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PPL 1 > Aircraft Systems > Flashcards

Aircraft Systems Flashcards

1
Q

Classification of 2 engine types

A

Cylinder arrangement, radial, inline, vtype, opposed
Operating cycle, 2 or 4
Cooling, air or liquid

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2
Q

Fixed pitch prop

A

Climb vs cruise prop, low vs high pitch
Some engines have shaft geared
Tachometer in rpm engine and prop

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3
Q

Adjustable pitch prop

A

Constant speed prop most common, maintains constant rpm despite air load
Most efficient
2 controlls: throttle for power output and prop for engine rpm

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4
Q

Constant speed prop governor maintains set rpm

A

Increase in airspeed or decrease in prop load causes prop angle to increase to maintain rpm
Decrease in airspeed or increase in prop load causes prop angle to decrease

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5
Q

Manifold pressure gauge

A

Absolute pressure of fuel-air mixture inside intake manifold
Color coded indicating engine ops range

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6
Q

Change manifold pressure and rpm in this order to avoid engine overstress

A

Reduce manifold pressure before rpm
Increase rpm before increasing manifold
Radial engines: minimize ops time at max rpm and manifold pressures

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7
Q

2 induction systems

A
  1. Carburetor mixes fuel and air before intake manifold
  2. Fuel injection mixes fuel and air immediately before each cylinder or injects fuel into cylinder
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8
Q

Types of carburetors

A

Flow type
Pressure type

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9
Q

Float type carburetor

A

Outside air through filter through venturi = narrow throat in carb
Low pressure area created forcing fuel to flow through main fuel jet at throat. Fuel then flows into airstream, mixed with air, drawn into intake manifold and combustion chamber

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10
Q

Float type disadvantages

A

Bad with abrupt maneuvers
Discharge of fuel at low pressure leads to incomplete vaporization
Icing tendency

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11
Q

Mixture Control

A

Full rich at sea level
Lower air density at altitude requires reduction in fuel density
Otherwise carbon build up occurs due to incomplete combustion causing loss of power
Increase mixture when descending
Monitor engine temp or exhaust gas temp

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12
Q

Carboator icing

A

Due to fuel vaporization and decrease in air pressure in venturi
Below 70F and above 80% humidity
Notice vibration, engine roughness
Use carboator heat to counter, will reduce engine power, use for a few min to melt ice

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13
Q

Temperature gauges

A

For outside air and carburetor air temp

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14
Q

Fuel injection system components

A

Engine driving fuel pump for after engine start
Fuel air control unit
Fuel manifold
Discharge nozzles
Auxiliary fuel pump for engine start
Fuel pressure/flow indicators

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15
Q

Fuel injection advantages

A

Reducing evaporation icing
Better fuel flow
Faster throttle response
Precise control of mixture
Better fuel distribution
Easier cold weather starts

Disadvantages
Difficulty starting hot engine, during hot days or restarting

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16
Q

Superchargers and Turbosuperchargers

A

Increase air pressure running through engine and therefor increase service ceiling of aircraft

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17
Q

Supercharger

A

Uses engine driven air compressor
1, 2 or variable speed
One or more stages
Intake air passes through ducts to carburetor, fuel-air charge ducted to supercharger blower impeller, accelerates outward, passes through diffuser, velocity traded for pressure, directed to cylinder

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18
Q

Turbocharger elements

A

Compressor and turbine
Induction air accelerated by impeller, large volume into compressor producing high pressure, high density air
Engine exhaust gas used to drive turbine wheel and impeller - adjusted with amount of exhaust gas directed to turbine vs waste gate
Use intercooler to cool compressed air

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19
Q

Overboost

A

Produce manifold pressure that exceeds engine limitations
Manual vs oil pressure control of waste gate
Advance throttle carefully
Oil temp in normal range first
Allow turbocharger to cool and turbine to slow before shutting off engine

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20
Q

Ignition system

A

2x magnetos, spark plugs, hich tension leads, ignition switch

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21
Q

Engine oil system functions

A

Lubrication of engine moving parts
Cooling of engine by reducing friction
Removing heat from cylinders
Seal between cylinder walls and pistons
Carrying away contaminants

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22
Q

Wet sump vs dry sump

A

Wet sump part of engine, pump drawing from sump routing into engine, then returns to sump
Dry sump external to the engine in a separate oil tank allowing for greater volumes of oil

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23
Q

Engine air cooling system

A

Air inlet, baffles, fins in cylinders, cowl flaps

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24
Q

Exhaust system

A

Exhaust valve and piping attached to cylinders
Muffler and Muffler shroud
EGT probe to measure exhaust manifold temp

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25
Q

Starting system

A

Direct cranking in small aircraft
Battery or external power, wiring, switches, solenoids

26
Q

Combustion: causes of detonation

A

Too low fuel grade than specified
Low rpm and very high manifold pressures
High power settings plus excessively lean mix
Extended ground ops or steep climbs with reduced cylinder cooling

