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Aircraft Systems AVP 221 > Exam 3 > Flashcards

Exam 3 Flashcards

1
Q

Source that the pilot controls and which will allow sufficient operation of electrical equipment should the generator fail.

A

Primary Power

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2
Q

Engine driven device (alternator or generator) which generates power to supply all normal loads and charge the battery

A

Generated Power

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3
Q

An alternate power source that is arranged so that it is available to the pilot, even if the aircraft battery is dead (the 152 does not have one!).

A

Auxiliary Power

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4
Q

Strips of copper with holes drilled in them at appropriate intervals which are connected to one side of a row of circuit breakers and to incoming power

A

Busbars

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5
Q

Remove power from a component if the circuit becomes overloaded

A

Circuit Breakers

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6
Q

Perform basically the same function as a circuit breaker, but cannot be reset

A

Fuses

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7
Q

Used in an electric circuit for protection and current control.

A

Resistors

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8
Q

Electron “check valves”that allow the flow of electrons in one direction, but not in the opposite direction.

A

Diodes

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9
Q

Used to control the availability of power to various components.

A

Switches

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10
Q

Found in electrical systems to drive fuel booster pumps, flaps, etc.

A

Motors

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11
Q

Used exclusively in pitot tubes, windshield heat, etc.

A

Heating Elements

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12
Q

Used in flap switches and act in the same manner as normal switches.

A

Micro-Switches

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13
Q

Remote controlled electrical switches.

A

Relays

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14
Q

Lead acid

A

Battery

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15
Q

Completes the electrical circuit, which closes or opens the battery relay.

A

Masterswitch

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16
Q

Shows the rate of charge or discharge from the battery

A

Ammeter

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17
Q

Displays the load or amp draw placed on the alternator.
•Battery
•Electrical Equipment

A

Load Meter

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18
Q

A solenoid that when closed will supply electrical power to the starter.

A

Starter Relay

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19
Q

Completes an electrical circuit, which closes or opens the starter relay.

A

Starter Switch

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20
Q

Rotates the crankshaft for engine start.

A

Starter Motor

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21
Q

for reciprocating engines FAR’s Require the following:

A
  • Two separate spark plugs for each cylinder

* Two separate circuits and sources of electrical energy, supplying spark to each cylinder.

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22
Q

Magneto Ignition System Operating Principals

A
  1. The magneto system consists of a rotating magnet and the core of the magneto coil.
  2. The rotating magnet is a permanent magnet.
  3. The core of the magneto coil is a conductor.
  4. As the magneto rotates, the core of the magneto coil cuts the lines of flux in the magnet, thereby inducing EMF in the core.
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23
Q

Consists of the primary winding of the coil, the breaker points, the capacitor, and the ignition switch.

A

Primary Circuit

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24
Q

Consists of approx 200 turns of copper wire wound over the core.

A

Primary Windings

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25
Q

Opens and closes the circuit of the coil and is timed to produce a maximum buildup and then release of the magnetic field.

A

Breaker Point

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26
Q

Acts as a storage chamber to absorb the sudden rise in voltage in the coil when the breaker is open.
•Voltage can be amplified by a change in the primary windings.

A

Condenser

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27
Q

Consists of the secondary winding of the coil, the distributor, the ignition harness, and the spark plugs.

A

Secondary Electrical System

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28
Q

Center of the distributor rotor.

A

High Voltage Contact

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29
Q

Will distribute the voltage to the ignition harness (spark plug lead).

A

Distributor Rotor

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30
Q

Will distribute the spark to the spark plug.

•Ignition harnesses are made of stranded copper or stainless steel, surrounded by rubber insulation.

A

Ignition Harnesses

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31
Q

Braided stainless steel that surrounds the insulation: this is necessary to prevent loss of engine performance and interference in electronic equipment.

A

Shielding

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32
Q
  1. Spark plugs provide an insulated electrical source inside the combustion chamber.
  2. A high voltage is applied so that a spark jumps from the electrode to the ground.
  3. Spark plugs are subjected to voltages in excess of 18,000 volts, gas temps as high as 3,000 F, and pressures from partial vacuum to 2,000psi!
  4. In a 100 hr operating period a spark plug is required to ignite 7,000,000 times.
A

Info about Spark Plugs

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33
Q

Types of Spark Plugs

A
  • Shielded Massive Electrode-Has three-pronged insert on the firing end from which the spark jumps to the ground.
  • Shielded Fine Wire-Has a center electrode and two ground electrodes.
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34
Q

Electrical Power

A
  • Primary Power
  • Generated Power
  • Auxiliary Power
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35
Q

any substance which tends to flow and conform to the outline of it container.

