ATA 22: Autoflight Flashcards
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
A
(c) Enter 400 in the DES CABIN RATE field on the CRZ page
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
A
(a) Either MCDU 1 or MCDU 2
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
A
(b) The corresponding MCDU has failed
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
A
(b) This results in an immediate level off and the V/S window displays 0
5
Q
On approach, ‘LAND’ is displayed on FMA’s when radio altitude is below:
(a) 700ft
(b) 400ft
(c) 200 ft
A
(b) 400ft
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
A
(b) Automatically at 30 feet if armed on the ground
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
A
(c) When the pilot orders DIR TO
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
A
(a) Maintains Vmax, V/S pulses and is boxed amber.
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
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
9
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
A
(c) This can be activated by pulling the heading knob when cleared by ATC
10
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.
A
(c) At takeoff, setting at least one thrust lever to FLX or TO/GA detent
11
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
A
(b) Armed but not active
12
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
A
(c) Both A and B are correct
13
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
A
(a) The aircraft has exited the alpha floor conditions and the TOGA power is frozen
14
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
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
15
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
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
16
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
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
17
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
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
18
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
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
19
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
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
20
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
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
21
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
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
22
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
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
23
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
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
24
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
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
25
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
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
26
AUTO\_03 Describe the different autothrust status.
Autothrust can be either
* _**\_\_\_\_\_\_\_\_\_\_**_,
* _**\_\_\_\_\_\_\_\_\_**_,
* or _**\_\_\_\_\_\_\_**_.
VOL. II, 22.2.7.2
AUTO\_03 Describe the different autothrust status.
Autothrust can be either
* **_disconnected_**,
* **_armed_**,
* or **_active_**.
VOL. II, 22.2.7.2
27
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
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
28
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
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
29
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
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
30
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
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
31
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:
Examples of Fixed thrust setting:
* _**\_\_\_\_\_\_\_\_**_
* _**\_\_\_\_\_\_\_\_**_
* _**\_\_\_\_\_\_\_\_**_
VOL. II, 22.2.7.4
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
32
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
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
33
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
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
34
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
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
35
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
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
36
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
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
37
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
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
38
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
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 altitud_**e constraints
VOL. II, 22.2.3.9
39
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
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
40
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
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 S**_peed_** 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
41
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
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 S**_elected_** speed.
* Pushed - Activates **_Managed_** speed.
VOL. II, 22.3.1
42
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
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
43
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
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
44
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
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 _S**elected**_ heading or T**_rack_** mode.
* The aircraft will then turn to the _S**elected**_ heading or T**_rack_** 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
45
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
AUTO\_07 Understand the control functions and indications on the FCU panel.
**8. LOC Pb**
* Pushing the pb **_arm_**s (or **_engage_**s), or **_disengages_** the LOC mode.
* Illuminates **_green_** when the LOC mode is **_armed_** or **_active_**.
VOL. II, 22.3.1
46
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
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
47
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
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 **_headin_**g and **_track_** values (if displayed)
* The V/S - FPA window between **_vertical speed_** and **_flight path angle_** (if displayed)
VOL. II, 22.3.1
48
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
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
49
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
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
50
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
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
51
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
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
52
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
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
53
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
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
54
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
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
55
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
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
56
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
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
57
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
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
58
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
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
59
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
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
60
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
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
61
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
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
62
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
AUTO\_09
Discuss the differences in landing capability shown in FMA Column 4.
* After an ILS app. is armed, the l**_anding 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
63
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
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
64
AUTO\_09 Discuss the differences in landing capability shown in FMA Column 4.
* CAT 3 SINGLE indicates a fail _**\_\_\_\_\_\_**_ autoland capability.
* A subsequent failure will not leave the aircraft in a significant **\_\_\_\_ __ \_\_\_\_\_\_** condition, but an _**\_\_\_\_\_\_**_ may not be possible.
VOL. II 22.2.17.3
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
65
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 _**\_\_\_\_\_\_\_**_ is not possible.
VOL. II 22.2.17.3
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
66
AUTO\_09 Discuss the differences in landing capability shown in FMA Column 4.
* A downgrade in landing capability is accompanied by a **\_\_\_\_\_\_ \_\_\_\_\_\_.**
* Below _**\_\_\_\_\_\_**_ ft. RA, the landing capability is frozen until the LAND mode is _**\_\_\_\_\_\_**_ or both autopilots are _**\_\_\_\_\_\_**_.
* If a failure occurred below _**\_\_\_\_\_\_**_ ft. RA, the landing capability display will **\_\_\_\_\_\_ \_\_\_\_\_\_**.
