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Aviation > Instruments - 6 Pack > Flashcards

Instruments - 6 Pack Flashcards

1
Q

In a standard return, how many degrees of heading change does the aircraft move every second?

A

Three degrees. It takes 2 minutes to turn 360°

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2
Q

Inclinometer

A

The glass level containing the black ball

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3
Q

Difference between a turn coordinator and a turn and Bank indicator

A

Turn on Bank in Decatur, also known as the turn and slip indicator, can only indicate yaw while the turn coordinator will indicate both of yawing motion and a rolling motion

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4
Q

Define turn quality

A

A quality turn is one that is “coordinated“.

In a coordinated turn, the centrifugal Force must be equal to the force of gravity acting on the ball. If that is equal, than the ball will remain in the center.

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5
Q

Define skid

A

Too much rudder, or not enough bank for the rate of turn

The center fugal force is greater than the force caused by gravity

ball moves towards the outside of the inclinometer

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6
Q

Define slip

A

Insufficient rudder Or too much bank for the rate of turn

The force caused by gravity is greater than the centrifugal force

The ball rolls to the inside of the inclinometer

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7
Q

Slipping and Skidding turns

A
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8
Q

Rule of thumb for Standard Rate Turn

A

• The bank required to fly a standard rate turn varies with
airspeed
Faster airspeed requires a greater bank to complete a similar
rate of turn as that performed at a lower airspeed.

Rule of thumb:
The bank angle needed for a standard rate turn can be
estimated by the formula:
•Bank Angle = (KTAS / 10) + 7
• Example 120 / 10 + 7 = 19°
• Bank angle required at 120 KTAS is 19°
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9
Q

The airspeed indicator is connected to

A

The petot tube and the static port

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10
Q

Air Speed Indicator

A

This instrument measures the aircraft speed through the air.

It is connected to both the Peto tube and the static port

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11
Q

Airspeed Indicator - how it works

A

ASI uses only Dynamic Pressure to indicate airspeed.

Pitot tube measures both Dynamic and Static Pressure.

Static port measures only Static Pressure.

The static port pressure resist the diaphragm from expanding therefore equalizing or subtracting the static pressure and leaving only the dynamic pressure.

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12
Q

Indicated airspeed (IAS)

A

The speed that we read directly off the dial of the airspeed indicator.

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13
Q

Major errors of the Airspeed Indicator

A

Positional Error
Compressibility Error
Density Error

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14
Q

Positional error

A

An error that is caused by the position of the pitot tube.

Air turbulence around aircraft can cause eddies and five incorrect readings - so we position pitot tube as far forward as possible on wings.

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15
Q

Calibrated airspeed (CAS)

A

If we correct IAS for Positional Error, we get this.

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16
Q

Compressibility error

A

Introduced at speeds greater than 250 kn,

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17
Q

Equivalent airspeed (EAS)

A

We get this when we correct calibrated airspeed for compressibility errors

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18
Q

Density error

A

This error is caused by changes in altitude and temperature.

At sea level IAS equals TAS. As altitudes increases a given TAS will be higher for an IAS

Rule of thumb is to add 2% to indicated airspeed for every thousand feet of pressure altitude increase. So at 6000 feet with a 100 KIAS we would add 12 kn

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19
Q

Petit system blockage what happens?

A

The airspeed will increase in a climb (overread)

The ASI will decrease in a decent (under read)

Basically, internally the airspeed indicator act similar to an alternator because it is not getting dynamic pressure.

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20
Q

What happens during a static system blockage?

A

Airspeed will decrease or under read in a claim

Airspeed will increase or over read in a dissent

This is extremely dangerous because the pilot could think they are approaching to quickly and slowing could equal a stall

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21
Q

What happens during a partial blockage of the Pitot system?

A

If the drain hole is left open, this will allow the air pressure to slowly leak out and the airspeed indicator will slowly decrease to zero

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22
Q

Markings (Arcs) on the ASI

A 
White Arc
Green Arc
Yellow Arc
Red Line
Blue Line
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23
Q

White Arc

A

Flap operating range.

Low limit: power off, full flap stall speed (Vso)

High Limit: maximum light extension speed of flaps (Vfe)

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24
Q

Vso

A

The bottom of the White Arc: power off, full flaps stall speed

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25
Q

Vfe

A

Maximum Flight Extension Speed where you can safely introduce flaps

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26
Q

Green Arc

A

The normal operating range

Bottom of the green is the power off stalling speed for clean configuration (Vs)

The top of the green is the maximum structural cruising speed (Vno)

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27
Q

Define “clean configuration”

A

The configuration where flops and gear are retracted

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28
Q

Yellow Arc

A

Caution speed range

Operate at these speeds only in smooth air and do not make abrupt control movements

The bottom of the yellow is the maximum structural cruising speed (Vno)

The top of the yellow is the red line (Vne)

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29
Q

Red Line

A

Never exceed speed (Vne)

The maximum speed of the aircraft can be operated

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30
Q

Blue Line

A

Found only on multi engine airplanes this is the speed to maintain in the event of a engine failure (Vyse)

