The Q-2 has been modified to take the Teledyne Continental 0-200 engine of 100 hp, two seat, side by side.
Gross Wt. 1100 lb
Empty Wt. 505 lb
Fuel capacity 20 USG
Wingspan 16’8”
Length 19’l0”
Engine Continental 0.200A, 100 hp
Top speed 220 mph
Cruise: 140 kt
Fuel burn @ cruise: 23 lt/hr
Stall 64 mph
Climb rate 1600 fpm
Service ceiling 21,000 ft
Takeoff run 610 ft
Landing roll 950 ft
The Q2 is a two-place, side-by-side version of the composite-construction Quickie-canard-platform aircraft. It is designed for high performance on low horsepower with high efficiency. The proven Revmaster 2100-D is used. Cruise for the Q2 is 170 mph at 8000 feet burning 3.8 gph for 44 mpg. According to its designers, the Q2’s equivalent flat plate area is now 1.18, cleaner than the Glasair or the original VW-powered VariEze prototype. Like the Quickie, the Q2 is built from basic foam and epoxy/fiberglass composite construction and is similar in configuration. The fuselage is pre-molded in four pieces to facilitate construction.
Designed in 1980. Price 1982: $9,595 (Excludes paint and battery). Won 1982 Cafe 250 race.
Units delivered to June 1981: 225.
Engine: Revmaster 2100, 64 hp
MTOW: 1,000 lb
Empty wt: 475 lb
Wingspan 16’8”
Wing area: 67 sq.ft
Top speed: 180 mph
Cruise speed: 160 mph
ROC: 800 fpm
Takeoff run 500 ft
Seats: 2
Range with res: 650 miles
In 1974, Tom Jewett and Gene Sheehan began designing an airplane that would provide “more flying enjoyment for less money” than other homebuilt aircraft designs. Burt Rutan assisted Jewett and Sheehan in the design work and the first Quickie was finished, tested in flight, and ready for a public introduction by April 1978.
Developed around a heavy but durable modified industrial en¬gine, the prototype was designed and built in less than three months and returns incredible performance figures for its minimal power: 201 kph (125 mph) cruise speed and 145 km (90 miles) on a single gallon of fuel. It has no tail surface, just a pair of sharply staggered wings with wheels set into the tips of the lower wing.
The original aircraft was awarded “Outstanding New Design” by the Experimental Aircraft Association in 1978. The aircraft is technically a canard design, however the nearly equal size of each wing makes it appear to be a biplane.
This revolutionary design incorporated state of the art materials, and proved to be highly efficient and forgiving. Sold in kit form for production by amateurs in 400 hours, the full kit (in 1977) cost only $6,395 (Cdn), about one-third the cost of a basic 2-seat factory production aircraft at the time. The Onan engine is a modified two cylinder, air-cooled industrial engine.
Basic to the Quickie’s economy is the 16-hp Onan flat, horizontally opposed, four-stroke engine commonly used to power lawn mowers and RV generators, modified to produce 22 hp. The wide canard of the Quickie carries the main landing wheels at each end, and a tiny tailwheel at the rear end is covered with a small rudder. Complete kits include engine, prefabricated cowling, canopy, all machined parts, all welded parts and some of the tools in an effort to limit building time for the inexperienced builder. Construction is from composite materials, and the cockpit is suitable for one pilot up to 210 pounds.
Price 1982: $4,995 (excludes paint and battery). Units delivered to June 1981: 550.
Engine Onan two-cylinder, 22-hp
MTOW: 820 lb
Empty Wt: 240 lb (109 kg)
Fuel cap: 8 USG
Wingspan 16’8”
Length 17 ft 4 in (5.3 m)
Wing area: 55 sq.ft
Height 4 ft 6 in (1.4 m)
Top speed: 140mph
Cruise: 130 mph (210 km/h)
Stall: 52mph
Climb rate 550 fpm
Ceiling: 14,800 ft
Takeoff run: 660 ft
Landing roll: 838 ft
Range 525 miles
Seats: 1
This monoplane was designed and built by William Lafayette Quick and apparently made a single flight in April, 1908 in Hazel Green, Alabama, making it the first aircraft to have flown in that state. The builders’ son, William Massey Quick, was the pilot. When the craft actually took to the air, the pilot leaned forward in order to admire the view below him. That pitched the nose down, and the craft crashed. It ended up being stored in a barn for 54 years. It’s now been restored and is on display at the U.S. Space & Rocket Center in Huntsville.
