The 1929 Sky Romer was designed by Paul Hobrock and Glenn Lampton, first flying on 9 February 1929.
Originally Sky Roamer, but the spelling was changed when Crosley Co claimed infringement of patent on their radio named “Roamio.”
Registered NX206E it was reportedly dismantled and stored in the early 1930s.
Engine: 180hp Hisso E
Wingspan: 45’9″
Cruise: 105 mph
Seats: 4
The Skyriders company builds a European version of the Ultralight Flight Phantom, which is identical to the American machine except for the power pack and a larger fuel tank.
Ultralight Flight fit a Kawasaki TA440 engine and, while this variant remains avail¬able in Europe, the popularity of Robin engines in Europe has led Skyriders to standardise on the Robin EC44 power unit.
Nicklow En¬gineering supplies his engine in lightweight form, without cooling fan, in which guise it gives 295 lb (134 kg) of static thrust.
Engine: Robin EC44, 58 hp at 7200 rpm
Propeller diameter and pitch 60 x 30 inch 1.52 x 0.76 m
Toothed belt reduction, ratio 2.5/1
Max static thrust 295 lb, 134 kg
Power per unit area 0.41 hp/sq.ft, 4.4 hp/sq.m
Fuel capacity 6.0 US gal, 5.0 Imp gal, 22.7 litre
Empty weight 229 lb, 104kg
Max take off weight 509 lb, 231 kg
Payload 280 lb, 127 kg
Max wing loading 3.61 lb/sq.ft, 17.6 kg/sq.m
Max power loading 8.8 lb/hp, 4.0kg/hp
Max recommended level speed 70mph, 113kph
Max possible level flight speed >80mph, >129kph
Never exceed speed 100 mph, 161 kph
Max cruising speed 70mph, 113kph
Economic cruising speed 50 mph, 80 kph
Stalling speed 28 mph, 45 kph
Max climb rate at sea level 1500 ft/ min, 7.6 m/s
Take off distance 60 ft, 18 m on concrete
Landing distance 50 ft, 15 m on concrete
Range at average cruising speed 150 mile, 241 km
Manufactured by Skyreach Aircraft of Johannesburg, South Africa, the aircraft construction is tubular Aluminium with anodised Stainless steel joiners, composite cowlings and Trylam wing and Fuselage coverings with Rip Block.
Known previously as the Cheetah, the BushCat tube/dacron sailcloth envelope, ultralight-style S-LSA had a $49,995 base price. By 2019 that was $113000.
Good short field take-off and landing capabilities a 90kt cruise.
Rotax 582, 65HP
Empty Weight: 617 lb
Wing Span: 31,5ft
Wing Area: 142 sq.ft
Wing Chord: 54 in
Aircraft length: 18,6 ft
Aircraft Height: 6,63 ft
Cabin Height: 54 in
Cabin Width: 47,25 in
Baggage Compartment: 2 x 25 L (81 lbs max)
Fuel Capacity: 24,8 gallons
Propeller (Recommended): 3 Blade Kiev
Fuel Consumption (80% power): 3,8 gal/hour
Take Off Roll: 328 ft
Rate of Climb: 700 ft/min
Service Ceiling: 12 000 ft
Max Crosswind Component: 32 MPH
Cruise Speed (65%): 75 MPH
VNE: 125 MPH
Glide Ratio: 10-1
Power Off Stall (no flaps): 40 MPH
Power Off Stall (with flaps): 35 MPH
Landing Ground Roll: 235 ft
Gross Weight: 1245 lb
Useful Load: 628 lbs
Load Factors: + 6/- 4
Endurance (with reserves): 6,5 hrs
Range (with reserves): 500 Miles
Rotax 912UL, 80HP
Empty Weight: 617 lb
Wing Span: 31,5ft
Wing Area: 142 sq.ft
Wing Chord: 54 in
Aircraft length: 18,6 ft
Aircraft Height: 6,63 ft
Cabin Height: 54 in
Cabin Width: 47,25 in
Baggage Compartment: 2 x 25 L (81 lbs max)
Fuel Capacity: 24,8 gallons
Propeller (Recommended): 3 Blade Kiev
Fuel Consumption (80% power): 4,5 gal/hour
Take Off Roll: 292 ft
Rate of Climb: 1000 ft/min
Service Ceiling: 12 000 ft
Max Crosswind Component: 32 MPH
Cruise Speed (65%): 95 MPH
VNE: 125 MPH
Glide Ratio: 10-1
Power Off Stall (no flaps): 40 MPH
