# Embraer 190 - Electrical

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ELECTRICAL QUESTIONS MADE FROM THE AOM VOL. 2
GOOD LUCK! SANTIAGO STOCKER.

• 1.

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

• A.

40 kVA, 220 VAC, 400 Hz

• B.

40 kVA, 115 VAC, 400 Hz

B. 40 kVA, 115 VAC, 400 Hz
Explanation
The correct answer is 40 kVA, 115 VAC, 400 Hz. This means that both the IDGs and the APU generator are rated at 40 kVA, providing 115 volts of alternating current (VAC) at a frequency of 400 Hz.

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• 2.

### 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.

• A.

RAT

• B.

BATTERY #1

A. RAT
Explanation
In flight, the RAT (Ram Air Turbine) is used as an emergency generator, supplying power to the ESS BUSES when both AC BUSES 1 and 2 are not powered.

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• 3.

### What does "IDG" means?

INTEGRATED DRIVE GENERATOR
Explanation
"IDG" stands for Integrated Drive Generator. This acronym is commonly used in the aviation industry to refer to a device that combines the functions of a generator and a hydraulic pump. The Integrated Drive Generator is typically used in aircraft to provide electrical power and hydraulic pressure for various systems.

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• 4.

### 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.

• A.

True

• B.

False

A. True
Explanation
When the IDG selector knob is set to the AUTO position, it allows for the automatic operation of the electrical system. This means that the generator line contactor is closed, allowing the IDG to provide electrical power to the system. However, if the selector knob is moved to the OFF position, the generator line contactor opens, causing the IDG to trip offline and stop providing power to the system. Therefore, in order for the electrical system to operate automatically, the IDG selector knob must be set to the AUTO position.

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• 5.

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

• A.

DISC

• B.

AUTO

A. DISC
Explanation
The flight crew can manually disconnect the Integrated Drive Generator (IDG) by selecting the respective knob to the DISC (disconnect) position. This action will disconnect the IDG from the engine, preventing it from providing electrical power to the aircraft systems. The flight crew does not have the ability to reconnect the IDG once it has been manually disconnected.

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• 6.

### 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.

• A.

BATT 1

• B.

BATT 2

B. BATT 2
Explanation
During the APU starting cycle, BATT 2 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.

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• 7.

### 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.

• A.

AC APU

• B.

AC GPU

B. AC GPU
Explanation
Before disconnecting the AC GPU from the airplane, the flight crew must push out the AC GPU pushbutton, even if the IN USE light has already extinguished. This is necessary to ensure that the AC GPU is properly disconnected and ready for the next connection.

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• 8.

### 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.

• A.

AC/DC GND SVC BUSES

• B.

DC GND SVC BUS

A. AC/DC GND SVC BUSES
Explanation
The ground staff can connect the GPU (Ground Power Unit) directly to the AC/DC GND SVC BUSES for ground maintenance and flight preparation. This can be done by pushing the respective button located on the front ramp panel or on the flight attendant panel at the forward right galley.

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• 9.

### 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.

• A.

STANDBY AC BUS

• B.

ESS DC BUS

A. STANDBY AC BUS
Explanation
The AC/DC inverter is used to convert the 28 V DC power from batteries to 115 V AC power. This is done in order to supply the STANDBY AC BUS when there is no AC power source available.

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• 10.

### 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.

• A.

AC power

• B.

DC power

A. AC power
Explanation
The RAT (Ram Air Turbine) is an AC electrical device that converts the kinetic energy of airflow across the turbine into AC power. The electrical power produced by the RAT is rated at 15 kVA, 115 V AC, 400 Hz, three-phase.

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• 11.

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

• A.

AC ESS BUS

• B.

DC ESS BUS

A. AC ESS BUS
Explanation
When the AC power sources are not supplying power to the AC buses, the RAT (Ram Air Turbine) is automatically deployed. After 8 seconds, the RAT starts supplying power to the AC ESS (Essential) BUS.

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• 12.

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

• A.

DC ESS BUS3

• B.

DC ESS BUSES

B. DC ESS BUSES
Explanation
The correct answer is "DC ESS BUSES." This answer suggests that the power for the mentioned entity is provided through the DC ESS BUSES.

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• 13.

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

• A.

AC ESS BUS.

• B.

STANDBY AC BUS.

B. STANDBY AC BUS.
Explanation
During the 8-second period, the batteries are used as a backup to power the DC ESS BUSES and the STANDBY AC BUS. This suggests that the STANDBY AC BUS is also an important component that needs to be powered to avoid a total loss of power.

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• 14.

### 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.

• A.

AC Motor-driven Pump (ACMP 3A)

• B.

AC Motor-driven Pump (ACMP 3B)

A. AC Motor-driven Pump (ACMP 3A)
Explanation
The RAT electrical power drives the AC Motor-driven Pump (ACMP 3A) for primary flight control tasks. These include high lift system actuation and power for essential avionics, communication, and battery recharging.