VOL. II 22.2.17.3
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
67
FLTMGT\_01 Understand the control functions and indications on the ADIRS panel.
1. ON BAT Light
* The ON BAT light illuminates when one or more ______ is supplied only by the aircraft _**\_\_\_\_\_\_**_.
* It also illuminates for a few seconds at the beginning of a _**\_\_\_\_\_\_**_ **\_\_\_\_\_\_** as part of the self test.
VOL. II, 34.2.12.2.7
FLTMGT\_01 Understand the control functions and indications on the ADIRS panel.
1. 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
68
FLTMGT\_01 Understand the control functions and indications on the ADIRS panel.
**2. IR pbs**
FAULT light - A fault is detected in the respective _**\_\_\_\_**_.
* Illuminated steady - The respective IR is _**\_\_\_\_\_\_**_.
* Flashing - Attitude and heading information may be recovered in _**\_\_\_\_\_\_**_ mode.
* OFF - If the pb is selected OFF, the OFF light _**\_\_\_\_\_\_**_ and the respective IR is selected off, without disabling the _**\_\_\_\_\_\_**_ portion of the ADIRU.
VOL. II, 34.2.12.2.7
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
69
FLTMGT\_01 Understand the control functions and indications on the ADIRS panel.
**3. Mode Selectors**
* OFF - Both the _**\_\_\_\_\_\_**_ and _**\_\_\_\_\_\_**_ of the respective IRU are _**\_\_\_\_\_\_**_.
* NAV - The _**\_\_\_\_\_\_**_ operating position.
* ATT - _**\_\_\_\_\_\_**_ mode.
* ______ position information is lost.
* In flight alignment is only possible in _**\_\_\_\_\_\_**_ mode.
VOL. II, 34.2.12.2.7
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
70
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 _**\_\_\_\_\_\_**_.
* OFF - If the pb is selected OFF, the OFF light illuminates and the respective _**\_\_\_\_\_\_**_ is selected off, without disabling the\_\_\_\_\_\_ portion of the ADIRU
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
71
FLTMGT\_02 **Describe how to accomplish a full ADIRS alignment.**
A green **\_\_\_\_ ______ \_\_\_\_\_\_** memo is displayed on the **\_\_\_\_\_\_** along with the approximate time until alignment is complete and navigation is possible (e.g., **\_\_\_\_ ______ \_\_\_\_\_\_** \> 7 MIN).
VOL. II, 34.2.13.2
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
72
FLTMGT\_03 Describe the **errors** that may be presented during an ADIRS alignment.
* The **\_\_\_\_\_\_ ______ \_\_\_\_\_\_** along with the approximate time (e.g., **\_\_\_\_\_\_ ______ \_\_\_\_\_\_** \> 7 MIN) appears in _**\_\_\_\_\_\_\_**_ if the engines are running.
VOL. II, 34.2.13.6
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
73
FLTMGT\_03 Describe the **errors** that may be presented during an ADIRS alignment.
* Alignment errors can occur due to:
* excessive aircraft _**\_\_\_\_\_\_**_ during alignment,
* or a position _**\_\_\_\_\_\_**_.
* The green _____ \_\_\_\_\_ \_\_\_\_memo on the E/WD flashes during the alignment process if an alignment problem exists:
* If excessive motion is detected, the alignment is automatically _**\_\_\_\_\_\_**_.
* Each IRU memorizes the computed present position when it is _**\_\_\_\_\_\_.**_
* If a significant _**\_\_\_\_\_\_**_ exists between the position entered on INIT page A and the last _**\_\_\_\_\_\_**_ position, the **\_\_\_\_\_\_ \_\_\_\_\_\_** prompt is displayed again on INIT page A and the position must be\_\_\_\_\_\_.
VOL. II, 34.2.13.6
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 **_disagreemen_**t.
* 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
74
FLTMGT\_04 Describe the EFIS data switching process.
Normally, ADIRU 1 supplies data for:
* the ______ _**\_\_\_\_\_\_**_,
* _**\_\_\_\_\_\_**_,
* _**\_\_\_\_\_\_**_,
* and ATC transponder _**\_\_\_\_\_**_.
ADIRU 2 supplies data for:
* the\_\_\_\_\_\_ ______ \_\_\_\_\_\_,
* _**\_\_\_\_**_,
* and ATC transponder _**\_\_**_.
ADIRU 3 normally does not provide information to the instrument system, and serves as a backup for ______ 1 or 2.