Power Off Stall (with flaps): 35 MPH
Landing Ground Roll: 235 ft
Gross Weight: 1245 lb
Useful Load: 628 lbs
Load Factors: + 6/- 4
Endurance (with reserves): 7,5 hrs
Range (with reserves): 600 Miles
Rotax 912ULS, 100HP
Empty Weight: 617 lb
Wing Span: 31,5ft
Wing Area: 142 sq.ft
Wing Chord: 54 in
Aircraft length: 18,6 ft
Aircraft Height: 6,63 ft
Cabin Height: 54 in
Cabin Width: 47,25 in
Baggage Compartment: 2 x 25 L (81 lbs max)
Fuel Capacity: 24,8 gallons
Propeller (Recommended): 3 Blade Kiev
Fuel Consumption (80% power): 5 gal/hour
Take Off Roll: 262 ft
Rate of Climb: 1200 ft/min
Service Ceiling: 14 000 ft
Max Crosswind Component 32 MPH
Cruise Speed (65%): 105 MPH
VNE: 125 MPH
Glide Ratio: 10-1
Power Off Stall (no flaps): 40 MPH
Power Off Stall (with flaps): 35 MPH
Landing Ground Roll: 235 ft
Gross Weight: 1245 lb
Useful Load: 628 lbs
Load Factors: + 6/- 4
Endurance (with reserves): 7,0 hrs
Range (with reserves): 700 Miles
Amphibian 912ULS, 100HP
Empty Weight: 865 lb
Wing Span: 31,5ft
Wing Area: 142 sq.ft
Wing Chord: 54 in
Aircraft length: 18,6 ft
Aircraft Height: 8,10 ft
Cabin Height: 54 in
Cabin Width: 47,25 in
Baggage Compartment: 2 x 25 L (81 lbs max)
Fuel Capacity: 24,8 gallons
Propeller (Recommended): 3 Blade Kiev
Fuel Consumption (80% power): 5 gal/hour
Take Off Roll: 540 ft (water)
Rate of Climb: 850 ft/min
Service Ceiling: 12 000 ft
Max Crosswind Component: 20 MPH
Cruise Speed (65%): 90 MPH
VNE: 115 MPH
Glide Ratio: 8-1
Power Off Stall (no flaps): 40 MPH
Power Off Stall (with flaps): 35 MPH
Landing Ground Roll: 305 ft
Gross Weight: 1430 lb
Useful Load: 565 lb
Load Factors: + 4/- 2
Endurance (with reserves): 7,0 hrs
Range (with reserves): 650 Miles
An LSA kit plane.
Cruise: 105 mph
Stall: 36 mph
Range: 460 sm
Rate of climb: 1200 fpm
Takeoff dist: 125 ft
Landing dist: 500 ft
Engine: Rotax 912, 80 hp
HP range: 50-100
Fuel capacity: 20 USG
Empty weight: 575 lb
Gross weight: 1212 lb
Length: 18.6 ft
Wing span: 31 ft
Wing area: 162 sq.ft
Seats: 2
Cockpit width: 43 in
Landing gear: nosewheel
The Frontier side by side is a bush plane kit aircraft. The Frontier Kit is divided into three sub-kits. Each sub kit comes with everything needed to finish the job. Complete, step-by-step instructions with illustrations and photos are included with each kit. The complete airframe should be ready to cover in only a few days.
The fuselage kit includes a powder coated fuselage that is ready to attach parts to. The builder will install the rudder pedals, master cylinders and pulleys. When the fuel system and control cables are installed the fuselage will be ready be covered.
The standard fuselage kit sold for US$16,200 in 2009.
The wing kit includes everything needed to finish the wings, flaps, ailerons, fuel tanks, and fabric system. Every nut and washer, screw and component part is in the kit. Attaching pulleys, running cables and urethaning ribs is all that is necessary prior to covering.
The standard wing kit sold for US$8,800 in 2009.
The finishing kit includes everything that doesn’t come in the first two kits, minus paint, the instruments, and the FWF. It includes: the engine cowl, engine mount, windows, seats with standard upholstery, shoulder harnesses and seat belts, boot cowl assembly and firewall, instrument panel, landing gear system, tailwheel and tail spring, 8:00 x 6 tires and tubes, and wing struts.
The standard finishing kit sold for US$7,600 in 2009.
