AGK Flashcards
pitot static instruments
airspeed indicator / altimeter / vertical speed indicator
gyroscopic instruments
attitude indicator / turn coordinator / heading indicator
force used to determine airspeed
dynamic pressure
dynamic pressure is equal to
(P total - P static) or (Pitot tube - static port)
ambient atmospheric pressure || pressure exerted in all directions
static pressure
measures total pressure
pitot tube
measures static pressure
static port
device for measuring the forward speed of the aircraft
airspeed indicator
speed read on the ASI
indicated airspeed
IAS corrected for installation and instrument error
calibrated airspeed
CAS corrected for altitude and non-standard temperature
true airspeed
TAS adjusted for wind
ground speed
instrument for determining altitude
altimeter
altitude read on the altimeter
indicated altitude
actual height above mean sea level
true altitude
actual height of the airplane above the Earth’s surface over which it is flying
absolute altitude
altitude when altimeter is set to 29.92 in Hg
pressure altitude
altitude corrected for non standard temperature
density altitude
QNH
query nautical height || local altitude pressure
QNE
query nulla est || 29.92 in Hg is set at higher altitudes
QFE
query field elevation || altimeter should display 0 when landed
instrument that indicates the rate of climb or descent
vertical speed indicator
if pitot tube is blocked
total pressure is undetermined / altimeter and airspeed moves the same way
it static port is blocked
static pressure is unknown / altimeter, vsi, and asi will be inaccurate
characteristic of a gyroscope
fast spinning
principles of a gyroscopic instrument
rigidity in space / precession
tilting/turning as a result of external forces
precession
instrument used to reference the aircraft’s pitch and bank against an artificial horizon
attitude indicator
instrument that displays the rate of turn and is used to determine the coordination of a turn and the bank angle required for a specific rate of turn
turn coordinator
standard rate of turn
360 degrees in 2 minutes / 3 degrees per second
coordinated turn
rate of turn and bank angle are proportionate (step on the ball)
skid
rate of turn is too great for the bank angle (ball out of turn)
slip
rate of turn is too slow for the bank angle (ball towards the turn)
instrument used to determine aircraft direction to aid the pilot in navigation
heading indicator
seventh instrument that is self contained and does not require to be checked for leaks
magnetic compass
magnetic compass is filled with what fluid
ethyl alcohol
why is magnetic compass filled with fluid
to avoid freezing at lower temperatures and dampen the oscillation of the float and card
latitude and longitude are based on true directions meaning they provide a constant horizontal and vertical plane with which to reference on maps and charts
variation
line that connects points of equal variation on a map
isogonic line
line that has a variation of 0 degrees
agonic line
best way to remember variation errors in magnetic compass
west is best, east is least
local magnetic fields in an aircraft is caused by electrical current flowing in the structure, in nearby wing, or any magnetized part of the structure cause a compass error
deviation
compass tends to dip toward the magnetic pole, most dominant as latitude increases
magnetic dip
when turning from a northerly heading
the compass will initially turn the opposite direction and then catch up by due east/west
when turning from a southerly heading
the compass will indicate a turn in the proper direction but will lead the actual heading, slowing down by due east/west
when the aircraft accelerates on a heading of east/west
inertia causes the weight to lag, and the card rotates toward north
when the aircraft decelerates on a heading of east/west
inertia causes the weight to move ahead, and the card rotates to the south
provides the necessary source of power for the flight of airplanes
powerplant
engines used by light airplanes that are higher, simpler, and cost effective
reciprocating engines
ignites a mixture of air and fuel
spark plug
used for spark ignition for reciprocating engines for airplanes
spark plug
involves compressing the mixture to raise its temperature to a point where automatic ignition occurs, such as in diesel engines
compression ignition
types of cylinder arrangements
radial / inline / v-type / opposed
types of operating cycle
two stroke / four stroke
methods of cooling
liquid cooled / air cooled
poor power to weight ratio || if air cooled, the rear cylinders receive much less cooling air
inline engine
very compact, has minimal weight, and excellent air cooling || frontal large area is a penalty for performance
radial engine
extremely powerful || a complex machinery that requires a liquid cooling system
v-type engine
widely used engine in light airplanes || light and compact || has limited power
opposed type engine
main components of a reciprocating engine
crankshaft / crank case / connecting rod / cylinder / piston / spark plug / exhaust valve / intake valve
four stroke cycle
intake / compression / power / exhaust
