Single seat single engined high wing monoplane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; conventional tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by quarter-span spoilerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile NACA 23015; 100% double surface. Undercarriage has three wheels in tail dragger formation; suspension on tailwheel and axle flex/ rubber suspension on main wheels. Push right go right tailwheel steering connected to yaw control. Aluminium tube framework, with pod. Engine mounted below wing driving pusher propeller.

Pod made from Keviar/Carbon fibre. Composite construction wing uses aluminium tubing to British HT30TF specification, Styrofoam, and wood veneer covering.

The Honeybird is a sophisticated pod: it is non structural and is attached to an aluminium framework.

Although the Honeybird is a microlight by definition, it is being built under the aegis of the British homebuilders association, the PFA, whose engineering requirements insist on gravity rather than pumped fuel feed. The main fuel tank is therefore in the wing, with a reserve situated aft of the pilot.

The Honeybird is basically a homebuilt, which in 1982 had yet to make its first flight.

Engine: NGL WAE 342, 30hp at 6800rpm
Micro V belt reduction
Power per unit area 0.23 hp/sq.ft, 2.5 hp/sq.m
Fuel capacity 3.6 US gal, 3.0 Imp gal, 13.6 litre in main tank; 4.8 US gal, 4.0 Imp gal, 18.2 litre in reserve
Length overall 18.5 ft, 5.64 m
Height overall 6.5ft, 1.98m
Wing span 32.5ft, 9.91m
Constant chord 4.0ft, 1.22m
Dihedral 3 deg
Sweepback 0 deg
Tailplane span 7.0ft, 2.13 m
Fin height 4.0ft, 1.22m
Total wing area 130 sq.ft, 12.1 sq.m
Total spoileron area 3.0 sq.ft, 0.28 sq.m
Wing aspect ratio 8.1/1
Wheel track 7.0ft, 2.13m
Tailwheel diameter overall 4 inch, 10 cm
Main wheels diameter overall 12 inch, 30 cm
Empty weight 2601b, 118kg
Max take off weight 510 lb, 231kg
Payload 250 lb, 113kg
Max wing loading 3.92 lb/sq.ft, 19.1 kg/sq.m
Max power loading 17.0 lb/hp, 7.7kg/hp
Load factors +6.0 design
Never exceed speed 109mph, 175kph
Max cruising speed 68mph, 109kph
Stalling speed 34mph, 55 kph
Best glide ratio with power off 15/1

A single seat single engine, high wing mono¬plane with hybrid control circa 1983. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by weight shift; yaw control by fully flying rudder; no separate roll control; control inputs through weight shift for pitch/yaw/roll. Wing braced from above by kingpost and cables, from below by cables; wing profile single ¬surface. Undercarriage has three wheels in tail dragger formation. Metal tube framework, without pod. Engine mounted below wing driving pusher propeller.

It appears to have a rudder to assist the weight-shift in yaw, a combination which is sufficient to class the Zhuravlic as a hybrid, but it is not clear whether a similar arrangement is used for pitch control or whether the pilot relies solely on weight shift for up/down control.

No details are given of the power unit, except that it is of 350 cc and is coupled to a two blade propeller.

Wing span 31.5 ft, 9.60 m
Engine: 350 cc
Empty weight 121 lb, 55 kg
Max level speed 37.5 mph, 60 kph
Best glide ratio with power off: 30/1
Take off distance 66ft, 20m
Landing distance 33ft, 10m
Service ceding 6600ft, 2000m