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FCOM System Description > 6. Electrical > Flashcards

6. Electrical Flashcards

1
Q

TR UNIT Light

A
  • On the ground: Any TR failed,
  • In flight: TR1 or TR2 and TR3 failed
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2
Q

ELEC Light

A
  • Fault existsin DC or Standby Power system,
  • Operates only on the ground
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3
Q

BAT Switch OFF

A
  • Removes power from Battery Bus and Switched Hot Battery Bus during normal operation,
  • Removes power from Battery Bus, Switched Hot Battery Bus, DC Standby Bus, Static Inverter and AC Standby Bus when Battery is only power source
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4
Q

CAB/UTIL Switch ON

A

Supplies power to:
- All 115V AC Galley Busses
- Recirculation Fans,
- Door Area heaters,
- Drain Mast heaters,
- Lavatory Water heaters,
- Logo lights,
- Potable Water Compressor,
- Shaver outlets,
- LED Cabin Lighting

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5
Q

DRIVE Light

A

IDG Low Oil Pressure caused by:
- IDG failure,
- Engine shutdown,
- IDG automatic disconnect due to high oil temperature,
- IDG disconnected through DISCONNECT switch

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6
Q

DISCONNECT Switches

A

Disconnects IDG if:
- Electrical power is available and,
- Engine Start Lever is in IDLE

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7
Q

STANDBY PWR OFF Light

A

One or more of the following busses are unpowered:
- AC Standby Bus,
- DC Standby Bus,
- Battery Bus

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8
Q

STANDBY POWER Switch

A

AUTO:
- Automatic switching from normal to alternate when,
- Power from AC Transfer Bus 1 or DC Bus 1 is lost

BAT:
- Overrides automatic switching and,
- Places AC, DC Standby Busses and Battery Bus on Battery power,
- BAT switch maybe On or OFF (if OFF Switched Hot Battery Bus is not powered)
OFF:
- STANDBY PWR OFF light illuminates,
- AC Standby Bus, Static Inverter and DC Standby Bus are not powered

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9
Q

BUS TRANSFER Switch

A

AUTO:
-DC Cross Tie Relay automatically provides normal or isolated operation,

OFF:
- Isolates AC Transfer Bus 1 from 2 if one IDG is supplying power to both AC Transfer Busses,
- DC Cross Tie Relay opens to isolate DC Bus 1 from 2,
- Inhibits TR3 input from connecting to AC Transfer Bus 1

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10
Q

AC Power Supply

A
  • 2 IDGs produce 115V, 400Hz,
  • IDGs supply their own busses and also opposite bus as well in case of an IDG failure,
  • APU operates a generator and can supply both AC Transfer Busses
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11
Q

Basic Principles of Electrical System

A
  • No parelleling of the AC sources of power,
  • The source being connected to a Transfer Bus automatically disconnects an existing source
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12
Q

Ground Service

A

Without powering all airplane busses, it provides power directly to the AC Ground Service Busses for:
- Utility outlets,
- Cabin lighting,
- Battery charger

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13
Q

AC Power System

A
  • Each consists of: Transfer Bus, Main Bus, 2 Galley Busses and Ground Service Bus,
  • Transfer Bus 1 also supplies power to the AC Standby Bus,
  • If AC source of a Transfer Bus fails or disconnected, that bus can be powered by any available source via BTB,
  • BTB: Bus Tie Breaker,
  • It’s not possible to power one Transfer Bus with External Power and one another with APU,
  • If an Engine Generator no longer supplies power, BTB automatically closes to allow the other Generator to supply both Transfer Busses
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14
Q

Generator On-line Feature

A
  • In case airplane takes off with APU powering both Transfer Busses,
  • If APU is shut down or fails, Engine Generators automatically connected to their related Transfer Busses,
  • Occurs only once in flight
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15
Q

Automatic Load Shedding

A

Engine Generators:
- Galley and Main Bus on Transfer Bus 2 are shed first,
- If an overload still sensed, Galley and Main Bus on Transfer Bus 1 are shed,
- If an overload still sensed IFE Busses are shed,
- Manual restoration of Galley and Main Busses can be attempted by recycling CAB/UTIL switch

APU Generator:
- Inflight if APU is the only electrical power source,
- All Galley and Main Busses are automatically shed,
- If an overload still sensed, both IFE Busses are automatically shed,
- On the ground APU attempts to carry a full electrical load,
- If an overload is sensed, Galley and Main Busses are shed until the load is within limits,
- Manual restoration of Galley and Main Busses can be attempted by recycling CAB/UTIL switch

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16
Q

IDG

A
  • Integrated Drive Generator,
  • Contains the Generator and Drive in a common housing,
  • Lubricated and cooled by self-contained oil system,
  • An integral electro-mechanical disconnect device allows for a complete mechanical isolation of the IDG
17
Q

DC Power Supply

A
  • 28V DC Power is supplied by 3 TR units, which are energized from the AC Transfer Busses,
  • Battery provides DC Power when no other source is available
18
Q

TR

A
  • Transformer Rectifiers,
  • Converts 115V AC to 28V DC,
  • Any 2 TRs are capable of supplying the total connected load
19
Q

TR Power Sources

A
  • TR1: Transfer Bus 1,
  • TR2: Transfer Bus 2,
  • TR3: Transfer Bus 2 and backup from 1 (When BUS TRANSFER Switch in AUTO)
20
Q