indicates the revolutions per minute performed by the crankshaft
tachometer
aircraft needs more ______ than _______
torque , power
controls the RPM
throttle
regulates the amount of fuel and air mixture sent to the cylinders
throttle
progressive burning of the whole mixture contained in the cylinder, from the moment it is ignited by the spark plugs, to the point where the exhaust valves are open
normal combustion
ensures a smooth build up of temperature and pressure and guarantees that the engine delivers the maximum possible power
normal combustion
an uncontrolled, explosive combustion of the mixture, which may cause excessive pressures and temperatures in the combustion chamber, and excessive stress onto the piston, cylinder, and valves
detonation
cause of detonation
lower than usual fuel octane/compression ratio of fuel
occurs when the mixture ignites ahead of the normal timing
pre-ignition
cause of pre-ignition
residual hot spot in the combustion chamber
how to clean deposits
push for higher rpm, lean the mixture
high temperatures may cause fuel to vaporize inside the fuel lines or the carburetor, forming bubbles which cause momentary losses of power or even stall the engine
vapor lock
caused by contamination of fuel by water
fuel lock
changes in temperature may cause the condensation of the humidity contained in the air from the fuel tanks, particularly if partially filled
fuel lock
this system’s purpose is to mix air from the outside with fuel in correct proportions before sending this mixture to the cylinders
induction system
fuel and air are mixed before it is sent towards the intake manifold
carburetor
fuel is injected directly into the cylinders directly into the cylinders
fuel injection
carburetor icing indication
gradual loss of power followed by engine roughness
carburetor icing temperature and humidity
21 C and 70% humidity
cold air - density relationship
cold air = more dense = cold air sinks
hot air - density relationship
hot air = less dense = hot air rises
methods used to restore a higher air pressure and thus greatly improve performance
turbocharging and supercharging
incorporates a turbine, which is driven by exhaust gases, and a compressor that pressurizes the incoming air
turbocharger
system that provides the spark needed to ignite the fuel and air mixture in the combustion chamber
ignition system
parts of the ignition system
magnetos / spark plug / ignition switch / wirings
source of electrical power at the center of the ignition system
magnetos
engine driven device totally independent from the airplane’s electrical system
magnetos
system that keeps the temperature of the running engine has to be kept within acceptable limits
engine cooling
system that lubricates the engine’s moving parts, reducing both wear and running temperature
oil system
oil is contained in a separate tank, circulated through the engine with the help of a pump
dry sump oil system
all oil is carried in a sump which is an integral part of the engine
wet sump oil system
designed to provide an uninterrupted flow of clean fuel from the fuel tanks to the engine, in all conditions of flight, and during all approved maneuvers
fuel system
uses the force of gravity to transfer fuel to the engine
gravity feed system
used to vaporize fuel directly into the cylinders during cold starts
fuel primer
engine driven pump draws fuel from the tanks and sends it to the engine
fuel pump system
used during engine start, for fuel pump system, and in the event the main fuel pump fails
electric pump
avgas 100 color
green
avgas 100LL color
blue
system that supplies electricity to all aircraft systems apart from the engine
electrical system
components of an electrical system
alternator / battery / battery switch / alternator switch / bus bar / voltage regulator / ammeter / all associated wiring
AC explanation
two way current
DC explanation
one way current
part of the electrical system driven by the engine’s crankshaft through a belt
alternator
stores a limited quantity of electricity used before engine start and in case of emergency
battery
monitors the airplane’s electrical system
ammeter
ammeter full scale minus
alternator has failed
ammeter full scale plus
regulator has failed
two part switch controlling both the alternator and the battery
master switch
comprises of switches and the fuses and/or circuit breakers associated with the various electrical systems
bus bar
an airfoil subjected to aerodynamic principles such as drag or stall
propeller
thrust through the propeller depends on
shape of the propeller / angle of attack / rpm of the engine
angle of incidence of a propeller blade
pitch
part of the propeller that allows for uniform thrust to be created from hub to tip
twist
effect of small pitch propeller
more efficient during climb
effect of high pitch propeller
high speed and low fuel consumption during cruise
propeller that allows to vary the pitch
constant pitch propeller
part of the propeller that automatically adjusts the pitch during cruise to maintain constant RPM despite changing air loads
governor
type of propeller wherein power controlled by the throttle is monitored by a manifold pressure gauge
constant speed propeller
