p2006t

8/8/2019 P2006t

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P2006T RetRactable GeaR •Fix GeaR

TWIN ENGINE

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P2006T This project is based on the revolutionary new aircrat engine the Rotax 912S, speciically designed to incorporate the latest technologies developed by the automotive industry. The

Rotax 912S is FAR 33 certiied and is currently the only aircrat engine approved to operate on automotive uel, giving it a s igniicant edge over standard GA engines. Some o the beneitsinclude: Reduced rontal area and better power-to-weight ratio. Lower uel consumption, lower propeller rpm resulting in higher eiciency and a lower noise proile. Stable cylinder head

temperatures due to liquid cooling. To date, this modern aircrat power plant has been used successully in our two-seat aircrat, 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, thereore, that a potential market exists or a our seat aircrat powered by two o these Rotax

engines. The result is the P2006T.This twin-engine ormula oers higher saety and lower operating costs than its single engine counterparts. Extensive research or this project has proven that the light twin-engine

aircrat will have a lower standard empty weight than comparable single engine ourseat aircra t in the 180 hp or 200 hp class.

The Tecnam P2006T also oers better per ormance, greater cabin comort and, due to its unique ability to use automotive uel, much lower operating costs. For the sake o comparison,the Lycoming 0-360-A1A 180 hp weighs 146kg and has a rontal area o 0.4 m2, while the Rotax 912S (with the same accessories) weighs only 64 kg each and has a reduced rontal area

o just 0.15 m2 each.

The Lycoming generates its maximum power o 2700 rpm and the Rotax at 2400 rpm at the propeller. The ollowing table compares the perormance o various other our- seat, 200hpaircrat available on the market today. It is evident that: For the irst time ever it is possible to compare twin-engine our seat aircrat to single-eng ine our-seat aircrat due to their similar

weight and power speciications.

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 eiciencyand because o the excellent power to weight ratio o the Rotax engine.

The wing-mounted engines relieve the aerodynamic load on the wing with a consequently lighter structure. The remarkable e iciency o the Tecnam P2006T is attributable to the low

propeller speed and the low engine drag. These, together with a streamlined uselage, result in unparalleled aerodynamic e iciency.

The Tecnam P2006T clearly boasts the highest ceiling and climb speed among its competitors. From an operating point o view, the ollowing points are worth considering: The option

to use automotive uel as well as AVGAS allows Tecnam P2006T operators to dramatically reduce direct costs, making it possible to ly in areas where AVGAS is diicult to ind or

prohibitively expensive. The dependable twin-engine coniguration o the Tecnam P2006T allows it to be lown over long distances and in areas where ground acilities are poor.

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ConstruCtionTecnam P2006T is a twin-engine our-seat aircrat with ully retractable landing gear. The superior

high-wing coniguration oers stability, superior cabin visibility and easy access or passengers

and luggage. Tecnam has used its extensive experience with aluminum airrames to create inthe Tecnam P2006T a robust yet very light airrame, resulting in an outstanding payload-to-total-

weight ratio.

Wings are o traditional construction, essentially mono spar coniguration. Integral uel tanks are

located outboard o the engines holding 100 liters each or a total o 200 liters. A laminar low

NACA 63A airoil o moderate thickness has been selected or the semitapered wing platorm.

This oers low drag and good high altitude perormance.The wide slotted aluminum laps, electrically operated, allow stall speeds below 48kts. These laps

oer the potential or 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-rodsin 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 o a hard landing.

The Tecnam P2006T’s ability to conorm to such rigid saety requirements has been proven during

dynamic tests carried out by a certiied laboratory, demonstrating orward load actors up to 26g.The horizontal stabilator is an all-moving structure, designed or remarkable longditudinal control

stability with excellent control authority. A wide trim-tab, part o 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

itted with a position indicator. As with most o the aircrat body, the horizontal stabilator

and the vertical in are metallic. The rudder eatures an electrically controlled trim-tab with aposition indicator situated on the instrument panel.

interiors & exteriorsThe generous interior dimensions o the Tecnam P2006T allow maximum space or pilots and

passengers alike. With its two doors, its upholstered seats complete with headrests and verticaladjustment, the cabin provides great lexibility or pilots o varying physical size to optimize

their comort.

Each seat is provided with three-point seat belts with inertia reel. Speciic care has been given

to cabin interiors and acoustic comort.

