ATA 22: Autoflight Flashcards

Question 1

Q

To change the maximum descent cabin rate to 400 feet per minute you would….

(a) Go to the DES page and enter -400 in the DES CABIN RATE field
(b) Select it manually on the overhead panel
(c) Enter 400 in the DES CABIN RATE field on the CRZ page

Answer

A

(c) Enter 400 in the DES CABIN RATE field on the CRZ page

Question 2

Q

With FMGEC 1 invalid and the FM source selector on BOTH ON 2, which MCDU would you use to enter data into the FMGEC 2?

(a) Either MCDU 1 or MCDU 2
(b) MCDU 2 on the First Officer
(c) MCDU 1 on the Captain’s side

Answer

A

(a) Either MCDU 1 or MCDU 2

Question 3

Q

The FAIL amber annunciator light illuminates on the MCDU. This means:
(a) The corresponding FMGEC has failed
(b) The corresponding MCDU has failed
(c) Both the MCDU and the FMGEC have failed

Answer

A

(b) The corresponding MCDU has failed

Question 4

Q

What happens if the V/S or FPA selection knob on the FCU is pushed?
(a) V/S window displays dashes and the FMGEC guides the aircraft to climb or descend based on the cost index
(b) This results in an immediate level off and the V/S window displays 0
(c) The V/S window displays the current V/S for 15 seconds and then the value disappears

Answer

A

(b) This results in an immediate level off and the V/S window displays 0

Question 5

Q

On approach, ‘LAND’ is displayed on FMA’s when radio altitude is below:

(a) 700ft
(b) 400ft
(c) 200 ft

Answer

A

(b) 400ft

Question 6

Q

The NAV mode engages:

(a) By pulling the HDG/TRK selector knob
(b) Automatically at 30 feet if armed on the ground
(c) Automatically when GA is selected

Answer

A

(b) Automatically at 30 feet if armed on the ground

Question 7

Q

The aircraft is in the heading mode. NAV mode re-engages:

(a) By performing a lateral revision at the next waypoint
(b) By selecting an intercept heading and pull the heading knob
(c) When the pilot orders DIR TO

Answer

A

(c) When the pilot orders DIR TO

Question 8

Q

The aircraft is descending in V/S mode. What will happen if the V/S is excessive and the aircraft speed accelerates to Vmo (slats not extended)?

(a) Maintains Vmax, V/S pulses and is boxed amber.
(b) An automatic reversion to OP DES will occur and the airspeed reduces to the previous selected speed
(c) V/S is automatically reduced to 1200 ft/mm

Answer

A

(a) Maintains Vmax, V/S pulses and is boxed amber.

Question 9

Q

The aircraft is descending in the managed DES mode. The aircraft is given radar vectors and the pilot selects the required heading and pulls the heading knob. What does this result in?

(a) The heading mode engages. The DES mode continues to be engaged as nothing is changed to alter the vertical mode
(b) There is no change in the modes. If a heading is to be selected, the DES mode needs to be disengaged first
(c) The heading mode engages. But the DES mode reverts to V/S mode as the managed lateral guidance is lost with the heading selection

Answer

A

(c) The heading mode engages. But the DES mode reverts to V/S mode as the managed lateral guidance is lost with the heading selection

Question 10

Q

A heading has been preset for go around. Mark the correct statement

(a) This is activated automatically at the engagement of the GA mode
(b) The value disappears after 45 seconds as the heading can be preset only for the take off
(c) This can be activated by pulling the heading knob when cleared by ATC

Answer

A

(c) This can be activated by pulling the heading knob when cleared by ATC

Question 11

Q

A/THR is armed on ground by:

(a) Depressing the FCU A/THR Pb once the FLEX temperature is entered and engines started
(b) Depressing the instinctive push button on the thrust levers after setting the levers to FLX or TO/GA detent
(c) At takeoff, setting at least one thrust lever to FLX or TO/GA detent.

Answer

A

(c) At takeoff, setting at least one thrust lever to FLX or TO/GA detent

Question 12

Q

When the thrust levers are in the TOGA position, autothrust is:

(a) Armed and is active
(b) Armed but not active
(c) Not armed but is active

Answer

A

(b) Armed but not active

Question 13

Q

When the A/THR is in the SPEED mode how is the speed target set?
(a) It is set automatically by the FMGEC in managed guidance mode
(b) It is selected on the FCU by the pilot in selected guidance mode
(c) Both A and B are correct

Answer

A

(c) Both A and B are correct

Question 14

Q

The message TOGA LK flashes on the FMA. What does this mean?
(a) The aircraft has exited the alpha floor conditions and the TOGA power is frozen
(b) The thrust levers are still in the TO/GA detent but the aircraft is no longer in the take off mode
(c) The levers have been moved inadvertently to the TO/GA detent while the A/THR is active

Answer

A

(a) The aircraft has exited the alpha floor conditions and the TOGA power is frozen

Question 15

Q

AUTO_01 Describe the methods of autopilot engagement and disengagement.

An autopilot will not engage unless all of its required systems are operating within limits.

These systems include:

The associated ____________
Certain flight control ________
At least two ____________
Flight control computers (at least one _________ and one _________)

Additionally, the aircraft must be within the _________ and _________ limits, and between _______ and ______.

VOL. II, 22.2.6.2

Answer

A

AUTO_01 Describe the methods of autopilot engagement and disengagement.

An autopilot will not engage unless all of its required systems are operating within limits.

These systems include:

The associated FMGEC
Certain flight control surfaces
At least two ADIRUs
Flight control computers (at least one PRIM and one SEC)

Additionally, the aircraft must be within the bank and pitch limits, and between VLS and VMAX.

VOL. II, 22.2.6.2

Question 16

Q

AUTO_01 Describe the methods of autopilot engagement and disengagement.

The autopilots may operate with the flight controls in ________ law, depending on the specific failure.
The autopilots are inoperative when the flight controls are in _________ law.

VOL. II, 22.2.6.2

Answer

A

AUTO_01 Describe the methods of autopilot engagement and disengagement.

The autopilots may operate with the flight controls in alternate law, depending on the specific failure.
The autopilots are inoperative when the flight controls are in direct law.

VOL. II, 22.2.6.2

Question 17

Q

AUTO_01 Describe the methods of autopilot engagement and disengagement.

The autopilot(s) are engaged by pushing the AP 1 or AP 2 pb on the FCU.

