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Europa Mono-Wheel
Single-engine two-seat light cabin monoplane, U.K.


Archive Photos [1]


[Europa Mono Wheel (N111EU, s/n 111, 1996) on display (7/16/2000) at the 2000 Torrance Airshow, Zamperini Field, Torrance, California (Photo by John Shupek copyright © 2000 Skytamer Images)]

[Europa Mono-Wheel (Ragle. L. Lincoln) (N27EU, s/n A027) on display (1/7/2006) at the 2006 Cable Airshow, Cable Airport, Upland, California (Photo by John Shupek copyright © 2006 Skytamer Images)]

Specifications [2]


Type:

  • Two-seat light cabin monoplane.

Program:

  • Design started in January 1990.
  • Prototype made first flight 12 September 1992 (G-YURO).
  • PFA certification achieved May 1993.
  • Produced mainly in kit form under PFA hospices, but two assembled by Europa Aviation in 1994.
  • First customer built aircraft (G-OPJK) flown 14 October 1995.
  • Total of 11 customer built aircraft flying by April 1996.

Current Versions:

  • Options of Rotax 912 or 914 Turbo engines.
  • Choice of nosewheel or tricycle landing gear.

Customers:

  • Total of 294 kits sold by December 1995.
  • Customer countries (with sales by spring 1996) include Austria (11), Germany (20), Switzerland (10) and USA (over 50).

1996 Costs:

  • Airframe: £12,475 + VAT
  • Rotax 912 kit: £8,347 + VAT
  • Total: £20,822 + VAT

Design Features:

  • Objectives included low-cost.
  • Economical cruise at IAS up to 120 kn (222 km/h; 138 mph) over 500 nm (926 km; 575 miles).
  • Grass field capability.
  • Ability to rig and de-rig quickly for storage in a trailer similar to a shorter version of glider trailer.
  • Rig/de-rig by six pip-pins, two for tail, two for each wing.
  • Kit building time claimed to be 700 man-hours.
  • Designed to JAR-VLA.
  • Stressed for maximum in-flight normal “g” of 4.3.
  • Proof factor of 2 used in design instead of the more usual 1.5, because of extensive use of composite materials in primary structure.
  • Aerofoil: laminar float Dykins design with 12% thickness/chord ratio and 1.5° washout at tips.
  • Wing dihedral 3°
  • No tail dihedral.

Flying Controls:

  • Conventional ailerons and rudder, all moving tailplane for pitch control with tab geared for balance, under pilot control for trim.
  • Ground adjustable tabs on ailerons and rudder.
  • Two control columns, one centrally mounted at each seat; two pairs of rudder pedals.
  • Central console between seats as throttle, combined flap and landing gear levers.
  • Pitch trim switch next to throttle.
  • Slotted flaps with setting of 0° and 25°, electrically actuated on tricycle landing gear version.

Structure:

  • General constructions of GFRP

Landing Gear:

  • Large single semi-retractable main-wheel and steerable tail-wheel; outriggers at about half-span mounted on nylon stalks which retract with flaps.
  • Main-wheel uses standard 6 in hub has in many light aircraft; and an 8.00-6 Tundra tire.
  • Tricycle landing gear version has spring steel legs, castoring nosewheel, 4.00-5 tires and toe brakes on port side rudder pedals.

Power Plant:

  • One 59.7 kW (80 hp) Rotax 912 flat-four engine, directly driving a three-blade fixed-pitch propeller.
  • Propeller pitch is adjustable on ground to match operating environment (fine pitch for good take-off distances and rate of climb but higher noise and lower cruising speeds; reverse for coarse pitch)
  • Alternative Subaru/NSI EA81 installation in 93 kW (90 hp) and 88 kW (118 hp) form first flown (G-NDOL) 18 November 1995.
  • MWAE rotary 73 kW (98 hp) and BMW 100RS engine installations under development in Spring 1996, the former to be installed in UK prototype (G-YURO) and US-built tricycle gear demonstrator.
  • Normal fuel capacity 73 liters (19.2 US gallons; 16 Imperial gallons).

Accommodation:

  • Enclosed cabin seating two side-by-side under individual upward-opening canopies, hinged on centerline.
  • Baggage compartment at rear of cabin with maximum 36 kg (80 lb) capacity.

Systems:

  • Hydraulics: Main wheel brake.
  • Electrical: 12V 30 Ah battery; alternator fit appropriate to engine.

Avionics:

  • Customer choice.

Dimensions, External:

  • Wing span: 7.92 m (26 ft 0 in)
  • Width, wings removed: 1.17 m (3 ft 10 in)
  • Wing aspect ratio: 7:1
  • Length overall: 5.85 m (19 ft 2½ in)
  • Height overall: 1.32 m (4 ft 4 in)
  • Tailplane span: 2.44 m (8 ft 0 in)
  • Propeller diameter 1.57 m (5 ft 2 in)
  • Propeller ground clearance: 0.36 m (1 ft 2 in)

Dimensions, Internal:

  • Cabin length: 1.42 m (4 ft 8 in)
  • Cabin maximum width: 1.12 m (3 ft 8 in)
  • Cabin maximum height: 0.97 m (3 ft 2 in)

Areas:

  • Wing, gross: 8.83 m² (95.0 ft²)
  • Aileron (total): 0.57 m² (6.10 ft²)
  • Trailing-edge flaps (total): 11.37 m² (14.7 ft²)
  • Fin: 1.03 m² (11.10 ft²)
  • Rudder: 0.48 square meters (5.20 ft²)

Weights and Loadings:

  • Weight empty, equipped: 340 kg (750 lb)
  • Maximum T/O and landing weight: 540 kg (1,300 lb)
  • Payload with full fuel: 197 kg (435 lb)
  • Maximum wing loading: 66.8 kg/m² (13.68 lb/ft²)
  • Maximum power loading: 9.89 kg/kW (16.25 lb/hp)

Performance (at Maximum T/O Weight, ISA):

  • Never-exceed speed (DNE): 160 kts (296 km/h; 184 mph)
  • Maximum level speed: 135 kts (250 km/h; 155 mph)
  • Maximum cruising speed: 130 kts (241 km/h; 150 mph)
  • Econ cruising speed, 75% power at 2,440 m (8,000 ft): 125 kts (232 km/h; 144 mph)
  • Stalling speed, power off, flaps up: 48 kts (89 km/h; 55 mph)
  • Stalling speed, power off, flaps down: 42 kn (78 km/h; 48 mph).
  • Rate of climb at S/L: 244 m/min (800 ft/min)
  • T-O and landing run: 183 m (600 ft)
  • T-O to 15 m (50 ft) 174 m (900 ft)
  • Range, normal fuel, 120 kts (222 km/h; 138 mph): 600 nm (1,111 km; 691 miles)

References


  1. Photos: John Shupek, Copyright © 2000, 2006 Skytamer Images. All Rights Reserved
  2. Paul Jackson, MRAeS (editor). “Europa Aviation Europa”, Jane's All The World's Aircraft 1996-97”, Jane's Information Group Limited, Sentinel House, 163 Brighton Road, Coulsdon, Surrey CR5 2NH, UK, 1996, ISBN 0-7106-1377-6, pages 521-522.

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