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4. Systems > 8 - FMGS / Navigation - GPS - ADIRS > Flashcards

8 - FMGS / Navigation - GPS - ADIRS Flashcards

1
Q
  1. (DSC-34-10) What does it mean when the ADR fault light illuminates steady on the ADIRS CDU ;
    (a) The respective IR is lost
    (b) No present position entry after 10 mins.
    (c) Alignment has been completed.
    (d) A fault is detected in air data reference.
A

(d) A fault is detected in air data reference.

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2
Q
  1. (DSC-34-10) On the pedestal mounted switching panel the ATT HDG and AIR DATA selectors are at NORM, meaning ;
    (a) ADIRU 1 supplies data to PFD 1, ND 1. ADIRU 2 supplies data to PFD 2, ND 2.
    (b) ADIRU 1 supplies data to PFD 1, ND 1 and RMI / VOR DME. ADIRU 2 supplies data to PFD 2, ND 2.
    (c) ADIRU 1 supplies data to PFD 1. ADIRU 2 supplies data to PFD 2.
    (d) ADIRU 1 supplies data to PFD 1 & ND 2. ADIRU 2 supplies data to PFD 2 & ND 1.
A

(b) ADIRU 1 supplies data to PFD 1, ND 1 and RMI / VOR DME. ADIRU 2 supplies data to PFD 2, ND 2.

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3
Q
  1. (DSC-34-30) Tuning of VOR / DME and ILS is provided by;

(a) Automatic tuning / Manual tuning / Back up tuning.
(b) Automatic tuning / Manual tuning.
(c) Automatic tuning / Back up tuning.
(d) Manual tuning / back up tuning.

A

(a) Automatic tuning / Manual tuning / Back up tuning.

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4
Q
  1. (DSC-34-30) In case of failure of FMGC 1 & 2 (Back up tuning) ;
    (a) VOR, ILS and ADF receivers 1 & 2 can be tuned through RMP 1.
    (b) VOR, ILS and ADF receivers 1 can be tuned through RMP 1.
    (c) RMP1 controls VOR, ILS DME and ADF receivers 1. RMP 2 controls VOR, ILS DME and ADF receivers 2.
    (d) VOR, ILS and ADF receivers 1 and 2 can be tuned through either RMP.
A

(c) RMP1 controls VOR, ILS DME and ADF receivers 1. RMP 2 controls VOR, ILS DME and ADF receivers 2.

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5
Q
  1. (DSC-34-10) the align light flashes ;
    (a) Within 5 mins. of Nav. mode selection when present position has not been entered.
    (b) IR alignment fault, or no present position entry after 10 mins or difference between position at shut down and entered position exceeds 1 deg. of lat. or long.
    (c) When alignment has been completed.
    (d) When the ADIRS switches are off.
A

(b) IR alignment fault, or no present position entry after 10 mins or difference between position at shut down and entered position exceeds 1 deg. of lat. or long.

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6
Q
  1. (DSC-22-10) The FMGS consists of the following main components ;
    (a) 2 FMGC - 2 MCDU - 2 FAC - 2 FCU control panels.
    (b) 2 FMGC - 2 MCDU - 2 FAC - 1 FCU control panel.
    (c) 2 FMGC - 2 MCDU - 2 FAC - 2 ECAM.
    (d) 2 FMGC - 2 MCDU - 2 ECAM - 1 FCU control panel.
A

(b) 2 FMGC - 2 MCDU - 2 FAC - 1 FCU control panel.

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7
Q
  1. (DSC-22-10) Normal electrical power supplies the aircraft, and the MCDU CRT is dark, without any other warning or message , it means ;
    (a) The FMGC has been switched off with the On / Off key on the key-pad.
    (b) The FMGC has failed.
    (c) The MCDU CB is pulled.
    (d) The MCDU ‘BRT’ knob is dimmed.
A

(d) The MCDU ‘BRT’ knob is dimmed.

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8
Q
  1. (PRO-NOR-SOP-06) On the ground, when electrical power is initially supplied to the aircraft, the MCDU will normally automatically display ;
    (a) Airport page.
    (b) Init. A page.
    (c) Data index page.
    (d) A/C status page ( for database validity check).
A

(d) A/C status page ( for database validity check).