TRs Power Output

A

Under normal conditions:
- DC Bus 1, 2 and DC Standby Bus connected via the Cross Bus Tie Relay,
- TR1 and 2 supplies DC Bus 1 & 2 and DC Standby Bus,
- TR3 supplies the Battery Bus and serves as a backup for TR1 & 2

21
Q

Cross Bus Tie Relay Open

A

When:
- BUS TRANSFER switch OFF,
- G/S capture during F/D or Autopilot ILS approach: this isolates DC busses to prevent a single failure from affecting both navigation receivers and FCCs

22
Q

Battery Power Supply

A
  • Dual 24V Nickel-Cadmium batteries, man and auxiliary, located in the Electronics Compartment,
  • Battery voltage range: 22-30V,
  • Can supply any part of the DC system,
  • Auxiliary operates in parallel with the Main Battery when Battery is powering Standby System,
  • At all other times Auxiliary Battery is isolated from power distribution system,
  • Two fully charged batteries supply Standby Power for a minimum of 60 minutes,
23
Q

DC Busses Powered From Battery During Standby Operation

A
  • Battery Bus,
  • DC Standby Bus,
  • Hot Battery Bus,
  • Switched Hot Battery Bus
24
Q

Switched Hot and Hot Battery Busses Power

A
  • Switched Hot Battery Bus: Powered when Battery switch is ON,
  • Hot Battery Bus: Always connected to Battery
25
Q

Battery Chargers

A
  • They are also TRs,
  • Main Battery Charger supplied by AC Ground Service Bus 2,
  • Auxiliary Battery Charger supplied by AC Ground Service Bus 1,
  • Following completion of primary charge cycle, Main Battery Charger reverts to constant voltage TR mode
26
Q

Battery Chargers Power Output

A
  • Following completion of primary charge cycle, Main Battery Charger reverts to constant voltage TR mode,
  • In normal TR mode it supplies Hot and Switched Hot Battery Bus,
  • If TR3 fails it also supplies Battery Bus,
  • If AC Transfer Bus or power source of DC Bus 1 fails, AC and DC Standby Busses powered by BOTH Chargers
27
Q

Standby Power System Supply in Normal Conditions

A
  • AC Standby Bus: AC Transfer Bus 1,
  • DC Standby Bus: TR1, 2 and 3,
  • Battery Bus: TR3,
  • Hot and Switched Hot Battery Bus: Main Battery and its Charger
28
Q

Standby Power System Supply Alternate Operation

A
  • AC Standby Bus: Batteries via Static Inverter,
  • DC Standby Bus: Directly from Batteries,
  • Battery Bus: Directly from Batteries,
  • Hot and Switched Hot Battery Bus: Directly from Batteries
29
Q

Static Inverter

A
  • Converts 24V DC power from Battery to 115V AC power,
  • Supplies AC Standby Bus during the loss of normal electrical power,
  • Power supply to the Inverter is controlled by the STANDBY POWER and BAT switches
30
Q

All Generator Inoperative Operative Items

A

Airplane General:
- Oxygen Systems,
- Dome Lights and STBY Compass Light,
- Emergency Instrument Flood Lights,
- Standby FWD Airstair

Air Systems:
- PACK valves and lights,
- BLEED TRIP OFF lights,
- Manual Pressurization Control,
- Cabin altitude warning horn and CABIN ALTITUDE lights

Anti-ice:
- CPTs Pitot Probe Heat,

Communications:
- Flight and Service Interphone system,
- PA system,
- VHF No. 1

Electrical:
- STANDBY POWER OFF light

Engines, APU:
-Upper Display Unit (all engine and fuel indications except Vibration),
- Thrust Reversers,
- Starter Valves,
- Right Igniters,
- APU operation (start attempts not recommended above 25000FT)

Fire Protection:
- APU and Engine Fire Extinguisher Bottles,
- APU and Engine Fire Detection System,
- Cargo Fire Extinguisher Bottle

Flight Instruments:
- CPT DUs (only PFD on outer for 700),
- Both Clocks,
- Left EFIS panel,
- Standby Instruments

Flight Management, Navigation:
- Left FMC, CDU,
- VHF, ILS, GLS, ADF, DME and Transponder No. 1,
- Heading/Track indications,
- Left IRS, GPS,
- Marker Beacon

Fuel:
- Crossfeed, Engine Shutoff and Spar Fuel Shutoff Valves,
- ENG VALVE and SPAR VALVE CLOSED ligts,
- Fuel Quantity indicators

Hydraulic Power:
- Engine Hydraulic Shutoff Valves,
- Standby Rudder Shutoff Valves

Landing Gear:
- Inboard Antiskid system,
- ANTISKID INOP light,
- Parking Brake,
- Air/Ground system,
- Landing Gear Indicator lights

Warnings:
- Stall Warning System,
- Aural Warnings,
- Master Caution Light Recall

31
Q

All Generator Inoperative Important Inop Items (Sim Experience)

A
  • Flap indicator,
  • Flap Asymetry Protection,
  • Radio Altimeters,
  • Only Main Tanks Fuel is usable via suction feeding (flameout is possible at high altitudes),
  • Thermal Anti-icing,
  • Electric Stabilizer trim,
  • Rudder Pedal NWS,
  • Autobrake and Auto Speed Brake

FCOM System Description (10 decks)

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