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A330 Systems > Indicating and Recording > Flashcards

Indicating and Recording Flashcards

1
Q
  1. The Flight Warning Computers (FWCs) acquire data to generate:

a. Alert messages, aural alerts, red warnings and amber caution, synthetic voice messages.

b. The display on system pages and engine/warning pages.

c. Only red warnings

A

a. Alert messages, aural alerts, red warnings and amber caution, synthetic voice messages.

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2
Q
  1. Which one of the following statements is true?

a. 3 Display Management Computers (DMCs) generate the alert messages and the red warnings.

b. 3 DMCs generate the images displayed on CRTs.

c. 3 DMCs are used to collect Aircraft data sensors information.

A

b. 3 DMCs generate the images displayed on CRTs.

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3
Q
  1. In normal operation:

a. DMC1 and DMC2 supply information to PFDs, NDs and ECAM.

b. DMC3 (ECAM part) supplies information to upper and lower ECAM.

c. DMC1 and 2 supply information to PFDs only, DMC3 supplies information to NDs and upper and lower ECAM.

A

b. DMC3 (ECAM part) supplies information to upper and lower ECAM.

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4
Q
  1. The APU BAT pb is blank. This indicates:

a. the system is operating normally

b. the system pb needs to be pushed

c. the corresponding system is deactivated

A

a. the system is operating normally

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5
Q
  1. The APU BAT pb shows amber FAULT light. This pb indicate:

a. the system is operating normally

b. there is a failure in the corresponding system

c. the corresponding system is deactivated

A

b. there is a failure in the corresponding system

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6
Q
  1. When the blue ON light on the external power A pb is illuminated:

a. the pb is in an abnormal position

b. you need to be aware of a failure in the system

c. the temporarily used system is operating normally

A

c. the temporarily used system is operating normally

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7
Q
  1. What is the function of (SDACs) System Data Acquisition Concentrators?

a. to generate displays to be sent to the various display units

b. to generate all visual and aural warnings

c. to supply information to the FWCs for warning calculations and data to the DMCs to be displayed

A

c. to supply information to the FWCs for warning calculations and data to the DMCs to be displayed

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8
Q
  1. Aural alerts and voice messages are transmitted:

a. only through the pilot’s headsets

b. through the loudspeakers even if the speakers are switch off

c. through the loudspeakers only if the speakers are switch on

A

b. through the loudspeakers even if the speakers are switch off

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9
Q
  1. In case of DU failure:

a. ECAM data cannot be transferred to another DU. The data is lost.

b. The information can be transferred to another DU to be displayed.

c. ND or PFD data cannot be transferred to another DU. The data is lost.

A

b. The information can be transferred to another DU to be displayed.

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10
Q
  1. Where is the PFD normally located on the instrument panel?

a. One PFD is located in front of each pilot on the inner display unit

b. One PFD is located in front of each pilot on the outer display unit

c. One PFD is located on the center Display unit for both pilots

A

b. One PFD is located in front of each pilot on the outer display unit

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11
Q
  1. The FMA displays:

a. annunciations and messages regarding FMGS operations

b. annunciations and messages regarding trajectory deviation

c. flags telling you which PFD information is lost

A

a. annunciations and messages regarding FMGS operations

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12
Q
  1. These green symbols = and \ indicate:

a. the maximum pitch and roll angles in normal flight control law

b. the maximum side stick deflection in normal flight control law

c. the maximum pitch and roll angles in all flight control laws

A

a. the maximum pitch and roll angles in normal flight control law

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13
Q
  1. When the Blue “TRU” appears above the heading display:

a. it signifies that the aircraft will be changing from the true to magnetic reference

b. automatically at high latitudes to signify that magnetic heading is replaced by true heading

c. only when you push the NORTH REF pb to TRUE

A

c. only when you push the NORTH REF pb to TRUE

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14
Q
  1. On the ND when in ROSE NAV, the data in the right corner reflects:

a. Waypoint/Track, distance, time to destination

b. Waypoint/Bearing-to-go, distance, ETA at the next waypoint

c. Waypoint/Frequency, DME distance, ETA

A

b. Waypoint/Bearing-to-go, distance, ETA at the next waypoint

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15
Q
  1. On the ND, the aircraft TO WAYPOINT is LMG. After LMG a solid green line is connected
    to AMB then to CND. Also another waypoint LCA is connected from LMG using a dashed yellow line. According to this, LCA is a waypoint:

a. on the active flight plan

b. on the temporary flight plan

c. on the secondary flight plan

A

b. on the temporary flight plan

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16
Q
  1. On ND, when a red G/S flag is displayed in the middle-right hand side, it indicates:

a. All glide slope information has been lost

b. There is discrepancy between the Captain’s and First Officer’s glide slope indication.

c. There is a discrepancy between data received by the DMC and data being displayed.

