DA20-C1Systems Introduction
DA20 Systems Introduction
✈ Airframe (FUSELAJE)
✈ Flight Controls
✈ Landing Gear and Hydraulics
✈ Engine and Associated Systems
✈ Electric and Navigation Systems
✈ What we’ll look at...
Aircraft Operating Limitations✈
✈ Emergency Procedures
✈ Performance Charts
✈ Annunciations and Alerts
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
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)
✈
Ailerons
Flight Controls
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Aileron Assembly
Flight Controls
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.
✈
Flaps
Flight Controls
Flaps electrically operated - 3 settings: cruise (UP), takeoff - 15o
(T/O),
landing - 45o (LDG).
✈
Flap Settings
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 Controls
Elevator Assembly
Flight Controls
Trim System Assembly
Flight Controls
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.)✈
Rudder
Flight Controls
✈ Ailerons
✈ Flaps
✈ Elevator
✈ Rudder
✈ Trim System
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 Gear
Nose Gear Assembly
Landing Gear
Main Wheels
✈Wheel brakes operated individually by means of toe pedals.
✈ Hydraulically operated disk brakes act on the wheels of the main
landing gear.
Tire pressure 2.3 bar or 33 psi.✈
Hydraulic System
Landing Gear
✈ Nose Gear
✈ Main Gear
✈ Hydraulic System
✈ Engine
✈ Fuel System
✈ Lubrication System
Engine and Associated Systems
Powerplant
✈
Horizontally opposed, fuel injected.
✈ Air cooled four-cylinder four-stroke engine.(Refrigerado por aire de
cuatro cilindros de cuatro tiempos del motor.)
Max power is 125 HP at 2800 rpm at Sea Level and Standard Atmospere.
✈
Powerplant-Air Intake
Fuel System
Fuel Pumps
✈Mechanical pump used for fuel supply during normal operation.
Equipped with both a mechanical and a 2 speed electric fuel pump.✈
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.
✈
High speed setting of electric pump, used for engine start.✈
Fuel Prime
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
✈ Oil Quantity:
Minimum 4 Quarts.
Maximum 6 Quarts.
✈ During the first 50 hours of operation of a new or overhauled
engine,
mineral oil should be used.
✈ Oil Temperature:Maximum 240 F.
Engine and Associated Systems
✈ 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 is generated by a 40 ampere alternator, mounted on the
front of the engine.
Power Generation
Ignition System
During Start
After Start
System powered by ‘SlickSTART’ electric start boost system.✈
✈ Delivers a shower of sparks during the engine start sequence to
provide better ignition characteristics.
Uses a conventional magneto system.✈
Electrical System
✈ Ignition
✈ Alternator/Generator
✈ Battery/Storage
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
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