The S-20 has the wings, tail, fuel system, and aero servo ailerons from the S-7S Courier, and engine system, control sticks, flap lever, rudder pedals, seats, and instrument panel from the Coyote II S-6S. The intent was to answer the many requests for a side by side bush plane, equal to or beyond the Courier.

Construction is straight forward and classic. The wing features 3″ and 2″ custom extruded spars, airfoil struts, and stamped aluminum ribs. All welded 4130 steel fuselage and tail complete the fuselage.

Design features that will make the plane an easy project include: Welded steel fuselage and tail (all welding is completed at the factory) CNC drilled spars that eliminate almost all critical drilling and locating of holes. One-piece stamped ribs are punched with final hole sizes, and many parts are anodized eliminating the need to prime or corrosion proof. The kits are very detailed and supplied with all critical components. Builders only need to supply, engine, prop, paint, avionics, and fluids

Gallery

Engine Rotax 912ULS 100Hp

The S-19 is a low wing monoplane of traditional aluminum construction, featuring a constant chord wing.

The S-19 is powered by a Rotax 912 ULS engine producing 100 HP. The aircraft seats two in side by side in a 43.5” wide cockpit. Headroom is ample for even 6’4” pilots, and even larger with slight modifications.

Baggage can be carried in a 13 cubic foot compartment behind the seats with a loading capacity of 70lb. This compartment can be extended to the rear for approximate 9.5 cubic foot additional baggage space with a loading capacity of 30 lb.

The S-19 structure is of “monocoque” (stressed skin) carrying most of the strength through the aluminum skins. The skins are sufficiently supported with an internal structure of bulkheads and stringers to maintain shape.

High quality blind rivets are used throughout the construction of the airframe, with the exception of the spars, which come assembled with solid rivets. The fit and finish of the parts allowing virtually jigless assembly, and many parts to final hole size accelerate and assure a high quality structure. The S-19 may appear complicated, and high in part count, but we assure you the well machined components will assemble quickly, and with much lightness, due to the great care made in keeping things light.
The S-19 is a low wing monoplane of traditional aluminum construction, featuring a constant chord wing.

Kit Price 2010 w/o Engine: US$25,650
Plans Price: FREE ON CD; US$100 paper manual

In 2012 the previous S-LSA—the S-19LS Venterra low-wing, all-aluminum cruiser and S-6LS Coyote II (2,000 delivered) moved back to E-LSA or EAB kits-only status.

Engine: Rotax 912S, 100 hp
Propeller Diameter: 68 in
Propeller: 2 Blade ground adjustable
Gear Reduction: 1:2.43
Fuel G.P.H.: 5.0 gal @ 75%
Wing Span: 28 ft
Wing area: 126.9 sq ft
Mean Chord: 4 ft 7 in
Aspect: 6.18
Height: 95.5 in
Cockpit Width: 43.5 in
Seats: 2
Landing Gear: nose or tail
Baggage Capacity: 70 lbs
Fuel Capacity: 28 gal US
Take Off Roll: 325 ft
Rate of Climb: 900 fpm
Service Ceiling: 14,500 ft
Cruise: 128 mph
VNE: 150 mph
Stall Clean: 51 mph
Stall Flaps: 45 mph
Landing Roll: 325 ft
Cruise (@75%): 128 mph
Fuel burn(75%): 5.0 USgal/hr
Endurance (@75%): 4.55 hrs
Range (@75%): 580 miles
Cruise (@65%): 120 mph
Fuel burn(65%): 4.5 USgal/hr
Endurance (@65%): 5.10 hrs
Range (@65%): 610 miles
Gross Weight: 1320 lbs
Empty Weight: 820 lb
Useful Load: 500 lbs
Wing Loading: 10.4 psf
Power Loading: 13.2 lb/hp
Design Load: +4.4/ -2

Developed in 2000, the S-18 is a two place version of the S-17 Stinger.

In 2000, the planned kit price (ready to ship in March 2001) was US$14,500 and included the dual carb 503, tundra tires and a nose pod. The kit includes the welded and painted fuselage. No painting, welding, bonding or sanding is required to build the S-18.

