Designed by John Dempsey, the Phantom is a 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 full 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 tricycle formation with tailskid; bungee suspension on all wheels. Push right go right nosewheel steering connected to yaw control. Optional brakes on main wheels. Aluminium tube framework, with pod. Engine mounted above wing driving tractor propeller.

Conceived under the direction of John Dempsey, the Phantom copied in 1982 the exploits of the Mirage in the previous year at Sun ‘n’ Fun where it carried off the prize for the most outstanding aircraft.

The Phantom is capable of a rate of roll, going from 45 degrees bank to 45 degrees bank the other way in 1.5 s. The wing has been tested as far as + 9.9 and 6.6 g ultimate with the aircraft at a gross of 420 lb (190kg) which would give a flight envelope of +6.6 and 4.4g. These tests were done with 3/32 inch (2.4 mm) cables which on the production aircraft have been increased to 1/8 inch (3.2 mm).

Ultralight Flight Phantom Article

The aircraft is delivered as a kit requiring 35 h for finishing at a price of $5995 in 1983. Options include principally, floats, wheel fairings, an instrument panel and, as with the Mirage MkII, the Cuyuna 430RL engine, since the Phantom is fitted with the Kawasaki TA440A as standard in the United States.

For Europe, the Skyriders company in Britain fits a Robin engine and a larger fuel tank and, since the aircraft thus modified has different performance characteristics etc.

Later marketed as the Phantom Sport Airplane Corp Phantom X1 and X2. The X2 being a two seat adaptation of the X1.

Gallery

Phantom
Engine: Kawasaki TA440A, 38.5hp at 6000rpm
Propeller diameter and pitch 58×27 inch, 1.47×0.69m
V belt reduction, ratio 2.4/1
Max static thrust 210 lb, 95 kg
Power per unit area 0.27 hp/sq.ft, 2.9 hp/sq.m
Fuel capacity 3.7 US gal, 3.1 Imp gal, 14.0 litre
Length overall 16.5 ft, 5.02 m
Height overall 8.8ft, 2.69m
Wing span 28.5ft, 8.68m
Constant chord 5.0 ft, 1.52m
Dihedral 2 deg
Sweepback 0 deg
Tailplane span 7.9 ft, 2.40 m
Fin height 5.0ft, 1.52m
Total wing area 142 sq.ft, 13.2 sq.m
Total aileron area 19.8 sq.ft, 1.84 sq.m
Fin area 5.8 sq.ft, 0.54 sq.m
Rudder area 8.6 sq.ft, 0.80 sq.m
Tailplane area 11.8 sq.ft, 1.10 sq.m
Total elevator area 9.8 sq.ft, 0.91 sq.m
Wing aspect ratio 5.7/1
Wheel track 3.4 ft, 1.05m
Wheelbase 3.7ft, 1.14m
Nosewheel diameter overall 10 inch, 25 cm
Main wheels diameter overall 10 inch, 25 cm
Empty weight 250 lb, 113kg
Max take off weight 510 lb, 231kg
Payload 260 lb, 118kg
Max wing loading 3.59 lb/sq.ft, 17.5 kg/sq.m
Max power loading 13.8 lb/hp, 6.0kg/hp
Load factors +6.6, 4.4 design; >+9.9, > 6.6 ultimate
Max level speed 61 mph, 98 kph
Never exceed speed 100 mph, 161 kph
Max cruising speed 50 mph, 80 kph
Economic cruising speed 40 mph, 64 kph
Stalling speed 26 mph, 42 kph
Max climb rate at sea level 800 ft/min, 4.1 m/s
Min sink rate 490 ft/min at 35 mph, 2.5 m/s at 56 kph
Best glide ratio with power off 7/1 at 38 mph, 61 kph
Take off distance 100 ft, 30 m
Land¬ing distance 100ft, 30m
Service ceiling 14,500 ft, 4420 m
Range at average cruising speed 130 mile, 209 km