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9
Q
  1. (DSC-34-10) What does a steady align light indicate on an ADIRU
    (a) The system can only be used in ATT mode.
    (b) The system is unable to enter Nav. mode to compute co-ordinates, switch it off.
    (c) The respective IR is operating normally in align mode
    (d) The system has not aligned and must be reset.
A

(c) The respective IR is operating normally in align mode

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10
Q
  1. (DSC-22-10-30) These messages appear on the co-pilot side ND ; ‘Select offside range/mode’ & ‘Map not available’.
    (a) The IRS’s have not reached complete alignment.
    (b) The flight plan entered in captains FMGC has not been transferred into co-pilots FMGC.
    (c) Single FMGC operation and the two EFIS control panels are not set at the same range and mode.
    (d) The FMGCs are in independent mode of operation.
A

(c) Single FMGC operation and the two EFIS control panels are not set at the same range and mode.

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11
Q
  1. (PRO-SUP-22) Engines running, ready to taxi, a message appears ; ‘Check GW’ ,access to init ‘B’ page is no longer available , On which page is it possible to insert the correct GW
    (a) T/o performance page.
    (b) Progress page.
    (c) Fuel prediction page.
    (d) Init ‘A’ page.
A

(c) Fuel prediction page.

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12
Q
  1. (PRO-NOR-SRP-01 FMS-30) Aircraft on runway centerline, ready for take off ; To preset a heading of 233 deg. ;
    (a) Pull Hdg. knob to disarm Nav. mode, set 233 deg. and press Hdg. knob to engage.
    (b) Turn Hdg. knob, set 233 deg. and pull to engage.
    (c) Turn Hdg. knob, set 233 deg., pull Hdg. knob when ATC clears to turn to 233 deg.
    (d) Write H233 onto MCDU ‘scratchpad’ and when cleared by ATC perform a lateral revision at the current waypoint to turn onto Hdg. 233 deg.
A

(c) Turn Hdg. knob, set 233 deg., pull Hdg. knob when ATC clears to turn to 233 deg.

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13
Q
  1. (DSC-22-30) One of the SRS disengagement conditions is not true;
    (a) Disengages automatically at FCU alt.
    (b) Disengages automatically at acceleration alt.
    (c) Disengages manually by pulling the speed knob.
    (d) Disengaged by setting a new FCU altitude.
A

(d) Disengaged by setting a new FCU altitude.

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14
Q
  1. (DSC-22-10) Control of the aircraft can be automatic or manual. Guidance of the aircraft can be managed or selected. How do you understand the following situation; Managed Guidance - Manual Control – Selected Speed.
    (a) FMGC computes and sends steering orders for navigation purpose, the pilot flies through the side stick, speed is adjusted in the FCU window.
    (b) The autopilot follows the flight plan, the pilot sets the necessary data for longitudinal and lateral control of the aircraft, the target speed is computed and displayed by the FMGC.
    (c) Managed guidance means the autopilot is engaged.
    (d) Selected guidance means the pilot is flying through the side stick.
A

(a) FMGC computes and sends steering orders for navigation purpose, the pilot flies through the side stick, speed is adjusted in the FCU window.

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15
Q
  1. (DSC-22-20-30-10-15) A hold has been entered in the flight plan, speed and Nav. are managed, You want to leave this hold ;
    (a) Use the CLR key.
    (b) Hold is automatically cancelled when overflying the holding fix.
    (c) Activate the ‘Imm EXIT’ prompt.
    (d) Clear any discontinuity after the holding fix and the aircraft will leave the hold next time over the holding fix.
A

(c) Activate the ‘Imm EXIT’ prompt.

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16
Q
  1. (DSC-22-20) For aircraft position determination, FMGC uses data from ;
    (a) GPS only.
    (b) Clocks and Ground speed computation.
    (c) ADIR 1 only.
    (d) DME, VOR, GPS or ILS systems and 3 ADIRS.
A

(d) DME, VOR, GPS or ILS systems and 3 ADIRS.

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17
Q
  1. (DSC-22-20-30-10-15) In flight, following a manual position updating of the FMGC ;
    (a) It is also necessary to update the IRS position.
    (b) An IRS cannot be updated during a/c motion.
    (c) It is also necessary to realign the ADIRs at the new position ( full align).
    (d) It is necessary to realign the ADIRs using the quick align method.
A

(b) An IRS cannot be updated during a/c motion.

