CERTIFIED
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 operate on automotive fuel, giving it a significant edge over standard GA engines. Some of the benefits include: Reduced frontal area and better powerto- weight ratio. Lower fuel consumption, lower propeller rpm resulting in higher efficiency and a lower noise profile. Stable cylinder head temperatures due to liquid cooling. To date, this modern aircraft power plant has been used successfully in our two-seat aircraft, its relatively high power to weight (rated at 73 kW/100 hp) makes it a popular choice in the aviation industry. It has become increasingly evident, therefore, that a potential market exists for a four seat aircraft powered by two of these Rotax engines. The result is the P2006 T. 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 first time ever it is possible to compare twin-engine four seat aircraft to single-engine four-seat aircraft due to their similar weight and power specifications. Tecnam P2006T has the better PAYLOAD/MAXIMUM TAKEOFF WEIGHT ratio (0.36) among its direct competitors. This can be attributed to the high structural and systems efficiency and because of the excellent power to weight ratio of the Rotax engine.
The wing-mounted engines relieve the aerodynamic load on the wing with a consequently lighter structure. The remarkable efficiency of the Tecnam P2006T is attributable to the low propeller speed and the low engine drag. These, together with a streamlined fuselage, result in unparalleled aerodynamic efficiency. The TecnamP2006T 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 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.
Construction
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Tecnam P2006T is a twin-engine four-seat aircraft with fully retractable landing gear. The superior high-wing configuration offers stability, superior cabin visibility and easy access for passengers and luggage. Tecnam has used its extensive experience with aluminum airframes to create in the Tecnam P2006T a robust yet very light airframe, resulting in an outstanding payload-to-total weight ratio.
Wings are of traditional construction, essentially mono spar configuration.
Integral fuel tanks are located outboard of the engines holding 100 liters each for a total of 200 liters.
A laminar flow NACA 63A airfoil of moderate thickness has been selected for the semitapered wing platform.
This offers low drag and good high altitude performance. The wide slotted aluminum flaps, electrically operated, allow stall speeds below 48kts. These flaps offer the potential for very steep approaches and short landings. Fraise ailerons allow aggressive roll rates with minimal adverse yaw. Aileron control is via internal cabin cables linked to push-rods in the wing leading edges.
Particular attention was paid to the cabin???s structural design in order to ensure the required crashworthiness prescribed in recent amendments to the FAA-FAR23 and EASA-CS23 codes.
Fuselage structure, seats and seatbelts combine to protect occupants in case of a hard landing. The Tecnam P2006T???s ability to conform to such rigid safety requirements has been proven during dynamic tests carried out by a certified laboratory, demonstrating for - ward load factors up to 26g.
The horizontal stabilator is an all-moving structure, designed for remarkable longditudinal control stability with excellent control authority. A wide trim-tab, part of the stabilator trailing edge, doubles as an anti-servo tab device. The cable-type pitch trim is controlled by a wheel located between the pilots??? seats and is fitted with a position indicator. As with most of the aircraft body, the horizontal stabilator and the vertical fin are metallic. The rudder features an electrically controlled trim-tab with a position indicator situated on the instrument panel.
 
Interior And Outdoor
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The generous interior dimensions of the TecnamP2006T allow maximum space for pilots and passengers alike. With its two doors, its upholstered seats complete with headrests and vertical adjustment, the cabin provides great flexibility for pilots of varying physical size to optimize their comfort. Each seat is provided with threepoint seat belts with inertia reel. Specific care has been given to cabin interiors and acoustic comfort. The ventilation system features one vent outlet for each occupant. The heating system uniformly warms the cabin and a defrost manifold prevents the windshield from fogging up even while taxiing.
Large windows, together with the high wings, provide excellent visibility for a very pleasant flight, as well as for safe ground operations. The cabin has a spacious luggage compartment of 350 liters, which is easily accessible.
 
