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P-3C Basics > Electrical System Review Questions > Flashcards

Electrical System Review Questions Flashcards

1
Q

The external power receptacle is located

A

in the lower, forward, starboard wing root area

Aircraft Walkthrough

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2
Q

Each of the main AC generators is cooled by an internally driven fan. Which of the following is true concerning this system?

A

Cooling air enters a duct in the oil cooler scoop and the shutoff valve is controlled mechanically by the E-Handle

NATOPS 2.9.10

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3
Q

When is it acceptable to enter the main center during flight?

A

In case of extreme emergency

NATOPS 12.3.1

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4
Q

The solid-state supervisory panels do not provide protection for

A

Overfrequency. Caution if RPM exceeds 109%, place GEN off

NATOPS 2.2.1.5

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5
Q

When the external power monitor senses the proper frequency, phase, and voltage, it will energize all AC buses via transfer relay

A

4

NATOPS 2.2.4.9

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6
Q

Ensuring a power source to main AC buses A and B is function of the

A

Transfer relays

NATOPS 2.2.2

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7
Q

The primary function of the runaround relays is to

A

Ensure a source of power to FEAC and MEAC buses

NATOPS 2.2.2

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8
Q

The forward load center contains essential bus relays, the inverter, and

A

Transformer Rectifier #3

NATOPS FO-10

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9
Q

The inverter is used to energize the ____ when no generators are operable

A

TIT gauges (through SEAC bus)

NATOPS FO-10, 15.1.1.2

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10
Q

The purpose of the reset position on the external power switch is to

A

Reset the sensor in the external power monitor

NATOPS 2.2.4.9

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11
Q

PMG voltage into the aircraft may only be stopped by

A

securing the engine

NATOPS 2.2.1.1; 12.3

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12
Q

39 VAC PMG power is supplied to a generators respective supervisory panel anytime the generator is turning (prop rotating). It can be stopped by:

A

Feathering the respective propeller

NATOPS 2.2.1.1; 12.3

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13
Q

Which buses are energized by the aircraft battery when initially connected?

A

FEDC, GOB, and APU Essential DC

NATOPS FO-10

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14
Q

What circuit breaker, if out, will deenergize transfer relay #7 and prevent generator 4 from powering any bus without bringing on the GEN 4 OFF light?

A

GEN 4 AUX control

NATOPS 2.2.1, 2.2.4.3

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15
Q

The circuit breaker that enables generators 2 and 3 to back each other up in the event of a generator 4 failure?

A

GEN 4 TRANS Control

NATOPS FO-10

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16
Q

If the bus A control circuit breaker is out

A

BUS A will be lost if the No. 2 engine is E-Handled

NATOPS FO-10

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17
Q

If generator 4 and the APU generator are the only generators available:

A

Generator 4 will power everything

NATOPS FO-10; 2.2.1

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18
Q

If the GEN 4 AUX Control circuit breaker is out:

A

Generator 4 cannot power any bus and there will be no light indication of this situation

NATOPS 15.1.1

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19
Q

If Transfer Rectifier #3 is lost in flight, the MON ESS DC bus would be powered by:

A

EMDC through a blocking diode

NATOPS FO-10

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20
Q

What are the priorities for powering the Monitorable Essential AC (MEAC) bus?

A

BUS A, 2, 4, 3

NATOPS FO-10

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21
Q

What are the priorities for powering Flight Ess AC (FEAC)?

A

2, 4, 3, BUS A

NATOPS FO-10

22
Q

With all buses normally energized, the APU Essential bus is powered by:

A

MEDC

NATOPS FO-10

23
Q

The transfer and runaround system sets the following priority to ensure bus B receives electrical power:

A

Gen 3, 4, APU, 2

NATOPS FO-10

24
Q

What are the priorities for powering MEDC?