X1
Speed max: 61 mph
Cruise: 55 mph
Stall: 26 mph
ROC: 800 fpm
Take-off dist: 100 ft
Landing dist: 150 ft
Service ceiling: 14,500 ft
Engine: Rotax 447, 40 hp
HP range: 40-70
Fuel cap: 5 USG
Weight empty: 250 lbs
Gross: 510 lbs
Height: 8.17 ft
Length: 16.75 ft
Wing span: 28.5 ft
Wing area: 142 sq.ft
Seats: 1
Landing gear: nose wheel
Cruise on 40hp: 65 mph

Phantom Aircraft Phantom XI
Engine: Rotax 447, 40 hp
HP range: 40-70
Top speed: 61 mph
Cruise: 55 mph
Stall: 26 mph
Rate of climb: 800 fpm
Takeoff dist: 100 ft
Landing dist: 150 ft
Service ceiling: 14,500 ft
Fuel capacity: 5 USG
Empty weight: 250 lb
Gross weight: 510 lb
Height: 8.2 ft
Length: 16.8 ft
Wing span: 28.5 ft
Wing area: 142 sq.ft
Seats: 1
Landing gear: nosewheel

X2
Speed max: 75 mph
Cruise: 68 mph
Range: 175 sm
Stall: 30 mph
ROC: 650 fpm
Take-off dist: 265 ft
Landing dist: 300 ft
Service ceiling: 14,500 ft
Engine: Rotax 503DC, 55 hp
HP range: 53-100
Fuel cap: 10 USG
Weight empty: 475 lbs
Gross: 975 lbs
Height: 8.42 ft
Length: 17 ft
Wing span: 30 ft
Wing area: 160 sq.ft
Seats: 2
Landing gear: nose wheel

Phantom Aircraft Phantom X2
Engine: Rotax 503 DC, 52 hp
HP range: 53-100
Top speed: 75 mph
Cruise: 68 mph
Stall: 30 mph
Range: 175 sm
Rate of climb: 650 fpm
Takeoff dist: 265 ft
Landing dist: 300 ft
Service ceiling: 14,500 ft
Fuel capacity: 10 USG
Empty weight: 950 lb
Gross weight: 425 lb
Height: 8.4 ft
Length: 17 ft
Wing span: 30 ft
Wing area: 160 sq.ft
Seats: 2
Landing gear: nosewheel

The Wombat, which is available in two basic versions comes with a tricycle undercarriage, but in its Bunyip form is a tail dragger aircraft. Construction is Dacron covered aluminium structure. Development work is continuing and a powerplant change to the English Huntington Field engine is currently being planned.

Bunyip
Engine: Fuji Robin 440
Prop: 144cm x 96cm pitch
Wingspan: 8.41 m
Length: 4.7m
Weight: 150kg
Fuel capacity: 23 ltr
Econ cruise speed: 50 kts
Stall: 27kts

In 1983 ULAC is working on a MX PUL 425 engined single seater of the X-99, called the X 77, but no other details were available.

Tandem two seat single engined high wing monoplane with conventional three axis con¬trol. Wing has unswept leading and trailing edges, and constant chord; V tail. Pitch/yaw control by elevon; roll control by one third-span spoilers; 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 100% double surface. Undercarriage has three wheels in tail dragger formation; steel spring suspension on tailwheel and suspension on main wheels. Push right go right tailwheel steering connected to yaw control. Brakes on main wheels. Aluminium tube framework, with optional pod. Engine mounted below wing driving pusher propeller.

Georges Borgeaud, the president of ULAC, acquired on the 14 August 1981 the rights to sell in Europe and Africa the Maxair Hummer. Starting with the basic single seater model designed by the late Klaus Hill, ULAC has developed its own tandem two seater, the X 99. The transformation principally in¬volved raising and reinforcing the wing, increasing the track of the undercarriage, the addition of spoilers to change the machine into a conventional three axis control aircraft and finally the adoption of the Hirth motor.

