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
2
Q
- 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
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
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
5
Q
- 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
6
Q
- 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
7
Q
- 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
8
Q
- 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
9
Q
- The BARO correction or reference selected is sent at each ADIRU via :
The FCU
The RMPS
The DMCS
A
The FCU
10
Q
- What are the basic MODES of the AP/FD :
V/S and HDG
ALT and NAV
SPD and HDG
A
V/S and HDG
11
Q
- The AFS computers are :
FMGC and ELAC
FMGC and SEC
FMGC and FAC
A
FMGC and FAC
12
Q
- 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
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
14
Q
- 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
15
Q
- The FAC compute RUDDER TRAVEL limit :
Only when AP is engaged
Only at LOW SPEED
At any time
A
At any time
16
Q
- 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
17
Q
- 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)
18
Q
- 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
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
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
21
Q
- 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
22
Q
- 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
23
Q
- 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
24
Q
- 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
25
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
26
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
27
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
28
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
29
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
30
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
31
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
32
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
33
```
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
34
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
35
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
36
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
37
490. RUDDER TRAVEL LIMITATION is a function of :
FAC only
FAC in normal and ELAC in alternate
ELAC only
FAC only
38
491. Can you display FD BARS and FPV at the same time, for CROSS-CHECKING on
different PFD'S :
Yes
No
No
39
```
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
40
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
41
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
42
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'
43
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
44
```
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
45
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
46
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
47
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
48
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
49
```
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
50
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
51
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
52
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
53
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
54
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
55
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
56
509. In approach, "LAND" illuminates green on FMA when radio altitude is :
700 ft
400 ft
1000 ft
400 ft
57
510. During an ILS approach the NAV MODE will be deactivated at :
GLIDE SLOPE capture
LOCALIZER capture
Both answers are correct
LOCALIZER capture
58
511. If YELLOW SYSTEM is lost, the SLATS are :
Normal
Slow
Lost
Normal
59
512. With a single HYDRAULIC SYSTEM FAILURE the flight control law is :
Normal
Alternate
Direct
Normal
60
513. If the GREEN SYSTEM is lost, FLAP operation is :
Slow
Normal
Lost
Slow