When an autopilot is engaged:

The sidesticks are held _________
The AP pb light illuminates ________
FMA Column 5 indicates AP engagement status in white as ________, _______, or _______ if both autopilots are engaged.

VOL. II, 22.2.6.3

Answer

A

AUTO_01 Describe the methods of autopilot engagement and disengagement.

The autopilot(s) are engaged by pushing the AP 1 or AP 2 pb on the FCU.

When an autopilot is engaged:

The sidesticks are held centered
The AP pb light illuminates green
FMA Column 5 indicates AP engagement status in white as AP 1, AP 2, or AP 1+ 2 if both autopilots are engaged.

VOL. II, 22.2.6.3

Question 18

Q

AUTO_01 Describe the methods of autopilot engagement and disengagement.

Usually only one autopilot may be _________ at a time.

If one AP is engaged and the other AP pb is pressed, the second will _________ and the first AP will _________ (no _________ or messages are displayed).

Engagement of two autopilots is only possible during an _________ approach after the _________ pb has been pushed.

The autopilot may be disengaged _________ or _________ .

VOL. II, 22.2.6.2

Answer

A

AUTO_01 Describe the methods of autopilot engagement and disengagement.

Usually only one autopilot may be engaged at a time.

If one AP is engaged and the other AP pb is pressed, the second will engage and the first AP will disengage (no warnings or messages are displayed).

Engagement of two autopilots is only possible during an ILS approach after the APPR pb has been pushed.

The autopilot may be disengaged manually or automatically.

VOL. II, 22.2.6.2

Question 19

Q

AUTO_01 Describe the methods of autopilot engagement and disengagement.

Manual Disengagement
The preferred method for disengaging the autopilot is to push the autopilot __________/__________ pb on a __________.

This results in:

__________ __________ light,
momentary red _____ _____ on the right side of the ECAM __________ memo display,
and a __________ aural warning (cavalry charge).

Note: A __________ push of the disconnect pb immediately stops the __________warning, extinguishes the ________ ________, and clears the __________.

VOL. II, 22.2.6.5

Answer

A

AUTO_01 Describe the methods of autopilot engagement and disengagement.

Manual Disengagement
The preferred method for disengaging the autopilot is to push the autopilot disconnect/takeover pb on a sidestick.

This results in:

MASTER WARN light,
momentary red AP OFF on the right side of the ECAM E/WD memo display,
and a momentary aural warning (cavalry charge).

Note: A second push of the disconnect pb immediately stops the aural warning, extinguishes the MASTER WARN, and clears the ECAM.

VOL. II, 22.2.6.5

Question 20

Q

AUTO_01 Describe the methods of autopilot engagement and disengagement.

As an alternate means, the autopilot can also be disengaged by either:

Significantly moving a _________** or a **________\_ pedal (as may be required for an evasive maneuver)
Pushing the illuminated ______\_ AP pb

Either of these actions is sensed as:

an AP ________\_ and results in a master warning,
a red ________\_ failure message,
a _________** **_________** **________\_ (CRC),
and ECAM ________\_ message.

VOL. II, 22.2.6.5

Answer

A

AUTO_01 Describe the methods of autopilot engagement and disengagement.

As an alternate means, the autopilot can also be disengaged by either:

Significantly moving a sidestick or a rudder pedal (as may be required for an evasive maneuver)
Pushing the illuminated FCU AP pb

Either of these actions is sensed as:

an AP fault and results in a master warning,
a red E/WD failure message,
a continuous repetitive chime (CRC),
and ECAM status message.

VOL. II, 22.2.6.5

Question 21

Q

AUTO_01 Describe the methods of autopilot engagement and disengagement.

Automatic Disengagement
The autopilot disengages automatically if:

APPR mode was engaged on a ____ ___ approach and the aircraft descends to ____ ft. below the ______ or at ___ft. RA if no ______ was entered.
Both thrust levers are set above the ______/______detent with the aircraft on the ground.
- o This prevents a ______ after touchdown with the autopilot engaged.
Any of the previously listed engagement requirements are ______

VOL. II, 22.2.6.5

Answer

A

AUTO_01 Describe the methods of autopilot engagement and disengagement.

Automatic Disengagement
The autopilot disengages automatically if:

APPR mode was engaged on a non-ILS approach and the aircraft descends to 50 ft. below the MDA, or at 400 ft. RA if no MDA was entered.
Both thrust levers are set above the FLX/MCT detent with the aircraft on the ground.
- o This prevents a go around after touchdown with the autopilot engaged.
Any of the previously listed engagement requirements are lost

VOL. II, 22.2.6.5

Question 22

Q

AUTO_01 Describe the methods of autopilot engagement and disengagement.

Automatic Disengagement
In normal law with all protections available, the autopilot disengages automatically if:

o _____ _____ protection becomes active
o _____ protection becomes active (speed at or below alpha _____)
o Pitch or bank limits are _____

VOL. II, 22.2.6.5

Answer

A

AUTO_01 Describe the methods of autopilot engagement and disengagement.

Automatic Disengagement
In normal law with all protections available, the autopilot disengages automatically if:

o High speed protection becomes active
o Alpha protection becomes active (speed at or below alpha prot)
o Pitch or bank limits are exceeded

VOL. II, 22.2.6.5

Question 23

Q

AUTO_01 Describe the methods of autopilot engagement and disengagement.

Automatic Disengagement
The autopilot disengages automatically if:

If both APs are used for an ILS approach, ________ disengages when ________ or ______ ________ disengages.
- No ________or ________ messages are displayed in this case.
Rudder pedal ________while on the ground.

Automatic disengagement results in:

a ______ ______,
a red________ failure message,
a ______ ______ _____ (CRC),
and an ECAM________ message.

VOL. II, 22.2.6.5

Answer

A

AUTO_01 Describe the methods of autopilot engagement and disengagement.

Automatic Disengagement
The autopilot disengages automatically if:

If both APs are used for an ILS approach, AP 2 disengages when SRS or GA TRK disengages.
- No warnings or ECAM messages are displayed in this case.
Rudder pedal displacement while on the ground.

Automatic disengagement results in:

a master warning,
a red E/WD failure message,
a continuous repetitive chime (CRC),
and an ECAM status message.

VOL. II, 22.2.6.5

Question 24

Q

AUTO_02 Discuss the thrust lever “active range”.