A

Fluid

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36
Q

Moves liquids under pressure to perform work. Commonly used in the operation of brakes, landing gear, flaps, struts, shock absorbers, shimmy dampeners, etc.

A

Hydraulic System

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37
Q

Uses the movement of a fluid to perform work, but once the fluid has been displaced, its energy in the systems is lost (water wheel). pertaining to hydraulics

A

Open System

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38
Q

Fluid is confined in such a way that its pressure may be increased to perform work (car jack, barber chair, brakes, etc.). pertaining to hydraulics

A

Closed System

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39
Q

PneumaticAdvantage

A

Moves gas or air under pressure to perform work.

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40
Q

Fluid Mechanics Definitions

A
  1. Force-Energy exerted that is the cause of motion or change.
  2. Pressure-When a force is applied over a given area.
  3. Work-When a force causes an object to move.
  4. Volume-Base of a container in square units times its height in the same units.
  5. Work-Product of force x distance.
  6. Power-Rate of work, or the work accomplished in a give amount of time.
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41
Q

energy is found in one of two forms:

A

Kinetic-Exists in an object due to its motion.(Expressed as velocity.)
Potential (Static)-Exists in an object due to its position or pressure.-(Expressed as pressure.)

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42
Q

Pressure in an enclosed container is transmitted equally and undiminished to all parts of the container and acts at right angles to the enclosing walls.

A

Pascal’s Law

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43
Q

As the velocity of a fluid increases, its internal pressure decreases.

A

Bernoulli’s Principle

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44
Q

Hydraulic Fluid Characteristics

A
  1. Be as incompressible as possible.
  2. Flow freely with minimal friction.
  3. Be compatible with components of the aircraft.
  4. Good lubricating properties.
  5. Not foam during operation.
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45
Q

Types of Hydraulic Fluids

A
  • Vegetable Based
  • Mineral Based
  • Synthetic Based
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46
Q

Hydraulic System Components

A
  • Pump - Heart of the hydraulic system.
  • Reservoir - Stores fluid for the system and serves as an expansion chamber where the system can purge itself of air accumulated in the operational cycle.
  • Fluid Lines - Made of aluminum alloy, are considered rigid, where synthetic rubber lines are considered flexible lines.
  • Actuator - Converts pressure in the fluid to work.
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47
Q

Type of aircraft brakes

A
  • Energizing Brakes
  • Non-Energizing Brakes
  • Brake Actuating System
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48
Q

Drum type brakes. Not used today because of modern disc type brakes, which have fewer moving parts and dissipates heat more rapidly.

A

Energizing Brakes

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49
Q

Disc brakes.
•Single disc type.
•Disc is rigidly mounted to the wheel and hydraulic pressure applies a squeezing action between the fixed linings and rotating disc.

A

Non-Energizing Brakes

50
Q

Pre-flighting the Hydraulic System

A
  1. Ensure the proper level of fluid is present in the various hydraulic systems.
  2. Check for leaks around all fittings.
51
Q

5 Structural Components

A
  • Fuselage
  • Wings
  • Stabilizers
  • Flight Control Surfaces
  • Landing Gear
52
Q

Uses struts and wire bracing to achieve strength.

High Drag and weight.

A

Truss Type Structure

53
Q

No internal framework, all loads are carried in the skin

A

Monocoque

54
Q

Uses an internal framework of formers and stringers to add strength and rigidity to the skin.

A

Semi-Monocoque

55
Q

Five stresses acting on an airplane.

A
  • Tension-Tries to pull a body apart.
  • Compression-Tries to squeeze parts together.
  • Bending-Tries to pull one side of the body apart and squeeze the other side together.
  • Torsion-Twisting force
  • Shear-Tries to slide a body apart.
56
Q

Materials Used in Aircraft Construction

A
  • Wood-Solid or laminated wood was the construction medium of preference in early aircraft.
  • Aluminum Alloy-Offers a lightweight, durable construction medium
  • Composites-New exotic plastics offer a lightweight construction material with ease of workmanship.
57
Q

Used to enhance lateral stability

A

Dihedral

58
Q

increasing the angle of incidence in the wing.

A

Wash-In

59
Q

Decreasing the angle of incidence in the wing.

A

Wash-Out

60
Q

Varying the angle of incidence within the wing enhances stall characteristics.

