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Ground School > Operation of Systems > Flashcards

Operation of Systems Flashcards

1
Q

What are the 4 main control surfaces and their functions?

A
  1. ELEVATORS - Control movement on the LATERAL axis. Otherwise known as Pitch.
  2. AILERONS - Control movement on the LONGITUDINAL axis. Otherwise known as Roll.
  3. RUDDER - Control Movement on the VERTICAL axis. Otherwise known as Yaw.
  4. TRIM - Small adjustable hinged surfaces on the aileron, rudder, or elevator that help the pilot relieve manual pressure on the controls.
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2
Q

What are flaps and what is their function?

A

Flaps are found on the trailing edges of the wings and may be extended downward into the flow of air beneath the wings to increase both lift and drag. They are meant to permit slower airspeed and steeper angle of descent.

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3
Q

Describe the landing gear system on our planes.

A

The landing gear consists of a tricycle type system, using two main wheels and a steerable nosewheel (20 degrees).
Main gear struts are provided shock absorption by tubular spring steel. Nose gear shock absorption is provided by an air/oil shock strut.

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4
Q

Describe the breaking systems on our planes.

A

Hydraulically actuated disc-type brakes are used on each main gear wheel. Hydraulic lines are connected to each rudder pedal and by applying pressure to the top of the pedals brakes will be applied.

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5
Q

What type of engine do our planes have?

A

Lycoming IO - 360 - B4A (IO meaning Fuel Injected, 360 meaning 360 cubic inches in size)
Rated at 180HP @ 2700 RPMs
4 Stroke Cycle
Naturally aspirated / Air cooled
Horizontally Opposed
Wet Sump (Engine sits on top of the oil)
Direct Driven (Propeller directly connected to the Crank Shaft)

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6
Q

What does the throttle do?

A

Allows the pilot to manually control the amount of fuel/air charge entering the cylinders. Allows you to manage engine power and speed.

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7
Q

What does mixture control do?

A

This regulates the fuel-to-air ratio. It is used to prevent the mixture being too rich while flying at high altitudes due to decreasing air density, and to lean the mixture during cross country fights to conserve fuel and optimum power.

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8
Q

Describe a fuel injection system installed in some aircraft.

A
  1. Engine driven fuel pump - Provides fuel under pressure from the fuel tank to the fuel/air control unit.
  2. Fuel/air control unit - Meters fuel based on mixture setting, then sends it to fuel manifold valve at a rate controlled by throttle.
  3. Fuel manifold valve - Distributes fuel to the individual fuel discharge nozzles.
  4. Discharge nozzles - Found in each cylinder head, they inject the fuel/air mixture at precise times for each cylinder directly into each intake port.
  5. Auxiliary Fuel Pump - For emergency use.
  6. Fuel pressure / flow indicators - Measures metered fuel flow/pressure.
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9
Q

What type of ignition system do our planes have?

A

Ignition is provided by two engine driven magnetos and two spark plugs per cylinder. (Completely independent of the electrical system)
Magnetos can sustain themselves but must be actuated by the battery to create the initial electrical current.

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10
Q

What is the purpose of fuel tank vents?

A

They provide a way of replacing fuel with outside air to prevent the formation of a vacuum. A vacuum forming in the fuel tank may affect fuel flow and lead to the engine cutting out entirely.

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11
Q

What type of fuel do our planes require? (Rating and color)

A

100LL (Low Lead) and the color is blue.

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12
Q

What other fuel types can be used if the required fuel grade is not available?

A

It is possible but not recommended, to use the next higher grade as a substitute. You should never use auto gas in aircraft engines unless it has been modified with an FAA-issued Supplemental Type Certificate (STC)

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13
Q

What color dye is used on the following fuel grades? 80, 100, 100LL Turbine.

A

80 (obsolete) - Red
100 (obsolete) - Green
100LL - Blue
Jet A (Turbine) - Colorless or Straw

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14
Q

If a non-turbine piston engine powered airplane is accidentally fueled with JET-A fuel, will it start?

A

Yes. The engine will run briefly but detonation and overheating will soon occur and cause power failure. Due to left over Avgas in the engine, the plane may taxi, run up, and even take off before experiencing the power failure.

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15
Q

Describe the electrical system on our planes.

A

Electrical energy is provided by a:
28-volt system
24-volt battery/and emergency battery
70-amp engine driven alternator

The electrical circuits are protected from overload by either circuit breakers or fuses or both. Both have the same function but circuit breakers can be reset while fuses must be reset.

