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CRJ 700 ENY STUDY GUIDE > Warnings & Alerts > Flashcards

Warnings & Alerts Flashcards

1
Q

What is the function of the Engine Indicating and Crew Alerting System (EICAS)?

A

The function of the EICAS is to display the engine instruments, visual and aural crew-alerting messages and real time interpretation of aircraft system operation.

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2
Q

What is the function of the Primary Flight Display (PFD)?

A

To present the Attitude Direction Indicator and Horizontal Situation Indicator on one screen

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3
Q

What is the function of the Multi-Function Display (MFD)?

A
  • To present HSI and map display data on selectable navigation formats
  • To act as a reversionary display if the PFD or EICAS display fails
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4
Q

Which multi-function display (MFD) formats cannot present weather radar information?

A

HSI format & FMS Plan Map format.

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5
Q

Why are the EICAS Displays (ED1 and ED2) limited to 5 minutes of operation when on the ground with battery power only?

A

Why are the EICAS Displays (ED1 and ED2) limited to 5 minutes of operation when on the ground with battery power only?

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6
Q

What does a DISPLAY TEMP warning on the MFD indicate?

A

This message is displayed on the radar line of the MFD when the display temperature is excessive. When the message is displayed, all information is removed.

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7
Q

What are the four levels of Crew Alerting System (CAS) messages?

A

Warning (red), Caution (amber), Advisory (green), Status (white).

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8
Q

What is the function of the GND ALTN position of the display cooling fan (DSPLY FAN)?

A

On the ground, if the fan fails, moving the switch from NORM to GND ALTN activates the fan normally used in flight.

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9
Q

What is the function of the NORM position of the display cooling fan (DSPLY FAN)?

A

The norm position indicates that the appropriate display fan is activated for either flight or ground operations.

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10
Q

What is the function of the FLT ALTN position of the display cooling fan (DSPLY FAN)?

A

In flight, if the fan fails, moving the switch from NORM to FLT ALTN activates the fan normally used on the ground.

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11
Q

What is the function of the STDBY position of the display cooling fan (DSPLY fan)?

A

If both fans fail, selecting the STDBY removes power from both of the display fans and allows air from the cockpit air conditioning duct to cool the CRT’s.

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12
Q

What page does EICAS Display (ED) 1 display by default?

A

The primary page.

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13
Q

What page does EICAS Display (ED) 2 display by default?

A

The status page.

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14
Q

What will occur after a failure of EICAS Display (ED) 1?

A

EICAS Display 2 will automatically default to the primary page and the failure renders the EICAS Control Panel (ECP) inactive.

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15
Q

What will occur after a failure of EICAS Display (ED) 2?

A

EICAS Display 1 will display the primary page (no change) and the EICAS Control Panel is rendered inactive. There is no automatic transfer of information should EICAS Display 2 fail.

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16
Q

How can the status page be displayed after the failure of EICAS Display (ED) 2?

A
  • Display Reversionary Panel – select to the EICAS position and the associated MFD displays EICAS data (defaults to the status page) and the EICAS Control Panel (ECP) is enabled which gains control over that display.
  • Source Selection Panel (SSP) – select the EICAS display rotary selector to the ED 1 position and the EICAS Control Panel (ECP) gains control over the remaining EICAS display.
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17
Q

How can the status page be displayed after the failure of EICAS display (ED) 1?

A
  • Display reversionary panel – select to the EICAS position and the associated MFD displays EICAS data (defaults to the status page) and the EICAS Control Panel (ECP) is enabled which gains control over that display.
  • Source Selection Panel (SSP) – select the EICAS display rotary selector to the ED 2 position and the EICAS Control Panel (ECP) gains control over the remaining EICAS display.
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18
Q

How can EICAS Display (ED) 1 present all synoptic pages associated with the EICAS Control Panel (ECP)?

