ELEC- Menta fresca

AC power frequency and voltage is ______. 240 CPS/115V. 400 CPS/115V. 60 CPS/110V. 400 CPS/240V.

The DC voltage of the battery and transformer/rectifier output is ______. 12V. 115V. 28V. 36V.

All generator bus sources must be manually connected through the movement of a switch. True. False.

When a new power source is switched onto a bus, the source that was previously powering the system is automatically disconnected. True. False.

On the ground, all the electrical busses may be supplied by ______. The APU generator. External AC ground power. One engine driven generator. Either a or b.

If one engine driven generator fails in flight, the ______ may be used to power all its busses. Other engine driven generator. APU generator. Battery. Battery charger.

Each transfer bus has an associated transfer relay which automatically selects the opposite generator bus as a power supply if its normal source fails and the transfer switch is in AUTO. True. False.

This light illuminates any time the engine generator is not connected to its respective bus.

This indicator shows the frequency of the selected source.

When this light is illuminated, the AC Standby Bus is inactive.

With this switch in the STBY PWR position, only the bus voltage will be displayed on the DC voltmeter.

This light illuminates whenever an operating external power source is connected to the airplane.

The OFF position of this switch deactivates the battery bus on the ground.

This switch is used to disconnect the generator drive when abnormal operation is detected.

This switch is used to deactivate the automatic transfer of AC power sources.

This light illuminates when the generator drive operating pressure is below a safe value.

Positioning this switch to ON will simultaneously trip both engine generators.

This switch connects the engine generator to its respective bus.

This amber light illuminates whenever electrical power is lost to its respective bus.

The BAT position of this switch powers the No. 1 VHF through the battery bus.

This amber warning light is normally illuminated before the engines are started.

Battery voltage can be checked by positioning this switch to the BAT position.

Under normal in flight operating conditions, what is the relationship of the No. 1 electrical system to the No. 2 electrical system?. Completely independent AC and DC busses. Independent AC busses, paralleled DC busses. Paralleled AC busses, independent DC busses. Parallel AC and DC busses.

Each transfer bus has an associated transfer relay which automatically selects the opposite generator bus as an alternate power supply if its primary source fails. (BUS TRANSFER - AUTO). True. False.

In flight, the Standby AC and DC busses can be powered from ______. Battery Bus. Transfer Bus No. 1. Transfer Bus No. 2. Either a or b.

DC power required for systems control, light, communications and navigation equipment can be supplied by ______. Transformer/Rectifier (T/R) units. Battery. No. 1 Main Bus. Both a and b.

The AC Standby Bus is normally powered by ______. Transfer Bus No. 1. Main Bus No. 1. Main Bus No. 2. Transfer Bus No. 2.

The DC Standby Bus is normally powered by. Battery Bus. No. 1 DC Bus. No. 2 DC Bus. T/R No. 3.

Transformer/Rectifier No. 3 receives its power from ______. No. 1 Generator Bus. No. 1 Main Bus. No. 2 Transfer Bus. No. 2 Main Bus.

Normal operation of a T/R may be confirmed by positioning the DC METER switch to the desired T/R position and observing a positive reading on the DC AMPS meter. True. False.

The T/R No. 3 disconnect relay automatically opens at glide slope capture. To prevent a single bus failure from affecting both navigation receivers and flight control computers. To provide more power to the AC Standby bus. To ensure that the Standby DC bus is powered. All of the above.

The maximum Generator Drive oil temperature is ______. 20°C. 157°C. 150°C. 145°C.

Illumination of the Generator Drive LOW OIL PRESSURE light requires the crew to. Trip the respective generator circuit breaker. Check the drive temperature for both IN and RISE. Land as soon as possible. Disconnect the Generator Drive.

When you disconnect the Generator Drive for Generator No. 1 in flight, what three lights of the electrical system illuminate? (APU not running). Generator Drive LOW OIL PRESSURE, GEN OFF BUS, BUS OFF. Generator Drive LOW OIL PRESSURE, APU GEN OFF BUS, STANDBY POWER OFF. TRANSFER BUS OFF, BUS OFF, GEN OFF BUS. STANDBY PWR OFF, HIGH OIL TEMP, GEN OFF BUS.

On the ground, the STANDBY PWR OFF light will normally extinguish when. The Battery Switch is positioned to ON. STANDBY POWER is positioned to BAT. Any AC source is connected to the generator buses. Either b or c.

An in flight loss of all generators requires the crew to immediately position the STANDBY POWER Switch to the BAT position. True. False.

The maximum generator drive oil temperature rise is ______. 20°C. 30°C. 160°C. 25°C.

The Battery Switch must be ON in order to connect ground power to the aircraft systems. True. False.

In flight, electrical load shedding automatically turns off the galley power when operating on one generator. This reduces power demand and ensures that the remaining generator will not be overloaded. True. False.