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AT 103 > Exam 2 Review > Flashcards

Exam 2 Review Flashcards

1
Q

Parts of an Oil System (9)

A

Pressure Oil Pump
Oil Pressure Relief Valve
Oil Reservoir
Oil Pressure Gage
Oil Temperature Gage
Oil Filter
Necessary Piping and Connections
Oil Coolers
Oil Dilution Systems

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2
Q

Oil Pressure Relief Valve

A

Control and limit the lubricating oil pressure
Prevent damage to the lubrication system
Ensure lubrication in case of a system failure

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3
Q

Oil Filter Types (5)

A

Full-Flow
Bypass
Strainer
Spin-On
Cuno Oil

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4
Q

Full-Flow Filter

A

Filtering all the circulated oil of contaminants
All oil are filtered before passing through bearing surfaces
If Filter is clogged, a relief valve will open. Allowing oil bypass

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5
Q

Bypass Filter

A

Filters about 10% of the oil through filtering element and returns oil to sump
Oil passing through bearings are not filtered oil

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6
Q

Strainer Filter

A

A simple tubular screen
Designed to collapse when clogged or designed with relief valves that also open when clogged

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7
Q

Spin-On Filter

A

Newest style
Canister and filter element are one unit
Incorporates wrench pad, steel case, cellulosic paper, and mounting plate with threaded end for mounting to the engine
Full-flow type

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8
Q

Cuno Oil Filter

A

Series of laminated plates or disks
Contaminants are trapped on the outer diameter of the plates
The spacing of the plates will determine the particle size that may pass through

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9
Q

Alternate Air Valve Function

A

Allows air to flow to the engine if air filter is clogged

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10
Q

Carb Heat Valve Function

A

Operated by the carburetor heat control in the cockpit
The valve closes the main air duct and opens the duct to the heater muff

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11
Q

Causes of Intake Icing (3)

A

Flying through Clouds, Fog, Rain, Sleet, Snow, or High moisture clear air
if the temperature before the air scoop is below freezing point of water
when particles of water in the air strike cold surfaces

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12
Q

Exhaust System Function

A

Removes the products of combustion from the engine safely and effectively

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13
Q

Exhaust System Issues

A

Poor maintenance can lead to Nacelle fires, Toxic gases entering the cockpit and cabin, Damage to parts and structure in nacelle and, Poor engine performance

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14
Q

Characteristics of Fuel (4)

A

High heat value
Ability to evaporate when exposed to air
Ability to evaporate at ordinary temperatures
High volatility

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15
Q

Fuel Grades and Colors (4)

A

100 (green)
100LL (blue)
UL94 (unleaded)
UL91

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16
Q

Fuel System Parts (9)

A

Fuel Tanks
Fuel Boost Pump
Tank Strainer
Fuel Tank Vents
Fuel Lines
Fuel Control or Selector Valves
Main Strainer
Fuel Flow and Pressure Gages
Fuel Drain Valves

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17
Q

Spark Plug Parts (3)

A

Electrodes
Ceramic Insulator
Metal Shell

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18
Q

Types of electrodes in Spark Plugs

A

Projected Core Nose
Two-Prong Fine-Wire
Two-Prong Ground
Push-Wire

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19
Q

Heat Range of Spark Plugs (3)

A

Hot
Normal
Cold

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20
Q

If an engine typically runs hot…

A

relatively cold spark plug is required

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21
Q

If an engine typically runs cold…

A

relatively hot spark plug is required

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22
Q

Why do we use magnetos in general aviation? (4)

A

Superior to battery ignition
Produces a hotter spark at high engine speeds
Self-contained unit
Not dependent on any eternal source of electric energy

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23
Q

Types of Magnetos (8)

A

Low Tension Magnetos
High Tension Magnetos
Rotating Magnet Magnetos
Inductor Rotor Magnetos
Single Magnetos
Double Magnetos
Flange Mounted Magnetos
Base Mounted Magnetos

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24
Q

Essential Parts of Carburetors (7)

A

Float Mechanism and its Chamber
Strainer
Main Metering System
Idling System
Economizer System
Accelerating System
Mixture Control System

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25
Q

Float Mechanism

A

Designed to control the level of fuel in the float chamber

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26
Q

Fuel Strainer

A

Fuel passes through a strainer screen
Strainers are commonly a fine wire mesh that will intercept any dirt particles

