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Mesa EJET > Electrical System > Flashcards

Electrical System Flashcards

1
Q

IDG 1 and IDG 2 Selector Knob

-AUTO

A

This position allows the IDG contactor to close, connecting the IDG to the respective AC BUS automatically, according to system logic

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2
Q

IDG 1 and IDG 2 Selector Knob

-OFF

A

Opens the IDG contactor isolating the IDG from the respective AC BUS

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3
Q

IDG 1 and IDG 2 Selector Knob

-DISC

A

Must be held in this position for one second to mechanically disconnect the IDG

Can’t be reconnected in flight

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4
Q

Normal AC Bus Priority

A

Onside IDG
AC BUS Tie
Offside IDG

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5
Q

Illumination of the Amber LED next to IDG DISC

A

Indicates to which pilot which IDG to disconnect

Will illuminate in association with the IDG 1(2) caution EICAS message & will extinguish when IDG is disconnected.

HOTLOP
-High oil temperature or Low oil pressure

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6
Q

AC BUS TIES Selector Knob

-1 OPEN

A

Opens the Bus Tie Contactor (BTC) 1, segregating AC BUS 1 from the AC BUS Tie

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7
Q

AC BUS TIES Selector Knob

-AUTO

A

This position allows automatic operation of the BTC’s according to system logic

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8
Q

AC BUS TIES Selector Knob

-2 OPEN

A

Opens the Bus Tie Contactor (BTC) 2, segregating AC BUS 2 from the AC BUS TIE

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9
Q

AC BUS Tie Priority

A

APU
GPU
IDG

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10
Q

GPU Button

-PUSH IN

A

Connects the AC GPU to the AC BUS Tie, according to the source priority

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11
Q

GPU Button

-PUSH OUT

A

Isolates the AC GPU from the AC BUS Tie

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12
Q

GPU Button

-AVAIL Light

A

AVIL will illuminate with the button pushed in or out when the AC GPU is connected, but is not powering the AC BUS Tie. Also indicates GPU is set to correct power setting.

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13
Q

GPU Button

-IN USE Light

A

Will only illuminate when button is pushed in & the AC GPU is powering the AC BUS Tie

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14
Q

APU GEN Button

-PUSH IN

A

This position allows the APU generator to connect to the AC BUS Tie, automatically according to source priority

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15
Q

APU GEN Button

-Push OUT

A

Opens the APU generator contactor and isolates the APU generator from the AC BUS Tie. The APU is tripped off line and de-excited

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16
Q

TRU ESS Toggle Switch

-AUTO

A

This position allows automatic connection of the TRU ESS to the DC ESS BUS 3

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17
Q

TRU ESS Toggle Switch

-OFF

A

Isolates the TRU ESS from DC ESS BUS 3

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18
Q

TRU 1 and TRU 2 Toggle Switches

-AUTO

A

This position allows automatic connection of the TRU 1(2) to the respective DC BUS 1(2)

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19
Q

TRU 1 and TRU 2 Toggle Switch

-OFF

A

Isolates the TRU 1(2) from the respective DC BUS 1(2)

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20
Q

BATT 1 Selector Knob

-ON

A

The battery is connected to the DC ESS BUS 1

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21
Q

BATT 1 Selector Knob

-OFF

A

The battery supplies power to HOT BATT BUS 1 only

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22
Q

DC BUS TIES Toggle Switch

-AUTO

A

This position allows automatic operation of the DC Tie contactor’s (1 DCTC / 1 & 2 ETC’s) according to system logic

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23
Q

DC BUS TIES Toggle Switch

-OFF

A

Opens all DC Tie contactors

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24
Q

BATT 2 Selector Knob

-AUTO

A

This position connects BATT2 to either the DC ESS BUS 2 or the APU START BUS automatically, according to system logic

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25
Q

BATT 2 Selector Knob

-OFF

A

The battery supplies power to HOT BATT BUS 2 only

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26
Q

AC Power

A 
2 IDG's (115 VAC, 400 Hz, 40 KVA)
1 APU (115 VAC, 400 Hz, 40 KVA)
1 AC GPU (115 VAC, 400 Hz, 40 KVA)
1 RAT (115 VAC, 400 Hz, 15 KVA)
1 Inverter (250 V)
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27
Q

1 IDG can power both AC Buses

A

On ground & In-flight

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28
Q

APU can power both AC Buses

A

On ground & In-flight up to FL330

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29
Q

GPU can power both AC Buses

A

On ground only

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30
Q

Primary source of AC power

A

IDG

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31
Q

IDG Selector Knob

A

AUTO- System logic controls contactor
OFF- Opens contactor
DISC- Mechanically disconnects the CSD from IDG

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32
Q

Can the flight crew reconnect an IDG

A

No, maintenance function only

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33
Q

Amber Light accompanied by an EICAS oil message indicates?

