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Sistemas avioneta da20c-1

Sistemas avioneta da20c-1

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  • Strengthen where needed – the spar, main bulkhead, ailerons and flaps.
  • pictures/movies: control linkages throughout airplane? hinges/roll pins/varnish
  • pictures/movies: control linkages throughout airplane? hinges/roll pins/varnish
  • videos/movies; flaps extending/retracting w/ lights (needs to be dark) circuit breaker NEW FLAPS MOVIE
  • videos/movies; flaps extending/retracting w/ lights (needs to be dark) circuit breaker NEW FLAPS MOVIE
  • videos/movies; flaps extending/retracting w/ lights (needs to be dark) circuit breaker NEW FLAPS MOVIE
  • videos/movies; bellcranks/bearings elevator moving up and down
  • videos/movies; bellcranks/bearings elevator moving up and down
  • videos/movies; bellcranks/bearings elevator moving up and down
  • - operate parking brake; pull lever down until it catches, pump brakes several times to build up pressure. -if copilot’s brakes fail, pilot’s are still operational; if pilot’s fail, both fail. -check for leaks around main wheels as part of every walkaround.
  • -equipped with both a mechanical and an electric fuel pump; mechanical for normal fuel supply, electrical pilot controlled -electrical for emergency and backup; turned on via FUEL PUMP switch during engine start, takeoff, and landing, as well as when switching tanks FUEL PUMP SWITCH PICTURE/FUEL SELECTOR PICTURE DO WE WANT ANYTHING ON FUEL TANKS OR THE FUEL QUANTITY MEASURING DEVICE?