The company was officially launched in May 2001, and by that summer employed a staff of 14. On October 16, 2002, the 27,000 square foot new Quest facility was officially dedicated and the team moved the production work to its current home at the Sandpoint (ID) Municipal Airport. Work began on the prototype aircraft.
In 2004, two years later to the day, the first flight of the Kodiak (N490KQ) took place. Within three months, the Kodiak had completed its 50th flight. In March 2007 s/n 001, the first fully conforming production aircraft, made its initial flight and joined the Kodiak prototype in the flight test program.
The Kodiak received FAA Type Certification on May 30 2007, and began customer deliveries in December of that year.
The 10 place Kodiak turboprop can take off in under 1,000 feet at full gross weight and climb at over 1,300 feet per minute. The landing gear and 19 inch propeller clearance allow the Kodiak to handle unimproved airstrips. The discontinuous leading edge technology brings control at slow speeds. At touchdown, the Kodiak only needs 705 feet to bring the full gross weight of 7,305 pounds to a stop–even on rough, bumpy strips.
Powered is by a Pratt and Whitney PT6-34 of 750shp with a 4,000TBO.
A wide range of options are available such as the external cargo compartment, TKS ice protection, Stormscope, Weather Radar, TCAS, and a jump package.
Kodiak is certified under Part 23 of the Federal Aviation Regulations in the Normal Category for day, night, VFR, and IFR flight operations, and certified for flight into known icing when equipped with the optional TKS Ice Protection System.
Kodiaks are in service with charter operators, corporate operators, personal owners, skydiving operations, governments, and humanitarian organizations.
Daher took over Quest Aircraft and the Kodiak in 2019.
Engine: P&W PT6A-34, 750 hp Takeoff @ 2200 RPM
Max. Continuous Power: 700 hp
Propeller: 96 in constant speed, feathering, reversible
Tip Clearance: 19 in
Cabin Width: 4’6″
Cabin Height: 4’9″
Cabin Length: 15’10″
Cargo Volume (exc. cockpit): 248 cu ft
Overall Length: 34’2″
Seats: 1-10
Doors: 3
Door Sill Height: 38 in
Cargo Door (LH side): 49.25 x 49.25 in
Cockpit Doors (both sides): 31 x 51 in
Wing Area: 240 sq ft
Span: 45′
Dihedral: 3°
Flap Type: Fowler, single-slotted
Flap Horizontal Span: 20′
Overall Height: 15’3″
Max. Ramp Weight: 7,305 lbs
Max. Takeoff Weight: 7,255 lbs
Base Aircraft Empty Weight: 3,770 lbs
Base Aircraft Useful Load: 3,535 lbs
Fuel Capacity: 320 USgal
Max. Wing Loading: 30.1 lbs/ sq ft
Max. Power Loading: 9.67 lbs/hp
Stall Speed Vs1 (flaps up): 77 kcas
Stall Speed Vs0 (flaps down): 60 kcas
Rate of Climb (max. cont. at SL): 1,371 ft/min
Rate of Climb (10,000 ft): 874 ft/min
Takeoff Ground Roll: 934 ft
Braked Roll (w/o reverse): 705 ft
Certified Ceiling: 25,000 ft
Cruise Performance: 183 ktas / 339 kph
Landing Gear: Fixed, faired leg, no pants
Main Gear: 8.5 x 10 Cleveland, spring steel
Nose Gear: 6.5 x 8 Cleveland, air-oleo, steel
Range w/ 45 min. reserve: (without Cargo Pod):
Max Cruise, at 174 ktas, 12,000 ft, fuel consumption 48 USgph – 1,005 nm / 5.8 hr
Max Range Cruise, at 135 ktas, 12,000 ft, fuel consumption 33 USgph – 1,132 nm / 8.4 hr
Designed by Jim Griswold, the prototype had only 50 hours on it when it arrived at Oshkosh 1988. Griswold’s company, Questair, was tooled up and nearly through the flight test program. The structural and flight test programs were the same as the FAA specified for factory certified planes.
The Venture uses stretched form fuselage skins that come as part of the kit ($49,950 1988). The cockpit was designed to be wider than a twin engined Beechcraft Baron.
The all-metal, roomy, fast, kit-built NuVenture (formally Questair Venture) was the winner and fastest plane at the Aircraft Spruce-sponsored 1998 Sun ’n Fun Sun100 race with an average speed of 303 mph.
The NuVenture flies on a Cont. I0-550-G with empty weight of 1240 lbs. The fuel tank holds 56 gallons. Vso is 61 KIAS. Range 12,000’ is 1,000Nm, VFR w/reserves or a cruise of 240 KTAS of 138 lb/h of fuel.
