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The Doman LZ-5 was a utility helicopter developed in the United States in the early 1950s by Doman Helicopters Inc. of Danbury, Connecticut. Despite the procurement of international manufacturing agreements, no series production of the aircraft ever occurred, and only three prototypes were built. Two of these were purchased by the United States Army as the YH-31, but eventually becoming VH-31. Like the preceding LZ-1 through LZ-4, the LZ-5 utilized designer Glidden Doman's unorthodox gimbaled rotor head system, which featured the elimination of rotor hinges and dampers and included blades of soft-in-plane dynamic design. The servo control system was entirely contained within the rotor head, with no external oil tanks or plumbing. The tail rotor was also hingeless and free floating to eliminate stresses in rapid tail rotor turns. In other ways, it had a conventional helicopter main rotor and tail rotor configuration. The pilot and co-pilot were seated over the engine, which was in the nose, and a six-passenger compartment was located behind them. The engine was cooled by exhaust ejectors, producing an energy saving that increased payload by 800 pounds. The aircraft featured wheeled quadricycle undercarriage, the main units of which carried dual wheels. The first prototype (registration N13458) flew on 27 April 1953, and by the end of 1955, two machines had been delivered to the Army (52-5779 and 52-5780). Eventually, the Army concluded that they had no requirement for an additional piston-powered helicopter model in this size category, and no further order was placed. After extensive flight testing and pilot training by the Army, one of the prototypes was taken over by the Navy for a helicopter flight research program at the Patuxent River Naval Air Test Center. Later that aircraft was re-purchased by the Doman company and used in its commercial sales efforts. Doman continued with development, building another LZ-5 aircraft in a joint venture with Fleet in Canada. The LZ-5 helicopters were simultaneously Type Certificated in the U.S. and Canada in 1954. The third helicopter flew extensively in Canada under Canadian registration CF-IBG and in the United States, France, and Italy under U.S. registration N812. It flew in the Paris Air Show in 1960. This aircraft was also modified with the installation of full blind flight instrumentation, which was demonstrated extensively in the effort to sell it as a trainer. The aircraft thus equipped was advertised as the D-10. The planned production version would have been modified with a turbo-charged engine and designated as the D-10B. Doman sold production rights for military versions to Hiller and for the Italian market to Ambrosini. Ultimately, none of these plans were to eventuate, and the LZ-5 never entered production. Variants LZ-5 (3 built) YH-31 - LZ-5 for military evaluation, Army designated VH-31 (2 built) LZ-5-2 - civil version, intended as prototype for production as D-10A (1 built) D-10B - Lycoming O-720 turbocharged engine; (proposed production version of LZ-5)

The EDRA Aeronautica Super Pétrel is an amphibious pusher configuration biplane, seating two side-by-side, brought into production in Brazil in 2002 though with French parentage. It remained in production in 2011, in kit and flyaway forms. The design of the Super Petrel has its origins in the Tisserand Hydroplum, a single-seat, wooden amphibian intended for kit building first flown in 1983 and its two-seat, Rotax 532-powered development, the Hydroplum II, in 1986. The Société Morbihannaise d'Aéro Navigation (SMAN) acquired production rights to the latter in 1987, marketing it as the Pétrel, and passed them on to Billie Marine when SMAN ceased trading. In 2002 the Super Petrel 100 was developed by Edra Aeronautica. By 2014 the design was being produced by Scoda Aeronáutica of Ipeúna, São Paulo, Brazil. The Super Petrel is of mixed construction, though with much use of composite materials. The wings have tubular aluminium alloy spars combined with PVC foam ribs. The leading edges and wingtips are formed from glass fibre composite, with fabric covering elsewhere. The wings have constant chord and zero sweep, with angled winglet tips; the upper wing has the greater span, less dihedral (2° 13′ compared with 3° 26′). There is slight stagger. The Super Petrel is a single bay biplane with N-form aluminium interplane struts with an additional diagonal strut in each bay from the lower fuselage to the top of the interplane struts. The centre section is supported by a pylon or cabane which also contains the engine mounting. Ailerons are carried only by the upper wings; there are no flaps. The wings can be disassembled in about 30 minutes for transportation by trailer. The single-step hull is an epoxy/carbon fibre foam monocoque, with a carbon fibre boom supporting the all-composite, cruciform and wire braced tail unit. The rear control surfaces are balanced. The cockpit is forward of the central pylon and seats two side-by-side with dual controls. It may be flown open, with just a windscreen, or enclosed by the single piece, forward-hinged canopy. There is a baggage compartment behind the seating. The Super Petrel has a short legged tricycle undercarriage for land operation; the main units, which have hydraulic brakes, retract upwards through 90° into the sides of the hull with the wheels exposed but recessed into the underside of the lower wing. The steerable nosewheel retracts forward, leaving the tyre partly exposed as a docking fender. A pair of small, stepped floats on the lower wings below the interplane struts stabilise the aircraft on water. The Super Petrel is powered by a 73.5 kW (98.6 hp) Rotax 912ULS flat-four engine mounted in pusher configuration on the central pylon just below the upper wing. It drives a three-blade Airplast propeller, either a fixed pitch model 175 or an electrically controlled, variable pitch model PV 50. Seven Super Petrel appeared on the civil aircraft registers of European countries, excluding Russia in mid-2010. There have also been sales in North America, Africa, Australia and New Zealand as well as in Brazil where there were 50 registered by December 2009. Variants Super Petrel 100 Designed in 2002. Lowered engine line, revised undercarriage and controls. Structural alterations with more carbon fibre; wingtips with washout and winglets which increased the span of both wings; floats moved from tips to wing underside. Super Petrel LS Designed in 2009. 280 mm (11 in) longer and with a 25 km/h (16 mph) increase in cruising speed; greater fuel capacity; redesigned cabin and tail group. AAC SeaStar SP North American version marketed by Amphibian Airplanes of Canada (AAC).

