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INSTRUMENTATION > PT3 - Inertial nav & FMS & EFIS & FANS > Flashcards

PT3 - Inertial nav & FMS & EFIS & FANS Flashcards

1
Q

INS

A

Inertial Navigation System

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2
Q

INS _ Platform (= mounted on a gimbal assembly)

A

2 accelerometers (N/S and E/W)
Possible third for vertical acceleration
3 integrating gyros (Long, Lateral, Normal)
3 gimbal motors (Pitch, Roll, Vertical)

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3
Q

Integrator

A

Time multiplication device

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4
Q

Integrating gyroscope

A

One degree of freedom gyro using viscous spring

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5
Q

INS _ Compensate for apparent wander

A

Earth rate : 15 sin(lat)

Transport rate : V/R (R = earth radius)

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6
Q

INS _ Alignment

A 
Accelerometers leveled (velocity set to 0)
Platform orientated to True North
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7
Q

INS _ Alignment steps

A

Warm up period
Coarse alignment : roughly leveled and aligned in azimuth
Coarse leveling : pitch and roll at 90°
Fine leveling : zero output from accelerometers
Gyro compassing : verification of position

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8
Q

Schuler period

A

Oscillation of 84.4 minutes

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9
Q

Bounded error

A

Return to 0 within the Schuler cycle

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10
Q

Unbounded error

A

Cumulative error

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11
Q

INS mode

A

OFF - STBY - ALLIGN - NAV - ATT REF

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12
Q

INS _ STBY mode

A

Power supplied

Insert the start position

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13
Q

INS _ ALLIGN mode

A

Platform leveled and aligned

  • -> READY NAV illuminate
  • -> switch to NAV mode
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14
Q

INS _ ATT REF mode

A

Disconnect computing and loses alignment

Gyros used for attitude and heading informations

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15
Q

INS _ BATT light

A

INS running on battery

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16
Q

INS _ NAV mode

A

Used for navigation

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17
Q

INS _ FROM/TO display

A

Waypoints between which INS assume it is flying

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18
Q

INS _ DIM control

A

Change the brightness

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19
Q

INS _ ALERT light

A

Aircraft approaching next waypoint
2 min before in auto mode
2 min before : on - 30 sec : flashing in manual mode

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20
Q

INS _ WARN light

A

System malfunction occurs

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21
Q

INS _ AUTO-MAN_RMT switch

A

Pilot implication

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22
Q

INS _ INSERT control

A

Enter info into the system

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23
Q

INS _ HOLD control

A

Update INS position

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24
Q

INS _ TK/GS display

A

Aircraft track - Ground speed

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25
Q

INS _ HDG/DA display

A

True heading - Drift angle

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26
Q

INS _ XTK/TKE display

A

Cross track distance - Track angle error

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27
Q

INS _ POS display

A

Present latitude - Present longitude

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28
Q

INS _ WPT display

A

Waypoint latitude - Waypoint longitude

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29
Q

INS _ DIS/TIME display

A

Distance to next waypoint - Time to next waypoint

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30
Q

INS _ WIND display

A

Wind direction - Wind speed

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31
Q

INS _ DSR TRK/STS display

A

Desired track - Blank

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32
Q

INS _ TEST display

A

All digits illuminates

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33
Q

INS _ Waypoint 0

A

Last INS position change

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34
Q

INS _ Initial set up

A

Slight latitude error : not recognized by INS
Gross latitude error : recognized by INS
Wrong longitude input : not verified

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35
Q

IRS

A

Inertial Reference System

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36
Q

IRS _ System

A

Strap down system

Laser gyros

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37
Q

INS _ System

A

Stand alone system

Mechanical gyros

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38
Q

Inertial navigation

A

Determination of vehicule’s location without external reference

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39
Q

IRS _ Outputs

A 
Primary attitude
Heading
Acceleration
Angular rate
Inertial velocity
Position
Wind data
Calculated data
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40
Q

INS _ Outputs

A 
Primary attitude
Heading
Acceleration
Position
Track Angle Error
Distance to waypoint
Time to waypoint
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41
Q