Landing Gear
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The retractable landing gear of the Tecnam P2006T is powered by a reversible electric pump. The main landing gear has trailing link suspension, constructed from high strength aluminium alloys and high tensile 15CDV6 steel, and is directly attached to the fuselage main bulkheads. An oleo-pneumatic shock absorber provides excellent ground load absorption.
The main landing gear retraction is very simple, rotating through 90?? into two fuselage side pods. The main gear of the TecnamP2006T is actuated by an aluminium push rod, which is connected to the hydraulic ram.
The main landing gear is equipped with Cleveland wheels (6.00-6) and rudder pedal with toe brakes. The nose landing gear features a 5.00-5 wheel and telescopic strut with an oleo-pneumatic shock absorber. It is linked to the cabin???s first bulkhead through a steel truss.
The gear extension of the Tecnam P2006T is fast for higher safety and is operated by a hydraulic ram through a drag brace, which in turn locks it into the down position. When extended, the nose wheel is connected by push-rods to the rudder pedals. A system of lights and warning horn informs the pilot of the status of the landing gear???s, extended/retracted position. A back-up system, ensures the gear can be extended even in the event of a main system failure.
 
Engine And Propeller
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The Tecnam P2006T is equipped with two four-cylinder four-stroke Rotax 912S engines of 100hp (73kW) each. These are liquid cooled with an integral reduction gearbox (1:2.4286) driving constant speed propellers with pitch feathering devices. Engine mounts are made of high strength Chrome-Molybdenum Steel tubes with the engines mounted on vibration absorbing mounts.
Very easy and convenient access to the engine compartment allows for fast daily inspections. From an operational point of view, the following benefits of the Tecnam P2006T should be stressed: The option to use either automotive fuel or AVGAS allows operators to dramatically reduce the direct costs, making it possible to fly to locations where AVGAS is difficult to obtain or prohibitively expensive.
The twin-engine configuration of the Tecnam P2006T is extremely dependable, enabling the aircraft to travel long distances over water or rough terrain. The fuel system features two fuel tanks integral with the wing box for a total capacity of 200 liters. Each engine is equipped with a mechanically driven fuel pump with an electric backup pump. Tank selection and cross feeding are controlled by two valves positioned overhead the pilot.
 
Standard Equipment
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FLIGHT INSTRUMENTS and INDICATORS
MAGNETIC COMPASS
AIRSPEED IND., Kts
ALTIMETER DUAL MODE (IN/MB)
VERTICAL SPEED
DIRECTIONAL ELECTRIC
ATTITUDE HORIZON ELECTRIC
TURN AND BANK INDICATOR
O.A.T.
PITOT SYSTEM, HEATED
STATIC SYSTEM
ALTERNATE STATIC SOURCE
STALL WARNING AUDIBLE
LANDING GEAR POSITION LIGHT, THREE
LANDING GEAR-in-TRANSIT/NOT LOCKED LIGHT
STABILATOR TRIM POSITION INDICATOR
RUDDER TRIM POSITION INDICATOR
ENGINE INSTRUMENTS
TACHOMETER + HOUR RECORDER, TWO
MANIFOLD, DUAL
OIL PRESS, TWO
OIL TEMP., TWO
HEAD TEMP., TWO
FUEL PRESS., TWO
AMMETER
VOLTMETER
LH + RH FUEL QTY
ANNUNCIATOR PANEL LIGHTED PUSH TO TEST:
- LH LOW FUEL
- RH LOW FUEL
- LH LOW OIL PRESS
- RH LOW OIL PRESS
- LH LOW VOLTAGE
- RH LOW VOLTAGE
- PILOT DOOR OPEN
FLIGHT CONTROLS
HYDRAULIC BRAKES
PARKING BRAKE
ELECTRICAL FLAPS
DUAL FLIGHT CONTROLS
STEERABLE NOSE WHEEL
AILERON AND ELEVATOR LOCK
STABILATOR TRIM (MANUAL)
ENGINE CONTROLS
- THROTTLE, TWO
- PROPELLERS, TWO
- CARBURETTOR HEAT, TWO
- CHOKE, TWO
FLIGHT TRIM CONTROLS
- RUDDER with INDICATOR
- STABILATOR with INDICATOR
LANDING GEAR, RETRACTABLE ELECTRO-HYDRAULIC
LANDING GEAR SELECTOR SWITCH
LANDING GEAR WARNING HORN
LANDING GEAR EMERGENCY EXTENSION
FUEL CONTROL SELECTOR WITH ON/OFF CROSSFEED
OVERHEAD PANEL SWITCHES:
- STARTER LH and RH
- FUEL PUMP LH and RH
- LEFT ENGINE LH and RH IGNITION SWITCHES
- RIGHT ENGINE LH and RH IGNITION SWITCHES
 