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31
Q

Define indicated airspeed

A

The uncorrected speed that is read directly off the indicator

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32
Q

Stalling Speed

A

Our stalling speed is always the same in terms of indicated airspeed and we should not alter our ApproachGuides from the value stated in the manual

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33
Q

Define calibrated airspeed

A

This is the indicated airspeed corrected for the instrument and installation error or positional errors in the pitot static system

Calibrated airspeed can be found by consulting a chart that appears in the Aircrafts POH

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34
Q

Define true airspeed

A

True airspeed is the calibrated airspeed corrected for air density error

True airspeed is also the actual speed of the aircraft through the air it can be found by using a flight computer, rule of thumb, or with a true airspeed indicator

The true airspeed indicator is always going to be higher than the indicated airspeed when at high altitudes or high temperatures. Indicated stall speed remain the same

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35
Q

How do you calculate true airspeed?

A

Use the E6B

Match the pressure altitude under the temperature, true airspeed is on the a scale immediately above the IAS/CAS value

For all practical purposes, CAS is equal to IAS for the speeds we fly

36
Q

On an E6B, where is TAS, IAS, and CAS located?

A

TAS is always on the outer A scale, well IAS and CAS is always on the B scale

37
Q

Rule of thumb for calculating true airspeed

A

Add 2% per thousand feet of altitude to the indicated airspeed

38
Q

Define groundspeed

A

This is the actual speed that the aircraft is travelling over the ground

During flight planning it can be estimated using our anticipated true airspeed and then cracking for the wind speed and direction at our intended altitude

Once flying it can be found by timing how long it takes to fly no one distance

39
Q

Does the Publix stalling indicated airspeed change with a change in altitude?

A

No. The true airspeed stalling speed at 10,000 feet above sea level is greater than the true airspeed stalling speed at sea level.

40
Q

How does bank angle affect stall speed’s?

A

As the bank angle increases, so does the stall airspeed increase

41
Q

How does centre of gravity affect stall speed?

A

As the centre of gravity moves forward, the stall speed increases Because the airplane will need to fly at a higher angle of attack for the same airspeed as compared to a Rearward or aft-loading

42
Q

How does an increase in weight affect stall speed?

A

An increase in weight increases the stalling airspeed. Because the wing will fly at a higher angle of attack for the same airspeed as compared to when it is lightning loaded.

43
Q

How does turbulence affect the stall speed?

A

Turbulence increases the stall airspeed as a Gust has the potential to increase the angle of attack suddenly.

A sudden reduction in the headwind, or a sudden increase in tailwind will also increase the stall speed factor

44
Q

How does contamination affect stall speed?

A

Contamination of any lifting surface increases installing airspeed by causing the smooth airflow over the wings to separate sooner. Causes include frost, snow, ice, or mud.

Roughness similar to medium or coarse sandpaper on the leading edge and upper surface of a wing reduces left by as much as 30%, and increases dragway as much as 40%.

45
Q

How does power affect stall speed?

A

Power reduces the airspeed at which the airplane will stall.

The upward component of thrust change is the relative airflow and reduces the angle of attack, the extra airflow over the root of the wings improve the amount of lift generated

46
Q

How does a rapid change of airflow affect stall speed?

A

This is considered an accelerated stall.

During the transition from crews to a climb, the relative airflow gradually changes with the pitch attitude. If the pitch attitude is made rapidly the relative airflow will not be able to change as quickly and the critical angle of attack will be exceeded at a high speed.

47
Q

What is the relationship between true airspeed an and altitude increases

A

True airspeed must increase with altitude increases in order to avoid stalls.

48
Q

How does warmer temperature or higher altitude affect true airspeed?

A

Hot/hi equals faster true airspeed.

49
Q

Equivalent airspeed With regard to adiabatic compression

A

Equivalent airspeed can be defined in terms of calibrated airspeed corrected for adiabatic compression flow at the altitude of flight

At sea level under ISA conditions, Equivalent airspeed and calibrated airspeed are the same

At any other altitude equivalent airspeed will be less than calibrated airspeed

50
Q

Explain how Altimeters work

A

The alternator is an android barometer which measures the pressure of the atmosphere. It is connected to the static port.

Inside the altimeter as a series of aneroid capsules that are filled with standard atmosphere at 29.92 HG

Static pressure decreases, aneroid capsule expands, indicates a climb

Static pressure increases, aneroid capsule contracts, indicating a Desent.

51
Q

Altimeter errors

A

Because the alternator is designed with a standard atmosphere, any deviations from standard atmosphere will result in an incorrect reading

52
Q

Define standard atmosphere

A

Sea level pressure is 29.92 inches of mercury
Sea level temperature is 15°C
Temperature decrease at the standard labs rate is 1.98°C per thousand feet
1 inch of mercury pressure dropped per thousand feet of altitude
The air is perfectly dry gas with no moisture

53
Q

What causes errors in the altimeter?

A

Low pressure systems
Temperature variations
Mountain affect and waves
Abnormally high pressure

54
Q

How do we set the altimeter?

A

Use the Kollaman window and said it to the altimeter setting.

After doing so, ensure the altitude displayed as within 50 feet of the field elevation

55
Q

What happens when flying from high-pressure area to a low pressure area?

