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ATP > Crew Awareness > Flashcards

Crew Awareness Flashcards

1
Q

In an electrical emergency (essential power mode), will RMU 1 remained powered?

A

Yes.

Reference: OM Vol. 2, Section 2-4, Crew Awareness

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2
Q

Does the takeoff configuration warning test for two engines running/operating?

A

No.

Reference: OM Vol. 2, Section 2-4, Crew Awareness

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3
Q

During a decreasing performance windshear warning, should the aircraft be immediately re-configured to Gear Up/Flaps 9°?

A

No.

Reference: OM Vol. 1, Section 3, Windshear Escape Maneuver

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4
Q

What does pressing the takeoff configuration button check for?

A

Pitch trim between 4°-8° (green band), flaps between 9°-22°, parking break not set, and spoilers stowed
Reference: OM Vol. 2, Section 2-4, Crew Awareness

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5
Q

What happens if the DAU 1A channel fails? What pilot action should be taken to restore lost data?

A

Engine #1 indications are replaced with amber dashes. Per the QRH, select the appropriate EICAS reversionary button, however not all data will be restored.
Reference: OM Vol. 2, Section 2-4, Crew Awareness

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6
Q

When is the aircraft aural warning unit tested?

A

As soon as the electrical system is powered, provided the aircraft has been de-energized for at least 2 minutes (Power Up Test).
Reference: OM Vol. 2, Section 2-4, Crew Awareness

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7
Q

What will be heard if the aural warning unit test is successful?

A

If both aural warning unit channels are operating properly, the voice message “AURAL UNIT OK” is generated.
Reference: OM Vol. 2, Section 2-4, Crew Awareness

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8
Q

During a failure of symbol generator 1, would RMU 1 automatically display engine backup page 1 indications?

A

Yes.

Reference: Reference: OM Vol. 2, Section 2-4, Crew Awareness

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9
Q

The EICAS caution message “AURAL WARN FAIL” will only be presented when?

A

The message is displayed when both channel A and channel B of the aural warning unit have failed simultaneously.
Reference: OM Vol. 2, Section 2-4, Crew Awareness

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10
Q

How many transponders are on the EMB-145 aircraft?

A

2

Reference: OM Vol. 1, Section 3 Receiving Flow/OM Vol.2, Section 2-18, Navigation and Communication

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11
Q

How do the 5 cockpit CRTs appear following the loss of DC Bus 2?

A

Red ‘X’ on MFD 2, MFD 1 and PFD 2 are blank.

Reference: OM Vol. 2, Section 2-4, Crew Awareness

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12
Q

A failure of an ADC would be indicated by___________. The proper corrective action is to______________

A

A red X failure indication appearing on the airspeed tape, altitude tape, and the vertical speed pointer is removed and replaced by a red boxed VS. Reference the QRH Navigation/Flight Instruments Failures Index, press the associated/affected side ADC button on the reversionary panel per the QRH. This will allow cross-side ADC information to be used, operation in RVSM airspace not authorized; notify ATC.
Reference: OM Vol. 2, Section 2-4, Crew Awareness/QRH

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13
Q

What does an amber HDG comparator flag on the PFD/MFD indicate?

A

A difference of 6 degrees between the heading information compared by the two symbol generators.
Reference: OM Vol. 2, Section 2-4, Crew Awareness

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14
Q

When would an amber IAS comparator flag be presented?

A

When the CA and FO indicated airspeeds (calibrated) differ by 5 knots or more than for longer than 2 seconds.
Reference: OM Vol. 2, Section 2-4, Crew Awareness

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15
Q

What messages will be presented if the CA side AHRS fails:

A

The Captain’s PFD and MFD will display the following messages: ATT FAIL (EADI), HDG FAIL (Digital Compass), and HDG FAIL (MFD Digital Compass if map view is selected).
Reference: OM Vol. 2, Section 2-4, Crew Awareness

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16
Q

What does the message ‘CAS MSG’ indicate when presented on the PFD?

A

There is a disagreement between the IC-600’s on the EICAS message displayed.
Reference: OM Vol. 2, Section 2-4, Crew Awareness

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17
Q

If the EICAS screen fails, will the information be displayed anywhere else automatically?

A

No, the information doesn’t appear anywhere immediately. EICAS information is only automatically displayed on the RMU engine page automatically following an SG1 failure.
Reference: OM Vol. 2, Section 2-4, Crew Awareness

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18
Q

When does the digital flight data recorder begin recording?

A

By turning on the beacon or weight off wheels

Reference: OM Vol. 2, Section 2-4, Crew Awareness

19
Q

What indications would be displayed on the MFD and PFD immediately following an AHRS 2 failure?

A

ATT FAIL, HDG FAIL, HDG FAIL (on MFD if in MAP mode) Reference: OM Vol. 2, Section 2-4, Crew Awareness

20
Q

When will the stick shaker activate?

A

When the aircraft symbol touches the PLI.

Reference: OM Vol. 2, Section 2-4, Stall Protection System

21
Q

When your airspeed is in the amber band of the low speed awareness tape, what color is the PLI?

A

The PLI is red.

