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A320/ FCOM > NAV Navigation > Flashcards

NAV Navigation Flashcards

1
Q

The Air Data and Inertial Reference System (ADIRS) supplies ___ to the EFIS system (PFD and ND) and to other user systems (FMGC, FADEC, ELAC, SEC, FAC, FWC, SFCC, ATC, GPWS, CFDIU, CPC).
4 items

A

temperature, anemometric, barometric and inertial parameters

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2
Q

ADIRS system includes:

A

‐ Three identical ADIRUs (Air Data and Inertial Reference Units).
‐ One ADIRS control panel on the overhead panel for selection of modes (NAV, ATT, OFF) and indications of failures.
‐ Four types of sensors:
‐ Eight ADMs (Air Data Modules) which convert pneumatic data from PITOT and STAT probes into numerical data for the ADIRUs.
‐ A switching facility for selecting ADR3 or IR3 for instrument displays in case of ADIRU1 or 2 failure.

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3
Q

Each ADIRU is divided in two parts, either of which can work separately in case of failure in the other:

A
  • The ADR part (Air Data Reference) which supplies barometric altitude, airspeed, Mach, angle of
    attack, temperature and overspeed warnings.
  • The IR part (Inertial Reference) which supplies attitude, flight path vector, track, heading,
    accelerations, angular rates, ground speed and aircraft position.
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4
Q

The Air Data and Inertial Reference System (ADIRS) includes four types of sensors:

A
  • Pitot probes (3)
  • Static pressure probes (STAT) (6)
  • Angle of attack sensors (AOA) (3)
  • Total air temperature probes (TAT) (2)
    These sensors are electrically heated to prevent from icing up.
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5
Q

ADIRU (1) is supplied by CAPT probes,
ADIRU (2) is supplied by F/O probes,
ADIRU (3) is supplied by ___

A

STBY probes and CAPT TAT.

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6
Q

IRS are normally initialized with the FMGC, but IRS may be initialized with the ___ as a backup.

A

ADIRS CDU

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7
Q

MAXIMUM DIFFERENCES BETWEEN SPEED/MACH INDICATIONS
They are provided in order for flight crews to determine if indeed ___ should be requested.

A

maintenance actions

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8
Q

Mach values lower than ___ in climb, and ___ in descent, are not displayed on ISIS.

A

M 0.50 / M 0.45

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9
Q

ADIRS - ABNORMAL OPERATIONS
Backup Speed/Altitude Scale
The BackUp Speed Scale (BUSS) enables to fly the aircraft when

A

airspeed indications are unreliable.

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10
Q

When the BackUp Speed Scale (BUSS) is activated:

A

‐ The BUSS replaces the normal speed
‐ The GPS altitude replaces the barometric altitude scale.

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11
Q

The reversible BUSS is activated and deactivated with two BKUP SPD/ALT pb available on the main instrument panel:

A

‐ One on the left of the Captain PFD
‐ One on the right of the F/O PFD.

Each BKUP SPD/ALT pb independently commands the display of the BUSS on its associated side.

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12
Q

The BUSS information is based on

A

the angle of attack (AOA), and depends on the slat/flap configuration.

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13
Q

ECAM ALERT AND MEMO
The ECAM displays a memo when the flight crew activates the BKUP SPD/ALT on one side:

A

BKUP SPD/ALT.

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14
Q

The non-reversible BUSS is displayed on both PFDs when

A

the flight crew turn off all ADRs.

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15
Q

BACKUP ALTITUDE SCALE
The ___ is no longer displayed.

A

vertical speed indication

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16
Q

SPEED MONITORING FUNCTION
The Speed Monitoring Function is provided by ___. This function uses four different speed sources:

A

FACs

‐ Three ADR speeds
‐ One Backup Speed.

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17
Q

SPEED MONITORING FUNCTION
Backup Speed is computed from AOA, load factor, aircraft weight, GPS altitude and aircraft configuration (ailerons, spoilers, THS, and slat/flap positions). Backup Speed has an accuracy of ___ with a flight domain restricted to 280 kt / M 0.78 in stable flight conditions with speed brakes retracted.

A

+/-15 kt

18
Q

The Speed Monitoring Function consists in:

A

‐ The comparison between those four speed sources
‐ The individual monitoring of each ADR speed in order to detect icing conditions.
The speed monitoring function assigns a validity status to each speed source. This validity status can be: RELIABLE, FAULT or UNCERTAIN.

19
Q

ASSOCIATED ALERTS
As soon as the speed monitoring function detects a change in the speed validity status, the following ECAM alert can be triggered:

A

‐ NAV AIR SPD STS CHANGED
‐ NAV ALL SPD UNCERTAIN

20
Q

DIGITAL BACKUP SPEED/ALTITUDE
The DBUS enables the flight crew to fly the aircraft with

A

the backup speed and backup altitude displayed on PFD.