VOL. II,31.2.5.6
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
75
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 _**\_\_\_\_\_\_**_ can be selected as a backup for either pilot’s instruments by using the:
* **\_\_\_\_\_\_** **\_\_\_\_\_\_** and
* **\_\_\_\_\_\_ \_\_\_\_\_\_** selectors.
VOL. II,31.2.5.6
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
76
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 _**\_\_\_\_\_\_\_**_ **\_\_\_\_**.
* In case of total failure of ADIRU 1 or 2, both the _**\_\_\_\_\_\_**_ _**\_\_\_\_\_\_**_and ___ **\_\_\_\_** selectors will need to be selected to:
* CA ON **\_\_\_\_** or
* F/O ON **\_\_\_\_** as appropriate.
VOL. II,31.2.5.6
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
77
FLTMGT\_05 Recall what flight instrument data is AD information vs IR information.
**Air Data**
• PFD
* Indicated **\_\_\_\_\_\_/\_\_\_\_\_\_**
* Barometric _**\_\_\_\_\_\_**_
* **\_\_\_\_\_\_ \_\_\_\_\_\_**velocity (barometric)
• ND
* _**\_\_\_\_\_\_**_ Speed (\_\_\_\_\_\_)
• SD
* **\_\_\_\_\_\_ ______ \_\_\_\_\_\_** (_**\_\_\_\_\_\_**_) and _**\_\_\_\_\_\_**_ **\_\_ __________ (\_\_\_\_\_\_**)
V2 34.2.12.2.3
34.2.12.2.5
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
78
FLTMGT\_05 Recall what flight instrument data is AD information vs IR information.
**Inertial Reference:**
• PFD
* _**A\_\_\_\_\_\_**_
* _**V\_\_\_\_\_\_**_velocity
* **F\_\_\_\_\_\_ P\_\_\_\_\_\_** vector
* _**H\_\_\_\_\_\_**_ (**\_\_\_\_\_\_ or \_\_\_\_\_\_**)
* _**T\_\_\_\_\_\_**_
• ND
* _**H\_\_\_\_\_\_**_ (**_true or magnetic_**)
* **\_\_\_\_\_\_ wind** direction and velocity
* **W\_\_\_\_\_\_** vector relative to the aircraft H_**\_\_\_\_\_\_**_ (displayed as an arrow on the _**\_\_\_\_\_\_**_)
* _**T\_\_\_\_\_\_**_
* **G\_\_\_\_\_\_ \_\_\_\_\_\_**
* _**P\_\_\_\_\_\_**_ (refined and provided via the FMS)
• DDRMI
* _**\_\_\_\_\_\_**_ (**_true or magnetic_**)
V2
34.2.12.2.5
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
79
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 \_\_\_\_\_\_\_\_**_g_** (true or magnetic)
* o True ________ direction and \_\_\_\_\_\_\_\_
* o Wind ________ relative to the aircraft ________ (displayed as an arrow on the **_ND_**)
* o \_\_\_\_\_\_\_\_
* o ________ speed
* o ________ (refined and provided via the FMS)
• DDRMI
* o _________ (true or magnetic)
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)
80
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 _**\_\_\_\_\_\_\_\_\_**_ (_**\_\_\_\_\_**_ or _**\_\_\_\_\_\_**_)
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_**)
81
FLTMGT\_06 Describe how GPS is integrated into the navigational systems.
The aircraft has _**\_\_\_\_\_\_**_ GPS receivers.
* Each GPS receiver is integrated, along with the\_\_\_\_ receivers, in a modular avionics unit called the:
* **\_\_\_\_\_\_ ______ \_\_\_\_\_\_** (MMR).
* Each MMR processes the data received and transmits it to its associated _**\_\_\_\_\_\_**_.
* The _**\_\_\_\_\_\_**_ then calculates a combined **\_\_\_\_\_\_-\_\_\_\_\_\_** position (the GPIRS position).
* The FMS uses the **\_\_\_\_\_\_-\_\_\_\_\_\_** position whenever GPS information is available.
* In normal operation, ADIRU 1 and 3 are supplied by _**\_\_\_\_\_\_**_
* ADIRU 2 is supplied by _**\_\_\_\_\_\_**_.
* If one MMR receiver fails, the remaining receiver _**\_\_\_\_\_\_**_ supplies all _**\_\_\_\_\_\_**_
VOL. II, 34.2.14.1
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
82
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 _**\_\_\_\_\_\_**_.
* The _**\_\_\_\_\_\_**_ then calculates a combined **\_\_\_\_\_\_-\_\_\_\_\_\_** position (the _**\_\_\_\_\_\_**_ position).
The FMS uses the **\_\_\_\_\_\_-\_\_\_\_\_\_** position whenever GPS information is available.
