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AIRCRAFT AVIONICS AND AUTOPILOT SYSTEM > PRELIM > Flashcards

PRELIM Flashcards

1
Q

It refers to a system that can significantly reduce workload during phases of flight. It also refers to a collection of systems that automate a plane’s operations.

A

AUTOPILOT

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2
Q

It tells your plane how to fly, including navigation, altitude, speed, and engine thrust, which controls the force by which the plane moves through the air.

A

Complex Computer Matrix

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3
Q

It describes a complete flight from departure to arrival.

A

Flight Plan

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4
Q

interface between the pilot and the FMS

A

Multipurpose Control and Display Unit (MCDU)

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4
Q

In cases of an autopilot, the FAA mandates that pilots be “________” for takeoffs and landings.

A

hands-on

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5
Q

on-board multi-purpose navigation, performance, and aircraft operations computer

A

Flight Management System (FMS)

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5
Q

capability to fly any desired flight path defined by waypoints

A

Area Navigation (RNAV)

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5
Q

Important component on the first aircraft autopilot

A

gyroscopic heading indicator & attitude indicator

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5
Q

Name of the Wright Brothers?

A

Wilbur & Orville Wright

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5
Q

Where was the first test flights of the Wright Brothers?

A

Kitty Hawk, North Carolina

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5
Q

Who and when was the credibility of autopilot demonstrated?

A

Lawrence Sperry, 1914

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6
Q

When was the first two gliders of the Wright Brothers flown?

A

1900 and 1901

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6
Q

Why did the first two gliders of the Wright Brothers fail?

A

there’s not enough lift and not fully controllable

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7
Q

The first aircraft autopilot was developed by _______ on _____.

A

Sperry Corporation, 1912

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8
Q

Who helped the brothers build a gasoline engine (that is light enough to propel an airplane and difficult controls)

A

Charlie Taylor

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9
Q

made it possible to fly during night and bad weather

A

a
Radio Navigation Aids

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9
Q

Other further developments of the autopilot include __________ and ________.

A

improved control algorithms, hydraulic servomechanism

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10
Q

gives inertial rotation data of an aircraft

A

laser gyro

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11
Q

When at rest, in a laser gyro, the two beams get to the sensor with the _________.

A

same frequency

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12
Q

What creates a difference of frequency between two beams?

A

aircraft rotation

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13
Q

After computation of the frequency difference, this output will provide _________ of the aircraft.

A

rotation information

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13
Q

It is measured by optical providing an analog output, which is sent to the analog to digital converter.

A

frequency difference

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14
Q

LASER is usually found in the ____________ along with CG of the aircraft.

A

center cabin floor panel

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14
Q

Give at least three disadvantages of auto pilot

A

-Automation – induced failures

-False alarms

-Boredom

-Over-reliance, complacency; willing to accept results without scrutinizing them first

-Reduced alertness of operator, by offering a false sense of security

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14
Q

Advantages of auto pilot

A

-Reduces manual workload and fatigue

-Relief from small errors

-Precision in the handling of routine tasks

-Increased productivity

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15
Q

If Laser Gyro fails, use the backup attitude gyro located on _____________.

A

cockpit instrument panel

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15
Q

If Laser Gyro fails, use the _______ located on cockpit instrument panel.

A

backup attitude gyro

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16
Q

wha is the pilot’s main role

A

maneuver the airplane from A to B safely and efficiently

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16
Q

Five sub-tasks of a pilot

A

-to operate, manage, and to monitor the engines and airplane control systems: Lights off Principle on Pushbutton Switches

-to avoid inadvertent encounters with either unfriendly terrain or with objects on the ground

-to navigate efficiently to the destination airport

-to ensure comfort to the passengers and crew by operating and monitoring such systems as pressurization and temperature control

-to communicate with company operations and with ATC

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17
Q

It contains the elements from which the flight plan is constructed.

