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

INSERT PICTURE HERE

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