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E.I.S. > POWERPOINT > Flashcards

POWERPOINT Flashcards

1
Q

Piston Engines

Turbo Propeller Engines

Gas Turbine Engines

A

General Engine Instrumentation

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2
Q

Pressure Measurement

Temperature Measurement

A

Pressure and Temperature Sensors

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3
Q

Manifold Pressure (MAP)

Engine Pressure Ratio (EPR)

Fuel and Oil Pressures

Temperature Indicators

Cylinder Head Pressure

Exhaust Gas Temperature

Fuel and Oil Temperatures

A

Pressure and Temperature Indicators

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4
Q

Tachometers

Magnetic Drag Tachometer

Tacho-Generator and Indicator System

Tachometer Probe and Indicator System

Propeller Auxiliary Systems

Synchronisation System

Synchrophasing System

Operation of a Synchrophasing System

A

RPM Indicators and Propeller Synchronizer Systems

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5
Q

Torque Meter

Negative Torque Sensing

A

Engine Torque Measurement

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6
Q

Vibration Monitoring System

A

Vibration Monitoring

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7
Q

Measurement of Fuel Quantity

Float Type

Ratio Meter Type

Fuel Gauge Capacitance Type of Fuel Gauge

Fuel Totalizer

Fuel Flow

A

Fuel Gauge

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8
Q

EICAS Architecture

Engine Displays

Crew Alerting

Warnings (Level A)

Cautions (Level B

Advisories (Level C

Master Warning/Caution Light

Inhibits

Display Status

Maintenance

EICAS Failure Modes

A

EICAS

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9
Q

Engine I Warning (EIW) CRT Display

The System I Status (SIS) CRT Display

ECAM System Architecture

Flight Warning Computers (FWCS)

Display management Computers (DMC)

System Data Acquisition Concentrators (SDAC)

ECAM Control Panel (ECPAttention Getters

ECAM System

Failure Categorization

System Operation

A

ECAM

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10
Q

(?) is vital to maintain the safe and efficient
operation of the aircraft engines and their associated systems.

A

Instrumentation

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11
Q

It varies according to the type of engines fitted (e.g. piston,
turboprop, or gas turbine), and in many cases the individual
instruments are identical.

A

Engine Instrumentation

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12
Q

Engine Speed

Induction Manifold Pressure, or Boost Pressure
(MAP)

Torque or Turning Moment

Cylinder Head Temperature

Lubricating Oil Pressure and Temperature

Fuel Flow

Fuel Quantity

Fuel Pressure

A

PISTON ENGINES

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13
Q

This is a measure of how much work is being
done by the engine, and is measured in
revolutions per minute (rpm).

A

ENGINE SPEED

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14
Q

-is the indicator that
indicates the engine
speed

A

TACHOMETER

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15
Q

This is a measure of the engine power of a
supercharged engine (absolute pressure).

A

Manifold Pressure

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16
Q

is usually given in inches of mercury (in Hg),
and boost is normally measured in pounds per square
inch (psi).

A

Manifold Pressure

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17
Q

Acts on the output shaft of the engine and is
proportional to the horsepower developed.

A

Torque or Turning Moment

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18
Q

It is occasionally used to provide information for
power control

A

Torque or Turning Moment

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19
Q

This temperature is important because excessive
temperatures can cause engine damage.

A

Cylinder Head Temperature

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20
Q

The temperature is measured in degrees Celsius
(0C).

A

Cylinder Head Temperature

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21
Q

measure the temperature of the cylinder head

A

Cylinder Head Temperature

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22
Q

Ensures adequate lubrication of the engine. In
pressure terms it may be HIGH or LOW, whereas
the temperature is usually in degrees Celsius
(0C).

A

(Lubricating) Oil Pressure and Temperature

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23
Q

-Provides a measure of the economy of the engine,
and is measured in pounds, kilograms or
gallons/hour.
- indicates the flow of the fuel.

A

Fuel Flow

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24
Q

Ensures that there is sufficient fuel to
complete the flight, and is measured as Fuel
Mass or Volume.

