Side by side two seat single engined mid wing monoplane with conventional three axis control. Wing has swept back leading and trailing edges, and tapering chord; no tail, canard wing. Pitch control by elevator on canard; yaw control by tip rudders; roll control by two thirds span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; main wing profile as Goldwing; but further modified; canard profile GU25; both double surface. Undercarriage has three wheels in tricycle formation; glass ribre suspension on all wheels. Push right go right nosewheel steering connected to yaw control. Brakes on main wheels. Aluminium tube/glass ribre fuselage, totally enclosed. Engine mounted below wing driving pusher propeller.
The Goldwing II is Eurowing’s contender in the two seat three axis market. In 1983 the Goldwing II was about to commence its test flight programme in the hands of its designer, Craig Catto. Craig originally produced the design for the US firm Goldwing Ltd, who exhibited a prototype at the 1982 Oshkosh, but since then Eurowing has taken over development of the machine, the legal position regarding two ¬seaters being much more favourable in Britain than in the US.

Single seat single engined mid wing mono¬plane with conventional three axis control. Wing has swept back leading and trailing edges, and tapering chord; no tail, canard wing. Pitch control by elevator on canard; yaw control by tip rudders; roll control by half-¬span up only ailerons and spoilers; control inputs through stick for pitch/roll and pedals for yaw. Cantilever wing; main wing profile, modified Liebeck; canard profile, GU25; both double surface. Undercarriage has three wheels in tricycle formation; glass fibre suspension on all wheels, brakes on main wheels, fuselage totally enclosed. Push right go right nosewheel steer¬ing connected to yaw control. No brakes. Aluminium tube glass fibre fuselage. Engine mounted above wing driving pusher propeller. Composite construction wing of foam and aluminium covered with glass fibre skin.
While the Goldwing SP may look like nothing more than a Goldwing with an enclosed cockpit, in reality it is rather more than that. Not only is the fuselage differently constructed, using no aluminium except in the bulkhead, but the canard span is increased too. Together, these changes im¬prove both fuel consumption and aesthetics.
There are other refinements too, such as nosewheel suspension and brakes on the mainwheels. Because of these alterations, the Goldwing SP is inherently heavier than its open counterpart, and is therefore not offered with the Robin engine. Standard engine for this machine is the Konig SC430, which in the form used by Eurowing develops 28 hp, 4 hp more than originally, thanks to redesigned pistons. The KFM 107 engine is an option. All Goldwing SPs, plus some later Goldwings, feature Eurowing’s patented vibration absorbing toothed belt reduction drive.
Like the Goldwing from which it is de¬veloped, the SP is a Craig Catto design. However, unlike the open machine, the SP is made only by Eurowing there is no factory built US equivalent.

Engine: Konig SC430, 28hp.
Toothed belt reduc¬tion.
Max static thrust 165 lb, 75 kg.
Length overall 12.0 ft, 3.66 m.
Height overall 7.5ft, 2.29m.
Wing span 30.0ft, 9.14m.
Chord at root 4.5ft, 1.37 m.
Chord at tip 3.0ft, 0.91m.
Canard span 12.0ft, 3.66m.
Canard chord 1.5 ft, 0.46 m.
Fin height 3.0 ft, 0.91 m.
Total wing area 148 sq.ft, 13.7 sq.m.
Main wing area 130 sq.ft, 12.1 sq.m.
Canard area 18 sq.ft, 1.7 sq.m.
Main wing aspect ratio 6.9/1.
Wheel track 5.0 ft, 1.52 m.
Wheelbase 7.3 ft, 2.21 m.
Nosewheel diameter overall 14 inch, 36 cm.
Main wheels diameter overall 16 inch, 41 cm.
Power per unit area 0.19hp/sq.ft, 2.0hp/sq.m
¬Fuel capacity 6.0 US gal, 5.0 Imp gal, 22.7 litre.
Empty weight 290 lb, 132kg.
Max take off weight 540 lb, 245kg.
Payload 250 lb, 113kg.
Max wing loading 3.65 lb/sq.ft, 17.9kg/sq.m.
Max power loading 19.3 lb/hp, 8.8kg/hp.
Load factors; +6.5, 3.0 ultimate.
Max level speed 85 mph, 137 kph.
Never exceed speed 90 mph, 145 kph.
Max cruising speed 70 mph, 113 kph.
Economic cruising speed 50 mph, 80 kph.
Stalling speed 28 mph, 45 kph.
Max climb rate at sea level 700 ft/min, 3.6 m/s.
Min sink rate 180 ft/min at 35 mph, 0.9 m/s at 56 kph.
Best glide ratio with power off 16/1 at 45 mph, 72 kph.
Take off distance 220 ft, 65 m.
Land¬ing distance 160 ft, 50 m.
Range at average cruising speed 220 mile, 354 km.