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18
Q
  1. (PRO-SUP-34) How long does a normal IR alignment take ;
    (a) Approximately 7 minutes
    (b) Approximately 2 minutes
    (c) Approximately 10 minutes
    (d) Approximately 5 minutes
A

(c) Approximately 10 minutes

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19
Q
  1. (DSC-22-30) What are the basic modes of the AP/FD (Flight engagement) ;
    (a) Pitch and roll.
    (b) V/S and HDG.
    (c) ALT and NAV.
    (d) SPD and HDG.
A

(b) V/S and HDG.

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20
Q
  1. (DSC-22-30) The engagement of both autopilots is possible ;
    (a) When ‘Land’ illuminates in green on the FMA.
    (b) When A/C is stabilised at G/S interception altitude.
    (c) As soon as the Loc. has been intercepted.
    (d) After appr. Pb. switch is pressed and illuminates.
A

(d) After appr. Pb. switch is pressed and illuminates.

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21
Q
  1. (DSC-31-40) Can you read the heading on the PFD ;
    (a) Yes.
    (b) No.
    (c) Only in ‘Plan’ mode.
    (d) Only when not in ‘Plan’ mode.
A

(a) Yes.

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22
Q
  1. (DSC-27-20-10) A/C is in clean configuration and normal law, when the FAC detects a too high angle of attack ;
    (a) Stall warning is activated.
    (b) THR LK flashes on FMA.
    (c) Alpha floor function operates.
    (d) LAF load alleviation function becomes active.
A

(c) Alpha floor function operates.

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23
Q
  1. (PRO-NOR-SRP-01 FMS-70) During ils approach, land 3 fail passive (also called Cat III single) , one engine fails below 100 ft. RA ; Will this cause a landing capability downgrade and require a go-around ;
    (a) Yes, a downgrade will occur and you must go-around.
    (b) No , a downgrade will not occur and you may continue to land.
    (c) Yes, a downgrade will occur BUT a go-around is not required.
    (d) Yes, a downgrade will occur, and you may land or go-around.
A

(b) No , a downgrade will not occur and you may continue to land.

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24
Q
  1. (DSC-22-30) During an ils approach the NAV mode will be deactivated at ;
    (a) Glide slope capture.
    (b) Localizer capture.
    (c) Loc. & glide must be captured.
    (d) MDA.
A

(b) Localizer capture.

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25
Q
  1. (DSC-22-30) Can you display FD bars and FPV at the same time, for cross checking on different PFDs ;
    (a) Yes, Capt. and F/o can each have HDG/Vs or Trk/Fpa.
    (b) No, the FD presentation on both PFDs will always be the same.
    (c) Yes, different presentations are possible but standard operating procedure requires both to be the same.
    (d) Yes, both presentations are possible and standard operating procedure permits both at the same time.
A

(b) No, the FD presentation on both PFDs will always be the same.

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26
Q
  1. (LIM-22) Certified FMGS limitations, max wind conditions for CAT III automatic approach, performed in managed speed guidance and with autothrust Head wind Tail wind X-wind

(a) 30 kt 10 kt. 20 kt.
(b) 40 kt. 10 kt. 15 kt.
(c) 20 kt. 10 kt. 20 kt.
(d) 40 kt. 10 kt. 20 kt.

A

(a) 30 kt 10 kt. 20 kt.

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27
Q
  1. (DSC-22-30) The continuous cavalry charge audio identifies only one of the following situations ;

(a) Over speed for the actual A/c configuration.
(b) Fire or oil low pressure on one engine.
(c) Autopilot disengagement.
(d) Excess cabin altitude.

A

(c) Autopilot disengagement.

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28
Q
  1. (DSC-22-30) Setting the thrust levers at idle will disengage the auto thrust mode, auto thrust will re-engage and become active :-
    (a) As soon as the thrust levers position is changed.
    (b) When the A/thr push button is pressed and the levers are back in the climb detent.
    (c) As soon as the levers are back in the climb detent.
    (d) Provided the levers are moved form the idle position.
A

(b) When the A/thr push button is pressed and the levers are back in the climb detent.

