.
All limit symbols are removed from the pilots PFDs
Greens =´s are depicted with amber x´s .Alpha prot and Alpha Max are replaced by Vls and Vs
Are never displayed and must be memorized by each A320 pilot
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SEC´s
FAC,s
Nothing they revert to mechanical back up.
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One
Two
Three
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Aproxsimently three minutes
Approximately 15 minutes
Approximately ten minutes
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Present position can be entered through the ADIRS CDU
Present position can be entered on the INIT page of the MCDU
Both A and B are correct .
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Flaps configuration 1
Any EPR exceed 1.25 and EPR´s differ by more than 0.30
Heading differes from track by 20 deg or more
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Are displayed as green x´s
Are displayed as green =´s
Are never displayed and must be memorized by eachA 320 pilot
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Will not allow the pilot to stall the aircraft
Prohibit steep bank angles
Can be overridden by the pilot , and it is posible to exceed Vmo, Mmo and stall the aircraft
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Extending the landing gear will place the aircraft in mechanical back up law
Extending the landing gear will place the aircraft in direct law
Extending the landing Gear will have not effect on the status of the flight controls
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Once a DMC has failed the information is unrecoverable
Rotate the EIS DMC switch on the switching panel to replace the failed DMC with DMC 3
No action is needed as recovery is automatic
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AD information will be disconnected
AD and IR information will be disconnected
The ADIRU is not energized AD and IR information is lost .
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ADMC 1 supplies data to PFD 1 ,ND 1 and LOWER ECAM supplies data for PFD 2 ND 2 and UPPER ECAM
DMC 1 supplies data to PFD 2 ND 2 and LOWER ECAM supplies data for PFD 1 ND 1 and LOWER ECAM
DMC 1 supplies data to PFD 1 and UPPER ECAM , DMC 2 supplies data for PFD 2 ,ND 2 and LOWER ECAM.
Protections , Load Factor , Pitch attitude , High AOA , Alpha floor , ange of bank ad high speed.
Protections , Load factor , Pitch attitude , High AOA and High speed.
Protections , Load factor , Pitch attitude , high AOA , Vls , alpha floor and High speed.
Pitch attitude
Bank angle
Load factor
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No power
DMC failure
The circuit breaker for that particular DU has popped
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The control surface to continue rolling the aircraft until reaching 55 degrees roll angle.
Control surface movements proportional to stick deflection, disconnected auto trim, and maintain its current attitude.
A load factor proportional to stick deflection , then maintain one G flight corrected for pitch attitude
When one or more IR´s are operating on aircraft battery power .
For few seconds at the beginning of the alignment process
Both A and B are correct
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Are displayed as green x´s
Are displayed as green =´s
Are displayed as Alpha port and Alpha max .These limits vary with GW ,CG, altitude and other environment factor.
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The flight controls revert to Direct Law
The side stick controller and flight controls revert to the AOA mode , and side stick deflection is proportional to AOA.
The flight controls remain in the load factor demand law .
Alpha speed
Vls
Alpha floor
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Alignment has been completed .
The respective IR is operating normally
Air data output has been disconnected.
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Check base Date
Check data base cycle
Check effective date
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Heading , altitude and vertical speed.
Heading , altitude and vertical speed.
Airspeed , altitude and backup vertical speed.
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NO
YES ,ILS approach
YES no LNAV or VNAV
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Pressing and holding the related system page pb on the ECAM control panel , the page will be displayed on the UPPER ECAM .
Rotating the ECAM/ND XFER switch , the LOWER ECAM page will be transferred to either the Cap or the FO BND
Both A and B
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Nothing
Move the ATT HDG knob on the switching panel to Cast 3
Move the AIR DATA knob on the switching panel to Cast 3
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Bearing and DME information for VOR 1 and ADF 1
Bearing and DME information for VOR 2 and ADF 2
Bearing only for VOR 1 and VOR 2
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1 y 2
1 y 3
1, 2 y 3
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Move the ATT HDG rotary selector knob to Cast 3
Move the EIS DMC rotary selector knob to F/O 3
Move the ATT HDG rotary selector Knob to F/O ·
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Present position needs to be entered
Attitude and heading information may be recovered in ATT mode
A completed failure of the respective IR has occurred
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Are displayed as green x´s
Are displayed as green =´s
Are never displayed and must be memorized by each pilots PFD
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The flight controls revert in Direct Law
The side stick controller and flight controls revert to the AOA mode , and side stick deflection is proportional to AOA
The fight controls remain in the load factor demand law
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Speed brakes are extended and flap handle is not at 0
Speed brake have a fault
Speed brakes are extended and engines are not at Idle
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Heading , altitude and vertical speed
Airspeed ,vertical speed and altitude
Airspeed , altitude ,and back up vertical speed
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No present position has been entered and ten minutes has elapsed since the IR was selected ON.
In addition to Answer A , an alignment fail may exist.
Altitude and Heading information have been lost
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The off light will iluminate and are data output will disconnect
The respective ADIRU will become deenergized
Both AD and IR information will be disconnected
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ADIRU 1 is supplying information to PFD 1 and ND2 and ADIRU 2 is supplying power to PFD 2 and ND 1
ADIRU 1supplying information to PFD 1, ND 1 and the DDRMI, ADIRU 2 is supplying power to PFD 2 and ND 2
None of the above
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