11718 Salem Warren Rd, Salem, OH 44460, USA.
LSA builder
LSA/UL
Skyline Cruiser
The Skyline Cruiser ZK-VOK was fully enclosed with strut batwing doors and built over four year period.
Powered by a Rotax UL Blue Head 582 and equipped with Micro Aviation B22 Bantam specs-wings, box spar aluminium leading edge, fabric covered, deltron paint scheme.
Cruise 68-70 kt IAS
Skyleader Aircraft Skyleader
The all metal trapezoidal wing with two spar construction consists of the outer parts and the wing center section. The short wing center section is firmly placed into the fuselage. The outer parts of the wing are separable for transport.
Wing profile is GA 
– 1 at the root and the GA – 2 at the tip. The main wing spar is placed in 33 % of the profile depth and is perpendicular to the longitudinal aircraft axis. The main spar is created from the dural beams and web. The beams are from metallurgical L – profiles, milled spanwise and riveted with web using full rivets. The web with changing thickness is relieved by the lightening holes spanwise. The ribs are stamped including lightening holes. The back spar is created by the L-profile and riveted web, which is relieving with lightening holes too. The cover is riveted with the pop rivets to the beams and the ribs. The flaps hinges are from dural sheets with milled grooves for flaps extending. Three safe attachment points attach the wing outer section parts with the wing center section.
The flaps – Fowler type with a proportional depth 29 % have 10 deg and 35 deg deflections. The flaps drive is mechanical in standard. The electrical system is available as an option. The mechanical drive system is created by toothed wheels with racks. The flap controller is placed in tunnel of the cockpit. Left and right parts of the flap drive are connected together. Flap construction is created by spar, ribs and cover, which are riveted with pop rivets.
The aileron is all metal with one spar. Construction consists of control rods and bent levers in the transverse control. The aileron deflections are differentiated.
The wing center section composed with two spars similar to the outer wing ones. These spars are firm attached into the fuselage construction. There are two fuel integral tanks in the front part of the wing center section, each one with 8.5 gallons of fuel capacity. The main landing gear is attached to the wing center section, so it creates an independent set, which can be moved at manufacturing or emergency transported during operation.
The all metal fuselage construction is created by dural L – form stringers, by metallic bulkheads and by cover. The stringers are attached together through the whole length of the fuselage and create a base supporting system of the fuselage. A transverse cross-section of the fuselage is shaped so that the cover could be unrolled and so was stabilized for an increasing of a critical tension. In the cockpit area is the supporting system replenished by steely spar of the closed square cross-section – middle panel of the cockpit. The seats are lengthwise adjustable and equipped by 4 points seat belts. The canopy creates perspex, which is inset into fiberglass frame with reinforcement from carbon and cevlar fibers. The canopy allows a perfect view backwards. The control is dual with control sticks and pedals. The directional control is funicular with turnbuckles.
The landing gear is retractable, controlled by electric motor with manual emergency control. Fixed Landing gear is determined for the Light Sport.
Both wheels of main landing gear and the nose wheel are towed and they are sprung with rubber shock absorbers, created by circular rubber segments. The nose landing gear is at protuberant position connecting with the foot’s control and is controllable at +15° range. The main landing gear wheels are braked with a central manual hydraulic brake lever at the control stick.
The airplane is equipped with Rotax 912 UL (80hp) engine, optionally with Rotax 912 ULS (100hp) or Rotax 914 UL (115hp turbo) engine. The engine is attached by welded bed with the use of rubber shock absorbers through the firewall into the fuselage stringers and central tunnel. Three (3) blade on-ground adjustable propeller is delivered with the plane as standard. As the optional order can be airplane equipped with mechanically or electrically in-flight adjustable propeller, two or three blade.
All metal tail units are standard alignment with a rudder and an elevator. The profile of Vertical Stabilizator and Horizontal Stabilizator is symmetrical to NACA 0012. They are created by spars, ribs and cover. An elevator is divided; therefore it is possible to take it down without disconnecting the controls. The same construction is used at the others control surfaces. A stabilizer is attached to the fuselage by four hinges and is possible to dismantle it without disconnecting the controls.
