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Q400 > Flight Instruments > Flashcards

Flight Instruments Flashcards

1
Q

What is FDPS?

A

Flight Data Processing system

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2
Q

The Electronic Instrument System (EIS) displays what data?

A

Primary flight data incl.
airspeed
Altitude
Attitude
Heading
IVSI
NAV
Eng
System messages

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3
Q

What screens does the 400 have?

A

PFD 1 & 2 primary flight display
MFD 1 & 2 multi function display
ED engine display

They are all LCD screens

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4
Q

The EIS consists of?

A

EFIS and ESID (engine system and integrated display)

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5
Q

What is powered with only the battery master switch on?

A

MFD 1
ED
MFD 1 reversion selector and ALL push button

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6
Q

With main and Aus batteries on what is powered?

A

PFD1 & 2
MFD 2
MFD 2 reversion selector
And all other push buttons

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7
Q

Besides navigation data what else can the MFD be used to display?

A

Aircraft systems pages including electrical, engine, fuel and doors

Use the MFD knob in the Sys position

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8
Q

MFD 1 permanent system area (PSA) for what?

A

PFCS powered flight control surfaces

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9
Q

MFD 2 Permanent system area for?

A

Flap position and hydraulic info

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10
Q

What does composite PSA display mode do?

A

When only one MFD available then the other MFD will show all permanent system display (incl flaps, hyd and PFCS)

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11
Q

What happens in reversion?

A

The MFD functions as backups for PFDs and the ED and can show their data on the MFD

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12
Q

What do you use to control the speed bugs, altimeter setting and DH or MDA?

A

Index control panel (ICP)

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13
Q

ADC 1 & 2 receive inputs from?

A

Two pitot statics and air temp probe

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14
Q

What do you see when IAS failure?

A

Speed tape numbers removed and ‘IAS FAIL’ can be seen

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15
Q

What does the ADC test switch do and how often must it be done?

A

Daily and it checks VMO warning tone and interfaces

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16
Q

If one ADC fails what happens?

A

Manual ADC reversion is necessary

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17
Q

What is the pitot isolation valve switch for?

A

To isolate the damaged pitot tube to allow the air data instruments to function

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18
Q

IVSI FAIL message caused by?

A

Failure if worthy AHRS or ADC

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19
Q

If both AHRS and ADC fail what happens?

A

No altitude info is available ‘ALT FAIL’

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20
Q

What data is shown on the integrated standby instrument (ISI)?

A

Attitude
Altitude
Airspeed

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21
Q

What is the ISI powered by?

A

Switched battery power bus

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22
Q

What is the ISI connected to?

A

Independent of the ADC and is connected to the standby pitot static probe located on the right side of the fuselage

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23
Q

What is the standby pitot Static probe heated by?

A

Right 28V DC essential bus

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24
Q

What happens when 1 or 2 RAD Alts fail?

A

If one fails the other one will still provide data on the PFD
If two fails there will be dashed red lines where the altitude would have shown on the PFD

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25
Q

What is the clocks power source?

A

Battery bus

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26
Q

Number 1 clock provides info to?

A

The CVR

27
Q

Which clock supplies the FDR?

A

Both clocks

28
Q

If the number 1 clock fails then what happens to the CVR?

A

It’ll use the number 2 clock

29
Q

How many avionics cooling fans are there?

A

3
Capt side
FO side
Standby fan

30
Q

Avionics cooling fans power?

A

Fan 1 and 2 on battery power bus
Fan 3 standby does not operate on battery power

31
Q

The indicated airspeed value is RED when VMO has been exceeded, it changes to white when airspeed is ?

A

VMO - 2

32
Q

When the PITOT STATIC ISOLATION VALVE is selected to ISOL ?

A

ADC1 receives static pressure information from pitot static probe 1

33
Q

On the ground an AHRS alignment takes approximately ?

A

60 seconds

34
Q

On the AHRS control panel (AHCP) the red SLAVE annunciator indicates ?

A

The magnetic information from the flux valve has failed

35
Q

The Minimum Descent Altitude (MDA) for an approach is set ?

A

Individually on each Index Control Panel (ICP)

36
Q

The message PITCH MISMATCH on the PFD indicates ?

