P2006T Twin                  click on photos for large versions                     Download PDF file for P2006T            TECNAM P2006 T   SECOND PROTOTYPE OF THE P2006 T HAS FLOWN The second prototype of the TECNAM P2006T - with analogue instruments - made its maiden flight on 9 June 2008. All test flights conducted to date have clearly confirmed the positive characteristics and performances found on the first prototype of this twin-engine light aircraft. Static tests and further flight tests are nearing completion and, based on the latest test program written with ENAC, we expect to receive the Type Certification for this analogue version at the beginning of October 2008. Certification for the Garmin 950 version of the TECNAM Twin will follow shortly thereafter. In the meantime, the production program has commenced and we anticipate the first TECNAM P2006T Twin aircraft to be delivered to clients by the end of October this year. GARMIN G950 FOR THE P2006 T TECNAM has sealed an agreement with Garmin for the supply of the G950 all-glass avionics suite to be installed in its new P2006Ttwin-engine light aircraft. The configuration consists of two multifunction screens and an analogue engine instrument. The first set of G950 screens has already been delivered by Garmin and is about to be installed in the first prototype of the P2006T. This is a unique aircraft in the current aviation market. It is appropriate for personal use and commercial applications as well as for use in flight schools. The low fuel consumption and high reliability, along with the flexibility of fuel options, Autogas and 100LL, make this aircraft extremely attractive from an economic point of view and will provide the opportunity for higher utilisation and profitability for any commercial application.     July 2008   P2006 T Specifications     DESIGN WEIGHT and LOADING lb kg   Maximum Take-Off Weight   2425 lb   1100 kg   Maximum Ramp Weight   2425 lb   1100 kg   Standard Equipped Weight   1411 lb   640 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%   Specs to Flight and Engine Instruments Layout and Other info