Single seat single engined mid wing monoplane with conventional three axis control. Wing has swept back leading and trailing edges, and tapering chord; no tail, canard wing. Pitch control by elevator on canard; yaw control by tip rudders; roll control by half-span up only ailerons and spoilers; control inputs through stick for pitch/roll and pedals for yaw. Cantilever wing; main wing profile, modified Liebeck; canard profile, GU25; both double surface. Undercarriage has three wheels in tricycle formation; no suspension on nosewheel and glass fibre suspension on main wheels. Push right go right nosewheel steer-ing connected to yaw control. No brakes. Aluminium tube glass fibre fuselage, partially enclosed. Engine mounted above wing driving pusher propeller.

Eurowing Goldwing Article

Composite construction wing of foam and aluminium covered with glass fibre skin.

Since 1981 Brian Harri¬son’s Eurowing company has been building the Goldwing under license from the US company Goldwing Ltd, but in those years he has made a number of modifications to the Craig Catto design, often with the help of Catto himself, to suit the aircraft better to European conditions. The principal changes concern the undercarriage and the engine. The narrow track undercarriage of the US version has been replaced by a more rugged wide track design with glass fibre suspension on the main wheels. Engines have been more of a problem. By replacing the Cuyuna with a 330 cc Robin, Eurowing was able to create a Goldwing which just satisfied the British microlight definition as regards wing loading. However, it only required the builder to be over generous with the glass fibre to the tune of 3 kg, and the wing loading would exceed the legal limit. The solution to this situation came with the KFM 107 and Konig SC430 engines, both of which are substantially lighter than the Robin.

Another small but significant modification has been to paint the canard with a matt finish. This has the effect of making water droplets form a continuous film which, unlike droplets on a shiny surface, does not spoil the airflow. The aircraft thus becomes much more manageable in the rain, a consideration which in Scotland, where Eurowing is based, is very important.

Manufactured in the US, the Goldwing Ltd Goldwing is a canard mono¬plane with sweptback main wings and movable control surfaces. The canard is used for pitch control only and is fitted with a separate elevator mechanism. The main wingtip rudders may be deployed simultaneously with the rudder pedals. Additional control surfaces include ailerons and spoilers. Composite construction is used throughout. The pilot is enclosed in an aerodynamic nacelle. POWERPLANT: Cuyuna 430D with recoil starter mounted in a pusher position behind the pilot nacelle. The engine has been modified for aircraft use with two extra main bearings, an extended crankshaft, lower compression ratio, separate ignition for each cylinder, special carburetor and tuned exhaust system. Direct drive is standard, turning a two-blade wooden propeller made by Goldwing. Fuel is carried in a plastic container located behind the pilot. A 2:1 reduction unit is optional. LANDING GEAR: Tricycle landing gear make use of moped shock absorbers with coil springs. The nosewheel is steerable, and there are no brakes. Main and nosewheels are 20 inches in diameter. First year built: 1978. Units delivered by June 1981 100+.
The Goldwing UL is the same as standard Goldwing, with lower-power engine and lighter weight to comply with Ultralight Category parameters. POWERPLANT: 25-hp Zenoah.
The Goldwing II is a two place. The Gold Duster is equipped with full spray equipment.
At 290 lbs the standard Goldwing Ltd Goldwing falls into the FAA’s Ex¬perimental category; not Ultralight.