The prototype made its first flights at the beginning of 1982 above the Californian desert near to Salton Sea. For the distribution of this aircraft, George Borgeaud built a factory at Monthey in the Vallais area in Switzerland. Shown at the first European Salon of Microlights at Lyon Bron in Septem¬ber 1982, and later at the microlight assembly at Blois in France, this machine met with considerable success amongst the established pilots at whom it is aimed. Georges has consistently followed an intelligent sales policy, hinged on safety, and will only sell this aircraft in Europe to qualified private pilot’s licence holders.

Ready to fly X 99s cost US$8650 in 1983 ex works for the standard version, trailer included. Standard are compass, ASI, altimeter, rev counter and CHTG. As an option, it can have climb, turn and slip gauges. Its spoilers can be used together as air brakes and the machine can be flown solo (from the front seat) without any modification. The rear seat can be replaced by a large supplementary fuel tank and other options include skis, floats, pod, main wheel fairings, dual controls, a second instrument panel for the rear seat and a three blade propeller.

Georges was working on a new wing design which can be rigged in two different spans 32.8 ft or 45.9 ft (10.00 or 14.00 m), and the larger span would bring the X 99 comfortably within British ultralight law.

Length overall 17.1 ft, 5.75 m]
Height overall 8.8 ft, 2.65 m
Wing span 34.1 ft, 10.40 m
Constant chord 4.4ft, 1.32 m
Sweepback 0 deg
Tailplane span 8.2 ft, 2.50 m
Fin height 2.1ft, 0.90m
Total wing area 147 sq.ft, 13.7 sq.m
Total spoiler area 1.9 sq.ft, 0.18 sq.m
Tailplane area 19.4 sq.ft, 1.8 sq.m
Total elevon area 13.6 sq.ft, 1.3 sq.m
Wing aspect ratio 7.9/1
Wheel track 4.1 ft, 1.24 m
Wheelbase 7.5 ft, 2.25 m
Tailwheel diameter overall 10 inch, 26 cm
Main wheels diameter overall 14 inch, 35 cm
Floats, dimensions 10. 1 x 2.0 ft, 3.30 x 0.59 m
Skis, dimensions 2.1 x 0.6 ft, 0.87 x 0.14 m
Engine: Hirth 272R 438 cc, 40 hp at 7000 rpm
Prop¬eller diameter and pitch 54 x 30 inch, 1.37×0.76m
Toothed belt reduction, ratio 2.2/1
Max static thrust 252 lb, 114 kg
Power per unit area 0.27 hp/sq.ft, 2.9 hp/sq.m
Fuel capacity 3.2 US gal, 2.7 Imp gal, 12.0 litre in main tank
Fuel capacity 21.7 US gal, 18.1 Imp gal, 82.0 litre in reserve
Empty weight 320 lb, 145kg
Max take off weight 662 lb, 300kg
Payload 3421b, 155 kg
Max wing loading 4.501b/sq.ft, 21.9kg/sq.m
Max power loading 16.6 lb/hp, 7.5kg/hp
Load factors; +5.0, 3.0 ultimate
Max level speed 62 mph, 100 kph
Never exceed speed 71 mph, 115 kph
Max cruising speed 53 mph, 85 kph
Economic cruising speed 44 mph, 70 kph
Stalling speed 24 mph, 38 kph
Max climb rate at sea level 350 ft/min, 1.8 m/s
Min sink rate 680 ft/min at 28 mph, 3.5 m/s at 45 kph
Best glide ratio with power off 7/1 at 37 mph, 60 kph
Take off distance 180 ft, 55 m
Land¬ing distance 80ft, 24m
Service ceiling 13,100ft, 4000 m
Range at average cruising speed 75 mile, 120 km

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 Ga 549; double surface. Undercarriage has three wheels in tricycle formation; steel spring suspension on nosewheel and glass fibre suspension on main wheels. Push right go right nosewheel steering connected to yaw control. Brakes on main wheels. Aluminium tube framework, with pod. Engine mounted below wing driving pusher propeller.

