Airplane Systems Flashcards

You may prefer our related Brainscape-certified flashcards:
1
Q

How are the various flight controls operated? /

A
  • The flight control surfaces are manually actuated through use of either a rod or cable system.
  • A control wheel actuates the ailerons and elevator, and rudder/brake pedals actuate the rudder.
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
2
Q

What type of trim system is installed in this airplane? 1

A

Both rudder and elevator trim are provided. They are both manually actuated. KNOW Your PLANE

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
3
Q

What are flaps, and what is their function?

A
  • The wing flaps are movable panels on the inboard trailing edges of the wings.
  • Increase both lift and drag
  • Permit a slower airspeed and a steeper angle of descent during a landing approach
  • Used to shorten the takeoff di s tance.
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
4
Q

Describe a typical wing flap system.

A

Know your plane.

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
5
Q

State some examples of leading edge lift devices. ~ (FAA-H-8083-31)

A
  • Slots
    • Directs high-energy air from under the wing to the airflow above the wing,
    • accelerating upper airflow to allow airflow separation will be delayed to higher angles of attack
    • allows lift at high AOA.
  • Slats:
    • They may be movable or fixed .
    • At low angles of attack , movable slats are held flush against the leading edge by positive air pressure.
    • At high angles of attack, the slats a removed forward either by the pilot or automatically by the low pressures present at the leading edge .
    • Slats provide the same results as slots .
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
6
Q

What are spoilers? (FAA-H-8083-31)

A
  • Located on the upper surface of a wing
  • reduce lift by “spoiling” the airflow above the wing.
  • used as speed brakes to slow an airplane down, both in flight as well as on the ground immediately after touchdown.
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
7
Q

What instruments operate from the pitot/static system?

A
  • altimeter
  • vertical speed indicator
  • airspeed indicator.
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
8
Q

Does this aircraft have an alternate static airsystem? ✓

A
  • Yes.
  • used In the event of external static port blockage
  • Know your airplane
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
9
Q

How does an altimeter work? (FAA-H-8083-15}

A

Aneroid wafers in the instrument expand and contract a s atmospheric pressure changes, and through a shaft and gear linkage , rotate pointers on the dial of the instrument.

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
10
Q

A pressure altimeter is subject to what limitations?

A

Non-standard pressure and temperature:

Temperature variations expand or contract the atmosphere and raise or lower pressure levels that the altimeter senses.

  • On a warm day -The pressure level is higher than on a standard day. The altimeter indicates lower than actual altitude.
  • On a cold day -The pressure level is lower than on a standard day. The altimeter indicates higher than actual altitude.

Changes in surface pressure also affect pressure levels at altitude.

  • Higher than standard pressure-The pressure level is higher than on a standard day. The altimeter indicates lower than actual altitude.
  • Lower than standard pressure-The pressure level is lower than on a standard day. The altimeter indicates higher than actual altitude.
  • Remember: High to low or hot to cold , look out below!
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
11
Q

Define and state how you would determine the following altitudes. (FAA-H-8083-25)

A

Indicated altitude: the altitude read directly from the altimeter (uncorrected)

Pressure altitude: the height above the standard datum plane indicated when the altimeter setting window is adjusted to 29.92 .

  • It is used for computer solutions to determine density altitude, true altitude, true airspeed .

True altitude-the true vertical distance of the aircraft above sea level.

  • Airport, terrain, and obstacle elevations found on aeronautical charts are true altitudes.

Density altitude - pressure altitude corrected for non standard temperature variations.

  • Directly related to an aircraft’s takeoff, climb, and landing performance.

Absolute altitude - the vertical distance of an aircraft above the terrain .

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
12
Q

How does the airspeed indicator operate? (FAA-H-8083-25)

A

It measures the difference between the impact pressure from the pitot head and atmospheric pressure from the static source.

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
13
Q

What are the limitations of the airspeed indicator? (FAA-H-8083-25)

A

The airspeed indicator is subject to proper flow of air in the pitot/ static system.

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
14
Q

The airspeed indicator is subject to what errors?

A

Position error:

  • Caused by the static ports sensing erroneous static pressure;
    • slipstream flow causes disturbances at the static port, preventing actual atmospheric pressure measurement. It varies with airspeed, altitude, and configuration, and may be a plus or minus value.

Density error-Changes in altitude and temperature are not compensated for by the instrument.

Compressibility error-Caused by the packing of air into the pitot tube at high airspeeds, resulting in higher than normal indications. It is usually not a factor.

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
15
Q

What are the different types of aircraft speeds?

A

Indicated Airspeed (IAS):the speed of the airplane as observed on the airspeed indicator. It is the airspeed without correction for indicator, position (or installation), or compressibility errors. Calibrated Airspeed (CAS)-the airspeed indicator reading corrected for position (or installation), and instrument errors. CAS is equal to T AS at sea level in a standard atmosphere. The colorcoding for various design speeds marked on airspeed indicators may be IAS or CAS.

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
16
Q

How does an altimeter work? (FAA-H-8083-15)

A

Aneroid wafers in the instrument expand and contract as atmospheric pressure changes, and through a shaft and gear linkage, rotate pointers on the dial of the instrument.

