, and also for many other missions as touring, territory surveillance, patrol, etc. A long experience in this field has allowed to realize a simple and light structure, easy to inspect and repair, by using many original design solution, manufacturing methods and tooling. The wing structures consist of a single spar metal torsion box with easy detachable leading edge of conventional metal structures. In the leading edge section, distant from the cabin, is located in wing an integral fuel tank (2x50 Lt.). Rear windows complete the 360° vision. A large luggage area is placed behind the seats. The dual control sticks come up forward, between pilot’s leg, in the conventional manner. The dual rudder pedals, of conventional type, control also the nose wheel steering. The all-moving tailplane provided remarkable longitudinal hand-off stability and control power with the minimum drag and weight penalty. A wide control trim-tab accomplishes also the anti-tab function. A push-button switch, on the stick grip, controls the pitch trim. The position indicator is on the instrument panel. The wide slotted flaps, electrically activated, allow stall speed lower than 64 Km/h . With flaps deployed, a steep approach is possible: a very short flare and roll out will result. The ailerons, are very effective, allowing an aggressive roll rate. The flaps and aileron are made of light alloy structure. The wide instrument panel is designed to accommodate standard and full optional instrument configuration. The new fast opening of the cowling allows the complete and easy access to the engine and equipment. The engine is set low and the cowling slopes down from the windshield, giving an excellent forward visibility. The engine is connected to the airframe through the Cr-Mo steel-tube engine mount and by vibration isolating suspensions. The firewall is soundproofed. One 73 kW (100 hp) Rotax 912ULS four-cylinders four-stroke liquid/air cooled engine, integrated reduction gear (1:2.4286) driving a two-blade wooden propeller is installed . The gascolator is installed in the engine vane. A back-up electrical pump engages if mechanical fuel pump is out. Engine is equipped with a 21A 14V generator, 18 Ah battery. All the circuits are fuse protected. The steel leaf main gear legs provide excellent shock absorption, are trouble free and require no maintenance. The levered suspension nose gear with rubber shock absorber has been designed to resist to high impact loading in basic training use. Wheels and hydraulic disc brakes are of standard aircraft type (5.00x5). The brake lever control is located forward between the seats. An hydraulic valve provides the parking brake control.
STANDARD EQUIPMENT:
Flight gauges, Controls, Airspeed indicator, Dual sticks and rudder pedals, Altimeter, Dual throttle, VSI, Longitudinal trim control (electric), Slip coordinator, Flap control (electric), Magnetic compass, Central brake lever, Parking brake valve, Fuel selector valves (lh/rh tanks), Engine gauges, Steerable nose wheel, RPM indicator, Light switches, Hour-meter, CHT, Oil temperature gauge, Engine & accessories, Oil pressure gauge, Electric backup fuel pump, Voltmeter, Electric starter, Fuel pressure gauge, Inox muffler & exhaust ducts, Fuel level sensors/gauges lh/rh, Mechanical fuel pump, Gascolator & quick drain. Other gauges/lights, Integral fuel tanks 2x50 litres, Trim position, Engine Rotax 912 ULS - 73KW (100hp), Flap position, Tonini wooden propeller, Generator light, Oil and water radiator, Strobe light Propeller’s spinner, Cabin upholstery/systems Others: Soundproofing upholstery, Steel nose wheel strut & main wheels, spring leaf, Swinging air vents, Pitot tube and static ports, Roomy luggage compartment, Left door lock, Fuses circuit, Wheel spats, Three-point seat belts Main wheels tyres 5.00x5 (Optional 600 x 6.0) / nose 4.00x6. Door side pockets, Adjustable seats (fabric covered), Aluminium instrument panel.
P2004 Bravo LSA Specifications
|
DIMENSIONS |
m |
ft |
|
Wing Span |
8.40 m |
27.5 ft |
|
Length over-all |
6.61m |
21.7 ft |
|
Height over-all |
2.60 m |
8.5 ft |
|
Width cabin |
1.15 m |
45 " |
|
Wing area |
11.0 m² |
118.4 sq ft |
|
Wing Dihedral |
1.5° |
1.5º |
|
Tailplane span |
2.9 m |
9.5 ft |
|
Wheeltrack |
1.85 m |
6.1 ft |
|
Wheel tyres |
5.00-5 |
5.00-5 |
|
ENGINE & PROPELLER |
|
|
Engine |
Rotax 912ULS |
|
Power max. |
100 Hp @ 5800 rpm |
|
Reduction |
2.4286 : 1 |
|
Propeller |
GT Tonini |
|
Fuel |
Leaded, Unleaded or AvGas |
|
Tanks |
100 Lt (2 x 50) 26.4 US Gal |
|
WEIGHT |
kg |
|
MTO design weight |
600 kg |
|
MTOW |
600 kg (LSA) |
|
Average empty weight |
340 kg |
|
Load ultimate factor |
+6 -3 |
| PERFORMANCES (MTOW - ISA cond.) |
|
| Max Speed s/l |
130 kts |
| Cruising Speed 75% (19 litres/hour) |
115 kts |
| Rate of Climb @ s/l |
1200 ft/min |
| Stalling speed (flap) |
34.5 kts |
| Service Ceiling |
14000 ft |
| Take off run |
140m |
| Landing run |
121m |
| VNE |
138 kts |
