24 Electrical Power

A319/A320/A321TECHNICAL TRAINING MANUAL

MECHANICS / ELECTRICS & AVIONICS COURSE

24 ELECTRICAL POWER

This document must be used for training purpose only

Under no circumstances should this document be used as a reference.

It will not be updated.

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.

GENERAL** System General Introduction (1) 1...............** Electrical System Location (1) 5................** System Diagram Description (1) 9................** System Main Control Panel Presentation (1) 23..** Circuit Breaker Panels Location (2) 27.........** ECAM Page Presentation (1) 39...................** System Warnings (3) 67..........................** ELEC SYS & Circuit Identification (2) 71.......

AC GENERATION** General Description (3) 89......................** IDG Description (3) 95..........................** IDG Cooling System (3) 99.......................** IDG Monitoring (2) 109..........................** IDG Disconnection / Reconnection (2) 113.......** IDG Components (2) 119..........................** IDG Oil Servicing (2) 129.......................** IDG Removal / Installation (3) 133.............** AC Main Generation D/O (3) 137..................** Generator Control Unit (GCU 1/2) D/O (3) 141...** Bus Tie Logic (3) 157............................** Main Generation Components (3) 161.............** AC Auxiliary Generation D/O (3) 173............** Auxiliary Generation Components (3) 177........** AC Emergency Generator D/O (3) 187.............** EMER ELEC Power Logic Description(3)(A320) 195.** EMER ELEC Power Logic Descr.(3)(A319/321) 205..** RAT Activation (3) 215..........................** CSM/G GCU D/O (3) 223............................** CSM/G Op. Test Electrical Circuit (3) 227......** Emergency Generation Components (3) 233........** Static Inverter Description/Operation (3) 247..** Static Inverter Components (3) 261.............** AC ESS BUS Switching (3) 271....................

** Fuel Pumps ELEC PWR Supply (SMK CONFIG)(3) 279.** AC/DC Sheddable Bus Supply (3) 291.............

EXTERNAL POWER** General Description (2) 299.....................** System Description/Operation (3) 303...........** Ground Power Control Unit D/O (3) 313..........** External Power Components (3) 317...............** Electrical Circuit (3) 325......................** AC/DC GND Service Distribution CMPNTS (3) 333..

DC GENERATION** DC Main Generation D/O (3) 345..................** DC Normal/ESS Generation SWTG D/O (3) 349......** DC Normal/ESS Generation SWTG ELEC CKT(3) 357..** Transformer Rectifier (TR) D/O 365.............** DC Main Generation Components (3) 377..........** Battery System Description/Operation (3) 391...** Battery Charge Limiter D/O 395..................** Battery Components (3) 399......................

AC AND DC LOAD DISTRIBUTION** Galley Supply Description/Operation (3) 409....** Galley Supply Components (3) 423................** Refuelling on Battery (2) 427...................

ECAM ELECTRICAL POWER INTERFACES** EGIU (3) 435.....................................** EGIU Components (3) 445.........................** AC/DC Bus OFF Warnings Logics (3) 449..........

CFDS/ELEC POWER INTERFACES** AC Generation Interfaces (3) 459................

MAINTENANCE PRACTICESSPECIFIC PAGES** CFDS Specific Page Presentation (3) 465......

_A319/A320/A321 TECHNICAL TRAINING MANUAL24 ELECTRICAL POWERMECHANICS / ELECTRICS & AVIONICS COURSE

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24 ELECTRICAL POWER

UC64200 TABLE OF CONTENTS Page

24 CONTENTSPage i

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24 ELECTRICAL POWER

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24 - ELECTRICAL POWER

24-00-00 ELECTRICAL SYSTEM GENERALINTRODUCTION

CONTENTS:AC Electrical GenerationDC Electrical GenerationEmergency Generator

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ELECTRICAL SYSTEM GENERAL INTRODUCTION

The AC electrical system can be supplied by the twoengine generators, the APU generator or an externalpower source.The DC electrical system is supplied from the ACelectrical system or from the batteries as a back upsource.An Emergency Generator, driven by the Blue HydraulicSystem pressurized by the Ram Air Turbine in emergencyconfiguration, can supply part of the AC and DCelectrical systems in case of loss of normal supply.

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ELECTRICAL SYSTEM GENERAL INTRODUCTIONTMUELE001-P01 LEVEL 1



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TMUELE001 LEVEL 1



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24-00-00 ELECTRICAL SYSTEM LOCATION

CONTENTS:AC Normal GenerationAC Emergency GenerationStatic InverterDC Normal GenerationDC Emergency Generation

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ELECTRICAL SYSTEM LOCATION

AC NORMAL GENERATION

There are 2 engine driven Integrated Drive Generator(IDGs).The IDG comprises two parts:

- the drive : Constant Speed Drive (CSD)- the generator.

Each IDG is installed on the associated engineaccessory gearbox.The AC Auxiliary Power Unit (APU) generator is locatedin the APU compartment.The external power receptacle is fitted forward of thenose landing gear bay.

AC EMERGENCY GENERATION

The AC Emergency Generation consists of a ConstantSpeed Motor (CSM) and an AC generator which form anassembly called Constant Speed Motor/Generator(CSM/G).The CSM/G is located in the main landing gear bay.

STATIC INVERTER

The Static Inverter is located in the right lateralavionics compartment.

DC NORMAL GENERATION

The two batteries (BAT 1 and BAT 2) and the two mainTransformer Rectifiers (TR1 and TR2) are located inthe right lateral avionics compartment.

DC EMERGENCY GENERATION

The Essential Transformer Rectifier (ESS TR) is locatedin the left lateral avionics compartment.