A

Source selection panel (SSP) – select the EICAS display (ED) knob to the ED 1 position and the EICAS Control Panel (ECP) gains control over ED 1.

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19
Q

What is the function of the Data Concentrator Units (DCU)?

A

The DCU collects data from various aircraft systems, processes the information and relays it to the proper component or display (EICAS displays, lamp driver unit, maintenance diagnostic unit & flight data recorder).

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20
Q

If a data concentrator unit (DCU) fails, are any aural warning functions lost?

A

System redundancy ensures that no displayed data is lost with a single DCU failure.

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21
Q

What is the function of the Lamp Driver Unit?

A

It receives information from the DCU’s and controls the panel and glareshield switchlight illumination

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22
Q

What is the function of the audio warning DISABLE switchlights (DCU 1DISABLE / DCU 2 DISABLE) located on the audio warning panel?

A

The switches are used to disable and silence the aural warnings of a malfunctioning Data Concentrator Unit (DCU).

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23
Q

What will occur if both DCU1 and DCU 2 DISABLE switchlights are selected to DISABLE?

A

Selection of both switches will disable all EICAS aural warnings.

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24
Q

What aural warnings are not disabled by the audio warning DISABLE switchlights?

A

EGPWS and TCAS aural warnings are not disabled.

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25
Q

What is the function of the EICAS Control Panel (ECP)?

A

The ECP has dedicated momentary contact buttons for control of the information displayed on the EICAS.

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26
Q

Which buttons remain operational with an EICAS Control Panel (ECP) microprocessor failure?

A

The four mechanical buttons that will operate are the PRI (primary), STAT (status), CAS (crew alerting system) & STEP buttons.

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27
Q

What will occur if the status page is displaying status messages and the STAT button is pressed?

A

Selecting the STAT button will remove (“box”) the status messages from the status page and display a white MSGS icon. The STAT button also allow the pilots to page forward and backward to view the entire list of status messages if the total number exceeds the presentation limit of the status page.

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28
Q

What will occur if a new status message occurs with a white MSGS icon present?

A

DCU generation of a new status message will remove the MSGS icon, and the most recent status message will be displayed on the top of the status message stack.

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29
Q

How can the pilot manually “un-box” the status messages?

A

After ”boxing” the status messages with a single press of the STAT button, pressing the STAT button a second time will “un-box” (remove the MSGS icon) the status messages.

30
Q

What is the indication that more than one page of status messages exists?

A

A “boxed” PAGE 1/2 is displayed at the bottom of the message list to indicate that another page of messages exists. At the end of a message list, PAGE 2/2 is displayed.

31
Q

How can the pilot scroll to a second page of status messages?

A

By pressing the STAT button a second time.

32
Q

What will occur if the primary page is displaying caution messages and the CAS button is pressed?

A

Selecting the CAS button will remove (“box”) the caution messages from the primary page and display a white MSGS icon in flight or on the ground if the engines are stabilized at idle.

33
Q

What will occur if a new caution message occurs with a white MSGS icon present?

A

DCU generation of a new caution message will remove the MSGS icon and the most recent caution message will be displayed on the top of the caution message stack.

34
Q

How can the pilot manually “un-box” the caution messages?

A

After “boxing” the caution messages with a press of the CAS button, pressing the CAS button a second time will “un-box” (remove the MSGS icon) the caution messages.

35
Q

What is the indication that more than one page of caution messages exists?

A

A “boxed” PAGE 1/2 is displayed at the bottom of the message list to indicate that another page of messages exists. At the end of a message list, PAGE 2/2 is displayed.

36
Q

How can the pilot scroll to a second page of caution messages?

A

By pressing the CAS button a second time.

37
Q

What is the function of the STEP button located on the EICAS Control Panel (ECP)?

A

The STEP button sequentially steps through all available pages, starting at the page currently selected and moves left to right as labeled on the EICAS Control Panel (ECP).

38
Q

What is the function of the synoptic pages?

