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QT A320 > ATA22 - Autoflight > Flashcards

ATA22 - Autoflight Flashcards

1
Q 
454. In which cases are AP/FD, A/THR and LANDING capacities (CAT2 & 3) totally lost ?
2 IRS's failure or ADR's failure
2 RA's failure
2 ILS's failure
Both FAC's failure
A

2 IRS’s failure or ADR’s failure

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2
Q
  1. The LOC P/B on the FCU is pressed to ARM LOC MODE. This MODE is used for :
    Performing a published localizer approach
    Tracking a VOR BEAM during an approach
    Performing a published localizer approach and tracking a VOR BEAM during an
    approach
A

Performing a published localizer approach and tracking a VOR BEAM during an
approach

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3
Q 
456. The TRIM function of the FAC is :
A PITCH TRIM
A RUDDER TRIM
An AILERON TRIM
A PITCH TRIM and a RUDDER TRIM
A

A RUDDER TRIM

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4
Q 
457. In CRUISE, lateral AP orders are executed by :
AILERONS and SPOILERS
AILERONS and RUDDER
RUDDER and SPOILERS
AILERONS, RUDDER, SPOILERS
A

AILERONS, RUDDER, SPOILERS

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5
Q
  1. On the FMA, on the second line of the longitudinal zone :
    ALT can be only in green or magenta
    ALT in cyan indicates that ALT MODE is active
    ALT in cyan indicates that ALT MODE is armed
A

ALT in cyan indicates that ALT MODE is armed

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6
Q
  1. What does a triple click mean, during an ILS approach ?
    A level 3 warning to the crew
    Landing capability downgrading warning
    FLAPS are set at 3 and the L/G is not down
A

Landing capability downgrading warning

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7
Q
  1. The EXPEDITE MODE is active, to disengage it , one of these statements is not
    correct :
    Pull the V/S-FPA KNOB
    Pull the SPD KNOB
    Press again the EXPD P/B to cancel this mode
A

Press again the EXPD P/B to cancel this mode

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8
Q
  1. The mandatory parameter used by the ALPHA FLOOR DETECTION is :
    A/C minimum speed
    A/C weight
    A/C angle of attack
A

A/C angle of attack

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9
Q
  1. The BARO correction or reference selected is sent at each ADIRU via :
    The FCU
    The RMPS
    The DMCS
A

The FCU

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10
Q
  1. What are the basic MODES of the AP/FD :
    V/S and HDG
    ALT and NAV
    SPD and HDG
A

V/S and HDG

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11
Q
  1. The AFS computers are :
    FMGC and ELAC
    FMGC and SEC
    FMGC and FAC
A

FMGC and FAC

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12
Q
  1. The continuous cavalry charge audio identifies only one of the following situations :
    Over speed for the actual A/C configuration
    FIRE or OIL LO PR on one engine
    AUTOPILOT disengagement
    Excessive cabin altitude
A

AUTOPILOT disengagement

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13
Q 
466. The active F-PLN is erased when :
The pilot calls the A/C STATUS PAGE
The wheels touch the runway at landing
The A/C has been on ground for 30 sec following the landing
One engine is shut down at parking place
A

The A/C has been on ground for 30 sec following the landing

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14
Q
  1. AUTO FLIGHT maximum wind conditions for CAT2 or CAT3 AUTOMATIC APPROCH
    LANDING and ROLL OUT are :
    HEAD WIND : 30 kts / TAIL WIND : 10 kts / CROSS WIND : 20 kts
    HEAD WIND : 40 kts / TAIL WIND : 10 kts / CROSS WIND : 15 kts
    HEAD WIND : 20 kts / TAIL WIND : 10 kts / CROSS WIND : 20 kts
A

HEAD WIND : 30 kts / TAIL WIND : 10 kts / CROSS WIND : 20 kts

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15
Q
  1. The FAC compute RUDDER TRAVEL limit :
    Only when AP is engaged
    Only at LOW SPEED
    At any time
A

At any time

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16
Q
  1. Setting THRUST LEVERS at IDLE will disconnect the A/THR MODE. A/THR will
    activate :
    As soon as THRUST LEVERS position is changed
    When A/THR P/B is pressed
    Provided the LEVERS are set in CLB detents
A

