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On the ground, with the BATTERY switch OFF and STANDBY POWER Switch in BAT, the switched hot battery bus is:

Correct! Wrong!

If the AC source powering a transfer bus fails, the transfer bus will remain unpowered.

Correct! Wrong!

Both On the ground and in flight a amber ELEC light comes on to indicate that a fault exists in DC power system or standby power system.

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The ELEC light is inhibited in flight.

What is the purpose of the GROUND SERVICE switch?

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Enables servicing airplane using external power without activating AC transfer busses.rn

The TR3 Disconnect Relay:

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When the STANDBY POWER Switch is OFF:

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A high oil temperature in the IDG would cause an automatic disconnect of the IDG.rnrnrn

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It is possible to power one transfer bus with external power and the other transfer bus with the APU?

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DC busses powered from the battery following a loss of both generators are:

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The cross bus tie relay:

Correct! Wrong!

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The GROUND POWER AVAILABLE light will extinguish when:

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AUTOMATIC LOAD SHEDDING (ENGINE GENERATORS) - For single generator operation, the system is designed to shed electrical load incrementally based on actual load sensing. What is the first bus that is shed?

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Transformer rectifier (TR) units and the main battery/battery charger supply DC power.

Correct! Wrong!

Which is the power source for the AC standby bus?

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The purpose of the AC ground service bus is to power:

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In flight if APU is the only source of electrical power:

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One basic principle of operation for the B737 electrical system is:

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Because engine generators power the transfer busses directly, and transfer busses are connected by a bus tie system, the loss of an engine driven generator will not necessarily result in the loss of any bus(ses).

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The illumination of the GND POWER AVAILABLE light indicates:

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Illumination of the BAT DISCHARGE light indicates:

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Illumination of the GEN BUS OFF light indicates:

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When the aircraft batteries is the only source of power:

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The 115V AC Standby Bus is powered by:

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Both AC Transfer busses can be powered simultaneously by:

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What is the significance of an illuminated ELEC light?

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With the STANDBY switch in the AUTO position, the loss of all engine or APU electrical power results in the automatic switching from the normal power source to the alternate source for standby power:

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Which bus supplies electrical power to the auxiliary battery charger?

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Galley busses are powered from:

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On the ground, with the battery switch OFF and STANBY POWER Switch in AUTO, the Battery Bus is:

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The TR UNIT will illuminate in flight if:

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The TR3 cross bus tie relay automatically opens at glide slope capture to:

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After the loss of all generators, two fully charged batteries have sufficient capacity to provide standby power for a minimum of:Two fully charged batteries have sufficient capacity to provide standby power forrna minimum of

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The Engine Integrated Drive Generators (IDGs):

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Illumination of the STANDBY POWER OFF light indicates:

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The IDGs contain the generator and drive in a common housing, and are lubricated and cooled by a external oil system attached to the gearbox.

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The IDGs contain the generator and drive in a common housing, and are lubricated and cooled by a self-contained oil system.

The purpose of the cross tie relay is to:

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For ground service, a ground service switch is available on:

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What is the source of power for TR3?

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The ELEC light will illuminate in flight if:

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The switched hot battery bus is powered whenever:

Correct! Wrong!

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Either generator or the APU can power both transfer buses. In the event a power source fails, what is required for that transfer bus to be powered by the opposite transfer bus power source?

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What is the source of power for TR2?

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DC voltage and amperage may be read on the DC voltmeter and ammeter for the battery and each of the 3 TRs. The Standby power and battery bus displays only Dc voltage. Normal indication is ______ volts

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In flight, if the APU is supplying both AC Transfer busses, positioning the BUS TRANS switch to OFF will:

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The main battery charger is powered through:

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AUTOMATIC LOAD SHEDDING (ENGINE GENERATORS) - For single generator operation, the system is designed to shed electrical load incrementally based on actual load sensing. When configuration changes to more source capacity (two generator operation), automatic load restoration of the main busses, galley busses and IFE buses occurs. Manual restoration of galley and main bus power can be attempted by:

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Illumination of the blue GEN OFF BUS light indicates:

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Normal AC voltmeter indication for the APU generator with the AC busses loaded:

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The auxiliary battery operates in parallel with the main battery when the battery is powering the standby bus.

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The main and auxiliary batteries also provide backup power for the DC standby system only.

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The main and auxiliary batteries also provide backup power for the AC and DC standby system.

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During cruise, one engine driven generator drops off-line. Indications that the crew should see include:

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Each IDG supplies its own bus system in normal operation and can also supply essential and non-essential loads of the opposite side bus system when one IDG is inoperative.

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With external DC power connected to the external DC power receptacle:

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DC voltage and amperage may be read on the DC voltmeter and ammeter for the battery and each of the three TRs. The standby power and battery bus displays only DC voltage. Normal indication is:

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During primary charge cycle operation battery voltage can be as high as 30 +/- 3 volts

Boeing 737 MAX - Electrical