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16
Q

The electrical system provides power for what equipment in the aircraft?

A
  1. Radio equipment
  2. Fuel Gauges
  3. Turn Coordinator
  4. Pitot Heat
  5. Interior and exterior lights
  6. Flaps (maybe)
  7. Stall warning system (maybe)
  8. Oil temperature gauge (maybe)
  9. Electric fuel pump (maybe)
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17
Q

Why is the generator/alternator voltage output slightly higher than the battery voltage?

A

The difference in voltage keeps the battery charged.

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18
Q

How does cabin heat work?

A

Fresh air enters the intake and is then heated by an exhaust shroud which is directed toward the cabin through various ducts.

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19
Q

What are the 3 basic functions of aircraft engine oil?

A

Lubricates - moving engine parts

Cools - the engine by reducing friction

Cleans - by carrying off metal and carbon particles and other oil contaminants.

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20
Q

What is detonation?

A

Detonation is an uncontrolled, explosive ignition of the fuel/air mixture within the cylinder’s combustion chamber. Causes piston, cylinder or valve failure. It can also cause overheating, roughness, or loss of power.

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21
Q

What can cause detonation?

A
  1. Using a lower than specified fuel grade
  2. Operating with extremely high manifold pressures in conjunction with low RPM
  3. Operating the engine at high power settings with an excessively lean mixture.
  4. Extended ground operations or steep climbs where cylinder cooling is reduced.
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22
Q

What actions should be taken when detonation is suspected?

A
  1. Make sure you are using the correct fuel grade.
  2. Use an enriched fuel mixture, and lower the climb angle to increase cylinder cooling during takeoff and climb.
  3. Avoid extended climbs at high power.
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23
Q

What is preignition?

A

Preignition occurs when the fuel/air mixture ignites prior to the engine’s normal ignition timing resulting in reduced power and high operating temperatures.
Usually caused by residual hot spot in the combustion chamber, often created by small carbon deposit on a spark plug. or any other damage to the cylinder.

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24
Q

What actions should be taken in the case of preignition?

A

Anything that would promote cooling
1. Reduce power
2. Reduce clime rate
3. Enrich fuel/air mixture

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25
Q

During pre-takeoff run up, you switch off the left magneto with the right magneto still on and notice there is no RPM drop. What condition does this indicate?

A

The left P-lead is not grounding, or the engine has been running on the right magneto because the left magneto has completely failed.

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26
Q

During a cross country flight you notice that the oil pressure is low, but the oil temperature is normal. What is the problem and what action should be taken?

A

A low oil pressure in flight could be the result of any one of several problems. The most common being that there is not enough oil. If the oil temperature continues to remain normal, a clogged oil pressure relief valve or an oil pressure gauge malfunction could be the cause.

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27
Q

What Instruments operate off of the pitot/static system?

A

Altimeter, Vertical Speed Indicator (VSI), and Airspeed Indicator (ASI)

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28
Q

How does an Altimeter work?

A

An Altimeter, is an aneroid barometer that measures the absolute pressure of the ambient air and displays it as feet above selected pressure level.
Aneroid Wafer expands as outside air pressure decreases and contracts as air pressure increases which bends the spring causing the needle to move.

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29
Q

Define and state how you would determine the following altitudes: absolute, indicated, pressure, true, and density.

A

Absolute Altitude - vertical distance between an aircraft and the surface.

Indicated Altitude - read directly from the altimeter after it is set to the current altimeter setting

Pressure Altitude - When the altimeter setting window is adjusted to 29.92. Used for computer solutions to determine density/true altitude, true airspeed, etc.

True Altitude - true vertical distance of aircraft above sea level (MSL)

Density Altitude - pressure altitude corrected for non standard temperature variations. Related to aircraft performance calculations.

30
Q

How does the airspeed indicator operate?

A

It is a gauge that measures the difference between impact pressure from the pitot head and undisturbed atmospheric pressure from the static source.

31
Q

What is the limitation of the airspeed indicator?

A

It needs proper flow of air in the pitot/static system to function properly.

32
Q

What are the errors of the airspeed indicator?

A

Position Error - Caused by static ports sensing the wrong static pressure, slipstream flow causes disturbances in the static port preventing actual atmospheric pressure measurement. It varies with airspeed, altitude, and configuration.
Density Error - Changes in altitude and temperature are not compensated for by the instrument.
Compressibility Error - Air packing into the pitot tube when flying at high speeds, this causes higher than normal readings on the ASI. Not a factor at slower speeds.

