# A 320 Sys Autopilot

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Questions: 38 | Attempts: 192

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• 1.

### In normal law , pitch and roll attitude limits depicted on each pilots PFD

• A.

Are displayed as green x´s

• B.

Are displayed as green =´s

• C.

Are never displayed and must be memorized by each pilots PFD

B. Are displayed as green =´s
Explanation
The correct answer is "Are displayed as green =´s". In normal law, the pitch and roll attitude limits depicted on each pilot's Primary Flight Display (PFD) are displayed as green "=" symbols. This visual representation helps the pilots easily understand and maintain the permissible limits of pitch and roll attitudes during flight. It provides a clear and intuitive indication of the aircraft's attitude, ensuring safer and more precise control.

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• 2.

### In normal law Mmo and Vmo limits depicted on each pilots PFD

• A.

Are displayed as green x´s

• B.

Are displayed as green =´s

• C.

Are never displayed and must be memorized by eachA 320 pilot

B. Are displayed as green =´s
Explanation
The given answer states that the Mmo and Vmo limits in a normal law Mmo and Vmo are displayed as green "=" symbols on each pilot's PFD. This means that the correct answer is that the limits are displayed as green "=" symbols.

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• 3.

### In normal Law the low speed limits depicted on each pilots PFD

• A.

Are displayed as green x´s

• B.

Are displayed as green =´s

• C.

Are displayed as AlpHa port and AlpHa max .These limits vary with GW ,CG, altitude and other environment factor.

C. Are displayed as AlpHa port and AlpHa max .These limits vary with GW ,CG, altitude and other environment factor.
Explanation
The correct answer is "Are displayed as Alpha port and Alpha max. These limits vary with GW, CG, altitude and other environment factors." This answer accurately explains that in normal law, the low speed limits are displayed as Alpha port and Alpha max. These limits are not represented by green x's or green ='s. Additionally, it mentions that these limits can vary depending on factors such as GW (gross weight), CG (center of gravity), altitude, and other environmental factors.

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• 4.

### While in flight operating in normal law , movement of the sidesitck and subsequent return to neutral will command.

• A.

The control surface to continue rolling the aircraft until reaching 55 degrees roll angle.

• B.

Control surface movements proportional to stick deflection, disconnected auto trim, and maintain its current attitude.

• C.

A load factor proportional to stick deflection , then maintain one G flight corrected for pitch attitude

C. A load factor proportional to stick deflection , then maintain one G flight corrected for pitch attitude
• 5.

### Which inflight operating in normal Law in the Alpha port range :

• A.

The flight controls revert in Direct Law

• B.

The side stick controller and flight controls revert to the AOA mode , and side stick deflection is proportional to AOA

• C.

The fight controls remain in the load factor demand law

B. The side stick controller and flight controls revert to the AOA mode , and side stick deflection is proportional to AOA
Explanation
In normal Law in the Alpha port range, the side stick controller and flight controls revert to the AOA mode, and side stick deflection is proportional to AOA. This means that the aircraft's flight controls will respond to the angle of attack (AOA) of the aircraft. The side stick deflection will directly correspond to the AOA, allowing the pilot to control the aircraft based on its angle of attack. This mode is designed to enhance the aircraft's safety and stability during normal flight operations.

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• 6.

### While inflight operating in Normal law , in the Alpha prot range :

• A.

The flight controls revert to Direct Law

• B.

The side stick controller and flight controls revert to the AOA mode , and side stick deflection is proportional to AOA.

• C.

The flight controls remain in the load factor demand law .

B. The side stick controller and flight controls revert to the AOA mode , and side stick deflection is proportional to AOA.
• 7.

### Which statement best describes protective limit symbols depicted on the pilots PFD while in alternate law ?

• A.

All limit symbols are removed from the pilots PFDs

• B.

Greens =´s are depicted with amber x´s .AlpHa prot and AlpHa Max are replaced by Vls and Vs

• C.

Are never displayed and must be memorized by each A320 pilot

B. Greens =´s are depicted with amber x´s .AlpHa prot and AlpHa Max are replaced by Vls and Vs
Explanation
In alternate law, the protective limit symbols on the pilots PFD are depicted with amber x's instead of green '=' symbols. Additionally, the symbols for Alpha prot and Alpha Max are replaced by Vls and Vs. This means that the pilot needs to be aware of these changes and understand the new symbols and their meanings.

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• 8.

### In normal Law all predictions are active , wich of the following lists the most complete list ?

• A.

Protections , Load Factor , Pitch attitude , High AOA , AlpHa floor , ange of bank ad high speed.