A

Fuel Quantity

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25
Q

Measured using a pressure gauge, and any drop
in fuel pressure may indicate a partially blocked
fuel filter.

A

Fuel Pressure

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26
Q

TURBO PROPELLER ENGINES
For an aircraft with a turbo propeller engine, the parameters that require monitoring are the:

A
  • RPM

 Torque

 Engine Exhaust Gas Temperatures (EGT), measured in °C.

 Lubricating oil pressure

 Lubricating oil temperature

 Fuel flow

 Fuel quantity

 Fuel Pressure

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27
Q
  • indicates the flow outside the engine and heat outside the exhaust.
  • measured in °C.
A

Engine Exhaust Gas Temperatures (EGT)

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28
Q

GAS TURBINE
ENGINES

For an aircraft with gas turbine engines,
the pilot must monitor:

A

Engine Pressure Ratio (EPR)
exhaust gas temperature
Oil Temperature and Pressure
Fuel Pressure and Temperature

Torque Meter
Tachometer
Engine Oil Pressure
Engine Oil Temperature

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29
Q

have pics, figures, and numbers.

A

Indicators

30
Q

Have only numbers.

A

Gauges

31
Q

EICAS

A

Engine Indicating and Crew - Alerting System

32
Q

ECAM

A

Electronic Centralized Aircraft Monitor

33
Q
  • This is the amount of useful thrust being
    developed by the engine. It is the product of the
    mass of air passing through the engine and its
    velocity at the exhaust nozzle minus the drag due
    to the air passing through the engine.
  • divide the pressure inside the engine.
A

Engine Pressure Ratio (EPR)

34
Q

Comparing the air pressure across the engine (i.e.
the exhaust pressure to the compressor inlet
pressure [EPR]) provides an indication of the
(?) output from the engine. EPR is usually
given as a percent thrust value.

A

thrust

35
Q

This is normally a percentage of its maximum value.

A

RPM, N1, N2 or N3

36
Q

The (?) requires monitoring in order to prevent excessive heat damaging the
turbine.

A

exhaust gas temperature (EGT)

37
Q

Monitoring ensures the safe
operation of the engine.

A

Oil Temperature and Pressure

38
Q

-Monitoring ensures that a supply of non-cavitated fuel is
at an acceptable pressure and temperature.
-A low fuel pressure warning light may back this up.

A

Fuel Pressure and Temperature

39
Q

are lilted to aircraft that sense or measure
pressure and temperature, create a signal,
proportional to that measurement

A

Devices

40
Q

In aviation. (?) is measured in pounds per square inch
(psi), inches of mercury (in Hg), millibars (mbar), or
kilopascals (kPa).

A

pressure

41
Q

the three most common types of pressure

A

Absolute Pressure
Gauge Pressure
Differential Pressure

42
Q

This is the pressure compared to a perfect
vacuum, which is more than this value. It is
given as PSIA or in Hg absolute.

A

Absolute Pressure

43
Q

This pressure compares to ambient pressure,
and is given as PSTG.

A

Gauge Pressure

44
Q

This is the difference between two different
pressures in an airplane, and is given as PSID.

A

Differential Pressure

45
Q

Airplane instruments used to register these
pressures are typically the:

A

Manifold pressure gauge
Oil pressure gauge
Cabin differential pressure gauge

46
Q

-this gauge measures absolute pressure

A

Manifold pressure gauge

47
Q

-this gauge measures gauge pressure

A

Oil pressure gauge

48
Q
  • this gauge measures the difference in pressure between the inside and the outside of the airplane, and is calibrated in PSID
A

Cabin differential pressure gauge

49
Q

Pressure measurements are required for various
applications such as:

A

 Static air pressure

 Fluid pressure

 Manifold pressure

 Differential pressure

 Pressure ratios

50
Q

Pressures are usually measured by using a
flexible metal chamber (?), which is spring loaded against the
effect of changes in pressure, or a Bourdon tube

A

aneroid capsule or bellows

51
Q

-To measure static pressure, the capsule is partially
evacuated and sealed, and is prevented from collapsing
by the action of a spring.
-This type of device is used to measure medium
pressures.

