2020 TECNAM P2012 TRAVELLER

2020

TECNAM

P2012 TRAVELLER

New

IFR

Brand New- Twin Engine Turbocharged Piston 11 seat Short Haul EASA CS23 and FAA FAR23 certified Fixed Gear Aircraft. Known Ice and Air Conditioning Available. Twin engine Lycoming TEO540 375 hp six cylinder turbocharged with Fadec/Electronic Ignition. Garmin 3 Display G1000 NXi with Garmin GFC 700 Autopilot. ADS B In/Out. Pilot and Copilot Door with Rear Entry Stair door with Fold Back Baggage Door. Rear and Nose Baggage compartments. 198 US gallons 100LL. fuel tcapacity. 8,113 lb ramp weight. Max gross takeoff and landing weight 8,069 lb. Aircraft manufactured in Italy.

1

The P2012 Traveller is an all-metal structure, high wing, twin-engine, unpressurised, piston aircraft with fixed tricycle landing gear. The aircraft can accommodate up to 11 occupants. Suitable allowance for luggage and optional equipment is also provided both in a wide nose compartment and in the rearside of the fuselage. Easy and fastseat removal and a large rear door allows for a quick re-configuration with available volumes shown in the picture. The fuselage is made of light aluminium alloy formed frames, beams, stringers and skins coupled by rivets and bolts. Some major items such as beams, wing and tail surface attachments are made from billets. The cantilever wing is also made of a traditional light alloy construction, with twin spars configuration coupled with formed sheet metal ribs and CFRP leading edge. A NACA five digit airfoil has beenselected for the semi-tapered wing platform; this offers low drag with high maximum lift coefficient and small aerodynamic movement. Integral fuel tanks are located in the wing box, behind leading edge andbetween the two spars (less fire risk) for a capacity of 375 litres (99USG) each (total of 750 litres, 198USG). Slotted light aluminium alloy flaps, electrically controlled, allow low stall speeds offering potential for very steep approaches and short landings. The vertical tail consists of a conventional vertical stabilizer and a rudder; the horizontal surface consists of a tail plane and an elevator. Trim-tabs are provided on all control surfaces. The rudder is provided with standard yaw-damper as well (integrated with the standard provided automatic flight control system). The main landing gear is composed of two fixed legs containing the oleo-pneumatic shock absorber. These legs are fitted onto the fuselage via a cantilever beam faired by a small streamlined pod which may be easily removed for maintenance purposes.The nose gear, steerable type, is fixed and consists of an oleo-pneumatic shock absorber leg, attached to the first fuselage bulkhead. It is provided with an anti-shimmy damper. Two wheels of 6.50-10 for main landing gear and 6.00-6 for nose gear are installed. The primary flight controls areconventional and characterized by easy maintenance with control cables coupled by push pull rods, all visible through the immediate removal of the cabin floor nomex sandwich CFRP panels. One of the main advantages of the P2012 Traveller is the option to operate in single-pilot mode in most countries arou

The Lycoming TEO-540-C1A Engine is a direct-drive six-cylinder, horizontally opposed, turbocharged, air-cooled engine. It has electronic fuel injection, electronic ignition, down exhaust. As equipment, the engine has an automotive type starter, one 28V alternator (140A) and a propeller governor pad. The EECS (Electronic Engine Control) is an electronic, microprocessor controlled system that which continuously monitors and adjusts ignition timing, fuel injection timing, and fuel mixture based on operating conditions. The EECS eliminates the need for magnetos and manual fuel/air mixture control lever. The main advantages and features of the Lycoming TEO-540-C1A engine are listed in the table below: as shown, include the P2012’s advantage on fuel consumption, as well as the active engine protection it affords against knock, overboost and temperatures will thereby guarantee a trouble free engine life, compared with any other old generation, turbocharged engines. TEO-540 -C1A TIO-540-J2B Fuel (Min Octane) 100/130, 100LL and UL100 100/130, or 100LL Fuel Scheduling/Mapping Changeable in Software N.A. Time limited takeoff rating Anticipated in Software N.A. Alternator 1 x Alternator – 28 Volt, 140 Amp Max 28 Volt, 70 Amp Engine Protection features Knock Control (independent for each cylinder) CHT, TIT over temp protection – Overspeed protection – Overboost protection N.A. Diagnostics Notification of Shorted/Open Sensor orActuators Out-of Range Failures In-Range Errors from sensor (Cross Checks) N.A. N.A. Pilot Interface All faults are logged in the ECU memory Service Fault History Record since last clearing by an authorized service tool Record of ’’Fault clearing History’’ N.A. Pilot Interface Only 2 Control Levers per engine (PWR, PROP) Single Button Start 3 Control Levers per engine Manual Start EASA Approval TC No EASA.IM.E.119 FAA Approval TC No E00009NY

4 Blade MT prop

Cargo Version Medevac Version Passenger/ Cargo Combi Version Special Mission Version

Yes

The avionic suite is based on the latest generation Garmin G1000 Nxi, composed of two 10-inch PFDs and a single central 12-inch MFD. Remote redundant AHRS and ADC (inertial and air data units) provide the main flight and attitude information, whilst a third back-up is provided by a small, vertical layout MD-302 (Mid-Continent). Communications and navigation are based on dual remote units which provide selectable data on the cockpit screens. An optionally provided Flight Management Optional system keyboard (FMS) allows immediate and comfortable insertion of frequencies and waypoints, while another optionally provided Garmin Flight Stream device allows an immediate and wireless link between flight suite and portable devices such as tablets or smartphones for immediate introduction of flight plans, waypoints, routes, frequencies etc. A remote unit transponder, mode-S, is provided as standard with ADSB-OUT, ADSB-IN, FIS-B to match the incoming future General Aviation requirements for navigation and traffic awareness. Dual standard heated pitot probes enhance the flight safety in all phases, supporting flight especially during single-pilot operations. A single, latest generation Garmin GMA 350C audio panel, manages the ATC and internal communications with several novelties such as 3D audio and separation of pilot/co-pilot communication channels (split function). The standard avionic suite is then completed by the latest generation Garmin-manufactured Automatic Flight Control System, with three axes of operations and provided with a yaw damper (selectable also when A/P is OFF). A/P mode controller, installed in the top of cabin cockpit, allows immediate interaction via dedicated push buttons and rotary wheels. Engine monitoring is fully integrated inside the avionic suite screens and allows a management of power, with significant fully automatic mixture control (absence of related lever and always guarantees the best fuel/air ratio for every single cylinder).

TKS Known Ice Option Air Conditioning Option Combustion Heater Passenger Option Weather Radar Option- Nose

Several different paint schemes

11

Pilot/ Copilot Seats plus 9 passengers

Specifications are believed to be accurate and complete, however it is the responsibility of the purchaser to verify and accept the aircraft upon physical inspection of the aircraft and its records.