
            
            Light-weight-aircraft, 2 seats (side by side), 
            composite-construction (lumber, Styrofoam,  glass-fibre and epoxy). 
            Low-wing monoplane with quick removable Wings and retractable 
            nose-wheel-landing-gear. The Flap movement is transferred to the 
            aileron in a reduced rate. Pendulum-elevator with anti-servo-flap. 
            Nose-wheel-steering and  a shock-absorber (rubber) for the 
            nose-landing-gear. Main-landing-gear made of strands on a 
            lumber-core, hydraulic-brakes simultaneously  applied by lever. 
            Full-sight-canopy slides opens in fwd direction. Rudder is 
            cable-controlled, elevator- and aileron-transmission is rod 
            controlled.
            
            Constructional guideline
            
            The load-assumptions, speed-rating as well as equipment were taken 
            from the American
            FAR 23 which is also valid in Switzerland.  
            Nevertheless the aircraft remains an ”Experimental”.
            A Good aerodynamic was chosen to save Performance. Economy and low 
            noise emission go along with that. Dimensions were kept compact 
            rather than increasing wing aspect ratio for even better 
            aerodynamics. 
            The construction was based on own manufacturing-facilities (welding 
            and 
            painting outside).  
            
            
            Hangar/transportation
            
            Permanent hangar-space is not necessary for the aircraft.
            For transportation both stabilizer-halves are removable and can be 
            stowed in the Cockpit. 
            Then the ”Cherry” will be towed on a simple trailer and fixed. By 
            pulling a bolt the Wings (30 Kg) can be removed and fixed on the 
            trailer beside the fuselage.
            
            Homebuilders requirements
            
            The aircraft is not built in a primitive manner and requires 
            anywhere from good up to advanced craftsmanship. The project 
            requires about 4000 hours. Even if the prototype swallowed just 10 
            000 SFr till it’s 1st flight (including engine and instruments) it 
            is recommended to assign at least 20 000 SFr. 
            
            During the construction period, which takes a few years, you can 
            easily do without travelling or other expensive activities and thus 
            save quiet the amount of money needed for this project.
            
            
            
            
             
              
               
               
               specifications 
 
              
                
                powerplant 
                propeller 
                length 
                height 
                wing span 
                wing area 
                seats 
                empty weight 
                
                
                useful load 
                gross weight 
                fuel capacity 
                range | 
                
                  Continental A 65 
                
                  Brändli 
                  1.60m 
                
                  
                5.23m 
                
                  2.02m 
                
                  7.00m 
                
                  8.50sq 
                m 
                2 
                
                  320kg 
                x 
                
                  550kg 
                80litres 
                
                x | 
               
             
            
            performance 
            
             
            
              
                
                takeoff 
                distance, ground roll 
                rate of climb 
                max speed 
                cruise speed 
                landing distance, ground roll 
                
                
                service ceiling | 
                
                  300m 
                
                  3m/s 
                x 
                
                  219 
                x 
                x | 
               
             
            
            limiting and recommended speeds
             
            
              
                
                design 
                manoeuvring speed (Va) 
                never exceed speed (Vne) 
                stall, power off (Vso) 
                landing approach speed  | 
                
                  170 
                
                  275 
                
                  96 
                x | 
               
             
            All specifications are based on 
            manufacturer's calculations 
   |