A

Aneroid Capsule

52
Q

This device is manufactured from a metal such as
phosphor bronze or beryllium-copper. It is in the
form of a coil and when affected by a change in pressure, extends or contracts.

A

Bourdon Tube

53
Q

The Bourdon tube may be used to measure: 3 pressure

A

oxygen pressure

hydraulic pressure

engine oil pressure

54
Q

In all of these types of pressure sensors, the
change in pressure acting on them converts into a
mechanical motion by the change in (?) of the
sensor.

A

shape

55
Q

The temperatures requiring measurement on an airplane are:

A

Air temperatures

Gas temperatures

Component temperatures

Fluid temperatures

56
Q

The variation in the physical properties of a substance is used in
measuring temperature, and any devices used on airplanes to measure temperature are called (?).

A

Temperature-Measuring Systems

57
Q

-This system, used to measure temperatures up to 140°F, uses the
property of expansion.
-Different materials expand and contract at different rates when
subjected to the same change in temperature.
-If two thermally dissimilar metals (e.g. iron and brass), are strapped
together and heat is applied, one expands more than the other, and the bi-metallic strip distorts.

A

Bi-metallic Temperature System

58
Q

The (?) can be formed into a coil so
that any change in temperature causes the strip
to wind or unwind and produce a rotational
movement.

A

bi-metallic strip

59
Q

This system consists of a Bourdon tube gauge,
which measures pressure, a thin walled bulb,
which is at the point of measurement, and a thin
capillary tube to connect them together

A

Mechanical Bulbs Temperature System

60
Q

It uses the principle of the increase in vapor
pressure within a confined space to measure
temperature.

A

Mechanical Bulbs Temperature System

61
Q

The system is filled with a chemical ,(e.g. Methyl
Chloride), which in its natural state is part liquid
and part gas.

A

Mechanical Bulbs Temperature System

62
Q

-The system is sealed, and as the temperature
increases, the pressure changes within the tube,
giving an accurate reading of temperature on the
Bourdon tube gauge.
-This pressure, and on some jet airplanes to
measure the compressor inlet temperature of the
engine.

A

Mechanical Bulbs Temperature System

63
Q

This method of measuring temperature requires
electrical power, and is useful for measuring
temperatures up to 300°F. The bridge circuit
consists of three fixed resistors and one variable
resistor.

A

Wheatstone Bridge System

64
Q

Wheatstone Bridge System:
The variable resistor is the (?),
and contains a coil of fine nickel wire.

A

temperature probe

65
Q

Wheatstone Bridge System:
As the (?) of the coil increases, its
resistance also increases, and current flows in
the bridge.

A

temperature

66
Q

This system is used to measure temperatures up
to about 500°F or more, and is the most
commonly used device. Unlike the Wheatstone
bridge, this system does not require an electrical
power source.

A

Thermocouple Temperature System

67
Q

Thermocouple Temperature System:
When one junction of two (?) metals is
heated a voltage proportional to the temperature
between the ‘hot’ and ‘cold ‘ junctions occurs, and
current flows in the circuit, with a reading taken
at the cold junction.

A

‘dissimilar’

68
Q

Thermocouple Temperature System:
Two commonly used metals are (?), which are both able to withstand high temperatures and produce a useable voltage.

A

Copper-Constantan and Iron - Constantan

69
Q

Thermocouple Temperature System:
The actual voltage produced is very low, so this device is not
usually used to measure temperatures below (?)°F.

A

400°F

70
Q

Thermocouple Temperature System:
To measure high temperatures up to 1000°F and above a
combination of (?) is used.

A

Chromel - Alumel

71
Q

N1

A

Low Pressure Compressor

72
Q

N2

A

High Pressure Compressor

E.I.S. (3 decks)

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