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27
Q

Main Metering System

A

Controls the fuel feed in the upper half of the engine speed range

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28
Q

Units of the Main Metering System (3)

A

Main Metering Jet
Main Discharge Nozzle
Passage Leading to the Idling System

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29
Q

Functions of the Main Metering System (3)

A

Proportion the A/F mixture
Decrease the pressure at the discharge nozzle
Control the airflow at full throttle

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30
Q

Idling System

A

Delivers fuel only when throttle valve is nearly closed

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31
Q

Accelerating System

A

Discharges an additional quantity of fuel into the carburetor airstream when throttle is opened suddenly

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32
Q

Economizer System

A

Opens at high speeds to provide an enriched mixture to reduce burning temperatures an prevent detonation

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33
Q

Mixture Control System

A

Prevent mixture from becoming too rich at high altitudes
Economize on fuel during engine operation in the low power range

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34
Q

Where do air and fuel mix?

A

Carburetor

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35
Q

Advantages of fuel injection (5)

A

Freedom from vaporization icing (carb icing)
More uniform delivery of air fuel mixture to each cylinder
Improved control of fuel/air ratio
Instant acceleration after idling with no tendency to stall
Increased engine fuel efficiency and power

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36
Q

Bendix RSA FI Servo

A

Designed to meter fuel in direct ratio to the volume of air being consumed by the engine
Done by sensing venturi suction and impact air pressure in the throttle body

37
Q

In the Bendix RSA FI Servo, throttle valve opening changes…

A

the velocity of air passing

38
Q

In the Bendix RSA FI Servo, when air velocity increases… (2)

A

pressure of the impact tubes remains constant
Air pressure at the venturi decreases

39
Q

The differential pressure is used as a measurement of…

A

the volume of air consumed

40
Q

Parts of the Fuel Injection system (5)

A

Servo Pressure Regulator
Idle Valve
Manual Mixture Control
Flow Dividers
Fuel Nozzles

41
Q

Servo Pressure Regulator

A

Fuel flow to the engine, passing through the metering jet generates a fuel pressure differential with unmetered fuel
Since fuel is metered to direct ratio with the air being consumed, the two opposite forces (fuel and air differentials) are equal

42
Q

What keeps both diaphragms connected in the Servo Pressure Regulator

A

Servo Valve

43
Q

The servo valve opening…

A

decreases the pressure in the meter fuel chamber
increases the pressure in fuel differential

44
Q

Idle Valve

A

Connected to the throttle linkage
Externally adjustable
Limits the area of the main metering jet
Meters fuel accurately in the idle range

45
Q

Idle mixture is correct when…

A

the engine gains 25-50 rpm from idle speed when mixture is placed in “idle cutoff”

46
Q

Manual Mixture Control

A

A sliding valve
Used by the pilot to effectively reduce the size of the metering jet
Also allows for shutting off the fuel flow to the engine at engine shutdown

47
Q

By changing the metering jet’s effective size, the pilot has the option of…

A

manually leaning the mixture

48
Q

Flow Dividers

A

a single four way fitting (4 cylinder engine) or a tee that divides flow into two paths

49
Q

Functions of Flow Dividers (2)

A

Ensure equal distribution of metered fuel to the nozzles
Provide isolation of each nozzle for clean engine shutdown

50
Q

At idle, fuel pressure is…

A

only enough to move the flow divider valve slightly

51
Q

As engine accelerates…

A

metered fuel pressure increases

52
Q

Fuel Nozzles

A

are of air bleed type
Fuel is discharged inside the nozzle body into a chamber which is vented to atmospheric air pressure

53
Q

Where are fuel nozzles mounted?

A

Nozzle is mounted in the intake valve port of the cylinder head

54
Q

Newton’s Third Law of Motion

A

Every action has an equal and opposite reaction

55
Q

Inventors of Gas Turbine Engines

A

The Chinese - used rockets as weapons in 1232

56
Q

Who designed the first true gas turbine engine?

A

Dr. F. Stolze - 1872

57
Q

What aircraft company flew the first flight of a gas turbine engine?

A

Ernst Heinkel Aircraft - 1939

58
Q

Who designed the first turbojet airplane?