The aircraft has two integral tanks with capacity of 2×32 liters (total 64l) of the fuel. Optionally can be installed the additional fuel tanks supplying the aircraft with additional 2×15 liters (total 30 liters) of the fuel. Therefore max. amount of the fuel should rise up to 94 liters. The tanks are created by lead box inside the wing center section, out of the fuselage. They are riveted through caulk mastic and the wing center section cover forms concurrently a tank wall. The fuel delivery is ensured by a pneumatic pump for the overflowing the system and in the reason of an error or delivery deficient of the pneumatic pump is possible to use an additional electric pump. A fuel amount is indicated by two analogue fuel gauges.
The aircraft is in UL category furnished with standard instruments for flight and engine control. The Radio, Transponder, Glass Panel, GPS or another flight and engine instruments are installed on the customer’s request. Color painting, upholstery and internal cockpit surface adjustment of the aircraft is realized individually on basis of plentiful amount of offered services and products.
Skyleader 100
Engine: HKS 700E
MTOW: 315kg
Cruise at 75% pwr: 75kts
Seats: 1
Skyleader 150 UL
Stall: 26 kt / 30 mph / 48 kmh
Cruise: 119 kt / 137 mph / 220 kmh
VNE: 130 kt / 149 mph / 240 kmh
Empty Weight: 282 kg / 622 lbs
MTOW Weight: 450 kg / 992 lbs
Skyleader 200 UL
Stall: 26 kt / 30 mph / 48 kmh
Cruise: 119 kt / 137 mph / 220 kmh
VNE: 130 kt / 149 mph / 240 kmh
Empty Weight: 282 kg / 622 lbs
MTOW Weight: 450 kg / 992 lbs
Skyleader 500 LSA
Stall: 31 kt / 36 mph / 58 kmh
Cruise: 120 kt / 138 mph / 222 kmh
VNE: 129 kt / 149 mph / 240 kmh
Empty Weight: 313 kg / 690 lbs
MTOW Weight: 580 kg / 1278 lbs
Sky King International
1984: 419 Wellesley Street E., Toronto, Ontario, Canada M4X 1H5.
LSA builder
Skyhook Sailwings
Amongst the early enthusiasts who were amongst the first to buy, build or fly a hang glider during early seventies who later went on to become manufacturers was Len Gabriels who founded Skyhook.
1982: Skyhook Sailwings Ltd, Vale Mill, Hollinwood Road, Oldham, Lancs OL8 4PG, Great Britain.
Skyhigh Sky Baby
Single seat single engined high wing monoplane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; conventional tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by half span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile; double-surface. Undercarriage has three wheels in tail dragger formation; suspension on tailwheel and bungee suspension on main wheels. Push right go right tailwheel steering connected to yaw control. No brakes. Aluminium tube/wood/steel tube fuselage partially enclosed. Engine mounted below wing driving pusher propeller.
The single seat Skybaby is aimed at homebuilders and is therefore only sold as sets of plans. It is intended to have a McCulloch Mc101 engine developing 12.5 hp at 9000rpm or, for heavier pilots, the Yamaha KT100S of 15 hp at 10,000 rpm. Certain parts are available from Skyhigh Ultralights, for example the landing gear, controls, reduction drive, seat etc.
The price of the plans was $55 in 1982. According to Skyhigh, the construction time for the Skybaby should not exceed 200h.
