1995-7: 2255 Orkla Dr., Golden Valley, MN 55427, USA.
Highlander Aircraft Corp offerd the Highlander two-seat monoplane in kit form, but originally designed in the U.K. by Richard Noble as the ARV Super2, then becoming Island Aircraft ARV-1 Super 2 and Aviation Scotland ARV-1 Super 2. Also certificated in Sweden as the ASL Hagfors Opus 280.
1997: Box 4, Drover, KS 66420, USA.
Offered the plans for Mitchell ul
An LSA legal kitplane.
Cruise: 100 mph
Stall: 45 mph
Range: 520 sm
Rate of climb: 1200 fpm
Takeoff dist: 400 ft
Landing dist: 250 ft
Engine: Rotax 912, 80 hp
HP range: 52-100
Fuel capacity: 18 USG
Empty weight: 638 lb
Gross weight: 1260 lb
Length: 20 ft
Wing span: 27.5 ft
Wing area: 137 sq.ft
Seats: 2 tandem
Cockpit width: 30 in
Landing gear: nose wheel
Receiving the “Best New Design” award at Oshkosh 1984 the Buccaneer was a conventional double-surface high-wing, three-axis control ultralight. Powered by a Rotax 277 single-cylinder, it came in three models — open framework, pod, and retractable amphibian. The landing gear was taildragger, or retractable/amphibian, using reinforced fiberglass hull & sponsons. Centre mounted joy stick, rudder pedals, tailwheel steerable through rudder pedals.
Later marketed by Keuthan Aviation as the Buccaneer SX and Buccaneer II, and by Arnet Pereyra Inc as the Aventura 1 HP/A and Aventura II A. A modified version, retrofitable to Buccaneers was marketed by Advanced Aeromarine as the Mallard. The Mallard was available as a conversion for existing Buccaneers or as a complete kit. First flown in 1993.
Although produced as an amphibious flying boat, the Buccaneer can be converted to a land plane by removing the boat hull and floats.
The Aero Adventure Aventura II Sport is a new model designed to minimize the expense and complexity of buying, building, and flying a two seat Aventura. With a strong 65 H.P. Rotax 582, the complete kit started at only $33,400. This is by far the most inexpensive two place amphibian on the market. Invest 250 hours of assembly time and this plane will be flying you and a friend anywhere.
The 100 H.P. 4-Stroke Rotax 912ULS with its 18 gallon fuel tank allows a solid 3 hours of flight with reserve. $44,900 for the complete kit.
The Aventura II XLR has a new engine cowling available, a new graphics package, an amazing new panel with AVMAP’s daylight readable GPS, a VSI, mode-C transponder, and more. Electric gear with indicator lights, differential hydraulic brakes, carpeting, headliner, 600-6 Soft Turf Tires, a 100 H.P. Rotax 912 ULS with an Air Box, a custom stainless steel exhaust, a warp drive 3-blade nickel edge prop and a spinner.
The Arnet Pereyra Buccaneer SX first flew in May 1986.
The Arnet Pereyra Buccaneer II first flew in March 1984.
The Arnet Pereyra Aventura UL and HP first flew in March 1995.
The Arnet Pereyra Aventura II first flew in June 1995.
Buccaneer (Land)
Empty wt: 228 lbs.
Empty weight (De Luxe) 250 lbs.
Wing span: 35 ft.
Wing area: 147 sq.ft.
Aspect ratio 8:1
Length: 17 ft 6 in
Fuel cap; 4.5 USG.
Construction: Aluminium, Dacron.
Engine: Rotax 277 (268cc) 28hp.
Max wt: 500 lbs.
Stall speed: 20 mph.
Max speed: 51 mph.
Vne: 75 mph.
Climb rate: 600 fpm @ 28 mph.
Design limit: +5, -3.5g.
Glide ratio: 8-1.
Wing loading: 3.4 lbs/sq.ft.