When A/THR P/B is pressed

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17
Q
  1. After a complete lost of generator (engines & APU), EMERGENCY GEN supplies the
    A/C :
    FMGC 1 only is available (NAV function only)
    FMGC 2 only is available
    Both FMGCS are available
A

FMGC 1 only is available (NAV function only)

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18
Q
  1. On ground, the AUTOTHRUST arming function :
    Must be carried out manually by the crew before TAKE-OFF
    Is performed automatically upon the second engine start
    Is performed automatically at the engagement of the TAKE-OFF MODES
A

Is performed automatically at the engagement of the TAKE-OFF MODES

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19
Q 
472. The FLIGHT GUIDANCE functions are :
AUTOPILOT, FLIGHT PLAN, A/THR
AUTOPILOT, PERFORMANCE , FLIGHT PLAN
AUTOPILOT, FLIGHT DIRECTOR, A/THR
FLIGHT MANAGEMENT, AUTOPILOT, A/THR
A

AUTOPILOT, FLIGHT DIRECTOR, A/THR

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20
Q 
473. The normal FMGC operation is :
Only one FMGC can compute at a time
FMGC 1 has priority, FMGC 2 is in STBY
FMGC's operate according to MASTER/SLAVE principle
FMGC's operate independently
A

FMGC’s operate according to MASTER/SLAVE principle

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21
Q
  1. For A/C POSITION determination, FMGC uses DATA from :
    DME, VOR, LOC or GPS
    3 ADIRS (MIX IRS)
    Both answers are correct
A

Both answers are correct

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22
Q
  1. When both FACs are valids, YAW DAMPER functions are controled :
    YAW DAMPER 1 has priority, YAW DAMPER 2 is in STANDBY
    YAW DAMPER 2 has priority, YAW DAMPER ACTUATOR 1 is slaved
    YAW DAMPER 1 and 2 are ACTIVE, the TWO ACTUATORS are pressurized
A

YAW DAMPER 1 has priority, YAW DAMPER 2 is in STANDBY

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23
Q
  1. THRUST LEVERS are in the CLB DETENT, if A/THR is disconnected : the engine
    THRUST
    Equals CLB THRUST LIMIT
    Is locked at the current THRUST
    Corresponds to the THRUST LEVERS position
    Progressively becomes equal to the THRUST LEVERS position
A

Is locked at the current THRUST

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24
Q
  1. When AP is engaged in APPR or in ROLL OUT MODE, the YAW DAMPER
    ACTUATOR is controlled by :
    A YAW order computed by the FAC
    An AP YAW order computed by the FMGC, via the FAC
    A turn coordination order computed by the FAC
A

An AP YAW order computed by the FMGC, via the FAC

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25
Q
  1. Regardless of the initial status of the A/THR and the position of the THR levers, when
    an ALPHA FLOOR is detected :
    A/THR is not engaged because the engines are already in CLB thrust
    A/THR automatically engages, but is not active
    A/THR automatically activates and controls the engines with TO/GA thrust
A

A/THR automatically activates and controls the engines with TO/GA thrust

26
Q
  1. A HOLDING PATTERN has been entered in the F-PLN, SPEED and NAV are
    managed. You want to leave this hold :
    Use the OVFY key
    “HOLD” is automatically cancelled when overflying the FIX
    Activate “IMM EXIT” prompt or do a Direct To xx
A

Activate “IMM EXIT” prompt or do a Direct To xx

27
Q
  1. The FCU allows :
    Modification of the flight plan of FM PART
    Selection of FG FUNCTIONS MODES
    Selection of RADIO-NAV frequencies
A

Selection of FG FUNCTIONS MODES

28
Q
  1. CLIMB and DESCENT phases are always limited :
    By flight plan (T/C. and (T/D) points
    By the ALTITUDE manually selected on the FCU
    By the aircraft weight calculated by the FMGC
A

By the ALTITUDE manually selected on the FCU

29
Q
  1. In flight, A/C without GPS, the FMGS position can be updated :
    Whenever a DME STATION is selected by the pilot
    Using DATA from the selected NDB, VOR or DME STATIONS
    Automatically by using the radio position
A