Gallery

Eurowing Goldwing
Engine: Robin EC34PM, 30 hp at 6200 rpm.
Propeller diameter and pitch 54 x 30 inch, 1.37 x 0.76 m.
V belt reduction, ratio 2.7/1.
Max static thrust 190 lb, 86 kg.
Length overall 12.0 ft, 3.66 m.
Height overall 6.0ft, 1.83m.
Wing span 30.0ft, 9.14m.
Chord at root 4.5ft, 1.37 m.
Chord at tip 3.0ft, 0.91m.
Canard span 10.0ft, 3.05m.
Canard chord 1.5 ft, 0.46 m.
Fin height 3.0 ft, 0.91 m.
Total wing area 145 sq.ft, 13.5 sq.m.
Main wing area 130 sq.ft, 12.1 sq.m.
Canard area 15 sq.ft, 1.4 sq.m.
Main wing aspect ratio 6.9/1.
Wheel track 5.0 ft, 1.52 m.
Wheelbase 7.0 ft, 2.13 m.
Nosewheel diameter overall 14 inch, 36 cm.
Main wheels diameter overall 16 inch, 41 cm.
Power per unit area 0.21 hp/sq.ft, 2.2 hp/sq.m.
Fuel capacity 6.0 US gal, 5.0 Imp gal, 22.7 litre.
Empty weight 290 lb, 132kg.
Max take off weight 540 lb, 245kg.
Payload 250 lb, 113kg.
Max wing loading 3.72 lb/sq.ft, 18.1 kg/m .
Max power loading 18.0 lb/hp, 8.2kg/hp.
Load factors; +6.5, 3.0 ultimate.
Max level speed 75 mph, 121 kph.
Never exceed speed 90 mph, 145 kph.
Max cruising speed 65 mph, 105 kph.
Economic cruising speed 45 mph, 72 kph.
Stalling speed 28 mph, 45 kph.
Max climb rate at sea level 750 ft/min, 3.8 m/s.
Min sink rate 200 ft/min at 35 mph, 1.0 m/s at 56 kph.
Best glide ratio with power off 14/1 at 45 mph, 72 kph.
Take off distance 200 ft, 60 m.
Land¬ing distance 180 ft, 55 m.
Range at average cruising speed 220 mile, 354 km.

Goldwing Ltd Goldwing
Engine: 30 hp Cuyuna 430D.
Engine displacement 429cc.
Rated hp 30.
Static thrust 150 lbs.
Wing¬span 30’.
Wing area 128 sq.ft.
Aspect ratio 5.6.
Overall length 12’.
Empty weight 290 lbs.
Wing loading 4.2 Ibs/sq.ft.
L/D power-off glide ratio 16:1.
Cruise speed (85% power) 60 mph.
Stall speed 24 mph.
Approach speed 40 mph.
Flare speed 30 mph.
Liftoff speed 26 mph.
Takeoff roll distance 150 ft.
Rate of climb 600 fpm.
Fuel capacity 2½ gal.
Range at cruise 100 mi.
Max pilot wt: 240 lbs.

Goldwing Ltd Goldwing UL
Wingspan 30’.
Wing area 148 sq.ft.
Length 12’.
Empty weight 250 lbs.
Gross weight 540 lbs.
Cruise speed 63 mph.
Stall speed 26 mph.
Vmax 70 mph.
Climb rate 500+ fpm.
Fuel capacity 3 USG.
Rated hp 25.

Goldwing Ltd Goldwing ST
Wingspan 30’.
Wing area 140 sq.ft.
Empty weight 280 lbs.
Gross weight 540 lbs.
Cruise speed 60 mph.
Stall speed 26 mph.
Vmax 70 mph.
Climb rate 800 fpm.
TO run: 150 ft.
Ldg roll: 200 ft.