Power loading: 17.86 lbs/hp.
Pilot weight category 90-225 lbs all models.
Buccaneer (Amphibian)
Empty wt: 298 lbs.
Wing span: 35ft
Wing area: 147 sq.ft.
Length: 17 ft 6 in
Fuel cap; 4.5 USG
Construction: Aluminium, Dacron, Fibreglass
Engine: Rotax 277 (268cc) 28hp
Max wt: 550 lb
Stall speed: 23 mph
Max speed: 54 mph
Vne: 75 mph
Climb rate: 600 fpm @ 28 mph
Design limit: +5, -3.5g
Glide ratio: 8-1
Wing loading: 3.4 lbs/sq.ft
Power loading: 17.86 lbs/hp.
Buccaneer II
Empty wt.: 550 lbs
Max wt.: 1025 lbs
Wing span: 35ft 7in
Wing area: 171 sq.ft.
Wing loading: 5.99 lbs/sq.ft
Power loading: 15.77 lbs/hp
Engine: Rotax 532
Max speed: 78 mph
Cruise: 60 mph
Stall: 31 mph
Vne: 85 mph
Seats: 2
Arnet Pereyra Buccaneer II
Speed max: 90 mph.
Cruise: 70 mph.
Range: 150 sm.
Stall: 32 mph.
ROC: 500 fpm.
Take-off dist: 300 ft (400 ft water).
Landing dist: 300 ft.
Service ceiling: 13.500 ft.
Engine: Rotax 582, 65 hp.
HP range: 65-80.
Fuel cap: 12 USG.
Weight empty: 580 lbs.
Gross: 1200 lbs.
Height: 7 ft.
Length: 22.3 ft.
Wing span: 29.77 ft.
Wing area: 156 sq.ft.
Seats: 2.
Landing gear: retractable tail wheel.
Buccaneer XA/430
Empty wt.: 318 lbs
Max wt.: 600 lbs
Wing span: 33 ft 5in
Wing area: 162 sq.ft
Wing loading: 3.7 lbs/sq.ft
Power loading: 15 lbs/hp
Engine: Rotax 447
Max speed: 68 mph
Cruise: 60 mph
Stall: 25 mph
Vne: 75 mph
Advanced Aeromarine Mallard
Speed max: 100 mph.
Cruise: 80 mph.
Range: 320 sm.
Stall: 35 mph.
ROC: 750 fpm.
Take-off dist: 350 ft.
Landing dist: 400 ft.
Service ceiling: 14,000 ft.
Engine: Rotax 912, 80 hp.
HP range: 65-110.
Fuel cap: 18 USG.
Weight empty: 775 lbs.
Gross: 1250 lbs.
Height: 7 ft.
Length: 22.33 ft.
Wing span: 29.58 ft.
Wing area: 156 sq.ft.
Seats: 2.
Landing gear: retractable tail wheel.
Aventura I HP/A
Speed max: 90 mph.
Cruise: 75 mph.
Range: 170 sm.
Stall: 38 mph.
ROC: 1100 fpm.
Take-off dist: 150 ft.
Landing dist: 160 ft.
Service ceiling: 13,500 ft.
Engine: Rotax 582, 65 hp.
HP range: 52-65.
Fuel cap: 10 USG.
Weight empty: 375 lbs.
Gross: 850 lbs.
Height: 6 ft.
Length: 20.5 ft.
Wing span: 29.67 ft.
Wing area: 156 sq.ft.
Seats: 1.
Landing gear: retractable tail wheel.
Aero Adventure Aventura HP
Cruise: 75 mph.
Range: 240 sm.
Stall: 32 mph.
ROC: 1100 fpm.
Take-off dist: 150 ft.
Landing dist: 150 ft.
Engine: Rotax 503, 50 hp.
HP range: 50-80.
Fuel cap: 12 USG.
Weight empty: 390 lbs.
Gross: 750 lbs.
