The H-3 Pegasus is a low-wing, open cockpit monoplane by noted lightweight sportplane designer Bert Howland. It features a lightweight fuselage, based on TIG-welded, square aluminum tubing that weighs only 18 pounds. The internal construction of the wings features a cantilevered design that eliminates struts and cables. Powerplant range is 28 hp to 55 hp. The prototype H-3 first flew in 1988 and won the “The Most Innovative Unltralight” award at Sun ‘N Fun 1989. The design was also designated “Best Commercial Ultralight’ at the 1990 event. The H-3 is not an ultralight vehicle as defined in FAR Part 103. Gross weight of the Pegasus is between 500 and 595 lbs. Pegasus plans cost $250 in 2009 and were available from Classic Aero Enterprises.

Speed max: 60 mph.
Cruise: 55 mph.
Stall: 27 mph.
ROC: 600 fpm.
Take-off dist: 200 ft.
Landing dist: 250 ft.
Service ceiling: 8,000 ft.
Engine: Hirth F263, 31 hp.
HP range: 28-65.
Fuel cap: 5 USG.
Weight empty: 252 lbs.
Gross: 555 lbs.
Height: 4.75 ft.
Length15 ft.
Wing span: 25 ft.
Wing area: 110 sq.ft.
Seats: 1.
Landing gear: tail wheel.

Classic Aero H-3
Engine: Hirth 2703, 55 hp
Wing span: 7.6 m
Wing area: 10 sq.m
MAUW: 226 kg
Empty weight: 114 kg
Fuel capacity: 45 lt
Max speed: 100 kph
Cruise speed: 88 kph
Minimum speed: 43 kph
Climb rate: 3 m/s
Fuel consumption: 12 lt/hr
Seats: 1
Plan price (1998): US$250

Single seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; inverted V tall. Pitch/yaw control by elevon; roll control by ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile; double surface. Undercarriage has three wheels in tricycle formation; suspension on all wheels. Push right go right nosewheel steering connected to yaw control. Brakes on main wheels. Aluminium ¬tube framework, with pod. Engine mounted at wing height driving pusher propeller.
Flown for the first time publically at the Aero 83 salon at Friedrich¬shafen, the prototype Milan from Howatherm UL Systeme made its first flight in March 1983. The prototype is fitted with a KFM 107 twin cylinder engine mounted level with the wing and driving a pusher propeller between the two booms carrying the tail¬plane, which is stiffened by cables.
By 1983 two prototypes had been built and the first production run of 10 machines was being laid down. This machine will be fitted as standard with drum brakes on the main wheels.

Length overall 18.0 ft, 5.50 m.
Height overall 8.5ft, 2.60m.
Wing span 34.4ft, 10.50m.
Constant chord 3.9 ft, 1.20m.
Dihedral 4 deg.
Sweepback 0 deg.
Tailplane span 8.2 ft, 2.50 m.
Total wing area 136 sq.ft, 12.6 sq.m.
Total aileron or spoiler area 25.8 sq.ft, 2.40sq.m.
Tailplane area 32.3 sq.ft, 3.00 sq.m.
Wing aspect ratio 8.8/1.
Wheel track 4.9ft, 1.50m.
Nosewheel dia¬meter overall 10 inch, 26cm.
Main wheels diameter overall 12 inch, 30cm.
Engine: KFM 107, 25 hp at 6300 rpm.
Propeller diameter and pitch 54 x 20 inch, 1.37 x 0.51 m.
V belt reduction, ratio 2.1/1.
Max static thrust 143 lb, 65 kg.
Power per unit area 0.18 hp/sq.ft, 2.0hp/sq.m
Fuel capacity 5.3 US gal, 4.4 Imp gal, 20.0 litre.
Empty weight 214 lb, 97kg.
Max take off weight 442 lb, 200 kg.
Payload 228 lb, 103 kg .
Max wing loading 3.25 lb/sq.ft, 15.9 kg/sq.m.
Max power loading 17.7 lb/hp, 8.0kg/hp.
Load factors; +6.0, 3.0 ultimate.
Max level speed 62 mph, 100 kph.
Never exceed speed 68 mph, 110 kph.
Max cruising speed 56 mph, 90 kph.
Economic cruising speed 37 mph, 60 kph.
Stalling speed 27 mph, 43 kph.
Max climb rate at sea level 400 ft/min, 2.0 m/s.
Best glide ratio with power off 13/1.
Take off distance 100 ft, 30 m.
Landing distance 100 ft, 30 m.

