1980->

American Sport Copter UltraSport 254 / Light’s American Sportscopter UltraSport 254

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American Sportscopter (ASI) was formed in 1990 to produce an ultralight helicopter to FAR Part 103, which was designated Ultrasport 254. Design objective of 254 was basic weight not to exceed 115kg (254 lb) in order to comply with FAR Pt 103.
First flown on 24 July 1993 and publicly displayed at Oshkosh that year, it is a single-seater with a semi-enclosed composite fuselage structure, skid undercarriage and a tubular tailboom with tailplane and twin fins and a tail rotor enclosed in a large circular shroud. Two prototypes were built and tested.
The two-blade composites construction main rotor has tip weights for momentum conservation in the event of an engine failure, an 8 deg linear twist and infinite life. The tail rotor drive is carried in a narrow streamlined tailboom. A centrifugal sprag clutch for starting engages rotors at 2,000 engine rpm and automatically disengages in the event of engine failure.
Fitted with a 5 US gallon tank, and the 8 foot wide landing gear stressed for landings at up to 2.5g, and has optional floats (weight 18kg). A quick build kit requires 80 hours to assembly. An overhead control stick operates with same movements as joysticks. A floor-mounted cyclic option has available since 1998.
It is powered by a 55hp Hirth 2703 engine mounted behind the cockpit rear bulkhead. In 2003 the engine used was the 41.0kW Hirth 27G3 dual-carburettor two-stroke engine with pull starter and 12:1 planetary transmission. Normal fuel capacity 19 litres.
The Ultrasport 254 was available in 2003 for US$34,900.

Engine: 55 hp Hirth 2703 522cc.
Transmission: 12:1 planetary.
Speed max: 63 mph.
Cruise: 63 mph.
Range: 70 sm.
ROC: 1000 fpm.
Rotor blades: Composite 21’, 6.7” chord, metal tail rotor 40”.
Fuel cap: 5 USG.
Weight empty: 252 lbs.
Gross: 525 lbs.
Height: 7.5 ft.
Length: 16.67 ft.
Seats: 1.
Landing gear: skids.

Engines: 55hp Hirth 2703, 65hp Hirth 2706 is optional. Dual carb,Dual CDI.
Transmission 12:1 Planetary
Rotor Blades: Composite 21′ diameter, 7″ chord
Composite tail rotor 30′ diameter.
Cruise 63 mph
Top Speed 63 mph
Empty Weight 252 lbs
Useful Load 273 lbs
Gross Weight 525 lbs
Width 8′
Height 7’10”
Length 19’2″

Ultrasport 254
Main rotor diameter: 6.4m
Tail rotor diameter: 0.76m
Length with rotor blades folded: 5.84m
Height: 2.39m
Take-off weight: 238kg
Empty weight: 114kg
Max level speed: 101km/h
Max rate of climb: 305m/min
Hovering ceiling, IGE: 3290m
Hovering ceiling, OGE: 2135m
Range with normal fuel at 100km/h: 120km

Sadler Vampire / Sadler A-22 Piranha / Wedgetail Vampire

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Single seat single engined mid wing mono¬plane with conventional three axis. Wing has unswept leading and trailing edges, and constant chord; two fin tail. Pitch control by elevator on tail; yaw control by fin mounted rudders; roll control by full span spoilers; control inputs through stick for pitch/roll, pedals for yaw. Cantilever wing; wing profile NACA 633 218A; double surface. Undercarriage has three wheels in tricycle formation; with tailskid; no suspension on any wheels. Push right go right nosewheel steering connected to yaw control. Brakes on main wheels. Aluminium steel tube framework, partially enclosed. Engine mounted at wing height driving pusher propeller. 6061 T6 aluminium tubes, 2024 alclad skin and glass flibre pod.
The prototype of the Sadler Vampire was unveiled at Oshkosh in August 1982, where it was announced as likely to be on sale during 1983.

The price with a 20 hp engine was $7950 in 1983.