Powered by a Rotax 503, the S-18 gets airborne in less than 300 ft, climbs at 700 fpm, with a cruise of 70 mph.

Single seat, developed into the two seat S-18

Prototyped as a taildragger at Oshkosh in 1994, it was later improved, first flown on 25 March 1997, as a nose gear, with a shorter and narrower chord wing, but 160 lb heavier. Powered by an 80 hp Rotax 912, it was shown at Sun ‘n Fun in April 1997.

The prototype was then fitted with a 129 hp Continental IO-240-B and a 66 x 66 Sensenich propeller.

The S-16 spar had been tested to + and –9G ultimate and the tail surfaces to the limit of Vne. The aircraft can be assembled without jigs. The spars are attached to the fuselage and the wing is then built around the spars. The fuselage is a composite shell, moulded in quarters, and encloses a prewelded 4130 tubular cage in the cockpit area. Four aluminium bulkheads are positioned between the rear of the turtledeck baggage compartment, which can be extended, and the tailcone. The fuselage composite is a straight laminate without a core.

The wing has a NASA GAW(2) series semi-symmetrical airfoil. It is all aluminium, covered with 2024-T3, 0.025 sheet. The main spars are tapered box beams of maximum 6 inch height with 2.5 inch caps. The rear spars are C channels. Each wing half has nine stamped aluminium ribs. Ailerons and flaps have an equal 50% span. Ailerons have a 2:1 differential with push-pull tube control; flaps offer three position deflection, manually operated to a maximum of 45 degrees through a centre positioned cockpit lever.

The tail’s vertical fin and stabiliser are seamless composite structures, moulded with the fuselage, and each having three composite ribs. Elevator and rudder are aluminium, containing four stamped ribs. The rudder is controlled by cable, and the elevator by torque tube. All of the aluminium components are assembled with Cherry Max blind rivets. Controls are dual, except the toe brakes on the left side only.

The cockpit is covered by a forward hinged, composite framed bubble canopy with gas lift struts. A composite and aluminium rollover arch is provided.

The option of nose or tailwheel is assisted by both type of gear sockets are included in the welded passenger cage. Both configurations use heat treated, tapered 6150 steel shaft. The tail spring is also tapered steel. The nose gear uses a chromoly strut with heavy duty compression spring. Leg fairings are metal, wheelpants composite. Aero Trainer 6.00 x 6 tires are on spun aluminium Matco wheels with dual caliper brakes on the mains.

Approach speed is around 75 mph, across the fence at 60 mph, and touchdown at 55 mph.

In 1998 the kit price, including Continental engine, was US$39,000. Less engine the kit was US$25,000, and less firewall forward was US$21,000.

Engine: Rotax 912, 78 hp
HP range: 78-130.
Vne: 248 mph
Cruise: 140 mph.
Range: 630 sm
Stall: 50 mph.
ROC: 800 fpm
Take-off dist: 375 ft.
Landing dist: 500 ft
Service ceiling: 14,000 ft.
Fuel cap: 16 USG
Weight empty: 700 lbs.
Gross: 1200 lb
Height: 5 ft.
Length: 19.9 ft
Wing span: 24 ft.
Wing area: 86 sq.ft
Wing: NASA GAW(2)
Seats: 2.
Landing gear: tail wheel
Wheel tread: 6 ft 8 in
Cockpit width: 40 in
Headroom: 38 in
Legroom: 52 in
Horizontal tail span: 6 ft 9 in

Engine: Continental IO-240B,130hp
Propeller: 66 x 66 Sensenich
Height: 5.4 ft
Length: 18.7 ft.
Wing span: 24 ft
Wing area: 87 sq.ft.
Wing: NASA GAW(2)
Weight empty: 830 lbs
MTOW: 1300 lbs.
Fuel cap: 32 USG.
Vne: 248 mph.
Cruise 65%: 170 mph
Stall: 55 mph.
Range: 850 sm
Rate of climb; 1200 fpm @ 95 mph
Take off speed: 60 mph
Take-off dist: 400 ft
Landing dist: 500 ft.
Service ceiling: 14,000 ft
Roll rate: 200 deg/sec
Glide ratio: 9:1
Seats: 2
Cockpit width: 40 in
Headroom: 38 in
Legroom: 52 in
Landing gear: tail or nose.
Wheel tread: 6 ft 8 in
Horizontal tail span: 6 ft 9 in
Design load: +9/-9g