• B.

Protections , Load factor , Pitch attitude , High AOA and High speed.

• C.

Protections , Load factor , Pitch attitude , high AOA , Vls , alpHa floor and High speed.

A. Protections , Load Factor , Pitch attitude , High AOA , AlpHa floor , ange of bank ad high speed.
• 9.

### Which protection is not available below 100´AGl

• A.

AlpHa speed

• B.

Vls

• C.

AlpHa floor

C. AlpHa floor
Explanation
Alpha floor is a protection system in aircraft that activates when the aircraft's angle of attack (AOA) is below a certain threshold (usually around 100° AOA). It automatically commands the aircraft to pitch up and increase thrust to prevent the aircraft from stalling. Therefore, the correct answer is Alpha floor, as it is not available below 100° AOA.

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• 10.

### When in alternate law , all protections except ,,,,,,,,,,,,,,,,,,,,,, protection will be lost

• A.

Pitch attitude

• B.

Bank angle

• C.

Explanation
When in alternate law, all protections except load factor protection will be lost. This means that the aircraft will no longer have the automatic systems to protect it from exceeding certain load factors, which are forces acting on the aircraft in various directions. Load factor protection is important because exceeding certain load factors can lead to structural damage or even failure of the aircraft. Therefore, when in alternate law, pilots must manually monitor and control the load factor to ensure the safety of the aircraft.

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• 11.

### High and low speed stabilities maybe available in alternate law stabilities

• A.

Will not allow the pilot to stall the aircraft

• B.

Prohibit steep bank angles

• C.

Can be overridden by the pilot , and it is posible to exceed Vmo, Mmo and stall the aircraft

C. Can be overridden by the pilot , and it is posible to exceed Vmo, Mmo and stall the aircraft
Explanation
Alternate law stabilities refer to the different modes in which an aircraft's flight control system operates. In this case, it means that the high and low speed stabilities can be available in alternate law mode. However, the correct answer states that in this mode, the pilot can override the system and potentially exceed the maximum operating speeds (Vmo and Mmo) and stall the aircraft. This means that the pilot has the ability to override certain limitations set by the system, which can be dangerous if not used properly.

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• 12.

### Which of the following statements is always true when operating in alternate law ?

• A.

Extending the landing gear will place the aircraft in mechanical back up law

• B.

Extending the landing gear will place the aircraft in direct law

• C.

Extending the landing Gear will have not effect on the status of the flight controls

B. Extending the landing gear will place the aircraft in direct law
Explanation
When operating in alternate law, extending the landing gear will place the aircraft in direct law. Alternate law is a mode in aircraft fly-by-wire systems where certain flight control protections are lost, and the system reverts to a simpler mode of operation. In direct law, the flight controls are directly linked to the pilot's inputs without any additional protections or assistance from the flight control system. Therefore, extending the landing gear in this mode will trigger the transition to direct law.

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• 13.

### What is the function of the FAC,,s ? 1) Rudder and yaw damping . 2) Flight envelope and Speed computations .  3) Windshear protection

• A.

1 y 2

• B.

1 y 3

• C.

1, 2 y 3

C. 1, 2 y 3
Explanation
The function of the FACs (Flight Augmentation Computers) includes rudder and yaw damping, flight envelope and speed computations, and windshear protection.

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• 14.

### What does amber SPEED BREAKS mean on lower ECAM ?

• A.

Speed brakes are extended and flap handle is not at 0

• B.

Speed brake have a fault

• C.

Speed brakes are extended and engines are not at Idle

C. Speed brakes are extended and engines are not at Idle
Explanation
The correct answer is "Speed brakes are extended and engines are not at Idle." This means that the amber SPEED BREAKS indication on the lower ECAM is indicating that the speed brakes are extended while the engines are not at idle thrust. This could be a potential issue or abnormal condition that the pilot needs to be aware of.

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• 15.

### If both ELAC.s fail , what controls the elevator and stabilizer ?

• A.

SEC´s

• B.

FAC,s

• C.

Nothing they revert to mechanical back up.

A. SEC´s
Explanation
If both ELACs fail, the elevator and stabilizer are controlled by the SECs.

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• 16.

### The DDRMI provides the pilot with :

• A.

Bearing and DME information for VOR 1 and  ADF 1

• B.

Bearing and DME information for VOR 2 and ADF 2

• C.

Bearing only for VOR 1 and VOR 2

C. Bearing only for VOR 1 and VOR 2
Explanation
The DDRMI provides the pilot with bearing information for VOR 1 and VOR 2. It does not provide DME information or ADF information for any of the VORs or ADFs.

