After being on hold, development of the Laser recommensed in 1998. Constructed in welded steel and riveted dural tube, the wings are foldable towards the top.

Engine: Rotax 582, 64 hp
Wing span: 6.7 m
Wing area: 9.3 sq.m
MAUW: 385 kg
Empty weight: 181 kg
Fuel capacity: 38 lt
Cruise speed: 161 kph
Minimum speed: 64 kph
Climb rate: 2.5 m/s
Fuel consumption: 15 lt/hr
Seats: 2

Designed by Homer Kolb, the Twinstar Mk.III uses a steel spaceframe cockpit and 14cm diameter dural tube for the tail boom and spars. The ribs are dural tube, riveted and gussetter. The 1997 kit price, including Rotax 582 engine, was US$12,484.

The Mark III Classic, with the aerodynamic expertise of BarnabyWainfan, became the Mark III Xtra while retaining the STOL performance of the Classic. The Mark III Xtra, along with all Kolb aircraft, has folding wings and tails which allows for easy set-up and take-down. The tail folds up and the wings fold back. The process can be done in about 15 minutes. No tools or brackets are required. Everything stores right on the airframe.
The LSA Mark III Xtra comes with an assembly manual, including 3D illustrations, technical drawings and step-by-step procedures.
The New Kolb Aircraft Mark III Xtra 2009 Price: US$18700

Mark III Classic
Engine: Rotax 582, 65 hp.
Hp range: 52-80.
Speed max: 85 mph.
Cruise: 75 mph.
Stall: 33 mph.
ROC: 950 fpm.
Take-off dist: 200 ft.
Landing dist: 200 ft.
Fuel cap: 10 USG.
Weight empty: 450 lbs.
Gross: 1000 lbs.
Height: 6.12 ft.
Length: 22.5 ft.
Wing span: 30 ft.
Wing area: 160 sq.ft.
Seats: 2.
Landing gear: tail wheel.

New Kolb Aircraft Mark III Clasic
Engine: Rotax 582, 65 hp
HP range: 65-80
Cruise: 75 mph
Stall: 41 mph
Rate of climb: 1000 fpm
Takeoff dist: 200 ft
Landing dist: 200 ft
Fuel capacity: 17 USG
Empty weight: 450 lb
Gross weight: 1000 lb
Length: 22.6 ft
Wing span: 30 ft
Wing area: 160 sq.ft
Cockpit width: 41.5 in
Landing gear: tailwheel

New Kolb Aircraft Mark III Xtra
Engine: Rotax 912, 912S
Cruise speed: 90 mph
Stall speed (Vs): 35 mph
Stall speed (Vso): 26 mph
Climb rate: 1,100 fpm
Take-off roll: 200 ft.
Wing span: 30 ft.
Cabin width: 45 in.
Fuel tank: 10 USgal.
Empty weight: 550 lbs
Gross weight: 1,000 lbs

New Kolb Aircraft Mark III Xtra
Engine: Rotax 582, 65 hp
HP range: 65-100
Cruise: 80 mph
Stall: 41 mph
Range: 230 sm
Rate of climb: 1000 fpm
Takeoff dist: 200 ft
Landing dist: 200 ft
Fuel capacity: 10 USG
Empty weight: 500 lb
Gross weight: 1000 lb
Length: 24 ft
Wing span: 30 ft
Wing area: 160 sq.ft
Seats: 2
Landing gear: tailwheel

Mark III
Engine: Rotax 582, 64 hp
Wing span: 9.14 m
Wing area: 14.86 sq.m
MAUW: 400 kg
Empty weight: 179 kg
Fuel capacity: 38 lt
Max speed: 152 kph
Cruise speed: 120 kph
Minimum speed: 55 kph
Climb rate: 4.5 m/s
Certification: PFA
Seats: 2
Fuel consumption: 16 lt/hr
Kit price (1998): £10,811

The microlight Kolb Twinstar is a side-by-side two seater built by the Kolb Co., Phoenixville, Pennsylvania. First flown in 1982, it is a high wing conventional design powered by a pusher Rotax engine.
Designed by Homer Kolb

Twinstar
Engine: Rotax 503
Empty wt. lbs: 292
Max wt. lbs: 725
Wing span: 30ft
Wing area sq.ft.: 160
Wing loading lbs/sq.ft: 4.53
Power loading lbs/hp: 15.42
Max speed mph: 70
Cruise mph: 60
Stall mph: 30
Vne mph: 80
Seats: 2

