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A340TECHNICAL TRAINING MANUAL

MECHANICS / ELECTRICS & AVIONICS COURSE

24 ELECTRICAL POWER

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This document must be used

for training purpose only.

Under no circumstances

should this document be used as a reference.

All rights reserved.

No part of this manual may be reproduced in any form,

by photostat, microfilm, retrieval system, or any other means,

without the prior written permission of Airbus Industrie.

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GENERAL

** Electrical System Introduction (1) 1............................

** Electrical System Location (1) 5..............................

** Electrical System Presentation (1) 9............................

** AC and DC ECAM Page Presentation (1) 15.........................

** System Control and Indicating (1) 35............................

** Emergency Elec System Ctl & Indicating (1) 39........................

AC GENERATION

** Elec System & Circuit Identification (3) 43..........................

** AC Main Generation (1) 47...............................

** AC Main Generation D/O (3) 51..............................

** AC Main Generation Transfer Circuit D/O (3) 55.......................

** Integrated Drive Generator (IDG) D/O (3) 59.........................

** IDG Generator Part D/O (3) 65..............................

_A340 TECHNICAL TRAINING MANUAL

24 ELECTRICAL POWERMECHANICS / ELECTRICS & AVIONICS COURSE

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F564200 TABLE OF CONTENTS

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** IDG Cooling D/O (3) 71.................................

** Integrated Drive Generator Monitoring (2) 75........................

** Generator Control Unit D/O (3) 79.............................

** APU Electrical Power (1) 85...............................

** AC Auxiliary Generation D/O (3) 91............................

** AC Emergency Generation (1) 97.............................

** AC Emergency Generation D/O (3) 101...........................

** CSM/G D/O (3) 105..................................

** CSM/G Control Logic (3) 109...............................

** Static Inverter Presentation (1) 113.............................

** Static Inverter D/O (3) 117................................

** AC ESS Generation Switching D/O (3) 121..........................

** Elec Contactor Management Sys Present (1) 125........................

** ECMU System D/O (3) 129................................

** AC Warnings and Operating Limitations (3) 145.......................



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** AC Generation Components (2) 149............................

** AC Generation Components (3) 165............................

EXTERNAL POWER

** External Power Supply (1) 177..............................

** External Power Supply D/O (3) 181............................

** Ground Power Ctl Unit (GPCU) D/O (3) 185.........................

** No Break Power Transfer D/O (3) 193...........................

** Inadvertent Paralleling Trip D/O (3) 197..........................

** AC and DC Ground Service Bus Control (3) 201........................

** External Power Components (2) 205............................

** External Power Components (3) 211............................

DC GENERATION

** DC Generation (1) 217.................................

** DC Main Generation D/O (3) 221.............................



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** DC Essential Generation D/O (3) 227............................

** Battery System D/O (3) 231...............................

** Battery Charge Limiter (BCL) D/O (3) 237..........................

** DC Normal Generation Switching D/O (3) 243........................

** DC Essential Generation Switching D/O (3) 247........................

** DC Warnings (3) 251..................................

** DC Generation Components (3) 255............................

SYSTEM OPERATION

** System Normal Operation (1) 271.............................

** System Abnormal Operation (1) 275............................

** System Emergency Operation (1) 279............................

CB MONITORING

** Circuit Breaker Monitoring Sys Pres (1) 283.........................

** Circuit Breaker Monitoring System D/O (3) 287........................



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** C/B Monitoring Warnings (3) 293.............................

** C/B Monitoring Component (3) 297............................

AC AND DC LOAD DISTRIBUTION

** AC Load Distribution (3) 303...............................

** DC Load Distribution (3) 313...............................

** Land Recovery D/O (3) 321...............................

** Refueling on Battery (1) 325...............................

** Galley Supply (1) 329..................................

** Galley Supply (3) 333..................................

** AC & DC Load Distribution Component (3) 341........................

MAINTENANCE PRACTICES

** IDG Servicing (2) 345..................................

** IDG Disconnection/Reconnection (2) 349..........................



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ELECTRICAL SYSTEM INTRODUCTION

AC Electrical SystemDC Electrical System

Emergency Electrical SystemAPU Start System

24 - ELECTRICAL POWER

DATE : APR 1994 Page 1 F24AA02



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AC ELECTRICAL SYSTEMThe entire Alternating Current (AC) Electrical System can be supplied byfour generators or by the Auxiliary Power Unit (APU) generator or byexternal power A and B.

Part of the AC network can be supplied via the static inverter or the

emergency generator in abnormal or emergency condition.

DC ELECTRICAL SYSTEMThe DC Electrical System is supplied from the AC network via transformerrectifiers.

Part of the DC network can be supplied from the batteries as a back-up

source.

EMERGENCY ELECTRICAL SYSTEM

The emergency generator is hydraulically driven by the green system and cansupply part of the Electrical System in case of loss of normal supply.