A

IDG disconnect is required

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34
Q

ICC

A

Integrated Control Center (4)

-Line replaceable

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35
Q

SPDA

A

Secondary power distribution assembly (2)

  • An electric load management unit
  • Receives power from ICC’s
  • Distributes power according to system logic
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36
Q

CSD

A

Constant speed drive

Converts variable engine speed into constant generator speed

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37
Q

IDG oil system is cooled how?

A

Air cooled

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38
Q

GCU

A

Generator control unit

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39
Q

Illumination of the amber LED next to IDG DISC indicates?

A

HOTLOP

-High oil temperature or low oil pressure

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40
Q

APU

A

Auxiliary Power Unit

-Secondary source of AC Power

41
Q

Required for APU Start?

A

BATT 1 & 2 or BATT 1 & DC GPU

42
Q

Which BATT is used to control APU’s FADEC?

A

BATT 1

43
Q

Why is BATT 2 isolated from the network during APU start?

A

To exclusively power the APU START BUS

44
Q

Minimum VDC for APU Start?

A

22.5 VDC

45
Q

Minimum VDC required to close batter contactor?

A

18.0 VDC

46
Q

Minimum BATT 2 temperature for start?

A

-20 C

47
Q

AC GPU

A

AC Ground Power Unit

-Secondary AC power source

48
Q

GPU power can be turned on in 3 locations

A
  • Cockpit Overhead Panel
  • AC GPU Panel (only powers ground service bus)
  • Opposite FWD Lav (only powers ground service bus)
49
Q

Normal AC Electrical Priority

A

On-side IDG
APU
GPU
Cross-side IDG

50
Q

Inverter

A
  • Powers the AC STANDBY BUS when normal AC power source is not available
  • Allows “A” igniters to always have power source
51
Q

RAT

A
  • Ram Air Turbine
  • Emergency AC Power source
  • No restriction for deployment
  • Manual deployment available
52
Q

RAT supplies power to which BUS

A

AC ESS BUS

53
Q

Minimum airspeed for RAT

A

130 knots

-As airspeed decreases, load shedding occurs until AC ESS BUS is not longer powered

54
Q

DC power provided by?

A

Transformer Rectifier Unit (TRU)
-28 VDC, 300 A

2 Batteries
-24 VDC, 27 AH

1 DC GPU
-28 VDC

55
Q

Primary source of DC power?

A

TRU’s

56
Q

Function of TRU

A

Convert 115 VAC to 28 VDC

57
Q

RAGO

A

AC System Priority

R- Respective IDG
A- APU
G- GPU
O- Opposite IDG

58
Q

Electrical Emergency Situation

-Batteries Only

A
  • Screen 2 (PFD)
  • Screen 3 (EICAS)
  • IESS
  • Clock
  • FO MCDU
  • CA CCD
  • 2 Comm panels
  • CA Display panel
  • CA Reversionary panel
  • Light for magnetic compass
59
Q

DC HOT BATT BUS 1

A
  • Engine 1A Fire Extinguisher
  • Engine 2A Fire Extinguisher
  • Engine Fuel SOV 1
  • Hydraulic system SOV 1
  • Engine 1 oil level indication
  • Courtesy / Service lights
  • DC ceiling lights
60
Q

DC HOT BATT BUS 2

A
  • Engine 1B Fire Extinguisher
  • Engine 2 B Fire Extinguisher
  • Engine Fuel SOV 2
  • Hydraulic system SOV 2
  • Engine 2 oil level indication
  • CMC
  • Panel refuel
  • Water and waste system
61
Q 
EPC
BATT 1(2) Over temp
A

Associated Battery…………………………OFF

Note– Do not start the APU

62
Q

Batteries

A

(2) NiCad Batteries
- Secondary source of DC power
- Back-up for DC ESS BUS
- Charged via any AC power source through TRU’s
- 18.0 volt min to close battery contactor
- Will provide 10 minutes of power during an electrical emergency

63
Q

DC GPU

A
  • Can replace BATT 2 during APU start

- Can only be turned on by a ground ramp button

64
Q

Function of ICC’s and SPDA’s

A

ICC’s collect and confirm the power is safe and then sends it to the SPDA’s, which distributes it

65
Q

How many networks make up the electrical system on the airplane? Why?

