A development of the Spider, the Twister uses an integral fairing and is usually equipped with an Air Creation wing.
The aircraft was supplied as a complete ready-to-fly-aircraft.
Empty weight: 195 kg
Wing span: 10 m
Wing area: 14.8 sq.m
Fuel capacity: 42 lt
Certification: Vz
Engine: Rotax 912, 80 hp
MAUW: 450 kg
Seats: 2
Max speed: 130 kph
Cruise speed: 80-110 kph
Minimum speed: 60 kph
Climb rate: 9 m/s
Fuel consumption: 7 lt/hr
Price (1998): 44 890 DM
A spaceframe trike with cantilever rear undercarriage and is usually equipped with an Air Creation wing.
Spider XP 12
Empty weight: 160 kg
Wing span: 9.20 m
Wing area: 11.80 sq.m
Fuel capacity: 42 lt
Certification: Vz
Engine: Rotax 582, 64 hp
Seats: 2
Max speed: 130 kph
Cruise speed: 80-110 kph
Minimum speed: 60 kph
Climb rate: 8 m/s
Fuel consumption: 9 lt/hr
Price (1998): 31 890 DM
The Sinus is an all composite motorglider. The prop folds into a housing in the engine cver.
Engine: Rotax 503, 52 hp
Wing span: 14.95 m
Wing area: 12.80 sq.m
MAUW: 450 kg
Empty weight: 225 kg
Fuel capacity: 64 lt
Max speed: 186 kph
Cruise speed: 165 kph
Minimum speed: 55 kph
Climb rate: 3.5 m/s
Fuel consumption: 9 lt/hr
Certification: vVz
Seats: 2
Price (1998): 60 950 DM
Slovenia
Produces three models of the Sinus two-seat microlight/ motorglider, for distribution through German agent.
1998:
Lessingstrasse 6
D-97072 Würsburg
Germany
First flew in 1995.
Speed max: 110mph.
Cruise: 105 mph.
Range: 350 sm.
Stall: 33 mph.
ROC: 860 fpm.
Take-off dist: 250 ft.
Landing dist: 350 ft.
Service ceiling: 14,000 ft.
Engine: Rotax 912, 80 hp.
Fuel cap: 13 USG.
Weight empty: 540 lbs.
Gross: 992 lbs.
Length: 20 ft.
Wing span: 32.4 ft.
Wing area: 144 sq.ft.
Seats: 2.
Landing gear: nose wheel.
The Flightstar Spyder is a single seat Ultralight type aircraft. The light weight airframe allows maximum performance on minimum installed powerand the Spyder was designed to accept the Rotax 447 and 503 engines on Flightstar’s dynafocal type engine mount. The front fairing and windshield come as standard equipment on the Spyder. The Spyder features conventional three axis controls with full span ailerons, steerable nose wheel and side mounted control stick. The standard fuel tank has a 5 USG capacity with a 10 USG capacity tank as an option. Equipped with the Flightstar wingfold system, the Spyder is easy to assemble and easy to care for.
Standard equipment includes a 42hp rotax 447 aircooled engine w/cowling, composite front fairing w/tinted lexan windshield, high lift wing with streamlined struts, vibration isolated instrument panel, durable aluminum and stainless custom hardware, rugged chromemoly cage and landing gear, heavy duty stamped dynofocal engine mount, anodized airframe for corrosion protection, and 3 point pilot restraint harness.
Optional equipment includes a 48 hp Rotax 503 aircooled engine with supercowl, full instrument package, four point harness, complete electrical system, in-flight adjustable trim, 3 blade composite propeller, azusa drum brake system, rear floor pan, and brs ballistic parachute system. The Flightstar Spyder can be upgraded to full Formula configuration.
Optional equipment also includes the HKS 700E (680 C.C. 60 HP @ 6200 RPM) with 2.58 TO 1 reduction ratio. Propeller options include the Tennessee prop. co. 2-blade, 66” dia and IVO-prop. 3-blade 62”.
The airfoil is the Flightstar FS-I-2 12% thick.
Engine: Rotax 447FA, 42 hp
Reduction; 2.58-1
Wing span: 30 ft.
Wing area: 144 sq.ft.
Height: 7 ft 10 in.
Length: 16 ft 6 in.
Weight empty: 127 kg / 280 lbs.
Gross weight: 650 lbs.
Structural Limit W/Rotax 503: 750 lb
Fuel cap: 5-10 USG.
VNE: 83 kt / 96 mph / 154 kmh
Cruise 75%: 65 mph.
Range 10 USG: 220 sm.
Stall: 36 mph.
ROC: 660 ft/min / 3 m/s
Take-off roll: 205 ft
Take-off distance (50ft obstacle): 350 ft / 107 m
Landing dist: 180 ft.
Service ceiling: 14,000 ft.