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ELECTRICAL SYSTEM LOCATIONTMUELE904-P01 LEVEL 1



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24-00-00 ELECTRICAL SYSTEM DIAGRAMDESCRIPTION

CONTENTS:Main AC GenerationEmergency GeneratorAC TransferAC DistributionDC GenerationDC DistributionBatteriesStatic InverterGround/Flight BusesGalleysMain Electrical ConfigurationsSelf Examination

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ELECTRICAL SYSTEM DIAGRAM DESCRIPTION

MAIN AC GENERATION

ENGINE GENERATORSThe aircraft electrical system is supplied by twoengine driven generators regulated in speed byintegrated drives.Generator 1 is driven by engine 1.Generator 2 is driven by engine 2.Engine generator characteristics are: 115 Volts, 400Hertz, 90 KVA.

APU GENERATORA third AC generator driven by the APU can replace oneor both main engine generators throughout the flightenvelope.APU generator characteristics are: 115 Volts, 400Hertz, 90 KVA.

EXTERNAL POWERA ground external power connector enables all bus barsto be supplied.External power characteristics are : 115 Volts, 400Hertz 90 KVA (minimum).

EMERGENCY GENERATOR

An AC emergency generator is driven by the Ram AirTurbine hydraulic circuit.It automatically provides emergency power in case offailure of all main aircraft generators.Emergency generator characteristics are: 115 Volts,400 Hertz, 5 KVA.

AC TRANSFER

The AC transfer circuit enables AC buses to be suppliedby any generator or external power, via the BusTransfer Contactors (BTCs).The priorities are:1 - GEN 1 (2) on AC BUS 1 (2)2 - EXT PWR even with one engine generator still running.3 - APU generator4 - The remaining engine generator.

AC DISTRIBUTION

AC BUS 1/2Each engine generator supplies its related AC bus.

AC ESS BUSThe AC ESS BUS is normally supplied by AC BUS 1, orby AC BUS 2 if AC BUS 1 fails.

AC ESS SHED BUSThe AC ESS SHED BUS is supplied by the AC ESS BUS.

115/26 V AUTO TRANSFORMERA 115 Volts to 26 Volts single phase autotransformersupplying a normal 26 Volts 400 Hertz sub-busbar isconnected to each main busbar and to the essentialbusbar.




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ELECTRICAL SYSTEM DIAGRAM DESCRIPTIONTMUELE103-P01 LEVEL 1



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DC GENERATION

DC generation is accomplished by TransformerRectifiers 1 and 2 (TR1 and TR2).All TRs have a maximum output of 200 A, 28 VDC.The ESS Transformer Rectifier unit replaces a faultymain TR to power the DC ESS BUS.

DC DISTRIBUTION

DC BUS 1/2DC BUS 1 and DC BUS 2 are supplied by their relatedTransformer Rectifier.DC BAT BUSThe DC BAT BUS is supplied by DC BUS 1 or by DC BUS 2if DC BUS 1 fails. Batteries can also supply the DCBAT BUS. DC ESS BUSThe DC ESS BUS is supplied by the DC BAT BUS. In anemergency, it is supplied either by BAT 2 or by theESS Transformer Rectifier. DC ESS SHED BUSThe DC ESS SHED BUS is supplied by the DC ESS BUS.

BATTERIES

Two batteries can be connected to the DC BAT BUS. Eachbattery has its own bus, HOT BUS 1 and HOT BUS 2. Theyare permanently supplied.Battery capacity is 23 Ah, nominal voltage is 24 VDC.

STATIC INVERTER

On batteries only, the static inverter connected tobattery 1 supplies the AC STAT INV BUS. Static Invertercharacteristics are: 115 Volts, 400 Hertz.

GROUND/FLIGHT BUSES

AC and DC ground flight buses are normally suppliedby the aircraft network, or directly by the externalpower unit, upstream of the External Power Contactor,without energizing the whole aircraft network.

GALLEYS

The main and secondary electrical circuits of thegalleys are supplied by AC BUS 1 and 2. The mainelectrical circuits are shed in single generatoroperation.




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ELECTRICAL SYSTEM DIAGRAM DESCRIPTIONTMUELE103-P02 LEVEL 1



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MAIN ELEC CONFIGURATIONS

GROUND SUPPLYOn ground, the complete circuit may be supplied by theexternal power unit or by the APU generator.




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ELECTRICAL SYSTEM DIAGRAM DESCRIPTION - MAIN ELEC CONFIGURATIONS (GROUND SUPPLY)TMUELE103-P03 LEVEL 1



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MAIN ELEC CONFIGURATIONS (CONT’D)

NORMAL CONFIGURATIONNormal flight Configuration.




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ELECTRICAL SYSTEM DIAGRAM DESCRIPTION - MAIN ELEC CONFIGURATIONS (NORMAL CONFIGURATION)TMUELE103-P04 LEVEL 1



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GROUND SERVICESFor ground service only, the AC and the DC groundflight buses can be supplied independently from thenormal circuit.




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ELECTRICAL SYSTEM DIAGRAM DESCRIPTION - MAIN ELEC CONFIGURATIONS (GROUND SERVICES)TMUELE103-P05 LEVEL 1



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LOSS OF MAIN GENERATORSIn flight, in case of total loss of all the maingenerators, and before the emergency generatorconnection, batteries 1 and 2 supply the AC and DC ESSbuses. This is a transient configuration, during RamAir Turbine extension or no emergency generatoravailable.If the gear is up, the emergency generator comes online and supplies the AC and DC ESS buses.During approach, when the landing gear is down, theemergency generator is deactivated. The batteriessupply the ESS buses.When the speed is lower than 100 knots, the DC BAT BUSis recovered, and when it becomes lower than 50 knots,the AC ESS BUS disconnects from the Static Inverter.