The thrust levers must be in the _________ range and the autothrust system active for autothrust to control thrust.
When active, the _________ _________ pb is illuminated and A/THR is displayed in _________ in FMA column ______._

VOL. II, 22.2.7.8

Answer

A

AUTO_02 Discuss the thrust lever “active range”.

The thrust levers must be in the active range and the autothrust system active for autothrust to control thrust.
When active, the FCU A/THR pb is illuminated and A/THR is displayed in white in FMA column 5.

VOL. II, 22.2.7.8

Question 25

Q

AUTO_02 Discuss the thrust lever “active range”.

Autothrust can only be active when the thrust levers are within the active range.

With two engines operating, the active range is from just above__\_ up to and including the _____ detent.
With one engine operating, the active range is from just above____ up to and including the ______ detent.

VOL. II, 22.2.7.8

Answer

A

AUTO_02 Discuss the thrust lever “active range”.

Autothrust can only be active when the thrust levers are within the active range.

With two engines operating, the active range is from just above idle up to and including the CL detent.
With one engine operating, the active range is from just above idle up to and including the MCT detent.

VOL. II, 22.2.7.8

Question 26

Q

AUTO_02 Discuss the thrust lever “active range”.

When the autothrust system is active the thrust lever __________ defines the thrust __________.
The thrust limit is the __________ permissible thrust setting the autothrust system may use.
After takeoff and initial acceleration the thrust levers are normally placed in the ________ detent.
- This allows the autothrust to use any setting up to__________ thrust to meet autoflight system demands.
- If the thrust levers were retarded to a position below the ________ detent, autothrust would be __________ by that thrust.

VOL. II, 22.2.7.8

Answer

A

AUTO_02 Discuss the thrust lever “active range”.

When the autothrust system is active the thrust lever position defines the thrust limit.
The thrust limit is the maximum permissible thrust setting the autothrust system may use.
After takeoff and initial acceleration the thrust levers are normally placed in the CL detent.
- This allows the autothrust to use any setting up to climb thrust to meet autoflight system demands.
- If the thrust levers were retarded to a position below the CL detent, autothrust would be limited by that thrust.

VOL. II, 22.2.7.8

Question 27

Q

AUTO_03 Describe the different autothrust status.

Autothrust can be either

____________,
___________,
or _________.

VOL. II, 22.2.7.2

Answer

A

AUTO_03 Describe the different autothrust status.

Autothrust can be either

disconnected,
armed,
or active.

VOL. II, 22.2.7.2

Question 28

Q

AUTO_03 Describe the different autothrust status.

When the autothrust is disconnected:

it is _______ and _______ operational.
it is neither _______ nor _______.
Thrust is controlled _______ using the thrust levers.

VOL. II, 22.2.7.2

Answer

A

AUTO_03 Describe the different autothrust status.

When the autothrust is disconnected:

it is off and not operational.
it is neither armed nor active.
Thrust is controlled manually using the thrust levers.

VOL. II, 22.2.7.2

Question 29

Q

AUTO_03 Describe the different autothrust status.

When the autothrust is armed:
- it is ready to become _________.
- It becomes _________as soon as the thrust levers are moved into the _________ range.
- While autothrust is armed, thrust is set _________ using the thrust levers.

VOL. II, 22.2.7.2

Answer

A

AUTO_03 Describe the different autothrust status.

When the autothrust is armed:
- it is ready to become active.
- It becomes active as soon as the thrust levers are moved into the active range.
- While autothrust is armed, thrust is set manually using the thrust levers.

VOL. II, 22.2.7.2

Question 30

Q

AUTO_03 Describe the different autothrust status.

When the autothrust is active it is:

____________ the thrust.
The thrust levers are in the __________ range
autothrust has the authority to control thrust between __________ and the __________ thrust lever setting.

VOL. II, 22.2.7.2

Answer

A

AUTO_03 Describe the different autothrust status.

When the autothrust is active it is:

controlling the thrust.
The thrust levers are in the active range
autothrust has the authority to control thrust between idle and the current thrust lever setting.

VOL. II, 22.2.7.2

Question 31

Q

AUTO_03 Describe the different autothrust status.

Disarming:

Autothrust status can be changed from armed to disconnected by either:

Pushing one of the ________ ________ pbs on the thrust levers.
Pushing the illuminated __________ pb on the FCU.

VOL. II, 22.2.7.2

Answer

A

AUTO_03 Describe the different autothrust status.

Disarming:

Autothrust status can be changed from armed to disconnected by either:

Pushing one of the instinctive disconnect pbs on the thrust levers.
Pushing the illuminated A/THR pb on the FCU.

VOL. II, 22.2.7.2

Question 32

Q

AUTO_04 Understand the difference between fixed and variable autothrust modes.

thrust is FIXED when:

flight guidance is using ________ to control airspeed (Airspeed is being controlled by _________.)

Examples of Fixed thrust setting:

__________
__________
__________

VOL. II, 22.2.7.4

Answer

A

AUTO_04 Understand the difference between fixed and variable autothrust modes.

thrust is FIXED when:

flight guidance is using pitch to control airspeed, (Airspeed is being controlled by pitch.)

Examples of Fixed thrust setting:

THR CLB
THR IDLE
THR DES

VOL. II, 22.2.7.4

Question 33

Q

A

AUTO_04 Understand the difference between fixed and variable autothrust modes.

Thrust is variable when:

Thrust controls _________. (_________ or _________)
Flight guidance is using _________ to control the flight path
- (e.g., altitude hold or glide slope),
When flight guidance is off, thrust is _________ to control airspeed.
- SPEED / MACH indicates a variable __________ setting
- ________\_ is being controlled by thrust

VOL. II, 22.2.7.4

Answer

A

AUTO_04 Understand the difference between fixed and variable autothrust modes.

Thrust is variable when:

Thrust controls airspeed. (SPEED or MACH)
Flight guidance is using pitch to control the flight path
- (e.g., altitude hold or glide slope),
When flight guidance is off, thrust is variable to control airspeed.
- SPEED / MACH indicates a variable thurst setting
- Aispeed is being controlled by thrust

VOL. II, 22.2.7.4

Question 34

Q

AUTO_05 Discuss the Alpha Floor autothrust protection.

Alpha floor is available in _________ law from ____ ___ until ___ ft. ___ on approach.
It is not available if the autothrust is ______ or has been ___ by holding either instinctive disconnect pb for ___ seconds.