Length: 20.6 ft.
Wing span: 29.8 ft.
Wing area: 158 sq.ft.
Cockpit width: 24 in.
Seats: 1.
Landing gear: tail wheel/ retractable.
Arnet Pereyra Aventura HP
Speed max: 90 mph.
Cruise: 75 mph.
Range: 150 sm.
Stall: 32 mph.
ROC: 1100 fpm.
Take-off dist: 150 ft.
Landing dist: 150 ft.
Service ceiling: 13,500 ft.
Engine: Rotax 582, 65 hp.
HP range: 52-65.
Fuel cap: 12 USG.
Weight empty: 430 lbs.
Gross: 950 lbs.
Height: 6 ft.
Length: 20.5 ft.
Wing span: 29.7 ft.
Wing area: 156 sq.ft.
Seats: 1.
Landing gear: tail wheel.
Arnet Pereyra Aventura 1 HP/A
Top speed: 90 mph
Cruise: 75 mph
Stall: 38 mph
Range: 170 sm
Rate of climb: 1100 fpm
Takeoff dist: 150 ft
Landing dist: 160 ft
Service ceiling: 13,500 ft
Engine: Rotax 582, 65 hp
HP range: 52-65
Fuel capacity: 10 USG
Empty weight: 375 lb
Gross weight: 850 lb
Height: 6 ft
Length: 20.5 ft
Wing span: 29.7 ft
Wing area: 156 sq.ft
Seats: 1
Landing gear: tailwheel
Aventura 1 UL/L
Speed max: 65 mph.
Cruise: 55 mph.
Range: 100 sm.
Stall: 30 mph.
ROC: 800 fpm.
Take-off dist: 125 ft.
Landing dist: 125 ft.
Service ceiling: 13,500 ft.
Engine: Rotax 447, 40 hp.
HP range: 28-52.
Fuel cap: 5 USG.
Weight empty: 254 lbs.
Gross: 580 lbs.
Height: 6 ft.
Length: 20.5 ft.
Wing span: 27.62 ft.
Wing area: 143 sq.ft.
Seats: 1.
Landing gear: tail wheel.
Aero Adventure Aventura UL
Cruise: 55 mph.
Range: 120 sm.
Stall: 24 mph.
ROC: 500 fpm.
Take-off dist: 150 ft.
Landing dist: 150 ft.
Engine: Rotax 447, 48 hp.
Fuel cap: 5 USG.
Weight empty: 328 lbs.
Gross: 650 lbs.
Length: 20.5 ft.
Wing span: 21.6 ft.
Wing area: 156 sq.ft.
Cockpit width: 24 in.
Seats: 1.
Landing gear: tail wheel/ retractable.
Aero Adventure Aventura II
Stall: 31 kt / 36 mph / 58 kmh
Cruise: 65 kt / 75 mph / 121 kmh
VNE: 83 kt / 95 mph / 153 kmh
Empty Weight: 295 kg / 650 lb
MTOW Weight: 559 kg / 1232 lb
Climb Ratio: 1100 ft/min / 6 m/s
Take-off distance land (50ft obstacle): 150 ft / 46 m
Landing distance land (50ft obstacle): 150 ft / 46 m
Arnet Pereyra Aventura UL
Speed max: 63 mph.
Cruise: 55 mph.
Range: 100 sm.
Stall: 27 mph.
ROC: 500 fpm.
Take-off dist: 125 ft.
Landing dist: 125 ft.
Service ceiling: 13,500 ft.
Engine: Rotax 447, 40 hp.
HP range: 28-40.
Fuel cap: 6 USG.
Weight empty: 324 lbs.
Gross: 650 lbs.
Height: 6 ft.
Length: 20.5 ft.
Wing span: 27.7 ft.
Wing area: 156 sq.ft.
Seats: 1.
Landing gear: tail wheel.