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• 17.

### The ATT HDG and AIR DATA selectors on the switching panel in the Norm position indicate that :

• A.

ADIRU 1 is supplying information to PFD 1 and ND2 and ADIRU 2 is supplying power to PFD 2 and ND 1

• B.

ADIRU 1supplying information to PFD 1, ND 1 and the DDRMI, ADIRU 2 is supplying power to PFD 2 and ND 2

• C.

None of the above

A. ADIRU 1 is supplying information to PFD 1 and ND2 and ADIRU 2 is supplying power to PFD 2 and ND 1
Explanation
The correct answer suggests that when the ATT HDG and AIR DATA selectors are in the Norm position, ADIRU 1 is supplying information to PFD 1 and ND2, while ADIRU 2 is supplying power to PFD 2 and ND 1. This means that ADIRU 1 is responsible for providing attitude and heading information to the primary flight display (PFD) 1 and navigation display 2 (ND2), while ADIRU 2 is supplying power to PFD 2 and ND 1.

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• 18.

### Placing on of the ADR push buttons OFF will accomplish what ?

• A.

The off light will iluminate and are data output will disconnect

• B.

The respective ADIRU will become deenergized

• C.

Both AD and IR information will be disconnected

A. The off light will iluminate and are data output will disconnect
Explanation
If one of the ADR push buttons is placed OFF, the off light will illuminate and the data output will disconnect. This means that the respective ADIRU (Air Data Inertial Reference Unit) will become deenergized and both AD (Air Data) and IR (Inertial Reference) information will be disconnected.

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• 19.

### What action should be taken if ADR 1 is lost ?

• A.

Nothing

• B.

Move the ATT HDG knob on the switching panel to Cast 3

• C.

Move the AIR DATA knob on the switching panel to Cast 3

C. Move the AIR DATA knob on the switching panel to Cast 3
Explanation
If ADR 1 is lost, the correct action to take is to move the AIR DATA knob on the switching panel to Cast 3. This is because the ADR (Air Data Reference) system is responsible for providing accurate airspeed, altitude, and other important data to the aircraft's systems. By switching the AIR DATA knob to Cast 3, the aircraft will switch to using the data from ADR 3 instead of ADR 1, ensuring that the necessary information is still available for the safe operation of the aircraft.

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• 20.

### What information is supplied by the Air data Modules ADM´s and displayed on the PFD´s ?

• A.

Heading , altitude and vertical speed

• B.

Airspeed ,vertical speed and altitude

• C.

Airspeed , altitude ,and back up vertical speed

C. Airspeed , altitude ,and back up vertical speed
Explanation
The Air Data Modules (ADM's) supply information about airspeed, altitude, and back up vertical speed. This information is then displayed on the Primary Flight Displays (PFD's). The airspeed provides the speed at which the aircraft is traveling through the air, the altitude indicates the aircraft's height above sea level, and the back up vertical speed gives the rate at which the aircraft is ascending or descending. These parameters are crucial for pilots to monitor and maintain the aircraft's performance and safety during flight.

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• 21.

### What information is supplied by the IR´s and displayed on the PFD ?

• A.

Heading , altitude and vertical speed.

• B.

Heading , altitude and vertical speed.

• C.

Airspeed , altitude and backup vertical speed.

A. Heading , altitude and vertical speed.
Explanation
The information supplied by the IR's (Instrumentation Reference) and displayed on the PFD (Primary Flight Display) includes the heading, altitude, and vertical speed. These are crucial parameters for pilots to maintain proper navigation and control of the aircraft. The heading provides the direction in which the aircraft is pointing, the altitude indicates the aircraft's height above sea level, and the vertical speed gives the rate at which the aircraft is ascending or descending.

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• 22.

### What causes a DU to display a black screen with a white diagonal line ?

• A.

No power

• B.

DMC failure

• C.

The circuit breaker for that particular DU has popped

B. DMC failure
Explanation
A DMC failure can cause a DU (Display Unit) to display a black screen with a white diagonal line. This failure could be due to a malfunction or damage in the DMC (Display Management Computer) system, which is responsible for controlling and managing the display units. When the DMC fails, it can result in abnormal display behavior such as a black screen with a white diagonal line.

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• 23.

### After a single DMC failure , how could a crew member recover the display unit ?

• A.

Once a DMC has failed the information is unrecoverable

• B.

Rotate  the EIS DMC switch on the switching panel to replace the failed DMC with DMC 3

• C.

