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Phenom Info > Electrical System > Flashcards

Electrical System Flashcards

1
Q

What bus bars are powered during the electrical emergency?

A

In an electrical emergency the top 4 busbars are powered.

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2
Q

What else does the left GCU do?

A

The left GCU samples ground power

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3
Q

Where are the busbars located?

A

Within the PDU’s

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4
Q

When are the bus bars powered?

A

When both generators are online all Bus Bars are powered
If ground power is online both busbars are powered

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5
Q

What happens if I lose one generator?

A

The shed bus is unpowered.

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6
Q

What happens if you lose both generators?

A

In flight when you lose both generators only the top four bus bars would be powered by the batteries. Embraer calls that the Electrical Emergency.

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7
Q

What are the generators restricted to in Flight and on the Ground?

A

In flight 300A
On the Ground 250A
Above 34,000 ft 250A due to air density

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8
Q

What does the GPU need to be?

A

24.5 V DC to 29 V DC, (800/1000) A
the electrical control panel GPU switch will show a white AVAIL indication when these parameters are met.

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9
Q

How many busbars and how are they composed?

A

2 × Main Bus - connected by Central Bus
2 × Hot Battery Bus
1 × Emergency Bus
1 × Shed Bus

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10
Q
A

EBC2 only closes during the Electrical Emergency

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11
Q

When should the batteries be green?

A

Between 27V to 29V

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12
Q

What must the ground power be to charge the batteries?

A

27V and above

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13
Q

What is the name of the Phenoms Electrical System?

A

Electrical Power Generation Distribution System (EPGDS)

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14
Q

What is the purpose of the EPGDS?

A

To provide the DC power to the aircraft systems and power for automatic and manual controls to the flight crew.

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15
Q

How is the EPGDS separated?

A

The EPGDS is separated into power generating systems and power distribution systems.
These systems can be divided into main and emergency power generation and primary and secondary power distribution. Normal operation of the electrical system is automatic.

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16
Q

What is the main power generating system?

A

The main power generating system is composed of two engine driven 325A (Capped at 300A for us) starter/generators and one external power unit connection, controlled by two Generator Control Units (GCUs).

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17
Q

What is the purpose of the Starter/Generator?

A

The starter/generators are used as a primary source of the DC electrical system supplying power to their respective DC BUS.

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18
Q

What is the secondary system composed of?

A

The secondary power distribution system is composed of two main Circuit Breaker (CB) panels, two secondary circuit breaker panels and two relay panels.

19
Q

What happens in the event of a power generating source failure?

A

Bus ties automatically connect between the networks with no significant operational degradation or additional workload.

20
Q

What are the EPGDS components?

A

Battery 1/Battery 2
Generator Control Units (GCUs)
Starter/Generators
Power Distribution Units
Emergency Power Distribution Unit (EPDU)
Circuit Breakers

21
Q

Where is battery 1 located?

A

Battery 1 is located in the forward compartment, which is a non-controlled environment, and can be accessed by removing the access panel in the forward baggage compartment. Its vent valves require the installation of ventilation tubes to avoid unsafe hydrogen accumulation inside the aircraft fuselage

22
Q

Where is Battery 2 Located?

A

Battery 2 is located in the aft compartment and can be accessed by opening battery compartment access door. Its vent valves do not require the installation of ventilation tubes, but its compartment requires ventilation overboard to avoid unsafe hydrogen accumulation inside the aircraft fuselage

23
Q

What are the purpose of the Generator Control Units (GCU’s)?

A

Operate the primary power distribution system contactors
Regulate, control, and provide protection functions for:
Electrical generating system
Perform power-up
Continuous BIT testing

Eliminate system disturbances (voltage dips and surges associated with start, cross-start assist and start-terminate)
Isolate faults
Provide system fault indication

24
Q

How do the Starter/Generators operate?

A

Each engine has a 28 V DC, 325 A SG monitored and controlled by a dedicated GCU. When an engine is successfully started, the SG will automatically come on line, powering the respective DC BUS. If the previous power source was a GPU, then the SG does not come on line until the GPU is disconnected from the CENTRAL BUS.

25
Q

What are the Power Distribution Comprised of?

A

They are comprised of contactors, relays, CBs, fuses and DC electrical buses.

26
Q

What Electrical Buses do the PDU’s power?

A

Left PDU:
DC BUS 1
CENTRAL BUS

Right PDU:
DC BUS 2
CENTRAL BUS
SHED BUS
HOT BATT BUS 2

27
Q

Where does the Emergency Power Distribution Unit provide power?

A

EMERGENCY BUS
HOT BATT BUS 1

28
Q

How long does the Battery system guarantee in the total loss of the main power generating system?