Arnet Pereyra Aventura 1 UL/A
Top speed: 65 mph
Cruise: 55 mph
Stall: 30 mph
Range: 100 sm
Rate of climb: 800 fpm
Takeoff dist: 121 ft
Landing dist: 125 ft
Service ceiling: 13,500 ft
Engine: Rotax 447, 40 hp
HP range: 28-52
Fuel capacity: 5 USG
Empty weight: 254 lb
Gross weight: 580 lb
Height: 6 ft
Length: 20.5 ft
Wing span: 27.7 ft
Wing area: 143 sq.ft
Seats: 1
Landing gear: tailwheel
Aventura II A
Speed max: 90 mph.
Range: 200 sm.
Stall: 35 mph.
ROC: 900 fpm.
Take-off dist: 200 ft.
Landing dist: 200 ft.
Service ceiling: 13,500 ft.
Engine: Rotax 582, 65 hp.
HP range: 65-85.
Fuel cap: 12 USG.
Weight empty: 550 lbs.
Gross: 1100 lbs.
Height: 6 ft.
Length: 23.25 ft.
Wing span: 30.67 ft.
Wing area: 161.7 sq.ft.
Seats: 2.
Landing gear: retractable tail wheel.
Aero Adventure Aventura II
Cruise: 86 mph.
Range: 290 sm.
Stall: 30 mph.
ROC: 700 fpm.
Take-off dist: 250 ft.
Landing dist: 250 ft.
Engine: Rotax 912, 80 hp.
HP range: 65-130.
Fuel cap: 12 USG.
Weight empty: 850 lbs.
Gross: 1430 lbs.
Length: 23 ft.
Wing span: 30.7 ft.
Wing area: 161.7 sq.ft.
Cockpit width: 44 in.
Seats: 2.
Landing gear: tail wheel/ retractable.
Arnet Pereyra Aventura II
Speed max: 90 mph.
Cruise: 70 mph.
Range: 150 sm.
Stall: 32 mph.
ROC: 500 fpm.
Take-off dist: 300 ft.
Landing dist: 300 ft.
Service ceiling: 13,500 ft.
Engine: Rotax 582, 65 hp.
HP range: 65-80.
Fuel cap: 12 USG.
Weight empty: 640 lbs.
Gross: 1200 lbs.
Height: 7 ft.
Length: 23 ft.
Wing span: 30.7 ft.
Wing area: 161.7 sq.ft.
Seats: 2.
Landing gear: tail wheel.
Arnet Pereyra Aventura IIA
Top speed: 90 mph
Stall: 35 mph
Range: 200 sm
Rate of climb: 900 fpm
Takeoff dist: 200 ft
Landing dist: 200 ft
Service ceiling: 13,500 ft
Engine: Rotax 582, 65 hp
HP range: 65-85
Fuel capacity: 12 USG
Empty weight: 550 lb
Gross weight: 1100 lb
Height: 6 ft
Length: 23.3 ft
Wing span: 30.7 ft
Wing area: 161.7 sq.ft
Seats: 2
Landing gear: tailwheel
Keuthan Buccaneer SX
Speed max: 90 mph.
Cruise: 65 mph.
Range: 100 sm.
Stall: 29 mph.
ROC: 650 fpm.
Take-off dist: 175 ft (350 ft water).
Landing dist: 100 ft.
Service ceiling: 12,000 ft.
Engine: Rotax 447, 52 hp.
HP range: 52-65.
Fuel cap: 5 USG.
Weight empty: 303 lbs.
Gross: 810 lbs.
Height: 6 ft.
Length: 20.16 ft.
Wing span: 29.77 ft.
Wing area: 143 sq.ft.
Seats: 1.
Landing gear: retractable tail wheel.
Arnet Pereyra Buccaneer SX
Speed max: 90 mph.
Cruise: 70 mph.
Range: 150 sm.
Stall: 29 mph.
ROC: 600 fpm.
Take-off dist: 200 ft (350 ft water).