17
Q

A pressure altimeter is subject to what limitations?

A

Non-standard pressure and temperature:

a. Temperature variations expand or contract the atmosphere and raise or lower pressure levels that the altimeter senses.

On a warm day-The pressure level is higher than on a standard day. The altimeter indicates lower than actual altitude.

On a cold day-The pressure level is lower than on a standard day.

The altimeter indicates higher than actual altitude.

b. Changes in surface pressure also affect pressure levels at altitude.

Higher than standard pressure-The pressure level is higher than on a standard day. The altimeter indicates lower than actual altitude.

Lower than standard pressure-The pressure level is lower than on a standard day. The altimeter indicates higher than actual altitude.

Remember: High to low or hot to cold, look out below!

18
Q

Define and state how you would determine the following altitudes. (FAA-H-8083-25)

A

Indicated altitude-the altitude read directly from the altimeter (uncorrected) after it is set to the current altimeter setting.

Pressure altitude-the height above the standard datum plane indicated when the altimeter setting window is adjusted to 29.92. It is used for computer solutions to determine density altitude, true altitude, true airspeed.

True altitude-the true vertical distance of the aircraft above sea level. Airport, terrain, and obstacle elevations found on aeronautical charts are true altitudes.

Equivalent Airspee d (EAS) - the air speed indicator reading corrected for position (or in stallation), or instrument error, and for adiabatic compressible flow for the particular altitude. EAS is equal to CAS at sea level in standard atmos phere.

True Air speed (TAS): CAS corrected for altitude and non standard temperature; the speed of the airplane in relation to the air mass in which it is flying.

19
Q

What airspeed limitations apply to the color-coded marking system of the airspeed indicator?

A

x

20
Q

What are some examples of important airspeed limitations that are not marked on the face of the airspeed indicator, but are found on placards and in the AFM or POH? (FAA-H-8083-25}

A

X

21
Q

How does the vertical speed indicator work? (FAA-H-8083-15)

A
  • The vertical speed indicator is a pressure differential instrument.
  • Inside the instrument case is an aneroid very much like the one in an airspeed indicator.
  • the case is vented through a calibrated orifice that causes the pressure inside the case to change more slowly than the pressure inside the aneroid.
  • shows a climb and indicating the number of feet per minute the aircraft is ascending.
22
Q

What are the limitations of the vertical speed indicator?

A

It is not accurate until the aircraft is stabilized.

23
Q

Which instruments contain gyroscopes?

A
  • turn coordinator
  • heading indicator
  • attitude indicator
24
Q

What are the two fundamental properties of a gyroscope?

A

Rigidity in space - A gyroscope remains in a fixed position in the plane in which it is spinning.

Precession -The tilting or turning of a gyro in response to a deflective force . The reaction to this force does not occur at the point where it was applied; it occurs at a point 90° later in the direction of rotation.

25
Q

What are the various sources that may be used to power the gyroscopic instruments in an airplane?

A
  • vacuum or pressure systems provide the power for the heading and attitude indicators,
  • the electrical system provides the power for the turn coordinator.
26
Q

How does the vacuum system operate?

A
  • Air is drawn into the vacuum system by the engine-driven vacuum pump.
  • It first goes throug h a filter, which prevents foreign matter from entering the vacuum or pressure system.
  • The air then moves through the attitude and heading indicators, where it causes the gyros to spin.
  • A relief valve prevents the vacuum pressure, or suction, from exceeding prescribed limits .
  • After that, the air is expelled overboard or used in other systems , such as for inflating pneumatic deicing boots.
27
Q

How does the attitude indicator work? (FAA-H-8083-25)

A
  • The attitude indicator’s gyro is mounted on a horizontal plane
  • and depends upon rigidity in space for its operation.
  • The fixed gyro remains in a horizontal plane as the airplane is pitched or banked about its axis , indicating the attitude of the airplane relative to the true horizon
28
Q

Discuss the limits of an attitude Indicator.

A

If limit is exceeded, the instrument will tumble or spill giving incorrect indications until reset. Some modern attitude indicators will not tumble.

29
Q

The attitude indicator is subject to what errors?

A
  • Attitude indicators are free from most errors,
  • but depending on the speed with which the erection system functions, there may be a slight nose- up indication during a rapid acceleration and a nose-down indication during a rapid deceleration.
  • There is also a possibility of a small bank angle and pitch error after a 180° turn.
  • These inherent errors are small and correct themselves within a minute or so after returning to straight-and-level flight.
30
Q

How does the heading indicator operate?

A
  • It uses the principle of rigidity in space;
  • the rotor turns in a vertical plane, and the compass card is fixed to the rotor.
31
Q

What are the limitations of the heading indicator?

A
  • Limits in the banking plane are usually from 100 degrees to 110 degrees, and the pitch limits are usually from 60 to 70 degrees.
  • If either limit is exceeded, the instrument will tumble or spill and will give incorrect indications until realigned.
  • A number of modern attitude indicators do not tumble