The document provides an overview of the key systems on a DA20 aircraft, including the airframe construction, flight controls, landing gear, engine and associated systems, electrical and navigation systems, and emergency procedures. It describes the composite material construction of the airframe and various control surfaces like the ailerons, flaps, elevator and rudder. It also outlines the hydraulic systems, fuel and lubrication systems, electrical power generation and ignition. Performance charts and annunciations/alerts are also mentioned.

1. DA20-C1
Systems Introduction

2. DA20 Systems
Introduction
✈ 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

3. 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

4. Flight Controls
✈ Ailerons
✈ Flaps
✈ Elevator
✈ Trim System
✈ Rudder

5. 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)

6. Flight Controls
Aileron Assembly
INSERT PICTURE HERE

7. 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.

8. 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)

9. Flight Controls
Flap Assembly

10. 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.)

11. Flight Controls
Elevator Assembly

12. Flight Controls
Trim System Assembly

13. 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.)

14. Flight Controls
✈ Ailerons
✈ Flaps
✈ Elevator
✈ Trim System
✈ Rudder

15. Landing Gear
✈ Nose Gear
✈ Main Gear
✈ Hydraulic System

16. 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.

17. Landing Gear
Nose Gear Assembly

18. 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.

19. Hydraulic System

20. Landing Gear
✈ Nose Gear
✈ Main Gear
✈ Hydraulic System

21. Engine and Associated
Systems
✈ Engine
✈ Fuel System
✈ Lubrication System

22. 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.

23. Powerplant-Air Intake

24. 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.

25. Fuel System
Fuel Tank
✈ Located behind seats under baggage compartment.
✈ Two drains must be checked during the preflight inspection.

26. Fuel System

27. Lubrication System

28. 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.

29. Engine and Associated
Systems
✈ Engine
✈ Fuel System
✈ Lubrication System

30. 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.

31. Electrical System

32. Electrical System
Power Generation
✈
✈ Power is generated by a 40 ampere alternator, mounted on the front of the
engine.

33. 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.

34. Electrical System
✈ Battery/Storage
✈ Alternator/Generator
✈ Ignition

35. 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.

36. Pitot-Static System