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29
Q
  1. (DSC-22-30) In one of the cases listed below, A/thr does not disengage ;
    (a) When the two thrust levers are set at the idle position.
    (b) Pressing the A/thr pushbutton on the FCU.
    (c) When the aural warning announces ‘Retard’.
    (d) Pressing the instinctive disconnect button.
A

(c) When the aural warning announces ‘Retard’.

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30
Q
  1. (DSC-22-30) The LOC Pb on the FCU is pressed to arm LOC mode, this mode is used for
    (a) Performing a published localizer approach.
    (b) Tracking a VOR beam during an approach.
    (c) Performing Non Precision Approaches VOR / ADF / RNAV.
    (d) Performing a published Localizer approach or approaching on an ils before intercepting the glideslope.
A

(d) Performing a published Localizer approach or approaching on an ils before intercepting the glideslope.

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31
Q
  1. (PRO-NOR-SRP-01 FMS-70) What does a triple click mean during an ils approach ;
    (a) A level 3 warning to the crew.
    (b) A primary failure is occurring, prepare for go-around.
    (c) Flaps are set at 3 and the landing gear is not down.
    (d) Landing capability down grade warning. .
A

(d) Landing capability down grade warning. .

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32
Q
  1. (PRO-ABN-24) Following a dual engine generator failure, emergency gen. supplies the A/C.
    (a) FMGC 1 only is available (Nav. function only).
    (b) FMGC 2 only is available.
    (c) Both FMGCs are available.
    (d) No FMGC is available.
A

(a) FMGC 1 only is available (Nav. function only).

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33
Q
  1. (PRO-ABN-34) In which case are AP/FD, ATS and Landing capacities totally lost ;
    (a) 2 IRS’s failure or 2 ADR’s failure.
    (b) 2 RA’s failure.
    (c) 2 ILS’s failure.
    (d) Both FAC’s failure.
A

(a) 2 IRS’s failure or 2 ADR’s failure.

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34
Q
  1. (DSC-27-20-10) The mandatory parameter used by the Alpha Floor detection is ;
    (a) A/C minimum speed.
    (b) A/C weight.
    (c) A/C maximum speed.
    (d) A/C angle of attack.
A

(d) A/C angle of attack.

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35
Q
  1. (DSC-27-10) Rudder travel limitation is a function of ;
    (a) FAC only.
    (b) FAC in normal and ELAC in alternate.
    (c) ELAC only.
    (d) ELAC in Normal and FAC in alternate.
A

(a) FAC only.

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36
Q
  1. (DSC-34-10) The Display Data Selector on the ADIRU id placed in the HDG position and the display SYS selector knob is selected to 1. What information is shown on the ADIRU CDU display window
    (a) Aircraft heading and track in relation to magnetic north, based on the average of the inputs from all three IR’s
    (b) Aircraft heading and track in relation to true north, based on the average of the inputs from all three IR’s
    (c) Aircraft heading in relation to true north as determined by IR 1
    (d) Aircraft heading in relation to magnetic north as determined by IR 1
A

(c) Aircraft heading in relation to true north as determined by IR 1

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37
Q
  1. (DSC-27-20-30) The ELAC safety tests (power up test) are automatically performed
    (a) On ground at computer power up.
    (b) In case of discrepancy between two computers.
    (c) In flight when a failure occurs.
    (d) In flight at autopilot engagement.
A

(a) On ground at computer power up.

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38
Q
  1. (DSC-34-20) The electric standby horizon normally draws current from;
    (a) The AC ESS BUS. In case of total electrical failure, the horizon remains unusable for 5 minutes.
    (b) The DC ESS BUS. In case of total electrical failure, the horizon remains usable for 5 minutes
    (c) The DC ESS BUS. In case of total electrical failure, the horizon remains unusable for 10 minutes
    (d) The DC ESS BUS. In case of total electrical failure, the horizon remains unusable for 5 minutes
A

(b) The DC ESS BUS. In case of total electrical failure, the horizon remains usable for 5 minutes

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39
Q
  1. (DSC-22-10) The FMGC functions are ;
    (a) Flight guidance and flight envelope protection.
    (b) Flight management and flight envelope protection.
    (c) Flight management and flight guidance.
    (d) Flight envelope protection and yaw axis control.
A

(c) Flight management and flight guidance.