33
Q

What are the different types of air speeds?

A

Indicated Airspeed (IAS) - Airspeed observed on the indicator. No correction for any of the ASI errors.
Calibrated Airspeed (CAS) - Airspeed reading corrected for position, and instrument errors. CAS is equal to TAS at sea level and standard pressure.
True Airspeed (TAS) - CAS corrected for altitude and nonstandard temperature. The airspeed of the plane in relation to the air mass it is flying in.

34
Q

What are the difference airspeed limitations not marked on the face of the airspeed indicator?

A

Design maneuvering speed (Va)
Landing gear operating speed (VLo)
Best angle-of-climb speed (Vx)
Best rate-of-climb (Vy) -

35
Q

Define design maneuvering speed (Va)

A

The maximum speed the plane is designed to fly at without sustaining structural damage.

36
Q

Define landing gear operating speed (VLo)

A

The maximum speed for extending or retracting landing gear. Only applies for aircraft with retractable landing gear.

37
Q

Define best angle-of-climb speed (Vx)

A

The best angle to gain the most height in the shortest possible distance. (Used for short field take offs)

38
Q

Define best rate-of-climb (Vy)

A

The best speed to gain the most altitude in a given period of time.

39
Q

How does a vertical speed indicator work?

A

It is a pressure differential instrument. It has an aneroid wafer just like the airspeed indicator.
- Both the inside of the aneroid and instrument itself are vented to the static system.
- But the case is also vented through a calibrated leak that causes pressure inside to change more slowly than inside the aneroid
- As the plane ascends, the pressure entering the calibrated leak is lower than what is inside the aneroid causing the pressure inside the case to compress the aneroid causing the needle to move up on the indicator.

40
Q

What are limitations of the vertical speed indicator (VSI)?

A

The VSI will not be accurate until the aircraft is stabilized. This is because of the restricted airflow to the static line. rough control or turbulent conditions will cause for inaccurate readings.

41
Q

Which instruments contain gyroscopes?

A
  1. Turn Coordinator
  2. Heading Indicator (Directional Gyro)
  3. Attitude Indicator (Artificial Horizon)
42
Q

What are the two fundamental properties of a gyroscope?

A
  1. Rigidity in Space
  2. Gyroscopic Precession
43
Q

What is rigidity in space?

A

it refers to when a gyroscope remains in a fixed position in the plane in which it is spinning.

44
Q

What is gyroscopic precession?

A

it refers to the turning or tilting of a gyro in response to a deflecting force.
The reaction to this force isn’t felt until 90 degrees later in the direction of rotation.

45
Q

What kind of power sources may be used to power gyroscopic instruments?

A
  • In some airplanes, all gyros are vacuum, pressure, or electrically operated
  • In other airplanes, vacuum or pressure is used only for heading and attitude while the turn coordinator is electrical.
46
Q

How does the vacuum system operate?

A

An engine driven vacuum pump provides suction which pulls air from the instrument case. Normal pressure entering the case is directed to rotor vanes and in turn spins the gyro at high speeds like a waterwheel. Air is drawn in from the cockpit and vented outside.

47
Q

How does the attitude indicator work?

A

There is a gyro in the instrument mounted on the horizontal plane and depends on the principle of rigidity in space to function. The horizon bar on the indicator represents the true horizon and is fixed to the gyro, and remains in the same position as the airplane rotates around it.

48
Q

What are the limitations of an attitude indicator?

A

The pitch and bank limits depend upon the make and model of the instrument. If either limit is exceeded, the instrument will tumble/spill and give incorrect readings until it is reset. Many modern indicators do not tumble at all.

49
Q

What are the errors of the attitude indicator?

A

Attitude indicators are free from most errors, but depending on the speed that the erection system functions, you may notice a slight nose-up indication during rapid acceleration and a nose-down indication during rapid deceleration. Other small errors like these will correct themselves after about a minute after returning to straight-and-level flight.

50
Q

How does the heading indicator operate?

A

The heading indicator depends on on the principle of rigidity in space. A rotor turns in a vertical plane and the compass card is fixed to the rotor. Since the rotor remains rigid in space, the points on the card hold the same position in space in relation to the vertical plane. As the the instrument case and plane revolve around the vertical axis, the card provides accurate heading information.

51
Q

What are the limitations of the heading indicator?

A

The pitch and bank limits depend upon the make and model of the instrument. If either limit is exceeded, the instrument will tumble/spill and give incorrect readings until it is reset. It can be reset using the caging knob. Many modern indicators do not tumble or spill at all.