Sistemas Sistemas Presentation Transcript

  • DA20-C1Systems Introduction
  • DA20 SystemsIntroduction ✈ What we’ll look at... ✈ Airframe (FUSELAJE) ✈ Flight Controls ✈ Landing Gear and Hydraulics ✈ Engine and Associated Systems ✈ Electric and Navigation Systems ✈ Aircraft Operating Limitations ✈ Performance Charts ✈ Annunciations and Alerts ✈ Emergency Procedures
  • DA20 Airframe Construction Materials ✈ Composite aircraft; constructed mostly of Glass Fibre Reinforced Plastic (GFRP), although Carbon Fibre (CFRP) is used to strengthen (FORTALECER) where needed. Fuselage ✈ Semi-monocoque molded construction. Fire-resistant matting on cabin side of firewall; stainless steel ✈ cladding on engine side. (revestimiento de acero inoxidable en el lado del motor). Wings ✈ Front and rear spar; top shell and bottom shell. (Delantera y trasera larguero; carcasa superior y la cubierta inferior). ✈ Principally sandwiched construction ✈ Empennage ✈ T-tail design. Semi-monocoque sandwiche contruction
  • Flight Controls ✈ Ailerons ✈ Flaps ✈ Elevator ✈ Trim System ✈ Rudder
  • Flight Controls Ailerons ✈ 4 hinges (BISAGRAS). ✈ Aileron Balancing Weight is located at the outboard edge of aileron ✈ The lock nut has varnish applied (called a torque seal) which indicates changes to factory adjustment; if the varnish has been disturbed, flight safety may be compromised. (La tuerca de seguridad tiene el barniz aplicada (llamado un sello de par) lo que indica cambios en el ajuste de fábrica, si el barniz se ha alterado, la seguridad del vuelo puede verse comprometida)
  • Flight Controls Aileron Assembly INSERT PICTURE HERE
  • Flight Controls Flaps ✈ Slotted flap , 4 hinges secured by a nut and bolt (Tapa ranurada, 4 bisagras garantizadas por una tuerca y un tornillo) ✈ Lock nut with lock varnish (CAPA) ; check for damage. ✈ Flap system protected by a circuit breaker.
  • Flight Controls Flap Settings ✈ Flaps electrically operated - 3 settings: cruise (UP), takeoff - 15o (T/O), landing - 45o (LDG). ✈ Note: when instrument lights are turned on, the flap indicator lights are dimmed (ATENUADO)
  • Flight Controls Flap Assembly
  • Flight Controls Elevator ✈ Steel pushrods.(VARILLAS DE ACERO) ✈ The bellcrank is visible next to the lower hinge of the rudder, as well as the elevator horn and its bearings. (La palanca acodada es visible al lado de la bisagra inferior del timón, así como la bocina elevador y sus cojinetes.)
  • Flight ControlsElevator Assembly
  • Flight ControlsTrim System Assembly
  • Flight Controls Rudder ✈ An upper hinge and a lower hinge with rubber stops; lower hinge is available for visual inspection. (Una bisagra superior y la bisagra inferior con topes de goma, la bisagra inferior está disponible para la inspección visual.) ✈ Connected by cables to the rudder pedals.(Conectado por cables a los pedales del timón.)
  • Flight Controls ✈ Ailerons ✈ Flaps ✈ Elevator ✈ Trim System ✈ Rudder
  • Landing Gear ✈ Nose Gear ✈ Main Gear ✈ Hydraulic System
  • Landing Gear Nose Wheel ✈ Free castering nose wheel (+/-60o) ✈ Sprung by elastomer package. (Surgido por conjuntos elastómero.) ✈ Tire pressure 1.8 bar or 26 psi.
  • Landing GearNose Gear Assembly
  • Landing Gear Main Wheels ✈ Hydraulically operated disk brakes act on the wheels of the main landing gear. ✈ Wheel brakes operated individually by means of toe pedals. ✈ Tire pressure 2.3 bar or 33 psi.
  • Hydraulic System
  • Landing Gear ✈ Nose Gear ✈ Main Gear ✈ Hydraulic System
  • Engine and AssociatedSystems ✈ Engine ✈ Fuel System ✈ Lubrication System
  • Powerplant ✈ Air cooled four-cylinder four-stroke engine.(Refrigerado por aire de cuatro cilindros de cuatro tiempos del motor.) ✈Horizontally opposed, fuel injected. ✈ Max power is 125 HP at 2800 rpm at Sea Level and Standard Atmospere.
  • Powerplant-Air Intake
  • Fuel System Fuel Pumps ✈ Equipped with both a mechanical and a 2 speed electric fuel pump. ✈ Mechanical pump used for fuel supply during normal operation. ✈ Electric pump is pilot controlled via the FUEL PUMP switch and should be on at engine start, during takeoff and landing, and during low throttle operations. Fuel Prime ✈ High speed setting of electric pump, used for engine start.
  • Fuel System Fuel Tank ✈ Located behind seats under baggage compartment. ✈ Two drains must be checked during the preflight inspection.
  • Fuel System
  • Lubrication System
  • Oil System ✈ During the first 50 hours of operation of a new or overhauled engine, mineral oil should be used. ✈ Oil Quantity: Minimum 4 Quarts. Maximum 6 Quarts. ✈ Oil Temperature: Maximum 240 F.
  • Engine and AssociatedSystems ✈ Engine ✈ Fuel System ✈ Lubrication System
  • Electrical System ✈ Storage Power is stored in a12 V 10 amp-hour or more lead-acid battery, mounted on the left hand side of the engine compartment.
  • Electrical System
  • Electrical System Power Generation ✈ ✈ Power is generated by a 40 ampere alternator, mounted on the front of the engine.
  • Ignition System During Start ✈ System powered by ‘SlickSTART’ electric start boost system. ✈ Delivers a shower of sparks during the engine start sequence to provide better ignition characteristics. After Start ✈ Uses a conventional magneto system.
  • Electrical System ✈ Battery/Storage ✈ Alternator/Generator ✈ Ignition
  • The Pitot Static System The Air Data Computer ✈ With respect to the G500, pitot static measurements are performed by the Air Data Computer. ✈ The airspeed and altimeter back-up instruments work on the same principle as standard pitot static instruments.
  • Pitot-Static System