A

Navigational Data Base (NDB)

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18
Q

contains all of the information required for building a flight plan

A

Navigational Data Base (NDB)

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19
Q

information required to build a flight plan

A

airways
airports
Standard Terminal Arrival (STAR)

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20
Q

consists of gyro, rate gyros, accelerometer, pitot-static system, and air temperature probes

A

detecting element

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20
Q

detect the movement of the aircraft about its three flight axes and the rate of that movement

A

detecting element

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20
Q

Pilots must understand the way databases are compiled and revised by the _______ and processed by the _________; updated every ___ days.

A

database provider, avionics mechanic, 28

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21
Q

considered to be internal controls or inner loop of the system

A

detecting element

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21
Q

brain of the system

A

computer amplifier

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21
Q

Basic AFCS consists of:

A

-sensing element
-command element
-output element
-computer/amplifier

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22
Q

considered to be external controls or the outer loop of the system

A

command element

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22
Q

consist of the pilot’s control panel and manually operated controls that include the pilot’s stick, rudder pedals, and navigation

A

command element

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23
Q

computes, amplifies, and processes the signal from the detecting and command element

A

computer amplifier

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24
Q

directs the output element to respond to the pilot’s and or system requirements

A

computer amplifier

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25
Q

consists of units, which move the control surfaces of the aircraft in response to the computer demands

A

output elements

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26
Q

Autopilot modes are capable of maintaining set of operating parameters using Flight Control Unit (FCU) which can include:

A

attitude hold
heading hold
vertical speed hold
altitude hold

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27
Q

Consists of the detection, amplification, correction, follow up, and the aircraft response loop

A

Basic AFCS Loop

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28
Q

It refers to a system of automatic controls which holds the aircraft on any selected magnetic heading and returns the aircraft to that heading when it is displaced from it.

A

Automatic Pilot

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28
Q

functions to cancel the input signal by applying an opposite signal proportional to the command required to bring the aircraft to the desired attitude

A

follow up signal

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29
Q

keeps the aircraft stabilized around its horizontal and lateral axes

A

Automatic Pilot

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30
Q

provide for one, two, or three stabilized planes.

A

Autopilot systems

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31
Q

Movement within each plane is _______, rather centered on axis.

A

about an axis

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32
Q

three principal axes

A

longitudinal, lateral, vertical

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33
Q

runs nose to tail through the CG

A

longitudinal axis

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34
Q

axis on the x-axis

A

longitudinal

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34
Q

runs perpendicular to the other two axes intersecting them at the CG

A

vertical axis

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35
Q

runs parallel with a line from wing tip to wing tip and intersects the x-axis at the CG

A

lateral axis

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36
Q

axis on the z-axis

A

vertical

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36
Q

axis on the y-axis

A

lateral

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36
Q

On ________, the power to move the control surfaces is provided by the muscles in the pilot’s arms and legs.

A

small light aircraft

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37
Q

The control column is physically connected to the control surfaces by ________.

A

cables

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38
Q

Wide bodied aircraft will corporate some form of _________ to move control surfaces.

A

power assistance

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38
Q

On __________, it is physically impossible to move the control surfaces by muscle alone.

A

larger aircraft

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39
Q

The __________ is provided by actuators or servo and these devices can operate from either mechanical input or electrical output.

A

power assistance

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40
Q

fifth element of many advanced autopilot systems

A

feedback or follow-up

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41
Q

When an aircraft fails to meet the conditions selected, an _____ is said to have occurred.

A

error

41
Q

This refers to signals sent as corrections are being made by the output elements to advise the autopilot of the progress being made.

A

feedback or follow-up

42
Q

This is the basis for autopilot system operation.

A

error correction

43
Q

A _________ uses information about the rate of movement of the aircraft, and move control surfaces to counter the rate of change that causes the error.

A

rate-based autopilot

43
Q

Two basic ways modern autopilot systems do for error correction

A

position-based autopilot, rate-based autopilot

44
Q

manipulates the aircraft’s controls so that any deviation from the desired attitude of the aircraft is corrected.

A

position-based autopilot

45
Q

is done by memorizing the desired aircraft attitude and moving the control surfaces so that the aircraft returns to that attitude.

A

position-based autopilot

46
Q

What type of autopilot system do most large aircrafts use?