Alpha floor is a ______ autothrust function activated by the ___s to aid in the recovery from ___ or potentially ___ angle of attack (___) conditions.

Alpha floor’s activation point depends on a ___ of parameters, and is ___ ______ on the airspeed display.

PRIMs {three flight control primary computers}

VOL. II, 22.2.7.11

Answer

A

AUTO_05 Discuss the Alpha Floor autothrust protection.

Alpha floor is available in normal law from lift off until 100 ft. RA on approach.
It is not available if the autothrust is inoperative or has been disabled by holding either instinctive disconnect pb for 15 seconds.

Alpha floor is a predictive autothrust function activated by the PRIMs to aid in the recovery from high or potentially high angle of attack (alpha) conditions.

Alpha floor’s activation point depends on a variety of parameters, and is not indicated on the airspeed display.

PRIMs {three flight control primary computers}

VOL. II, 22.2.7.11

Question 35

Q

AUTO_05 Discuss the Alpha Floor autothrust protection.

Alpha floor is inhibited:

In case of ______ ______ with either flaps ______ or ______ takeoff
Below ____ ft. ___ on landing
Above [.____ M]

VOL. II, 22.2.7.11

Answer

A

AUTO_05 Discuss the Alpha Floor autothrust protection.

Alpha floor is inhibited:

In case of engine failure with either flaps extended or derated takeoff
Below 100 ft. RA on landing
Above [.53 M]

VOL. II, 22.2.7.11

Question 36

Q

AUTO_05 Discuss the Alpha Floor autothrust protection.

When alpha floor activates, the autothrust commands _______ thrust, regardless of thrust lever position.

The following indications are provided:

A green __ _____, _____ in amber, is shown in column __ of the FMA
and __ _____ in amber on the ______ for as long as the alpha floor triggering conditions are present.

VOL. II, 22.2.7.11

Answer

A

AUTO_05 Discuss the Alpha Floor autothrust protection.

When alpha floor activates, the autothrust commands TOGA thrust, regardless of thrust lever position.

The following indications are provided:

A green A FLOOR, boxed in amber, is shown in column 1 of the FMA
and A FLOOR in amber on the E/WD for as long as the alpha floor triggering conditions are present.

VOL. II, 22.2.7.11

Question 37

Q

AUTO_06 Discuss the FMA indications on the PFD.

The FMA is arranged in five columns, left to right displaying:

___________ operation
___________flight guidance modes
___________flight guidance modes
___________ capabilities and _______/________
___________, ___________, and___________engagement status

VOL. II, 22.2.3.9

Answer

A

AUTO_06 Discuss the FMA indications on the PFD.

The FMA is arranged in five columns, left to right displaying:

Autothrust operation
Vertical flight guidance modes
Lateral flight guidance modes
Approach capabilities and MDA/DH
Autopilot, Flight Director, and Autothrust engagement status

VOL. II, 22.2.3.9

Question 38

Q

AUTO_06 Discuss the FMA indications on the PFD.

The active modes currently in use by the autopilot, flight directors, and autothrust systems are depicted on the _____ line of columns __, ___, and __.
Armed modes appear on the ______ line,
and flight _________, flight _________, and _______ switching messages on the third line.

VOL. II, 22.2.3.9

Answer

A

AUTO_06 Discuss the FMA indications on the PFD.

The active modes currently in use by the autopilot, flight directors, and autothrust systems are depicted on the first line of columns 1, 2, and 3.
Armed modes appear on the second line,
and flight control, flight management, and EFIS switching messages on the third line.

VOL. II, 22.2.3.9

Question 39

Q

AUTO_06 Discuss the FMA indications on the PFD.

The FMA uses color to further define the meaning of an indications in columns one through three:

Green - ________ modes
Blue - ________ modes
Magenta - ________ ________ constraints

VOL. II, 22.2.3.9

Answer

A

AUTO_06 Discuss the FMA indications on the PFD.

The FMA uses color to further define the meaning of an indications in columns one through three:

Green - engaged modes
Blue - armed modes
Magenta - armed altitude constraints

VOL. II, 22.2.3.9

Question 40

Q

AUTO_06 Discuss the FMA indications on the PFD.

Each new or changed annunciation is boxed in _______ or _______ for ______ seconds as an attention getter.

Messages may appear in (color)

_______,
_______,
or _______ to indicate _______, _______, or _______ messages.

White Messages indicate:

Aircraft _______,
engaged _______ systems,
flight director _______

A/THR appears in white when autothrust is _______ and in blue when _______.

VOL. II, 22.2.3.9

Answer

A

AUTO_06 Discuss the FMA indications on the PFD.

Each new or changed annunciation is boxed in white or amber for 10 seconds as an attention getter.

Messages may appear in (color)

red,
amber,
or white to indicate warning, caution, or advisory messages.

White Messages indicate:

Aircraft capabilities,
engaged autoflight systems,
flight director status

A/THR appears in white when autothrust is active and in blue when armed.

VOL. II, 22.2.3.9

Question 41

Q

AUTO_07

Understand the control functions and indications on the FCU panel.

1, SPD/MACH Pb

Switches the value in the Speed/Mach window (if displayed) between _______ and _______.

2. Speed/ Mach Window

Displays the selected _______ or _______
When managed speed is active, the window displays _______ unless the Speed/Mach knob has been recently adjusted.

VOL. II, 22.3.1

Answer

A

AUTO_07

Understand the control functions and indications on the FCU panel.

1, SPD/MACH Pb

Switches the value in the Speed/Mach window (if displayed) between IAS and Mach.

2. Speed/ Mach Window

Displays the selected Speed or Mach.
When managed speed is active, the window displays dashes unless the Speed/Mach knob has been recently adjusted.

VOL. II, 22.3.1

Question 42

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

3. Managed Speed Dot

The _______ appears when managed speed is active.

4. Speed/Mach Knob

Turning the knob adjusts the _______ or _______ (as selected with the speed/Mach pb) displayed in the speed/Mach window.

If managed speed remains active the speed/Mach window will revert to _______ within [_____] seconds.

Pulled - Activates _______ speed.
Pushed - Activates _______ speed.

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

3. Managed Speed Dot

The dot appears when managed speed is active.

4. Speed/Mach Knob

Turning the knob adjusts the Speed or Mach (as selected with the speed/Mach pb) displayed in the speed/Mach window.

If managed speed remains active the speed/Mach window will revert to dashes within [45] seconds.