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ELECTRICAL SYSTEM DIAGRAM DESCRIPTION - MAIN ELEC CONFIGURATIONS (LOSS OF MAIN GENERATORS)TMUELE103-P06 LEVEL 1



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SELF EXAMINATION

The static inverter operates:A - permanentlyB - when on batteries onlyC - when one engine generator fails

AC ESS BUS is normally supplied by the:A - AC BUS 1B - AC BUS 2C - Emergency Generator

DC BAT BUS can be supplied by the:A - DC BUS 1 or batteriesB - DC BUS 1, DC BUS 2 or batteriesC - DC BUS 2 or batteries

AC tranfers enable AC buses:A - to be connected in parallelB - to be supplied by any generator or

external powerC - to be supplied by APU GEN or EXT PWR only

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24-00-00 ELECTRICAL SYSTEM MAIN CONTROLPANEL PRESENTATION

CONTENTS:IDG 1/2 PushbuttonsGEN 1/2 PushbuttonsAPU GEN PushbuttonEXT PWR PushbuttonBUS TIE PushbuttonAC ESS FEED PushbuttonBAT 1/2 PushbuttonsGALY & CAB PushbuttonMAINT BUS Switch

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ELECTRICAL SYSTEM MAIN CONTROL PANEL PRESENTATION

IDG 1/2 PUSHBUTTONS

When the IDG pushbutton is momentarily pressed, theIntegrated Drive Generator is disconnected from itsdrive shaft.It can only be reconnected by maintenance.

GEN 1/2 PUSHBUTTONS

In normal operation:the generator is energized and the line contactorcloses, when electrical parameters are correct.

When OFF:the generator is de-energized and the line contactoropens.

APU GEN PUSHBUTTON

In normal operation:the APU generator is energized and the line contactorcloses, if electrical parameters are correct and ifthe APU generator has priority.

When OFF:the APU generator is de-energized and the linecontactor opens.

EXT PWR PUSHBUTTON

When ON:the external power connects to the electrical networkif electrical parameters are correct and if it haspriority.

BUS TIE PUSHBUTTON

When set to AUTO:the Bus Tie Contactors open or close automaticallyaccording to priority to maintain the power supply toAC BUS 1 and AC BUS 2.

When OFF:the Bus Tie Contactors open.

AC ESS FEED PUSHBUTTON

In normal operation:the AC ESS bus is supplied by AC BUS 1.

When set to ALTN:the AC ESS bus is supplied by AC BUS 2.

BAT 1/2 PUSHBUTTONS

In normal operation:the Battery Charge Limiter automatically controls theconnection and disconnection of the battery to the DCBAT Bus.

When OFF:the battery is disconnected.T

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ELECTRICAL SYSTEM MAIN CONTROL PANEL PRESENTATIONTMUELE202-P01 LEVEL 1



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GALY & CAB PUSHBUTTON

When set to AUTO:the main and secondary electrical circuits of thegalleys are supplied.The main electrical circuits are automatically shedwhen only one generator is operating.On ground, all galleys are available on APU or externalpower.

When set to OFF:main and secondary electrical circuits of the galleysare shed.Note : Two AC and two DC sheddable buses for cabin

systems are also affected by the switchposition.

MAINT BUS SWITCH

When the MAINT BUS switch is ON, and with only the EXTPWR available (green AVAIL light on), the AC and DCGRND FLT buses are supplied.The MAINT BUS switch is located in the forward galleyarea (ceiling panel).




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24-50-00 CIRCUIT BREAKER PANEL LOCATION

CONTENTS:GeneralCockpitPassenger CompartmentAvionics Compartment

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CIRCUIT BREAKER PANEL LOCATION

GENERAL

The green C/Bs are monitored by the SDAC (System DataAcquisition Concentrator - ATA 31).When a green C/B is tripped, after a time delay amessage "C/B TRIPPED", with the C/B location, appearson the ECAM E/WD.The number on the top of the C/B indicatesthe nominal current in AMP, i.e.: 3 AMP.

Specific C/Bs :- The WTB C/Bs (Wing Tip Brakes - ATA 27) cannot bemanually tripped.- The C/Bs with a yellow cap must be tripped whenflying on batteries only.

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TMUELBZ01-P01 LEVEL 2

CIRCUIT BREAKER PANEL LOCATION - GENERAL



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CIRCUIT BREAKER PANEL LOCATION - COCKPIT



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CIRCUIT BREAKER PANEL LOCATION - COCKPITTMUELBZ01-P06 LEVEL 2



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CIRCUIT BREAKER PANEL LOCATION - PASSENGER COMPARTMENTTMUELBZ01-P07 LEVEL 2



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CIRCUIT BREAKER PANEL LOCATION - AVIONICS COMPARTMENTTMUELBZ01-P08 LEVEL 2



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CIRCUIT BREAKER PANEL LOCATION - AVIONICS COMPARTMENTTMUELBZ01-P09 LEVEL 2



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24-00-00 ECAM PAGE PRESENTATION

CONTENTS:GEN 1/2 IndicationsIDG IndicationsAPU GEN IndicationsEXT PWR IndicationsAC Bus Bars IndicationsAC Transfer IndicationsGalley Shed IndicationEMER GEN IndicationsTR 1/2/ESS IndicationsDC Bus Bars IndicationsDC Bat Bus IndicationsBat 1/2 IndicationsStatic Inverter Indications

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ECAM PAGE PRESENTATION

GEN 1/2 INDICATIONS

Engine generator parameters are green when normal.




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GEN 1/2 INDICATIONSTMUELE301-P01 LEVEL 1



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IDG INDICATIONS

The Integrated Drive Generator symbol and parametersare displayed here below.




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IDG INDICATIONSTMUELE301-P02 LEVEL 1



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APU GEN INDICATIONS

Only the white APU GEN message is displayed if the APUMASTER SW pushbutton is set to OFF.




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APU GEN INDICATIONSTMUELE301-P03 LEVEL 1



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EXT PWR INDICATIONS

External power parameters are displayed when theexternal power unit is plugged in and the deliveredparameters are correct.




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EXT PWR INDICATIONSTMUELE301-P04 LEVEL 1



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AC BUS BARS INDICATIONS

AC Bus bars are green when supplied, amber when notsupplied.




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TMUELE301-P05 LEVEL 1

AC BUS BARS INDICATIONS



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AC TRANSFER INDICATIONS

Transfer lines are green when the contactors areclosed.They are not displayed when the contactors are open.




