P96 Golf   click photos for larger versions   Download your P96 PDF file     P96 Golf The ultralight that outclasses general aviation aircraft - given equal power, it is faster, goes further, climbs more rapidly, lands and take off in less space. Operational costs cut in half. All load-bearing structures are light alloy and built to meet international air-navigation standards.Wing structure features a single spar torque box connected to fuselage via three pin attachments to each half wing. Fuselage structure is a steel tubing framework for cabin area high protection and semimonococque light alloy tail to support empennage. Ease of inspection; immediate access for servicing that is efficient and inexpensive at the same time. Particular attention is devoted to fuselage aerodynamics with the adoption of a composite fairing that elegantly and efficiently joins the cabin with the vertical tail. The wide cabin (1.10 m) features two side by side seats that can be adjusted via sliding rail stops, a large baggage compartment is located behind seats. Cabin access is through a canopy that slides towards rear of aircraft overlapping tail fairing consequently allowing unrestricted opening even with aircraft in flight. The wide windshield offers a complete view unhindered by structural elements, while large side windows allow for excellent visibility. The entirely moving tailplane permits superior control and a high degree of stick free stability, moving surfaces feature mass balancing. Landing gear components have been thoroughly tested and feature a clear record of safety and effinciency. The main landing gear consists of special steel springs with 5.00-5 size tyres and hydraulically actuated disc brakes, while nose gear features a steereable wheel with rubber shocks. Specially studied wheel fairings are mounted on each wheel to reduce parasite drag. Landing light is located inside engine cowling in correspondence of nose wheel strut. Engine cowling is made up two parts and allows for quick and complete opening. Fuel tanks are integral part of the wing structure and feature 35 liter capacity per each half wing. Fuel feed is via an engine driven pump and is backed-up for emergency by an electric pump. Instrument panel meets General Aviation standards both in size and quality allowing for installation of a wide variety of flight instrumentation inclusive of IFR, engine controls and com/nav apparatus. Flight controls are traditional type with dual stick, dual rudder pedals and dual throttle knobs on control panel. Longitudinal trim and electrical flap controls with position indicators are also located on control panel. Cabin ventilation is via adjustable air vents fed via buried scoops. ENGINE IS FOUR STROKE, FOUR STROKE OPPOSING CYLINDERS TBO 1500 HR - AUTOMOBILE GRADE FUEL * ROTAX 912 S DA 73,5 kW (100 hp) REDUCTION GEARBOX 1:2,428428   P96 Golf Specifications    DIMENSIONS      Wing Span    27 ft 7 in    Length Over-all    21 ft    Height Over-all    7 ft 6 in    Width Cabin    3 ft 8 in    Wing Area    121.3 sq ft    Transverse Dihedral    5º    Tailplane Span    9 ft 6 in    Wheel Track    5 ft 10 in    Wheel Tyres    5.00 - 5    ENGINE and PROPELLER      Power Max.    73.5 Kw (100 Hp) @ 5800 rpm    Reduction    2.4286 : 1    Propeller    Bipala GT - 172 / 164    Fuel    Premium Unleaded / AvGas    Tanks    70 lt (2 x 35) 18.5 US Gallons    PERFORMANCE      Max Speed s/l    130 kts    241 kmh    Cruising Speed 75% 5250 rpm    116 kts    215 kmh    VNE (never exceed limit)    140 kts    260 kmh    Rate of Climb    1180 ft/min    Stalling Speed with Flap    33 kts    61 kmh    Service Ceiling    14800 ft       Max Range (without reserve) 65%    400 nm    740 km    Take Off to 15 m    590 ft    180 m    Take Off Run    328 ft    100 m    Landing Run    328 ft    100 m    WEIGHT        Designed MTOW    1212 lb    550 kg    Max take-off weight    1212 lb    550 kg    Basic Empty Weight (standard)    619 lb    281 kg    Load Ultimate Factor    +6  -3