The quiet operation of the prototype was mainly due to the use of a reconnaissance and target drone engine of Israeli manufacture. The aircraft’s use of an aluminium riveted skin for the tail surfaces and the wing with ribs of pressed aluminium may not be unusual in general aviation but is very rare in the ultralight world. The profile of the wing is NACA 633 218A and is laminar. Beneath the spoilers, running the full span of the wings at the trailing edge, are four position hinged flaps.
American Microflight intend only to sell their Sadler Vampire ready to fly.
Option of KFM 107 engine.
In 1983 Ultra Light Aircraft Corporation (ULAC) was setting up a production facility for the American Microf¬light Sadler Vampire, for which ULAC has acquired the Europe/Africa licence.

Bill Sadler had his Sadler Vampire at the 2008 U.S. Sport Aviation Exposition. Sadler announced the introduction of the plane into the lightsport aircraft category at Airventure 2007, at that time it was planned that the craft would be powered by the 100 HP Rotax 912 S.

Sadler Aircraft Corp, previously known as American Microlight Inc, developed A-22 Piranha lightly armed surveillance version of its microlight, also being developed by TUSAS. Tusas Aerospace Industries Inc in Turkey developed the TG-X1 Bat very light single-seat attack / surveillance aircraft (first flown February 1997, based on U.S. Sadler A-22 Piranha).

The Vampire was available and fully built at Wedgetail Aircraft factory at Camden in NSW, Australia, circa 2019.

Engine: NGL WAE 34, 26 hp
Poly V belt reduction, ratio 2.0/1
Power per unit area 0.20 hp/sq.ft, 2.35 hp/sq.m
Fuel capac¬ity 5.0 US gal, 4.2 Imp gal, 18.9 litre in main tank
Length overall 18.1 ft, 5.51 m
Height overall 4.8ft, 1.42m
Wing span 30.1 ft, 9.40m
Constant chord 5.0ft, 1.52m
Sweepback 0 degs
Total wing area 128sq.ft, 11.9sq.m
Wing aspect ratio 7.4/1
Nosewheel diameter overall 10 inch, 256mm
Main wheels diameter overall 10 inch, 250mm
Empty weight 220 lb, 100kg
Max take off weight 450 lb, 204kg
Payload 230 lb, 104kg
Max wing loading 3.5 lb/sq.ft, 17.1 kg/sq.m
Max power loading 17.3 lb/hp, 7.8 kg/hp
Max level speed 85mph, 137kph
Max cruising speed 55 mph, 88 kph
Stalling speed 25 mph, 40kph
Take off distance 300 ft, 91 m
Landing distance 200 ft, 61 m

Engine: Solo 210 (210 cc) 20 hp
Static thrust: 130 lb
Empty wt: 250 lb
Wing span: 30 ft
Wing area: 125 sq.ft
Height: 4 ft 8 in
Length: 17 ft 6 in
Fuel cap; 4.5 USG
Construction: Aluminium, Fibreglass
Max wt: 500 lb
Stall: 25 mph
Max speed: 63 mph
Vne: 85 mph
Climb rate: 350 fpm @ 45 mph
Design limit: +6, -6g
Glide ratio: 12-1
Wing loading: 4 lbs/sq.ft
Power loading: 25 lbs/hp