Two prototype examples of this machine were on show at Friedrichshafen in March 1983, but the Wildente did not fly for the first time until 16 April. This machine has a welded tubular framework, which appears to have great rigidity and is also claimed to allow derigging and rigging in less than 10 min. It is sold built and ready to fly. Options include wheel fairings and a three blade propeller.

Length overall 19.4ft, 5.90m
Wing span 34.4ft, 10.50m
Constant chord 4.9ft, 1.50 m
Total wing area 166 sq.ft, 15.4 sq.m
Wing aspect ratio 7.2/1
Wheel track 5.1 ft, 1.55 m
Engine: Hirth F263, 22hp at 4000rpm
Propeller diameter 51 inch, 1.30 m
Belt reduction, ratio 1.8/1
Max static thrust 172 lb, 78 kg
Power per unit area 0.13 hp/sq.ft, 1.4 hp/sq.m
Fuel capacity 5.3 US gal, 4.4 Imp gal, 20.0 litre
Empty weight 221 lb, 100kg
Max take off weight 464 lb, 210kg
Payload 243 lb, 110kg
Max wing loading 2.79 lb/sq.ft, 13.6kg/sq.m
Max power loading 21.1 lb/hp, 9.5kg/hp
Load factors; +6.0, 3.0 ultimate
Never exceed speed 62mph, 100kph
Economic cruising speed 47 mph, 75 kph
Stalling speed 26 mph, 42 kph
Max climb rate at sea level 240 ft/min, 1.2m/s
Min sink rate 310ft/min, 1.6m/s
Best glide ratio with power off 9.5/1
Take off distance 130 ft, 40 m
Range at average cruising speed 124 mile, 200 km

The Sparrow Hawk is a twin boom, twin fin, ultralight aircraft built with mixed construction including Kevlar, Carbon Fiber, Polyurethane Foam, a Rotax 532 four-stroke engine in Pusher configuration, and features a cantilever shoulder wing, fixed landing gear and two seat enclosed cockpit. Former Boeing design engineer Charles “Chuck” Herbst was responsible for the original design.

The public debut of the Sparrow Hawk was at the EAA Annual Convention and Fly-In in July 1985, when two Sparrow Hawks attended, registered N5793F and N5832M. The manufacturer and model of N5793F is recorded by the Federal Aviation Administration (FAA) as an “Ultralight Aircraft Ltd Sparrow Hawk Mk II”, while N5832M is recorded as an “Aero Dynamics Ltd Sparrow Hawk MkII”.
Seven were manufactured by Aero Dynamics Limited.

Although it did fly, the SparrowHawk was a somewhat marginal airplane that needed redesign to correct a number of problems including empennage flutter, drive design and some less than sufficient structure. It was also underpowered.

The design faltered and exchanged hands several times, being held longest by the same folks who owned the now failed NSI. During that period the project really went nowhere, and it was gathering dust in the corner of their shop.

A Sparrow Hawk (N23SH) is currently preserved at the Oakland Aviation Museum.

Sparrow Hawk II
Powerplant: 1 × Rotax 532, 64 hp (48 kW)
Wingspan: 34 ft 5 in (10.49 m)
Length: 17 ft 10 in (5.44 m)
Maximum speed: 105 mph (169 km/h; 91 kn)
Cruise speed: 95 mph (153 km/h; 83 kn)
Stall speed: 36 mph (58 km/h; 31 kn)
Crew: one
Capacity: one passenger

Sparrow Hawk IIB
Powerplant: 1 × 90hp Norton P62
Wingspan: 34’5″
Length: 17’10”
Useful load 700 lb
Maximum speed: 130 mph (09 km/h; 113 kn)
Cruise speed: 120 mph (193 km/h; 104 kn)