Twinstar Mk.II
Empty wt. lbs: 330
Max wt. lbs: 750
Wing span: 30ft
Wing area sq.ft.:160
Wing loading lbs/sq.ft: 4.69
Power loading lbs/hp: 15.95
Engine: Rotax 503
Max speed mph: 73
Cruise mph: 65
Stall mph: 30
Vne mph: 80
Seats: 2

Single seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tall. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by full span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile Kolb; double surface. Undercarriage has three wheels in tail dragger formation; suspension on tailwheel and optional spring suspen¬sion on main wheels. Push right go right tailwheel steering connected to yaw control. Brakes on main wheels. Aluminium tube framework, without pod. Engine mounted below wing driving pusher propeller.
This Homer Kolb production was shown for the first time in public at the Sun ‘n’ Fun meeting in March 1982, then next at Oshkosh. Kolb Company announced that the Ultrastar would go on sale in October 1982 but initial production was delayed, the first kits not being delivered until December.
As with the Flyer, the machine is supplied as a kit requiring the purchaser to do all the fabrication, all the materials and necessary components being included in a price of $3595 in 1982. In March 1983 Kolb Company announced that for $1995 you could have a basic Ultrastar kit of just materials and plans and in addition a covering kit for $345, an accessory kit for $1355 and prefabricated wing ribs for $99.

Engine: Rotax 377
Empty wt. lbs: 245
Max wt. lbs: 525
Wing span: 27ft 8in
Wing area sq.ft.: 148
Length: 20’.
Wing loading lbs/sq.ft: 3.55
Power loading lbs/hp: 15.28
Max speed mph: 63
Cruise mph: 55
Stall mph: 26
Vne mph: 75
Seats: 1

Engine Cuyuna ULII 02, 35 hp at 6250 rpm.
Prop¬eller diameter and pitch 50×30 inch, 1.27×0.76m.
V belt reduction, ratio 2.0/1.
Power per unit area 0.24hp/sq.ft, 2.6 hp/sq.m.
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre.
Length overall 20.0 ft, 6.09 m.
Height overall 6.0ft, 1.83m.
Wing span 27.5ft, 8.35m.
Constant chord 5.5 ft, 1.65 m.
Sweepback 0 deg.
Tailplane span 7.8 ft, 2.33 m.
Total wing area 145 sq.ft, 13.5sq.m.
Total aileron area 27.0 sq.ft, 2.51 sq.m.
Wing aspect ratio 5.2/1.
Main wheels diameter overall 14 inch, 36 cm.
Empty weight 235 lb, 107kg.
Max take off weight 470 lb, 213kg.
Payload 235 lb, 107kg.
Max wing loading 3.13 lb/sq.ft, 15.3 kg/sq.m.
Max power loading 13.4 lb/hp, 6.1 kg/hp.
Max level speed 63 mph, 101 kph.
Never exceed speed 70 mph, 113 kph.
Max cruising speed 50 mph, 80 kph.
Economic cruising speed 40 mph, 64 kph.
Stalling speed 25 mph, 40 kph.
Max climb rate at sea level 1000 ft/min, 5.1 m/s.

The Flyer SS fuselage is a resin infusion moulded composite structure consisting of a carbon fiber/epoxy resin laminate with rigid PVC, birch plywood and balsa cores. The all-metal wet wing is a single-strut, single spar construction, covered with aluminum skins. The horizontal empennage features a cantilever stabilizer structure covered with aluminum and with fibreglass tips. The vertical tail, ailerons, flaps and elevator are also aluminum covered. Ailerons, elevator are mass balanced.
The airplane features dual control sticks, dual rudder pedals and a dual differential braking system. The Frise Ailerons are deflected through a bellcrank / pushrod mechanism mounted on ball bearings. The Fowler flaps are operated by a torque tube connected to an electric motor. Ailerons deflect 30° up and 17° down and flaps 40°. The rudder is cable operated while the elevator is operated via a set of 2 push-pull tubes connected by a central bellcrank. The trim tab is controlled by an electric servo motor.

The main Wittman type landing gear legs are made of heat-treated 6150 HR steel rods, faired with fibreglass. The system consists of a right and a left leg, bolted in two landing gear sockets located at each end on an extruded aluminum carry through square tube laminated in place in the bottom of the fuselage. The nose gear leg is made in the same fashion as the main gear but with a different camber. The wheel is mounted in an aluminum fork and suspension is provided by natural leg bending. The nose wheel is free and can rotate 360°.