Reference: OM Vol. 2, Section 2-4, Stall Protection System

22
Q

When is the stick pusher inhibited?

A

 On the ground (except during the test)
 Below .5 G
 If the quick disconnect button is kept pressed
 Below 200 ft. AGL (reverts to 10 seconds after takeoff if the radio altimeters have failed)
 If either SPS cutout button has been pressed (released or, unlatched button position)
 Above 200 KIAS
 If at least one SPS channel is inoperative Reference: OM Vol. 2, Section 2-4, Stall Protection System

23
Q

What does the EICAS message SPS ADVANCED indicate?

A

SPS ADVANCED indicates that Stick shaker and pusher actuation is set to lower AOAs (higher speeds) due to a system component failure.
Reference: OM Vol. 2, Section 2-4, Stall Protection System

24
Q

Under what conditions will the electrical system operate as two separate, independent systems?

A

When 4 or more generators are online.

Reference: OM Vol.2, Section 2-5, Electrical

25
Q

When is the ground service bus powered?

A

The ground service bus will be powered when a GPU is powered and plugged into the aircraft but not selected and the batteries are off.
Reference: OM Vol.2, Section 2-5, Electrical

26
Q

What buses are energized while in the essential power mode?

A

The essential buses, hot battery buses and the central dc bus.
Reference: OM Vol.2, Section 2-5, Electrical

27
Q

Which of the following is still available in essential power mode? Flaps, pressurization, and/or normal gear extension.

A

Normal gear extension.

Reference: QRH, Electrical, Loss of all generators checklist.

28
Q

Describe the number of generators and respective voltage of the electrical system.

A

5 generator each capable of producing 28 VDC and 400 amps.

Reference: OM Vol.2, Section 2-5, Electrical

29
Q

Can the GPU be used to recharge the main aircraft batteries?

A

No, BC1 and BC2 open automatically when the GPU is selected and supplying power.
Reference: OM Vol.2, Section 2-5, Electrical

30
Q

What items are powered from the 115 VAC Bus?

A

TCAS, E-GPWS, Windshear.

Reference: OM Vol.2, Section 2-5, AC System

31
Q

Which electrical bus supplies power to the ISIS on the 145XR?

A

The backup battery hot bus.

Reference: OM Vol. 2, Section 2-5, Electrical/2-17, Flight Instruments

32
Q

Under what conditions are shed buses powered while on the ground?

A

With GPU powering the aircraft and the shed bus switch in the auto or override position.
With at least one generator online and the shed bus in the override position.
With 3 or more generators online. Reference: OM Vol.2, Section 2-5, Electrical

33
Q

How many minutes will the NICAD main batteries supply power in flight when in the essential power mode?

A

40 minutes or 45 minutes with pitot/static 3 heat deselected.
Reference: OM Vol.2, Section 2-5, Electrical/OM Vol. 1 Section 1, Limitations/QRH

34
Q

Will the electrical system still be configured as two separate systems after the loss of the APU generator and engine driven generator 1?

A

No. At least 4 generators must be online to have redundant electrical systems.
Reference: OM Vol.2, Section 2-5, Electrical

35
Q

Of the cockpit screens, FMS, RMU’s, and flight instrumentation, which are available in the essential power mode following a loss of all generators?

A

The EICAS, RMU1/2, and the standby instruments/ISIS.

Reference: OM Vol.2, Section 2-5, Electrical

36
Q

What criteria must be established in order to have shed bus power in flight?

A

At least 3 generators must be online for shed bus power in flight.
Reference: OM Vol.2, Section 2-5, Electrical

37
Q

With GPU power available and selected, where should the shed bus switch be positioned to energize the shed buses?

A

Auto or Override.

Reference: OM Vol.2, Section 2-5, Electrical

38
Q

Is DME available when is essential power mode?

A

No, but VOR or LOC type approaches may be flown so long as DME is not required.
Reference: OM Vol.2, Section 2-5, Electrical/Section 2-18, Navigation Backup Page

39
Q

Define the EICAS master warning ELEC ESS XFR FAIL.

A

The electrical system has failed to properly transfer into the essential power mode following a loss of all generators.
Reference: OM Vol.2, Section 2-5, EICAS Messages

40
Q

What is the function of the backup battery button on the overhead panel?

A

The backup battery button connects or disconnects the backup battery from the electrical system (via hot bus1).
Reference: OM Vol.2, Section 2-5, Controls and Indications

41
Q

What does the GPU AVAIL inscription on the GPU button on the overhead panel indicate?

A

The GPU AVAIL inscription indicates that the GPU is properly connected to the aircraft receptacle and some power is available (not necessarily sufficient or stable power though).
Reference: OM Vol.2, Section 2-5, Controls and Indications

42
Q

What items are powered from the backup battery/backup hot bus?

A

The Electrical Distribution Logic, the 5 Generator Control Units and the ISIS (XR only).
Reference: OM Vol.2, Section 2-5, Backup Battery.

43
Q

What is the power source for SG 2?

A

: DC Bus 2.

Reference: OM Vol. 2, Section 2-5, Electrical

ATP (19 decks)

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