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[[File:Tecnam P2008 Low.jpg|thumb|Tecnam P2008]]
[[File:Tecnam P2008 Low.jpg|thumb|Tecnam P2008]]
The '''Tecnam P2008''' is a single-engine, high-wing two-seat aircraft built by [[Tecnam]] in Italy but aimed at the [[US]] market.  It is the first Tecnam aircraft to incorporate major [[Composite material|composite]] components. It was introduced at the [[AERO Friedrichshafen]] 2009 show, with first deliveries in December 2009.<ref name="WDLA11">Bayerl, Robby; Martin Berkemeier; et al: ''World Directory of Leisure Aviation 2011-12'', page 80. WDLA UK, Lancaster UK, 2011. {{ISSN|1368-485X}}</ref><ref name="WDLA15">Tacke, Willi; Marino Boric; et al: ''World Directory of Light Aviation 2015-16'', page 82. Flying Pages Europe SARL, 2015. {{ISSN|1368-485X}}</ref>
The '''Tecnam P2008''' is a single-engine, high-wing two-seat aircraft built by [[Tecnam]] in Italy but aimed at the [[US]] market.  It is the first Tecnam aircraft to incorporate major [[Composite material|composite]] components. It was introduced at the [[AERO Friedrichshafen]] 2009 show, with first deliveries in December 2009.


==Design and development==
==Design and development==
The P2008 is a conventionally laid out [[wing configuration#number and arrangement of mainplanes|strut braced high-wing]] [[monoplane]] aimed specifically at the US market.  Resembling the earlier [[Tecnam P92]] and [[Tecnam P2004|P2004]] in general appearance, the P2008 differs by introducing  a [[carbon fibre]] [[fuselage]] and integrated [[fin]]. The wings and tailplane are all-metal.  It can be adapted to [[Light-sport aircraft|LSA]], [[ultralight]] or [[ELA1]] categories.<ref name=JAWA11/><ref name="WDLA15"/>
The P2008 is a conventionally laid out [[wing configuration#number and arrangement of mainplanes|strut braced high-wing]] [[monoplane]] aimed specifically at the US market.  Resembling the earlier [[Tecnam P92]] and [[Tecnam P2004|P2004]] in general appearance, the P2008 differs by introducing  a [[carbon fibre]] [[fuselage]] and integrated [[fin]]. The wings and tailplane are all-metal.  It can be adapted to [[Light-sport aircraft|LSA]], [[ultralight]] or [[ELA1]] categories.


The wing [[leading edge]] is straight except for some pinching at the root and the wing has constant chord over about the inner 60% of span.  Outboard, the [[trailing edge]] is tapered; the straight [[wing tips]] are slightly upturned.  [[Ailerons#Types of ailerons|Frise ailerons]] on [[piano hinge]]s span the outboard sections and the inner sections are spanned by [[flap (aircraft)#Types|slotted flaps]]. There is a single [[lift strut]] on each side, attached to the lower fuselage. The P2008 has a low set [[stabilator|all-moving]] constant chord tailplane with an [[anti-balance tab]].  The fin is swept and the [[rudder]] moves above the tailplane.<ref name=JAWA11/>
The wing [[leading edge]] is straight except for some pinching at the root and the wing has constant chord over about the inner 60% of span.  Outboard, the [[trailing edge]] is tapered; the straight [[wing tips]] are slightly upturned.  [[Ailerons#Types of ailerons|Frise ailerons]] on [[piano hinge]]s span the outboard sections and the inner sections are spanned by [[flap (aircraft)#Types|slotted flaps]]. There is a single [[lift strut]] on each side, attached to the lower fuselage. The P2008 has a low set [[stabilator|all-moving]] constant chord tailplane with an [[anti-balance tab]].  The fin is swept and the [[rudder]] moves above the tailplane.


The P2008 is powered by a [[Rotax 912ULS]] [[flat four engine|flat four piston engine]] driving a two blade [[propeller (aircraft)|propeller]].  The cabin seats two side-by side with a door each side and baggage space behind.  The cabin and cabin doors are wider than on earlier Tecnam high-wing aircraft.  Its fixed [[tricycle undercarriage]] has spring [[cantilever]] main legs and a [[caster|castoring]], non-steerable nosewheel on a compressed rubber suspension.  Ground steering is achieved by differential braking.  All wheels have [[aircraft fairing|speed fairings]].<ref name=JAWA11/>
The P2008 is powered by a [[Rotax 912ULS]] [[flat four engine|flat four piston engine]] driving a two blade [[propeller (aircraft)|propeller]].  The cabin seats two side-by side with a door each side and baggage space behind.  The cabin and cabin doors are wider than on earlier Tecnam high-wing aircraft.  Its fixed [[tricycle undercarriage]] has spring [[cantilever]] main legs and a [[caster|castoring]], non-steerable nosewheel on a compressed rubber suspension.  Ground steering is achieved by differential braking.  All wheels have [[aircraft fairing|speed fairings]].


The first flight was on 30 September 2008.<ref name=JAWA11/>
The first flight was on 30 September 2008.