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40
Q
  1. (DSC-27-10) The trim function of the FAC is ;
    (a) Pitch trim.
    (b) Rudder trim.
    (c) Aileron trim.
    (d) Pitch trim and Rudder trim.
A

(b) Rudder trim.

41
Q
  1. (DSC-22-10) The AFS computers are ;
    (a) FMGC and ELAC.
    (b) FMGC and SEC.
    (c) FMGC and FAC.
    (d) ELAC and SEC.
A

(c) FMGC and FAC.

42
Q
  1. (DSC-22-10) With AP 1 and AP 2 not engaged, FD 1 and FD 2 engaged and A/Thr active ;
    (a) FMGC 1 controls engine 1, FMGC 2 controls engine 2.
    (b) FMGC 1 controls both engines.
    (c) FMGC 2 controls both engines.
    (d) Flight controls and engines are controlled by only one FMGC.
A

(b) FMGC 1 controls both engines.

43
Q
  1. (DSC-22-30) Which of the following will NOT cause the autopilot to disengage ;
    (a) Side stick deflection in roll.
    (b) Side stick deflection in pitch.
    (c) Rudder pedal deflection.
    (d) Deflection of NWS tiller.
A

(d) Deflection of NWS tiller.

44
Q
  1. (DSC-22-10) In normal operation, with the two MCDU showing the same page, a modification made by the pilot on MCDU 1 is sent to MCDU 2 ;
    (a) Directly.
    (b) Via FMGC 1.
    (c) Via FMGC 1 and FMGC 2.
    (d) Via FMGC 1, FMGC 2 and RMP 2.
A

(c) Via FMGC 1 and FMGC 2.

45
Q
  1. (DSC-22-10) The flight guidance functions are ;
    (a) Autopilot, flight plan, autothrust.
    (b) Autopilot, performance, flight plan.
    (c) Autopilot, flight director, autothrust.
    (d) Flight management, autopilot, autothrust.
A

(c) Autopilot, flight director, autothrust.

46
Q
  1. (DSC-22-20) The position of the aircraft, used in the flight plan is computed by ;
    (a) FG part of the FMGC.
    (b) FM part of the FMGC.
    (c) The DMC.
    (d) The MCDU.
A

(b) FM part of the FMGC.

47
Q
  1. (DSC-22-30) The flight director is engaged ;
    (a) By pressing the FD P/b on the FCU.
    (b) Automatically at system power up.
    (c) By selecting a mode on the FCU.
    (d) By selecting the Init page on the FCU.
A

(b) Automatically at system power up.

48
Q
  1. (DSC-27-10) With autopilot engaged, the rudder is normally controlled by;
    (a) The FMGC.
    (b) The FAC.
    (c) The ELAC.
    (d) The SEC.
A

(b) The FAC.

49
Q
  1. (DSC-22-10) The normal FMGC operation is ;
    (a) Only one FMGC can operate at a time.
    (b) FMGC 1 has priority, FMGC 2 is in standby.
    (c) FMGC’s operate according to a master slave principle.
    (d) FMGC’s operate independently.
A

(c) FMGC’s operate according to a master slave principle.

50
Q
  1. (DSC-22-10) The FCU allows ;
    (a) Modification of the flight plan.
    (b) Selection of flight guidance functions / modes.
    (c) Selection of radio nav frequencies.
    (d) IRS alignment.
A

(b) Selection of flight guidance functions / modes.

51
Q
  1. (DSC-27-20-10) In cruise lateral AP orders are executed by ;
    (a) Ailerons and spoilers.
    (b) Ailerons and rudder.
    (c) Rudder and spoilers.
    (d) Ailerons spoilers and rudder.
A

(d) Ailerons spoilers and rudder.

52
Q
  1. (DSC-22-30) With the aircraft in flight, AP engaged and A/Thr active, The A/Thr mode ;
    (a) Can be chosen by the pilot on the FCU.
    (b) Can be chosen by the pilot on the MCDU.
    (c) Depends on the AP lateral mode.
    (d) Depends on the AP vertical mode.
A

(d) Depends on the AP vertical mode.