Cleveland 5 inch wheels and brakes with 5.00*5 tires are used for all three wheels. Brakes are toe operated and the KOLB FLYER SS offers differential braking from pilot and passenger seats.

The flaps are electrically operated by an electric actuator. The flap control is located in the center console. They offer 5 positions from -4° to 40°. One elevator trim, electrically operated, that combines as an anti-servo tab. Fixed trims are used for the rudder and the ailerons.
Two seats, side by side and adjustable, leather seat cushions, dual sticks, dual pedals, center console, top hinged bubble doors, blown acrylic windshield, windows and skylights, baggage compartment accessible via a cargo door on the pilot’s side and over the central bulkhead. Three-point seat belts – shoulder harness for both seats. The two seats are moving forward and aft and are electrically actuated. The control is done via a rocker switch located between the two seats on the center console.

The Rotax 912S develops 100 HP at 5,800 RPM for take-off and 95 HP continuous at 5,500 RPM. Stainless steel exhausts system. 4 cylinder, 4 stroke liquid/air cooled engine with opposed cylinders, dry sump forced lubrication with separate 3l (.8 gal US) oil tank, automatic adjustment by hydraulic valve tappet, 2 CD carburetors, mechanical fuel pump, electronic dual ignition, electric starter, integrated reduction gear 1= 2.43.

Flyer SS
Engine: Rotax 912S, 100 hp
Wing span: 32Ft / 9.75m
Length: 20.6ft6./ 28m
Fin height: 8.25ft / 2.5m
Airfoil: GA30U-418
Wing area: 117Sq.ft. / 10.8 sq.m
Aspect ratio: 8.73
Dihedral: 0.9 deg
Incidence: 2.5 deg
Aileron Span: 57.6In / 1.46m
Aileron Area (each): 3.9Sq.ft / 0.36Sq.m
Flap Span: 103.4in
Flap Area (each): 6.9Sq.ft / 0.64Sq.m
Stabilizer span: 9ft / 2.74m
Stabilizer area: 13.9Sq.ft. / 1.29Sq.m
Elevator area: 9.7Sq.ft. / 0.9Sq.m
Trim tab area: 1Sq.ft. / 0.1Sq.m
Horizontal tail Angle of incidence: -1deg
Fin area: 4Sq.ft. / 0.37Sq.m
Rudder area: 7.1Sq.ft / 0.66Sq.m
Landing gear Track: 7.3Ft / 2.23m
Wheel base: 68.7In / 1.74m
Cabin width: 47 In / 1.2m
Cabin Leg room: 46 In / 1.17m
Maximum cruising speed: 117 ktas
Maximum speed (flaps extended): 74 ktas
Cruising speed: 115 ktas
Never to exceed speed (VNE): 140 ktas
Stall speed (flaps retracted): 45 ktas
Stall speed flaps 10°: 38 ktas
Stall speed flaps 25°: 32 ktas
Stall speed flaps 40°: 30 ktas
Climb rate: 1,234 fpm
Take-off ground roll: 725 ft.
Landing ground roll: 500 ft.
Operating ceiling: 12,000 ft.
Maximum take-off weight: 1,320 lbs / 600 kg
Typical empty weight: 850 lbs / 385 kg
Typical useful load: 470 lbs / 213 kg
Maximum weight per seat: 240 lbs / 109 kg
Maximum baggage weight: 28 lbs / 13 kg
Maximum fuel load: 162 lbs / 73 kg
Minimum single pilot weight: NO single pilot weight minimum

Single seat twin engined high wing mono¬plane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by one-third span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile Kolb; double surface. Undercarriage has two wheels side by side with tailskid; suspension on both wheels. No ground steering. No brakes. Aluminium tube framework, without pod. Engines mounted below wing driving pusher propellers.

Kolb Flyer Article

The actual Flyer, christened with the same name as the Wright brothers’ aircraft, was built and made its first flight in 1970. Homer Kolb’s prototype weighed 130 lb (59 kg) and flew without problems from its first take off, using two McCulloch Mc101 engines of 12.5 hp each. Refined over the passage of the years but only released to the public since 1980, the Kolb Flyer was only sold as plans in 1982 ($65) or kits at various stages of completion: structural materials $1198, finishing kit $1900 (engines, propellers, wheels, coverings, seat etc) or complete materials kit for $2995.