APU START SYSTEM

The Auxiliary Power Unit (APU) can be started by using the APU battery orthe APU transformer rectifier or both at the same time.





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STUDENT NOTES





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ELECTRICAL SYSTEM LOCATION

AC Normal GenerationAC Emergency Generation

Static InverterDC Normal GenerationDC Essential Generation


DATE : APR 1994 Page 1 F24AT02



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AC NORMAL GENERATIONThere are 4 engine driven Integrated Drive Generators (IDGs).

The IDG is an assembly with two parts :

- the drive : Constant Speed Drive (CSD)

- and the generator.

Each IDG is installed on the associated engine gearbox pad.

The Auxiliary Power Unit generator is located in the APU compartment.The external power receptacles are fitted behind the nose landing gear bay.

AC EMERGENCY GENERATION

The AC Emergency Generation consists of a Constant Speed Motor (CSM)and an AC generator which form an assembly called Constant SpeedMotor/Generator (CSM/G).

The CSM/G is located in the main landing gear wheel well.

STATIC INVERTER

The static inverter is located in the avionics compartment.

DC NORMAL GENERATION

The two main Transformer Rectifiers (TR1 and TR2), and the two mainbatteries (BAT1 and BAT2), are located in the avionics compartment.

The APU TR and the APU battery are located in the bulk cargo compartment.

DC ESSENTIAL GENERATIONThe ESSential TR is located in the forward left hand side of the avionicscompartment.





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STUDENT NOTES





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ELECTRICAL SYSTEM PRESENTATION

AC GenerationAC Emergency Generation

AC TransferAC DistributionDC GenerationDC Distribution

Static InverterExternal PowerService BusesGalleys

Self Examination


DATE : APR 1994 Page 1 F24AB02



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AC GENERATIONThe main Alternating Current (AC) Generation is provided by four IntegratedDrive Generators (IDG), one Auxiliary Power Unit (APU) generator and twoexternal power units.Each IDG is normally connected to its own busbar.

The entire aircraft network can be supplied by two of the four engine drivengenerators or by the APU generator or by the external power units but not bya single IDG.

AC EMERGENCY GENERATION

The emergency generator driven by the green hydraulic system provides ACpower in case of loss of AC BUS 1-1 and AC BUS 2-4.

AC TRANSFERAC transfer is automatically achieved by the transfer circuit and thecorresponding contactors.

AC DISTRIBUTIONNote:

In abnormal configuration (loss of AC BUS 1-1), the AC BUS 2-4automatically supplies the AC ESSential buses.

DC GENERATION

The Direct Current (DC) Generation is provided by four identicalTransformer Rectifiers (TRs 1, 2, ESSential and APU) and three identical

batteries (battery 1, 2 and APU).The APU TR and APU battery are only used to start the APU.Note :

In abnormal configuration (loss of AC BUS 1-1), the AC BUS 2-4automatically supplies the ESSential TR.

DC DISTRIBUTION

Note:In normal configuration there is no connection between DC BAT BUS

and DC BUS 2.The batteries are connected to the network through DC BAT BUSonly when the batteries need to be charged.The batteries are only used for back-up.

STATIC INVERTER

The static inverter is supplied from battery 1 and battery 2 and automatically

supplies the AC essential bus if no other power source is available.





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EXTERNAL POWERTwo external power units can supply the entire network via thetransfer circuit.

Note:With one External Power (EXT. PWR) connected, the System

Isolation Contactor (SIC) is closed.

SERVICE BUSES

The AC and DC service buses can be directly supplied from external powerA only.

GALLEYSThe galleys are supplied from the AC main buses.





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SELF EXAMINATION

AC essential buses are normally supplied by AC BUS 1-1. In abnormalconditions which AC BUS supplies AC essential buses?

A - AC BUS 1-2.B - AC BUS 2-3.C - AC BUS 2-4.

In normal configuration which source supplies DC BAT BUS ?

A - Batteries.

B - DC BUS I.C - DC BUS 2.





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AC AND DC ECAM PAGE PRESENTATION

AC Power SourcesAC Busbars

Transformer Rectifiers (TRs)GalleysAC EmergencyDC Power Sources

DC BusbarsBatteriesDC Emergency


DATE : JAN 1998 Page 1 F24AU01



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AC POWER SOURCESAll the sources used for AC generation are represented and provide thefollowing information:

- percentage of load- voltage- frequency and

- Integrated Drive Generator (IDG) oil outlet temperature.

The sources are the four Integrated Drive Generators (IDGs), Auxiliary

Power Unit generator (APU GEN), external power A and B (EXT A,EXT B), emergency generator (EMER GEN) and static inverter (STAT INV).

EXT A and EXT B are only displayed on ground.





