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hij was blijkbaar niet echt makkelijk, er vliegen er natuurlijk ook geen honderden van rond
open floor voor wat mij betreft
HELLENIC AERONAUTICAL TECHNOLOGIES - HAT HAT LS2
TYPE: Two-seat light aircraft.
PROGRAMME: Design started 1 June 1990; designation LS2 indicates landplane, single engine, two-seat.
Construction of first prototype began 1 February 1993; first flight (SX-LS2) 20 May 1997.
Certification sought to JAR 22.
COSTS: Dr30million (1998).
DESIGN FEATURES: Low-cost, low-power, simple to build kitbuilt. Wings fold for easy storage. Laminar flow aerofoil; NACA 542–415 section at root and 641–412 at tip; leading-edge sweep 2º 42', dihedral 4º, incidence 2º, twist 2º.
FLYING CONTROLS: Conventional and manual. Cable-operated elevator and rudder; pushrods operate ailerons. Sweptback fin with tapered tailplane. Trim tab on elevator, stick force augmentation
provided by spring; horn-balanced rudder and elevators. Four-position flaps.
STRUCTURE: Glass fibre throughout, except nose landing gear and engine mount, both of which are 4130 steel. Single-spar wing.
LANDING GEAR: Fixed tricycle type with free-castoring (±55º) nosewheel. One 4 × 5.00 Azusa wheel on each unit. Mainwheel tyre pressure 3.45 bars (50 lb/sq in); nosewheel tyre pressure 3.10 bars (45 lb/sq in). Azura drum brakes on mainwheels; glass fibre speed fairings on all units.
POWER PLANT: Prototype has one 47.7 kW (64 hp) VW motorcar piston engine driving a fixed-pitch wooden two-blade propeller. Fuel capacity 68 litres (18 US gallons; 15 Imp gallons) in single fuselage tank between cabin and firewall; gravity refuelling point. Oil capacity 2.6 litres (0.7 US gallon; 0.6 Imp gallon). ACCOMMODATION: Pilot and passenger side by side in enclosed cabin, with upward-hinged gullwing door each side. Baggage compartment behind seats.
open floor voor wat mij betreft
HELLENIC AERONAUTICAL TECHNOLOGIES - HAT HAT LS2
TYPE: Two-seat light aircraft.
PROGRAMME: Design started 1 June 1990; designation LS2 indicates landplane, single engine, two-seat.
Construction of first prototype began 1 February 1993; first flight (SX-LS2) 20 May 1997.
Certification sought to JAR 22.
COSTS: Dr30million (1998).
DESIGN FEATURES: Low-cost, low-power, simple to build kitbuilt. Wings fold for easy storage. Laminar flow aerofoil; NACA 542–415 section at root and 641–412 at tip; leading-edge sweep 2º 42', dihedral 4º, incidence 2º, twist 2º.
FLYING CONTROLS: Conventional and manual. Cable-operated elevator and rudder; pushrods operate ailerons. Sweptback fin with tapered tailplane. Trim tab on elevator, stick force augmentation
provided by spring; horn-balanced rudder and elevators. Four-position flaps.
STRUCTURE: Glass fibre throughout, except nose landing gear and engine mount, both of which are 4130 steel. Single-spar wing.
LANDING GEAR: Fixed tricycle type with free-castoring (±55º) nosewheel. One 4 × 5.00 Azusa wheel on each unit. Mainwheel tyre pressure 3.45 bars (50 lb/sq in); nosewheel tyre pressure 3.10 bars (45 lb/sq in). Azura drum brakes on mainwheels; glass fibre speed fairings on all units.
POWER PLANT: Prototype has one 47.7 kW (64 hp) VW motorcar piston engine driving a fixed-pitch wooden two-blade propeller. Fuel capacity 68 litres (18 US gallons; 15 Imp gallons) in single fuselage tank between cabin and firewall; gravity refuelling point. Oil capacity 2.6 litres (0.7 US gallon; 0.6 Imp gallon). ACCOMMODATION: Pilot and passenger side by side in enclosed cabin, with upward-hinged gullwing door each side. Baggage compartment behind seats.