Landing dist: 200 ft.
Service ceiling: 11,000 ft.
Engine: Rotax 503, 52 hp.
HP range: 52-65.
Fuel cap: 12 USG.
Weight empty: 450 lbs.
Gross: 810 lbs.
Height: 6 ft.
Length: 20.16 ft.
Wing span: 29.77 ft.
Wing area: 143 sq.ft.
Seats: 1.
Landing gear: retractable tail wheel.
Keuthan Buccaneer II
Speed max: 90 mph.
Cruise: 75 mph.
Range: 2250 sm.
Stall: 33 mph.
ROC: 650 fpm.
Take-off dist: 275 ft (400 ft water).
Landing dist: 150 ft.
Service ceiling: 14,000 ft.
Engine: Rotax 582DCDI, 65 hp.
HP range: 65-80.
Fuel cap: 12 USG.
Weight empty: 580 lbs.
Gross: 1140 lbs.
Height: 7 ft.
Length: 22.33 ft.
Wing span: 29.67 ft.
Wing area: 156 sq.ft.
Seats: 2.
Landing gear: retractable tail wheel.
1984: 110 Mingo Trail, Dept. GR, Longwood, FL 32750, USA.
LSA builder
In 1942 an Aircraft Division was formed in Higgins Industries Inc, owned by Andrew Higgins, with the object of manufacturing transport aircraft for the United States Air Force.
There was also a Helicopter Division concerned with building and perfecting a helicopter designed by Enea Bossi.
This small two-seater helicopter had a main four-bladed rotor, consisting of two two-bladed rotors a few inches apart, and a small two-bladed tail rotor. The latter was fixed to the end of the upward-rising tail so that the tail rotor hub was at approximately the same level as the main rotor.
The two-place, side-by-side cabin interior was designed to resemble as closely as possible that of a lightweight aircraft with a wheel control column and a standard panel of flying instruments.
The fuselage is entirely covered, has a forward section with metallic skin, while the tail is covered with fabric.
There is a small, two-bladed, vertical tail rotor and a fixed tricycle landing gear. The pitch-control and clutch-control levers look much like the gearshift on a car. The rudder pedals resemble brake and clutch pedals of an automobile.
EB-1
Engine: 1 x Warner, 190hp
Rotor diameter: 9.75m
Weight fully loaded: 1155kg
Empty weight: 885kg
Cruising speed: 200km/h
Seats: 2
In 1942 an Aircraft Division was formed in Higgins Industries Inc, owned by Andrew Higgins, with the object of manufacturing transport aircraft for the United States Air Force.
There was also a Helicopter Division concerned with building and perfecting a helicopter designed by Enea Bossi.
The 1909 Hieronymus Type I was designed and built by Hieronymus in Austria/Hungary.
Span: 39’4″
In 1914 Otto Hieronimus manufactured the six-cylinder Hiero E, also known as the Hiero 6 engine which was derived from earlier 4-cylinder engines. The Hiero engine like the Austro-Daimler powered many of Austria’s World War I aircraft. Hiero aircraft engines were designed by Otto Hieronimus, a famous Austrian auto racer of the early 1900s. His initial designs were liquid-cooled inline engines built by the Laurin & Klement Automobile Works of Austria.
The Hiero E had a 135 mm x 180 mm bore/stroke (15.46L / 943.4cuin) and delivered 200-230 hp. The engine had the typical features of an inline vertical 6-cylinder: aluminum bed, cast iron cylinders, one inlet and one exhaust valve per cylinder controlled by bars and rockers, with the cam-shaft in the bed, and dual ignition by two Bosch magnetos. During World War I, the highly regarded Hiero engines were built under license by Essler, Warschalowski & Company of Vienna and the Breitfeld-Daněk company of Czechoslovakia. A point of recognition of Hiero engines compared with other Central Powers OHC inline’s is that the intake was on the right and the exhaust on the left. After World War I, production was continued by the Avia company and powered a number of their early aircraft.