Automatically by using the radio position

30
Q
  1. In flight, AP engaged and A/THR ACTIVE, the A/THR MODE :
    Can be choosen by the pilot on the FCU
    Can be choosen by the pilot on the MCDU
    Depends on the AP VERTICAL MODE
A

Depends on the AP VERTICAL MODE

31
Q
  1. When SRS MODE is engaged :
    A/THR automatically arms and is active
    A/THR automatically arms but is not active
    A/THR does not automatically arm and the engines are controlled by the THRUST
    LEVERS
A

A/THR automatically arms but is not active

32
Q
  1. The engagement of both AUTOPILOTS is possible :
    After APPR P/B switch is pressed and illuminates
    When A/C is stabilized at G/S interception altitude
    As soon as the LOC has been intercepted
A

After APPR P/B switch is pressed and illuminates

33
Q 
486. Normal electrical power supplies the A/C and the MCDU CRT is dark, without any other
warning, it means :
The FMGC is OFF
The FMGC has failed
The 'BRT' knob is dimmed
A

The ‘BRT’ knob is dimmed

34
Q
  1. Both AP’s are not engaged, both FD’s are engaged and A/THR is active :
    FMGC 1 controls engine 1, FMGC 2 controls engine 2
    FMGC 1 controls both engines
    FMGC 2 controls both engines
    Flight controls and engines are controlled by only one FMGC
A

FMGC 1 controls both engines

35
Q
  1. Control of the A/C can be automatic or manual guidance. The A/C can be in managed
    or Selected mode. How do you understand this situation : managed guidance - manual
    control - Selected speed ? :
    Stall warning is activated
    THR LK flashes on FMA
    ALPHA FLOOR function operates
A

ALPHA FLOOR function operates

36
Q
  1. Control of the A/C can be automatic or manual guidance of the A/C can be managed or
    selected how do you understand this situation : managed guidance - manual control -
    selected speed :
    FMGC computes and sends steering orders for navigation purpose. The pilot flies
    through the side stick and speed is manually set on the FCU
    The AUTOPILOT follows the F-PLN. The pilot sets the necessary DATA for lateral
    and vertical navigation and speed is automatically set from FMGC
A

FMGC computes and sends steering orders for navigation purpose. The pilot flies
through the side stick and speed is manually set on the FCU

37
Q
  1. RUDDER TRAVEL LIMITATION is a function of :
    FAC only
    FAC in normal and ELAC in alternate
    ELAC only
A

FAC only

38
Q
  1. Can you display FD BARS and FPV at the same time, for CROSS-CHECKING on
    different PFD’S :
    Yes
    No
A

No

39
Q 
492. On ground, when electrical power is initially supplied to the A/C, the MCDU will
automatically display :
AIRPORT PAGE
INIT A PAGE
A/C STATUS PAGE
A

A/C STATUS PAGE

40
Q
  1. The SAFETY TESTS are automatically performed :
    On ground, at computer power up
    In case of discrepency between 2 computers
    In flight when a failure occurs
A

On ground, at computer power up

41
Q
  1. During TAKE-OFF and GO AROUND, the speed window on the FCU displays :
    The speed manually inserted by the crew into the FCU and the light is OUT
    The speed manually inserted by the crew into the MCDU and the light is illuminated
    Dashes and the light is illuminated
A

Dashes and the light is illuminated

42
Q
  1. In which case A/THR does not disengage ?
    When the two THRUST LEVERS are set at IDLE POSITION
    Pressing the A/THR P/B on the FCU
    When the aural warning announces ‘RETARD’
A

When the aural warning announces ‘RETARD’

43
Q
  1. The FMGS consists of the following main components :
    2 FMGCs - 2 MCDUs - 2 FACs - 2 FCU CONTROL PANELS
    2 FMGCs - 2 MCDUs - 2 FACs - 1 FCU CONTROL PANEL
    2 FMGCs - 2 MCDUs - 2 ECAMs - 1 FCU CONTROL PANEL
A