Engine Two Solo 209, 11.5 hp each at 4500 rpm.
Prop¬eller diameter and pitch 36×10 inch, 0.91 x 0.25 m.
No reduction.
Power per unit area 0.14 hp/sq.ft, 1.5 hp/sq.m.
Fuel capacity 1.7 US gal, 1.4 Imp gal, 6.4 litre.
Length overall 20.0 ft, 6.09 m.
Height overall 4.3ft, 1.29m.
Wing span 29.0ft, 8.83m.
Constant chord 5.5 ft, 1.65 m.
Sweepback 0 degs.
Total wing area 160 sq.ft 14.9sq.m.
Wing aspect ratio 5.2/1.
Main wheels diameter overall 14 inch, 35 cm.
Empty weight 185 lb, 84kg.
Max take off weight 392 lb, 178kg.
Payload 207 lb, 94kg.
Max wing loading 2.45 lb/sq.ft, 11.9kg/sq.m.
Max power loading 17.0 lb/hp, 7.7kg/hp.
Load factors; +4.0, 2.5 ultimate.
Max level speed 53 mph, 85 kph.
Max cruising speed 40 mph, 64kph.
Stalling speed 20mph, 32kph.
Max climb rate at sea level 250 ft/min, 1.2 m/s.
Best glide ratio with power off 10.8/1 at 27 mph, 43 kph.
Take off distance 250 ft, 76 m.
Land¬ing distance 75 ft, 23 m.
Service ceiling 6850 ft, 2090 m.
Range at average cruising speed 35 mile, 56 km.

First produced in 1985. The wings and tail fold for transport.
Designed by Homer Kolb
The 1997 kit price including a Rotax 447 was $9039.

The FireStar II is a two place version of the Firestar I.
The 1997 kit price was US$9264 including the engine.
The New Kolb Aircraft LSA Firestar II 2009 Price: 9000 US$

Firestar
Engine: Rotax 377
Empty wt. lbs: 264
Max wt. lbs: 535
Wing span: 27ft 8in
Wing area sq.ft.: 148
Wing loading lbs/sq.ft: 3.6
Power loading lbs/hp: 15.3
Max speed mph: 63
Cruise mph: 55
Stall mph: 26
Vne mph: 75
Seats: 1

Firestar I
Engine: Rotax 447, 41 hp.
Speed max: 70 mph.
Cruise: 60 mph.
Stall: 26 mph.
ROC: 1000 fpm.
Take-off dist: 125 ft.
Landing dist: 125 ft.
Fuel cap: 5 USG.
Weight empty: 275 lbs.
Gross: 550 lbs.
Height: 5.83 ft.
Length: 21.25 ft.
Wing span: 27.5 ft.
Wing area: 143 sq.ft.
Seats: 1.
Landing gear: tail wheel.

New Kolb Firestar I
Engine: Rotax 503, 52 hp.
Wing span: 27.8 ft.
Wing area: 143 sq.ft.
Length: 22.6 ft.
Weight empty: 325 lbs.
Gross: 760 lbs.
Fuel cap: 10 USG.
Cruise: 70 mph.
Stall: 27 mph.
ROC: 850 fpm.
Take-off dist: 150 ft.
Landing dist: 200 ft.
Seats: 2 tandem.
Cockpit width: 23 in
Landing gear: tail wheel.

FireStar II
Engine: Rotax 447, 41 hp.
Height: 5.83 ft.
Length: 21.25 ft.
Wing span: 27.5 ft.
Wing area: 143 sq.ft.
Weight empty: 290 lbs.
Gross: 725 lbs.
Fuel cap: 10 USG.
Speed max: 70 mph.
Cruise: 60 mph.
Stall: 30 mph.
ROC: 650 fpm.
Take-off dist: 225 ft.
Landing dist: 200 ft.
Seats: 2.
Landing gear: tail wheel.

The New Kolb Aircraft Firestar II
Stall: 30 kt / 35 mph / 56 kmh
Cruise: 61 kt / 70 mph / 113 kmh
VNE: 74 kt / 85 mph / 137 kmh
Empty Weight: 147 kg / 325 lbs
MTOW Weight: 329 kg / 725 lbs
Climb Ratio: 800 ft/min / 4 m/s
Take-off distance (50ft obstacle): 250 ft / 76 m
Landing distance (50ft obstacle): 300 ft / 91 m