The ventilation system eatures one vent outlet or each occupant. The heating system uniormlywarms the cabin and a derost maniold prevents the windshield rom ogging up even while taxiing.

Large windows, together with the high wings, provide excellent visibility or a very pleasant light,

as well as or sae ground operations.The cabin has a spacious luggage compartment o 350 liters, which is easily accessible.

Analogic instrument panel

Digital instrument panel

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Landing gear

The retractable landing gear o the Tecnam P2006T is powered by a reversible electric pump. The

main landing gear has trailing link suspension, constructed rom high strength aluminum alloys

and high tensile 15CDV6 steel, and is directly attached to the uselage 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 uselage side pods.

The main gear o the Tecnam P2006T is actuated by an aluminum 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 toebrakes. The nose landing gear eatures a 5.00-5 wheel and telescopic strut with an oleo-pneumatic

shock absorber. It is linked to the cabin’s irst bulkhead through a steel truss.

The gear extension o the Tecnam P2006T is ast or higher saety and is operated by a hydraulic

ram through a drag brace, which in turn locks it into the down position. When extended, the

nosewheel is connected by push-rods to the rudder pedals.

A system o lights and warning horn inorms the pilot o the status o the landing gear’s

extended/retracted position. A back-up system, ensures the gear can be extended even in the

event o a main system ailure.

engine and ProPeLLer

The Tecnam P2006T is equipped with two our-cylinder our-stroke Rotax 912S engines o 100hp

(73kW) each. These are liquid cooled with an integral reduction gearbox (1:2.4286) driving constant

speed propellers with pitch eathering devices.

Engine mounts are made o high strength Chrome-Molybdenum Steel tubes with the engines

mounted on vibration absorbing mounts.

Very easy and convenient access to the engine compartment allows or ast daily inspections.

From an operational point o view, the ollowing beneits o the Tecnam P2006T should be stressed:

The option to use either automotive uel or AVGAS allows operators to dramatically reduce the

direct costs, making it possible to ly to locations where AVGAS is diicult to obtain or prohibitivelyexpensive.

The twin-engine coniguration o the Tecnam P2006T is extremely dependable, enabling the

aircrat to travel long distances over water or rough terrain.

The uel system eatures two uel tanks integral with the wing box or a total capacity o 200 liters.

Each engine is equipped with a mechanically driven uel pump with an electric backup pump.

Tank selection and cross eeding are controlled by two valves positioned overhead the pilot.

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s t a n d a

r d e q u i P m e n t

FLight instruments and indiCators

Magnetic Compass

Airspeed Ind., Kts

Altimeter Dual Mode (In/Mb)

Vertical Speed

Directional Electric

Attitude Horizon Electric

Turn and Bank ind.

O.A.T.

Pitot System Heated

Static System Alternate Static Source

Stall Warning Audible

Landing Gear Position Light, Three (only P2006T·RG)

Landing Gear-In-Transit/Not Locked Light (only P2006T·RG)

Stabilator Trim Position ind.

Rudder Trim Position ind.

engine instruments

Tachometer & Hour Recorder, Two

Maniold, Dual

Fuel Flow, Two

Oil Press, Two

Oil Temp., TwoHead Temp., Two

Fuel Press., Two

Ammeter

Voltmeter

LH & RH Fuel Qty

Annunciator Panel Lighted Push To Test:

LH &RH Low Fuel

LH &RH Low Oil Press

LH &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 ind.

Stabilator with ind.

Landing Gear

Retractable Electro-Hydraulic (only P2006T·RG)

Landing Gear

Selector Switch (only P2006T·RG)Landing Gear

Warning Horn (only P2006T·RG)

Landing Gear

Emergency Extension (only P2006T·RG)

Fuel Control Selector with On/O Crosseed

Overhead Panel Switches:

Starter LH & RH

Fuel Pump LH & RH

Let Engine LH & RH Ignition Switches

Right Engine LH & RH Ignition Switches

eLeCtriCaL system

12 Volt 35 Ah Gill 35A12 Volt Alternators-40 Amp., Two

Rocker Switches int. lighted:

Master Switch

Landing Light (only P2006T·RG)

Taxi Light

Navigation Lights

Strobe Light

Pitot Heat

Map Light

External Power Supply Receptable

Circuit Breaker Panel

Static Discharge Wicks

Landing/Taxi Light

FueL system

Two Integral Fuel Tanks with 200 Litres Total Capacity

Engine Driven Fuel Pumps, Two

Auxiliary Fuel Pumps, Electric, Two

Fuel Tank Quick Drain , Two

2 X Shut O Valves with Cross Feed

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s t a n d

a r d e q u i P m e n t

interior

Pilot and Co-Pilot Seats:

