Embraer 190 - Electrical

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Questions: 36 | Attempts: 3,306 | Updated: Dec 18, 2023

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ELECTRICAL QUESTIONS MADE FROM THE AOM VOL. 2
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Dec 18, 2023

Quiz Edited by
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Jun 07, 2011

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Embraer 190 - Electrical

Both IDGs and the APU generator are rated at _______________________ , three-phase.

In flight, the _____ is used as an emergency generator, supplying power to the ESS BUSES when both AC BUSES 1 and 2 are not powered.

What does "IDG" means?

For automatic operation of the electrical system, the IDG selector knob must be set to the AUTO position. Moving the selector knob to OFF position, the generator line contactor opens, tripping off-line and de-exciting the selected IDG.

Manual disconnection is achieved by selecting the respective knob to the _______ position. The flight crew cannot reconnect the IDG.

During the APU starting cycle, ________ is isolated from the network, powering the APU START BUS exclusively. In flight, the APU can be started up within operational limits, and replaces any IDG sources with no operational degradation.

Before disconnecting the AC GPU from the airplane, the flight crew must push out the _________________ pushbutton, even if the IN USE light has already extinguished. The AC GPU pushbutton has to be pushed out for the next connection.

Ground staff can connect the GPU directly to the ____________________________ for ground maintenance and flight preparation, by pushing the respective button located on the front ramp panel or on the flight attendant panel at the forward right galley.

The AC/DC inverter converts 28 V DC power from batteries to 115 V AC power to supply the _________________ when an AC power source is not available.

The RAT is an AC electrical device installed in the airplane nose section, which converts the kinetic energy of airflow across the turbine into _________ . The electrical power produced is rated at 15 kVA, 115 V AC, 400 Hz, three-phase.

Whenever AC power sources are not powering AC buses, the RAT is automatically deployed, and after 8 s, supplies power to the __________ .

(ON RAT POWER) ____________________ are powered through the ESS TRU.

To avoid total loss of power during this 8 s period, batteries are used as backup to power the DC ESS BUSES and the __________________ .

The RAT electrical power drives the _________________________ for primary flight control tasks. These include high lift system actuation and power for essential avionics, communication and battery recharging.

In flight, __________ altitude restriction for RAT deployment.

______ kt is required to ensure the RAT continues supplying AC/DC ESS BUSES. At speeds below this, the RAT may only supply the AC ESS BUS, and the batteries will automatically provide electrical power to the DC ESS BUSES and the STANDBY AC BUS through an AC/DC inverter.

The DC electrical system comprises: • (1) transformer rectifier units (TRU)s; • (2) batteries.

On ground, a DC ground power unit (DC GPU) can be connected to the airplane supplying power to only the _______________________ .

In certain conditions, _____________________________ to backup all DC ESS BUSES and the AC STBY BUS. Battery #2 also supplies the APU START BUS, during APU starting.

Three TRUs convert 115 VAC power into 28 VDC. Each TRU works in isolation. If one of them fails, the BUSES will automatically be powered by the remaining TRUs, as long as the DC BUS TIES toggle switch is selected to ______.

TRU 1 provides DC power to:

TRU 2 provides DC power to:

TRU ESS provides DC power to:

In an ELECTRICAL EMERGENCY, batteries are capable to supply airplane essential systems for at least _____________ , even if the RAT is failed.

Whenever the battery temperature reaches _________________________ , the associated indication becomes red and the EICAS WARNING message BATT 1 (2) OVERTEMP is triggered.

The minimum battery #2 temperature for APU starting is ...

The _________ is used when the battery is no longer available or the battery #2 temperature is below -20°C.

A suitable DC GPU should be able to supply the airplane systems with at least _______________________ , when under use. The voltage may be checked on the synoptic page on MFD.

The ______ is an electrical-electronic integrated device, providing power distribution and protection for the airplane electrical loads, the secondary power distribution assemblies (SPDAs) and the circuit breakers that are located on the cockpit sidewall panels.

Each ICC, installed in the electronics bay, incorporates _______ , _ , _ and _______ . The LRUs and LRMs allow quick access and easy replacement of electrical components, thereby minimizing any delays due to maintenance servicing.

An SPDA is an electrical load management unit, which receives power from the ____ AC/DC electrical buses and distributes it to the airplane systems, according to system distribution logic.

____ independent SPDAs replace thermal circuit breakers (CBs) and electromechanical relays used in other airplanes, thereby reducing the amount of electrical hardware as well as flight crew workload.

Some thermal CBs are located ...

The electronic CBs are located ...

The ____ remote thermal CBs can only be reset by maintenance personal when the airplane is on ground.

The flight crew can reset the ______ remote electronic CBs via the MCDU.