Engine: Continental IO-240
Wing span: 7.32 m
Wing area: 8.8 sq.m
MAUW: 544 kg
Empty weight: 318 kg
Fuel capacity: 121 lt
Max speed: 399 kph
Cruise speed: 275 kph
Minimum speed: 80 kph
Climb rate: 5 m/s
Seats: 2
Kit price (1998): $39,000
Load factor: +9 / -9

Engine: Rotax 912
Wing span: 7.32 m
Wing area: 8.8 sq.m
MAUW: 544 kg
Empty weight: 318 kg
Fuel capacity: 121 lt
Max speed: 399 kph
Cruise speed: 275 kph
Minimum speed: 80 kph
Climb rate: 5 m/s
Seats: 2
Kit price (1998): $30,000
Load factor: +9 / -9

First flew in 1991.

Gallery

Engine: Rotax 582, 65 hp
HP range: 46-65.
Speed max: 120 mph
Cruise: 90 mph.
Range: 200 sm
Stall: 38 mph.
ROC: 1000 fpm
Take-off dist: 225 ft.
Landing dist: 130 ft
Service ceiling: 15,000 ft.
Fuel cap: 9 USG
Weight empty: 390 lbs.
Gross: 775 lbs
Height: 7 ft.
Length: 18.83 ft
Wing span: 26.47 ft.
Wing area: 100 sq.ft
Seats: 1.
Landing gear: nose wheel.

The S-12XL Airaile went into production in March of 1990 and has enjoyed a progressive evolution. Improvements to cabin comfort, durability, and performance are the direct result of working with user input. The Airaile was designed to fulfill requests for a two-place pusher with side-by-side seating that was economical to buy, quick to build, easy to fly, and rugged enough to withstand the rigors of training. The Airaile only requires a two-car garage and common shop tools and skills to complete from start to finish.

The S-12S, “Super Airaile” is based on the S-12XL series. Changes made to the S-12S include a lower cabin and engine mount height. The result is less frontal area and a lower thrust line. Headroom is still more than adequate and will accommodate pilots up to 6ft 6in. Dacron coverings were replaced with traditional dope and fabric. To adapt the new covering system, mods to the wing and tail included new ribs all around, plus leading edge wraps for the wing. The total effect of the mods brought about an increase in cruise, climb, glide ratio, and a lower stall. In the air the handling is improved in both roll and yaw.

Build time for the Super Airaile will be on the average 200 to 300 hours more than the XL, but still within reason. Most builders should complete the plane in 6 to 12 months. This is due to the tremendous amount of pre-fabrication and precise fit of our parts. Quality airtime is built around a kit that is designed to be built by the first time builder. A good manual is at the center of fast build times.

Gallery

Engine: Rotax 503, 52 hp
Propeller Dia: 68 in
Propeller Type: Wood
Gear Reduction: 1:2.58
Fuel G.P.H.: 4.0 USgal @ 85%
Wing Span: 31.0 ft
Wing area: 152 sq ft
Mean Chord: 4 ft 10.5 in
Aspect: 6.33:1
Length: 21 ft 8 in
Height: 88 in
Cockpit Width: 41 in
Headroom: 41.5 in
Legroom: 44.5 in
Seats: 2
Doors: 2
Landing Gearfixed nose
Fuel Capacity: 18 gal US
Gross Weight: 920 lbs
Empty Weight: 430 lbs
Useful Load: 490 lbs
Wing Loading: 6.0 lbs
Power Loading: 17.7 lbs
Limit Load Factors: +4 -2
Take Off Roll: 285 ft
Rate of Climb: 500 fpm
Service Ceiling: 12,500 ft
Cruise: 65 mph
VNE: 100 mph
Stall Clean: 38 mph
Stall Flaps: 32 mph
Roll Rate: 70° /sec
Glide Ratio: 7:1
Landing Roll: 200 ft
Endurance: 4.5 hrs
Range: 292.5 miles