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AC BUSBARSThe main and essential busbars are displayed and connected according to theaircraft supply configuration.

The busbars are displayed in green when supplied or in amber when notsupplied.

Note: SHED in amber comes into view if the AC ESS SHED BUS isno longer supplied.





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TRANSFORMER RECTIFIERS (TRs)The Transformer Rectifiers (TRs) are supplied by their related ACbusbars.

They are normally displayed in white, or in amber when failed.





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GALLEYSGalley and commercial indications on the bottom of the page provideinformation about the galley and commercial supply status.

Indications:

GALLEY PARTIALLY SHED means "some galleys switched off"

GALLEY SHED means "all galleys off"

COMMERCIAL OFF means "all galleys off and Service Bus not supplied".





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AC EMERGENCYIn emergency configuration, the emergency generator is represented andprovides voltage and frequency information.

The EMERgency GENerator is displayed in white or in amber when faulty.

In emergency configuration (loss of the emergency generator), the staticinverter is represented and provides voltage and frequency information.

The STATic INVerter is displayed in white or in amber when faulty.

The LND RCVRY indication appears in green when the land recovery P/Bswitch is pressed in.





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DC POWER SOURCESAll the sources used for the DC generation are represented and provide DCvoltage and load information.

The sources are the main Transformer Rectifiers (TR1 and TR2), the essentialTR (ESS TR) and APU TR all powered by the AC sources.

Note: ESS TR can also be supplied by AC BUS 2-4 or the emergencygenerator.





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DC BUSBARSThe main and essential busbar, as well as the APU and battery busbars, aredisplayed and connected according to the aircraft supply configuration.

They are displayed in green when supplied, otherwise in amber.

Note: SHED in amber comes into view when the DC ESS SHED BUSis no longer supplied.





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BATTERIES

The three batteries indicate voltage and load.

Arrows provide information about the charge or discharge status of thebatteries.

The arrow appears in green when the battery is in charge configuration or inamber when the battery is in discharge configuration.





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DC EMERGENCY

In emergency configuration, the emergency generator supplies the essentialtransformer rectifier.

EMER GEN is normally displayed in white, or in amber when faulty.

In batteries only configuration, the static inverter is supplied from thebatteries.

STAT INV is normally displayed in white, or in amber when faulty.





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SYSTEM CONTROL AND INDICATING

BAT 1(2 or APU) Selector SwitchBAT 1(2) Pushbutton Switch

APU BAT Pushbutton Switch

AC ESS FEED Pushbutton SwitchGalley Pushbutton SwitchCommercial Pushbutton Switch

IDG 1(2, 3 or 4) Pushbutton SwitchGEN 1(2, 3 or 4) Pushbutton SwitchAPU GEN Pushbutton SwitchBUS TIE Pushbutton Switch

EXT Power Pushbuttons


DATE : NOV 1997 Page 1 F24AD02



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BAT 1(2 or APU) SELECTOR SWITCH

The displayed battery voltage corresponds to the battery selector position(battery 1 or battery 2 or APU battery).

The selected voltage is always displayed.

BAT 1(2) PUSHBUTTON SWITCH

In normal configuration, the batteries are automatically connected ordisconnected according to the DC electrical configuration.

The FAULT light comes on amber in case of thermal runaway or shortcircuit.The OFF light comes on white if the BAT pushbutton is released out (battery

disconnected).

APU BAT PUSHBUTTON SWITCH

In normal configuration, the APU battery is automatically connected or

disconnected for battery charge or APU start.

The FAULT light comes on amber in case of thermal runaway or shortcircuit.

The OFF light comes on white if the BAT pushbutton is released out (batterydisconnected).

AC ESS FEED PUSHBUTTON SWITCH

In normal configuration, the AC ESSential BUS is supplied by AC BUS 1-1.In abnormal configuration (AC BUS 1-1 lost), the AC ESS BUS is

automatically supplied from AC BUS 2-4.The FAULT light comes on amber when the AC ESS BUS is no longersupplied.In case of an automatic transfer failure, the safety guarded AC ESS FEEDpushbutton must be released out, ALTN light comes on white and the AC

ESS BUS supply is transferred from AC BUS 1-1 to AC BUS 2-4.

GALLEY PUSHBUTTON SWITCH

In automatic mode, switch pressed in, the galleys are automatically suppliedor shed according to the electrical configuration. The commercial switch mustalso be pressed in.

The FAULT light comes on amber in case of generator overload detection

and automatic shedding not operating.The OFF light comes on white when the galley pushbutton is released out, soall the galleys are shed.

COMMERCIAL PUSHBUTTON SWITCH

The commercial pushbutton allows commercial loads (galleys, cabin lights,...)to be shed when it is released out.

The OFF legend comes on white.