ELECTRICAL SYSTEM
12 VOLT 23 Ah GILL 35A
12 VOLT 10 Ah SPARK 500
12 VOLT ALTERNATORS-40 AMP., TWO
ROCKER SWITCHES INTERNALLY LIGHTED
- Master Switch
- Landing Light
- Taxi Light
- Navigation Lights
- Strobe Light
- Pitot Heat
- Map Light
EXTERNAL POWER SUPPLY RECEPTABLE
CIRCUIT BREAKER PANEL
STATIC DISCHARGE WICKS
LANDING/TAXI LIGHT LED
FUEL SYSTEM
TWO INTEGRAL FUEL TANKS WITH 52,83 GAL TOTAL CAPACITY
ENGINE DRIVEN FUEL PUMPS, TWO
AUXILIARY FUEL PUMPS, ELECTRIC, TWO
FUEL TANK QUICK DRAIN, TWO
2 X SHUT OFF VALVES WITH CROSS FEED
INTERIORS
PILOT and CO-PILOT PASSENGER SEATS Simulated leather
- Adjustable Fore and Aft
- Vertical Adjustment
SEAT BELTS & Shoulder Harness, All Seats
WALL TO WALL CARPETING
FIRE EXTINGUISHER
MAP & STORAGE POCKETS
RADIO CALL PLATE
TOW BAR
SOUNDPROOFING
LUGGAGE COMPARTMENTS
OVERHEAD COCKPIT SPEAKER
FOUR POSITION INTERCOM SYSTEM
FIRST AID KIT
 
INTERIOR LIGHTING
Pilot/Copilot Cabin Overhead Lights
Passenger Overhead Light
Interior Lights Dimming Control
Avionics Radios internally lighted
Compass internally lighted
Map Light
EXTERIOR
EPOXY CORROSION PROOFING, All structure
LH FRONT DOOR Pilot/Co-pilot, Lock and Key
RH REAR DOOR Passenger, Lock and Key
REAR WINDOWS
ALL WINDOWS TINTED
RETRACTABLE LANDING GEAR
TIE DOWN RINGS
MAIN WHEELS, 6.00 X 6 - NOSE 5,00 X 5
CABIN CONFORT SYSTEM
WINDSHIELD DEFROSTER
VENTILATOR ADJUSTABLE, 4 place
HEATING SYSTEM
 
POWERPLANT AND PROPELLER
ENGINES - 2 ROTAX 912S3 100 HP, 4 Cylinders liquid/air cooled, integrated reduction gear
DUAL IGNITION SYSTEM
THROTTLE CONTROL LH/RH
TUBULAR STEEL ENGINE MOUNT
PROPELLERS - 2 MT, 2 Blade, Constant Speed
PROPELLER SPINNER, TWO
PROPELLER CONTROL LH/RH
AIR FILTER, TWO
OIL FILTER, TWO
OIL AND WATER COOLERS, TWO
CARBURETOR HEAT with Manual Control
PRODUCT SUPPORT/DOCUMENTS
MANUFACTURER'S FULL TWO YEAR LIMITED WARRANTY
PILOT'S OPERATION HANDBOOK
MAINTENANCE MANUAL
PARTS CATALOG
AIRCRAFT LOG BOOK
ENGINE LOG BOOK
STANDARD AVIONICS PACKAGE
GMA 340 AUDIO PANEL
GTX 328 TRANSPONDER
GTN 650 COMM/NAV/GPS with GI-106A VOR/LOC/GS/GPS INDICATOR
GNC 255A COM/NAV with Md200 VOR Indicator
DME-KING Kn63 with KD572 indicator
ELT 406 ARTEX
- Control Wheel Push-To-Talk Switch-Pilot/Copilot
- Mic & Phone Jacks-Pilot/Copilot/Passengers
- Hand Held Microphone
- Antennas
  - Marker Beacon
  - Transponder
  - VHF/GPS (2)
  - NAV
  - Emergency Locator Transmitter External
 
Photo Gallery Details
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Photo Gallery Flights
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