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AC TRANSFER INDICATIONSTMUELE301-P06 LEVEL 1



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GALLEY SHED INDICATION

Galley shed is displayed when the galley electricalcircuits are not supplied or only partially suppliedby one generator.




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GALLEY SHED INDICATIONTMUELE301-P07 LEVEL 1



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EMER GEN INDICATIONS

Emergency generator parameters are displayed when theemergency Generator Line Contactor is closed.They are green when normal.




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EMER GEN INDICATIONSTMUELE301-P08 LEVEL 1



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TR 1/2/ESS INDICATIONS

Transformer Rectifier parameters are green whennormal.The parameters of the Essential Transformer Rectifierare only displayed when it is in use.




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TR 1/2/ESS INDICATIONSTMUELE301-P09 LEVEL 1



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DC BUS BARS INDICATIONS

DC Bus bars are green when supplied, amber when notsupplied.




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DC BUS BARS INDICATIONSTMUELE301-P10 LEVEL 1



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DC BAT BUS INDICATIONS

The DC Battery Bus is normally green.It becomes amber when the voltage is low.




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DC BAT BUS INDICATIONSTMUELE301-P11 LEVEL 1



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BAT 1/2 INDICATIONS

Battery parameters are green when normal.




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BAT 1/2 INDICATIONSTMUELE301-P12 LEVEL 1



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STATIC INVERTER INDICATIONS

Static Inverter parameters are only displayed duringStatic Inverter operation.




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STATIC INVERTER INDICATIONSTMUELE301-P13 LEVEL 1



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24-00-00 ELECTRICAL SYSTEM WARNINGS

CONTENTS:IDG OIL LO PR/OVHTGEN FAULTBAT 2 FAULTGEN OVERLOADAC BUS 2 FAULTAC ESS BUS FAULTAC ESS BUS SHEDDC BUS 1 FAULTDC ESS BUS FAULTDC ESS BUS SHEDDC BAT BUS FAULTEMER CONFIG

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ELECTRICAL SYSTEM WARNINGS



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TMUELE402 LEVEL 3

ELECTRICAL SYSTEM WARNINGS



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24-00-00 ELECTRICAL SYSTEM AND CIRCUITIDENTIFICATION

CONTENTS:System IdentificationCircuit IdentificationComponent IdentificationMain Bus Bar IdentificationSub-Bus Bar IdentificationARINC Bus IdentificationVirtual Bus Bar IdentificationConnector IdentificationCoding System

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ELECTRICAL SYSTEM AND CIRCUIT IDENTIFICATION

An alpha numeric reference code is used to identifysystems, circuits and components.

SYSTEM IDENTIFICATION

The first letter of the reference code is used forsystem identification.A system is a set of circuits which fulfills a mainfunction.All components not specifically related to a circuitare identified by the letter V.The second letter defines the type of component.

CIRCUIT IDENTIFICATION

The second letter of the reference code is used forcircuit identification within the system.A circuit is a series of components with or withoutwiring, serving a specific function in a given system.All components not specifically related to a circuitare identified by the letter V.The second letter defines the type of component.Mechanical and electrical/electro-mechanicalcomponent have been differentiated by using the letterM in place of the second circuit letter for realmechanical equipment.

COMPONENT IDENTIFICATION

The four numeric characters, in front of the circuitidentification, identify the component within thecircuit.For electrical components, the reference numbers arefrom 1 to 999.Purely mechanical component are referenced from 5000to 7999.Four supplementary characters (left justified andwithout non significant zero) are used to identifysymetrical or multiple installations.Example: 1CC1 for FAC 1, 1CC2 for FAC 2.

MAIN BUS BAR IDENTIFICATION

The main bus bars are identified using:- a sequence number,- letters XP for AC BUS BARS and PP for DC BUSBARS,

- a phase letter (when applicable).The first number (1 or 2 or 3...) indicates the busbar number. The letters (XP or PP) indicate thecorresponding power form (alternating current ordirect current).Example: 1 XP: main alternating current bus bar 1.1 PP: main direct current bus bar 1.1 XP-A: main alternating current bus bar 1 phase A6 PP: direct current service bus bar.

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ELECTRICAL SYSTEM AND CIRCUIT IDENTIFICATIONTMUELAA01-P01 LEVEL 2



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SUB-BUS BAR IDENTIFICATION (CONT’D)

The sub-bus bars are identified in the same way as themain bus bar, but with three identification numbers:

- the first is identical to the number of thecorresponding main bus bar,

- the two following numbers are the sub-bus barnumbers.

Example: 401 XP is the first sub-bus bar of the AC ESSBUS.601 PP is the first sub-bus bar of the SERVICE BUS.It should be noted that for the AC network, the thirtiesare used for the 26V-400Hz distribution.Example: 103 XP, 131 XP are sub-bus bar of the mainbus bar 1XP, but 131 XP is the 26V-400Hz distributionsub-bus bar.




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TMUELAA01 LEVEL 2



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ARINC BUS IDENTIFICATION

ARINC 429 buses are numbered from 7000 to 7999 withthe ATA 100 prefix of the corresponding system.An ARINC 429 BUS shielded cable consists of two wires:one coloured in blue and one coloured in red.




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ELECTRICAL SYSTEM AND CIRCUIT IDENTIFICATION - ARINC BUS IDENTIFICATIONTMUELAA01-P02 LEVEL 2



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VIRTUAL BUS BAR IDENTIFICATION

Some circuit breakers do not have their supply on thebus bars of the aircraft distribution network. Theyare directly connected to the power source.In schematic representations, this supply appears asa virtual bus bar.A virtual bus bar is identified as follows:

- 1. a channel number,- 2. letters IW for virtual bus bars followed byXP for AC bus bars or PP for DC bus bars.