53
Q
  1. (DSC-22-30) With the aircraft in flight, A/Thr not engaged, Thr levers on CLB detent, an Alpha floor is detected ;
    (a) A/Thr does not get engaged because the engines are already in CLB. Thrust.
    (b) A/Thr automatically engages but is not active.
    (c) A/Thr automatically engages and controls the engines with CLB thrust.
    (d) A/Thr automatically engages and controls the engines with TOGA thrust.
A

(d) A/Thr automatically engages and controls the engines with TOGA thrust.

54
Q
  1. (DSC-27-10) The FAC computes rudder travel limit ;
    (a) Only when AP is engaged.
    (b) Only at low speed.
    (c) Only in case of ELAC failure.
    (d) At any time.
A

(d) At any time.

55
Q
  1. (DSC-22-30) On the FMA, on the second line of the longitudinal zone ;
    (a) ALT can be only in green or magenta.
    (b) ALT in cyan indicates that ALT mode is active.
    (c) Alt in cyan indicates that ALT mode is armed.
    (d) ALT in cyan indicates that ALT mode is active or a FM altitude constraint.
A

(c) Alt in cyan indicates that ALT mode is armed.

56
Q
  1. (DSC-22-30) With the thrust levers in the climb gate, A/Thr disengages ; the engines thrust ;
    (a) Equals the Climb thrust limit.
    (b) Is frozen at the existing thrust.
    (c) Corresponds to the thrust lever position.
    (d) Progressively becomes equal to the thrust lever position.
A

(b) Is frozen at the existing thrust.

57
Q
  1. (DSC-22-30) When Take off mode is engaged ;
    (a) A/Thr automatically engages and is active.
    (b) A/Thr automatically engages but is not active.
    (c) A/Thr does not automatically engage and the engines are controlled by the thrust levers.
    (d) A/Thr does not automatically engage and the engines are controlled by the last thrust target.
A

(b) A/Thr automatically engages but is not active.

58
Q
  1. (DSC-34-10) ADIRU 3 can supply information to ;
    (a) DMC 1 and DMC 2 only.
    (b) DMC 1 and DMC 3 only.
    (c) DMC 2 and DMC 3 only.
    (d) DMC 1, DMC 2 and DMC 3.
A

(d) DMC 1, DMC 2 and DMC 3.

59
Q
  1. (DSC-34-10) Air data modules (ADM) supply pressure information to the ADIRU’s from ;
    (a) All pitot probes and static ports.
    (b) The pitot probes only.
    (c) The static ports only.
    (d) The captain and F/o pitot probes and static ports only.
A

(a) All pitot probes and static ports.

60
Q
  1. (DSC-34-10) ADIRS 3 receives TAT information from ;
    (a) The captains TAT sensor.
    (b) The F/O’s TAT sensor.
    (c) The Captain and F/o’s TAT sensors.
    (d) The stand- by TAT sensor.
A

(a) The captains TAT sensor.

61
Q
  1. (DSC-34-10) The baro. correction or reference selected is sent to each ADIRU via ;
    (a) The Master FMGC.
    (b) The FCU.
    (c) The RMPs.
    (d) The DMCs.
A

(b) The FCU.

62
Q
  1. (DSC-34-10) Each ADIRU receives two analogue inputs ; They are ;
    (a) Angle of attack (AOA) and total air temperature (TAT).
    (b) Angle of attack (AOA) and Baro correction or reference.
    (c) Total Air Temperature (TAT) and Baro correction or reference.
    (d) FMGC status and Baro correction or reference.
A

(a) Angle of attack (AOA) and total air temperature (TAT).

63
Q
  1. (DSC-34-10) In normal operation the ADIRUs are aligned using information from
    (a) The ADIRS CDU.
    (b) The CFDS.
    (c) The FCU.
    (d) The MCDU.
A

(d) The MCDU.

64
Q
  1. (DSC-34-10) If ADIRU 2 fails, the correct action is ;
    (a) Set ATT HDG and AIR DATA selectors to CAPT/3.
    (b) Set ATT HDG and AIR DATA selectors to F/O/3.
    (c) Set ATT HDG selectors to CAPT/3, AIR DATA selector to F/O/3.
    (d) Set ATT HDG selectors to F/O/3, AIR DATA selector to CAPT/3.
A

(b) Set ATT HDG and AIR DATA selectors to F/O/3.