Pulled - Activates Selected speed.
Pushed - Activates Managed speed.

VOL. II, 22.3.1

Question 43

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

5. Heading/Track Window

Displays the ________ heading or track.
When managed lateral guidance is active the window displays ________ unless the _______/_______ knob has been recently adjusted.

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

5. Heading/Track Window

Displays the selected heading or track.
When managed lateral guidance is active the window displays dashes unless the HDG/TRK knob has been recently adjusted.

VOL. II, 22.3.1

Question 44

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

6. Managed Lateral Guidance Dot

The ________ appears when managed lateral guidance is ________ (including ________).

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

6. Managed Lateral Guidance Dot

The dot appears when managed lateral guidance is active (including LOC).

VOL. II, 22.3.1

Question 45

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

7. HDG/TRK Knob

Turning the knob adjusts the ________ or ________ displayed in the _______/_______ window.
If managed guidance remains active the window will revert to ________ within ______ seconds, except during_______f_ and ________.

Pulled - Activates _____\_ heading or ______ mode.

The aircraft will then turn to the _____\_ heading or ______ in the ________ direction.
If the knob is ________ and then ________, the aircraft will turn to ________ the selection up to 359° from the current heading or track.

Pushed - Arms managed______ guidance.

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

7. HDG/TRK Knob

Turning the knob adjusts the heading or track displayed in the HDG/TRK window.
If managed guidance remains active the window will revert to dashes within 45 seconds, except during takeoff and approach.

Pulled - Activates Selected heading or Track mode.

The aircraft will then turn to the Selected heading or Track in the shortest direction.
If the knob is pulled and then turned, the aircraft will turn to follow the selection up to 359° from the current heading or track.

Pushed - Arms managed lateral guidance.

VOL. II, 22.3.1

Question 46

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

8. LOC Pb

Pushing the pb ________ (or ________), or ________ the LOC mode.
Illuminates ________ when the LOC mode is ________ or ________

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

8. LOC Pb

Pushing the pb arms (or engages), or disengages the LOC mode.
Illuminates green when the LOC mode is armed or active.

VOL. II, 22.3.1

Question 47

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

9. HDG - V/S / TRK FPA Mode

HDG V/S - Heading / vertical speed mode is active for selection of______ and ________ modes.
HDG/TRK knob selects ________.
The V/S - FPA knob selects ________ speeds.

TRK FPA -

Track / flight path ________ mode is active for selection of ________ and ________ modes.
Movement of the HDG/TRK knob selects ________.
The V/S - FPA knob selects flight ______ ______.

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

9. HDG - V/S / TRK FPA Mode

HDG V/S - Heading / vertical speed mode is active for selection of lateral and vertical modes.
HDG/TRK knob selects headings.
The V/S - FPA knob selects vertical speeds.

TRK FPA -

Track / flight path angle mode is active for selection of lateral and vertical modes.
Movement of the HDG/TRK knob selects tracks.
The V/S - FPA knob selects flight path angles.

VOL. II, 22.3.1

Question 48

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

10. HDG-V/S/TRK-FPAPb
Pressing the pb alternately switches:

The flight director display between the HDG / V/S mode (______ ______) and the TRK / FPA mode (____ ____ _____).
The heading / track window between ________ and ________ values (if displayed)
The V/S - FPA window between ______ ______ and______ ______ ______ (if displayed)

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

10. HDG-V/S/TRK-FPAPb
Pressing the pb alternately switches:

The flight director display between the HDG / V/S mode (cross hairs) and the TRK / FPA mode (flight path vector).
The heading / track window between heading and track values (if displayed)
The V/S - FPA window between vertical speed and flight path angle (if displayed)

VOL. II, 22.3.1

Question 49

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

11. AP (1/2) Pbs
Pressing the pb turns on the respective ________.

For ILS approaches, both autopilots may be ________ or ________ simultaneously after the ________ pb has been pushed.

Otherwise pressing one pb with the opposite autopilot engaged, ________ the selected autopilot and ________ the first autopilot.

If illuminated, pushing the pb ________ the autopilot.

Illuminates ________ when the respective autopilot is engaged.

Note: The autopilots will not engage on the ________ with ______ ______

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

11. AP (1/2) Pbs
Pressing the pb turns on the respective autopilot.

For ILS approaches, both autopilots may be armed or engaged simultaneously after the APPR pb has been pushed.

Otherwise pressing one pb with the opposite autopilot engaged, engages the selected autopilot and disengages the first autopilot.

If illuminated, pushing the pb disengages the autopilot.

Illuminates green when the respective autopilot is engaged.

Note: The autopilots will not engage on the ground with engines running

VOL. II, 22.3.1

Question 50

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

12. A/THR Pb

Pressing the pb: ________, ________, or ________ the autothrust.
Illuminates green when A/THR is ________ or _______._

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

12. A/THR Pb

Pressing the pb: arms, activates, or disengages the autothrust.
Illuminates green when A/THR is armed or active.

VOL. II, 22.3.1

Question 51

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

13. Altitude Window

Displays the selected altitude at all times.

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

13. Altitude Window

Displays the selected altitude at all times.

VOL. II, 22.3.1

Question 52

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

14. ALT Knob

100 / 1000 selector (outer knob) - Determines selection ________of inner knob.
Inner knob - Selects the value in the altitude window at ________ or ________feet per click as selected with the ________ knob.
Pulled - Selects an ________ climb or ________ descent toward the selected altitude.
Pushed - Engages ________ climb or ________ descent toward the selected altitude if engagement criteria are met (e.g., ______ ______is engaged).

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

14. ALT Knob

100 / 1000 selector (outer knob) - Determines selection increment of inner knob.
Inner knob - Selects the value in the altitude window at 100 or 1000 feet per click as selected with the outer knob.
Pulled - Selects an OPEN climb or OPEN descent toward the selected altitude.
Pushed - Engages MANAGED climb or MANAGED descent toward the selected altitude if engagement criteria are met (e.g., MANAGED lateral is engaged).

VOL. II, 22.3.1

Question 53

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

15. ALT Pb

Pushed - Commands an ______ ______ ____.
- ______ ______ mode will engage at the altitude the aircraft levels off at (not the altitude the pb was ______ ___).
- Illuminates green when altitude hold is ________ (________, ________ ______, or ______ ______).