A

Twist

61
Q

4 types of Wing Alignment

A

Dihedral
Wash-In
Wash-Out
Twist

62
Q

Makes sure the center of mass for a flight control is on or slightly ahead of the hinge point.

A

Mass Balancing

63
Q

Gains rigidity in control surface skin.

A

Corrugation

64
Q

Primary Flight Controls

A
  1. Pitch Control
  2. Bank/Roll Control
  3. Directional/Yaw Control
65
Q

Moveable control surface attached to horizontal stabilizer.

•Typically seen in high wings where there is greater downwash.

A

Elevator-pitch control

66
Q

Entire horizontal stabilizer is pivoted about its main spar.

A

Stabilator-pitch control

67
Q

used to roll the airplane about the longitudinal axis

A

Ailerons-roll control

68
Q

Help to counteract adverse yaw by moving the up aileron up more the down aileron moves down (increasing PD).

A

Differential Ailerons

69
Q

Location of hinge point causes the leading edge portion of the aileron to extend into the relative wind to increase parasite drag and counteract adverse yaw.

A

Frise Ailerons

70
Q

Secondary (Auxiliary) Flight Controls

A 
Trim Tabs
Balance Tabs
Anti-Servo Tab
Servo-Tab
Fixed Trim Tab
71
Q

Small moveable portions of the trailing edge of the control surface.

A

Trim Tabs

72
Q

Operate similar to trim tabs, except the control tab rod is connected to a fixed surface.

A

Balance Tabs

73
Q

Used on stabilator equipped aircraft.

A

Anti-Servo Tab

74
Q

Used on large aircraft with heavy control surfaces.

A

Servo-Tab

75
Q

Small piece of metal affixed to the trailing edge of a flight control.

A

Fixed Trim Tab

76
Q

Auxiliary Lift Devices

A

Trailing Edge Flaps-Allow the aircraft to fly a steeper glidepath without an increase in airspeed.
•Plain•Split•Slotted•Fowler
Leading Edge Lift Devices
•Leading Edge Flaps•Slots•Slats•Stall Strips
Other Lift Devices
•Winglets, Tip Tanks, Droop Tips.•Vortex Generators

77
Q

Enhance boundary layer control at higher speeds.

A

Vortex Generators

78
Q

Why is Weight & Balance important?

A

-A properly loaded aircraft is a safe aircraft.
-Manufacturers test for safe limits for loading for certification
 Maximum takeoff and landing weights
 Center of Gravity limits forward and aft
 Structural Limits

79
Q

The center of balance of all components of the mass or an imaginary point
where the aircraft would balance if suspended.

A

Center Of Gravity (CG)

80
Q

Imaginary vertical plane, in which all horizontal distances are measured for weight and balance, set by the manufacturer.

A

Datum

81
Q

The horizontal distance of any object measured from the datum

A

Arm

82
Q

A rotational force caused by weight acting on an arm. Weight X Arm =

A

Moment

83
Q

Weight of standard airplane, optional equipment, unusable fuel, and full
operating fluids.

A

Basic Empty Weight

84
Q

Fuel that cannot be consumed by the engine, undrainable fuel

A

Unusable Fuel

85
Q

A comprehensive list of equipment installed on a particular aircraft,
including optional equipment

A

Equipment List

86
Q

Aircraft weight loaded for flight prior to engine start, limit referred as

A

Ramp weight

87
Q

Subtract the weight of fuel burned during start, taxi, runup, weight just prior to takeoff

A

Max Takeoff weight

88
Q

Takeoff weight minus the weight of fuel burned in flight, limit sometimes referred as

A

Max Landing Weight

89
Q

Weight of flight crew, usable fuel, any passengers, baggage and cargo. Basic empty weight minus ramp weight or takeoff weight

A

Useful Load

90
Q

Weight of only passengers, baggage and cargo

A

Payload

91
Q

Effects of Center of Gravity -Forward CG Effects

A

 Increases download on tail(+TDF)
 Slower Cruise speed
 Nose up trim is required (Heavier Elevator controls)
 Higher Stall Speed(increased wing loading)
 Harder to rotate on takeoff/flare on landing

92
Q

Effects of Center of Gravity -Aft CG Effects

A

 Decreases download on tail(-TDF)
 Higher Cruise Speed
 Less nose up trim(Lighter Elevator controls), poor stability, nose wanders up and down
 Lower stall speed(decreased wing loading)
 Harder stall recovery, may lead to flat spin!!!