A

A pitch attitude mismatch of 3 degrees of more between PFDs

37
Q

In the directional gyro mode, the EHSI heading can be corrected ?

A

Manually with the DG SLEW push buttons

38
Q

The Integrated Standby Instrument (ISI) is powered by ?

A

The switched battery power bus

39
Q

The SAT value on the Engine Display (ED) is provided by ?

A

ADC 1

40
Q

The electronic instrument system uses colour to convey information. WHITE is used for ?

A

Advisories

41
Q

Engine and aircraft system parameters are normally presented on which displays?

A

ED and both MFDs

42
Q

With both MFDs displaying the NAV page, pushing and holding the ELEC SYS page ?

A

Will display the electrical system page on the ED

43
Q

With only the battery master switch selected ON which displays are powered?

A

MFD1 and ED

44
Q

When the Engine Display (ED) fails during flight, the ED ?

A

Is automatically transferred to MFD1

45
Q

The Powered Flight Control Surfaces (PFCS) information is normally displayed ?

A

On MFD1

46
Q

The electronic instrument system uses colour to convey information. CYAN is used for ?

A

Selectable parameters

47
Q

The Permanent System Area (PSA) is normally displayed ?

A

At the bottom of each MFD

48
Q

The Permanent System Area (PSA) display is available on an MFD when it is set to display ?

A

NAV or SYS

49
Q

The air data system converts static and pitot pressure to an electronic format for use ?

A

All of the above

50
Q

The AHRUs use?

A

laser vertical and directional gyroscopes, and accelerometers, to sense aircraft movement. The information from the gyros and accelerometers is
converted into pitch, roll, and heading information.

51
Q

If a pitch and roll
mismatch condition occur at the same time, which one has a higher priority?

A

pitch mismatch message will be shown. It has a higher indication priority than the roll mismatch message.

52
Q

In case of attitude data failure what happens ?

A

all attitude data is removed and replaced with an ATT FAIL flag.

53
Q

How can the AHRS be aligned ?

A

Pressing the individual ATT/HDG align annunciator switch.

54
Q

If the true airspeed information from an ADC is unreliable, what do you do ?

A

manual reversion is required to supply true airspeed to the AHRU.
Manual reversion is achieved by using the
EFIS ADC Source
Selection Switch on the
ESID Control panel.

55
Q

While True Airspeed information is not being provided by the ADC, the associated AHRU does what ?

A

automatically transitions to the basic attitude mode. In this mode, the associated EADI functions like a conventional mechanically gimbaled attitude indicator. When this happens, the green BASIC annunciator light on the associated AHCP illuminates.

56
Q

The AHRU monitors the
MDU. A heading failure flag is displayed when what occurs ?

A

the magnetic heading information from the MDU has failed.

57
Q

slaved mode is indicated by the EHSI being replaced by a red HDG FAIL message and the illumination of a red
SLAVE annunciation on the AHRS Control Panel.
The condition is cleared by?

A

pressing the
Directional Gyro (DG) pustbutton on the AHRS
Control Panel.

58
Q

In the DG mode, the heading is corrected manually by ?

A

by using the plus or minus DG Slew pushbuttons on the AHRS Control Panels.

59
Q

When will you get a HDG mis match ?

A

This indicates the two inertial sources are providing heading values differing by at least 8 degrees.

60
Q

When the aircraft is at the selected DH what do you see ?

A

A yellow DH alert annunciation on the attitude sphere flashes for 3 seconds then goes steady.

61
Q

The GPWS triggers a “Minimums” aural alert if the DH is ? .

A

is greater than 50 ft

62
Q

What’s
AHRS
ADC
SPM
FGM
EIS
EADI
EHSI
IVSI
ICP
FDPS
DU
ESID

A

Attitude heading reference system
Air data computer
Stall protection module
Flight guidance module
Electronic instrument system
Electronic attitude directional indicator
Electronic Horizontal situational indicator
Instantaneous vertical speed indicator
Display unit
Engine and system integrated display

63
Q

The electronic instrument system uses reverse video for 5 seconds on messages that ?

A

When a change in operating state occurs not initiated by the crew.

Q400 (33 decks)

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