A

Synoptic pages are simplified top-level schematic diagrams used for pilot and maintenance information. The synoptic pages are dynamic displays of aircraft systems status and operation.

39
Q

What information can be set or checked from the menu page?

A
  • Inserting the N1 reference for display on the primary page
  • Fuel used reset
  • Engine oil quanity
40
Q

What occurs between the oil pressure and N1 vibration gauges after a normal engine start while on the ground?

A

After the engine start, when both engines are stabilized at idle and engine oil pressures are normal, the EICAS logic replaces the oil pressure analogue gauges with N1 fan vibration gauges.

41
Q

Where do the Automatic Performance Reserve (APR) and reverse thrust (REV) icons normally appear when their respective systems are activated?

A

In the center of the N1 analogue indicator.

42
Q

Where does the N2 vibration icon appear if the parameters exceed the predetermined value?

A

In the center of the N2 analogue indicator.

43
Q

What occurs to the N2 gauges when the wing anti-icing is selected on?

A

White arcs are displayed on the N2 gauges between 0%-77%. The arcs remind the pilots that N2 core speed should be kept at a high rpm when the wing anti-ice is on to ensure an adequate flow of bleed air from the engine.

44
Q

When will the landing gear, slat/flap and brake temperature information be displayed on the primary & status pages?

A

When the slats are greater than zero degrees, gear is selected down or brake temperature exceeds normal limits.

45
Q

When is the landing gear, slat/flap and brake temperature information removed from the primary & status page?

A

Slats are up, landing gear is up & locked and the brake temperatures are normal (green).

46
Q

When are the APU analogue and digital RPM & EGT gauges presented on the status page?

A

When the APU Power Fuel (PWR FUEL) switchlight is selected on.

47
Q

What is the function of an advisory message?

A

They are used to advise of aircraft configuration for a particular phase of flight, successful system test or confirmation of shutoff valve (SOV) closure.

48
Q

What is the function of a status message?

A

Status messages are used to indicate status of a specific system that has been manually or automatically activated or to identify a low-priority failure.

49
Q

What is the function of the NORM position on the Display Reversionary Panel?

A

When the norm position is selected, the MFD is configured to act as a multi-function display (MFD).

50
Q

What occurs when the Display Reversionary Selector is set to the EICAS position?

A

When the EICAS position is selected, the MFD is reconfigured to act as an EICAS display and the status page is presented as the default page. The ECP is now functional and can be used to view synoptic or other EICAS pages.

51
Q

What occurs when the Display Reversionary Selector is set to the PFD position?

A

When the PFD position is selected, the MFD is configured to act as a primary flight display (PFD).

52
Q

What is the function of the Maintenance Diagnostic Computer (MDC)?

A

The MDC is an onboard computer that is used to record mechanical and avionics system data that maintenance personnel can retrieve for use in engine trend analysis computation, significant event recording and for avionics/aircraft system failure detection.

53
Q

What is the function of the takeoff configuration warning system?

A

The takeoff configuration system monitors the position of the flaps, flight spoilers, parking brake, autopilot, aileron, rudder and horizontal stabilizer trims, to ensure that they are in a safe configuration for takeoff.

54
Q

What is displayed in the cockpit when the aircraft is in a safe takeoff configuration?

A

Green advisory message “T/O CONFIG OK” displayed on the status page.

55
Q

What are the requirements to obtain a TAKEOFF CONFIG OK Status Message?

A
  • Flaps at 8 or 20 degrees
  • Flight Spoilers stowed
  • Parking Brake OFF
  • Autopilot Disengaged
  • Trims in the green
56
Q

How can the pilots interrupt an inadvertent stick pusher activation?

A

By pressing the AP/SP disc switch on either yoke.

57
Q

What is the function of the Enhanced Ground Proximity Warning System (EGPWS)?

