Britten-Norman Low Volume Production

Single seat high wing ultra-light monoplane. Of all wood construction, the parallel chord parasol wing featured 1/2 inch thick plank spars. The leading edge was plywood covered, forming a D-shaped torsion box, while every third rib bay was plywood covered top and bottom. The entire trailing edge contained control surfaces - two large ailerons and a single central flap. Construction of the slab-sided fuselage was conventional, built around four longerons, with minimal vertical and cross members, the whole skinned in 1/16 plywood. The decking of the rear fuselage was built up of formers and stringers, with a fabric covering. The cockpit was to the rear of the two main frames, with a readily removable plywood seat for control adjustments.
In front of the cockpit was a shaped aluminium fuel tank, then the firewall is of stainless steel sheet backed with 1/8 inch thick asbestos. From the four fuselage longerons, the engine mounting was carried from flat plate fittings. The mounting itself was of welded steel tube, with rubber vibration dampers. The undercarriage comprised two cantilever legs with internal bungee springing. The fin was an integral structure with a substantial kingpost for pilot protection in the event of the aircraft turning over. Both fin and rudder were fabric covered. The tail plane was bolted to the top longerons with small strut braces the rear spar. The tail plane leading-edge was formed from Duralumin sheet screwed on to the front spar. One 40 h.p. Aeronca-J.A.P. J-99 powerplant.
Following a take-off accident on 16 August 1950, the aircraft was sevearly damaged. The aircraft was rebuilt with a new fuselage, redesigned tailplane and greater span wings, the powerplant being replaced by a 55 h.p. Lycoming O-145. It first flew in this form on 26 May 1951.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
23 ft	16 ft 8 in	6 ft	80 sq ft	408 lb	630 lb	56 mph/ 49 kn	68 mph/ 59 kn	200 mi
7.01 m	5.08 m	1.83 m	7.43 m2	185 kg	286 kg	90 kph	109 kph	322 km

Four seat all-metal high-wing braced monoplane, for supply in kit form and susequent assembly by approved licensees. The structure of the Nymph was expressly designed for this, and eliminated the need for the elaborate tooling usually required in the final stages of aircraft manufacture. It was intended all the detail parts for the aircraft would be produced from precision matched dies in the U.K., ensuring perfect assembly overseas by competent aircraft repair or maintenance organisations. A special assembly school would be set up at Bembridge for training the licensee’s foremen and supervisors. Structure was conventional, with a two spar, constant chord wing and tailplane, a slightly swept fin and rudder, and near-rectangular monocoque fuselage. To have been offered with three different engine options, 115hp,130hp and 160hp, it was only fitted with a 115 h.p. Lycoming O-235 powerplant.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
39 ft 4 in	23 ft 7 in	9 ft 6 in	169 sq ft	1140 lb	1925 lb	113 mph/ 98 kn	117 mph/ 102 kn	600 mi	11200 ft
11.99 m	7.19 m	2.9 m	15.7 m2	517 kg	873 kg	182 kph	188 kph	966 km	3414 m