Engine: Rotax 582, 65 hp
Propeller Diameter: 68 in
Propeller Type: Wood
Gear Reduction: 1:2.58
Fuel G.P.H.: 5.75 USgal @ 85% / 14 lt/hr
Wing Span: 31.0 ft / 9.45 m
Wing area: 152 sq ft / 15.1 sq.m
Mean Chord: 4 ft 10.5 in.
Aspect: 6.33:1
Length: 21 ft 8 in
Height: 88 in
Cockpit Width: 41 in
Headroom: 41.5 in
Legroom: 44.5 in
Seats: 2
Doors: 2
Landing Gear: fixed nose
Fuel Capacity: 18 gal US / 50 lt
Take Off Roll: 250 ft
Rate of Climb: 900 fpm / 2.5 m/s
Service Ceiling: 14,000 ft
Cruise: 75 mph / 120 kph
VNE: 100 mph
Stall Clean: 40 mph
Stall Flaps: 33 mph
Roll Rate: 70° /sec
Glide Ratio: 7:1
Landing Roll: 200 ft
Endurance: 3.1 hrs
Range: 232.5 miles
Gross Weight: 975 lbs / 435 kg
Empty Weight: 475 lbs
Useful Load: 500 lbs
Wing Loading: 6.4 lbs
Power Loading: 15.0 lbs
Limit Load Factors: +4 -2
Certification: VZ

Engine: Rotax 912/912S, 80 hp/100 hp
Propeller Diameter: 68 in to 72 in
Propeller Type: Wood
Gear Reduction: 1:2.27/1:2.43
Fuel G.P.H.: 4.5/5 USgal @ 75%
Wing Span: 31.0 ft
Wing area: 152 sq ft
Mean Chord: 4 ft 10.5 in
Aspect: 6.33:1
Length: 21 ft 8 in
Height: 88 in
Cockpit Width: 41 in
Headroom: 41.5 in
Legroom: 44.5 in
Number of Seats: 2
Doors: 2
Landing Gear: fixed nose
Fuel Capacity: 18 gal US
Gross Weight: 1100 lbs
Empty Weight: 575 lbs
Useful Load: 525 lbs
Wing Loading: 7.2 lbs
Power Loading: 11 lbs
Limit Load Factors: +4 -2
Take Off Roll: 285/220 ft
Rate of Climb: 900/1200 fpm
Service Ceiling: 14,000/14,500 ft
Cruise: 85/90 mph
VNE: 100 mph
Stall Clean: 42 mph
Stall Flaps: 35 mph
Roll Rate: 70° /sec
Glide Ratio: 7:1
Landing Roll: 200 ft
Endurance: 4.4/4.0 hrs
Range: 374/360 miles

S-12S
Stall: 36 kt / 42 mph / 68 kmh
Cruise: 87 kt / 100 mph / 161 kmh
VNE: 104 kt / 120 mph / 193 kmh
Empty Weight: 295 kg / 650 lbs
MTOW Weight: 522 kg / 1150 lbs
Climb Ratio: 1200 ft/min / 6 m/s
Glide Ratio: 8:1
Take-off distance (50ft obstacle): 400 ft / 122 m
Landing distance (50ft obstacle): 400 ft / 122 m

S-12XL Airaile
Stall: 29 kt / 33 mph / 53 kmh
Cruise: 65 kt / 75 mph / 121 kmh
VNE: 87 kt / 100 mph / 161 kmh
Empty Weight: 215 kg / 475 lbs
MTOW Weight: 442 kg / 975 lbs
Climb Ratio: 900 ft/min / 5 m/s
Glide Ratio: 7:1
Take-off distance (50ft obstacle): 400 ft / 122 m
Landing distance (50ft obstacle): 400 ft / 122 m

First flown in 1986, the Sakota can cross country or aerobat. The small but potent wing gives it high performance in short take-offs and 120 mph cruise speeds and the tapered wing reduces drag. A bubble canopy and large under wing windows offer exceptional visibility. Comfort for two in the 37″ wide cabin with well upholstered bench seat. A quick build kit was available. Fly aerobatics solo and cross country with 2.