IDG 1(2, 3 OR 4) (INTEGRATED DRIVE GENERATOR)

PUSHBUTTON SWITCH

The safety guarded IDG pushbutton allows the associated IDG to bedisconnected from the engine accessory gearbox.

The FAULT light comes on amber in case of oil low pressure or oil overheat..Immediate disconnection is required to avoid IDG damage.The OFF light comes on white when the IDG is disconnected.

NOTE : The white OFF legend remains on until IDG reset is done.



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GEN 1(2, 3 OR 4) PUSHBUTTON SWITCH

The GENerator pushbutton allows the associated generator to be connected ordisconnected from the aircraft network.

The FAULT light comes on amber in case of generator failure or engine notrunning.

When the GEN pushbutton is released out, the OFF/R light comes on white,the generator is disconnected and the fault circuit is reset.Note : /R stands for Reset.

APU GEN PUSHBUTTON SWITCHThe APU GENerator pushbutton allows the APU generator to be connectedor disconnected from the aircraft network.

The FAULT light comes on amber in case of generator failure.When the APU GEN pushbutton is released out, the OFF/R light comes onwhite, the generator is disconnected and the fault circuit is reset.

NOTE : When the APU is not running or in underspeed, the FAULT light is

inhibited.BUS TIE PUSHBUTTON SWITCH

The BUS TIE pushbutton switch controls the System Isolation Contactor(SIC) and the four Bus Transfer Conctactors (BTCs).In automatic mode, the SIC and the four BTCs automatically control thesupply transfer of the AC network according to the priority logic.

When released out, the OFF light comes on white and the SIC and the fourBTCs open.

CAUTION : The OFF light does not come on if the aircraft is on batteriesonly.In this case the message "BUS TIE P/B OFF" is displayed on the upperECAM.

EXT PWR PUSHBUTTONS

The EXTernal power pushbuttons A and B allow the external power sourcesA or B to be connected or disconnected. If the mechanical connection iscorrect and the external power parameters are normal, the AVAIL light comeson green.

When an EXT A or B springloaded pushbutton is pressed in, the associated(ON or AUTO) light comes on blue. The AVAIL light goes off. The externalpower A is in use, B is in use or available depending on the priority logic.NOTE : The APU generator has priority over the EXT PWR B.

When pressed again, the light goes off and the AVAIL light comes on green.The external power is disconnected.NOTE : If one of the external power parameters is abnormal, the external

power is disconnected and the ground power source is also switched off.



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EMERGENCY ELECTRICAL SYSTEM

CONTROL AND INDICATING

Emer Gen Test Pushbutton (Guarded)Land Recovery Pushbutton SwitchEmer Gen Fault LightMan On Pushbutton (Guarded)


DATE : APR 1994 Page 1 F24AS02


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EMER GEN TEST PUSHBUTTON (GUARDED)

Two tests can be performed using the EMER GEN TEST pushbutton :

1- If the green hydraulic system is pressurized and the EMER GEN TESTpushbutton switch is pressed in, the emergency generator runs and suppliesthe ESSential network.

2- If the green hydraulic system is not pressurized and no electrical power isconnected and the EMER GEN TEST pushbutton switch is pressed in, thestatic inverter is operative and supplies the AC ESSential bus only.

Check the results on the ECAM for both tests.

LAND RECOVERY PUSHBUTTON SWITCH

In case of electrical power emergency configuration, certain busbars are nolonger supplied.

When the LAND RECOVERY pushbutton switch is pressed in, the ON

legend comes on, the associated AC and DC land recovery sub-busbars arerecovered to supply systems for safe landing.

EMER GEN FAULT LIGHT

In case of electrical power emergency configuration, the FAULT light comeson red in case of emergency generator shutdown.

MAN ON PUSHBUTTON (GUARDED)

The emergency generator automatically starts when AC BUS 1-1 and ACBUS 2-4 are lost.

In case of failure of this automatic function, the MAN ON guardedpushbutton must be pressed in to start the emergency generator.




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AC MAIN GENERATION

Main GeneratorGenerator Control Unit

Control and Indication

DistributionSelf Examination


DATE : APR 1994 Page 1 F24AE02


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MAIN GENERATOR

The Integrated Drive Generator consists of a constant speed drive part and agenerator.

GENERATOR CONTROL UNIT

The Generator Control Unit (GCU) fulfills several functions.

The main functions of the GCU are :- Voltage and frequency regulation

- GLC control in accordance with Electrical Contactor ManagementUnit (ECMU)

- Control and protection- No Break Power Transfer (NBPT)- BITE function- Interface with the SDACs.

The BITE signals are connected via the Ground Power Contol Unit (GPCU)to the Central Maintenance Computers (CMCs).

CONTROL AND INDICATIONThe Integrated Drive Generators (IDGs) are controlled by pushbuttonswitches located on the overhead ELEC panel.