A

rate-based autopilot

47
Q

Its basis is “Gyro, accelerometers, and others and other sensor equipment can detect the uncommand attitude changes far more accurately and then provide an electrical output to an actuator or servo.”

A

Fly-By-Wire Principle

48
Q

When the pilot moves the control column or rudder pedals, an electrical signal from the stick or ________ is transmitted to an electrically operated actuator and the control surface is deflected by pilot’s input.

A

pedals transducer

49
Q

When the pilot moves the control column or rudder pedals (a commanded attitude change), an electrical signal from the stick or pedals transducer is transmitted to an electrically operated actuator and the control surface is deflected by pilot’s input. In this electrically operated system, it is _________, not _________, which control the actuator or servo operation.

A

electrical signals, mechanical inputs

50
Q

The _________ of the aircraft provide the flight control computer with inputs of heading, attitude, waypoints, etc.

A

avionics system

51
Q

The avionics system of the aircraft provide the flight control computer with inputs of heading, attitude, waypoints, etc. and the flight control computer repositions the actuator with electrical signals to maintain the aircraft on the programmed flight path. What is this called?

A

autopilot

51
Q

The ____________ repositions the actuator with electrical signals to maintain the aircraft on the programmed flight path.

A

flight control computer

52
Q

Give at least one advantage of fly-by-wire principle

A

-improved reliability

-damage tolerance

-more effective control of a necessary highly maneuverable plane

53
Q

Give at least one disadvantage of fly-by-wire principle

A

-redundancy (airline operator)
-complexity
-cost

54
Q

Gyro-sensing units are connected to flight instruments that indicate _______, _______, ______, or _____.

A

direction, rate of turn, bank, pitch

54
Q

The automatic pilot system flies the aircraft by using electrical signals developed in ___________.

A

gyro-sensing units

55
Q

If the flight attitude or magnetic heading is changed, _____________ are developed in the gyros.

A

electrical signals

55
Q

The electrical signals developed in the gyros when the flight attitude or magnetic heading is changed are sent to the autopilot computer/amplifier and are used to control the operation of _________.

A

servo units

56
Q

A servo for each of the three control channels converts electrical signals into ________, which moves the control surface in response to corrective signals or pilot commands.

A

mechanical force

57
Q

The components used in an Auto flight control system (AFCS) to move the aircraft’s control
surfaces are called ______ , ________or by the name of the control surfaces or channel
that it controls.

A

servomotors, servo actuators

58
Q

All flight controls are hydraulically operated by the actuators which receive electrical signals
from the computer except the ______ and the _______

A

Rudder and the Trimmable Horizontal Stabilizer (THS)

59
Q

powered by two servo controls

A

Aileron

60
Q

are powered by their dedicated PCU

A

The Flaps and Slats surfaces

61
Q

is powered by a single servo

A

Spoiler surface

61
Q

is powered by 3 servo controls.

A

rudder surface

62
Q

powered by 2 servo controls

A

elevator surface

62
Q

The servo actuators convert these electrical signals into control surface movement by
converting the ________into ____________, which is usually done by torque motors

A

electrical,mechanical motion

63
Q

moved by one actuator

A

THS

64
Q

The _________ received from the AFCS are electrical. Therefore, the control of the _________ is
electrical.

A

signals, actuators

65
Q

The servo actuators convert these electrical signals into control surface movement by
converting the electrical into mechanical motion, which is usually done by ______________

A

torque motors

66
Q

Servomotors maybe connected in _________ or ________ with the AFCS.

A

series or parallel

67
Q

A ____________ is
one that moves the control surfaces without moving pilot’s control

A

series servomotor

68
Q

the ________________
moves control surfaces and the pilot’s control.

A

parallel servomotor

69
Q

Three main types of actuators

A

-electric motor
-ecltro-pneumatic
-electro-hydraulic

70
Q

the biggest feature of _____________ is high safety, cheap price and fast response speed.

A

Pneumatic Actuator

71
Q

It uses compressed gas as the power source.

A

pneumatic actuator

72
Q

Among the three types of actuators, _____________ has the advantages of fire proof, explosion proof, safe fault location and simple
operation.

