ATA22 - Autoflight Flashcards by Thibaut Ricard

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

2 IRS’s failure or ADR’s failure

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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

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

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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 RUDDER TRIM

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

AILERONS, RUDDER, SPOILERS

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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

ALT in cyan indicates that ALT MODE is armed

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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

Landing capability downgrading warning

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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

Press again the EXPD P/B to cancel this mode

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

A/C angle of attack

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The BARO correction or reference selected is sent at each ADIRU via :
The FCU
The RMPS
The DMCS

The FCU

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What are the basic MODES of the AP/FD :
V/S and HDG
ALT and NAV
SPD and HDG

V/S and HDG

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The AFS computers are :
FMGC and ELAC
FMGC and SEC
FMGC and FAC

FMGC and FAC

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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

AUTOPILOT disengagement

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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

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

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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

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

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The FAC compute RUDDER TRAVEL limit :
Only when AP is engaged
Only at LOW SPEED
At any time

At any time

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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

When A/THR P/B is pressed

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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

FMGC 1 only is available (NAV function only)

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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

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

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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

AUTOPILOT, FLIGHT DIRECTOR, A/THR

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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

FMGC’s operate according to MASTER/SLAVE principle

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

Both answers are correct

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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

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

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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

Is locked at the current THRUST

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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

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

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

479. 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

Activate "IMM EXIT" prompt or do a Direct To xx

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

Selection of FG FUNCTIONS MODES

481. 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

By the ALTITUDE manually selected on the FCU

482. 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

Automatically by using the radio position

483. 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

Depends on the AP VERTICAL MODE

484. 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/THR automatically arms but is not active

485. 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

After APPR P/B switch is pressed and illuminates

``` 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 ```

The 'BRT' knob is dimmed

487. 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

FMGC 1 controls both engines

488. 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

ALPHA FLOOR function operates

489. 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

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

490. RUDDER TRAVEL LIMITATION is a function of : FAC only FAC in normal and ELAC in alternate ELAC only

FAC only

491. Can you display FD BARS and FPV at the same time, for CROSS-CHECKING on different PFD'S : Yes No

``` 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/C STATUS PAGE

493. 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

On ground, at computer power up

494. 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

Dashes and the light is illuminated

495. 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'

When the aural warning announces 'RETARD'

496. 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

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

``` 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 ```

It can be reset manually

498. 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

FM PART of the FMGC

499. 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

At system power up

500. 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

Via FMGC 1 then FMGC 2

501. 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

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

``` 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 ```

The FAC, via the FMGC

503. 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

Flight management and flight guidance

504. 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

Disengages by setting a new FCU altitude

505. 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

Both answers are correct

506. 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

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

507. 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

CLIMB AT V2 + 10 with both engines running

508. 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

All answers are correct

509. In approach, "LAND" illuminates green on FMA when radio altitude is : 700 ft 400 ft 1000 ft

400 ft

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

LOCALIZER capture

511. If YELLOW SYSTEM is lost, the SLATS are : Normal Slow Lost

Normal

512. With a single HYDRAULIC SYSTEM FAILURE the flight control law is : Normal Alternate Direct

Normal

513. If the GREEN SYSTEM is lost, FLAP operation is : Slow Normal Lost

Slow

ATA22 - Autoflight Flashcards

(60 cards)