No. 13013. Briffaud G.B.10 Pou-Push (F-PYOJ c/n 01)
Photographed by Ron Smith

Briffaud G.B.10 Pou-Push

09/30/2016. Remarks by Johan Visschedijk: "On the basis of ten years' experience in aviation, Georges Briffaud of Versailles, France, began the design and construction of a small single-seat light aircraft of the Mignet tandem-wing type in 1974. After 5,000 hours of work, the prototype (temporarily registered F-WYOJ) was flown for the first time on June 23, 1983 by Mr. Desmots. Subsequent testing was taken over by the designer's son, Michel Briffaud, and the Pou-Push received a CofA in 1984 and was reregistered F-PYOJ. As the CofA expired the registration was cancelled on March 1, 1993.

TYPE. Single-seat tandem-wing light aircraft.
WINGS. Forward wing comprises two strut braced semi-span structures which could be varied independently in incidence for roll control and collectively for pitch control. NACA 25000 series wing section. Slight dihedral from roots. Each half-span was made up of a main box spar with spruce booms and okoumé plywood webs, forming a D leading-edge torsion box with plywood skin; spruce trellis ribs; an auxiliary rear spar; and over-all fabric covering. Trim tab in inboard trailing-edge of each half-span. Rear wing, of similar section and construction, was fixed, except for a wide-span central flap which deflects only upward to increase rate of descent.
FUSELAGE. All-wood box structure of okoumé plywood over spruce frames and longerons. Lower surface fabric covered. Top decking and nosecone of composites.
TAIL UNIT. Triangular endplate fin at each tip of rear wing, with independent horn balanced rudder that deflected only outward and was returned to a neutral position by a spring. Structures of wood with fabric covering.
LANDING GEAR. Non-retractable tricycle type, with single wheel on each unit. One-piece cantilever arch structure of composites carried mainwheels, with sprung wire bracing. Duralumin nose wheel fork was carried on a composites spring. Friction pad brake on steerable nose wheel. Wire guard under rear fuselage to protect propeller and rudders in taildown attitude.
POWERPLANT. A 30 hp Hirth 276R air-cooled two-cylinder inline two-stroke engine, driving directly a two-blade wooden fixed-pitch pusher propeller, diameter 2 ft 11.5 in (0.90 m). Fuel comprised petroleum/oil (3-5 %) mixture in composites tank on CG, capacity 10 gal (38 l).
ACCOMMODATION. Single seat in enclosed cockpit, under one-piece removable transparent canopy. Control by conventional stick and rudder pedals.
SYSTEM. Electrical system included 12V generator on engine for starting, and 12V 14A battery inside removable nosecone.

Created September 30, 2016