Glide Ratio: 8:1
Sink rate: 400 fpm
Aspect Ratio: 6.25
Roll Rate (45 To 45): 2.8 sec
Seats: 1.
Landing gear: nose wheel.
Cockpit width: 41 in
Engine: Rotax 447, 42 hp
Wing span: 9.14 m
Wing area: 13.40 sq.m
MAUW: 295 kg
Empty weight: 126 kg
Fuel capacity: 38 lt
Max speed: 160 kph
Cruise speed: 105 kph
Minimum speed: 42 kph
Climb rate: 5 m/s
Fuel consumption: 9.5 lt/hr
Certification: VZ
Seats: 1
Engine: Rotax 582, 65 hp
Wing span: 9.8 m
Wing area: 14.63 sq.m
MAUW: 450 kg
Empty weight: 236 kg
Fuel capacity: 40 lt
Max speed: 154 kph
Cruise speed: 120 kph
Minimum speed: 62 kph
Climb rate: 3.3 m/s
Seats: 2
Fuel consumption: 17 lt/hr
Certification: Vz
Kit price (1998): US$15.595
Engine: Rotax 447, 42 hp.
Height: 7.5 ft.
Length: 16.5 ft.
Wing span: 30 ft.
Wing area: 144 sq.ft.
Fuel cap: 10 USG.
Weight empty: 320 lbs.
Gross: 750 lbs.
Speed max: 96 mph.
Cruise: 75 mph.
Range: 180 sm.
Stall: 28 mph.
ROC: 1100 fpm.
Take-off dist: 120 ft.
Landing dist: 180 ft.
Service ceiling: 14,000 ft.
Seats: 1.
Landing gear: nose wheel.
Flightstar designer Tom Peghiny built the first Flightstar in the mid-1980s for the US FAR 103 Ultralight Vehicles category with its maximum 254 lb (115 kg) empty weight requirement. The two-seat Flightstar II soon followed to fill the role of a trainer. The designs quickly became commercial successes and the basic design has been extensively developed over time. By 2007 over 700 single seaters had been sold.
All models are constructed from anodized aluminum tubing assembled with bolts. The fuselage is suspended from a keel tube that also mounts the engine at the front, the tail at the back and the wings. The wings are strut-braced and utilize jury struts. The wings and tail surfaces are covered in pre-sewn Dacron envelopes, which reduces construction time. The wings have full-span ailerons, while the tail features conventional elevators and rudder. The landing gear is a tricycle gear arrangement with bungee suspension on the main wheels. The nosewheel is steerable and mainwheel brakes are an available option. The reported construction time for the single seat models is 100 hours.
The Flightstar II is LSA legal.
The Flightstar-IISC is the Sport Cabin version of the IISL. The IISC includes all that’s needed to enclose the plane for more comfort and all season flying. The cabin parts include the Fastback rear enclosure, composite cabin fairings, door posts, Lexan roof and zippered sport doors. The IISC was developed with the sport pilot in mind. The large wing allows predictable slow flight handling and quiet low throttle cruising. The IISC features the 54HP dual carb, dual ignition, Rotax 503 with the Flightstar 503 Super Cowl. The optional engines include the 64HP Rotax 582 liquid-cooled twostroke and the 60HP HKS 700E four-stroke engine. The Flightstar II was shown at the ’98 Sun ‘n Fun with an HKS 700 engine.
Standard equipment includes high lift wing with streamlined struts, Flightstar wingfold system, vibration isolated instrument panel, 10 USG rotational molded fuel tank w/sump, full dual control system, chromemoly cage and landing gear, heavy duty stamped dynofocal engine mount, anodized airframe for corrosion protection, and point pilot restraint harnesses.
Optional equipment includes, full instrument package, 4 point harnesses, complete electrical system. in-flight adjustable trim, 3 blade composite propeller, azusa drum brake system, and brs ballistic parachute system.
The Flightstar II SC airfoil is the Flightstar FS-II-2 13% thick.
The Flightstar-IISL combines the open air freedom of ultralight type flying and the fun of being side by side with your passenger. With a 120 hour assembly time and the Flightstar wingfold system, the IISL is fitted with full dual controls. The wide stance landing gear for cross wind landings and light wing loading offers easy handling and landings. The airframe is designed for the rigors of flight training and is tested to last. The IISL offers the same standard and optional equipment as the IISC.
The full engine options are the Rotax 503FA (496 C.C. 54HP @ 6800 RPM) with 2.58 TO1 reduction ratio, and the HKS 700E (680 C.C. 60 HP @ 6200 RPM) with 3.47-1 reduction ratio. Propeller options include Tennessee prop. Co. 2-blade, 68” dia, Ivo-prop. 3-blade 68”, and Powerfin F model 70” diameter.
The Flightstar II kit, including engine, cost US$15,395 in 1997.