DISTRIBUTION

There are four distribution networks :- Network 1 consists of AC BUS 1-1, AC ESSential BUS and AC ESSSHED BUS.- Network 2 consists of AC BUS 1-2.- Network 3 consists of AC BUS 2-3.

- Network 4 consists of AC BUS 2-4.

Network 4 is also a backup supply for AC ESS BUSes.

24 ELECTRICAL POWER



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24 ELECTRICAL POWER


C C OWC N CS / C CS & V ON CS COU S

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SELF EXAMINATION

What is the power rating of an IDG ?

A - 110 KVA.

B - 90 KVA.C - 75 KVA.

Which generator parameters are controlled by the GCU ?

A - Voltage and oil temperature.B - Oil temperature and frequency.

C - Voltage and frequency.

DATE : APR 1994 Page 4 F24AE02Page 50

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AC GENERATION TRANSFER CIRCUIT D/O

GeneralOperation

DATE : JUN 1996 Page 1 F24BU01Page 55

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GENERAL

The transfer circuit consists of the 4 BTCs and the SIC. The SIC is controlledby ECMU 1 and via the BUS TIE switch on the electrical power controlpanel.

OPERATION

During normal system operation, the BUS TIE switch remains in the

latched-in position (AUTO). In this position, the SIC and the four BTCs areautomatically commanded open or closed by the ECMUs and the GCUs(depending on the power source configuration and NBPT request).

In the unlatched off position, the OFF legend on the switch comes on,provided busbar 401XP is still supplied; the SIC opens, the 4 BTCs open (dueto switch status change sent to both ECMUs), and the switch status changeis sent to both FWCs; the message "ELEC BUS TIE OFF" is displayed on

the ECAM.

CAUTION : On batteries only, with the switch in off position, the legenddoes not come on. Check the message on ECAM. It is not possible to connect

external power or APU generator to the network.


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IDG COOLING D/O

GeneralIDG Cooling Principle

Oil CoolingComponent

DATE : MAR 1999 Page 1 F24IC01Page 71

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GENERAL

The IDG oil is used for IDG cooling and lubrication at the same time.

The oil enters the IDG at the opposite side of the drive end and is ported to:- the generator stator and rotor,- the differential gear,

- the charge pump,- the input seal.

IDG COOLING PRINCIPLE

The input housing has rectangular grooves cut around the main generatorstator core in which oil flows to cool the stator and maintain a lower IDGsurface temperature.

The oil entering the rotor is distributed for cooling of:- the exciter and main generator rotors,- the exciter and main generator windings,- the diodes.

The oil, supplied to the differential gear, is also used to spray cool the PMGstator and lube the disconnect spline.The charge pump draws in the oil flow at its suction port and intensifies its

pressure.The charge oil is then used :

- as a motive flow in the hydraulic and control system,- for cooling and lubrication of the hydraulic parts.

This used oil is then either directly ported to the deaerator or leaked to theIDG sump where it is scavenge and pumped to the deaerator. There it runs

through the filter into the external system lines for cooling.

OIL COOLING

An engine fuel/oil cooler cools the IDG oil an limits the IDG inlettemperature to 127C.

Engine oil and IDG oil go through the fuel/oil cooler but do not mix together.Note: the normal IDG inlet temperature is between 40C and 105C.


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COMPONENT


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ELECTRICAL CONTACTOR MANAGEMENT

SYSTEM PRESENTATION

Electrical Contactor Management Unit

ECMU Functions

Self Examination

DATE : MAY 1994 Page 1 F24AI02Page 125

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ELECTRICAL CONTACTOR MANAGEMENT UNIT

The system consists of two Electrical Contactor Management Units(ECMUs).

ECMU 1 monitors the network and manages left hand contactors, AuxiliaryGenerator Contactor (AGC), External Power Contactor B (EPC B) and the

System Isolation Contactor (SIC).

ECMU 2 monitors the network and manages right hand contactors plusExternal Power Contactor A (EPC A).

ECMU FUNCTIONS

The main ECMU functions are :

- monitoring of the aircraft network- No Break Power Transfer (NBPT) function (only available onground)- controlling the AC/DC main contactors.

The DC contactors are controlled by both ECMUs.

NBPT is done by paralleling AC power sources (generators 1,2,3,4, APUgenerator or external power A,B) during the transfer period.


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SELF EXAMINATION

The main ECMU functions are ?

A - Network monitoring and AC/DC main contactor control

only.B - No break power transfer, AC/DC main contactor controland network monitoring.C - AC/DC main contactor control and no break power transfer

only.


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ECMU SYSTEM D/O

GeneralPower Supply

AC Contactors ControlNBPT LinksDC Contactors ControlGalley/Commercial Load Control

Service Bus ControlBITE Function

DATE : JAN 1996 Page 1 F24BL01Page 129

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GENERAL

Two identical and interchangeable ECMUs are installed to monitor andcontrol several systems.