Goldwing Ltd Goldwing II
Engine: Rotax 503, 50 hp.
Wingspan 32’.
Wing area 170 sq.ft.
Empty weight 340 lbs.
Gross weight 790 lbs.
Cruise speed 60 mph.
Stall speed 32 mph.
Vmax 75 mph.
Climb rate 500 fpm.
TO run: 200 ft.
Ldg roll: 250 ft.

Goldwing Ltd Gold Duster
Engine: Cuyuna 430, 35 hp.
Wingspan 30’.
Wing area 140 sq.ft.
Empty weight 310 lbs.
Gross weight 640 lbs.
Cruise speed 60 mph.
Stall speed 26 mph.
Vmax 70 mph.
Climb rate 600 fpm.
TO run: 150 ft.
Ldg roll: 200 ft.

A variation of the Maestro, the Spring-Bock features a shorter wing and enclosed cockpit.

Engine: Rotax 582, 65 hp
Wing span: 9.56 m
Wing area: 16 sq.m
MAUW: 450 kg
Empty weight: 250 kg
Fuel capacity: 42 lt
Max speed: 145 kph
Cruise speed: 125 kph
Minimum speed: 53 kph
Climb rate: 5.5 m/s
Seats: 2
Fuel consumption: 11 lt/hr
Price (1998): 119 759 Fht
Kit price (1998): 59 500 Fht

The Maestro 2 FL is known for smoothness of its controls.

Maestro 2 FL
Engine: Rotax 582, 65 hp
Wing span: 10.50 m
Wing area: 17.01 sq.m
MAUW: 450 kg
Empty weight: 200 kg
Fuel capacity: 42 lt
Max speed: 135 kph
Cruise speed: 115 kph
Minimum speed: 45 kph
Climb rate: 5 m/s
Fuel consumption: 13 lt/hr
Seats: 2
Kit price (1998): 49 500 Fht sm

A side by side two seater, the S 5 Velocity is built of riveted sheet dural and powered by a variety of engines from 50 hp to a 100 hp Continental.

Engine: Rotax 912, 80 hp
Wing span: 9.12 m
Wing area: 12.4 sq.m
MAUW: 450 kg
Empty weight: 263 kg
Fuel capacity: 55 lt
Max speed: 200 kph
Cruise speed: 174 kph
Minimum speed: 70 kph
Climb rate: 6 m/s
Fuel consumption: 13 lt/hr
Seats: 2
Price (1998): 66 000 000 L

Europa Aircraft began in the 1990s to build a small aeroplane capable of quiet, comfortable, high speed, low cost touring. The basic concept was to produce an aircraft that be easily transported on its own trailer, operate on car fuel, be rigged and ready for flight in under ten minutes, carry two people in comfort, and take off and land on unprepared grass fields
The original model, the Europa Classic designed by Ivan Shaw, was easily capable of being rigged and de-rigged by a crew of two, road transportable on a purpose-built trailer, simple to construct, and easy to maintain.
The Europa Classic sold in hundreds, and in 1995, the first Europa built by a home constructor was airborne. It was exhibited outside the Department of Trade and Industry who had invested money into the fledgling Europa Aircraft company.

The Monowheel was the first model of the Europa Classic in 1995. With a single retractable wheel in the centre of the fuselage and retractable outriggers on each wing the overall drag of the aircraft is minimised with advantages in speed and economy.
At launch, the Europa XS was available in two versions – the Europa XS Monowheel and the Europa XS Trigear. It had preformed hollow wings, more streamlined cowling, extended tailwheel, enlarged baggage bay and a better balanced spinner. These developments meant extra speed, extra range, extra baggage space and extra comfort. It was also designed to reduce the build time. The Europa XS was named one of the UK’s Millennium Products. The XS Monowheel can be supplied with a number of different engines, although recommended are those from Rotax. The Rotax engines range from 80 HP through to 115 HP.
The Europa XS tricycle undercarriage was developed although the fixed undercarriage imposes a slight drag penalty, fitting the optional speed kit minimises this effect resulting in only a very slight reduction in top speed compared to the Europa XS Monowheel.
The nose gear is a castoring fork type with the same size wheel as the main gear. Steering is by differential braking on the main wheels. The nose wheel suspension is a dual system, the secondary safety cable limiting the total movement of the leg should the primary system fail thus minimising the risk of prop strike.
The XS Trigear can be supplied with a number of different engines, although recommended are those from Rotax. The Rotax engines range from 80 HP through to 115 HP.
The construction of the Europa XS is greatly simplified using high-strength, pre-molded sections with pre-structured, panelized wings incorporating special “constructor’s gel-coat finish” ready for final finish; a feature significantly reducing the complexity and building time associated with many composite airplanes.