A

2 independent networks for redundancy and fault isolation

66
Q

What happens if a power generating source fails?

A

Bus ties automatically connect to provide no system degradation

67
Q

What components power the AC system?

A 
1 IDG's
APU
Inverter
RAT
AC GPU
68
Q

What components power the DC system?

A

2 NiCad batteries
2 TRU’s
DC GPU

69
Q

How does the IDG maintain a stable power output?

A

A constant speed drive (CSD) attaches the IDG to the AGB (accessory gear box)

70
Q

What monitors and controls the IDG’s?

A

Each has a generator control unit

71
Q

Can one IDG power the entire electrical system?

A

Yes

72
Q

What will cause the amber IDG light on the overhead panel to illuminate?

A

High oil temp
Low oil pressure

HOTLOP

73
Q

If an IDG is manually disconnected can it be reconnected in flight?

A

No

74
Q

What is the primary purpose of the AC generators?

A

To power the AC BUSSES and AC ESS BUS which power the 3 TRU’s (1, 2 & ESS)

75
Q

What is the purpose of the TRU’s?

A

To convert 115 VAC to 28 VDC

76
Q

Can an APU replace a failed IDG?

A

Yes

77
Q

What is the AC electrical system’s priority?

A

Onside (IDG)
Inside (APU)
Outside (GPU)
Cross-side (Other IDG)

78
Q

How is it known that an AC GPU is hooked up to the airplane and ready to provide electricity?

A

GPU button displays AVAIL and the GPU icon is presented on the electrical synoptic page
-Once the GPU button is pushed in, the button will display IN USE provided another AC power source is not available

79
Q

What does it mean if the AC GPU is plugged in and the outside GPU panel button displays IN USE?

A
  • Ground service bus is in use

- Cockpit GPU button will display AVAIL even though the ground service bus is in use

80
Q

If the airplane is using the AC GPU and the APU is started what should the pilot be sure to do?

A

Deselect the GPU button before the next GPU connection

81
Q

What will charge the batteries?

A

Any AC power source

82
Q

How long will the aircraft’s batteries last with no recharging?

A

10 minutes

83
Q

What is the purpose of the DC GPU receptacle?

A

For APU start when batteries

84
Q

What is the minimum battery temp for APU start?

A

-20 C

85
Q

What is the minimum voltage to close the battery bus ties?

A

18 volts

86
Q

What battery is used for the APU start?

A

BATT 2 powers the APU Start Bus

BATT 1 powers the FADEC & EICAS for monitoring

87
Q

What is the purpose of the inverter?

A

Converts 28 VDC from the batteries to 115 VAC to power the AC STANDBY BUS when an AC source is not available

88
Q

What is on the AC STANDBY BUS?

A

Engine exciters 1A & 2A

89
Q

What powers the RAT?

A

Airflow turns the RAT propeller which spins the turbine inside

90
Q

When will the RAT deploy?

A

Automatically deploys if AC BUSSES are not powered or manually by pilot

91
Q

How long after deployment before the RAT will supply power?

A

8 seconds

92
Q

Is there a total loss of power during the 8 second RAT deployment?

A

No. Batteries supply power to the DC ESS BUSSES and AC STANDBY BUS

93
Q

What does the RAT power?

A

ESS BUSSES

94
Q

What is the minimum airspeed for the RAT?

A

130, load shedding occurs below this speed

95
Q

When is the RAT icon is displayed on the electrical synoptic page?

A

When the RAT is deployed

96
Q

What manages the electrical system?

A

4 Integrated Control Center’s (ICC) &

2 Secondary Power Distribution Assemblies (SPDA)

97
Q

What is an ICC?

A

An electrical control device which provides power distribution and protection for electrical loads

98
Q

What is an SPDA?

A

An electrical load-management unit (powered by the ICC’s) that distributes electrical loads to aircraft systems according to distribution logic

99
Q

Can the flight crew reset the ICC and SPDA remote electronic CB’s

A
  • ICC CB’s can only be reset by maintenance

- SPDA CB’s can be reset via the MCDU

Mesa EJET (10 decks)

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