IRS _ Inputs

A 
3 laser gyros
3 inertial accelerometers
Initial position
Barometric altitude
True Air Speed
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42
Q

IRS _ Laser gyros

A

Based on Sagnac effect

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43
Q

Sagnac effect

A

2 beams of light rotating in opposite direction
Condition : whole number of wave length
Measure of a frequency difference
–> Compute a rotation

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44
Q

IRS _ Laser gyros - Construction

A 
3 mirrors
2 beams of light
Helium neon
2 photo electric cells
1 piezo electric dither motor
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45
Q

IRS _ Laser gyros - Drift

A

Major source of error

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46
Q

IRS _ Laser gyros - Accuracy

A

The longer the path the greater the accuracy

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47
Q

IRS _ Laser gyros - Lock in

A

Synchronization of the beams

–> no more fringe pattern

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48
Q

IRS _ Alignment

A

True North : with earth rotation measured
Latitude : compute and compare with the inserted one
Alignment : mathematical leveling process
= Establishing the trihedron

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49
Q

IRS/INS _ Advantages

A

Activation : no spin up time
Maneuvering : insensitive to “g” attitude
Construction : mechanically simple and highly reliable
Range : wide dynamic range
Drift : small drift rates

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50
Q

Radio altimeter _ Principle

A

Measuring aircraft’s height above ground level from 2500ft.

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51
Q

Radio altimeter _ Use

A

Automatic landing system

Ground Proximity Warning System (GPWS)

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52
Q

Radio altimeter _ Emission

A

Frequency Modulated Continuous Wave

Change of frequency between emission and reception : compute frequency difference

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53
Q

SHF band

A

4200 to 4400 MHz

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54
Q

UHF band

A

1600 to 1660 MHZ

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55
Q

Radio altimeter _ Working angles

A

Pitch : 30°

Bank : 60°

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56
Q

Radio altimeter _ Pointer

A

Disappear behind mask
Altitude over 2500 ft.
Fault in transmitted signal
Altimeter switched off

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57
Q

Radio altimeter _ Press to test button

A

Press : turn the indicator = test

Turned : select a Low Altitude Index

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58
Q

Radio altimeter _ Boeing

A

2500 to 1000 ft. : nothing
1000 ft. to decision height - 100 ft. : white circle
decision height - 100 ft. to decision height : amber circle

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59
Q

Radio altimeter _ Accuracy

A

Higher between 3% and 1 ft.

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60
Q

Radio altimeter _ Delay

A

Residual height = difference between antenna on the fuselage and bottom of the trailing wheels
Cable length

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61
Q

FSM _ LNAV

A

Lateral NAVigation

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62
Q

FSM _ VNAV

A

Vertical NAVigation

63
Q

CDU

A

Control Display Unit

64
Q

FGS

A

Flight Guidance System

65
Q

FMC

A

Flight Management Computer

66
Q

ADC

A

Air Data Computer

67
Q

GPS

A

Global Positioning System

68
Q

FMS _ CDU

A

Interface between aircraft and crew

69
Q

FMS _ CDU - Independent mode

A

Decoupled operation

70
Q

FMS _ CDU - Dual mode

A

2 computation compared

71
Q

FMS _ CDU - Single mode

A

1 FMS active and distribute to 2 CDU

72
Q

FMS _ Navigation database

A

Information referring to navigation charts
Valid for 28 days
(Nav aids, airports, runways, SIDs, STARs, approaches, company routes)

73
Q

FMS _ Performance database

A

Information required to compute pitch and thrust commands

74
Q

FMS _ Initial action

A

IDENT - POS INIT - RTE - PREF INIT - TAKE OFF

75
Q

FMS _ IDENT page

A

Check databases & OS present and valid for aircraft model

76
Q

FMS _ POS INIT page

A

Insert position and check for time

77
Q

FMS _ RTE page

A

Enter starting and destination airport, select a route, flight number

78
Q

FMS _ PERF INIT page

A

Weight (gross; zero fuel), fuel (qty; reserves), altitude (cruise; transition), cost index, high level winds