2 FMGCs - 2 MCDUs - 2 FACs - 1 FCU CONTROL PANEL

44
Q 
497. In flight, in case of temporary loss of electrical power on FAC 2, FAC 2 P/B 'FAULT'
comes on and :
It will reset automatically
There is no way to reengage FAC 2
It can be reset manually
A

It can be reset manually

45
Q
  1. The position of the aircraft, used in the flight plan is computed by :
    FG PART of the FMGC
    FM PART of the FMGC
    The MCDU
A

FM PART of the FMGC

46
Q
  1. The FLIGHT DIRECTOR is automatically engaged :
    At system power up
    By selecting a mode on the FCU
    By selecting the INIT PAGE on the MCDU
A

At system power up

47
Q
  1. In normal operation, when both MCDUs are showing the same PAGE, a modification
    made by the pilot on MCDU 1 is sent to MCDU 2 :
    Directly
    Via FMGC 1
    Via FMGC 1 then FMGC 2
    Via FMGC 1, FMGC 2 and RMP 2
A

Via FMGC 1 then FMGC 2

48
Q
  1. The following AP/FD LATERAL MODES are managed :
    NAV, HDG, APPR, LOC, RWY, RWY TRK
    HDG, NAV, APPR, LOC, GA TRK
    NAV, APPR, LOC, RWY, RWYTRK, GA TRK
A

NAV, APPR, LOC, RWY, RWYTRK, GA TRK

49
Q 
502. With AUTOPILOT engaged, the RUDDER TRIM or YAW functions are normally
controlled by :
The FMGC
The FAC, via the FMGC
The ELAC
The SEC
A

The FAC, via the FMGC

50
Q
  1. The FMGC functions are :
    Flight guidance and flight envelope protection
    Flight management and flight envelope protection
    Flight management and flight guidance
    Flight envelope protection and yaw axis control
A

Flight management and flight guidance

51
Q
  1. One of the SRS disengagement conditions is not true :
    If the crew engages another vertical mode
    Disengages automatically at acceleration altitude
    Disengages manually by pulling the speed KNOB
    Disengages by setting a new FCU altitude
A

Disengages by setting a new FCU altitude

52
Q
  1. The AUTOPILOT disengages when :
    The pilot moves on the SIDESTICK harder than a certain threshold or pushes the
    RUDDER PEDALS 10°C out of trim
    The pilot moves the PITCH TRIM WHEEL beyond a certain threshold
    Both answers are correct
A

Both answers are correct

53
Q
  1. A/THR can be armed :
    Manually on ground (engines running), automatically after TAKE-OFF
    In flight, manually or automatically if there is an ALPHA FLOOR detection
    Automatically when pilot initiates a TAKE-OFF or a GO AROUND
A

Automatically when pilot initiates a TAKE-OFF or a GO AROUND

54
Q
  1. During TAKE-OFF, FMA shows ‘SRS’, What is the order of horizontal FD BAR ?
    CLIMB AT V2 + 10 with both engines running
    CLIMB AT V2 with both engines running
A

CLIMB AT V2 + 10 with both engines running

55
Q
  1. Having a triple click means that :
    ILS CAPABILITY DOWNGRAD (CAT2 / CAT3 lost)
    Modes reversions or GPS PRIMARY LOST message with NON PRECISION APPR
    expected
    All answers are correct
A

All answers are correct

56
Q
  1. In approach, “LAND” illuminates green on FMA when radio altitude is :
    700 ft
    400 ft
    1000 ft
A

400 ft

57
Q
  1. During an ILS approach the NAV MODE will be deactivated at :
    GLIDE SLOPE capture
    LOCALIZER capture
    Both answers are correct
A

LOCALIZER capture

58
Q
  1. If YELLOW SYSTEM is lost, the SLATS are :
    Normal
    Slow
    Lost
A

Normal

59
Q
  1. With a single HYDRAULIC SYSTEM FAILURE the flight control law is :
    Normal
    Alternate
    Direct
A

Normal

60
Q
  1. If the GREEN SYSTEM is lost, FLAP operation is :
    Slow
    Normal
    Lost
A

Slow

QT A320 (21 decks)

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