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
New Zealand
Flight Engineers Ltd was a joint company formed by agricultural operator Barr Brothers and Marine Helicopters Ltd. to maintain own fleets, but also undertook license-assembly of Transavia PL-12 Airtruk agricultural aircraft from 1973. T320 version powered by Continental Tiara engine introduced 1977. Production ended 1980.
An evolution of the original Seasprite with a new twin tail and the installation of two engines.
This single- or two-seat homebuilt glider is distinguished by an aerofoil-shaped fuselage and bat-like sailwing type wings, the tail unit being carried on an aluminium boom. It is an unpowered Stage 1 version of an aircraft which, in fully developed powered form, will be known as the Flightsail VII, the Seasprite being of more simplified construction, and it is being marketed as plans to amateur constructors.
The fuselage is a framework of aluminium tubing, the sides and top of which are covered with polyethylene foil, except for the upper part of the nose section, which has a transparent covering of polyester film and Plexiglas. Alternatively, the structure can be covered with aluminium foil for only a minimal weight increase, and this has a much longer life. The underside of the fuselage has catamaran-type twin floats, built of plastics with a plywood covering, enabling the Seasprite to be operated off water if so desired.
The wings are of triangular planform with aluminium tube leading edges and wire trailing edges, the whole being covered in polyethylene. They can be folded rearwards when not in use but are otherwise braced to the fuselage sides. The wing tips pivot about their leading edges to provide roll control. The tail is built as a single fin/tailplane unit pivoting only in the vertical plane for control in pitch.
The pilot sits in an open cockpit in the centre section, to the right of the aluminium boom carrying the tail unit, and his weight is balanced by a counterweight at the port wing tip if a second pilot or passenger is not carried.
One Seasprite has been fitted with twin tail booms preparatory to adding a small pusher engine between them, this being an interim stage, as the Seasprite II, in the development of the Flightsail VII.
Wingspan 34 ft 0 in
Length 20 ft 0 in
Height 8 ft 0 in
Wing area: 166.0 sqft
Aspect ratio: 6.96
Empty weight: 165 lb
Max weight: 500 lb
Lift off speed 30 mph
Cruise speed 35 mph
Max aero-tow speed: 35 mph
Best glide ratio: 6:1 at 50 mph
Design begun in 1966 and first first flown in October 1970, the Flightsail VII can either be towed behind a 70-hp ski boat or it can have a 90-hp Continental pylon mounted above the fuselage to fly the Flightsail under its own power. The structure is built from bolted aluminum, foam and epoxy. This two-seater amphi¬bian features twin booms and twin tails.
Engine 90-hp Continental
Gross wt. 1600 lb
Empty wt. 1100 lb
Fuel capacity 12 USG
Wingspan 39 ft
Length 29 ft
Top speed 95 mph
Cruise 80 mph
Stall 35 mph.
Climb rate 500 fpm.
Takeoff time 20 sec
Range 200 miles
The company’s four-seat C4 project has slowed down its planned U.S. certification schedule to take advantage of anticipated streamlining of the Part 23 process by FAA, so deliveries could slide into 2015.
Flight Design entered receivership in 2016. Work on the C4 had come to a standstill after the company ran into financial difficulty. Production had also slowed to a trickle as the company workforce was trimmed to 10 people in Germany and around 60 in the Ukraine.
Flight Design completed the sale of all major company assets to the German investment group Lift Holding, allowing for the resumption of work on the C4, a Part 23-certified four-seater with a projected selling price of $250,000.
Created to complement the existing CTsw and CTLS, the MC offers utility and performance in a metal airframe. Constructed from Aluminum, steel and composites, the MC features a steel space frame, all aluminum flying surfaces and a composite cabin and cowling.
The focus with the MC was to provide more utility with a giant cabin and easy-to-maintain modular construction.
Designed with training and commercial fleet uses in mind, the MC visibility, baggage area and easy cabin entry are features.
The metal flying surfaces of the MC are buck riveted and corrosion proofed for maintenance free flying. The steel pilot cage is covered with easy to remove composite shells to allow quick access to the landing gear and controls for annual or 100 hour inspections. The main landing gear is the Flight Design nobounce composite gear introduced on the CTLS.
The cabin of the MC has a width of nearly 52 inches, 2-way adjustable seats and extra-wide cabin doors. The four-point safety harnesses, wing located fuel tanks and the BRS 1350 parachute system are standard.
Standard features include 2 blade composite propeller, conventional three-axis controls, electric pitch trim system, cabin door gas struts, two large capacity baggage compartments, two cockpit storage compartments, electric pre-selector flap system, one piece molded windshield, steerable nose wheel, hydraulic brakes, durable, two-part urethane paint.
2012 Price: US$114,627.
