BD-4 SC OPERATOR'S MANUAL

5. Grease center spar and aileron torque tube. 6. Slide wing onto spar until it is 2.5" from fuselage. Aileron torque tube must be aligned with its socket. 7. Lower rear edge of forward overhead access panel in cabin and screw the wing push-off rod into wing at least three turns. 8. Connect fuel line, vent, and electrical connector. 9. Use wing pry bar to seat wing against fuselage. Guide wing skin under fuselage skin overhang. 10. Install two bolts under wing near the root, and install covers. 11. Install screws that retain fairing to fuselage. 12. Install the aileron drive bolts in each wing. 13. Replace access panels in the headliner. 14. Remove the wing push-off rod and close the forward access panel. 12 SPECIFICATIONS Wing Span 29.2 ft. Wing Area 116.7 ft. Wing Chord 48 in. Aspect ratio 7.3 Length overall 21.4 ft. Height overall 7.2 ft. Horizontal tail span 7.3 ft. Aileron area 3.5 sq. ft. Flap area 9.6 sq. ft. Fin area 6.9 sq. ft. Rudder area 1.5 sq. ft. Horizontal tail area 21.3 sq. ft. Cabin width 41 in. Cabin length 89 in. Cabin height 41 in. Flap span 96”/side Fuel capacity 42 gal. Unusable fuel per tank 0.5 gal. Aileron deflection - up 25° Aileron deflection - down 17° Elevator deflection - up 15° Elevator deflection - down 6° Servo tab - up 18° Servo tab - Down 10° Rudder left and right 16° Flap deflection 10° 20° 30° 40° 13 PERFORMANCE Gross weight 2600 lbs. Empty weight 1557 Engine rating @ 4000 R.P.M. 199 H.P. Useful load 1043 Wing loading 21.9 lb./sq. ft. Power loading 12.84 lb./hp. Max. speed at sea level 184 mph Cruising speed @ 2 P.S.I boost 161 mph Fuel burn rate at cruise 14 GPH Stalling speed - flaps down 40° @ 2557 lb. 62 mph Stalling speed - flaps up @ 2557 lb. 75 mph Rate of climb – Prop pitch = 15°, 1861 lb. 1100 fpm Best rate of climb speed 95 mph Best angle of climb speed 75 mph Maximum range 472 miles 14 N682BD Stall Performance 66 64 61 58 55 70 67 63 60 58 73 70 66 63 60 75 72 68 65 62 64 62 59 56 53 40 45 50 55 60 65 70 75 80 0 10 20 30 40 Flap Setting Indicated Airspeed 2082 Lb. 2283 Lb. 2431 2557est. 1795 est. 15 OPERATING LIMITATIONS Never exceed speed (smooth air) 234 mph Maximum structural cruising speed 180 mph Maximum speed Flaps 10° 130 mph Flaps 10° to 30° 105 mph Flaps 40° 90 mph *Maximum maneuvering speed 133 mph * The maximum speed at which abrupt control travel can be used without exceeding the design load factor. __________________________________________ AIRSPEED INDICATOR MARKINGS Never exceed (smooth air) 234 mph (red line) Caution range 180 - 234 mph (yellow arc) Normal operating range 66 - 180 mph (green arc) Flap operating range 58 - 105 mph (white arc) 16 THREE VIEW DRAWING 17 18 CG Calculation Weight Station Moment Empty 1535 79.18 121536 Front Seats ______ 95.00 ______ Rear Seats ______ 126.00 ______ Fuel ______ 90.27 ______ Baggage ______ 152.00 ______ Total ______ ______ ______ __________________________________________ 19 Equipment List Compass Airspeed indicator Attitude gyro Altimeter Turn coordinator gyro Directional gyro Vertical speed indicator Clock Fuel pressure indicator Manifold pressure indicator Oil Temperature indicator Oil pressure indicator Water temperature indicator Water pressure indicator Voltmeter Ammeter Fuel level indicator (2) Communication radio Transponder with altitude encoder Intercom EGT, 6 probe 20 FUEL INFORMATION 5-15-2000 Total fuel per wing - 21 gal. Unusable Fuel - 0.5 gal. per tank. Fuel flow rate at wing exit - 34.3 gph. Fuel flow rate at firewall - 30.0 gph. Measured at fuel rail return line. 21 Modifications to Original Design  Changed nose gear from tail-wheel to “Murphy” design.  Increased nose gear strut wall thickness to 3/16” to prevent breakage.  Used supercharged Ford 3.8 liter V6, rather than a Lycoming engine to reduce cost.  Added a belly scoop to provide pressure differential across the radiator.  Increased radius on angles at side of windshield to improve airflow.  Used Brekke straight fuselage design to provide more room at rear seats.  Used “JR’s” aluminum wing design in place of fiberglass wing panels.  Lengthened wings by 22 inches per side.  Lengthened flaps to 96 inches per side.  Increased flap deflection angle to 40° to provide additional drag on final approach.  Added two delrin bearings along the span of each flap to absorb added loads.  Extended flap actuator rod through three ribs to improve robustness.  Added enclosed baggage compartment.  Increased access panel size at rear of fuselage to improve accessibility for service.  Added large removable panels to provide access to the rear of the control panel.  Changed from a “Stick” to a “Yoke” control system.  Moved the battery to the rear of fuselage to balance heavier engine.  Added an electrical stabilator trim tab drive to reduce sensitivity. 22 Modifications (continued)  Add an electrically driven rudder trim system.  Added a header tank with two fuel pumps, a low fuel level sensor, and a water sensor.  Added a vent line from the top of the header tank, connected through a “tee” fitting to the outer ends of each wing tank.  Modified the fuel valve to feed from both wing tanks simultaneously.  Added fuel sumps, with drains, at the lowest point at the outer edge of each wing tank. The sumps also incorporate forward facing vents that terminate at the inboard end of each wing tank.  Replaced the gascolator with a drain from the header tank.  Added mercury switch controlled fuel valves in each wing tank to select front or rear fuel pick-up, depending on aircraft attitude or inertia loading.  Used Cessna front seats in place of BD design for adjustability.  Added antenna in wing tip for handheld back-up transceiver.  Added doubler to main gear legs to reduce splay.  Changed gear box from .063 to .093” thick aluminum to eliminate cracking problems.  Added gussets at main gear box attach points to improve robustness.  Added wing removal assist system.  Added foam seals at aileron and flap pass-through points on the fuselage.  Increased windshield thickness to ¼ inch.  Modified the windshield mounting to ease maintenance or replacement. 23 Modifications (continued)  Modified the doors to hinge from top and added two latching pins near the bottom.  Replaced “sling” style rear seat with a fabricated aluminum bench seat, which can swing up for maintenance.  Added a movable overhead panel forward of the center-section spar, enclosing the wing removal assist devices, a loudspeaker, and cockpit lighting.  Added a rudder return cable and pulley to absorb heavy braking pressure.