21
Q

The following ECAM alerts request that the flight crew to activate the DBUS when it is reliable and when at least ___ ADRs are confirmed unreliable:
‐ NAV ADR SPD STS CHANGED
‐ NAV ADR 1(2)(3) FAULT
‐ NAV ADR 1+2(1+3)(2+3) FAULT ‐ NAV ADR 1+2+3 FAULT.

A

two

22
Q

The ECAM displays NAV BKUP SPD FAULT when the

A

DBUS is failed

23
Q

DIGITAL BACKUP SPEED
DBUS activation on the PFD is indicated by:

A

‐ BKUP SPD and GPS ALT labels

‐ Amber double dash over the last digit of speed and mach
‐ Amber double dash over the last two digits of altitude.

24
Q

DIGITAL BACKUP SPEED
When at least one ADR is valid, the computation of the characteristic speeds is based on this valid ADR source.
When all ADR becomes invalid, the characteristic speeds are computed based on ___

A

the backup speed / mach and GPIRS altitude.

25
Q

DIGITAL BACKUP SPEED
When NAV ALL SPD UNCERTAIN is triggered, the red and black strip does not appear as the VSW cannot be computed, however ___ remains fully functional.

A

STALL WARNING alert

26
Q

BACKUP ALTITUDE SCALE AND VERTICAL SPEED SCALE
The vertical speed indication is displayed on DBUS in contrast to ___

A

BACKUP ALTITUDE SCALE on BUSS

27
Q

The Global Positioning System (GPS) is a satellite-based radio navigation aid. Worldwide, ___ satellites broadcast accurate navigation data that the aircraft use for precise determination of its position.

A

24

28
Q

The aircraft has ___ independent GPS receivers. Depending of the aircraft configuration, each receiver consists:
‐ Of a GPS Sensor Unit (GPSSU), or
‐ Is integrated in the Multi Mode Receiver (MMR). The GPS1 receiver in MMR1, and the GPS2
receiver in MMR2.

A

two

29
Q

The GPSSU or the MMR processes the received data, and transfers them to the ___.
Then each ADIRU performs the GP-IRS hybrid position calculation. ___ use this hybrid position.

A

ADIRUs / FMGCs

30
Q

GPS information are available on

A

the FMS – GPS Monitor Page

31
Q
  • During normal operations
    The GPS receiver 1 supplies the ___ and the GPS receiver 2 supplies
    the ___
A

ADIRU 1 and the ADIRU 3 / ADIRU 2

32
Q

STANDBY INSTRUMENTS
Because of the location of the APU power on contactor in the cockpit, the APU start sequence may disturb the

A

compass reading

33
Q

DESCRIPTION OF THE ISIS
The ISIS system displays the following information:

A

‐ Attitude
‐ Airspeed and mach
‐ Altitude
‐ Barometric pressure
‐ LS function
‐ Bugs

34
Q

The ISIS system must be reset after 350 h of continuous electrical supply using

A

the « ATT RST » pushbutton.

The attitude indication can be reset by pressing this pushbutton for at least 2 s. The aircraft must be level during this procedure. During the reset time (approximately 10 s), the “ATT 10 s” message is displayed on the screen. This pushbutton is also used to realign the system, if excessive aircraft movement is detected during the alignment phase.

35
Q

RADIO NAV - TUNING
Three modes of tuning are available
:

A
  1. Automatic Tuning
  2. Manual Tuning
  3. Back Up Tuning
36
Q

RADIO NAV - Back Up Tuning
If both FMGCs fail, the flight crew can use the

A

RMPs (Radio Management Panels 1 and 2) on the pedestal for back up tuning.

37
Q

RADIO NAV - NAVAIDS
- The aircraft has ___ VOR receivers.
- The aircraft has ___ ILS receivers.
- The aircraft has ___ DMEs.
- ___ marker beacon system is included in VOR receiver 1.

A
  • 2
  • 2
  • 2
  • 1
38
Q

The aircraft has ___ radio altimeters (RA).

A

2

CAPT PFD displays the RA1 height, and the F/Os PFD displays the RA2 height. If one RA fails, both PFDs display the height from the remaining RA.

39
Q

The ___ generates a synthetic voice for radio height announcement below 2 500 ft. These announcements come through the cockpit loudspeakers, even if the SPEAKERS ARE TURNED OFF.

A

FWC

40
Q

INTERMEDIATE CALL OUT
If time between two consecutive predetermined call outs exceeds a certain threshold, the present height is repeated at regular intervals.
The threshold is:
‐ 11 s above 50 ft
‐ 4 s below 50 ft
The repeating interval is ___

A

4 s.

41
Q

RETARD ANNOUNCEMENT
The loudspeaker announces RETARD at:
‐ 20 ft, or
‐ 10 ft if autothrust is active and one autopilot is in

A

LAND mode.

A320/ FCOM (32 decks)

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