The Duruble Edelweiss is a light utility aircraft designed in France in the early 1960s and marketed for homebuilding. It is a low-wing cantilever monoplane with retractable tricycle undercarriage and all-metal construction. The aircraft was designed for a load factor of 9. Two- and four-seat versions were designed. The aircraft's creator, Roland Duruble flew the first example, a two-seater designated RD-02 in 1962, and in 1970 began to market plans for a stretched version with a rear bench seat as the RD-03. Over the next 15 years, 56 sets of plans had been sold, and at least nine Edelweisses finished and flown. In the 1980s, Duruble marketed an updated version of his original two-seater as the RD-02A, and sold around seven sets of plans, with at least one aircraft flying by 1985. Variants RD-02 RD-02A Variant designed for homebuilt construction[2] RD-03A Two-seat variant with a 100 hp (75 kW) Continental O-200 engine. RD-03B Variant designed to have either a 135 hp (101 kW) Lycoming O-320 or Franklin Sport 4B engine. Utility variant with two seats or a normal variant with 2+2 seating. RD-03C Variant with a 150 hp (112 kW) Lycoming engine and increased fuel capacity. Utility variant with two-seats or a normal variant with 2+2 seating for four adults.

The Dyn'Aéro CR.100 is a French kit built single engine, two-seat monoplane, developed in the 1990s and intended as both an aerobatic trainer and a tourer, primarily for aero club use. The CR.100 was designed by Christophe Robin to provide a two-seater that could both provide competitive aerobatic training and be used as a tourer. Suitability for club use, particularly low cost and maximum utility, were prime considerations. It is produced in kit form for home assembly. The CR.100 is a conventional single engine, low-wing monoplane, with the large control surface areas and absence of dihedral expected in an aerobatic aircraft. The structure is mostly wood and fabric, though the main wing spar is a plywood and carbon laminate composite and carbon covered ply is an option for the wing surfaces. All the flying surfaces are straight edged and tapered. The ailerons take up about 60% of the wing's trailing edge. The ailerons have spades to reduce control loads. The remainder of the wing trailing edge is three-position flaps. The rudder and elevators are horn balanced and there is a fixed rudder trim tab. The width of the flat sided fuselage is determined by the side by side seating arrangement. Full dual controls, including a pair of left hand throttles, are fitted. A sliding bubble canopy covers the cockpit and is faired behind into a raised and rounded fuselage top decking. The wide track main conventional undercarriage has cantilever legs in fairings, with wheels usually in spats. The tailwheel is freely castoring. The CR.100T variant offers the alternative of a tricycle undercarriage. The CR.100 is powered by a 180 hp (135 kW) Lycoming O-360 flat-4 engine, driving a fixed pitch, two-bladed propeller. The CR.110 variant has a Lycoming engine uprated to 200 hp (150 kW). The CR.120 high agility version is intended to be competitive in the 200 hp class of the Doret Cup and also has the uprated engine. It differs from the CR.110 aerodynamically in having almost full span ailerons and a shorter span to increase the roll rate, at the cost of the flaps, and structurally in having an entirely carbon fibre airframe. The CR.120 was also intended for use as a military trainer. The first flight of the CR.100 was on 27 August 1992. The CR.120 flew in September 1996 and the CR.100T in November 2000. The RC.100 won the Championnat de France II, the national competition for two-seat light aircraft, in 1994 and 1995. By 2001, more than 35 kits had been sold. In 2010 13 CR.100s, 1 CR.100T and 2 CR.120s were on the French civil aircraft register. Two CR.100s flew with the l'Equipe Voltige de l'Armée de l'Air between 1995 and 1997; one of these was later registered in the UK,[8] the other is now a French civilian. Variants CR.100 Standard version. CR.100T As CR.100 but with tricycle undercarriage. CR.110 As CR.100 but with uprated engine. CR.120 As CR.110 but wingspan reduced from 8.50 m to 7.77 m, with full span ailerons, without flaps. Full carbon fibre reinforced wooden airframe. Standard landing gear configuration is conventional with tricycle gear optional.