Europa LSA (Light Sport Aircraft)
The Europa XS is a two seater side-by-side composite monoplane. It has a range and carrying capacity that makes it ideally suited to touring, and has acquired the reputation of being an extremely enjoyable aircraft to fly.
The Europa LSA doesn’t lose any of the handling characteristics of the Europa XS. Compared to other available LSA planes, it is faster, quicker in the climb, and comparatively economical to run. It is designed to be quickly de-rigged and stored on a trailer in a garage – features that many builders take full advantage of. In order to keep all of the style and functionality of the Europa XS, the Europa LSA’s main difference lies in the wing. The LSA wing will be manufactured from carbon fibre and incorporate a leading edge slot.
The inclusion of the slot and the use of carbon gives a weight reduction of 30% whilst maintaining the same wing area. This design reduces the empty weight to below 600 kgs (1320 lbs) MTOW and slightly increases the payload.
Europa launched the Europa Motor Glider and the glider wings can be interchanged with the wings on the Europa XS Monowheel and Trigear, providing a choice.
Over 500 kits have been sold worldwide with over 100 kits under construction in the U.S. In certain countries the MTOW can be increased to 1450 lb (657.7 kg) and the useful load can be increased accordingly.

On 7 October 2013 the first Europa (G-BWUP) to be fitted with a UL Power UL260iS 107 Hp engine flew for the first time from a Private strip in Wiltshire, UK. With the test pilot going up for a 30 min first flight and no real probs reported apart from the Constant speed prop needed adjusting. The second flight was a little shorter but the Prop was working well no and the take off roll with one up and half fuel and nil wind was only 220 meters.

Europa
Engine: Rotax
Wing span: 7.93 m
Wing area: 9.18 sq.m
MAUW: 591 kg
Empty weight: 331 kg
Fuel capacity: 70 lt
Max speed: 259 kph
Cruise speed: 241 kph
Minimum speed: 81 kph
Climb rate: 4.5 m/s
Seats: 2
Fuel consumption: 16.2 lt/hr
Kit price (1998): £15,245

Europa XS Monowheel
Wing span (tip to tip) 27.133 ft / 8.270 m
Wing span (inc tip influence) 26.917 ft / 8.204 m
Wing area (inc tip influence) 102.11 sq.ft / 9.485 sq.m
Aspect ratio (inc tip influence) 7.096
Overall length 19.17 ft / 5.843 m
Overall height 4.33 ft / 1.320 m
Baggage space 22.50 cu.ft / 0.637 cu.m
Maximum take-off weight 1370-1450 lb / 621.4-657.7 kg
Empty weight / Useful load (Rotax 912 UL) 793 / 577 lb / 360 / 261 kg
Empty weight / Useful load (Rotax 912 ULS) 835 / 535 lb / 379 / 242 kg
Empty weight / Useful load (Rotax 914 UL) 878 / 492 lb / 398 / 223 kg
Maximum baggage capacity 80 lb / 36 kg
Wing loading at max take-off weight 13.42 lb/sq.ft / 65.52 kg/sq.m
Design +3.80g / -1.90g
Ultimate +8.55g / -4.28g
Stall speed flaps extended: 44 kts / 51 mph / 81 kph
Stall speed clean: 52 kts / 60 mph / 96 kph
Cruise speed 8,000 ft 75 % pwr (Rotax 912 ULS) (TAS): 140 kts / 161 mph / 259 kph
Max cruise speed 10,000 ft (Rotax 914 UL Turbo)(TAS): 174 kts / 200 mph / 322 kph
Rate of climb at 1370 lb gross weight (Rotax 912 ULS): 1000 fpm / 5.08 m/s
Rate of climb at 1370 lb gross weight (Rotax 914 UL Turbo): 1300 fpm / 6.60 m/s
Maximum Fuel (Standard Tank): 15 Imp gal / 18 US gal / 68 Litres
Maximum Fuel (Long Range Tank): 23 Imp gal / 28 US gal / 105 Litres
Fuel burn 55% power / 95–100 kts @ SL (Rotax 912 UL): 2.20 Imp Gal/hr / 2.65 Us Gal/hr / 10.02 Litres/hr
Fuel burn 55% power /103-108 kts @ SL (Rotax 912 ULS): 3.14 Imp Gal/hr / 3.77 Us Gal/hr / 14.28 Litres/hr
Standard Tank Range 55% power (912 UL): 576.2 nm / 663.1 sm / 1067.2 km
With Long Range Tank: 930.1 nm / 1070.4 sm / 1722.6 km
Standard Tank Range 55% power (912 ULS): 416.3 nm / 479.1 sm / 771.0 km
With Long Range Tank: 684.0 nm / 787.2 sm / 1266.8 km