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

15. ALT Pb

Pushed - Commands an immediate level off.
- Altitude Hold mode will engage at the altitude the aircraft levels off at (not the altitude the pb was pressed at).
- Illuminates green when altitude hold is engaged (ALT, ALT CRZ, or ALT CST).

VOL. II, 22.3.1

Question 54

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

Managed Level Change Dot

The dot appears when ______ ______ guidance is active.

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

Managed Level Change Dot

The dot appears when managed vertical guidance is active.

VOL. II, 22.3.1

Question 55

Q

AUTO_07 Understand the control functions and indications on the FCU panel. VOL. II, 22.3.1

17. METRIC ALT Pb
Alternately displays or removes the ________ altitude (or ________ altitude if one exists), and the current altitude in ________ from the PFD altitude display.

The FCU altitude remains displayed in ________.

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel. VOL. II, 22.3.1

17. METRIC ALT Pb
Alternately displays or removes the selected altitude (or constraint altitude if one exists), and the current altitude in meters from the PFD altitude display.

The FCU altitude remains displayed in feet.

VOL. II, 22.3.1

Question 56

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

18. V/S FPA Window
Displays the ________ vertical speed or flight path angle.

If managed vertical is active and a vertical speed or FPA is selected (but the knob is not pulled) the window reverts to dashes after [______] seconds.

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

18. V/S FPA Window
Displays the selected vertical speed or flight path angle.

If managed vertical is active and a vertical speed or FPA is selected (but the knob is not pulled) the window reverts to dashes after [45] seconds.

VOL. II, 22.3.1

Question 57

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

19. V/S - FPA Knob
Selects the ______ ______ or ______ _____ _______ in the V/S - FPA window.

The FCU V/S FPA window may be ________ with a V/S or FPA value for up to [______] seconds before engaging.
The FCU V/S FPA window ________ if V/S (FPA) is not engaged within this time.
________ - Commands an immediate level off.
When level the aircraft remains in V/S - FPA mode with ______ ______ ______ or ______° flight path angle.

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

19. V/S - FPA Knob
Selects the vertical speed or flight path angle in the V/S - FPA window.

The FCU V/S FPA window may be preset with a V/S or FPA value for up to [45] seconds before engaging.
The FCU V/S FPA window clears if V/S (FPA) is not engaged within this time.
Pushed - Commands an immediate level off.
When level the aircraft remains in V/S - FPA mode with 0 vertical speed or 0° flight path angle.

VOL. II, 22.3.1

Question 58

Q

AUTO_07 Understand the control functions and indications on the FCU panel.

20. APPR Pb
________, ________, ________, or ________ the approach mode.
Arms ________ and ________ modes if an ILS type approach (ILS, LDA, SDF, etc.) has been selected by:

Inserting the approach to the destination airport in the ______ ______.
Tuning approach guidance raw data on the ILS line of the ______ ______ page
Tuned an ILS in ______ ______ (through an RMP - radio management panel)

Arms approach-nav ________ mode if a non-precision approach is selected in the active flight plan.

VOL. II, 22.3.1

Answer

A

AUTO_07 Understand the control functions and indications on the FCU panel.

20. APPR Pb
Arms, disarms, engages, or disengages the approach mode.
Arms LOC and G/S modes if an ILS type approach (ILS, LDA, SDF, etc.) has been selected by:

Inserting the approach to the destination airport in the flight plan.
Tuning approach guidance raw data on the ILS line of the RAD NAV page
Tuned an ILS in STBY NAV (through an RMP - radio management panel)

Arms approach-nav FINAL mode if a non-precision approach is selected in the active flight plan.

VOL. II, 22.3.1

Question 59

Q

AUTO_08 Describe how to engage, disengage, and reset the Flight Directors, as well as the FMA indications during flight director usage.

Flight directors are engaged by pushing the FD pb on each pilot’s ________ control panel.
When engaged, the ________ FD pb light illuminates.

Caution: Flight directors should______ be engaged or ________ disengaged.

Display of a FD on only one side (e.g., PM) could result in the PF not satisfying FD guidance commands required to keep the aircraft within ________ limits.

FMA column _____ indicates which flight directors are on and which______ is controlling each one.
A number on each side of the letters FD indicates the controlling ________.
A dash indicates the FD is selected _______._

VOL. II, 22.2.5.2

Answer

A

AUTO_08 Describe how to engage, disengage, and reset the Flight Directors, as well as the FMA indications during flight director usage.

Flight directors are engaged by pushing the FD pb on each pilot’s EFIS control panel.
When engaged, the green FD pb light illuminates.

Caution: Flight directors should both be engaged or both disengaged.

Display of a FD on only one side (e.g., PM) could result in the PF not satisfying FD guidance commands required to keep the aircraft within airspeed limits.

FMA column 5 indicates which flight directors are on and which FMGEC is controlling each one.
A number on each side of the letters FD indicates the controlling FMGEC.
A dash indicates the FD is selected off.

VOL. II, 22.2.5.2

Question 60

Q

AUTO_08 Describe how to engage, disengage, and reset the Flight Directors, as well as the FMA indications during flight director usage.

To reset the flight directors, ________ must be turned off, remain off for a ________ seconds, and reselected on.

VOL. II, 22.2.5.2

Answer

A

AUTO_08 Describe how to engage, disengage, and reset the Flight Directors, as well as the FMA indications during flight director usage.

To reset the flight directors, both must be turned off, remain off for a few seconds, and reselected on.

VOL. II, 22.2.5.2

Question 61

Q

AUTO_08 Describe how to engage, disengage, and reset the Flight Directors, as well as the FMA indications during flight director usage.

The normal flight director indication on the both FMAs is ________.
- This indicates that the captain’s FD is displaying commands from ________,
- and the first officer’s FD is displaying commands from ________.

VOL. II, 22.2.5.2

Answer

A

AUTO_08 Describe how to engage, disengage, and reset the Flight Directors, as well as the FMA indications during flight director usage.

The normal flight director indication on the both FMAs is 1FD2.
- This indicates that the captain’s FD is displaying commands from FMGEC 1,
- and the first officer’s FD is displaying commands from FMGEC 2.

VOL. II, 22.2.5.2

Question 62

Q

AUTO_08 Describe how to engage, disengage, and reset the Flight Directors, as well as the FMA indications during flight director usage.

If one FMGEC fails, the remaining FMGEC provides ______ ________commands.
1FD1 (or 2FD2) indicates that one ________ as failed and the other ________ is providing the FD commands on both ________.