The Flightstar II-SL kit, including engine, cost US$13,795 in 1997.
The two seat models all have side-by-side seating and have folding wings. The aircraft were also produced under licence in India by Albatross Flying Systems.
In 2009 the Flightstar single and two-seat, high wing, single engined kit aircraft produced by Flightstar Sportplanes of South Woodstock, Connecticut, rights, tooling and parts inventory were sold to Yuneec International of China when Flightstar Sportplanes’ business was wound up.
In July 2009 a new single seat model was exhibited at EAA AirVenture Oshkosh as the Yuneec e-Spyder electric-powered version.
Flightstar II
Engine: Rotax 503, 54 hp.
Height: 7.5 ft.
Length: 19 ft.
Wing span: 32.5 ft.
Wing area: 162 sq.ft.
Fuel cap: 10 USG.
Weight empty: 420 lbs.
Gross: 970 lbs.
Speed max: 96 mph.
Cruise: 65 mph.
Range: 180 sm.
Stall: 36 mph.
ROC: 700 fpm.
Take-off dist: 200 ft.
Landing dist: 300 ft.
Service ceiling: 14,000 ft.
Seats: 2.
Landing gear: nose wheel.
Flightstar II SL
Engine: Rotax 503FA, 48 hp.
HP range: 42-65.
Height: 7.5 ft.
Length: 19 ft.
Wing span: 32.5 ft.
Wing area: 160 sq.ft.
Fuel cap: 10 USG.
Weight empty: 365 lbs.
Gross: 500 lbs.
Speed max: 96 mph.
Cruise: 55 mph.
Range: 165 sm.
Stall: 34 mph.
ROC: 600 fpm.
Take-off dist: 150 ft.
Landing dist: 300 ft.
Service ceiling: 13,000 ft.
Seats: 2.
Landing gear: nose wheel.
Cockpit width: 41 in
Flightstar II SC
Engine: Rotax 503FA, 48 hp.
Wing Span 32 ft
Length 19 ft 7 in
Height 7 ft 10 in
Wing Area 157 Sq. Ft.
Empty Weight 385 Lbs.
Gross Weight 950 Lbs.
Fuel Capacity 10 USG.
Cruise Speed (@ 75%) 65 mph
Stall Speed (Vso) 36 mph
Vne 96 mph.
Climb Rate 600 Fpm.
Aspect Ratio 6.53
Max. Range (W/10 USG) 200 Miles.
Roll Rate (45 To 45) 2.8 Sec.
Takeoff Roll 205 Ft. ‘
Glide Ratio 7 To 1
Sink Rate 450 Fpm
Flightstar II-SC
Engine: HKS 700E, 52 hp
HP range: 52-80
Length: 16 ft
Wing span: 32 ft
Wing area: 160 sq.ft
Fuel capacity: 10 USG
Empty weight: 465 lb
Gross weight: 992 lb
Cruise: 70 mph
Stall: 38 mph
Range: 230 sm
Rate of climb: 700 fpm
Takeoff dist: 200 ft
Landing dist: 300 ft
Seats: 2
Cockpit width: 41 in
Engine: Rotax 582, 65 hp
Wing span: 9.8 m
Wing area: 14.63 sq.m
MAUW: 450 kg
Empty weight: 236 kg
Fuel capacity: 40 lt
Max speed: 154 kph
Cruise speed: 120 kph
Minimum speed: 62 kph
Climb rate: 3.3 m/s
Seats: 2
Fuel consumption: 17 lt/hr
Certification: Vz
Kit price (1998): US$15.595
1995-8: PO Box 760, Ellington, CT 06029, USA.
2009: Flight Design USA, 91 Route 169, PO Box 325, S. Woodstock, CT 06267, USA.
LSA builder
A 1981 hang glider for advanced pilots designed by Warren Bird with help from Bob Martin. The Shark was produced by Flight Sails NZ in New Zealand probably in 1982 and 1983. It had no keel pocket and the double surface was 90%, not sewn on the top surface. The keel was fully enclosed between both surfaces. The king post holds the keel which is not sewn into the top surface. The wing contained 30 battens.
Only a few were made and it was never fully developed. From the first production Shark they were gradually de-tuned from then on to try to improve the handling.
Distributed in England, it cost just over £1000 in 1982.
Performance was good but handling was not. Great in a straight line but really hard to turn. Sometimes it would turn and sometimes it wouldn’t. Turning was improved by upper wing spoilers which also could be used for air brakes.
This was the first Delta to beat the Manta Fledgling when flown by Graeme Bird at the 1981 World Champs in Japan.
Reportedly the Shark made one awesome trike wing in the 80’s. With a British Tri-pacer trike, 330cc motor, Graeme Henderson flew his across Foveaux Strait, New Zealand, in the first crossing by a microlight in 1981.