A

The EGPWS supplies visual and aural alerts related to ground (terrain) clearance, sink rate, glideslope error, flap setting and windshear conditions. The EGPWS also supplies aural indications of specified radio altitudes (RA) and bank angle limits.

58
Q

What does the EGPWS terrain clearance floor (TCF) database include?

A

The TCF data provides worldwide coverage of all airports with runways longer than 3500 feet. The TCF provides an increasing terrain clearance protection zone around the center point of the nearest airport runway.

59
Q

What is the purpose of the EGPWS auto alert function?

A

When a conflicting terrain or obstacle is detected, the terrain overlay automatically pops up on the MFD and the display range is set to 10 miles.

60
Q

When is the EGPWS audio message “Caution Terrain” or “Caution Obstacle” generated?

A

The GND PROX switchlight flashes on the glareshield, and the conflicting terrain or obstacle is shown on the MFD as a solid yellow color with approximately 60 seconds to impact.

61
Q

What is the purpose of the TERRAIN and FLAP OVRD switchlights on the GND PROX / MECH Call Control Panel?

A

To disable the Terrain or Flap warning functions of the EGPWS

62
Q

When is the EGPWS audio message “Terrain Terrain, Pull Up” or “Obstacle Obstacle, Pull Up” generated?

A

The GND PROX switchlight flashes on the glareshield and the conflicting terrain or obstacle is shown on the MFD as a solid red color with approximately 30 seconds to impact.

63
Q

How is the detection of an increasing performance windshear displayed (indicated) to the pilots?

A

An amber WINDSHEAR message and Alpha Margin Indicator (AMI) appears on the PFD’s.

64
Q

How is the detection of a decreasing performance windshear displayed (indicated) to the pilots?

A

The EGPWS computer sounds the audio warning “Windshear, Windshear, Windshear”. The red message WINDSHEAR and the amber Alpha Margin Indicator appears on the PFD’s. The flight director bars will automatically provide escape guidance when a windshear warning occurs.

65
Q

What is the function of the Alpha Margin Indicator (AMI)?

A

It is a visual representation of stick shaker activation.

66
Q

When is the Alpha Margin Indicator (AMI) displayed on the primary flight display (PFD)?

A

Only during windshear events.

67
Q

Where is the weather display presented in the cockpit?

A

Weather radar can be presented on both MFDs at the same time. The MFD presentations can be operated at different ranges and antenna tilt elevations.

68
Q

What is a functional weather radar test?

A

When the test mode is selected, the radar system completes a self-test of the internal components and antenna operation. The transmitter does not transmit. The multi-function display (MFD) radar test pattern consists of six equally-spaced colored bands.

69
Q

What is the function of auto tilt?

A

When auto tilt is on and a different range is selected or the aircraft changes altitude, the system automatically tilts the antenna to maintain the same relationship between the beam deflection and the display.

70
Q

What is the function of the sector scan button (SEC) located on the radar control panel (RCP)?

A

It allows the pilots to adjust the radar scan from +/- 60 (120 maximum) degrees each side of the aircraft nose or +/- 30 (60 maximum) degrees either side.

71
Q

What is the function of the transfer control (XFR) button located on the radar control panel (RCP)?

A

In normal operations the left sweep of the radar antenna is displayed on the left MFD and the right sweep is displayed on the right MFD. Should a radar control panel fail, the XFR switch is used to transfer all radar control to the other radar control panel. The operational radar control will then use both the left & right sweeps. When in XFR, the radar line on the MFD becomes amber and an “x” appears in front of the mode line.

72
Q

What is the function of the Path Attenuation Correction feature of the weather radar?

A

The yellow Path Attenuation Correction alert arc appears and informs the pilots that the radar beam is being severely attenuated and that the area of shadow behind the intervening rainfall may contain hidden and possibly significant precipitation. Avoid flight into the area between the displayed weather and the yellow Path Attenuation Correction alert.

CRJ 700 ENY STUDY GUIDE (17 decks)

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