American Jet Hustler

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Unveiled at American Jet Industries plant in Van Nuys, California, in October, 1975, the seven place Hustler 400 turboprop/ turbojet has been modified since announcement was made. A major change was the redesign of the tail to a “T” tail configuration, and other changes include an increase of 52 inches in the wing span and installation of double slotted Fowler flaps on the supercritical wing. Sixteen inches have also been added to the fuselage.
An 850 shp United Aircraft of Canada turboprop PT6A 41 in the nose provides power for the Hustler while the Teledyne turbojet engine will be used for standby’ power in the event of an engine failure. According to American Jet’s data the standby engine will enable the aircraft to maintain an airspeed of 170 mph at 13,500 feet with the nose turboprop engine feathered. A top speed of 380 mph for the Hustler is predicted with a maximum range of 2970 miles.
Three prototypes were under construction at the American Jet California facility; two were to be used for flight testing and the third for ground structural testing. The Hustler faces some serious hurdles; for instance, no certificated jet engine of the size required by the design existed. Only various engines used for APUs, missiles or drones. If, on the other hand, a “single engine” classification were sought, the jet engine being viewed merely as a JATO unit, then the Hustler would face the challenge of making the FAA’s 70 mph landing speed requirement with a wing loading of at least 36 pounds per square foot.
The Hustler was powered by a Pratt & Whitney PT6A-41 turboprop in the nose and a standby turbojet in the tail and made its first flight on January 12, 1978.
Gulfstream American decided to replace the 850 shaft horsepower Pratt & Whitney PT6 turboprop engine in the nose of the Hustler with a 900 shp Garrett TPE331. The Pratt & Whitney JT15D remains Gulfstream’s choice for the Hustler’s rear mounted turbofan. Maximum takeoff weight was been increased to 10,000 from 9,500.
Flight testing of the Gulfstream American Hustler 500 began late in January 1981 at Van Nuys, California, and continued at Mojave. This second Hustler prototype was powered by a 900 shp Garrett AiResearch TPE 331 10 501 turboprop in the nose and a 2,200 lb st (1000 kgp) Pratt & Whitney JT15D 1 turbofan in the tail.

Hustler 400 A
Engine: Pratt&Whitney PT6A-41, 838 shp & Teledyne turbojet
Length: 37.795 ft / 11.52 m
Height: 10.761 ft / 3.28 m
Wing span: 32.644 ft / 9.95 m
Wing area: 185.141 sq.ft / 17.2 sq.m
Max take off weight: 7497.0 lb / 3400.0 kg
Weight empty: 3999.9 lb / 1814.0 kg
Cruising speed: 343 kts / 636 kph
Wing load: 40.59 lb/sq.ft / 198.0 kg/sq.m
Range: 1303 nm / 2414 km
Crew: 1
Payload: 6 Pax

Hustler 500
Engine: 1 x Garrett AiResearch TPE 331 10 501, 900 shp turboprop & 1 x Pratt & Whitney JT15D 1 turbofan 2,200 lb st (1000 kgp)

American Homebuilts John Doe

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A STOL utility aircraft (LSA) with interchangeable flaps and ailerons, as well as elevators and rudder, and an 18 cu.ft cargo area. First fown in 1994.

The man who designed this airplane was named Steve Nussbaum, he flew out of the airport I worked at, Galt airport 10C. I remember on a good day he could get one of these off the ground in 88 ft. He also designed the ribs to be replaceable in the field if they ever broke during a forced landing.
Ted Domski

Engine: Continental IO-240, 125 hp
Wing span: 30.6 ft
Wing area: 130.6 sq.ft
Fuel capacity: 26 USG
Empty weight: 850 lb
Gross weight: 1400 lb
Height: 6.5 ft
Length: 20.8 ft
Top speed: 140 mph
Cruise: 117 mph
Stall: 30 mph
Range: 500 sm
Takeoff dist: 100 ft
Landing dist: 125 ft
Service ceiling: 12,500 ft
Seats: 2 tandem
Landing gear: tailwheel

Cruise: 100 mph
Stall: 30 mph
Range: 490 sm
Rate of climb: 1000 fpm
Takeoff dist: 120 ft
Landing dist: 120 ft
Engine: Continental O-200, 100 hp
HP range: 100-125
Fuel capacity: 26 USG
Empty weight: 771 lb
Gross weight: 1320 lb
Length: 21.9 ft
Wing span: 30.6 ft
Wing area: 130.5 sq.ft
Seats: 2 tandem
Cockpit width: 28 in
Landing gear: tailwheel