The large square plan wing section provides a very low pitching moment. There is very little need to use the trim in either the SP2000 or 4000. When flaps are set, the increase or decrease in power has very little effect on the pitching which makes the aircraft very easy to fly. Wing cord is 1.5m thickness 20 cm maximum at about 1/3 cord.
With a wingspan of only twenty-eight feet, (28′) the square plan wings have an inbuilt anti-stall feature that keeps the wing tips flying right up to the stall. On landing, the large flaps are effective; the aircraft can slow right down and the effect of crosswinds is much less pronounced. Although they’re comparatively short, the wings on the SP2000 provide excellent stability in the air and on the ground.
The tyres are fifteen inch (15”) Air Tracs with disk brakes, and can handle rough or bush strips with ease. The nose wheel casters.
The LSA ‘Speed’ was available in various configurations, from the lightweight RAA registerable SP-2000S (Nosewheel or tailwheel) to the four seat SP-4000 (Nosewheel only).
Fitted with side control sticks, hydraulic toe operated disk brakes, elevator trim, and multi position electric flaps.

Australian LightWing SPEED SP-2000-S
Engine: Rotax 912-s or Rotax 914
Wingspan: 28 ft
Wing cord: 1.5m
Wing thickness: 20 cm maximum at about 1/3 cord.
Wing Area: 12.62 sqm
Fuel Capacity: 120 lt
Useable fuel: 112 lt
Cruise 115 kts
VNE 145 kts
Stall Speed full flap: 45 kts
Range max: 600 nm
Takeoff distance to 50 ft MTOW: 600m
Seats: 2
Undercarriage: Nosewheel or Tailwheel
Structural testing: +- 5 G
Wheels: 6″ x 6″ tyres 15″
Rear baggage area: 1m x .8m x .8m

The Hughes Group of companies has been producing the Australian LightWing, range of 2 and 4 seat light aircraft for the Australian and world aviation market. With one hundred and seventy-five aircraft produced since 1984.

The development of this two-seat aircraft began back in 1984 by Howard Hughes En¬gineering Pty Ltd with production underway in 1985 from Ballina in NSW. Flaps, brakes and instrumentation are fitted. Both VW and Rotax powered versions were available.
The 582 designation informs us that it is fitted with a Rotax 582, two-stroke engine and the -T tells us that it has a tricycle undercarriage.
The tailwheel version (the GR-912) and the nose-wheel version, the ALW SPORT 2000 are 2 seat high wing monoplane. Construction consists of a riveted alloy wing partly covered with aircraft fabric (part alloy) combined with a welded light weight steel fuselage also part composite, part fabric covered. The welded steel fuselage provides a high degree of protection in the event of an accident while the slow stall speed (35 kts) reduces momentum adding to safety.
Economical Cruise Speed is 75 kts for both aircraft and a maximum cruise speed is 85 kts. Range is a little over 3 hours with 2 wing mounted fuel tanks of 30 l each.

Gallery

Variants:

ALW Sport 2000
Engine: Rotax 912, 80 hp
Wing span: 9.5 m
Wing area: 14.25 sq.m
MAUW: 480 kg
Empty weight: 300 kg
Fuel capacity: 2 x 31 lt
Max speed: 150 kph
Cruise speed: 140 kph
Minimum speed: 64 kph
Climb rate: 4 m/s
Certification: CASA
Seats: 2
Fuel consumption: 14 lt/hr
Price (1998): Aus$78,000
Undercarriage: Nose Wheel

GR 912-s
2 Seat Tail Wheel
Engine: Rotax 912.

GR 582
Engine: Rotax 582.
2 Seat High Wing

GR 582 Amphibious LightWing
Engine: Rotax 582.
2 Seats High Wing

GR 582 Float Plane
Engine: Rotax 582.
2 Seat

Side-by-side two-seat cabin monoplane.

The Hughes Group of companies has been producing the Australian LightWing, range of 2 and 4 seat light aircraft for the Australian and world aviation market. With one hundred and seventy-five aircraft produced since 1984.

Tandem two-seat cabin monoplane