A

a. All glide slope information has been lost

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17
Q
  1. On the ND, when an amber flag CHECK HDG is displayed:

a. there is a discrepancy between the ND mode displayed and the mode chosen on the EFIS control panel

b. the FWC has detected a difference between the Captain’s and First Officer’s heading

c. all ND information is lost

A

b. the FWC has detected a difference between the Captain’s and First Officer’s heading

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18
Q
  1. A red ND flag reading “VOR”

a. the ROSE VOR bearing is not valid

b. you have to check VOR frequency

c. there is a failure of a navigation receiver

A

a. the ROSE VOR bearing is not valid

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19
Q
  1. Which type of information is represented on the lower part of the E/WD?

a. Memo messages

b. Permanent data

c. The fuel on board and flats/flaps position

A

a. Memo messages

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20
Q
  1. A magenta memo message “TO INHIBIT” in the E/WD indicates:

a. the take off should be aborted

b. all warnings will be generated when required

c. all warnings are inhibited except those that could result in an aborted take off

A

c. all warnings are inhibited except those that could result in an aborted take off

21
Q
  1. Permanent data such as GW, SAT, TAT and etc. are displayed on:

a. The upper part of the Systems Display

b. The lower part of the System Display

c. The lower part of the E/WD

A

b. The lower part of the System Display

22
Q
  1. ECAM procedure “GREEN ENG 1….PUMP OFF” in blue, is displayed due to GREEN RSVR LO AIR PRESS. According to this ECAM indications:

a. the hydraulic system is operating normally

b. the failure is affecting flight safety

c. the blue statement on the ECAM requires pilot action to turn off the green engine 1 pump

A

c. the blue statement on the ECAM requires pilot action to turn off the green engine 1 pump

23
Q
  1. In emergency electrical configuration:

a. both PFD are available

b. CPT’s PFD and ND are available

c. CPT’s PFD and F/O’s ND are available

A

b. CPT’s PFD and ND are available

24
Q
  1. An amber PFD flag reading “CHECK ALT” indicates:

a. a discrepancy of the altitude information of the two PFDs

b. a failure of this PFD altitude data only

c. altitude data is not available

A

a. a discrepancy of the altitude information of the two PFDs

25
Q
  1. Amber ECAM message “APU AUTO SHUT DOWN”, amber Master Caution light and a single chime means:

a. you need to take immediate action

b. the only effect is a loss of redundancy of system degradation

c. you need to be aware of the failure, but it does not directly affect flight safety

A

c. you need to be aware of the failure, but it does not directly affect flight safety

26
Q
  1. A red ECAM message “ENGINE 2 FIRE”, red Master Warning light and a continuous repetitive chime indicates:

a. you need to take immediate action

b. this failure does not require immediate action

c. this failure does not require any action on your part

A

a. you need to take immediate action

27
Q
  1. When will you see the F/CTL ECAM page displayed?

a. During engine start

b. Only when you push the Flight Control Pushbutton on the ECAM Control Panel

c. Automatically during the flight control check when the sidestick or rudder is moved

A

c. Automatically during the flight control check when the sidestick or rudder is moved

28
Q
  1. During normal operations:

a. an ECAM page is automatically displayed for the corresponding flight phase

b. you need to press a key on the ECAM Control Panel to display the ECAM page for that flight phase

c. you need to press the ENG key to display the Engine page during an engine start

A

a. an ECAM page is automatically displayed for the corresponding flight phase

29
Q
  1. Which statements is true about the use of the ALL key on the ECAM Control Panel?

a. when you press the ALL key, you cannot stop at a particular systems page until all have been displayed

b. when you press the ALL key, all the systems pages in succession

c. the ALL key is not operable in case of failure of the ECAM Control Panel

A

b. when you press the ALL key, all the systems pages in succession

30
Q
  1. What action must the crew perform in case of DMC 1 fault?

a. Nothing, the transfer to the other DMC is automatically done

b. The pilot must transfer to EFIS DMC3

c. The pilot must transfer to EFIS DMC2

A

b. The pilot must transfer to EFIS DMC3

31
Q
  1. What happens, when a discrepancy between the signal sent to the E/WD and the feedback signal is detected?

a. A “CHECK E/WD” message appears on the upper ECAM and on the ND

b. A “CHECK E/WD” message appears on the upper and lower ECAM

c. ECAM operation is not affected is not affected because there are 3 identical FWCs