Example: 1IWXP channel 1 of AC virtual bus bar.1IWPP channel 1 of DC virtual bus bar.Channel 1: consists of 1XP-101XP-103XP-110XP-131XP

1PP-101PP-103PP3PP-301PP701PP-703PP702PP-704PP901XP

Channel 2: consists of 2XP-202XP-204XP-210XP-212XP214XP-216XP-231XP2PP-202PP-204PP-206PP-208PP501PP-502PP601PP-602PP

Channel 4: for essential channel,it consists of: 401XP-431XP

801XP401PP801PP




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ELECTRICAL SYSTEM AND CIRCUIT IDENTIFICATION - VIRTUAL BUS BAR IDENTIFICATIONTMUELAA01-P03 LEVEL 2



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CONNECTOR IDENTIFICATION

Connections to components are identified by a suffixletter (or two for multiple connection parts) followingthe circuit identification




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ELECTRICAL SYSTEM AND CIRCUIT IDENTIFICATION - CONNECTOR IDENTIFICATIONTMUELAA01-P04 LEVEL 2



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TMUELAA01-P05 LEVEL 2

ELECTRICAL SYSTEM AND CIRCUIT IDENTIFICATION - CODING SYSTEM



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ELECTRICAL SYSTEM AND CIRCUIT IDENTIFICATION - CODING SYSTEMTMUELAA01-P10 LEVEL 2



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ELECTRICAL SYSTEM AND CIRCUIT IDENTIFICATION - CODING SYSTEMTMUELAA01-P11 LEVEL 2



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24-20-00 AC GENERATION - GENERALDESCRIPTION

CONTENTS:Normal OperationAbnormal Operation

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AC GENERATION - GENERAL DESCRIPTION

NORMAL OPERATION

GEN 1 and GEN 2 and APU GEN are monitored by a GeneratorControl Unit (GCU).This computer receives various parameters from thecorresponding generator, processes them and if theyare correct, provides a control signal to the GeneratorLine Contactor (GLC).For the External Power generation, the Ground PowerControl Unit (GPCU) has the same function as the GCUbut monitors the Ground Power Unit parameters.

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AC GENERATION - GENERAL DESCRIPTION - NORMAL OPERATIONTMUELAB01-P01 LEVEL 3



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AC GENERATION - GENERAL DESCRIPTION

ABNORMAL OPERATION

If one generator parameter is not correct, theassociated GCU sends a signal to trip the GLC andtrigger warnings.

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AC GENERATION - GENERAL DESCRIPTION - ABNORMAL OPERATIONTMUELAB01-P02 LEVEL 3



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24-21-00 IDG DESCRIPTION

CONTENTS:GeneralGenerator DriveSpeed ControlControl and MonitoringSelf Examination

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IDG DESCRIPTION

GENERAL

Each engine drives its associated Integrated DriveGenerator (IDG) through the accessory gearbox. Thedrive speed varies according to the engine rating.The IDG is split in two parts: the drive and thegenerator.The IDG is cooled and lubricated by the IDG oil system.

GENERATOR DRIVE

Using the variable input speed, the generator driveproduces a constant speed on the output shaft via avariable ratio differential.The output constant speed is regulated at 12000 RPM.

SPEED CONTROL

A mechanical governor, acting on a hydraulic trim unit,controls the differential gear in order to maintainthe constant output speed.The differential gear also controls the oil systempumps in order to lubricate and cool the IDGcomponents.

CONTROL AND MONITORING

AC generation is monitored by the Generator ControlUnit (GCU). GEN 1 OR 2 pushbutton controls generatorexcitation via its Generator Control Unit.For safety reasons and IDG protection, an IDG1 (orIDG2) guarded pushbutton allows manual disconnectionof the IDG.

NOTE: Reset of the system can only be performed onground, with engines stopped, by pulling thereset handle mounted on IDG casing.

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IDG DESCRIPTIONTMUELAC06-P01 LEVEL 3



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SELF EXAMINATION

How is IDG1 disconnected?A - Automatically, when an overspeed is

detected.B - Automatically, when a faulty parameter

is detected by the GCU.C - By pressing the IDG1 guarded pushbutton.

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24-21-00 IDG COOLING SYSTEM

CONTENTS:GeneralOperation PrincipleCold ConditionsFilter cloggedTemperature and Pressure MonitoringSelf Examination

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IDG COOLING SYSTEM

GENERAL

The IDG oil cooling system consists of a self-containedoil circuit and a fuel/oil heat exchanger.

OPERATION PRINCIPLE

A scavenge pump pumps the oil through the oil filterand the fuel/oil heat exchanger. A charge pump providesregulated oil supply pressure to the users.The engine fuel flow regulates the IDG oil temperaturethrough the fuel/oil heat exchanger.

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IDG COOLING SYSTEM - OPERATION PRINCIPLETMUELAD05-P01 LEVEL 3



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IDG COOLING SYSTEM

COLD CONDITIONS

In cold conditions, due to the high oil viscosity, theoil pressure increases, the cooler bypass valve opens;oil runs in the IDG internal circuit.As the oil warms up, the cooler bypass valve closesand the oil flows through the fuel/oil heat exhanger.




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IDG COOLING SYSTEM - COLD CONDITIONSTMUELAD05-P02 LEVEL 3



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IDG COOLING SYSTEM

FILTER CLOGGED

A clogged filter indication is provided by a localvisual Delta Pressure pop-out indicator (DPI).In case of clogging indication, a DPI reset can bedone in some conditions and associated with maintenanceprocedures.When the filter is clogged, the relief valve opens.




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IDG COOLING SYSTEM - FILTER CLOGGEDTMUELAD05-P03 LEVEL 3



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IDG COOLING SYSTEM

TEMPERATURE AND PRESSURE MONITORING

For overheat detection, oil temperature sensorsmonitor the temperature of both input and output oil.A pressure switch operates in the event of a loss ofcharge oil pressure.




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IDG COOLING SYSTEM - TEMPERATURE AND PRESSURE MONITORINGTMUELAD05-P04 LEVEL 3



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SELF EXAMINATION

When does the cooler bypass valve open?A - When an overtemperature is detected.B - During cold conditions operation.C - When the filter is clogged.