79
Q

Cost index

A

Operating cost / Fuel cost

80
Q

FMS _ LNAV

A

Great circle path

81
Q

FMS _ Accuracy

A

Less than 0.5 NM/h

82
Q

FMS _ CDU keys

A

Alphanumeric
Function
Line select

83
Q

FMS _ MSG Annunciator

A

Color = white

Alerting or advisory message

84
Q

FMS _ FAIL Annunciator

A

Color = amber

FMC failure detected

85
Q

FMS _ DISPLAY Annunciator

A

Color = white

Page displayed not relative to active flight plan

86
Q

FMS _ OFFSET Annunciator

A

Color = white

Actually flying on a trajectory with an offset

87
Q

EFIS

A

Electronic Flight Instrument System

88
Q

EFIS _ Displays

A

Attitude and navigation information
Attitude Director Indicator (ADI)
Horizontal Situation Indicator (HSI)

89
Q

EFIS _ Components

A 
Attitude Director Indicator (ADI)
Horizontal Situation Indicator (HSI)
Control panel
Symbol generator
Remote light sensor unit
90
Q

EFSI _ Display unit

A

Cathode Ray Tubes
OR
Liquid Crystal Displays (LCD) : smaller & less heat

91
Q

EFSI _ Colors

A

White : present situation
Green : present situation with less priority
Magenta : ‘fly to’ informations
Cyan : sky heading & low priority information
Yellow : ground shading & caution information display
Red : heaviest precipitations levels

92
Q

EFSI _ Remote Light Sensor

A

Automatically adjust the brightness

93
Q

EFSI _ ADI control panel

A

BRT : brightness control
DH SEL : selector for decision height
DH RST : reset for decision height
DH REF : display decision height

94
Q

EFSI _ ADI display

A 
Pitch and Roll attitude
Attitude from IRS
Flight director commands
Localizer and glide slope deviation
Ground speed
Radio altitude
Decision height
Automatic Flight Control System
Speed error scale
95
Q

Decision height

A

Height above runway elevation by which a go around must be initiated unless adequate visual reference has been initiated

96
Q

EFSI _ Full VOR mode

A

Full compass rose

VOR frequency
Selected course
Course deviation
TO/FROM pointer and annunciator
DME distance
Current heading
Current track
Selected heading
Wind speed and direction
97
Q

EFSI _ Expanded VOR mode

A

90° of compass rose

VOR frequency
Selected course
Course deviation
TO/FROM annunciator
DME distance
Current heading
Current track
Selected heading
Wind speed and direction

Weather radar available with range arcs

98
Q

EFSI _ Full ILS mode

A

Full compass rose

ILS frequency
Selected course
Localizer deviation
Glide slope deviation
DME distance
Current heading
Current track
Selected heading
Wind speed and direction
99
Q

EFSI _ Expanded ILS mode

A

90° of compass rose

ILS frequency
Selected course
Localizer deviation
Glide slope deviation
DME distance
Current heading
Current track
Selected heading
Wind speed and direction

Weather radar available with range arcs

100
Q

EFSI _ Map mode

A

Moving map background
90° of a compass rose

Heading
Active route
Active waypoint & Inactive waypoint
Distance & Time to next waypoint
Wind speed and direction
Lateral & Vertical deviation from selected flight path

Weather radar available with range arcs

101
Q

EFSI _ Plan mode

A

Static map background orientated to True North

Top portion same as map

Planned route

102
Q

EFSI _ Failure annunciation

A

Failure of data signal displayed

Faul messages displayed

103
Q

Present track

A

Predicted ground track from present heading and wind

104
Q

Computers

A

Device or set of device that can store data and a program that operates on the data