93
Q

Effects of Operating at a High Total Weight

A

 Taxi speed should be reduced – larger aircraft causes high tire/brake temperatures
 Longer takeoff rolls and higher speeds higher density altitude may not be able to takeoff at certain weights
 Angle and Rate of Climb are Reduced
 Unable to obtain higher cruise altitudes
 Range and speed are reduced at cruise
 Higher fuel consumption
 Stalls at a higher speed
 Longer landing distance and higher touchdown speed carry less weight to meet landing requirements
 Increased brake wear and temperatures

94
Q

Pressure Measuring Instruments (Pitot Static Instruments)

A
  1. ASI
  2. VSI
  3. Altimeter
95
Q

Typically installed on wing of SE aircraft outside of slipstream.

A

Pitot Tube

96
Q

Typically flush mounted to side of fuselage.

A

Static Ports

97
Q

Usually installed in static lines and should be drained prior to flight.

A

Water Traps

98
Q

May be located on or under instrument panel and for pressurized aircraft, static air is taken from inside the cabin behind instrument panel.

A

Alternate Static Source

99
Q

May be used to remove or prevent the formation of ice on the pitot tube.

A

Pitot Heat

100
Q

Components of Pitot Static Instruments

A 
Pitot Tube
Static Ports
Water Traps
Alternate Static Source
Pitot Heat
101
Q

Caused by static ports sensing erroneous static pressure measurements.
•Slip
•Skid
•Configuration(landing gear, flaps etc)

A

Position Error

102
Q

Caused by changes in altitude and temperature for which the instrument does not automatically compensate.

A

Density Error

103
Q

Caused by packing of air into pitot tube at higher airspeeds, resulting in higher than normal readings.

A

Compressibility Error

104
Q

Airspeed Errors

A

Position Error
Density Error
Compressibility Error
Instrument Blockage

105
Q

Types of Airspeed

A

Indicated Airspeed
Calibrated airspeed
Equivalent airspeed
True airspeed

106
Q

Indicated Airspeed

A

Read from instrument.Remains the same with an increase in altitude.

107
Q

Calibrated airspeed

A

Indicated corrected for instrument and installation error.

108
Q

Equivalent airspeed

A

Calibrated corrected for adiabatic compressibility for a given altitude.

109
Q

True airspeed

A

Airspeed relative to undisturbed air.

110
Q

Aneroid barometer calibrated in feet instead of inches Hg.

A

Altimeter

111
Q

Types of Altitude

A
  1. Absolute Altitude-AGL
  2. True Altitude-MSL
  3. Calibrated Altitude-Altitude corrected for instrument and installation errors.
  4. Indicated Altitude-Read directly from altimeter (uncorrected).
  5. Pressure Altitude-Altitude indicated when altimeter is set to standard datum plane (29.92).
  6. Density Altitude-Pressure altitude corrected for non-standard temperature.
112
Q
  1. Indicates whether aircraft is climbing, descending, or in level flight.
  2. Indicates rate and trend of climb.
  3. Automatically compensates for temperature.
A

Vertical Speed Indicator

113
Q

GYROSCOPIC INSTRUMENTS

A
  1. Attitude Indicator
  2. Heading Indicator
  3. Turn Coordinator
114
Q

Wheel or disc designed to utilize gyroscopic principles based upon Newton’s Laws of Motion.

A

Gyroscope

115
Q

Mountings of the gyro wheels.

A

Gimbals

116
Q

Any friction applies a deflecting force to a gyro.

A

Bearing Friction

117
Q

Factors affecting gyroscopic inertia:

A
  • Weight-Heavier mass for a given size is more resistant to disturbing forces.
  • Angular Force-higher velocity = greater rigidity.
  • Radius at which the Weight is Concentrated-maximum effect when weight is concentrated near the rim.
118
Q

Resultant action or deflection of a spinning wheel when a deflective force is applied to its rim (

A

Precession

119
Q

Eliminates errors of magnetic compass while providing a consistently reliable source of heading information.

A

Heading Indicator

120
Q

Heading Indicator Errors

A
  1. Misuse of Magnetic compass when setting the DG.

2. Random Drift-Caused by friction and slight imbalances in the gyro and gimbal.

121
Q

Combination of two instruments to sense aircraft movement about the yaw and roll axes.

A

Turn Coordinator

122
Q

Turn Coordinator Errors

A
  1. Insufficient or excessive rotor speed.

2. Inaccurate adjustment of the calibrating spring.

Aircraft Systems AVP 221 (3 decks)

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