The Spirit derivative has fixed undercarriage.
Engine: Continental IO-550N6B, 310HP @ 2700 RPM
Propeller: McCauley BlackMac, 68″
Wing span: 27.5 ft
Wing area: 72.5 sq ft
Wing loading: 27.6 lb / sq ft
Structural limits: +5 G, -2.5G @ 2000 lb
Fuel capacity: 56 USG std, 88 optional
Gross weight: 2000 lb
Empty weight, equipped: 1300 lb
Payload: 700 lb
Cruise speed: 240 kt, 276 mph
Cabin width: 46 inches
Sea level top speed: 250 knots
Max rate of climb: 2500 ft / min
Takeoff to 50 ft: 1000 ft
Landing over 50 ft: 1600 ft
Range: 1000 nm, VFR reserves
Vx (best angle of climb): 90 knots
Vy (best rate of climb): 130 knots
Vne (never exceed): 300 knots
Va (maneuvering speed): 156 knots
Vso (stall in landing configuration): 61 knots
Vs1 (stall, clean): 68 knots
Gear speed (all): 170 knots
Seats: 2
The CQR-1 two-seat homebuilt aircraft was more or less a scaled-up development of the Roussoulières Occitan and was a design of Louis Cariou, former RSA President.
The prototype CQR-1 was constructed by the RSA at Centre Régional de Construction Aéronautique Amateur Quercy-Rouergue (CQR) under the leadership of Charles Roussoulières and it flew for the first time on March 2, 1997. This aircraft was powered by a 90 hp Limbach L2400EO3 engine.
A second very similar aircraft was also completed in France in 1998 or 1999 and by late 2010 at least 6 were constructed.
Engine: JPX / Limbach , 90 hp
Wing span: 7.4 m
Wing area: 8.9 sq.m
MAUW: 588 kg
Empty weight: 358 kg
Fuel capacity: 73 lt
Max speed: 250 kph
Cruise speed: 210 kph
Climb rate: 5 m/s
Seats: 2
Fuel consumption: 14 lt/hr
Plan price (1998): 1600 Fttc
Kit price (1998): 70 000 Fttc
Taken at Mineola airfield, the Queen Speed Monoplane / Double Gnome Monoplane; fitted with two Gnôme rotary engines of 50 hp – the two bladed propellers driven in opposite direction to prevent torque. Its design influenced by the Blériot monoplane (Queen built Blériot XI monoplanes under license at the time), the twin engine construction was thought to be safer, that in the case of malfunction of one, flight could continue using the other. The machine was financed by the banker Willis McCormick, who was president of the New York Aeronautical Society. Built in Fort George, New York in 1911, its first flight was made by Frank Stone on July 10, 1911. Unfortunately the machine was unstable during the climb, turned and crashed, injuring the fearless Stone. The machine was ruined, never to fly again.
Span: 26’4″
A two place version of the Challenger. This is a 2 seat high wing pusher microlight with a semi-enclosed cabin with a factory built airframe. All U.S. tubing. 10-15 minute set up time.
Quad City Challenger II Article
The Challenger II features two-seats and a 31.5 ft wingspan long wing. The Challenger II qualifies as a 51% kit for Experimental – Amateur-Built, can be flown with Sport Pilot Permit, and qualifies as Light Sport Aircraft.
In 2010 quick-build kits were from US$11,940 to US$16,035 ex engine with engine options being the Rotax 447, 503, 582 and HKS 700E.
The Challenger II Special is a 2 place with a 26 ft wingspan for quick roll rate and up 95 mph cruise speed.
With a 30 mph cross-wind capability and 300 ft take-off roll (average dual), the Challenger II Special qualifies as a 51% kit for Experimental – Amateur-Built, can be flown with Sport Pilot Permit, and qualifies as Light Sport Aircraft.
In 2010 quick-build kits were from US$13,165 to US$16,035 ex engine and engine options were the Rotax 447, 503, 582 and HKS 700E.
A version released in the UK circa 1998 was revised by Mike Whittaker.
