1995: PO Box 249, Southern Pines, NC 28388, USA.
UL builder
1980->
Phantom Airplane Corp
1997: 6154 West G Ave, Kalamazoo, MI 49009, USA.
UL builder
Phantom Aircraft Firecracker
Single seat single engined high wing monoplane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform 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 below by struts; wing profile; double surface. Undercarriage has three wheels in tricycle formation; suspension on all wheels. Push right go right nose-wheel steering connected to yaw control. Aluminium tube/steel tube framework, with optional pod. Engine mounted at wing height driving tractor propeller.
Phantom Aircraft Firecracker Article
This prototype was undergoing an intensive test flying programme in 1983.
Engine: Zenoah G25B, 22 hp at 6500 rpm
Power per unit area 0.14 hp/sq.ft, 1.6hp/sq.m
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre
Length overall 17.0 ft, 5.18 m
Height overall 7.0ft, 2.13m
Wing span 32.0ft, 9.75m
Constant chord 4.8 ft, 1.43 m
Sweepback 0 deg
Total wing area 150 sq.ft, 13.9 sq.m
Wing aspect ratio 6.8/1
Empty weight 216 lb, 98kg
Max take off weight 450 lb, 204kg
Payload 234 lb, 106kg
Max wing loading 3.0 lb/sq.ft, 14.6kg/sq.m
Max power loading 20.5 lb/hp, 9.3kg/hp
Load factors; +4.5, 3.0 ultimate
Max level speed 65 mph, 105 kph
Max cruising speed 55 mph, 88 kph
Stalling speed 25 mph, 40 kph
Max climb rate at sea level 600 ft/min, 3.0 m/s
Min sink rate 290 ft/min, 1. 5 m/s
Best glide ratio with power off 10/1
Take off distance 100ft, 30m
Landing distance 125ft, 38m
Service ceiling 10,000ft, 3050m
Range at average cruising speed 165 mile, 265 km
Phantom Aircraft
1983: Phantom Aircraft Inc, 1450 NE 39th Street. Ocala, Florida 32671, USA.
UL builder
Phalanx Organization Inc
USA
Founded to develop MP-18 Dragon small-size and turbofan- powered combat aircraft of very unusual and futuristic design, capable of VTOL flight using vectoring nozzles. Prototype was under construction in mid-1980s, but no flight is known.
PGO Aviation AJS 2000 Cobra
The 1983 PGO Aviation AJS 2000 is a two-seater tandem multiaxis ultralight. It was fitted with dual controls, hydraulic disc brake, and Fournalès shock absorbers.
Engine: Rotax 532, 65 hp
Wingspan: 10.60 m
Wing area: 16 sq.m
Fuel capacity: 40 lt
VNE: 145 km / h
Cruise: 110 km / h
VSo: 55km / h
Fuel consumption: 13 lt/hr
PGK PGK-1 Hirondelle
The PGK-1 Hirondelle was designed by Jean Peters, Glenn Gibb and John Kopala. The prototype aircraft C-GWYL (pictured) was six years in development and the designers main objectives were: to design a two-place aircraft that was safe and easy to fly; fast and maneuverable; comfortable and attractive; and easy and economical to build. The aircraft is well suited to first time builders. Engines of 100-125 hp.
Western Aircraft Supplies of Canada markets plans and some components to construct the PGK-1 Hirondelle two-seat monoplane.
Gross Wt. 1475 lb
Empty Wt. 933 lb
Fuel capacity approx. 28 USG
Wingspan 26’
Length 20’7”
Wing area: 117 sq.ft
Engine Lycoming O-235-CI8
Top speed 150 mph
Cruise 145 mph
Stall 61 mph
Climb rate 900 fpm
Takeoff run 750 ft
Ceiling 12,600 ft
Seats: 2
Petit Breezy
The Breezy is a high-wing monoplane with a standard tail. The Breezy takes 30 hp and has a tricycle type undercarriage. Sold as plans only.
Wingspan 30 ft
Wing area 150 sq.ft
Chord 5 ft
Aspect ratio 6:1
Length 15 ft
Empty weight 246 lbs
Pilot max weight 230 lbs
Cruise speed 38-40 mph
Stall speed 26 mph
Vmax 50 mph
Takeoff roll 175 ft
Climb rate 400 fpm
Petit
1984: 2450 N. 56th St., Mesa, AZ 85205, USA.
Sold plans for the Petit Breezy LSA
Peterson 260SE/STOL
In the early 1980s Todd Peterson, having built numerous Cessna 182-based Wren 460s, decided to certify a new aircraft to replace the Wren. The new improved machine is known as the 260SE/Stol and came on stream during 1988.
This model retains the high lift canard wing and is powered by the TCM IO-470F engine. Special attention has been given to reducing drag from the undercarriage, forward fuselage, cowl and engine baffles and the canard. The canard wing consists of a fixed horizontal stabiliser and a movable elevator, just like a conventional tailplane, but mounted on the side of the engine cowling just behind the propel¬ler. It is push rod actuated and works in conjunction with the normal tail elevator but in the opposite sense. As the rear elevator moves up to raise the aircraft nose, the canard elevator moves down. The end result is a marked handling improvement especially in the low speed range and short field performance.
Base price: US$80,000 (conversion only); US$200,000 (conversion and aircraft)
Engine: TCM IO-470-F, 260 hp@2700@SL
TBO: 1500 hr
Fuel type: 100LL
Propeller: McCauley CS
Landing gear type: Tri/Fixed
Max ramp weight: 2950 lb
Gross weight: 2950 lb
Landing weight: 2950 lb
Empty weight, std: 1800 lb
Useful load, std: 1150 lb
Payload, full std. fuel: 622 lb
Usable fuel, std: 88 USG
Oil capacity: 12 qts
Wingspan: 36 ft. 0 in
Overall length: 28 ft. 1.5 in
Height: 9 ft. 2 in
Wing area: 174 sq. ft
Wing loading: 16.9 lbs./sq. ft
Power loading: 10.6 lbs./hp
Wheel base: 9 ft. 1 in
Wheel track: 9 ft. 1 in
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 2
Cabin width: 42 in
Cabin height: 48.5 in
Baggage capacity: 200 lb
Max level speed: 153 kt
Cruise speed 75% power @ 6,500 ft: 150 kt
Cruise speed 65% power @ 6,500 ft: 145 kt
Cruise speed 55% power @ 6,500 ft: 138 kt
Max range (w/ reserve) 75% power: 849 nm
Max range (w/ reserve) 65% power: 918 nm
Max range (w/ reserve) 55% power: 1018 nm
Fuel consumption 75% power: 13.2 USgph
Fuel consumption 65% power: 12.0 USgph
Fuel consumption 55% power: 10.5 USgph
Stall speed (flaps up): 42 kt IAS
Stall speed (flaps down): 35 kt IAS
Best rate of climb (fpm): 1380
Service ceiling: 19,500 ft
Takeoff ground roll: 390 ft
Takeoff over 50-ft. obstacle: 705 ft
Landing ground roll: 390 ft
Landing over 50-ft. obstacle: 600 ft
All Aero 