A

pneumatic actuator

73
Q

They are suitable for use in petrochemical, petroleum, and oil processing industries.

A

pneumatic actuator

74
Q

The disadvantage of _________ is its poor stability, which is due to gas compressibility,
which makes ________ lack sufficient anti offset performance.

A

pneumatic actuator

74
Q

the advantages of _________ are that it is
cost effective, easy to use, install and maintain and has relatively low technical requirements for
personnel.

A

pneumatic actuator

75
Q

________ has a large output thrust
and high stability, but at the same time the
cost is lower than hydraulic actuator, which
is a cost-effective choice.

A

Electric actuator

76
Q

receives electric signal,
which is prone to sparking problems.

A

Electric actuator

76
Q

The parameter control of _________
is very accurate, but its structure is complex, the failure rate is higher than that of pneumatic actuator, and it requires professional personnel with higher technical level to operate and maintain it.

A

electric actuator

76
Q

The downsides of ___________ include backlash, jamming and thermal management issues.

A

electromechanical actuators

77
Q

A primary benefit of electromechanical
actuators compared to conventional
electrohydraulic actuators is their ______________.

A

elimination of hydraulic fluid

78
Q

__________________ may appear to be an
optimal solution for more-electric and all-electric
aircraft, since they completely eliminate the need for
hydraulic fluid.

A

Electromechanical actuators

78
Q

_________ can occur due to
gaps between interlocking gear teeth or screw
threads and results in positional inaccuracies.
It can increase as repeated wear cycles cause surface degradation.

A

Backlash

79
Q

____________ is a risk for
electromechanical actuators due to potential failures involving screw components interfering or seizing up, preventing motion of the actuator.

A

Jamming

80
Q

The performance advantages of __________ are many, such as large output thrust, good
offset resistance, precise control, fast response speed, stable operation and etc.

A

hydraulic actuator

81
Q
A
81
Q

Hydraulic actuator is driven by _________.

A

liquid

82
Q

The liquid has the characteristics of _________ , _______________, and __________.

A

incompressibility, good anti offset ability and very stable adjustment

83
Q

The disadvantages of _________ are the high cost and large volume. To run _______, hydraulic stations and oil pipelines are required.

A

hydraulic actuator

84
Q

The ________ increases the risk of leakages and requires a large volume
of hydraulic fluid.

A

large hydraulic network

84
Q

These are used in high performance aircraft and consist of two main types:

A

 Power-Assisted
 Power-Operated

84
Q

The ___________ also requires a system of pipes to deliver pressurized hydraulic fluid to actuators distributed throughout the aircraft, adding additional weight and taking up
space.

A

central hydraulic network

85
Q

In the _______________, the pilot’s control stick is connected to the control surface via a control
lever.

A

power-assisted system

85
Q

The continuous energy
expenditure results in heating of the hydraulic fluid, requiring a ___________ to maintain
acceptable hydraulic fluid temperature.

A

cooling system

86
Q

In a ___________, the pilot’s control column movements are interpreted by a flight computer that sends
electrical signals to actuator control electronics.

A

fly-by-wire
system

86
Q

________ are displaced allowing the hydraulic fluid to flow to the left side of the actuating jack, which is secured to the structure
of the aircraft.

A

control valve pistons

87
Q

__________ enabled aircraft manufacturers to integrate
more electrically powered actuators in airplane systems such as electro hydrostatic actuators
and electromechanical actuators.

A

Fly-by-wire systems

87
Q

The _________ instruct the operation of
either hydraulic control valves to set in motion hydraulic actuators or electric motors to move
electromechanical actuators.

A

control electronics

88
Q

__________________ have excellent power density (kW/kg) at the equipment
level but poor power density at the power distribution network level.

A

Conventional electrohydraulic actuators

88
Q

The pressure exerted on the piston causes the whole servo unit and control level to move _________ and because of the greater control effort produced, the pilot is assisted in moving the control surfaces

A

move left

89
Q

calculates orders to automatically control the flight controls and
the engines.

A

Automatic Flight System (AFS)

90
Q

The ____________ calculates the position of the aircraft using several aircraft sensors.

