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      Rihn Design Series DR-109 
      
      
        
      
      
            
            
              
            
            
            Type  
            Two seat aerobatic aircraft - competition and aerobatic training 
             
            Design Features  
            Low wing monoplane with a specially designed symmetrical airfoil, 
            16% thick, conic nose and flat sides. Large symmetrical ailerons. 
            Wire braced tail surfaces. Solo from rear seat. Cockpit equipped 
            with dual control sticks, dual rudder pedals, dual throttle, dual 
            propeller controls, dual trim controls, dual brakes, and dual 
            instrumentation. 
             
            Structure  
            Fuselage has a welded steel tube truss covered with sheet metal from 
            the firewall aft to the cockpit, aft the tail. Aluminum sheet metal 
            turtledeck. The tail surfaces are fabric covered and wire braced 
            with steel tube spars and bent up steel sheet metal ribs. The one 
            piece wing is all wood, Douglas Fir Box main spar, Douglas Fir 
            spars, plywood ribs and plywood covered. Large span ailerons are 
            built of wood and are plywood covered. The fiberglass engine cowl in 
            a two piece, split horizontally and is easily removable for ease in 
            maintenance. 
             
            Flying Controls  
            Pushrod actuated ailerons and elevator, cable actuated rudder. 
            Ailerons are mass balanced and aerodynamically counterbalanced. Each 
            aileron is fitted with a ground adjustable balance surface suspended 
            below the aileron. A trim tab on each elevator also acts as a servo 
            tab to reduce stick pressures. 
             
            Power Plant  
            Three engine options are available: AEIO-360 A1E6, 200 HP , AEIO-540 
            D4A5, 260 HP, AEIO-540 L1B5, 300 HP. The prototype DR-109 is 
            equipped with an AEIO-540 D4A5, 260 HP. Driving an MTV-9, three 
            blade variable pitch constant speed propeller. The main fuel tank is 
            located in the fuselage ahead of the cockpit, capacity is 30 
            gallons, auxiliary fuel for cross country is located in the wing, 
            capacity is 16 gallons. Total fuel capacity is 46 gallons. 
             
            Landing Gear 
            Non-retractable tail wheel type, main gear is a one piece aluminum 
            spring, tail wheel is steerable and full swivel mounted on a 
            cantilever steel spring. Main wheels are 5.00 x 5 with hydraulic 
            disk brakes. 
             
            Accommodation  
            Each cockpit seat has an adjustable seat back nominally reclined to 
            30 degrees and is equipped with a five point aerobatic seat belt 
            system. 
             
            Systems  
            Electrical system of 12 volts. Electric engine starter. Terra VHF 
            radio. Terra transponder with encoder. Grand Rapids Technology 
            Engine Information System (front and rear cockpit). Sigtronics voice 
            activated intercom. 
            
              
            
             
              
               
               
               specifications 
 
              
                
                powerplant 
                propeller 
                length 
                height 
                wing span 
                wing area 
                seats 
                empty weight 
                
                useful load 
                gross weight 
                fuel capacity 
                range | 
                
                
                Lycoming 
                200/260/300 HP 
                x 
                
                22 ft 
                
                5.5 ft 
                
                24 ft 
                
                114 sq ft 
                2 
                
                1260/1350/1420 
                
                lbs 
                
                690/900/900 
                
                lbs 
                
                1950/2250/2320 
                
                lbs 
                
                30/45 x-country 
                
                404/450/430 mi | 
               
             
            
            performance 
            
             
            
              
                
                takeoff distance, 
                ground roll 
                rate of climb 
                max speed 
                cruise speed 
                landing distance, ground roll 
                
                
                service ceiling | 
                
                600 ft 
                
                x 
                
                192/205/215 mph 
                
                168/178/185 
                x 
                x | 
               
             
            
            limiting and recommended speeds
             
            
              
                
                design manoeuvring speed (Va) 
                never exceed speed (Vne) 
                stall, power off (Vsl) 
                landing approach speed  | 
                
                
                x 
                x 
                
                58 Solo/60 Dual mph 
                x | 
               
             
            All specifications are based on manufacturer's 
            calculations 
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