Variants:
Hiero 145hp: 145 hp (108.1 kW) (probably designated Hiero B or Hiero C )
Hiero 185hp: 185 hp (138.0 kW) (probably designated Hiero D)
Hiero E: 200 hp (149.1 kW) – 230 hp (171.5 kW)
Applications:
Aero A.14
Letov Š-1
Phönix C.I
Phönix D.I
Ufag C.I
Lloyd C.II
Specifications:
Hiero E
Type: 6-cyl in-line Water-cooled
Bore: 135 mm (5.31in)
Stroke: 180 mm (7.09in)
Displacement: 15,459 cc (943cu in)
Designer: Otto Hieronimus
Valvetrain: overhead-cam
Cooling system: water
Power output: 200 – 230 hp (149 – 172 hp)
When developing the Mitsubishi J8M1 (Me-163 copy) the Japanese were unfamiliar with the handling characteristics of aircraft lacking a conventional horizontal tail. To provide a means of expediting the training of pilots eventually to be assigned to the rocket-driven fighter, the Scientific Division of the Navy Air Technical Arsenal at Yokosuka had been assigned the task of creating a full-scale wooden glider version of the Shusui. While definitive design work and prototype construction proceeded at Nagoya, Hidemasa Kimura who had been responsible for the Tachikawa-built A-2600 that had created a new international closed-circuit distance record developed the glider which was known as the MXY8 Akikusa (Autumn Grass). This was flown for the first time at the Hyakurigahara airfield, the base of the 312th Naval Air Group which, it had been decided, would be the first recipient of the Shusui. This event took place on 8 December, its pilot being Lt Cdr Toyohiko Inuzuka who had taken the place of Lt Cdr One as the project test pilot after the latter had been taken ill. The Akikusa glider was towed into the air by a Kyushu K10W1 and its handling characteris¬tics received a highly favourable report from Jnuzuka. The second Akikusa was sent to the Army Aerotechnical Research Institute, the Rikugun Kokugijutsu Kenkyujo, at Tachikawa where it was tested by Col Aramaki with similarly successful results.
On 1 December, the completed structural test specimen was inspected and approved by both services, but a week later, on 7 December, the Tokai district, in which Nagoya was situated, was wracked by strong earth tremors and the airframe, which was undergoing loading tests, was overstressed and suffered distortion, On 18 December, the Ohe plant in which the “heavy gliders” were being built suffered a heavy attack from B-29 Superfortresses and it was decided to transfer the salvaged airframes, together with the structural test specimen, to a plant that had been created in a mountain cave at Taura, Yokosuka, although the Ohe plant continued, together with the Nanko plant, to build a number of pre-series Shusui interceptors. Despite these setbacks, the first “heavy glider” Shusui was test flown by Lt Cdr Inuzuka at Hyakürigahara airfield on 8 January 1945, after being towed into the air by a Nakajima B6N1 Tenzan attack bomber.
For the initial flight, the engineless Shusui weighed 2,286 lb (1037 kg) and the Cl was situated at 16.8 per cent of the aerodynamic mean chord, Inuzuka confirming that there was no difference between the handling characteristics of this “heavy glider” and the Akikusa apart from a minor change of trim at take-off. During subsequent flights, some devon vibration was experienced at gliding speeds in excess of 184 mph (296 km/h) but this was eradicated when the gap between the wing and elevon was reduced and the Frise balance near the devon tip shortened. Various problems were encountered in the oil pressure system, but these were quickly resolved and in March all Navy flight testing of the “heavy glider” was to be pronounced satisfactorily completed. The second “heavy glider” was tested by the Navy at the Kashiwa airfield, Chiba, and this was eventually to be tested also by the Army. These tests were not to commence until August, and at an early stage in the trials, the Shusui parted company with its towplane prematurely and crashed in a pine forest, its pilot suffering injuries.