Simulated Leather

Adjustable Fore and At

Vertical Adjustment

Two Rear Passenger Seats

Seat Belts & Shoulder Harness, All Seats

Wall To Wall Carpeting

Fire Extinguisher

Map & Storage Pockets

Radio Call PlateTow Bar

Soundproofng

Luggage Compartments

Overhead Cockpit Speaker

Four Position Intercom System

First Aid Kit

interior Lighting

Avionics Instruments int. lighted

Avionics Radios int. lighted

Engine Instruments int. lighted

Flight Instruments int. lighted

Compass int. lightedMap Light

exterior Lights

Navigation LH/RH Wing Tip and Vertical Tail

Vertical Tail Strobe

Landing/Taxi Light

exterior

Epoxy Corrosion Proofng,

All Structure

LH Front Door Pilot/Co-Pilot,

Lock and Key

RH Rear Door PassengerRear Window

All Windows Tinted

Retractable Landing Gear

Tie Down Rings

Main Wheels, 6.00 X 6

Nose Wheel, 5.00 X 5

Cabin ComFort system

Windshield Deroster

Ventilator Adjustable,

4 Place

Heating System

PowerPLant and ProPeLLer

Engines:

2 Rotax 912S3 100 Hp

4 Cylinders Liquid/Air CooledIntegrated 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 Filt er, Two

Oil Filter, Two

Oil and Water Coolers, Two

Carburettor Heat with Manual Control

standard garmin avioniCs PaCkage

GNS 430W Comm/Nav/Gps MFD

GI-106A Cvor/Loc/Gs/Gps ind.

GTX 328 Transponder

GMA 340 Audio Panel

Altitude Encoder

Avionics Master Switch

Microphone Telex 100T

Avionics Circuit Breaker Panel

Pilot and Co-Pilot Ptt

ELT 406 Artex

ProduCt suPPort/doCumentsManuacturer's Full Two Year Limited Warranty

Pilot's Operation Handbook

Maintenance Manual

Parts Catalog

Aircrat Log Book

Engine Log Book

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design weight & Loading

Maximum Take-O Weight 1180 kg 2599 LB

Maximum Ramp Weight 1180 kg 2599 LB

Standard Equipped Weight 780 kg 1723 LB

Standard Useul Load 400 kg 880 LB

Limit Load Factors +3,8g / -1,78 g

Ultimate Load Factor +5,7g / -2,9g

Baggage Allowance 80 kg 176 LB

engines

Manuacturer ROTAX

Model 912 S3

Number O Cylinder 4

Take O Perormance 98 hp 73,5 kW

Maximum Continuous Perormance 9 2 hp 69 k W

Gearbox Reduction Ratio 2,43:1

ProPeLLer

Manuacturer MT pROpeLLeR

Model MTV-21-A-C-F/CF178-05

Numeber O Blades 2

Type COnSTAnT Speed · FuLL FeATheRing

PerFormanCe

Max. Speed Sea Level (IAS - 0 FT) 148 kTS

Cruise Speed (75% 7000 FT) 140 kTS

Cruise Speed (65% 9000FT) 135 kTS

Stalling Speed Flap Down 47 kTS

Vlo (Landing Gear Extension) 91 kTS

Va (Manouvring Speed) 116 kTS

Vne (Never Exceed Speed) 168 kTS

Rate O Climb 1140 FT/Min

Rate O Climb - Single Engine230 FT/Min

Range To 65%, 30’ Reserve 620 n.M.

Service Ceiling (Twin Engine) 15000 FT

Single-Engine Ceiling 7500 FT

Take O Distance 370 M 1213 FT

Take O Run 274 M 898 FT

Landing Distance 390 M 1279 FT

Landing Run 2 00 M 6 56 FT

wing

SPAN 11,4 M 37,4 FT

AREA 14,8 M² 159,1 SqFT

FuseLage

LENGHT 8,7 M 28,5 FT

HEIGHT 2,85 M 9,35 FT

Cabin

WIDTH 1,25 M 49,2 in

LENGHT(WITH BAGG.) 3,35 M 11 FT

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VIA MAIORISE081043 CAPUA (CE) ITALY

TEL. +39 0823 620134FAX +39 0823 622899

[email protected]

p2006t

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