65
Q
  1. (DSC-34-10) In normal operation ADIRU 1 supplies information to ;
    (a) The Captains PFD and the First Officers ND.
    (b) The Captains ND and the First Officers PFD.
    (c) The Captains PFD and ND.
    (d) The First Officers PFD and ND.
A

(c) The Captains PFD and ND.

66
Q
  1. (DSC-31-45) In Rose Nav mode with VOR 1 selected, the ND displays what VOR information :
    (a) Deviation Bar, selected course and the bearing pointer.
    (b) Bearing pointer only.
    (c) Deviation bar and selected course only.
    (d) Deviation bar and bearing pointer only.
A

(b) Bearing pointer only.

67
Q

67 (DSC-31-45) In Rose Ils mode, the ND displays what ils information :

(a) G/S and LOC scales.
(b) Deviation bar and selected course.
(c) Deviation bar, selected course and G/S scale.
(d) Deviation bar, selected course, G/S and LOC scales.

A

(d) Deviation bar, selected course, G/S and LOC scales.

68
Q
  1. (DSC-31-45) In the event of no ADF 1 reception, with ADF 1 selected on ND;
    (a) The bearing pointer goes out of view and ADF flag is displayed.
    (b) The bearing pointer goes out of view and station ID is replaced by red crosses.
    (c) The bearing pointer goes red and station ID is replaced by frequency.
    (d) The bearing pointer goes out of view and station ID is replaced by frequency.
A

(d) The bearing pointer goes out of view and station ID is replaced by frequency.

69
Q
  1. (DSC-31-45) In Rose Vor mode, in the event of VOR receiver failure ;
    (a) The VOR flag flashes red for nine seconds then remains steady.
    (b) The VOR flag becomes red and the course pointer rotates
    (c) The VOR flag flashes red for nine seconds then disappears
    (d) The VOR information flashes and the course pointer disappears.
A

(a) The VOR flag flashes red for nine seconds then remains steady.

70
Q
  1. (DSC-22-30) During Take-Off and Go-Around, The speed window on the FCU Displays ;
    (a) The speed manually inserted by the Crew into the FCU and the light is out.
    (b) The speed manually inserted by the crew into the MCDU and the light is illuminated.
    (c) Dashes and the light is illuminated ; Managed speed such as V2 or memorised Vapp are automatically used by the FMGS.
    (d) The target Vapp if the speed is managed for approach.
A

(c) Dashes and the light is illuminated ; Managed speed such as V2 or memorised Vapp are automatically used by the FMGS.

71
Q
  1. (DSC-22-30) The following AP/FD lateral modes are managed ;
    (a) NAV, HDG, APPR, LOC, RWY, RWY TRK.
    (b) HDG, NAV, APPR, LOC, GA TRK.
    (c) NAV, APPR, LOC, RWY, RWY TRK, GA TRK.
    (d) HDG, LOC, APPR.
A

(c) NAV, APPR, LOC, RWY, RWY TRK, GA TRK.

72
Q
  1. (DSC-22-30) In Approach, ‘LAND’ illuminates green on FMA when radio altitude is ;
    (a) 700 ft.
    (b) 400 ft.
    (c) 1,000 ft.
    (d) 200 ft.
A

(b) 400 ft.

73
Q
  1. (DSC-22-30) On the ground, the engagement of the autothrust function ;
    (a) Must be carried out manually by the crew before take off.
    (b) Is performed automatically upon the second engine start.
    (c) Is performed automatically at the engagement of the take off modes.
    (d) Is performed manually by pressing the A/THR buttons in the thrust levers.
A

(c) Is performed automatically at the engagement of the take off modes.

74
Q
  1. (DSC-22-30) Climbs and descents are always limited ;
    (a) By flight plan (T/C) and (T/D) points.
    (b) By the altitude manually selected on the FCU.
    (c) By the aircraft weight calculated by the FMGC.
    (d) By the CRZ altitude manually inserted on the MCDU.
A

(b) By the altitude manually selected on the FCU.