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24-21-00 IDG MONITORING

CONTENTS:Temperature MonitoringTemperature Rise IndicationPressure MonitoringSelf Examination

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IDG MONITORING

TEMPERATURE MONITORING

If an overtemperature is detected at the IDG outlet,the associated alarms are triggered.If the temperature rises above 147°C, the ELEC ECAMpage is automatically displayed and the temperatureindication flashes. If the temperature exceeds 180°C,the indication turns from green to amber. Above 185°C, the MASTER CAUTION and IDG FAULT lightscome on, the single chime is triggered.

TEMPERATURE RISE INDICATION

If the temperature rise indication is over a givenlimit, a signal is sent to the CFDIU through the GroundPower Control Unit.GPCU: Ground Power Control Unit.CFDIU: Centralized Fault Display Interface Unit.Message on the MCDU: IDG 1 (or 2) HIGH DELTA TEMP(class 2 failure).

PRESSURE MONITORING

In case of loss of charge oil pressure thecorresponding indications and warnings are triggeredonly when the corresponding engine is running.The low pressure warning is inhibited, for IDGinput speed below 2000 RPM(Normal input speed range: between 4500 and 9120 RPM).

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IDG MONITORINGTMUELAE04-P01 LEVEL 2



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SELF EXAMINATION

When does the IDG FAULT light come on?A - In case of overheat or low pressure

detectionB - In case of overheat and high pressure

detectionC - In case of overheat or high pressure

dectection

TMUELAE04 LEVEL 2



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24-21-00 IDG DISCONNECTION ANDRECONNECTION

CONTENTS:IDG DisconnectionIDG Reconnection

TMUELAF06 LEVEL 2



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IDG DISCONNECTION AND RECONNECTION

IDG DISCONNECTION

In case of oil overheat or drop of oil pressure, theamber IDG FAULT light comes on and the ECAM system istriggered.To disconnect the IDG from the accessory gearbox, theIDG pushbutton must be pressed.

NOTE: Do not maintain the IDG pushbutton pressed formore than 3 seconds to avoid damage of thesolenoid.

When the engine is not running, the IDG disconnectioncontrol signal is inhibited by the engine oil lowpressure switch.

NOTE: IDG FAULT light goes off when the failure signalis no longer present. The GEN FAULT amber lightcomes on.

TMUELAF06-T01 LEVEL 2



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IDG DISCONNECTION AND RECONNECTION - IDG DISCONNECTIONTMUELAF06-P01 LEVEL 2



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IDG DISCONNECTION AND RECONNECTION

IDG RECONNECTION

In flight, IDG disconnection is irreversible. Thesystem can only be reconnected on the ground withengines shut down to avoid damage to the drive shaftclutch device.A mechanical reset handle (ring) fitted to the IDGenables the drive to be reconnected while the engineis stationary on the ground.

NOTE: Do not reconnect the IDG when the engine is inwindmilling as it will damage the IDGdisconnection mechanism.

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IDG DISCONNECTION AND RECONNECTION - IDG RECONNECTIONTMUELAF06-P02 LEVEL 2



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TMUELAF06 LEVEL 2



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24-21-00 IDG COMPONENTS

CONTENTS:Integrated Drive GeneratorOil Cooler

TMUELAH05 LEVEL 2



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IDG COMPONENTS

INTEGRATED DRIVE GENERATOR

IDENTIFICATIONFIN: 4000XU

LOCATIONZONE: 400

COMPONENT DESCRIPTIONThe IDG Input shaft has a shear neck to protect theengine gearbox and to safeguard the IDG against furtherdamage.

FILTER CLOGGING INDICATORThe sensing device for the filter clogging indicatoris automatically suppressed during cold oil runningconditions (high oil viscosity).The Delta Pressure pop-out Indicator (DPI) can be resetup to 3 times prior to IDG removal if these conditionsare fulfilled:- No metal particles in the filter and no otherindications.- Oil and filter change is required.- Write on the IDG DPI label that DPI reset is done.

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IDG COMPONENTS - INTEGRATED DRIVE GENERATOR - FILTER CLOGGING INDICATORTMUELAH05-P01 LEVEL 2



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IDG COMPONENTS


QUICK ATTACH DETACHThe IDG is attached to the engine gearbox by a QuickAttach Detach device.

OIL LEVEL INDICATOR

1 - If the oil level is above the line between thegreen and the yellow band (IDG cold) or above theyellow band (IDG hot), oil servicing is required.2 - If the oil level is within the green band (IDGcold) or within green or yellow bands (IDG hot), oilservicing is not required.3 - If the oil level is below the green band, oilservicing is required.Note : The yellow band corresponds to the oil thermalexpansion margin.




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TMUELAH05-P02 LEVEL 2

IDG COMPONENTS - INTEGRATED DRIVE GENERATOR - QUICK ATTACH DETACH - OIL LEVEL INDICATOR



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IDG COMPONENTS


OIL FILTER

DISCONNECT MECHANISMThe disconnect mechanism consists of a solenoid, aspring-loaded disconnect plunger with threaded pawl,a worm shaft, and a reset handle.The purpose of the disconnect mechanism is to uncouplethe power supply of the gearbox from the IDG in theevent of an IDG failure.Once uncoupled, the disconnect mechanism cannot bereset in flight.




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IDG COMPONENTS - INTEGRATED DRIVE GENERATOR - OIL FILTER - DISCONNECT MECHANISMTMUELAH05-P03 LEVEL 2



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IDG COMPONENTS

OIL COOLER


LOCATIONZONE: 400




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IDG COMPONENTS - OIL COOLERTMUELAH05-P04 LEVEL 2



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TMUELAH05 LEVEL 2



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24-21-00 IDG OIL SERVICING

CONTENTS:Oil Replenishing of the IDG after Replacement of theIDG or a Cooling Circuit Component

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IDG OIL SERVICING

OIL REPLENISHING OF THE IDG AFTER REPLACEMENT OF THEIDG OR A COOLING CIRCUIT COMPONENT

Refer to your Aircraft Maintenance Manual whenperforming this procedure by yourself.