Features:
Rotax 582 65 HP liquid cooled with dual CDI ignition; RPM gauge; 2-Blade wood prop; 4130 Welded steel fuselage, tail group and tapered steel landing gear; Aluminum wheels with aircraft tires; Wheel pants; Pre-formed trussed wing ribs; .020 Aluminum leading edge wrap; 3″ Tubular Aluminum Main spars; 2″ Tubular Aluminum Aft spars; (2) 9 Gallon wing tanks; Seat adjustable in tilt and fore and aft; 2.7 ounce aircraft covering fabric, all tapes, glue, and inspection plates; Aluminum framed canopy; Airfoil struts; In-flight pitch trim; In-flight start; “Deep Set” panel; Roll over protection; Shoulder harnesses and lap belts; Dual elevator horns; 1 1/4″ Push-pull elevator tube; Cable operated rudder; 3-Position flaps; Differential ailerons are cable and push-pull tube operated; Dual control sticks and throttles; Center flap lever; Pre-molded cowling; 12″ Composite spinner; Heavy duty engine mount; Under the wing windows; Dual fuselage foot pegs and wing steps; Dual wire braced folding tail; Steerable tail wheel; Dual rudder pedals; Hydraulic brakes; Firewall sound proofing; Baggage compartment.

The S-10 Sakota is an FAA Approved 51% Kit – No welding required, with a build time of 350 to 600 hours.

Engine: Rotax 582, 65hp
Propeller Diameter: 68 in to 70 in
Propeller Type: Wood
Gear Reduction: 1:2.58
Fuel G.P.H.: 5.75 USgal @ 85%
Wing Span: 24.0 ft
Wing area: 95.0 sq ft
Mean Chord: 4 ft 2 in
Aspect: 4.23:1
Length: 17 ft 10 in
Height: 4 ft 10 in
Cockpit Width: 37 in
Headroom: 38 in
Legroom: 42 in
Number of Seats: 2
Doors: 2
Landing Gear: fixed tail
Baggage Volume: 8 cubic ft
Baggage Capacity: 30 lbs
Fuel Capacity: 18 gal US
Gross Weight: 960 lbs
Empty Weight: 460 lbs
Useful Load: 500 lbs
Wing Loading: 10.1 lbs
Power Loading: 14.7 lbs
Limit Load Factors: +4 -2
Take Off Roll: 300 ft
Rate of Climb: 800 fpm
Service Ceiling: 12,500 ft
Cruise: 110 mph
VNE: 130 mph
Stall Clean: 45 mph
Roll Rate: 100° /sec
Glide Ratio: 7:1
Landing Roll: 400 ft
Endurance: 3.1 hrs
Range: 341 miles

Engine: Rotax 912, 78 hp
HP range: 65-78.
Speed max: 150 mph
Cruise: 120-130 mph.
Range: 540 sm
Stall: 42-45 mph.
ROC: 800 fpm
Take-off dist: 325 ft.
Landing dist: 500 ft
Service ceiling: 14,000 ft.
Fuel cap: 18 USG
Weight empty: 525 lbs.
Gross: 1100 lbs
Length: 17.83 ft.
Wing span: 24 ft
Wing area: 95 sq.ft.
Height: 4.8 ft
Seats: 2.
Landing gear: tail wheel
Aerobatic.