52
Q

What error is the heading indicator subject to?

A

Because of precession caused mainly by friction, the heading indicator will creep or drift away from its current setting.

53
Q

How does the turn coordinator operate?

A

The turn part of the instrument uses the principle of precession to indicate the direction and approximate rate of turn. A gyro reacts by trying to move in reaction to the force applied thus moving the needle or mini aircraft in proportion to the rate of turn. The slip/skid indicator (otherwise known as the “ball”) is a liquid-filled tube with a ball that reacts to centrifugal force and gravity.

54
Q

What information does the turn coordinator provide?

A

The turn coordinator shows the yaw and roll of the aircraft around the vertical and longitudinal axis.

55
Q

What will the turn indicator indicate when the aircraft is in a “skidding” or a “slipping” turn?

A

Skid - The ball will be to the outside of the turn; turning too fast for the amount of bank
Slip - The ball will be on the inside of the turn; turning too slow for the amount of bank

56
Q

How does the magnetic compass work?

A

Magnetized needles fastened to a float assembly, a compass card is mounted around it. The needles then align themselves parallel to the earth’s lines of magnetic force. The liquid inside of the compass is white kerosene.

57
Q

What limitations does the magnetic compass have?

A

The type of mounting allows the float freedom to rotate and tilt up to approximately 18 degrees angle of bank. After this point, the indications become erratic and unpredictable.

58
Q

What is an ADC?

A

Air Data Computer. An aircraft computer that receives and processes all air and atmosphere related data (pitot pressure, static pressure, and temperature). It uses this information to calculate altitude, indicated airspeed, true airspeed, vertical speed, and air temperature.

58
Q

What are the various compass errors?

A

Oscillation error - erratic movement of the compass card caused by turbulence or rough control.
Deviation error - Due to electrical and magnetic disturbances in the aircraft.
Variation error - Angular difference between true and magnetic north. (Isogonic lines)
Dip errors:
Acceleration error - On east or west headings, while accelerating, the magnetic compass shows a turn to the north, and when decelerating, it shows a turn to the south.
Remember: ANDS
A - Accelerate
N - North
D - Decelerate
S - South

Northerly turning error - the compass leads in the south half of a turn and lags in the north half of a turn.
Remember: UNOS
U - Undershoot
N - North
O - Overshoot
S - South

59
Q

What is a AHRS?

A

Attitude and Heading Reference System. Composed of three axis sensors providing heading, attitude, and yaw information to the aircraft. Designed to replace mechanical gyroscopic flight instruments for better reliability and accuracy.

60
Q

What is a PFD?

A

Primary Flight Display.

61
Q

What is a MFD?

A

Multi-Function Display.

62
Q

What is a FD?

A

Flight Director.

63
Q

What is a FMS?

A

Flight Management System.

64
Q

What is a INS?

A

Inertial Navigation System.

65
Q

What is the function of a magnetometer?

A

It is a device that measures the strength of the earth’s magnetic field to determine the aircraft heading. It provides this information digitally to the AHRS which is then projected to the PFD.

66
Q

Which standby flight instruments are normally provided in an advanced avionics aircraft?

A

Every aircraft equipped with electronic flight instruments must also have a minimal set of backup instruments. Usually conventional “round dial instruments” that typically include a attitude indicator, an airspeed indicator, and an altimeter.

67
Q

If one display fails (PFD or MFD), what information will be presented on the remaining display?

A

Some systems allow you to reverse the displays which will display primary flight instruments and engine gauges on the remaining operative display.

68
Q

What display information will be affected when an ADC failure occurs?

A

Inoperative airspeed, altitude, and vertical speed indicators, shown with red Xs on the PFD.

69
Q

What display information will be affected when an AHRS failure occurs?

A

Inoperative attitude indicator, shown with a red X on the PFD.

70
Q

For aircraft with electronic flight instruments, what is the function of the standby/emergency battery?

A

The standby battery is held in reserve and kept charged in case of a failure of the charging system and eventual exhaustion of the main battery.

71
Q

What are the two types of ADS-B equipment?

A

Automatic Dependent Surveillance - Broadcast Out (ADS-B Out) – automatically broadcasts the aircrafts GPS position, altitude, velocity, and other information out to ATC and other aircraft. Required in all airspaces where transponders are required.
Automatic Dependent Surveillance - Broadcast In (ADS-B In) – is the receipt, processing, and display of ADS-B transmissions. Needed to receive information from ADS-B Out and other broadcasting services.

Ground School (4 decks)

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