Europa XS Trigear
Wing Span (tip to tip): 27.133 ft / 8.270m
Wing Span (inc tip influence): 26.917 ft / 8.204 m
Wing area (inc tip influence): 102.11 sq.ft / 9.485 sq.m
Aspect Ratio: 7.096
Overall length: 19.17 ft / 5.843 m
Overall height: 7.00 ft / 2.133 m
Baggage space: 22.50 cu.ft / 0.637 cu.m
Maximum take-off weight: 1370 lb / 621.4 kg
Empty weight (Rotax 912 UL): 832 lb / 377 kg
Useful load (Rotax 912 UL): 538 lb / 244 kg
Empty weight (Rotax 912 ULS): 853 lb /387 kg
Useful load (Rotax 912 ULS): 517 lb / 234 kg
Empty weight (Rotax 914 UL): 897 lb / 407 kg
Useful load (Rotax 914 UL): 473 lb / 214 kg
Maximum baggage capacity: 80 lb / 36 kg
Wing loading at max take-off weight: 13.42 lb/sq.ft / 65.52 kg/sq.m
Design Load: +3.80g / -1.90g
Ultimate Load: +8.55g / -4.28g
Stall speed flaps extended: 44 kts / 51 mph / 81 kph
Stall speed clean: 52 kts / 60 mph / 96 kph
Cruise 8,000 ft 75 % pwr (Rotax 912 ULS) (TAS): 135 kts / 155 mph / 250 kph
Max cruise speed 10,000 ft (Rotax 914 UL Turbo)(TAS): 166 kts / 191 mph / 307 kph
Take-off ground roll gross weight (Rotax 912 ULS): 590 Feet / 180 Metres
Take-off ground roll at gross weight (Rotax 914 UL Turbo): 500 Feet / 152 Metres
Landing roll: 600 Feet / 183 Metres
Rate of climb at 1370 lb gross weight (Rotax 912 ULS): 1000 fpm / 5.08 m/s
Rate of climb at 1370 lb gross weight (Rotax 914 UL Turbo): 1300 fpm / 6.60 m/s
Maximum Fuel (Standard Tank): 15 Imp gal / 18 US gal / 68 Litres
Fuel burn 55% power 95-100 kts @ SL (Rotax 912 UL): 2.20 Imp Gal/hr / 2.65 Us Gal/hr / 10.02 Litres/hr
Fuel burn 55% power 103 – 108 kts @ SL (Rotax 912 ULS): 3.14 Imp Gal/hr / 3.77 Us Gal/hr / 14.28 Litres/hr
Standard Tank Range 55% power (Rotax 912 UL): 576.2 nm / 663.1 sm / 1067.2 km
Standard Tank Range 55% power (Rotax 912 ULS): 416.3 nm / 479.1 sm / 771.0 km