No action is needed as recovery is automatic

B. Rotate  the EIS DMC switch on the switching panel to replace the failed DMC with DMC 3
Explanation
After a single DMC failure, the crew member can recover the display unit by rotating the EIS DMC switch on the switching panel to replace the failed DMC with DMC 3. This action allows for the failed DMC to be replaced with a functioning one, ensuring that the information can still be displayed and accessed. No other action is needed as the recovery process is automatic once the switch is rotated.

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• 24.

### Is the LOWER ECAM DU fails , is there a way to retrieve that information ?

• A.

Pressing and holding the related system page pb on the ECAM control panel , the page will be displayed on the UPPER ECAM .

• B.

Rotating the ECAM/ND XFER switch , the LOWER ECAM page will be transferred to either the Cap or the FO BND

• C.

Both A and B

A. Pressing and holding the related system page pb on the ECAM control panel , the page will be displayed on the UPPER ECAM .
Explanation
Pressing and holding the related system page pb on the ECAM control panel allows the information from the LOWER ECAM DU to be displayed on the UPPER ECAM. This means that even if the LOWER ECAM DU fails, the information can still be retrieved and viewed on the UPPER ECAM. Therefore, the correct answer is pressing and holding the related system page pb on the ECAM control panel.

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• 25.

### Where is the information displayed by DMC 1 and DMC 2 ?

• A.

ADMC 1 supplies data to PFD 1 ,ND 1 and LOWER ECAM supplies data for PFD 2 ND 2 and UPPER ECAM

• B.

DMC 1 supplies data to PFD 2 ND 2 and LOWER ECAM supplies data for PFD 1 ND 1 and LOWER ECAM

• C.

DMC 1 supplies data to PFD 1 and UPPER ECAM , DMC 2 supplies data for PFD 2 ,ND 2 and LOWER ECAM.

C. DMC 1 supplies data to PFD 1 and UPPER ECAM , DMC 2 supplies data for PFD 2 ,ND 2 and LOWER ECAM.
• 26.

### What are the correct position for the PFD and ND ?

• A.

The PFD should be outboard and the ND should inboard

• B.

The PFD should be inboard and the ND should be outboard

• C.

The PFD should be tp the left of the ND for both seat positions

A. The PFD should be outboard and the ND should inboard
Explanation
The correct position for the PFD (Primary Flight Display) is outboard, meaning it should be placed on the side farthest from the center of the cockpit. On the other hand, the ND (Navigation Display) should be inboard, meaning it should be placed on the side closest to the center of the cockpit. This arrangement allows for better visibility and accessibility of both displays for the pilot.

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• 27.

### How many Air Data/Inertial Reference Units (ADIRU´S) are installed on the A 320 ?

• A.

One

• B.

Two

• C.

Three

C. Three
Explanation
The correct answer is Three. The A320 aircraft has three Air Data/Inertial Reference Units (ADIRUs) installed. These units are responsible for providing critical data such as airspeed, altitude, and attitude to the aircraft's flight control systems. Having three ADIRUs enhances redundancy and ensures accurate and reliable data for the safe operation of the aircraft.

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• 28.

### How long does a normal Ir alignment take ?

• A.

Aproxsimently three minutes

• B.

Approximately 15 minutes

• C.

Approximately ten minutes

C. Approximately ten minutes
Explanation
The correct answer is approximately ten minutes. This is the average duration for a normal IR alignment process. It is important to allocate enough time for this procedure to ensure accurate results.

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• 29.

### How can the present position of the aircraft be installed ?

• A.

Present position can be entered through the ADIRS CDU

• B.

Present position can be entered on the INIT page of the MCDU

• C.

Both A and B are correct .

C. Both A and B are correct .
Explanation
Both options A and B are correct because the present position of the aircraft can be installed either through the ADIRS CDU or on the INIT page of the MCDU. The ADIRS CDU is a control and display unit used for entering and managing the aircraft's navigation data, including the present position. On the other hand, the MCDU (Multipurpose Control and Display Unit) is a multifunctional interface used for managing various aircraft systems, including the initialization of navigation data, including the present position. Therefore, both options A and B provide valid methods for installing the present position of the aircraft.

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• 30.

### The white IR ALIGN light is flashing .What does this means ?

• A.

No present position has been entered and ten minutes has elapsed since the IR was selected ON.

• B.

• C.

Altitude and Heading information have been lost

B. In addition to Answer A , an alignment fail may exist.
Explanation
The flashing white IR ALIGN light indicates that there may be an alignment fail in addition to the fact that no present position has been entered and ten minutes have elapsed since the IR was selected ON. It suggests that there might be an issue with the alignment process of the IR system, which could affect the accuracy of altitude and heading information.

