P2006 TSpecifica�on, Descrip�on & Price

IN RO UCTIONT D

This document is published for the purpose of providing general information for the

evaluation of design, performance and equipment of the Tecnam model P2006 T

Should more information be required, please contact:

This document describes only the Tecnam model , its powerplant andl P2006 T

equipment.

Contents

GENERAL DESCRIPTION 3

CONSTRUCTION 4

INTERIORS & EXTERIORS 4

LANDING GEAR 5

ENGINE AND PROPELLER 5

AIRCRAFT MAIN FEATURES 6

VIEWS 7

P2006T STANDARD EQUIPMENT LIST

CABIN SECTION

9

8

OPTION 1 – IFRG950 13

OPTIONAL 14

PAG.2

GENERAL DESCRIPTION

All information here applies to the Tecnam model equipped with the engi-P2006 Tne Rotax 912 S3.This project is based on the revolutionary new aircraft engine the Rotax 912S, speci-fically designed to incorporate the latest technologies developed by the automotiveindustry. The Rotax 912S is FAR 33 certified and is currently the only aircraft engineapproved to operate on automotive fuel, giving it a significant edge over standard GAengines. Some of the benefits include: Reduced frontal area and better power-to-weight ratio. Lower fuel consumption, lower propeller rpm resulting in higherefficiency and a lower noise profile. Stable cylinder head temperatures due to liquidcooling. To date, this modern aircraft power plant has been used successfully in ourtwo-seat aircraft, its relatively high power to weight (rated at 73 kW/100 hp) makes ita 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 ofthese Rotaxengines. The result is the P2006 T.This twin-engine formula offers higher safety and lower operating costs than its sin-gle engine counterparts. Extensive research for this project has proven that the lighttwin-engine aircraft will have a lower standard empty weight than comparable singleengine four seat aircraft in the 180 hp or 200 hp class.The Tecnam also offers better performance, greater cabin comfort and, dueP2006Tto 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 tosingle-engine four-seat aircraft due to their similar weight and power specifications.Tecnam has the better PAYLOAD/MAXIMUM TAKEOFF WEIGHT ratio (0.36)P2006Tamong its direct competitors. This can be attributed to the high structural andsystems efficiency and because of the excellent power to weight ratio of the Rotaxengine.The wing-mounted engines relieve the aerodynamic load on the wing with aconsequently lighter structure. The remarkable efficiency of the Tecnam isP2006Tattributable to the low propeller speed and the low engine drag. These, together witha streamlined fuselage, result in unparalleled aerodynamic efficiency.The Tecnam clearly boasts the highest ceiling and climb speed among itsP2006Tcompetitors. From an operating point of view, the following points are worthconsidering: The option to use automotive fuel as well as AVGAS allows TecnamP2006T operators to dramatically reduce direct costs, making it possible to fly inareas where AVGAS is difficult to find or prohibitively expensive. The dependabletwin-engine configuration of the Tecnam allows it to be flown over longP2006Tdistances and in areas where ground facilities are poor.

PAG.3

CONSTRUCTION

Tecnam is a twin-engine four-seat aircraft with fully retractable landing gear.P2006TThe superior high-wing configuration offers stability, superior cabin visibility and easyaccess for passengers and luggage. Tecnam has used its extensive experience withaluminum airframes to create in the Tecnam a robust yet very light airframe,P2006Tresulting 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 atotal of 200 liters.A laminar flow NACA 63A airfoil of moderate thickness has been selected for thesemitapered wing platform.This offers low drag and good high altitude performance. The wide slotted aluminumflaps,electrically operated, allow stall speeds below 48kts. These flaps offer the potentialfor very steep approaches and short landings. Fraise ailerons allow aggressive rollrates with minimal adverse yaw. Aileron control is via internal cabin cables linked topush-rods in the wing leading edges.Particular attention was paid to the cabin’s structural design in order to ensure therequired crashworthiness prescribed in recent amendments to the FAA-FAR23 andEASA-CS23 codes.Fuselage structure, seats and seatbelts combine to protect occupants in case of ahard landing.The Tecnam ’s ability to conform to such rigid safety requirements has beenP2006Tproven 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 longdi-tudinal control stability with excellent control authority. A wide trim-tab, part of thestabilator trailing edge, doubles as an anti-servo tab device.The cable-type pitch trim is controlled by a wheel located between the pilots’ seatsand is fitted with a position indicator. As with most of the aircraft body, the horizontalstabilator and the vertical fin are metallic. The rudder features an electrically control-led trim-tab with a position indicator situated on the instrument panel.

