A102

GFRP

CFRP

Body of the aircraft

Primary lift generating component of an aircraft

Triangular material, attached to the leading edge of a wing towards the root area. Designed to induce turbulent airflow at higher angles of attack, resulting in a stall in that particular section of the wing.

Delay airflow separation from the upper surface of the wings and increase control surface effectiveness, throughout most phases of flight.

Gives longitudinal control

Gives lateral control

Gives yaw control

Degree of castering nose wheel

Tire pressure

Four stroke operating cycle

Covers the powerplant

Attaches below the front of the engine and is an entry point for air

Converts brake horsepower from the engine into thrust

Force that moves the aircraft through the air

Aligns itself with the magnetic axis formed by the N/S magnetic field of the earth

Provides system pressure indications to the pilot

Reads and displays the rotations per minute (RPMs) of the engine

Shows the aircraft's indicated airspeed in nautical miles per hours (kts)

Shows pitch and roll

Indicates an aircraft's MSL altitude by sensing pressure changes

Displays aircraft's position in relation to a selected course

Shows when the airplane is slipping or skidding

Shows the direction of the plane in relation to a preset heading

Gives an indication of rate of climb or descent based on deviation from a constant pressure level

Shows the current flowing between the battery and the main bus

Shows voltage on the main bus

Number of separate brake systems

Fuel filter bowl; Acts as a trap for sediment and water that has entered the fuel line from the tank

Provides induction air to the engine cylinders and air to the heater and defroster

Supplies air to the air distribution system

Number of air intake openings

Supplies air through a filter assembly and large flexible hose to the engine intake manifold

Supplies unfiltered air through a duct and large flexible hose to the heat-exchanger on the muffler

Alternate air intake

Pneumatic System source

Pneumatic System carrier

Pneumatic System user

Pneumatic System pump

Pneumatic System bypass

Pneumatic System filter

Fuel system source

Fuel system carrier

Fuel system user

Fuel system pump(s)

Fuel system bypass

Fuel system filter

Brake system source

Brake system carrier

Brake system user

Brake system pump

Brake system bypass

Brake system filter

Number of ignition systems

Components of the ignition system

Positions of ignition switch

Left/Right magnetos connect to which spark plugs?

What happens when the ignition switch is turned to START and the GEN/BAT is on?

Ignition system pathway

Oil system source

Oil system carrier

Oil system user

Oil system pump

Oil system bypass

Oil system filter

Oil system pathway

2 sources of electrical power

Supplies power for the system under normal operation

Type of electrical system

Electrical system source

Electrical system carrier

Electrical system user

Electrical system pump

Electrical system bypass

Electrical system filter

Components of the pitot-static system

Supplies pitot pressure and static pressure to the air data instruments

Supplies transponder for Mode C operation and the the GPS for altitude input

Directs ram air through the exhaust heat shroud into the valve

3 standard warnings

8 major components

Primary flight controls

Reciprocating engines: Four strokes

Basic parts of a propeller

Returns vapors to the gas tank

Delivers fuel to the throttle body

Specified fuel for the DA-20

Stabilizes, divides, and routes air proportionally to each of the four engine cylinders

Ignition system source

Ignition system carrier

Ignition system user

Ignition system pump

Ignition system bypass

Ignition system filter

Oil weight per gallon

3 types of oil that can be used in the DA-20

Voltmeter close to 12

Voltmeter close to 14

Two functions of the vernatherm