Sky Raider Frontier
Lycoming 290
Gross Weight 1320/1600 Ibs
VNE 130 mph
Wing span wlo wing tips 30 ft
Cruise 105 mph
Wing Area wi wing tips 107 sq. ft
Stall w/ Flaps 40 deg 38 mph
Length 22 ft 2 in
Stall clean 42 mph
Height 6 ft 8 in
Take off Roll 250 ft
Width Folded 7 ft 9 in
Climb Rate 820 fpm
Length Folded 22 ft 2 in
Empty weight 916 lbs
Gear Width 76 in
Useful load 682 lbs
Cabin Width 47 in
Load limit factors +6g – 4g
Fuel Capacity 26 USgal
Sky-MAXX gives higher cruise speeds with aircraft in the Light Sports Aircraft (LSA/SLA) or microlight/ultralight category. Of full aluminium construction, Sky-MAXX is a conventional, three axis, non-strut-braced monoplane. It’s high lift wing, incorporating electrical flaps, produces short take-off and landing (STOL) performance, whilst maintaining a 180 km/h cruise. The two seat Sky-MAXX was designed with an all-metal duralumin alloy structure.
Several editions (tropical, desert, photography) “Ready for fly” or as a kit. 2009 Price: US$ 95,000 / EUR 80,750
Engine: Rotax 80-102 hp, HIRTH, BMW, Jabiru 6-cylinder
Empty Weight: 270 kg / 595 lbs
MTOW Weight: 750 kg / 1653 lbs
Stall: 35 kt / 40 mph / 65 kmh
Cruise: 108 kt / 124 mph / 200 kmh
VNE: 139 kt / 160 mph / 258 kmh
Climb Rate: 1400 ft/min / 7 m/s
Take-off distance (50ft obstacle): 100 ft / 30 m
Landing distance (50ft obstacle): 100 ft / 30 m
LSA variations on the Carlson Aircraft Sparrow.
Sparrow Sport Special
Cruise: 85 mph
Stall: 31 mph
Range: 350 sm
Rate of climb: 1750 fpm
Takeoff dist: 85 ft
Landing dist: 175 ft
Engine: Rotax 503, 52 hp
HP range: 50-68
Fuel capacity: 10 USG
Empty weight: 400 lb
Gross weight: 775 lb
Length: 16.8 ft
Wing span: 26 ft
Wing area: 117 sq.ft
Seats: 1
Cockpit width: 24 in
Landing gear: tailwheel
Sparrow II XTC
Cruise: 110 mph
Stall: 39 mph
Range: 460 sm
Rate of climb: 1100 fpm
Takeoff dist: 250 ft
Landing dist: 350 ft
Engine: Rotax 912, 80 hp
HP range: 80-100
Fuel capacity: 24 USG
Empty weight: 630 lb
Gross weight: 1300 lb
Length: 18 ft
Wing span: 31.1 ft
Wing area: 140 sq.ft
Seats: 2
Landing gear: nose or tail
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
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
1946 aviation periodicals told of a “new twin-boom Skylark project” in three versions: two-place 246, four-place 446, and five–place 546. When the prototype appeared, it was as 447, with model number amended to fit the year.
The 1946 two-place Skycraft 246 featured wing ailerons and flaps. It is unknown if any were built in this designation, possibly was an evolutionary project, prised at $3,800-4,200.
No record of production found for the 1945 four-place Skycraft 445 and Skycraft 545. Partially-retracting gear to prevent structural damage in the event of a wheels-up landing, the 545 was noted in a brochure as slated for “Air Taxi service.”
The 1947 four-place Skycraft 446 and 447 featured all-metal construction, twin booms and tails; no ailerons, but wing spoilers served that purpose.
Partially-retracting gear to prevent structural damage in the event of a wheels-up landing. Priced at $5,800-7,500, one was built, NX25607 (registration also belonged to a North American NA-50A that went to Thailand).
Skycraft 246
Engine: 115hp Continental
Wingspan: 36’0″
Length: 26’3″
Useful load: 710 lb
Max speed: 139 mph
Cruise: 120 mph
Stall: 43 mph
Range: 445 ni
Ceiling: 12,500 ft
Seats: 2
Skycraft 445
Seats: 4
Skycraft 545
Seats: 4
Skycraft 446
Engine: 190hp Lycoming R-680
Wingspan: 36’0″
Length: 26’3″
Useful load: 1240 lb
Max speed: 162 mph
Cruise: 142 mph
Stall: 49 mph
Range: 715 mi
Ceiling: 16,000 ft
Seats: 4
Skycraft 447
Engine: 190hp Lycoming R-680
Wingspan: 36’0″
Length: 26’3″
Useful load: 1240 lb
Max speed: 162 mph
Cruise: 142 mph
Stall: 49 mph
Range: 715 mi
Ceiling: 16,000 ft
Seats: 4
All Aero 