105
Q

Computers _ Basic components

A

Input device
Output device
Memory
CPU

106
Q

Computers _ CPU

A

Arithmetic Logic Unit (ALU)
Shift registers
Control unit

107
Q

Computers _ ALU

A

Arithmetic calculations and logical operations

108
Q

Computers _ Shift registers

A

Temporary stores

109
Q

Computers _ Control unit

A

Computer’s clock

Synchronize computer operations

110
Q

ROM

A

Read Only Memory

111
Q

PROM

A

Programmable Read Only Memory

112
Q

EPROM

A

Erasable Programmable Read Only Memory

113
Q

EEPROM

A

Electronically Erasable programmable Read Only Memory

114
Q

Volatile memory

A

Loses data when shut down

115
Q

Non-volatile memory

A

Keep data when shut down

116
Q

RAM

A

Random Access Memory

Normally volatile

117
Q

Permanent memory

A

Electronic chip
Optical disk
Magnetic disk

118
Q

Computers _ Software safety

A

EUROCAE

119
Q

Computers _ Level A

A

Catastrophic

120
Q

Computers _ Level B

A

Hazardous

121
Q

Computers _ Level C

A

Major

122
Q

Computers _ Level D

A

Minor

123
Q

Computers _ Level E

A

No effect

124
Q

FANS _ ATC

A

Use radar to provide a positive control

Use VHF communications

125
Q

FANS _ position update crossing the Atlantic

A

Every 30 to 60 minutes

126
Q

FANS _ GNSS

A

Global Satellite Navigation System

127
Q

FANS _ VHF limitation

A

200 NM

128
Q

FANS _ SATCOM limitation with geostationary satellites

A

80° of latitude

129
Q

FANS _ Data link

A

Connecting one location to another for the purpose of transmitting and receiving informations

130
Q

FANS _ Uplink

A

From ground to satellite or airborne platform

131
Q

FANS _ Downlink

A

From satellite or airborne platform to ground

132
Q

FANS _ Organizations providing Data Link to aviation

A

Société Internationale de Télécommunication Aéronautiques (SITA)
Air Radio Incorporated (AIRINC)

133
Q

FANS _ Equipment for Data Link

A

Communications Management Unit (CMU)
Data Communications Display Unit (DCDU)
Multi Control and Display Unit (MCDU)
Printer

134
Q

FANS _ ACARS

A

Uses Data Link
Messages between aircraft and
Air Trafic Controller (ATC)
Aircraft Operating Companies (AOC)

135
Q

FANS _ ATSU

A 
Provide:
Flight information service
Alerting service
Air Traffic Advisory Service
Air Traffic Control Service
136
Q

FANS _ AOC important messages

A

Out of Gate
Off Ground
On Ground
In Gate

137
Q

FANS _ Logon

A

Manual logon to access the Data Link service

138
Q

FANS _ FANS

A

Provide an integrated air traffic control system in areas where radar is not available

139
Q

FANS _ FANS A

A

Communications, Navigation and Surveillance (CNS)
Automatic Dependent Surveillance (ADS)

Transmitted over the ACARS network

140
Q

FANS _ ADS contracts

A

Periodic
On demand
On event
Emergency

141
Q

FANS _ CPLCD

A

Permis Data Link messages to be generated for all stages of flight

142
Q

FANS _ FANS B

A

Operates within High Density airspace having good VHF coverage

143
Q

Great circle displacement

A

shortest distance between two points on earth

144
Q

INS _ Latitude

A

N/S acceleration integrated

145
Q

INS _ Longitude

A

N/S acceleration integrated
Use of a seccent gear to compute longitude
E/W acceleration integrated

146
Q

ILS

A

Instrument Landing System

147
Q

DME

A

Distance Measuring Equipment

148
Q

FMS _ Use

A

From climb after aircraft is cleaned up until LOC capture

149
Q

EFSI _ HSI limit

A

Magnetic North between 73°N and 65°S

150
Q

EFIS _ Engaged mode color

A

Green

151
Q

EFIS _ Armed mode color

A

White / Cyan

152
Q

EFIS _ Limit of flight enveloppe color

A

Red

153
Q

FMS _ Position computing

A

2 INS/IRS : mean of INS/IRS positions + RadioNAV

3 INS/IRS : ?

154
Q

FMS_ TAKE OFF page

A

Check take off speeds

INSTRUMENTATION (3 decks)

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