Challenger II
Engine: Rotax 447, 42 hp
HP range: 40-52
Height: 6 ft
Length: 19 ft
Wing span: 31 ft
Wing area: 175 sq.ft
Weight empty: 310 lb
Gross: 800 lb
Fuel cap: 5 USG
Speed max: 85 mph
Cruise: 57 mph
Range: 150 sm
Stall: 25 mph
ROC: 600 fpm
Take-off dist: 200 ft
Landing dist: 200 ft
Service ceiling: 12,500 ft
Seats: 2
Landing gear: nose wheel
Cross-wind capability: 20 mph
Quad City Ultralights Aircraft Challenger II
Cruise: 70 mph
Stall: 30 mph
Range: 210 sm
Rate of climb: 700 fpm
Takeoff dist: 250 ft
Landing dist: 250 ft
Engine: Rotax 503, 50 hp
HP range: 40-65
Fuel capacity: 5USG
Empty weight: 330 lb
Gross weight: 850 lb
Length: 20 ft
Wing span: 31.5 ft
Wing area: 175 sq.ft
Cockpit width: 30 in
Landing gear: nosewheel
Cross-wind capability: 20 mph
Challenger II
Engine: Rotax 503, 52 hp
Wing span: 8.7 m
Wing area: 15.44 sq.m
MAUW: 386 kg
Empty weight: 175 kg
Fuel capacity: 38 lt
Max speed: 160 kph
Cruise speed: 130 kph
Minimum speed: 60 kph
Climb rate: 2.5 m/s
Certification: PFA
Seats: 2
Fuel consumption: 13 lt/hr
Kit price (1998): £9500
Quad City Ultralights Aircraft Challenger II CW LSS
Engine: Rotax 503, 52 hp
HP range: 50-75
Length: 20 ft
Wing span: 25 ft
Wing area: 145 sq.ft
Empty weight: 450 lb
Gross weight: 960 lb
Fuel capacity: 10 USG
Cruise: 95 mph
Stall: 40 mph
Range: 200 sm
Rate of climb: 700 fpm
Takeoff dist: 400 ft
Landing dist: 400 ft
Cockpit width: 28 in
Seats: 2
Landing gear: nosewheel
Cross-wind capability: 20 mph
Quad City Challenger II CW
Engine: Rotax 503, 52 hp
Height: 6 ft
Length: 20.5 ft
Wing span: 26 ft
Wing area: 143 sq.ft
Weight empty: 350 lb
Gross: 850 lb
Fuel cap: 5 USG
Speed max: 100 mph
Cruise: 85 mph
Range: 220 sm
Stall: 30 mph
ROC: 1000 fpm
Take-off dist: 300 ft
Landing dist: 200 ft
Service ceiling: 12,000 ft
Seats: 2
Landing gear: nose wheel
Cross-wind capability: 20 mph
Quad City Challenger II
Engine: Rotax 503, 52 hp
HP range: 52
Height: 6 ft
Length: 20.5 ft
Wing span: 26 ft
Wing area: 143 sq.ft
Empty weight: 350 lb
Gross weight: 850 lb
Fuel capacity: 5 USG
Top speed: 100 mph
Cruise: 85 mph
Stall: 30 mph
Range: 220 sm
Rate of climb: 1000 fpm
Takeoff dist: 300 ft
Landing dist: 200 ft
Service ceiling: 12,000 ft
Seats: 2
Landing gear: nosewheel
Cross-wind capability: 20 mph
Quad City Ultralights Aircraft Challenger II Special
Engine: Rotax 503, 50 hp
HP range: 50-65
Length: 20 ft
Wing span: 26 ft
Wing area: 143 sq.ft
Empty weight: 360 lb
Gross weight: 880 lb
Fuel capacity: 10 USG
Cruise: 85 mph
Stall: 36 mph
Range: 230 sm
Rate of climb: 700 fpm
Takeoff dist: 300 ft
Landing dist: 250 ft
Cockpit width: 30 in
Landing gear: nose wheel
Cross-wind capability: 20 mph
The Challenger Special is a single seat, clipped wing version, for a quicker roll rate. It qualifies as a 51% kit for Experimental – Amateur-Built, can be flown with a Sport Pilot Permit. And qualifies as a Light Sport Aircraft.
In 2010 quick-build kits were from US$10,215 to US$12,965 ex engine, and engine options include the Rotax 447, 503, 582 and HKS 700E.
The all have a 30 mph cross-wind capability and 200 ft take-off roll.
Engine: Rotax 447, 42 hp
HP range: 42-50
Height: 6 ft
Length: 18 ft
Wing span: 26 ft
Wing area: 117 sq.ft
Weight empty: 270 lb
Gross: 550 lb
Fuel cap: 5 USG
Speed max: 100 mph
Cruise: 85 mph
Range: 160 sm
Stall: 32 mph
ROC: 1000 fpm
Take-off dist: 200 ft
Landing dist: 200 ft
Service ceiling: 14,400 ft
Seats: 1
Landing gear: nose wheel
Cockpit width: 24 in
All Aero 