A

Transformer Rectifier 3, and EMDC as a backup

NATOPS FO-10

25
Q

The Bus B control circuit breaker on MEDC powers:

A

The B side of Transfer relay 3

NATOPS FO-10

26
Q

If the Gen 4 AUX CONTROL circuit breaker is out:

A

Generator 4 cannot power any bus

NATOPS FO-10

27
Q

The generator 4 transfer control circuit breaker allows:

A

Generator 2 to power Bus B and Generator 3 to power Bus A

NATOPS FO-10

28
Q

What is the purpose of the GEN 4 AUX CONTROL circuit breaker powered by the FEDC bus

A

It gives generator 4 priority over the APU

NATOPS FO-10

29
Q

Generator 4 and the APU cannot concurrently supply power to the aircraft electrical system. Transfer relay # ____ gives generator #4 priority over the APU.

A

7

NATOPS 2.2.1, FO-10

30
Q

If the generator 4 transfer control circuit breaker were tripped, it would:

A

Not allow generator 3 to power BUS A

NATOPS FO-10

31
Q

If the GEN 4 AUX CONT C/B is out, the GEN 4 OFF light will:

A

Not come on and the generator will not assume a load.

NATOPS 2.2.4.3, 15.1.1

32
Q

With all buses energized, turning off the Essential Bus Monitoring switch will secure which buses?

A

MEAC and SEAC

NATOPS FO-10

33
Q

The red GEN mechanical failure light for an engine driven generator will illuminate when the:

A

Auxiliary bearing is under a load

NATOPS 2.2.1.4

34
Q

the APU provides air for:

A

Engine starting

NATOPS 2.1

35
Q

The APU intake and exhaust doors will:

A

close automatically if a fire is detected in the APU compartment.

NATOPS 12.2

36
Q

If the APU and Fire Extinguisher Safety Switch on the port side of the fuselage is actuated during ground operations, the APU will shutdown if running and cannot be started. The switch also:

A

deactivates the APU fire extinguishing system.

NATOPS 2.1.4.1

37
Q

When the APU fire detection system activates:

A

the APU shuts down automatically.

NATOPS 2.1.4

38
Q

In the event of a fire in the APU compartment, the fire detector system will:

A

automatically shutdown the APU, close the doors, and discharge the HRD agent.

NATOPS 2.1.4

39
Q

On the ground, the APU INFLIGHT ARMING switch, in the ARM position, will:

A

disable the bleed air functions of the APU

NATOPS 2.1.3.3

40
Q

RPM limits for the APU in flights are ____%

A

98-103%

NATOPS 4.4

41
Q

APU RPM limits for ground operation are ____%

A

98-102%

NATOPS 4.4

42
Q

The APU is capable of starting any single engine at field elevations up to ___ feet.

A

6000

NATOPS 4.4

43
Q

The maximum continuous Exhaust Gas Temperature (EGT) for the GTCP 95-10 APU is ____ degrees C

A

649

NATOPS 4.4

44
Q

The maximum peak EGT for the GTCP 95-10 is ____ degrees C

A

732

NATOPS 4.4

45
Q

All of the following will cause automatic shutdown of the APU except:

A

Failure of the #2 boost pump.

NATOPS 7.5.3

46
Q

The maximum peak (10 seconds) EGT for the GTCP 95-10 APU is ____ C

A

710

NATOPS 4.4

47
Q

The maximum airspeed for using the APU is ____ knots

A

225

NATOPS 4.4

48
Q

The 8000 feet barometric switch utilized by the APU for full load monitoring is controlled by:

A

the APU GEN CONT circuit breaker.

NATOPS 2.2.5.2

49
Q

During single engine-driven generator operation, which of the following will not load monitor when prop or EMP deice is activated?

A

1A hydraulic pump

NATOPS Fig. 2-2

50
Q

At what pressure altitude will automatic full load monitoring occur when operating with only the APU generator available?

A

8,000

NATOPS Fig 2-2, 2.2.5.2, 15.1.3.2

P-3C Basics (33 decks)

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