A

a. A “CHECK E/WD” message appears on the upper ECAM and on the ND

32
Q
  1. In case of FWC1 fault:

a. a message “FWC fault” appears on the upper ECAM

b. a message “FWC fault” appears on the upper and lower ECAM

c. ECAM operation is not affected because there are 2 identical FWCs

A

c. ECAM operation is not affected because there are 2 identical FWCs

33
Q
  1. The system page automatically displayed on ECAM during TAXI is:

a. DOOR/OXY

b. FLIGHT CONTROLS

c. WHEEL

A

c. WHEEL

34
Q
  1. DMC 1 normally processes:

a. CAPT PFD, CAPT ND and E/WD display

b. CAPT PFD, CAPT ND

c. F/O PFD, F/O ND and E/WD display

A

b. CAPT PFD, CAPT ND

35
Q
  1. DMC 2 normally processes:

a. CAPT, PFD, CAPT ND

b. F/O PFD, F/O ND

c. CAPT PFD, CAPT ND and E/W display

A

b. F/O PFD, F/O ND

36
Q
  1. When the upper ECAM OFF/BRT knob is rotated to OFF:

a. the STATUS page is being displayed on the Upper ECAM

b. no STATUS message can be displayed in this configuration

c. the STATUS page is being displayed when the STS pb is pushed and held

A

c. the STATUS page is being displayed when the STS pb is pushed and held

37
Q
  1. All ECAM DUs are normal and the STS white light on the ECAM control panel is illuminated:

a. you need to push the STS pb to display the ECAM STATUS page

b. the only way to clear the STATUS page is to push the STS pb

c. the STATUS page is being displayed on the lower ECAM

A

c. the STATUS page is being displayed on the lower ECAM

38
Q
  1. In the ECAM DMC SWITCHING panel, the selector is in AUTO position:

a. DMC 3 is supplying data to both ECAM DUs

b. If DMC 3 fails, you will have no display on either ECAM DU

c. DMC 2 is replacing DMC 3

A

a. DMC 3 is supplying data to both ECAM DUs

39
Q
  1. An illuminated green light in the LS pushbutton on the EFIS control panel indicates:

a. STD Baro reference has been selected

b. the glideslope and localizer scales are displayed on the PFD

c. optimal waypoint data is displayed on the ND

A

b. the glideslope and localizer scales are displayed on the PFD

40
Q
  1. The ECAM DMC rotary selector is in “AUTO”. When failure of the DMC 3 is detected, what will process the ECAM displays?

a. DMC 1

b. DMC 2

c. DMC 3

A

a. DMC 1

41
Q
  1. What effect does the ECAM DMC rotary selector have on EFIS displays?

a. it has no effect on the EFIS displays

b. it enables the PFD and ND images to be interchanged

c. it enables an ECAM image to be displayed on CAPT or F/O ND

A

a. it has no effect on the EFIS displays

42
Q
  1. Which computer generates all aural warnings signal (except GPWS warnings) annunciated in the cockpit?

a. DMC

b. SDAC

c. FWC

A

c. FWC

43
Q
  1. The boxed STS reminder on the E/WD display indicates:

a. a message is present on the status page

b. a message is present on the system page

c. the present status of the display unit is faulty

A

a. a message is present on the status page

44
Q
  1. What information is permanently displayed on the upper part of the E/WD?

a. engine parameters, fuel quantity, slats and flaps position

b. engine parameters, fuel quantity and memo messages

c. engine parameters, fuel quantity, warnings and caution messages

A

a. engine parameters, fuel quantity, slats and flaps position

45
Q
  1. The LDG memo will appear below:

a. 500 ft
b. 800 ft
c. 2,000 ft

A

c. 2,000 ft

46
Q
  1. The T.O memo is displayed automatically 2 min. after the second engine start or:

a. 2 minutes after doors are closed

b. 2 minutes after slats and flaps extension

c. when the T.O. config test pb is pressed provided at least 1 engine is running

A

c. when the T.O. config test pb is pressed provided at least 1 engine is running

47
Q
  1. The green lines on the overhead panels connected along switches show:

a. current electrical/fluid flow directions

b. current fluid flow during abnormal operations

c. basic system architecture

A

c. basic system architecture

48
Q
  1. If the ECAM control panel fails, how can the pilot view a particular system page?

a. hold the “ALL” button down until the page of interest comes up and then release the
button

b. hold the STS button down until the page of interest comes up then release the button

c. hold the RCL button down until the page of interest comes up and then release the button

A

a. hold the “ALL” button down until the page of interest comes up and then release the button

A330 Systems (17 decks)

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