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• 15.

### In flight, __________ altitude restriction for RAT deployment.

• A.

There is

• B.

There is no

B. There is no
Explanation
During a flight, there is no altitude restriction for RAT (Ram Air Turbine) deployment.

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• 16.

### ______ 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.

130, 130kt, 130 kt, 130 knots, 130knots
Explanation
The given answer options (130, 130kt, 130 kt, 130 knots, 130knots) suggest that the missing word in the statement is a speed measurement. The explanation is that a speed of 130 knots (or any of the other given options) is required to ensure that the RAT (Ram Air Turbine) continues supplying electrical power to the AC/DC ESS BUSES. Below this speed, the RAT can only supply power to the AC ESS BUS, and the batteries will automatically provide power to the DC ESS BUSES and the STANDBY AC BUS through an AC/DC inverter.

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• 17.

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

• A.

(1)Three / (2)Two

• B.

(1)Two / (2) One

A. (1)Three / (2)Two
Explanation
The correct answer is (1)Three / (2)Two. The DC electrical system comprises three transformer rectifier units (TRUs) and two batteries.

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• 18.

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

• A.

DC ESS BUS3

• B.

APU START BUS

B. APU START BUS
Explanation
The correct answer is APU START BUS. This is because the DC ground power unit can only supply power to the APU start bus on the airplane when it is on the ground. The APU start bus is responsible for starting the auxiliary power unit (APU) which provides electrical power to the aircraft when the main engines are not running.

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• 19.

### 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.

• A.

Batterie #1 is used

• B.

Batterie #2 is used

• C.

Batteries #1 and #2 are used

C. Batteries #1 and #2 are used
Explanation
In certain conditions, both Battery #1 and Battery #2 are used to backup all DC ESS BUSES and the AC STBY BUS. Additionally, Battery #2 also supplies power to the APU START BUS during APU starting.

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• 20.

### 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 ______.

AUTO, auto
Explanation
If one of the TRUs fails, the remaining TRUs will automatically power the BUSES as long as the DC BUS TIES toggle switch is selected to AUTO. The term "auto" refers to the automatic mode of the switch, which allows the system to automatically switch to the remaining TRUs for power in case of a failure.

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• 21.

### TRU 1 provides DC power to:

• A.

DC BUS 1, DC ESS BUS 1, DC GND SVC BUS, HOT BATT BUS 1 and battery #1 charging.

• B.

DC BUS 2, DC ESS BUS 2, HOT BATT BUS 2 and battery #2 charging.

A. DC BUS 1, DC ESS BUS 1, DC GND SVC BUS, HOT BATT BUS 1 and battery #1 charging.
Explanation
TRU 1 provides DC power to DC BUS 1, DC ESS BUS 1, DC GND SVC BUS, HOT BATT BUS 1, and battery #1 charging. This means that TRU 1 is responsible for supplying power to these specific components and systems. It does not provide power to DC BUS 2, DC ESS BUS 2, HOT BATT BUS 2, or battery #2 charging, which are powered by a different source.

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• 22.

### TRU 2 provides DC power to:

• A.

DC BUS 1, DC ESS BUS 1, DC GND SVC BUS, HOT BATT BUS 1 and battery #1 charging.

• B.

DC BUS 2, DC ESS BUS 2, HOT BATT BUS 2 and battery #2 charging.

B. DC BUS 2, DC ESS BUS 2, HOT BATT BUS 2 and battery #2 charging.
Explanation
TRU 2 provides DC power to DC BUS 2, DC ESS BUS 2, HOT BATT BUS 2, and battery #2 charging. This means that TRU 2 supplies power to the second set of DC buses, essential DC buses, and the second hot battery bus. Additionally, it is responsible for charging battery #2.

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• 23.

### TRU ESS provides DC power to:

• A.

DC ESS BUS 3.

• B.

DC ESS BUS 2.

A. DC ESS BUS 3.
Explanation
The correct answer is DC ESS BUS 3. This means that TRU ESS (Transformer Rectifier Unit - Essential Services System) provides DC power to the DC ESS BUS 3.

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• 24.

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

• A.

10 minutes

• B.

30 minutes

A. 10 minutes
Explanation
During an electrical emergency, when the RAT (Ram Air Turbine) fails, the batteries are designed to provide power to the essential systems of the airplane. The question asks for the minimum amount of time the batteries can supply power in this situation. The correct answer is 10 minutes, indicating that the batteries are capable of sustaining the essential systems for at least 10 minutes, even if the RAT fails.

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• 25.

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

• A.

50Â°C for at least 5 seconds

• B.

70Â°C for at least 2 seconds

B. 70Â°C for at least 2 seconds
Explanation
The associated indication becomes red and the EICAS WARNING message BATT 1 (2) OVERTEMP is triggered when the battery temperature reaches 70Â°C for at least 2 seconds.

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• 26.

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

• A.

-20Â°C.

• B.

-40Â°C.