Engine: Rotax 912/921S, 80/100hp
Propeller Diameter: 68 in to 70 in
Propeller Type: Wood
Gear Reduction: 1:2.58
Fuel G.P.H.: 4.1/4.5 USgal @ 80%
Wing Span: 24.0 ft
Wing area: 95.0 sq ft
Mean Chord: 4 ft 2 in
Aspect: 4.23:1
Length: 17 ft 10 in
Height: 4 ft 10 in
Cockpit Width: 37 in
Headroom: 38 in
Legroom: 42 in
Number of Seats: 2
Doors: 2
Landing Gear: fixed tail
Baggage Volume: 8 cubic ft
Baggage Cap: 30 lbs
Fuel Capacity: 18 gal US
Take Off Roll: 325 ft/310 ft
Rate of Climb: 900 fpm/1200 fpm
Service Ceiling: 14,000 ft/14,500 ft
Cruise: 120 mph/125 mph
VNE: 130 mph
Stall Clean: 48 mph
Roll Rate: 100° /sec
Glide Ratio: 8:1
Landing Roll: 400 ft
Endurance: 4.4 hrs/4 hrs
Range: 528 miles/520 miles
Gross Weight: 1010 lbs
Empty Weight: 510 lbs
Useful Load: 500 lbs
Wing Loading: 10.6 lbs
Power Loading: 12.6 lbs
Load Limit: +4 -2g

The S-9 Chaos has been in production since 1986. A stock S-9 equipped with a Rotax 503 47hp engine is potent enough to compete in sportsman class aerobatics. S-9’s have been equipped with up to 100 hp engines with spectacular results. With full inverted capability, a Chaos can achieve advanced aerobatics. As with all RANS kits, the Chaos comes welded and pre-fabricated, reducing assembly time and increasing precision.

The S9 Chaos powered by a Rotax 503 has wing and header fuel tanks, a four point harness plus lapstrap, and open cockpit with optional canopy.

Gallery

Engine: Rotax 504, 47 hp
Prop: 68-70 in dia.
Prop reduction: 2.58-1
Fuel consumption: 4USG/hr at 70% pwr
Wing Span: 22.0 ft
Wing area: 91.5 sq ft
Mean Chord: 4 ft 2 in
Aspect: 5.3:1
Length: 15 ft 8 in
Height: 4 ft 10 in
Cockpit Width: 26 in
Headroom: 38 in
Legroom: 45.5 in
Number of Seats: 1
Doors: 1
Landing Gear: nose or tail
Fuel Capacity: 9 or 18 gal US
Take Off Roll: 250 ft
Rate of Climb: 800 fpm
Service Ceiling: 13,500 ft
Cruise: 90 mph
VNE: 130 mph
Stall Clean: 38 mph
Roll Rate: 100° /sec
Glide Ratio: 8:1
Landing Roll: 400 ft
Endurance: 2.25 hrs/4.5 hrs
Range: 202.5 miles/405 miles
Gross Weight: 670 lbs
Empty Weight: 340 lbs
Useful Load: 330 lbs
Wing Loading: 7.32 lbs
Power Loading: 14.2 lbs
Limit Load Factors: +6 -4

Engine: Rotax 582, 65 hp
Prop: 68-70 in dia.
Prop Reduction: 1:2.58
Fuel consumption: 5.76USG/hr at 85% pwr
Wing Span: 22.0 ft
Wing area: 91.5 sq ft
Mean Chord: 4 ft 2 in
Aspect: 5.3:1
Length: 15 ft 8 in
Height: 4 ft 10 in
Cockpit Width: 26 in
Headroom: 38 in
Legroom: 45.5 in
Number of Seats: 1
Doors: 1
Landing Gear: nose or tail
Fuel cap: 9 or 18 USG
Take Off Roll: 200 ft
Rate of Climb: 1000 fpm
Service Ceiling: 15,000 ft
Cruise: 100 mph
VNE: 130 mph
Stall Clean: 41 mph
Roll Rate: 100° /sec
Glide Ratio: 8:1
Landing Roll: 400 ft
Endurance: 1.56 hrs/3.13 hrs
Range: 156.5 miles/313 miles
Gross Weight: 710 lbs
Empty Weight: 375 lbs
Useful Load: 335 lbs
Wing Loading: 7.76 lbs
Power Loading: 11.0 lbs
Limit Load Factors: +6 -4g