The ECMUs control and monitor the following sub-systems :- contactors responsible for AC main generation and distribution

- No Break Power Transfer (NBPT)- contactors responsible for DC main generation and distribution- galley and commercial load- service bus

- BITE interface.

The ECMUs pin programming identifies :- equipment installed on side 1 and on side 2

- installation of options- type of aircraft.

The ECMU is a type 2 computer. It operates as soon as its power is supplied.

POWER SUPPLY

Each ECMU is supplied by four independent 28 VDC power sourcesdepending on the aircraft configuration.

Normal configuration without external power :- ECMU 1 is supplied from 301PP and 401PP

- ECMU 2 is supplied from 303PP and 403PP.

External power connected :- ECMU 1 is supplied from External Power B (EPB)

- ECMU 2 is supplied from External Power A (EPA).This internal supply has priority over the HOT BUSsupply. HOT BUS supplyis only possible if the battery switches are in AUTO position.

In electrical emergency configuration, the ECMUs are in stand by modesupplied by the HOT BUSes, because they are not operative in this mode. Butin case of successful engine or APU start they become automaticallyoperative to permit the normal network supply by the available generator.

ADIRU : Air Data Inertial Reference Unit

LGCIU : Landing Gear Control and Interface Unit

The ECMUs are interfaced with the ADIRU 1 and 3, and the LGCIU 1.LGCIU 1 provide the ground/flight information to both ECMUs. ADIRU 1provides the speed signal "less than 50 Kts" to ECMU 1.ADIRU 3 providesthe speed signal "less than 50 Kts" to ECMU 3.


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AC CO AC O S CO O




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AC CONTACTORS CONTROL

ECMU 1 manages only side 1 contactors and ECMU 2 side 2 contactors.

Each ECMU receives the following information :- voltage from AC BUS 1-1 and 1-2 for ECMU 1- voltage from AC BUS 2-3 and 2-4 for ECMU 2

- from all GCUs (PR status, S1 and D signal)- all AC contactors and BUS TIE switch status.

The ECMUs determine the aircraft electrical configuration according to thisinput status data.

On the basis of this configuration, each ECMU controls the followingcontactors :

- GLC 1,2, APU GLC, BTC 1,2, SIC, EPC B from ECMU 1

- GLC 3,4, BTC 3,4, EPC A from ECMU 2.These contactors are responsible for the connection and the transfer of the ACpower sources with respect to the priority rules, the NBPT and the IPT.

NOTE : With the BUS TIE switch in the OFF position, the 4 BTCs and theSIC are permanently open.


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NBPT LINKS




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NBPT LINKS

The NBPT function (only available on ground) serves to perform a powersupply transfer between two power sources (such as IDGs, APU generator,external power A and B) without busbar supply cutoffs.

On the basis of the data provided by the 5 GCUs, the GPCU and the contactor

status, the ECMUs manage the following contactors :- ECMU 1 : GLC 1,2, APU GLC, BTC 1,2, SIC, EPC B- ECMU 2 : GLC 3,4, BTC 3,4, EPC A.

This managing enables the paralleling of two synchronized AC power sources

during the transfer phase.

The signals involved in the NPBT function are :from GCU :

- D - request signal- S1 - established synchronization signal- Power Ready Relay status.

from ECMU : S2 - NBPT end

from GPCU : Frequency Reference Unit (FRU)from APU GCU : S4 - FRU change signal.

If the ECMUs detect a persisting paralleling between two power sources, they

activate the appropriate protections by opening the related contactors.ECMU 1 lost GLC 1*, GLC 2*, BTC 1,2, APU GLC, EPC B, SICECMU 2 lost GLC 3*, GLC 4*, BTC 3,4, EPC B.

(*) : Remain closed due to self-holding function.


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DC CONTACTORS CONTROL




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DC CONTACTORS CONTROL

Each ECMU controls contactors 1PC1 and 1PC2 according to the followingstatus data in order to manage the main DC buses supply.Both ECMUs receive the contactor status data of 5PU1, 5PU2, 1PC1, 1PC2,and 4PC.

ECMU 1 receives :- status of TR 2 (FAULT, OverCurrent)- 28 VDC from TR 1 to supply 1PC1 and 1PC2 control logic- voltage from busbar 101PP.

ECMU 2 receives :- status of TR 1 (FAULT, OverCurrent)- 28 VDC from TR 2 to supply 1PC1 and 1PC2 control logic

- voltage from busbar 206PP.

Note : the OverCurrent signal is used by the ECMU to inhibit the automatictransfer in case of detected overcurrent on one side.

Loss of one ECMU does not affect the main DC buses supply.