VOL. II, 22.2.5.2

Answer

A

AUTO_08 Describe how to engage, disengage, and reset the Flight Directors, as well as the FMA indications during flight director usage.

If one FMGEC fails, the remaining FMGEC provides both FD commands.
1FD1 (or 2FD2) indicates that one FMGEC as failed and the other FMGEC is providing the FD commands on both PFDs.

VOL. II, 22.2.5.2

Question 63

Q

AUTO_09

Discuss the differences in landing capability shown in FMA Column 4.

After an ILS app. is armed, the ______ ______ is displayed in FMA column 4.
The ______ ______ is based on the current ________ of aircraft systems and functions.

VOL. II 22.2.17.3

Answer

A

AUTO_09

Discuss the differences in landing capability shown in FMA Column 4.

After an ILS app. is armed, the landing capability is displayed in FMA column 4.
The landing capability is based on the current status of aircraft systems and functions.

VOL. II 22.2.17.3

Question 64

Q

AUTO_09 Discuss the differences in landing capability shown in FMA Column 4.

CAT 3 DUAL indicates a fail ________ autoland capability.
In a fail ________ system, a ______ ______ still allows an autoland with the remaining components.

VOL. II 22.2.17.3

Answer

A

AUTO_09 Discuss the differences in landing capability shown in FMA Column 4.

CAT 3 DUAL indicates a fail operational autoland capability.
In a fail operational system, a subsequent failure still allows an autoland with the remaining components.

VOL. II 22.2.17.3

Answer 65

A

AUTO_09 Discuss the differences in landing capability shown in FMA Column 4.

CAT 3 SINGLE indicates a fail passive autoland capability.
- A subsequent failure will not leave the aircraft in a significant out of trim condition, but an autoland may not be possible.

VOL. II 22.2.17.3

Answer 66

A

AUTO_09 Discuss the differences in landing capability shown in FMA Column 4.

CAT 1 or CAT 2 indicates that the system can track an ILS signal but an autoland is not possible.

VOL. II 22.2.17.3

Answer 67

A

AUTO_09 Discuss the differences in landing capability shown in FMA Column 4.

A downgrade in landing capability is accompanied by a triple click.
Below 200 ft. RA, the landing capability is frozen until the LAND mode is disengaged or both autopilots are off.
If a failure occurred below 200 ft. RA, the landing capability display will not change.

VOL. II 22.2.17.3

Answer 68

A

FLTMGT_01 Understand the control functions and indications on the ADIRS panel.

ON BAT Light

The ON BAT light illuminates when one or more IRs is supplied only by the aircraft batteries.
It also illuminates for a few seconds at the beginning of a full alignment as part of the self test.

VOL. II, 34.2.12.2.7

Answer 69

A

FLTMGT_01 Understand the control functions and indications on the ADIRS panel.

2. IR pbs
FAULT light - A fault is detected in the respective IR.

Illuminated steady - The respective IR is lost.
Flashing - Attitude and heading information may be recovered in ATT mode.
OFF - If the pb is selected OFF, the OFF light illuminates and the respective IR is selected off, without disabling the ADR portion of the ADIRU.

VOL. II, 34.2.12.2.7

Answer 70

A

FLTMGT_01 Understand the control functions and indications on the ADIRS panel.

3. Mode Selectors

OFF - Both the IR and ADR of the respective IRU are unpowered.
NAV - The normal operating position.
ATT - Attitude mode.
- IR position information is lost.
- In flight alignment is only possible in ATT mode.

VOL. II, 34.2.12.2.7

Answer 71

A

FLTMGT_01 Understand the control functions and indications on the ADIRS panel.

4. ADR pbs

FAULT light illuminated - A fault is detected in the respective ADR.
OFF - If the pb is selected OFF, the OFF light illuminates and the respective ADR is selected off, without disabling the IR portion of the ADIRU

VOL. II, 34.2.12.2.7

Answer 72

A

FLTMGT_02 Describe how to accomplish a full ADIRS alignment.

A green IRS IN ALIGN memo is displayed on the UPPER E/WD along with the approximate time until alignment is complete and navigation is possible (e.g., IRS IN ALIGN > 7 MIN).

VOL. II, 34.2.13.2

Answer 73

A

FLTMGT_03 Describe the errors that may be presented during an ADIRS alignment.

The IRS IN ALIGN along with the approximate time (e.g., IRS IN ALIGN > 7 MIN) appears in amber if the engines are running.

VOL. II, 34.2.13.6

Answer 74

A

FLTMGT_03 Describe the errors that may be presented during an ADIRS alignment.

Alignment errors can occur due to:
excessive aircraft movement during alignment,
or a position disagreement.
The green IRS IN ALIGN memo on the E/WD flashes during the alignment process if an alignment problem exists:
- If excessive motion is detected, the alignment is automatically restarted.
- Each IRU memorizes the computed present position when it is shutdown.
- If a significant difference exists between the position entered on INIT page A and the last memorized position, the ALIGN IRS prompt is displayed again on INIT page A and the position must be re-entered.

VOL. II, 34.2.13.6

Answer 75

A

FLTMGT_04 Describe the EFIS data switching process.

Normally, ADIRU 1 supplies data for:

the Captain’s PFD,
ND,
DDRMI,
and ATC transponder 1.

ADIRU 2 supplies data for:

the first officer’s PFD,
ND,
and ATC transponder 2.

ADIRU 3 normally does not provide information to the instrument system, and serves as a backup for ADIRU 1 or 2.

VOL. II,31.2.5.6

Answer 76

A

FLTMGT_04 Describe the EFIS data switching process.

Should a failure of either heading and attitude data, or air data be indicated on the EFIS:
- ADIRU 3 can be selected as a backup for either pilot’s instruments by using the:
  - ATT HDG and
  - AIR DATA selectors.

VOL. II,31.2.5.6

Answer 77

A

FLTMGT_04 Describe the EFIS data switching process.

Should a failure of either heading and attitude data, or air data be indicated on the EFIS:

Selecting CAPT on 3 or F/O on 3 will transfer the data source from the normal source to ADIRU 3.
In case of total failure of ADIRU 1 or 2, both the AIR DATA and ATT HDG selectors will need to be selected to:
- CA ON 3 or
- F/O ON 3 as appropriate.

VOL. II,31.2.5.6

Answer 78

A

FLTMGT_05 Recall what flight instrument data is AD information vs IR information.

