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Neukom AN-22


Single-seat single-engined high-wing mono-plane with conventional three-axis control. Wing has unswept leading edge, swept for-ward trailing edge on outboard half of span, and tapering chord; conventional 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 NACA 4415; double-surface. Undercarriage has three wheels in tricycle formation with addi-tional tailskid; no suspension on nosewheel and rubber suspension on main wheels. Push-right go-right nosewheel steering con-nected to yaw control. Brakes on main wheels. Aluminium-tube framework with optional pod. Engine mounted below wing driving pusher propeller.

The AN-22 was designed by the Swiss Albert Neukom who also built the first two examples to obtain certification in West Germany. The AN-22 made its first flights in March 1983 and was shown in the same month at the Aero 83 exhibition at Friedrichshafen. Point Aviation acquired the licence to build and sell this machine throughout the world, the first production machines being built in spring 1983. The model makes use of the original formula tried by Albert Neukorn in 1982 on the prototype AN-20, whereby the three-cylinder Konig 430 cc engine is carried behind the wing on a mount coming from the large diameter spar which carries the tail. This spar also acts as the axis of the propeller which is driven through a triple V-belt reduction drive. The two blades can fold backward parallel to the spar.

Production versions were factory built and sold by Point Aviation in West Germany.

Neukom completed the construction (May 1983) of the AN-22 Twin, a two-seater version of the AN-22.


Length overall 18.4 ft, 5.60 m
Height overall 4.3ft, 1.30m
Wing span 33.511, 10.20m
Chord at root 3.9ft, 1.20m
Chord at tip 3.3ft, 1.00m
Dihedral 4 degrees
Sweepback 0 degrees
Tailplane span 8.5 ft, 2.60 m
Fin height 3.1 ft, 0.95 m
Total wing area 126 sq.ft,11.8 sq.m
Total aileron area 12.1 sq.ft, 1.12 sq.m
Fin area 6.6 sq.ft, 0.61 sq.m
Tailplane area 11.7sq.ft, 1.09sq.m
Total elevator area 6.5 sq.ft, 0.60sq.m
Wing aspect ratio 8.9/1
Wheel track 6.2 ft, 1.90 m
Nosewheel diameter overall 10 inch, 26cm
Main wheels diameter overall 12 inch, 30 cm
Engine: Konig SC430, 22hp at 4200rpm
Propeller diameter 52 inch, 1.32 m
Belt reduction, ratio 1.8/1
Max static thrust 143 lb, 65 kg
Power per unit area 0.17 hp/sq.ft, 1.9 hp/sq.m
Fuel capacity 5.3 US gal, 4.4 Imp gal, 20.0 litre
Empty weight 232 lb, 105 kg
Max take-off weight 464 lb, 210kg
Payload 232 lb, 105kg
Max wing loading 3.68 lb/sq.ft, 17.9 kg/sq.m
Max power loading 21.1 lb/hp, 9.5kg/hp
Load factors +6.0, -3.0 ultimate
Max level speed 75 mph, 120 kph
Never exceed speed 81 mph, 130 kph
Max cruising speed 56 mph, 90 kph
Economic cruising speed 44 mph, 70 kph
Stalling speed 24 mph, 40 kph
Max climb rate at sea level 600 ft/min, 3.1 m/s
Min sink rate 200 ft/min at 32 mph, 1.0 m/s at 52 kph
Best glide ratio with power off 14/1 at 34 mph, 55 kph
Take-off distance 330 ft, 100 m
Land-ing distance 260 ft, 80 m
Range at average cruising speed 124 mile, 200 km

AN-22 Twin



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