* In normal operation, **\_\_\_\_\_\_ __ and \_\_** are supplied by MMR 1
* and **\_\_\_\_\_\_ \_\_** is supplied by MMR 2.
* If one _**\_\_\_\_\_\_**_ receiver fails, the remaining receiver automatically supplies all ADIRUs
VOL. II, 34.2.14.1
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
83
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
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
84
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 _**\_\_\_\_****_--_****\_\_\_\_**_ hybrid position which is more accurate than the gate position.
VOL. II, 34.2.14.1
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
85
FLTMGT\_07 Describe the Polar navigation features.
* Due to **\_\_\_\_\_\_ \_\_\_\_\_\_** anomalies, only true heading is available in the polar regions.
* True heading may be selected for display at any time using the **\_\_\_\_\_\_ \_\_\_\_\_\_** pb on the forward instrument panel.
* If TRUE is not selected when approaching the polar regions, the **\_\_\_\_\_ _____ \_\_\_\_\_**message is displayed on the _**\_\_\_**_.
* If TRUE is not selected manually, a switchover to TRUE will occur _**\_\_\_\_\_\_**_ accompanied by an _**\_\_\_\_\_\_**_ message.
* VOL. II, 34.4.4.15
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
86
FLTMGT\_07 Describe the Polar navigation features.
Caution: If the heading reference is allowed to switch over automatically, an _**\_\_\_\_\_\_**_ disconnect may occur.
* This is because a heading _**\_\_\_\_\_\_**_ may occur if all _**\_\_\_\_\_\_**_ do not reach the switch over _**\_\_\_\_\_\_**_ simultaneously.
VOL. II, 34.4.4.15
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
87
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:
* _**\_\_\_\_\_**_is displayed above the _**\_\_\_\_\_**_ and _**\_\_\_\_\_**_ heading scales.
VOL. II, 34.4.4.15
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
88
FLTMGT\_07 Describe the Polar navigation features.
* The heading reference will not _**\_\_\_\_\_\_\_\_\_\_**_ switch back to _**\_\_\_\_\_**_ when magnetic heading information becomes available.
* Selection of _**\_\_\_\_\_\_**_ should be delayed until clear of the polar region.
VOL. II, 34.4.4.15
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
89
FLTMGT\_08 Recall where to find the navigational accuracy level in the MCDU.
**GPS PRIMARY:**
* GPS PRIMARY is displayed when the _**\_\_\_\_\_\_**_ navigation mode is **\_\_\_\_\_\_ \_\_\_\_\_\_**
* When GPS PRIMARY is not available or navigation mode is not GPS/IRS, the field is _**\_\_\_\_\_\_**_.
* The MCDU scratchpad and _**\_\_\_\_**_ displays the message **\_\_\_\_\_\_ \_\_\_\_\_\_** when the field first appears
* and _**\_\_\_\_\_\_ ______ \_\_\_\_\_\_**_ when the field becomes blank.
* VOL. II, 34.6.8.1. 11-14
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 LOS_**T when the field becomes blank.
* VOL. II, 34.6.8.1. 11-14
90
FLTMGT\_08 Recall where to find the navigational accuracy level in the MCDU.
REQUIRED:
* The REQUIRED field displays the default value for the **\_\_\_\_\_ ____________ \_\_\_\_\_\_ (\_\_\_\_\_\_)** level in NM for the current area or procedure.
* The field can be modified if a different _**\_\_\_\_\_\_**_ value is known for the particular area or procedure.
VOL. II, 34.6.8.1. 11-14
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
91
FLTMGT\_08 Recall where to find the navigational accuracy level in the MCDU.
**ACCUR:**
* The ACCUR field displays the evaluation of the _**\_\_\_\_\_\_**_ accuracy value as compared to the _**\_\_\_\_\_\_**_ accuracy level.
* If the _**\_\_\_\_\_\_**_ position error is equal to or **\_\_\_\_\_\_ \_\_\_\_\_\_** the _**\_\_\_\_\_\_**_ value, the field displays _**\_\_\_\_\_\_**_.
* If the error is greater than the _**\_\_\_\_\_\_**_ value the field displays _**\_\_\_\_\_\_**_.
* VOL. II, 34.6.8.1. 11-14
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
92
FLTMGT\_08 Recall where to find the navigational accuracy level in the MCDU.
**ESTIMATED:**
* The ESTIMATED field displays the current estimated **\_\_\_\_\_\_ \_\_\_\_\_\_** in NM as computed by the _**\_\_\_\_\_\_**_.
VOL. II, 34.6.8.1. 11-14
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
