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‐ Generates a reference frequency used by GCU for synchronisation before No Break Power
Transfer (NBPT).
EMERGENCY GENERATOR
Applicable to:
The green hydraulic circuit drives an emergency generator that automatically supplies emergency
AC power to the aircraft electrical system, if all main generators fail. This generator supplies 5.5 KVA
of three-phase 115 V/200 V 400 Hz power, except when the Ram Air Turbine powers the green
hydraulic circuit, and the aircraft speed is below 260 kt; in this case, the emergency generator
supplies 3.5 KVA, leading to some shedding.
A generator control unit (GCU) :
‐ Keeps the emergency generator at a constant speed.
‐ Controls the generator's output voltage.
‐ Protects the network by controlling the emergency generator line contactor.
‐ Controls the emergency generator start-up.
EMERGENCY GENERATOR
Applicable to: ,
The green hydraulic circuit drives an emergency generator that automatically supplies emergency
AC power to the aircraft electrical system, if all main generators fail. This generator supplies 8.6 KVA
of three-phase 115 V/200 V 400 Hz power, except when the Ram Air Turbine powers the green
hydraulic circuit, and the aircraft speed is below 260 kt; in this case, the emergency generator
supplies 3.5 KVA, leading to some shedding.
A generator control unit (GCU) :
Keeps the emergency ‐ generator at a constant speed.
‐ Controls the generator's output voltage.
‐ Protects the network by controlling the emergency generator line contactor.
‐ Controls the emergency generator start-up.
STATIC INVERTER
Applicable to: ALL
A static inverter transforms DC power from the DC ESS bus into 2.5 KVA of single-phase
115 V400 HzAC power, which is then supplied to part of the AC essential bus. In flight, the inverter
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OPERATING MANUAL
AIRCRAFT SYSTEMS
ELECTRICAL
DESCRIPTION - GENERATION OF ELECTRICAL POWER
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is automatically activated, if nothing but the batteries is supplying electrical power to the aircraft,
regardless of the position of the BAT 1 and BAT 2 pushbuttons.
On ground, the inverter is activated, if only the batteries are supplying electrical power to the aircraft,
and both BAT 1 and BAT 2 pushbuttons are on.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
ELECTRICAL
DESCRIPTION - GENERATION OF ELECTRICAL POWER
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OPERATING MANUAL
AIRCRAFT SYSTEMS
ELECTRICAL
DESCRIPTION - GENERATION OF ELECTRICAL POWER
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DC GENERATION
TRANSFORMER RECTIFIERS (TR)
Applicable to: ALL
Two main Transformer Rectifiers TR1 and TR2 (200 A) and one essential TR (100 A), supply the
aircraft’s electrical system with DC current.
A fourth TR (100 A) is dedicated to APU start or APU battery charging.
Each TR controls its contactor by internal logic.
BATTERIES
Applicable to: ALL
Two main batteries, each with a normal capacity of 37 Ah, are permanently connected to the two hot
busses.
An identical third battery (37 Ah) is dedicated to APU start.
Each battery has an associated Battery Charge Limiter (BCL).
The BCL monitors battery charging and controls its battery contactor.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
ELECTRICAL
DESCRIPTION - GENERATION OF ELECTRICAL POWER
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OPERATING MANUAL
AIRCRAFT SYSTEMS
ELECTRICAL
DESCRIPTION - GENERATION OF ELECTRICAL POWER
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CONTACTORS
GENERAL
Applicable to: ALL
Two identical Electrical Contactor Management Units (ECMUs) provide:
AC and DC contactors control (excepted TR contactors, ‐ which are controlled by the TR itself).
‐ Galley shedding control.
‐ No Break Power Transfer control (NBPT).
‐ Monitoring and indicating.
For this purpose, each ECMU receives the following information:
‐ Voltage of all normal busbars
‐ Position of all AC and DC contactors
‐ Availability of all generators, or power source (from GCU or GPCU)
‐ Position of all galleys' contactors
‐ TR status
‐ Pushbutton position (BUS TIE, GALLEY SHED and COMMERCIAL)
‐ Flight/ground signal from associated LGCIU.
AC AND DC CONTACTOR CONTROL
Applicable to:
ECMU 1
controls :
: ‐ The Generator Line Contactor (GLC) 1.
　
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