A. -20Â°C.
Explanation
The minimum battery #2 temperature for APU starting is -20Â°C. This means that the battery needs to be at a minimum temperature of -20Â°C in order to start the APU (Auxiliary Power Unit). Starting the APU is important for providing power to the aircraft when the engines are not running, such as during ground operations or in the event of an engine failure. If the battery temperature is below -20Â°C, it may not have enough power to start the APU, resulting in a delay or inability to provide necessary power to the aircraft systems.

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• 27.

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

• A.

AC GPU

• B.

DC GPU

B. DC GPU
Explanation
A DC GPU (Ground Power Unit) is used when the battery is no longer available or the battery #2 temperature is below -20Â°C.

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• 28.

### 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.

• A.

24 VDC and no more than 29 VDC

• B.

28 VDC and no more than 32 VDC

A. 24 VDC and no more than 29 VDC
Explanation
The suitable DC GPU should be able to supply the airplane systems with a voltage between 24 VDC and 29 VDC when under use. This range ensures that the voltage supplied is within the acceptable limits for the airplane systems to function properly. The voltage can be checked on the synoptic page on the Multi-Function Display (MFD) to ensure it falls within this range.

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• 29.

### 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.

ICC, icc, iccs, ICCs, icc s
Explanation
The ICC (Integrated Control Center) is an electrical-electronic integrated device that provides power distribution and protection for the airplane electrical loads, the secondary power distribution assemblies (SPDAs), and the circuit breakers located on the cockpit sidewall panels.

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• 30.

### 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.

• A.

Thermal circuit breakers (CBs)

• B.

Line replaceable units (LRUs)

• C.

Line replaceable modules (LRMs)

• D.

AC/DC electrical buses

• E.

All of above

E. All of above
Explanation
The correct answer is "all of above". Each ICC, installed in the electronics bay, incorporates thermal circuit breakers (CBs), line replaceable units (LRUs), line replaceable modules (LRMs), and AC/DC electrical buses. These components allow for quick access and easy replacement of electrical components, minimizing any delays due to maintenance servicing.

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• 31.

### 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.

• A.

ICC

• B.

IGD

A. ICC
Explanation
An SPDA receives power from the ICC (Integrated Control Center) AC/DC electrical buses and distributes it to the airplane systems. The ICC is responsible for controlling and monitoring various electrical systems on the aircraft, and it provides the power source for the SPDA to distribute to the different systems based on the system distribution logic. The IGD (Integrated Generator Drive) is not mentioned in the question and therefore cannot be the correct answer.

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• 32.

### ____ 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.

• A.

Two

• B.

Four

A. Two
Explanation
Two 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. This means that in this particular scenario, there are two independent SPDAs that are being used to replace the thermal circuit breakers and electromechanical relays. This helps to reduce the amount of electrical hardware needed and also reduces the workload for the flight crew.

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• 33.

### Some thermal CBs are located ...

• A.

On the cockpit sidewall panels and others inside the ICCs in the electronics bays.

• B.

Inside the SPDAs, in the electronics bays.

A. On the cockpit sidewall panels and others inside the ICCs in the electronics bays.
Explanation
This answer suggests that thermal circuit breakers (CBs) are located in two different places. Some are located on the cockpit sidewall panels, while others are located inside the Integrated Control Centers (ICCs) in the electronics bays.

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• 34.

### The electronic CBs are located ...

• A.

On the cockpit sidewall panels and others inside the ICCs in the electronics bays.

• B.

Inside the SPDAs, in the electronics bays.

B. Inside the SPDAs, in the electronics bays.
Explanation
The correct answer is inside the SPDAs, in the electronics bays. This means that the electronic circuit breakers (CBs) are located inside the Solid-state Power Distribution Assemblies (SPDAs) which are in the electronics bays. Additionally, it suggests that there may be other CBs located on the cockpit sidewall panels and inside the Integrated Control Centers (ICCs) in the electronics bays as well.

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• 35.

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

ICC, icc
Explanation
The ICC (Integrated Control Center) and icc (integrated control center) are the correct remote thermal circuit breakers that can only be reset by maintenance personnel when the airplane is on the ground. These circuit breakers are designed to ensure the safety and proper functioning of the aircraft's electrical systems. Resetting them requires specialized knowledge and can only be done during maintenance procedures to prevent any potential risks or malfunctions while the aircraft is in the air.

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• 36.

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

SPDA, spda
Explanation
The flight crew can reset the SPDA (Special Purpose Data Acquisition) remote electronic circuit breakers via the MCDU (Multipurpose Control and Display Unit). This means that they can use the MCDU to reset any SPDA circuit breakers that may have tripped or malfunctioned during the flight. The SPDA circuit breakers are an important part of the aircraft's electrical system, and being able to reset them remotely helps to ensure the safe operation of the aircraft.

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• Dec 18, 2023
Quiz Edited by
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• Jun 07, 2011
Quiz Created by
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