A

Automatic Flight System AFS

91
Q

These actuators are powered by electricity produced by
engine- driven generators delivered over power-by-wire systems

A

electro hydrostatic actuators and electromechanical actuators.

91
Q

The Auto Flight System (AFS) is divided into four main parts:

A

 Flight Management (FM),
 Flight Guidance (FG),
 Flight Augmentation,
 Fault Isolation and Detection System (FIDS).

92
Q

AFS computes orders and sends them to the ________ and to the ________ to control flying surfaces and engines.

A

Electrical Flight Control System (EFCS), Full Authority Digital Engine Control (FADEC)

92
Q

A _________ describes a
complete flight from departure to arrival; it gives vertical information and all intermediate waypoints.
The plan can be displayed on the EFIS or on the Multipurpose Control & Display Units.

A

flight plan

93
Q

When the
AFS is not active, the above-mentioned components are controlled by the same systems but orders are generated by the_______ and ____________.

A

side sticks and thrust levers

93
Q

A fundamental function of the AFS is to calculate the aircraft position. To compute the aircraft
position, the system uses several aircraft sensors, which give useful information for this purpose.

A

NAVIGATION

94
Q

The FG part has 3 functions:

A

Autopilot (AP),
Flight Director (FD),
Auto thrust (A/THR).

94
Q

A flight plan describes a
complete flight from departure to arrival; it gives vertical information and all intermediate waypoints. The plan can be displayed on the ______ or __________.

A

EFIS or on the Multipurpose Control & Display Units

95
Q

The __________ has several functions linked to the flight plan such as lateral and vertical guidance associated with
performance
computation.

A

FM part

95
Q

_________ calculates the signal for the flight controls in order to follow the selected modes.

A

Autopilot

96
Q

Auto Pilot engagement

A

 Two AP (Auto Pilot) pushbutton
switches located on Flight Control
Unit (FCU)
 Provide short term control

96
Q

These modes
can be adjusted using Flight Control Unit (FCU) which can include:

A

 Attitude Hold
 Heading Hold
 Vertical Speed Hold
 Altitude Hold

96
Q

 Two AP (Auto Pilot) pushbutton
switches located on __________

A

Flight Control Unit (FCU)

97
Q

The ____________ is the primary entry/ display interface
between the pilot and Flight Management and
Guidance Computer

A

Multipurpose Control and Display Unit MCDU

97
Q

Auto Pilot Disengagement

A

 Side Stick Push Button
 By force
 AP Pushbutton on FCU

98
Q

Primary Flight Display (PFD)

A

-show the flight parameter (basic 6 instruments) and its display Autopilot engagement.

99
Q

Upper ECAM/ Engine Warning Display Divided into 2 sections:

A

 Upper Area
 Lower Area

100
Q

-Shows the flight plan

A

Navigational Display

101
Q
  • Shows engine parameters
A

ECAM Upper Area

102
Q
  • Dedicated to warning
    messages and memo.
A

ECAM LOWER AREA

103
Q

The ________ display the guidance commands on both PFDs.

A

Flight Directors

103
Q

displays symbols on the PFD which gives orders to the pilot to maintain the desired
parameters.

A

Flight Directors function

104
Q

-shows 11 system pages

A

Lower ECAM/ System Display Pages (SD)

105
Q

-The FD function displays symbols on the PFDs representing the ________ to be monitored by the pilot.

A

AP orders

106
Q

The _________ fulfils the following functions through the control of the thrust: Speed or Mach hold, Thrust hold, Thrust
reduction during descent and during flare in final approach, Protection against insufficient speed linked to excessive angle of
attack.

A

AUTOTHRUST

107
Q

Auto thrust Engagement for manual and automatic

A

Manual: Pressing the A/THR on FCU
Automatic: When the A/P is engaged in take off (TO) or Go Around (GA)

108
Q

To fulfil the A/THR functions, the FMGCs communicate with the Full Authority Digital Engine Control (FADEC) via the ________ and the ________.

A

FCU and the Engine Interface Units (EIUs)

AIRCRAFT AVIONICS AND AUTOPILOT SYSTEM (1 decks)

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