PAG.4

The generous interior dimensions of the Tecnam allow maximum space forP2006Tpilots and passengers alike. With its two doors, its upholstered seats complete withheadrests and vertical adjustment, the cabin provides great flexibility for pilots ofvarying physical size to optimize their comfort. Each seat is provided with three-point seat belts with inertia reel. Specific care has been given to cabin interiors andacoustic comfort. The ventilation system features one vent outlet for each occupant.The heating system uniformly warms the cabin and a defrost manifold prevents thewindshield from fogging up even while taxiing.Large windows, together with the high wings, provide excellent visibility for a verypleasant flight, as well as for safe ground operations. The cabin has a spacious lug-gage compartment of 350 liters, which is easily accessible.

INTERIORS & EXTERIORS

PAG.5

LANDING GEAR

ENGINE AND PROPELLER

The retractable landing gear of the Tecnam is powered by a reversible elec-P2006Ttric pump. The main landing gear has trailing link suspension, constructed from highstrength aluminium alloys and high tensile 15CDV6 steel, and is directly attached tothe fuselage main bulkheads. An oleo-pneumatic shock absorber provides excellentground load absorption.The main landing gear retraction is very simple, rotating through 90° into two fuselageside pods. The main gear of the Tecnam is actuated by an aluminium pushP2006Trod, which is connected to the hydraulic ram.The main landing gear is equipped with Cleveland wheels (6.00-6) and rudder pe-dal with toe brakes. The nose landing gear features a 5.00-5 wheel and telescopicstrut with an oleo-pneumatic shock absorber. It is linked to the cabin’s first bulkheadthrough a steel truss.The gear extension of the Tecnam is fast for higher safety and is operated byP2006Ta 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 landinggear’s, extended/retracted position. A back-up system, ensures the gear can be ex-tended even in the event of a main system failure.

The Tecnam is equipped with two four-cylinder four-stroke Rotax 912S engi-P2006Tnes 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 theengines mounted on vibration absorbing mounts.Very easy and convenient access to the engine compartment allows for fast dailyinspections. From an operational point of view, the following benefits of the TecnamP2006T should be stressed: The option to use either automotive fuel or AVGAS al-lows operators to dramatically reduce the direct costs, making it possible to fly tolocations where AVGAS is difficult to obtain or prohibitively expensive.The twin-engine configuration of the Tecnam is extremely dependable, ena-P2006Tbling the aircraft to travel long distances over water or rough terrain. The fuel systemfeatures 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 ba-ckup pump. Tank selection and cross feeding are controlled by two valves positionedoverhead the pilot.

CertificationThe Tecnam is certified to the requirements of CS2 / FAR23P2006 T

ENGINEManufacturer ROTAXModel 912 S3Number of cylinders 4

Maximum Continuous Power 100 hpGearbox Reduction Ratio 2,43:1

PROPELLERManufacturer MT PROPELLERModel MTV-21-A-C-F/CF 178-05Number of Blades 2Type CONSTANT SPEED-FULL FEATHERING

DESIGN WEIGHT & LOADINGMTOW 2712 lbStandard Equip. Empy Weight 1764 lbStandard Equip. Useful Weight 948 lbLimits Loads Factors +3,8 -1,78 GUltimate Loads Factors +5,7 - 2,67 GBaggage Allowance 80kg 176 lb

PERFORMANCE 15ºC SEA LEVEL 1290KGVMAX 155 KTSCruise Speed 75% . 00 ft( pwr at 6 5 ) 140 KTSVNE 172 KTSStall Speed flaps down power off 48 KTSVLO 118 KTSVA 122 KTSRate of Climb 1200 ft/minRate of Climb sinle engine 250 ft/minRange (with extra tank) 742 N.M. - 1020 N.M. (with extra tank)Practical Ceiling 15000 ftTakeoff Run 771 ftTakeoff Distance 1476 ftLanding Run 623 ftLanding Distance 1050 ft

DIMENSIONFuselage Height 9,35 ftFuselage Length 28,5 ftWing Span 37,4 ftWing Area 159,1 sqftCabin Width 4 ftCabin Height seat to cover 3 ftCabin Length with baggage 11ftFuel Tank Capacity 26,4 X2 US GAL

PAG.6

AIRCRAFT MAIN FEATURES

VIEWS

PAG.7

PAG.8

CABIN SECTION

P2006T STANDARD EQUIPMENT LIST

The following list of equipment is included on the standard aircraft Analogue AvionicsPackage and does not reflect optional equipment.

