Tecnam P2002 Sierra

The P2002 is a twin seat, single engine light aircraft with a cantilever low wing and tricycle landing gear. Type Certificated according to JAR-VLA Regula-tions, as well as Ultralight/Microlight.
The main uses of the P2002 in both the versions are in the recreational and educational field, in the sport, tourist and aerial work flights

The wing presents a tapered, no sweep, plan form, with NACA 63A- wing sections. The slotted flaps extend on 45% of the wing span. The ailerons are Frise type.
The RH and LH wings join together by means of the carry-through beam integrated in the fuselage truss framework.
The wing structure is made up of a conventional single spar torque box. Two bolts connect each wing to the carry-through beam. Two other fittings, in the leading edge area and connected with the secondary spar, serve mainly to carry the torsion loads.
All structural parts are made of aluminium light alloy (2024-T3 and 6061-T6), except for tips and fairings which are in fibreglass.

The fuselage structure consists of a steel truss framework in the cabin area, capable of providing satisfactory protection in case of crash-landing, and a light alloy semi-monocoque cone for the aft section.
The engine mount and nose wheel fittings are directly connected to the steel truss framework through the fireproof bulkhead. The empennage fittings are installed in the last two frames of the tail cone.

The wide cabin features two side by side seats, which can be adjusted via sliding rail stops. A baggage compartment is located behind the seats. Cabin access is through a sliding canopy that opens toward the rear, overlapping the aft cabin fairing. A large panel allows the space for the standard flight instrumentation and for a wide variety of Com-Nav equipments. Flight controls are of conventional dual stick and dual rudder pedals design. Flap and longitudinal trim controls are electrically operated with position indicators located on the instrument panel.

The horizontal trimmable tail plane is all-moving type, which allows a high control authority and a better stick free stability. The vertical tail is conventional fin and rudder type. Both horizontal and vertical tail plane structures are aluminium light alloy (2024-T3 and 6061-T6), except tips which are in fibreglass.


The main landing gear is realized with simple steel spring-leaves, 5.00x5 wheel and tires, disc brakes, renowned for their operational record of effectiveness and safety. The nose gear features a steerable wheel with a rubber doughnut shock absorber.

The engine is the last FAR 33 FAA Type certified version of the 73,5 kW ROTAX 912S2, 4 stroke, 4 cylinders horizontally opposed, driving a certified two blade fixed pitch Hoffmann propeller, or the Ultralight version of the same motor. The fuel is stored in two integral fuel tanks, one in each wing leading edge (total ca-pacity 90 lt.). Fuel supply is via an engine-driven mechanical pump and an emergency electrical fuel pump. The electrical system draws power from a 280 W engine-driven alternator, equipped with an electronic rectifier/regulator and a 12 V, 18 Ah battery.

wing span
wing area
empty weight
useful load
gross weight
fuel capacity
Rotax 912ULS / 912S FAR33
6.61 m
2.43 m
8.60 m
11.5 mq
291 Kg / 330 Kg

544 Kg / 580 Kg
26.4 US gal


takeoff distance, ground roll
rate of climb
max speed
cruise speed
landing distance, ground roll
service ceiling
180 m
1050 ft/min
135 kt
119 kts
125 m
14000 ft

limiting and recommended speeds

design manoeuvring speed (Va)
never exceed speed (Vne)
stall, power off (Vsl)
landing approach speed
156 kts
39 Kts

All specifications are based on manufacturer's calculations