75
Q
  1. (DSC-22-20) In flight the FMGS position can be updated ;
    (a) Whenever a DME station is selected by the pilot.
    (b) Using data from the selected NDB, VOR or DME stations.
    (c) Automatically with the DMEs through the auto tuning function.
    (d) Using BRG/BRG information from two manually selected NDBs.
A

(c) Automatically with the DMEs through the auto tuning function.

76
Q

Why are the wind heading and arrow different?

A

Wind Heading is displayed in true while the arrow displays in magnetic.

77
Q

What does ADIRU 2 power?

A

FO PFD, ND and lower ECAM

78
Q

What are the 4 reasons fora IRS IN ALIGN memo?

A

M inute: 1 minute to alignment countdown but still not aligned

M easure: FROM airport is not current position

M emory: shutdown position different than present by 1 degree lat or long

M otion: when tugged during alignment, will restart alignment process in 10 minutes

79
Q

How many Ring Laser Gyros are on board?

A

9
1 per axis per IR

80
Q

What are the pilot inputs to the ADIRS?

A

Baro Reference Selectors

ADIRS Control and Display Unit (CDU)

(MCDUs) Multifunction Control and Display Units

81
Q

What does GPS PRIMARY mean?

A

GP-IRS position is accurate and used by FMS

82
Q

What are the inputs for ADIRU 2?

A

FO angle of attack

FO Total air temperature

FO pitot and static systems

Uses 3 ADMs

83
Q

How long does a fast realignment take and how do you accomplish?

A

30 seconds, Switch all ADIRS knobs to NAV - OFF - NAV

84
Q

What are the inputs for ADIRU 3?

A

Standby angle of attack

CA Total air temperature

Standby pitot (1) and static (2) systems

Uses 2 ADMs

85
Q

When is the only time the aircraft is navigated by a ground station?

A

When APPR is pressed for an ILS approach or LOC is pressed for a LOC approach

86
Q

How is GPS data calculated?

A

Through 2 Multi Mode Receivers (MMRs) which then send data to the ADIRUs. MMR1 =ADIRU1&3 MMR2=ADIRU2

87
Q

What is the MMR hierarchy?

A

On-side position

ADIRU3 position

Off-side position

88
Q

What are the inputs for ADIRU 1?

A

CA angle of attack

CA Total air temperature

CA pitot and static systems

Uses 3 ADMs

89
Q

How many accelerometers are on board?

A

9
1 per axis per IR

90
Q

How is MIX IRS re-calibrated in-flight?

A

While in flight using MIX IRS position, FMS recalculates position based on DME/DME or VOR/DME and applies the BIAS to the FMS position. The MIX IRS position is never changed only the FMS position.

91
Q

When GPS is lost and FMS is working off MIX IRS, what realignment take place during takeoff.

A

During takeoff, the FMS knows the location of the runway threshold and corrects the MIX IRS position when TOGO power is applied.

92
Q

When GPS is lost how is position information calculated?

A

After alignment, the 3 independent IRs calculate present position. The FMS then take the average as the MIX IRS position.

93
Q

What are the portions of the (ADIRUs) Air Data and Inertial Reference Units?

A

(ADR) Air Data Reference :
-Pitot/Static info

(IR) Inertial Reference:

  • Gyro type info (attitude and heading)
  • position
94
Q

How does ADIRS calculate present position (PPOS)?

A

Calculated hybrid position using GPS and IRS positions

IRS position only if GPS fails

Radio Navigation

Internal NAV Database

95
Q

What systems use the ADIRS data?

A

(EIS) Electronic Instrument System
(FMS)
Engine computers
Flight Control computers
Warning Computers

96
Q

What does ADIRU 1 power?

A

CA PFD, ND and upper ECAM

97
Q

What does the IR (Inertial Reference) supply data to ?

A

Airspeed trend

Attitude Indicator and BEta Target (slip/skid)

Instant VSI

Heading

All ND info (except TAS)

G load meter

98
Q

What does the AD (Air Data) supply data to ?

A

Airspeed

Altitude

Backup VSI (amber boarder around VSI)

TAS

Total Air Temp (TAT) and Saturated Air Temp (SAT)

99
Q

What does ADIRS consist of?

A

3 separate (ADIRUs) Air Data and Inertial Reference Units

4. Systems (19 decks)

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