27
Q

Preignition

A

Residual hot spot in cylinder
Carbon deposit on spark plug or cracked spark plug insulator or other damage
Severe engine damage, lose power

28
Q

FADEC

A

Full Authority Digital Engine Control
Eliminates need for magnetos, carburetor heat, mix control, engine priming

29
Q

Turbine engine consists of

A

Air inlet, compressor, combustion chambers, turbine section, exhaust

30
Q

types of compressors

A

Centrifugal flow
Axial flow
Centrifugal-axial flow

31
Q

Types of turbine engine

A

Turbo jet
Turboprop
Turbo fan
Turboshaft

32
Q

Turbojet

A

Compressor passes inlet air to combustion chamber with fuel and igniter, expanding air drives turbine, connected to shaft, connected to compressor

33
Q

Turboprop

A

Exhaust gas drives turbine with shaft connected to reduction gear assembly for prop

34
Q

Turbofan

A

Secondary airflow bypass combustion chamber, increases thrust, cools engine, aids with noise suppression

35
Q

Turbine engine instruments

A

Oil pressure, oil temp, engine speed, exhaust gas temp, fuel flow
Engine pressure ratio, turbine discharge pressure, torque

36
Q

Engine pressure ratio EPR

A

For power output
Ratio of turbine discharge to compressor inlet pressure

37
Q

Exhaust gas temp EGT

A

Prevent overheating of turbine with temp sensors
Turbine inlet temp, turbine outlet temp, interstage turbine temp, turbine gas temp

38
Q

N1 N2 Indicators

A

N1 rotational speed of low pressure compressor
N2 rotational speed of high pressure compressor

39
Q

Turbine engine operations

A

Temp limits
Thrust variations
Forgein object damage
Hot/Hung start
Compressor stalls
Flameout

40
Q

Performance comparisons 3 options

A

Brake horsepower - usable hp delivered to output shaft
Net thrust - produced by turbojet or turbofan
Thrust hp - hp equivalent of the thrust produced by turbojet and turbofan
Equivalent shaft hp - sum of shaft hp to prop and thrust hp by exhaust => in turboprop

41
Q

Airframe systems

A

Fuel, electrical, hydraulic, oxygen systems

42
Q

Fuel systems

A

Gravity fed in high wing planes
2 fuel pumps in low wing planes, one engine driven, one electrical for starting and backup
Fuel primer helps evaporate fuel during cold start

43
Q

Fuel strainers, sumps, drains

A

Removes water and sediments, settle in sump, remove through drain before every flight

44
Q

Fuel contamination

A

Inadequate pre flight
Service with improperly filtered fuel from small tanks, drums
Store with partially filled tanks
Lack of maintenance

45
Q

Fuel system icing

A

Undisolved or dissolved
Entrained = minute water particles suspended in fuel
Free water through bad refueling or settling

46
Q

Prevent icing

A

Additives
Hexylene glycol, methanol derivatives, ethylene glycol monoethyl ether

47
Q

Refueling

A

Avoid static electricity
Ground wire to aircraft
Ground refueling drum
Connect nozzle to aircraft

48
Q

Heating systems

A

Fuel fired heaters
Exhaust heating systems
Combustion heater systems
Bleed air heating systems

49
Q

Electrical system

A

Alternator/generator
Battery
Master/battery switch
Alternator/generator switch
Bus bar, fuses, circuit breakers
Voltage regulator
Ammeter/load meter
Electrical wiring

50
Q

Equipment that needs power

A

Position lights
Anticollision lights
Landing lights
Taxi lights
Cabin lights
Instrument lights
Radio equipment
Turn indicator
Fuel.gauges
Electric fuel pump
Stall warning
Pitot heat
Starting motor

51
Q

Hydraulic systems used for..

A

Wheel brakes
Retractable landing gear
Constant speed prop
Flight control surfaces
Wing flaps
Spoilers

52
Q

Hydraulic systems consist of

A

Reservoir
Pump
Filter
Selector valve
Relief valve
Actuator

53
Q

Tricycle landing gear

A

Can brake harder
Better visibility
Prevent swerving
Nose gear either steerable or castering

54
Q

Pressurized aircraft

A

Aircraft Altitude
Ambient temp
Ambient pressure
Cabin altitude
Differential pressure

55
Q

Decompression

A

Explosive vs rapid
Hypoxia and unconsciousness

56
Q

Oxygen systems

A

Flight crew between 12500-14000ft
Everyone above 15000ft
Some have issues at 15000ft

57
Q

Oxygen system types

A

Oxygen mask
Cannula
Diluter demand
Pressure demand
Continuous flow
Electrical pulse demand

58
Q

Anti ice and deice wing systems

A

Boot system
Thermal anti ice
Weeping wing

59
Q

Windscreen and prop anti ice

A

Using alcohol or wires producing electrical heat
Or prop boots

60
Q

CLHAND
150s and 96X has Continental

A

Carburetor
Lycoming
Horizontally opposed
Air cooled
Naturally aspirated
Direct drive

PPL 1 (15 decks)

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