Engine: McCulloch Mc 101, 12.5hp at 9000rpm
Power per unit area 0.09hp/sq.ft, 1.1 hp/sq.m
Fuel capacity 3.0 US gal, 2.5 Imp gal, 11.4 litre
Length overall 17.0 ft, 5.18 m
Height overall 5.0ft, 1.52m
Wing span 32.0ft, 9.75m
Constant chord 4.0 ft, 1.22 m
Sweepback 0 deg
Total wing area 128 sq.ft, 11.9sq.m
Wing aspect ratio 8.0/1
Empty weight 155 lb, 70kg
Max take off weight 360 lb, 163kg
Payload 205 lb, 93kg
Max wing loading 2.81 lb/sq.ft, 13.7 kg/sq.m
Max power loading 28.8 lb/hp, 13.0kg/hp
Load factors; +5.0, 3.0 ultimate
Max level speed 40 mph, 64 kph
Never exceed speed 50 mph, 80kph
Max cruising speed 35mph, 56kph
Stalling speed 24 mph, 39 kph
Max climb rate at sea level 225 ft/min, 1.1 m/s
Best glide ratio with power off 9/1
Take off distance 200 ft, 60 m
Landing distance 100 ft, 30 m
Skyhigh
1982: Skyhigh Ultralights Inc, PO Box 64, Langhorne, Pennsylvania 19047, USA.
1987: Skyhigh Ultralights, Langhorne, Pennsylvania.
UL builder
Skyfox CA-25 Gazelle
To meet market demand CA-22 were again reworked and a new type certificate was gained for the CA-25N (nose-wheel) Gazelle. This name stems from the fact that the redevelopment finance for this aircraft was obtained from the Swiss agents Gisela. Production of the CA-22 Elan and the CA-25 Impala (both with tail-wheels) continued but sales of the CA-25N (nose-wheel) went at about l0 to 1.
The CA-25N nose wheel development, first flew 1995.
The airframe is built from 4130 chrome molyb¬denum steel, with the wings built up on tubular spars with an internal web, along with metal drag and anti drag braces. Plywood ribs are epoxy bonded to the spars. They are then covered with Stits polyfibre and Dulux paint. Power is from a Rotax 912, which gives the aircraft the flatter engine cowl¬ing — the easiest way to differentiate this machine from the radial type cowl of the US Kitfox.
Production ceased in late 1999 after about 106 tail-draggers and 83 nose-wheeled machines had been constructed.
CA-25
Tail wheel undercarriage
CA-25N
Extended wingspan: 9.52m (folded: 2.4m)
Skyfox CA-22
About 100 CA-22 tail-wheel machines were built and registered either as CA-22s in the ultralight (AUF) class, or as CA-22As under full VH registration marks. To meet market demand these models were again reworked and a new type certificate was gained for the CA-25N (nose-wheel) Gazelle. Production of the CA-22 Elan and the CA-25 Impala (both with tail-wheels) continued but sales of the CA-25N (nose-wheel) went at about l0 to 1.
Skyfox Aviation Skyfox
Stall: 43 kt / 49 mph / 80 kmh
Cruise: 70 kt / 81 mph / 130 kmh
VNE: 93 kt / 107 mph / 172 kmh
Empty Weight: 315 kg / 694 lbs
MTOW Weight: 520 kg / 1146 lbs
Glide Ratio: 10:1
Take-off distance (50ft obstacle): 330 ft / 100 m
Landing distance (50ft obstacle): 390 ft / 120 m
Skyfox Aviation
Skyfox Aviation came on the scene in 1991 at Caloundra, north of Brisbane, after acquiring the rights to manufacture the US Kitfox ultralight. The aircraft was significantly modified to meet the CAQ 101-55 standards for a commercially-built two-seat ultralight able to be used for flight training. The aircraft was also re-worked to meet the international JAR/VLA certification standards for sale in Europe and this was completed by about mid-1993, as the CA-22.
Founded as a public company in 1996 but originating in 1991. Offers the Skyfox STOL two-seat braced high-wing cabin monoplane (first flown September 1989) for pleasure, training, surveillance and other roles, in CA22 ultralight, CA25 tailwheel general aviation and CA25N nosewheel general-aviation versions.
A fi¬nancial crisis in 1997 saw the company again re¬financed.
All Aero 