A

Sir Frank Whittle - 1941

59
Q

What year was the first US jet plane built?

A

1943

60
Q

What was the world’s first operational jet fighter

A

Messerschmitt Me 262 - 1942

61
Q

Bernoulli’s Principle

A

Total energy in a column of moving fluid remains constant throughout the column
Total Energy = Potential Energy + Kinetic Energy

62
Q

Otto Cycle

A

Intake (Suck)
Compression (Squeeze)
Power (Bang)
Exhaust (Blow)

63
Q

What is the difference between the Otto Cycle and the Brayton Cycle?

A

The Brayton Cycle is the same as the Otto Cycle except:
Events occur at the same time
Events occur at different locations within the engine

64
Q

Subsonic Convergent Duct vs. Divergent Duct

A

C: Velocity decreases, Pressure and temperature increase
D: Velocity increases, Pressure and temperature decrease

65
Q

Supersonic Convergent Duct vs. Divergent Duct

A

C: Air does not speed up but compresses, Velocity decreases, Pressure and density increases
D: Air expands, Velocity increases, Pressure and density decreases

66
Q

Non-Air vs Air Breathing Engine Types

A

Non-Air carries all the needed oxygen within their fuel and generates heat by chemical reaction between fuel and an oxidizer
Air Breathing takes air in through the air inlet

67
Q

Types of Air Breathing Engines (6)

A

Turbojet
Turboprop
Turboshaft
Turbofan
Pulse-Jet
Ramjet

68
Q

Turbojet Engine

A

Takes air in through the air inlet
Compresses the air
Mix compressed air with fuel
Air and fuel mixture ignited and burned
Hot gases passes through turbine
Air forced out of a specially shaped exhaust nozzle forming a high-speed jet

69
Q

Turboprop Engine

A

Drives a propeller
A derivative of the turbojet engine

70
Q

Methods of driving a propellor (2)

A

Connecting the propeller to the compressor
Connecting the propeller to a turbine separate from the core engine (Free-Turbine Engine)

71
Q

Turboshaft Engine

A

Commonly used for helicopters
More efficient at constant RPM required by helicopters
Most drives output shaft with multistage free turbine
Reduction gearbox is remote from the engine

72
Q

Turbofan Engine

A

Increased propulsive efficiency
Lower Noise
Lower fuel consumption
Lengthened blades in early stage(s) of low-pressure compressor
Air from the fan section flows around the outside of the core engine
Fan can produce 30-75% of the total thrust

73
Q

Bypass Ratio

A

Ratio of the mass or air moved by the fan to the mass of air moved by the core engine

74
Q

Types of Bypass Ratio (3)

A

Low-Bypass
High-Bypass
Ultra-High-Bypass

75
Q

Low-Bypass Ratio

A

Less than 2 : 1

76
Q

High-Bypass Ratio

A

Ratio of 4 : 1 or greater

77
Q

Ultra-High-Bypass Ratio

A

Exceeds 30 : 1

78
Q

Pulse-Jet Engine

A

Early air-breathing reaction engines
Used as early as World War II in missiles

79
Q

Ramjet Engine

A

Simplest type of air-breathing reaction engine
Requires high-velocity air entering the engine to work

80
Q

Types of Thrust (2)

A

Net
Gross

81
Q

Net Thrust

A

Thrust produced by the engine while in flight

82
Q

Gross Thrust

A

Thrust produced by the engine while engine is static and not moving

83
Q

% RPM

A

Compressor speed
approximately proportional to the trust being produced by the engine
Used in smaller jet engines

84
Q

EPR

A

Engine Pressure Ratio
Ratio of the turbine discharge total pressure to the compressor inlet total pressure
Used in larger jet engines

85
Q

Ways to increase thrust (3)

A

Water Injection
Duct Heater
Afterburners

86
Q

Water Injection

A

Increases mass airflow and reduces turbine inlet temp.
Increases takeoff thrust by 10-30%

87
Q

Duct Heater

A

Fuel is added to the fan-discharge air and burned

88
Q

Afterburners

A

Only 25% of air passing through the core is used for combustion
Remaining air used for cooling
Fuel is sprayed into the hot exhaust gases and ignited
Additional heat further accelerates the air to create 50% increase in thrust
Threefold increase in fuel consumption

AT 103 (5 decks)

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