The Davenport BD-2 Nuggit (sic) is an American biplane developed for homebuilt construction. The B-2 Nuggit is a single place biplane with conventional landing gear. The cockpit is covered with a sliding bubble canopy. The fuselage is welded steel construction with aircraft fabric covering. A round cowling covers the engine to appear like a radial engine installation. The wing uses a wooden spar with aluminum wing ribs.

The Culver Dart was a 1930s American two-seat light monoplane aircraft produced by the Dart Aircraft Company (later the Culver Aircraft Company). In the early 1930s Al Mooney was working for the Lambert Aircraft Corporation, builders of the Monocoupe series aircraft. He designed a small two-seat monoplane, the Monosport G. When the company ran into financial difficulties Mooney bought the rights to his design and with K.K. Culver formed the Dart Aircraft Company. The aircraft was renamed the Dart Dart or Dart Model G. The aircraft was a low-wing monoplane designed to be light with clean lines to enable it to use low powered aero-engines. It had a fixed undercarriage and a tailwheel. The initial version was named the Dart G powered by a 90 hp (67 kW) Lambert R-266 radial engine. That engine was in short supply, so the aircraft was fitted with a Ken-Royce engine and designated the Dart GK. The final version was the Dart GW powered by a Warner Scarab Junior radial engine. Two special aircraft were built with larger engines. In 1939 the company was renamed the Culver Aircraft Company and the aircraft was renamed the Culver Dart. Variants Dart G Initial production version powered by a 90 hp (67 kW) Lambert R-266 - ca. 50 built. Dart GC 125 hp (93 kW) Continental O-200 - 10 built Dart GK Variant fitted with a 90 hp (67 kW) Ken-Royce 5G engine - 25 built. Dart GW Final production version powered by a 90 hp (67 kW) Warner Scarab Junior - 8 built. Dart GW Special Two aircraft fitted with larger Warner engines, one with a 125 hp (93 kW) Warner Scarab engine, and the other with 145 hp (108 kW) Warner Super Scarab SS-50A engine. X-F 220 Super Dart An experimental variant modified with a 220 hp (160 kW) Continental R-670, 8 foot wing reduction and a 188 mph (163 kn; 303 km/h) cruise speed. Used by Rodney Jocelyn in national aerobatics.

The McDonnell 120 Flying Crane, also V-1 Jeep, was a lightweight utility flying crane helicopter designed and built by the McDonnell Aircraft Corporation during the 1950s. The open frame fuselage supported the three gas-producers and main rotor mast, with a small single-seat cockpit in the nose, which was originally open, but later enclosed. McDonnell had been interested in the flying-crane concept from just after the war, investigating rotors driven directly by ramjets and compressed air tip jets on the McDonnell XH-20 Little Henry, the cancelled McDonnell 79 Big Henry and the McDonnell XV-1 high-speed compound helicopter. The expected advantages included: inherent angle of attack stability increased inherent pitch and roll damping greatly improved dynamic helicopter stability ability to start and stop in high winds; no need for tracking and no dampers required no possibility of mechanical instability or ground resonance; very low vibration low maintenance due to absence of highly loaded bearings, reduction gears, shafting, and anti-torque rotor automatic rotor speed control. McDonnell started development of a private-venture flying crane helicopter in December 1956, progressing rapidly with a mock-up in January 1957 and the first of two prototypes flying on 13 November 1957, piloted by John R. Noll. The airframe of the Model 120 was very simple, comprising a welded steel-tube open structure, with the three-bladed main-rotor mast and gas-producers attached without covering. Rotor drive was by compressed air rotor-tip jets, fed by three 200 hp (149 kW) gas power AiResearch GTC 85-135 gas-producers. The Model 120 was only ever intended to carry loads under-slung or attached directly to cargo hooks on the underside of the top fuselage beam, including specialised pods. Although aimed at the US Army the Model 120 was also evaluated by the US Navy at the Naval Air Test Center (NATC), NAS Patuxent River, in September 1959. The Model 120 experienced powerplant problems initially, but demonstrated an excellent load to weight ratio of 1.5:1, but despite the proven performance no orders were forthcoming and cancellation of the project in February 1960 signalled the end of McDonnell's helicopter aspirations. Only two examples were built.