P2006T Twin - Tecnam Australia

TECNAM P2006T

This project is based on the revolutionary, new aircraft engine the Rotax 912S, specifically designed to incorporate the latest technologies developed by the automotive industry. The Rotax 912S is FAR 33 certified and is currently the only aircraft engine approved to utilize automotive fuel, giving it a significant edge over standard GA engines.

Some of the benefits include:

Reduced frontal area and better power-to-weight ratio
Lower fuel consumption
Lower propeller rpm resulting in higher efficiency and lower acoustic profile
Stable cylinder head temperatures due to liquid cooling.

To date, this modern aircraft power plant has been used successfully in two-seat aircraft, its relatively low power capacity (rated at 73 kW/100 hp) making it a popular choice in the aviation industry. It has become increasingly evident, therefore, that a potential market exists for a fourseat aircraft powered by two of these Rotax engines, with very little weight disadvantage. The result is the P2006T. This twin- engine formula offers higher safety and lower operating costs than its single engine counterparts. Extensive research for this project has proven that the light twin-engine aircraft will have a lower standard empty weight than comparable single engine four-seat aircraft in the 180 hp or 200 hp class.

The Tecnam P2006T also offers better performance, greater cabin comfort and, due to its unique ability to use automotive fuel, much lower operating costs. For the sake of comparison, the Lycoming 0-360-A1A 180 hp weighs 146kg and has a frontal area of 0.4 m2, while the Rotax 912S (with the same accessories) weighs only 64 kg and has a reduced frontal area of just 0.15 m2.

The Lycoming generates its maximum power of 2700 rpm at the propeller and the Rotax at 2400 rpm. The following table compares the performance of various other four- seat, 200hp aircraft available on the market today. It is evident that: For the first time ever it is possible to compare twin-engine fourseat aircraft to single-engine four-seat aircraft due to their similar weight and power specifications.

The Tecnam P2006T's empty weight is the lowest among its direct competitors, while the payload is higher. This can be attributed to the high structural and systems efficiency and because of the excellent weight-to-power ratio of the Rotax engine.

The wing-mounted engines relieve the aerodynamic load on the wing with a consequently lighter structure. The remarkable propulsive efficiency of the Tecnam P2006T is attributable to the low propeller rotating speed and the low engine drag. These, together with a streamlined fuselage, result in uncommonly efficient aerodynamics.

The Tecnam P2006T clearly boasts the highest ceiling and climb speed among its competitors. From an operating point of view, the following points are worth considering: The option to use automotive fuel as well as AVGAS allows Tecnam P2006T operators to dramatically reduce direct costs, making it possible to fly in regional or remote areas where AVGAS is difficult to find or prohibitively expensive. The dependable twin-engine configuration of the Tecnam P2006T allows it to be flown over long distances and in areas where ground facilities are poor.

P2006 T Specifications

DESIGN WEIGHT and LOADING	lb	kg
Maximum Take-Off Weight	2601 lb	1180 kg
Maximum Ramp Weight	2601 lb	1180 kg
Standard Equipped Weight	1723 lb	780 kg
Standard Useful Load	1014 lb	460 kg
Baggage Allowance	132 lb	60 kg

DIMENSIONS	ft	m
Wing Span	34.8 ft	10.6 m
Wing Area	155.0 sq ft	14.4. sq m
Fuselage Length	28.4 ft	8.66 m
Fuselage Height	9.4 ft	2.85 m
Cabin Width	47.2 ft	1.20 m
Cabin Length	8.2 ft	2.5 m

ENGINE
Manufacturer	ROTAX
Model	912 S
Number of Cylinders	4
Take-off Performance	73.5 kw 98 hp
Max Continuous Performance	69 kw 92 hp
Gearbox Reduction Ratio	2.43:1

PROPELLER
Manufacturer	Hoffman
Type	Variable Pitch propeller feathering
Number of Blades	2
Model	HO-V352

PERFORMANCE
Max speed at sea level	153kts	283 km/h
Cruise speed(75%, 7000ft)	147 kts	272 km/h
Cruise speed (65%, 9000ft)	141 kts	261 km/h
Stall speed flap up	53.5 kts	99 km/h
Stall speed flap down	48 kts	89 km/h
Climb rate, s.l.	1360ft/min	6.9 m/s
Climb rate, s.l. (single engine)	380 ft/min	1.9 m/s
Range to 75%, 30' reserve	610 nm	1130 km
Range to 65%, 30' reserve	710 nm	1315 km
Service ceiling (twin engine)	16,007 ft	4880 m
Service ceiling (single engine)	6690 ft	2040 m
Takeoff roll	738 ft	225 m
Takeoff (50' obstacle)	1378 ft	420 m
Landing roll	591 ft	180 m
Landing (50' obstacle)	1115 ft	340 m

All performance figures in this table are guaranteed within +/- 5%