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.• PI OT SYSTEMT , 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

PAG.9

P2006 STANDARD EQUIPMENT LIST

• 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• LEFT ENGINE LH and RH IGNITION SWITCHES• RIGHT ENGINE LH and RH IGNITION SWITCHES

Electrical System• 12 VOLT Ah GILL 35A23• 12 VOLT Ah10 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

PAG.10

Interiors• PILOT, CO-PILOT and 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

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 comfort 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• CARBURETTOR HEAT with Manual Control

P2006 STANDARD EQUIPMENT LIST

• Interior Lighting• Pilot/Copilot Cabin Overhead Lights• Passenger Overhead Light• Interior Lights Dimming Control• Avionics Radios internally lighted• Compass internally lighted• Map Light

PAG.11

P2006 STANDARD EQUIPMENT LIST

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

•

••

GTN 650 COMM/NAV/GPS with GI-106A VOR/LOC/GS/GPS INDICATOR

GNC 255A COM/NAV with Md200 VOR IndicatorDME-KING Kn63 with KD572 indicator

•GTX 328 TRANSPONDER•GMA 340 AUDIO PANEL

• ELT 406 ARTEX• Control Wheel Push-To-Talk Switch-Pilot/Copilot• Mic & Phone Jacks-Pilot/Copilot/Passengers

• Antennas:• Marker Beacon• Transponder• VHF/GPS (2)• NAV• Emergency Locator Transmitter External

• Hand Held Microphone

VIEW OF THE STANDARD PANEL ANALOG IFR

Option also pictured

Export certification requirements may require additional equipment and charges

PRICE

$ ,500.00479ALL PRICES ARE “FLY AWAY” FL WITH

NO ADDITIONAL CHARGEPayment terms:

10% with order, full remaining balance

due on pick-up from Florida.

PAG.12

PAG.13

Non additive, replace standard equipment and avionic• G950 Integrated Flight Deck System• GMA-1347 Digital Audio Panel with Marker Beacon/Intercom• GTX-33 Transponder-Mode S w-TIS• GIA-63W NAV/COM/GPS/WAAS with GS #1• GIA-63W NAV/COM/GPS/WAAS with GS #2• GDU-1040 Primary Flight Display (PFD)• GDU-1040 Multi-Function Display (MFD)

• GRS-77 AHRS• GDC-74A Air Data Computer with OAT Probe• GMU-44 Magnetometer•

•

Backup Airspeed, Attitude, and Altimeter Internally Lighted

DME-KING KN63 integrated control dysplayed on PFD

OPTION 1 – G950

VIEW OF THE STANDARD PANEL G950 IFR

Option also pictured

PRICE

$ , 00.00559 9ALL PRICES ARE “FLY AWAY” FL WITH

NO ADDITIONAL CHARGEPayment terms:

10% with order, full remaining balance

due on pick-up from Florida.

Export certification requirements may require additional equipment and charges

PAG.14

OPTIONAL

$ 33,700.00

$ 6,400.00

$ 24,000.00

$ 9,300.00

$ 15,600.00

$ 6,100.00

$ 10,400.00

$ 15,300.00

$ 6,400.00

$ 15,000.00

$ 11,800.00

$ 18,000.00

$ 11,300.00

$ 1,650.00

$ 4,100.00

$ 2,800.00

$ 4,500.00

$ 4,600.00

$ 6,000.00

$ 68,500.00

$ 78,000.00

ONLY FOR STANDARD VERSION

ONLY FOR THE GLASS VERSION

ONLY FOR THE STANDARD AND GLASS VERSION

(exc. for DG with Heading Bug)

GTN 750 Com/Nav/Gps with Ant. and inst. With GI106A Ind.(Exc.for GTN560)

CODE PRICEDESCRIPTION