A

From high to low, look out below

Meaning the altimeter will show higher than actual altitude. You are closer to the ground than you think

56
Q

Define altitude

A

The vertical distance between mean sea level and a point in the air

57
Q

Define height

A

The vertical distance between a point on the ground and a point in the air. Think of it as the height above a building or a plateau on the ground

58
Q

Define elevation

A

The vertical distance between mean sea level and a point on the ground

59
Q

If you left a sea level airport and the altimeter was set to 29.92 inches of mercury, and later the barometer detected 25.14 inches of mercury would you be higher or lower?

A

Higher. As altitude increases, barometric pressure decreases.

60
Q

What would be the standard barometric pressure at 3000 feet above MSL?

A

26.9 2 InHg Because the barometric pressure drops by 1 inch of mercury for every thousand feet of altitude gained.

61
Q

QNH

A

Mean sea level pressure at a certain moment in time.

62
Q

QFE

A

The current pressure at the aerodrome level

63
Q

If your alternator is set to 29. 92, but there’s actually a high pressure system representing say 30.06 InHg, how will your altimeter read?

A

The indicated altitude will be lower than the actual altitude. He will be flying higher than the indicated altitude suggest.

64
Q

If there is a low pressure system and you have set your altimeter to 29.92 but the pressure is actually 28.99, how will the altimeter read?

A

The indicated Altitude will be higher than the actual altitude. In other words, you’ll be flying lower than what is indicated

65
Q

How does temperature affect the altimeter?

A

In warmer air, the plane will be higher than what is indicated

In cooler air the plane will be closer to the ground than what is indicated

66
Q

Cold correction chart

A

The cold correction chart shows us how much our indicated altitude can be in error in very cold conditions

67
Q

Mountain Effect on Altimeter

A

Wind that is deflected around mountains increases speed’s due to Bernoulli’s principle.

The increasing windspeed will result in a decrease in the local pressure

Therefore a pressure altimeter would be subject to a decrease in pressure and given altitude reading that is too high.

In other words, during mountain the fact your plane is closer to the ground than the altimeter is reading

68
Q

Mountain waves and downdrafts affect on altimeter

A

Mountain waves cause downdrafts around mountains

If your plane is caught in a downdraft it will descend, but the altimeter will not register the decent Because the pressure is changing in the downdraft.

This can be very dangerous

69
Q

How should we guard against Altimeter error?

A

Anytime we fly around mountains, we should fly much higher than we think we need to.

Imagine this worst case scenario:

Mountain waves, and going from warm air to cold air, and going from high-pressure to low-pressure

70
Q

How often should the pedo/static instrument to be inspected for IFR flights?

A

Every 24 months

71
Q

Indicated altitude

A

The altitude read directly off the face of the altimeter when the correct altimeter setting is placed in the kollsman window

72
Q

Define pressure altitude

A

The altitude that is indicated when they altimeter barometric scale it said to 29.92 inches of mercury.

Pressure altitude is based on the standard atmosphere

73
Q

Calculating pressure altitude method one

A

Set the aircraft altimeter to 29.92

74
Q

Calculating pressure altitude, method 2

A

Remember that 1 inch of mercury is equal to 1000 feet of altitude

Take 29.92, the standard atmosphere value and subtract the current altimeter setting

Multiply this value by 1000

If the number is positive it will be added to the elevation.

If the number is negative it will be subtracted from the elevation

75
Q

Define true altitude

A

This is our exact height above mean sea level MSL

Heights on aeronautical charts are given in terms of true altitudes

76
Q

Define absolute altitude

A

The actual height above the earth surface (a GL) with the altimeter setting correctly set and non-standard variations in temperature taking into consideration

Basically, this is the true altitude subtracting out the height of the terrain below

77
Q

Define density altitude

A

This is the pressure altitude corrected for non-standard temperature

The performance of our aircraft at the calculating density altitude will be the same as it was actually flying at that altitude

78
Q

In what altitude is the aircraft service ceiling and absolute ceiling given?

A

Density Altitude

79
Q

Mode C operation of a transponder

A

Allows ATC to know the pressure altitude as well as the position of a transponder equipped aircraft using the encoding altimeter

80
Q

What altitude does ATC radar see from an aircraft

A

Using the encoder altimeter operation, the information is displayed in the form of pressure altitude to the controller

81
Q

List the 6-pack

A 
Airspeed Indicator
Attitude Indicator
Altimeter
Turn Coordinator
Heading Indicator
Vertical Speed Indicator
82
Q

VOR

A

The VHF Omnidirectional Range is a radio
navigation instrument.

Its Course Deviation Indicator (CDI) gives
the pilot an indication on the position of the
aircraft in relation to a ground station.
The VOR is the primary system used to
define airways.

83
Q

ILS

A 
The Instrument Landing System is a very
sensitive VOR that also includes vertical, glide
slope information.
It is used for precision approaches when
landing in poor weather conditions.
84
Q

The heading indicator uses the principal of

A

Rigidity in space

85
Q

Define AHRS

A

Altitude and Heading Reference System

Aviation (22 decks)

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