VIDEO SEQUENCEDo not touch the IDG system components for a shorttime after the engine is shutdown. The enginecomponents stay hot for sometime and can cause injury.If the oil is below the minimum level (the green band),add oil to the IDG.Now prepare the IDG for servicing.Remove the caps from the overflow drain and pressurefill valves.First connect a drain hose to the overflow drain valve,then connect the pressure fill hose from a serviceunit to the pressure fill valve.Using the service unit, add oil until the level reachesthe FULL mark and the oil overflows through the drainhose.Drain oil until the oil level moves down to the greenband.Remove the drain and pressure fill hoses fromconnectors and reinstall the caps.Finally, perform a leak test. Do another check of theoil level 5 minutes later.

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IDG OIL SERVICING - OIL REPLENISHING OF THE IDG AFTER REPLACEMENT OF THE IDG OR A COOLINGCIRCUIT COMPONENT

TMUELAI04-P01 LEVEL 2



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24-21-00 IDG REMOVAL/INSTALLATION

CONTENTS:IDG RemovalIDG Installation

TMUELAJ04 LEVEL 3



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IDG REMOVAL/INSTALLATION

IDG REMOVAL


VIDEO SEQUENCEBefore removing the IDG the engine must be shutdownfor at least 5 minutes to prevent burns because theoil stays hot for a few minutes.First of all, the IDG must be drained and the oil tubedisconnected and removed.Also remove the banjo couplings and note their initialposition, then disconnect the three electricalconnectors from the IDG.Remove the cover plate of the IDG terminal box anddisconnect the output cables.Next, place the special dolly in position and raiseit up to the IDG. When the IDG is on the dolly releasethe Quick Attach/Detach coupling, then pull the IDGforward to disengage it.

IDG INSTALLATION


VIDEO SEQUENCEUsing the dolly, lift the IDG up to its position andalign the open marks on the Quick Attach/Detachcoupling.When the IDG is engaged tighten the couplingsufficiently to secure it, then remove the dolly,reconnect the electrical connectors and reinstall theoil tubes.T

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IDG REMOVAL/INSTALLATIONTMUELAJ04-P01 LEVEL 3



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TMUELAJ04 LEVEL 3



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24-22-00 AC GENERATION - AC MAINGENERATION D/O

CONTENTS:GeneratorGenerator Control Unit SupplyGenerator Operation ControlGenerator MonitoringGenerator 1Generator ResetSelf Examination

TMUELAK06 LEVEL 3



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AC GENERATION - AC MAIN GENERATION D/O

GENERATOR

The generator is a conventional 3 co-axial componentbrushless generator which consists of:

- a Permanent Magnet Generator (PMG),- a rotating diode pilot exciter,- the generator itself.

The generator is driven at a constant speed of 12000 RPMand cooled by oil spraying.

GENERATOR CONTROL UNIT SUPPLY

The Permanent Magnet Generator (PMG) supplies theexciter field through the Generator Control Relay (GCR)and the Generator Control Unit through a RectifierUnit.The Generator Control Unit (GCU) supply from theaircraft network is duplicated (Back up supply). Thesupply is taken from the DC essential system.The excitation control and regulation module keeps thevoltage at the nominal value at the Point Of Regulation(POR).

GENERATOR OPERATION CONTROL

The generator is controlled by the correspondinggenerator pushbutton. When pressed in, if the generatorspeed is high enough, the generator is energized.If the delivered parameters are correct (Power Readyrelay closed) the Generator Line Contactor (GLC) closesto supply its network.

GENERATOR MONITORING

The FAULT light comes on when any generator parameteris not correct or when the Generator Line Contactoris open.The generator failure signal is sent to SDAC 1 and 2through the Electrical Generation Interface Unit(EGIU). When the engine is shut down, the correspondingGEN FAULT light is on.

NOTE: During the AVIONICS SMOKE procedure, the FAULTlight does not come on when the GEN1 LINEpushbutton is set to off.

GENERATOR 1

To avoid complete loss of fuel pumps electrical supplyduring the smoke procedure, the GEN 1 LINE pushbuttonis released out to open the line contactor.Generator 1 is still excited and supplies fuel pumps1LH and 1RH.

GENERATOR RESET

When the GEN pushbutton is released out after a faultdetection, the Generator Control Unit is reset.The Generator Control Relay (GCR) and the Power Readyrelay (PR) are reset.

TMUELAK06-T01 LEVEL 3



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AC GENERATION - AC MAIN GENERATION D/OTMUELAK06-P01 LEVEL 3



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SELF EXAMINATION

With the GEN 1 and 2 on line, when does the GEN 1FAULT light come on?

A - As soon as the GEN 1 LINE pushbutton isreleased out.

B - When any GEN 1 parameter is not correct.C - When any GEN 1 parameter is not correct

and the GEN 1 pushbutton is released out.

When released out, what does the GEN 1 LINEpushbutton enable?

A - To close GLC 1 and supply the fuel pumpsfrom the AC NORMAL BUS.

B - To open GLC 1 and supply the fuel pumpsfrom GEN 1.

C - To close the BTC and supply the fuelpumps from the AC NORMAL BUS.

TMUELAK06 LEVEL 3



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24-22-00 GENERATOR CONTROL UNIT (GCU 1/2)D/O

CONTENTS:GeneralVoltage RegulationControl and ProtectionIndications and WarningsBITESelf Examination

TMUELAL01 LEVEL 3

EFFECTIVITY 24-22-00Page 1

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GENERATOR CONTROL UNIT (GCU 1/2) D/O

GENERAL

The Generator Control Unit has four differentfunctions:

- Voltage regulation.- Generator control and protection of the networkand generator.

- Control of the various indications andwarnings.