Air Data
• PFD

Indicated airspeed/Mach
Barometric altitude
Backup vertical velocity (barometric)

• ND

True Air Speed (TAS)

• SD

Total Air Temperature (TAT) and Static Air Temperature (SAT)
*V2 34.2.12.2.3**
34. 2.12.2.5

Answer 79

A

FLTMGT_05 Recall what flight instrument data is AD information vs IR information.

Inertial Reference:

• PFD

Attitude
Vertical velocity
Flight path vector
Heading (true or magnetic)
Track

• ND

Heading (true or magnetic)
True wind direction and velocity
Wind vector relative to the aircraft heading (displayed as an arrow on the ND)
Track
Ground speed
Position (refined and provided via the FMS)

• DDRMI

Heading (true or magnetic)

V2
34.2.12.2.5

Answer 80

A

FLTMGT_05 Recall what flight instrument data is AD information vs IR information. V2 34.2.12.2.3
34.2.12.2.5

Inertial Reference
• ND

o Heading (true or magnetic)
o True wind direction and velocity
o Wind vector relative to the aircraft heading (displayed as an arrow on the ND)
o Track
o Ground speed
o Position (refined and provided via the FMS)

• DDRMI

o Heading (true or magnetic)

Answer 81

A

FLTMGT_05 Recall what flight instrument data is AIR DATA AD information vs IR information. V2 34.2.12.2.3
34.2.12.2.5

Inertial Reference
• DDRMI

o Heading (true or magnetic)

Answer 82

A

FLTMGT_06 Describe how GPS is integrated into the navigational systems.

The aircraft has two GPS receivers.

Each GPS receiver is integrated, along with the ILS receivers, in a modular avionics unit called the:
- Multi Mode Receiver (MMR).
Each MMR processes the data received and transmits it to its associated ADIRU.
- The ADIRU then calculates a combined GPS-IRS position (the GPIRS position).
- The FMS uses the GP-IRS position whenever GPS information is available.
- In normal operation, ADIRU 1 and 3 are supplied by MMR 1
  - ADIRU 2 is supplied by MMR 2.
- If one MMR receiver fails, the remaining receiver automatically supplies all ADIRUs

VOL. II, 34.2.14.1

Answer 83

A

FLTMGT_06 Describe how GPS is integrated into the navigational systems.

Multi Mode Receiver (MMR):

Each MMR processes the data received and transmits it to its associated ADIRU.
The ADIRU then calculates a combined GPS-IRS position (the GPIRS position).

The FMS uses the GP-IRS position whenever GPS information is available.

In normal operation, ADIRU 1 and 3 are supplied by MMR 1
and ADIRU 2 is supplied by MMR 2.
If one MMR receiver fails, the remaining receiver automatically supplies all ADIRUs

VOL. II, 34.2.14.1

Answer 84

A

FLTMGT_06 Describe how GPS is integrated into the navigational systems. VOL. II, 34.2.14.1

The FMS uses the GP-IRS position whenever GPS information is available.

In normal operation, ADIRU 1 and 3 are supplied by MMR 1 and ADIRU 2 is supplied by MMR 2.

If one MMR receiver fails, the remaining receiver automatically supplies all ADIRUs

Answer 85

A

FLTMGT_06 Describe how GPS is integrated into the navigational systems.

Note: Do not enter the gate coordinates unless GPS is inoperative.

When GPS is operative, the ADIRUs calculate a GPS-IR hybrid position which is more accurate than the gate position.

VOL. II, 34.2.14.1

Answer 86

A

FLTMGT_07 Describe the Polar navigation features.

Due to magnetic field anomalies, only true heading is available in the polar regions.
True heading may be selected for display at any time using the NORTH REF pb on the forward instrument panel.
If TRUE is not selected when approaching the polar regions, the SELECT TRU REF message is displayed on the ND.
If TRUE is not selected manually, a switchover to TRUE will occur automatically accompanied by an ECAM message.
VOL. II, 34.4.4.15

Answer 87

A

FLTMGT_07 Describe the Polar navigation features.

Caution: If the heading reference is allowed to switch over automatically, an autopilot disconnect may occur.

This is because a heading disagreement may occur if all IRUs do not reach the switch over latitude simultaneously.

VOL. II, 34.4.4.15

Answer 88

A

FLTMGT_07 Describe the Polar navigation features. VOL. II, 34.4.4.15

When selected heading references on the PFDs, NDs, and DDRMI are relative to true north:

TRU is displayed above the PFD and ND heading scales.

VOL. II, 34.4.4.15

Answer 89

A

FLTMGT_07 Describe the Polar navigation features.

The heading reference will not automatically switch back to MAG when magnetic heading information becomes available.
- Selection of MAG should be delayed until clear of the polar region.

VOL. II, 34.4.4.15

Answer 90

A

FLTMGT_08 Recall where to find the navigational accuracy level in the MCDU.

GPS PRIMARY:

GPS PRIMARY is displayed when the FMS navigation mode is GPS PRIMARY.
When GPS PRIMARY is not available or navigation mode is not GPS/IRS, the field is blank.
The MCDU scratchpad and ND displays the message GPS PRIMARY when the field first appears
- and GPS PRIMARY LOST when the field becomes blank.
VOL. II, 34.6.8.1. 11-14

Answer 91

A

FLTMGT_08 Recall where to find the navigational accuracy level in the MCDU.

REQUIRED:

The REQUIRED field displays the default value for the Required Navigation Performance (RNP) level in NM for the current area or procedure.
- The field can be modified if a different RNP value is known for the particular area or procedure.

VOL. II, 34.6.8.1. 11-14

Answer 92

A

FLTMGT_08 Recall where to find the navigational accuracy level in the MCDU.

ACCUR:

The ACCUR field displays the evaluation of the ESTIMATED accuracy value as compared to the REQUIRED accuracy level.
If the ESTIMATED position error is equal to or less than the REQUIRED value, the field displays HIGH.
If the error is greater than the REQUIRED value the field displays LOW.
VOL. II, 34.6.8.1. 11-14

Answer 93

A

FLTMGT_08 Recall where to find the navigational accuracy level in the MCDU.

ESTIMATED:

The ESTIMATED field displays the current estimated position error in NM as computed by the FMS.

VOL. II, 34.6.8.1. 11-14

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ATA 22: Autoflight Flashcards

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