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• 31.

### The IR ALIGN light is extinguish .What does this means ?

• A.

Alignment has been completed .

• B.

The respective IR is operating normally

• C.

Air data output has been disconnected.

A. Alignment has been completed .
Explanation
The correct answer is "Alignment has been completed." This means that the process of aligning the IR (Inertial Reference) system has finished successfully. The IR system is responsible for providing accurate position, attitude, and velocity information to the aircraft. When the IR ALIGN light is extinguished, it indicates that the alignment process has been completed and the system is now ready for use.

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• 32.

### If the IR mode rotary selector is selected off

• A.

• B.

AD and IR information will be disconnected

• C.

The ADIRU is not energized AD and IR information is lost .

C. The ADIRU is not energized AD and IR information is lost .
Explanation
When the IR mode rotary selector is turned off, it means that the ADIRU (Air Data Inertial Reference Unit) is not powered or activated. As a result, both AD (Air Data) and IR (Inertial Reference) information will be lost. The ADIRU is responsible for collecting and processing data related to airspeed, altitude, and attitude of the aircraft. Without the ADIRU being energized, the aircraft will not have access to this crucial information, which can affect its navigation and flight control systems.

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• 33.

### The ON BAT light will iluminate amber .

• A.

When one or more IR´s are operating on aircraft battery power .

• B.

For few seconds at the beginning of the alignment process

• C.

Both A and B are correct

C. Both A and B are correct
Explanation
The ON BAT light will illuminate amber when one or more IR's are operating on aircraft battery power. This indicates that the IR's are using the battery as their power source. Additionally, the ON BAT light will only illuminate for a few seconds at the beginning of the alignment process. Therefore, both statements A and B are correct.

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• 34.

### An amber flashing IR FAULT light indicates that

• A.

Present position needs to be entered

• B.

Attitude and heading information may be recovered in ATT mode

• C.

A completed failure of the respective IR has occurred

B. Attitude and heading information may be recovered in ATT mode
Explanation
The amber flashing IR FAULT light indicates that attitude and heading information may be recovered in ATT mode. This means that there is a fault or failure in the respective IR, but it is still possible to retrieve attitude and heading information by switching to ATT mode. In this mode, the system may be able to provide limited or alternative data to ensure the safe operation of the device or system.

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• 35.

### What action should be taken if aIR 2 is lost ?

• A.

Move the ATT HDG rotary selector knob to Cast 3

• B.

Move the EIS DMC rotary selector knob to F/O 3

• C.

Move the ATT HDG rotary selector Knob to F/O ·

C. Move the ATT HDG rotary selector Knob to F/O ·
Explanation
If aIR 2 is lost, the correct action to be taken is to move the ATT HDG rotary selector knob to F/O. This is because the ATT HDG rotary selector knob is responsible for selecting the primary source of attitude and heading reference, and in this case, it needs to be switched to the First Officer (F/O) to maintain proper reference for attitude and heading information.

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• 36.

### If LOW ACCURACY message is displayed ,are they any approach restrictions ?

• A.

NO

• B.

YES ,ILS approach

• C.

YES no LNAV or VNAV

C. YES no LNAV or VNAV
Explanation
If the message "LOW ACCURACY" is displayed, there are approach restrictions. Specifically, there are no restrictions on using the ILS approach, but the use of LNAV (lateral navigation) or VNAV (vertical navigation) approaches is not allowed.

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• 37.

### What message is displayed if the data base effective date does not match the clock date ?

• A.

Check base Date

• B.

Check data base cycle

• C.

Check effective date

B. Check data base cycle
Explanation
If the data base effective date does not match the clock date, the message "Check data base cycle" is displayed. This suggests that the user should verify the data base cycle to ensure that it is properly aligned with the current date and time. This could be important for maintaining accurate and up-to-date information in the database.

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• 38.

### When does the sideslip indicator change to a blue Beta target ?

• A.

Flaps configuration 1

• B.

Any EPR exceed 1.25 and EPR´s differ by more than 0.30

• C.

Heading differes from track by 20 deg or more

B. Any EPR exceed 1.25 and EPR´s differ by more than 0.30
Explanation
The sideslip indicator changes to a blue Beta target when any EPR exceeds 1.25 and the EPR's differ by more than 0.30.

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• Mar 21, 2023
Quiz Edited by
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• Dec 30, 2019
Quiz Created by
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