==Operational history==
==Operational history==


The first P2008 was delivered to the US in December 2009. By November 2010 six had been registered in Australia, Italy, [[South Korea]] and the United States.<ref name=JAWA11/> {{As of|2013|1}}, five have been registered in New Zealand, including two as Class 2 [[Microlights]].{{update-inline|date=October 2023}}
The first P2008 was delivered to the US in December 2009. By November 2010 six had been registered in Australia, Italy, [[South Korea]] and the United States. {{As of|2013|1}}, five have been registered in New Zealand, including two as Class 2 [[Microlights]].{{update-inline|date=October 2023}}


==Variants==
==Variants==
;P2008
;P2008
:Base model with a {{convert|100|hp|kW|0|abbr=on}} [[Rotax 912ULS]] engine.<ref name="WDLA15"/>
:Base model with a {{convert|100|hp|kW|0|abbr=on}} [[Rotax 912ULS]] engine.
;P2008 TC
;P2008 TC
:Turbocharged {{convert|115|hp|kW|0|abbr=on}} [[Rotax 914]] engine with three blade propeller.<ref>{{cite journal|journal=AOPA Pilot|date=April 2014|page=66|title=Luxury Level LSA|author=Alton K. Marsh}}</ref>
:Turbocharged {{convert|115|hp|kW|0|abbr=on}} [[Rotax 914]] engine with three blade propeller.
;P2008 JC
;P2008 JC
:[[Type certificate|Certified]] version under [[EASA CS-VLA]] rules.<ref name="WDLA15"/>
:[[Type certificate|Certified]] version under [[EASA CS-VLA]] rules.


==Specifications==
==Specifications==
{{Aircraft specs
{{Aircraft specs
|ref=Jane's All the World's Aircraft 2011/12<ref name=JAWA11/><!-- for giving the reference for the data -->
|ref=Jane's All the World's Aircraft 2011/12<!-- for giving the reference for the data -->
|prime units?=met<!-- imp or kts first for US aircraft, and UK aircraft pre-metrification, met(ric) first for all others. You MUST choose a format, or no specifications will show -->
|prime units?=met<!-- imp or kts first for US aircraft, and UK aircraft pre-metrification, met(ric) first for all others. You MUST choose a format, or no specifications will show -->
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{{reflist|refs=
{{reflist|refs=


<ref name=JAWA11>{{cite book |title= Jane's All the World's Aircraft 2011-12|last= Jackson |first=Paul  |year=2011|publisher= IHS Jane's|location=Redhill, UK|isbn=978-0-7106-2955-5|pages=394–6}}</ref>
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<!-- ==Further reading== -->
<!-- ==Further reading== -->

Revision as of 21:49, 22 April 2025

P2008
Role Light aircraft
National origin Italy
Manufacturer Costruzione Aeronautiche Tecnam
First flight 30 September 2008
Introduction 2009
Status Active
Produced 2008-present
Developed into Tecnam P2010
Tecnam P2008

The Tecnam P2008 is a single-engine, high-wing two-seat aircraft built by Tecnam in Italy but aimed at the US market. It is the first Tecnam aircraft to incorporate major composite components. It was introduced at the AERO Friedrichshafen 2009 show, with first deliveries in December 2009.

Design and development

The P2008 is a conventionally laid out strut braced high-wing monoplane aimed specifically at the US market. Resembling the earlier Tecnam P92 and P2004 in general appearance, the P2008 differs by introducing a carbon fibre fuselage and integrated fin. The wings and tailplane are all-metal. It can be adapted to LSA, ultralight or ELA1 categories.

The wing leading edge is straight except for some pinching at the root and the wing has constant chord over about the inner 60% of span. Outboard, the trailing edge is tapered; the straight wing tips are slightly upturned. Frise ailerons on piano hinges span the outboard sections and the inner sections are spanned by slotted flaps. There is a single lift strut on each side, attached to the lower fuselage. The P2008 has a low set all-moving constant chord tailplane with an anti-balance tab. The fin is swept and the rudder moves above the tailplane.

The P2008 is powered by a Rotax 912ULS flat four piston engine driving a two blade propeller. The cabin seats two side-by side with a door each side and baggage space behind. The cabin and cabin doors are wider than on earlier Tecnam high-wing aircraft. Its fixed tricycle undercarriage has spring cantilever main legs and a castoring, non-steerable nosewheel on a compressed rubber suspension. Ground steering is achieved by differential braking. All wheels have speed fairings.

The first flight was on 30 September 2008.

Operational history

The first P2008 was delivered to the US in December 2009. By November 2010 six had been registered in Australia, Italy, South Korea and the United States. As of January 2013, five have been registered in New Zealand, including two as Class 2 Microlights.[needs update]

Variants

P2008
Base model with a 100 hp (75 kW) Rotax 912ULS engine.
P2008 TC
Turbocharged 115 hp (86 kW) Rotax 914 engine with three blade propeller.
P2008 JC
Certified version under EASA CS-VLA rules.

Specifications

Data from Jane's All the World's Aircraft 2011/12

General characteristics

  • Capacity: 2
  • Length: 6.93 m (22 ft 9 in)
  • Wingspan: 8.80 m (28 ft 10 in)
  • Height: 2.46 m (8 ft 1 in)
  • Wing area: 11.50 m2 (123.8 sq ft)
  • Aspect ratio: 6.7
  • Airfoil: NACA 63A
  • Empty weight: 354 kg (780 lb)
  • Max takeoff weight: 600 kg (1,323 lb)
  • Fuel capacity: 110 L (24.2 Imp gal, 29.0 US gal)
  • Powerplant: 1 × Rotax 912S flat four air and water cooled piston, 73.5 kW (98.6 hp)
  • Propellers: 2-bladed Tonini GT fixed pitch

Performance

  • Cruise speed: 215 km/h (134 mph, 116 kn) economical, 65% power at 2,286 m (7,500 ft)
  • Stall speed: 73 km/h (45 mph, 39 kn) flaps down
  • Range: 1,277 km (793 mi, 690 nmi)
  • Service ceiling: 4,265 m (13,993 ft)
  • g limits: +4/-2
  • Rate of climb: 5.85 m/s (1,152 ft/min) at sea level

Avionics

References


External links

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