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GALLEY/COMMERCIAL LOAD CONTROL




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The galley/commercial load control consists in controlling the galley RemoteControl Circuit Breakers (RCCBs) which serve to shed the galley supplyaccording to the electrical sources available and overloads, and the Galley andCommercial control switches position.Each ECMU determines the electrical configuration of the aircraft on the

basis of the status data from the five GCUs, the GPCU (overload) and the twocontrol switches.The two main relays, 2XA1 and 2XA2, are supplied from busbar 601PP viathe two control switches in series and from the corresponding ECMU. These

two main relays control the power to thecorresponding RCCBs.

Individual opening or closing of the RCCBs is controlled from the PARTIALSHED logic of each ECMU. If one RCCB is open due to generator

overload,the message : "GALLEY PART SHED"is displayed on ECAM.

If the GALLEY control switch is in the off position :- the OFF legend comes on

- both main relays are de-energized- all galleys are off

- the ECAM message "GALLEY SHED" is displayed- the control logic is reset.

If the COMMERCIAL control switch is in the off position :- the OFF legend comes on- all galleys are off

- all service buses are off- the ECAM message "COMMERCIAL OFF" is displayed.


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SERVICE BUS CONTROL




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The ECMUs control the RCCBs which serve to supply the SERVICEBUSES. The opening or closure of the RCCBs depends on the aircraft supplyconfiguration sensed by the ECMUs.

ECMU 1 monitors and controls RCCBs 6XN1 and 7XN1.

ECMU 2 monitors :- RCCBs 6XN2 and 7XN2- TR2 supply contactor 2PU (TR supply from AC BUS 2-3)

- position of the MAINT BUS switch.ECMU 2 controls RCCBs 6XN2, 7XN2, 1XX, 2XX, 3XX and 4XX.

If the COMMERCIAL switch is in the off position :

- the ECAM message "COMMERCIAL OFF" is displayed- the OFF legend comes on- all RCCBs open, the SERVICE BUS is no longer supplied.

Note : Also the galleys are no longer supplied.


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BITE FUNCTION




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ARINC 429 buses serve to transmit BITE data to both CMCs andconfiguration data to both SDACs.Each ECMU continually monitors its inputs, outputs and internal functions todetermine if a failure condition exists. Failure information will be stored inthe internal NVM and also sent to the CMCs.

A self-test of the ECMU is automatically performed at power-up, or manuallyby requesting a test through the CMS.Based on the analysis of the ECMU functions, each ECMU provides data toboth SDACs to display on ECAM the condition of the power supply and the

messages "GALLEY SHED", "GALLEY PART SHED" or "COMMERCIALOFF".


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STUDENT NOTES




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SYSTEM NORMAL OPERATION

Ground ConfigurationAPU Generator Supply Only

APU Generator and Generator 2 SupplyNormal Configuration

Self Examination

DATE : APR 1994 Page 1 F24AL02Page 271

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GROUND CONFIGURATION




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The aircraft network is supplied :

- by external power A only or,- by external power A and B or,- by external power A and B and APU GENerator according to supply logic

priority.

APU GENERATOR SUPPLY ONLY

The whole aircraft network is supplied by the APU generator after external

power A and B disconnection.

APU GENERATOR AND GENERATOR 2 SUPPLY

The aircraft network is supplied by the APU generator and generator two.

NORMAL CONFIGURATION

In normal flight configuration, the aircraft network is supplied by four main

generators.


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STUDENT NOTES




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SYSTEM ABNORMAL OPERATION

Loss of One Main GENLoss of Two Main GEN

Loss of Three Main GENLoss of ESS TR

Loss of One Main TRLoss of AC Bus 1-1

Self Examination

DATE : MAY 1994 Page 1 F24AM02Page 275

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LOSS OF ONE MAIN GEN

If one main generator is lost all the aircraft network is supplied




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If one main generator is lost, all the aircraft network is supplied(with or without the Auxiliary Power Unit (APU) generator) through thetransfer circuit.

LOSS OF TWO MAIN GEN

If two main generators of opposite sides are lost, the entire aircraft networkis supplied through the transfer circuit.

If two main generators of the same side are lost, the entire aircraft network

is supplied through the transfer circuit.

LOSS OF THREE MAIN GEN

If three main generators are lost, only half of the AC network is supplied.

If APU GENerator is connected, the entire aircraft network is supplied

through the transfer circuit.

LOSS OF ESS TR

If the ESSential Transformer Rectifier (ESS TR) is lost, the DC ESS BUSand DC ESS SHED BUS are automatically recovered from the TR1 throughthe DC BAT BUS.

LOSS OF ONE MAIN TR

If one main Transformer Rectifier is lost the other main TR automaticallyrestores all DC buses.

LOSS OF AC BUS 1-1

If AC BUS 1-1 is lost, the AC ESSential BUS and the ESSential TR areautomatically supplied from AC BUS 2-4.