A

The battery system guarantees 45 min of uninterrupted power for the aircraft loads on the EMERGENCY BUS.

29
Q

How is the EPGDS Distribution controlled?

A

Essential contactors controlled by hardware logic:
Battery Contactors - BC 1 and BC 2
Emergency Bus Contactors - EBC 1 and EBC 2
Quiet Start Contactor - QSC

Non-essential contactors controlled by the GCUs:
Generator Line Contactors - GLC 1 and GLC 2
Ground Power Contactor - GPC
Start Contactors - SC 1 and SC 2
Bus Tie Contactors - BTC 1 and BTC 2
Shed Bus Contactor - SBC

30
Q

In normal operation what do the generators power?

A

Left engine starter generator (SG 1) powers DC BUS 1, EMERGENCY BUS and HOT BATT BUS 1
Right engine starter/generator (SG 2) powers DC BUS 2, CENTRAL BUS, SHED BUS and HOT BATT BUS 2
The EPGDS manages the power source priority between the aircraft starter-generators and the external power source

31
Q

What does the Electrical Power System (EPS) supply?

A

All electrical systems
Power secondary flight controls (trims and flaps) and autopilot
Assists powering mechanical and hydraulic components and electric pumps for operation of landing gear, spoilers and wheel brakes
Feeds the inverter to provide AC electrical power

32
Q

What is the Electrical Power System (EPS) comprised of?

A

Battery 1 and 2 switches (On/Off)
Generator 1 and 2 switches (On/Off)
GPU button
BUS TIE knob
ELEC EMER guarded button (In/Out)

33
Q

What does the GPU button on the Electrical Power System (EPS) do?

A

IN - GPU connected to Central Bus, indication In Use
OUT- Isolated from bus
The GPU switch ‘AVAIL’ light illuminates when a GPU is plugged into the aircraft GPU socket and its voltage is within limits for connection to the system CENTRAL BUS (voltage between 24.5 and 29 V DC)

34
Q

What does the BUS TIE knob on the Electrical Power System (EPS) do?

A

AUTO - allows the EPGDS to automatically operate the BTC1 and BTC2
1 OPEN - opens the BTC1 isolating DC BUS 1 and allows the BTC2 automatic operation
2 OPEN - opens the BTC2 isolating DC BUS 2 and allows the BTC1 automatic operation

35
Q

What does the ELEC EMER guarded button (In/Out): on the Electrical Power System (EPS) do?

A

IN - overrides the EPGDS automatic transfer to the electrical emergency circuitry, connecting the batteries directly to the EMERGENCY BUS, regardless of any other command from the Electrical Distribution Logic. The button is illuminated when in
OUT - the power contactors operate automatically according to the Electrical Distribution Logic

36
Q

How are Battery Voltages Displayed on the EPS Diagnostic screen on the MFD?

A

GREEN - Voltage is ≥27 V and ≤29 V
WHITE - Voltage is >10 V and <27 V, or >29 V
YELLOW - Voltage is ≤10 V
RED X - Voltage is 0 or >40 V, or parameter monitoring loss

37
Q

What is the Minimum Battery Voltage for Engine Start?

A

24 V

38
Q

What is the Minimum GPU voltage for BATT Charge?

A

27V

39
Q

What is the Maximum Generator Load - Ground?

A

250 A each

40
Q

What is the Maximum Generator Load - In Flight (above/below 34 000 ft)?

A

250 A each/300 A each

41
Q

When can the batteries be charged with the GPU?

A

provided the GPU voltage is between 27 and 29 V DC. If GPU voltage drops below 27 V DC, the batteries are not charged and the CAS message BATT DISCHARGE will be displayed.

42
Q

How do you connect the GPU to the aircraft system, and start the engine?

A

Switch ON BATT 1 and BATT 2
Press the GPU button (AVAIL) to connect the GPU to the aircraft system
Confirmation is given by the GPU button IN USE indication; the PFD displays the CAS Advisory Message, GPU CONNECTED
When the engine has completed the start-up cycle, disconnect the GPU from the system by pushing the GPU switch again.

43
Q

Engine Start Procedure concerns

A

Avoid starting the engine with tail winds speeds higher than 10 Kts. It may lead to engine surge, ITT Exceedances and Exhaust Burns

If any starting limit is exceeded, do not attempt further starts and report to the maintenance personnel

If a hung or no start occurs, accomplish the Dry Motoring Procedure before attempting another start to reduce hot starts occurrence

If the batteries have been cold soaked for 2 hours or longer, at ambient surface temperature of -18 °C (0 °F) or lower, they must be preheated to above -18 °C (0 °F) prior to engine start

Phenom Info (35 decks)

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