American Blimp A60+

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The U.K.’s Defense Evaluation and Research Agency (DERA) cornpleted field trials in Kosovo of a prototype of an ultrawideband synthetic aperture radar being developed to detect mines and unexploded ordnance.
The project was run by Mineseeker, a joint venture between DERA and The Lightship Group, a company owned by Virgin Atlantic chief Richard Branson. Mineseeker aims to employ airships as mobile sensor platforms to detect and delineate mined areas and unexploded cluster bombs and other ordnance. In addition to serving as a realistic test bed for DERNs ultrawideband radar, the airship was also fitted with electro-optic sensors. The Kosovo deployment provided valuable imagery and data for the U.N.’s Mine Action Coordination Center (MACC) which is conducting mine clearance operations in the country.
Feasibility flight trials of the radar mounted on a helium-filled, nonrigid airship were conducted by DERA in January in the U.K. The same 40-meter-long A60+ airship, built by the American Blimp Corp., was used in Kosovo. Data generated from the ultrawideband radar deployment in Kosovo is being studied by DERA officials in the U.K. The sensor is intended to locate and differentiate metal and plastic mines.
The deployment began with the manned airship starting operations four days later, operating from bases in Kosovo and Italy. Over a period of six weeks, the Mineseeker team surveyed 30 sites in Kosovo, locating, identifying and mapping recorded minefields, as well as searching for unexploded ordnance from cluster bomb strikes.

American Blimp Corporation A-60+

Ameri-Can Ultralights Euraka

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Of pre-manufactured sub-assemblies, with wings, tail empennage and fuselage all pre-built, ready for bolt-on, the kit arrives pre-fabricated and pre-painted white. The wings are built around a single deep spar. There are 26 foam ribs in each 12 foot long wing. When this assembly has been built, it is covered in full-span panels of pre-painted (white) aluminum skins, durable and UV-resistant. The resultant wing weighs less than 35 pounds. It is attached to the fuselage with just a few bolts, and in about 5 minutes. This airplane can be easily assembled in the field, and allows for trailer transport.
The purchaser assembles pre-built components with the supplied aircraft-grade bolts and nuts. This means that wrenches are the only tools required to assemble this aircraft kit.
It was designed to fly with a Hirth F-33 25hp engine, with electric start, or alternately, the Zenoah GB25 22hp engine with pull start can be used. Higher horsepower engines are not recommended.
First flown in August 1997, by July 2003 the Eureka had been withdrawn from the market due to lack of resources.

Engine: Hirth F33, 25hp
HP Range: 22-26
Wing Span: 26 ft
Wing Area: 104 sq.ft.
Height: 5.0 ft
Length: 14.5 ft
Empty Weight: 230 lb
Gross Weight: 460 lb
Fuel Capacity: 5 USG
Top Speed: 63 mph
Cruise: 55 mph
Endurance: 1.5 hours
Stall: 27 mph
Rate of Climb: 500 fpm
Takeoff Distance: 300 ft
Landing Distance: 250 ft
Service Ceiling: 10,000 ft
Seats: 1
Landing Gear: Tailwheel
Bldg. Materials: Aluminum, Foam
Airframe Cost: $5000 (2009)

Engine: Zenoah G25B, 22hp
HP Range: 22-26
Wing Span: 26 ft
Wing Area: 104 sq.ft.
Height: 5.0 ft
Length: 14.5 ft
Empty Weight: 238 lb
Gross Weight: 460 lb
Fuel Capacity: 5 USG
Top Speed: 63 mph
Cruise: 55 mph
Endurance: 1.6 hours
Stall: 27 mph
Rate of Climb: 450 fpm
Takeoff Distance: 350 ft
Landing Distance: 250 ft
Service Ceiling: 10,000 ft
Seats: 1
Landing Gear: Tailwheel
Bldg. Materials: Aluminum, Foam
Airframe Cost: $5000 (2009)

Engine: Cuyuna, 22 hp
HP range: 22-25
Wing span: 26 ft
Wing area: 104 sq.ft
Length: 14.5 ft
Height: 5 ft
MTOW: 460 lb
Empty wt: 250 lb
Fuel cap: 5 USG
Top speed: 63 mph
Cruise: 60 mph
Stall: 27 mph
Range: 150 sm
ROC: 350 fpm
TO dist: 400 ft
Ldg dist: 250 ft
Service ceiling: 7000 ft
Seats: 1
Undercarriage: tailwheel
Take-off distance (50ft obstacle): 300 ft / 91 m
Landing distance (50ft obstacle): 250 ft / 76 m