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SELF EXAMINATION




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What happens in case of loss of three main generators without APU generatoravailable ?

A - The entire network is supplied.B - Only the AC BUS corresponding to the available generatoris supplied.C - Only half of the network is supplied.

What happens in case of loss of AC BUS 1-1 ?

A - The AC ESS BUS and ESS TR are recovered from ACBUS 2-4.B - The AC ESS and DC ESS buses are not recovered.C - The AC ESS BUS and TR1 are no longer supplied.


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SYSTEM EMERGENCY OPERATION

EMER Generator Normal SupplyEMER Generator Supply by RAT

Batteries SupplySelf Examination

DATE : MAY 1994 Page 1 F24AN02Page 279

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EMER GENERATOR NORMAL SUPPLY

In emergency configuration (loss of AC BUS 1-1 and AC BUS 2-4), the ACESS BUS, AC ESS SHED BUS and ESS TR are restored via the emergency




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g y g ( )ESS BUS, AC ESS SHED BUS and ESS TR are restored via the emergencygenerator using the green hydraulic system pressurized by engine drivenpumps.

DC ESS BUS and DC ESS SHED BUS are restored through the ESS TR.

EMER GENERATOR SUPPLY BY RAM AIR TURBINE

In case of Ram Air Turbine (RAT) operation (Emergency configuration and

loss of engines 1 and 4), the AC and DC ESS buses are powered, the DC ESSSHED bus and some AC ESS SHED sub-busbars are automatically shed.

BATTERIES SUPPLY

When the EMERgency GENerator is unavailable in flight, the main batteriessupply the DC ESS BUS, the HOT BATtery BUS and the static inverter,

which, in turn, supplies the AC ESS BUS.


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SELF EXAMINATION




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In emergency configuration, if the emergency generator is driven by the greenhydraulic system, powered by engine driven pumps, which buses arerestored ?

A - AC ESS BUS, AC ESS SHED BUS, DC ESS BUS andDC ESS SHED BUS.B - AC ESS BUS, DC ESS BUS and DC BAT BUS.

C - AC ESS BUS, AC ESS SHED BUS and DC ESS BUS.


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AC LOAD DISTRIBUTION




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AC LOAD DISTRIBUTION

AC Main DistributionAC Essential Distribution

Land RecoverySub-busbar Remote Control Circuit Breaker

Commercial SwitchAuto-transformer

Self Examination

DATE : JUN 1996 Page 1 F24FA04Page 303

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AC MAIN DISTRIBUTION

The AC main distribution is composed of 4 independent networks (networks1 to 4) and their associated sub-busbars.




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AC ESSENTIAL DISTRIBUTION

The AC essential distribution is composed of AC ESSential BUS 9XP, ACESSential BUS SHED 4XP and their associated sub-busbars.

LAND RECOVERY

In emergency configuration (CSM/G), before the extension of the slats andlanding gear, the crew must release out the LAND RECOVERY pushbuttonswitch




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switch.

The ON legend, on the LAND RECOVERY pushbutton switch, comes on.

The sub-busbar 903XP-C is recovered through the closed contactor 10XH.


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SUB-BUSBAR RCCB

The RCCBs are controlled by the commercial pushbutton switch 22XNthrough the ECMUs.

COMMERCIAL SWITCH

Each RCCB has an associated control logic in the ECMUs depending on theCOMMERCIAL pushbutton switch position.




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Certain sub-busbars are supplied through RCCBs.

NOTE :

Sub-busbars 111XP,113XP,115XP,212XP,214XP and 216XP can be

supplied directly from the external power in ground serviceconfiguration.

ON position (pushed) :

This position enables closure of RCCBs 6XN1, 7XN1, 6XN2, 7XN2,5XN and power supply of the galleys through ECMUs 1 and 2.

OFF position (released out) :

The OFF legend comes on. Sub-busbars 111XP, 113XP, 212XP,214XP, 208XP and all the galleys are shed.

NOTE :

The COMMERCIAL OFF message is displayed on the ELEC ACpage.


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AUTO-TRANSFORMER

Three 115/26VAC transformers are used by the AC distribution.

Two of them by the main distribution and the third one by the essential




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distribution.


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SELF EXAMINATION

Which sub-busbars of the AC ESS BUS is recovered by the LANDRECOVERY hb tt it h ?




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RECOVERY pushbutton switch ?

A - 931XP-A and 903XP-A.B - 905XP-B and 903XP-C.C - 401XP only.

Which items are supplied when the commercial PB SW is in ONposition ?

A - 111XP, 113XP, 208XP, 214XP, 212XP sub-busbars andthe galleys.B - 111XP, 113XP, 214XP, 212XP sub-busbars only.C - 111XP, 113XP, 214XP, 212XP sub-busbars and the

galleys.


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