Embraer 190 - Electrical

Both IDGs and the APU generator are rated at _______________________ , three-phase.

In flight, the _____ is used as an emergency generator, supplying power to the ESS BUSES when both AC BUSES 1 and 2 are not powered.

What does "IDG" means?

For automatic operation of the electrical system, the IDG selector knob must be set to the AUTO position. Moving the selector knob to OFF position, the generator line contactor opens, tripping off-line and de-exciting the selected IDG.

Manual disconnection is achieved by selecting the respective knob to the _______ position. The flight crew cannot reconnect the IDG.

During the APU starting cycle, ________ is isolated from the network, powering the APU START BUS exclusively. In flight, the APU can be started up within operational limits, and replaces any IDG sources with no operational degradation.

Before disconnecting the AC GPU from the airplane, the flight crew must push out the _________________ pushbutton, even if the IN USE light has already extinguished. The AC GPU pushbutton has to be pushed out for the next connection.

Ground staff can connect the GPU directly to the ____________________________ for ground maintenance and flight preparation, by pushing the respective button located on the front ramp panel or on the flight attendant panel at the forward right galley.

The AC/DC inverter converts 28 V DC power from batteries to 115 V AC power to supply the _________________ when an AC power source is not available.

The RAT is an AC electrical device installed in the airplane nose section, which converts the kinetic energy of airflow across the turbine into _________ . The electrical power produced is rated at 15 kVA, 115 V AC, 400 Hz, three-phase.

Whenever AC power sources are not powering AC buses, the RAT is automatically deployed, and after 8 s, supplies power to the __________ .

(ON RAT POWER) ____________________ are powered through the ESS TRU.

To avoid total loss of power during this 8 s period, batteries are used as backup to power the DC ESS BUSES and the __________________ .

The RAT electrical power drives the _________________________ for primary flight control tasks. These include high lift system actuation and power for essential avionics, communication and battery recharging.

In flight, __________ altitude restriction for RAT deployment.

______ kt is required to ensure the RAT continues supplying AC/DC ESS BUSES. At speeds below this, the RAT may only supply the AC ESS BUS, and the batteries will automatically provide electrical power to the DC ESS BUSES and the STANDBY AC BUS through an AC/DC inverter.

The DC electrical system comprises: • (1) ______ transformer rectifier units (TRU)s; • (2) ______ batteries.

On ground, a DC ground power unit (DC GPU) can be connected to the airplane supplying power to only the _______________________ .

In certain conditions, _____________________________ to backup all DC ESS BUSES and the AC STBY BUS. Battery #2 also supplies the APU START BUS, during APU starting.

Three TRUs convert 115 VAC power into 28 VDC. Each TRU works in isolation. If one of them fails, the BUSES will automatically be powered by the remaining TRUs, as long as the DC BUS TIES toggle switch is selected to ______.

TRU 1 provides DC power to:

TRU 2 provides DC power to:

TRU ESS provides DC power to:

In an ELECTRICAL EMERGENCY, batteries are capable to supply airplane essential systems for at least _____________ , even if the RAT is failed.

Whenever the battery temperature reaches _________________________ , the associated indication becomes red and the EICAS WARNING message BATT 1 (2) OVERTEMP is triggered.

The minimum battery #2 temperature for APU starting is ...

The _________ is used when the battery is no longer available or the battery #2 temperature is below -20°C.

A suitable DC GPU should be able to supply the airplane systems with at least _______________________ , when under use. The voltage may be checked on the synoptic page on MFD.

The ______ is an electrical-electronic integrated device, providing power distribution and protection for the airplane electrical loads, the secondary power distribution assemblies (SPDAs) and the circuit breakers that are located on the cockpit sidewall panels.

Each ICC, installed in the electronics bay, incorporates _____________ , _____________ , _____________ and _____________ . The LRUs and LRMs allow quick access and easy replacement of electrical components, thereby minimizing any delays due to maintenance servicing.

An SPDA is an electrical load management unit, which receives power from the ____ AC/DC electrical buses and distributes it to the airplane systems, according to system distribution logic.

____ independent SPDAs replace thermal circuit breakers (CBs) and electromechanical relays used in other airplanes, thereby reducing the amount of electrical hardware as well as flight crew workload.

Some thermal CBs are located ...

The electronic CBs are located ...

The ____ remote thermal CBs can only be reset by maintenance personal when the airplane is on ground.

The flight crew can reset the ______ remote electronic CBs via the MCDU.

The DC electrical system comprises: • (1) transformer rectifier units (TRU)s; • (2) batteries.

Each ICC, installed in the electronics bay, incorporates _______ , _ , _ and _______ . The LRUs and LRMs allow quick access and easy replacement of electrical components, thereby minimizing any delays due to maintenance servicing.