- System self monitoring and Test.The GCU is supplied by the Permanent Magnetic Generator(PMG).The GCU is also supplied by the aircraft network(Back-Up supply).

TMUELAL01-T01 LEVEL 3


Nov 30/95


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GENERATOR CONTROL UNIT (GCU 1/2) D/O - GENERAL

TMUELAL01-P01 LEVEL 3


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VOLTAGE REGULATION

The voltage regulation is achieved by regulating thegenerator excitation current.It also supplies the exciter field through theGenerator Control Relay, which is normally closed, andthrough a rectifier.When the generator starts running, the PermanentMagnetic Generator supplies the GCU.The exciter field current is reduced inside the GCUuntil 335 Hz is obtained.As the PMG frequency is below the threshold, thegenerator excitation is reduced through the excitationcontrol module.The voltage regulation shutdown signal, generated bythe protection module, triggers the voltage regulationshutdown control module which simulates a highgenerator load signal via the current limit module.As soon as the PMG frequency is over the threshold,the generator excitation is regulated normally.The excitation current depends on the comparisonbetween the voltage sensed at the Point Of Regulation(POR) and a reference voltage.As the parameters are correct, the Generator LineContactor closes.The generator excitation also depends on the load.If a fault is detected by the GCU protection module,the voltage regulation shutdown control modulesimulates a high generator load signal. The exciterfield coils are no longer supplied.

NOTE: the GCR and the GLC are tripped.



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GENERATOR CONTROL UNIT (GCU 1/2) D/O - VOLTAGE REGULATION



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CONTROL AND PROTECTION

The generator control and protection functions aremainly provided by means of the Generator Control Relayand the Power Ready relay.The GCR controls the generator excitation. The PRcontrols the Line Contactor and activates thecorresponding warning.

ENGINE FIRE AND OPEN FEEDER CABLE PROTECTIONThe feeder cable is duplicated from the engine pylonto the forward cargo compartment. Each cable ismonitored by a Current Transformer and a sensor.If an open parallel condition exits, or if the EngineFire pushbutton is released out, the GCU trips the GCRand the GLC and turns off the voltage regulator.The Ground Power Control Unit (GPCU) determines whethera fire trip or an open cable trip has occured.



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GENERATOR CONTROL UNIT (GCU 1/2) D/O - CONTROL AND PROTECTION- ENGINE FIRE AND OPEN FEEDER CABLE PROTECTION -



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CONTROL AND PROTECTION - DIFFERENTIAL PROTECTION

The differential protection prevents the electricalwiring between the two detection Current Transformersfrom being damaged.The protected area is divided into two parts (ZONE 1& ZONE 2).

ZONE 1The zone 1 protected area comprises the generator coilsand feeders between the IDG Current Transformer (CT)and the GLC.The zone 2 protected area comprises the wiring betweenthe GLC and the Current Transformer (CT).In the event of a short circuit between phases or tothe ground, a noticeable difference betweentransformer currents activates the protection system.When activated the protection system opens GLC and BTC(GEN FAULT light comes on) and the generator is stillexcited.If the fault persits, the Generator Control Relay istripped thus the generator is de-excited. The Bus TieContactor closes automatically, therefore allowing thenetwork to be supplied by another generation source.In that configuration, the short circuit is locatedin zone 1.When the generator is cut off, the protection systemof zone 2 remains operational.The IDG senses a null current. If there is no shortcircuit in zone 2, the sum of currents sensed by theline CTs is null (opposite current direction).If a short circuit occurs in zone 2, an unbalancedcurrent is detected by the GCU which activates theprotection system.

ZONE 2If a short circuit occurs, the protection system opensthe GLC and confirms the BTC opening. The generatoris still excited. The GEN1 FAULT light comes on.If the fault does not persist, the short circuit hasbeen isolated and the GCR is tripped thus the generatoris de-excited.In this case, the BTC remains open and is locked out,and the AC BUS 1 supply cannot be recovered. The ACESSential Bus supply is recovered through the AC ESSFEED control.

The system is recovered by resetting the protectionsystem from the associated GEN pushbutton. Two resetactions maximun can be performed.The Generator Control Relay (GCR) closes enablinggenerator excitation. The Power Ready relay isre-energized to control the Generator Line Contactorclosing.The Bus Tie Contactor lock out function is removed.The DP Counter is reset either by pressing the DP Resetpushbutton on the front face of the GCU or at eachpower-up.



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GENERATOR CONTROL UNIT (GCU 1/2) D/O - CONTROL AND PROTECTION - DIFFERENTIAL PROTECTION


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CONTROL AND PROTECTION - OTHER PROTECTIONS

The GCR and PR relays are deenergized by the Protectionmodule which processes various electrical parametersnecessary for the protection functions.Note that the overload protection is only processedto give warning on the ECAM. In underspeed conditionsthe Under-Frequency and the Under-Voltage protectionsare inhibited.If the GLC remains closed (welded contact) aftertripping of the PR relay, the BTC lock-out functionis activated.



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GENERATOR CONTROL UNIT (GCU 1/2) D/O - CONTROL AND PROTECTION - OTHER PROTECTIONS


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INDICATIONS AND WARNINGS

IDG indications and warnings are computed by the GCU.The warnings and indications triggered are:

- generator “FAULT” amber warning light with ECAMactivation

- galley “FAULT” amber warning light with ECAMactivation

- IDG “FAULT” amber warning light with ECAMactivation.

The GCU also processes the following indications:- generator load, frequency, IDG oiltemperature and low pressure which are alsodisplayed on the ECAM system.



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GENERATOR CONTROL UNIT (GCU 1/2) D/O - INDICATIONS AND WARNINGS


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BITE

The GCU contains an integral BITE system to help insystem trouble shooting.The BITE system detects and isolates active and passivefailures.The BITE system consists of two sections:

- Operational BITE- Maintenance BITE

After generator tripping, the operational BITEidentifies the protection, analyses the conditions anddetermines the fault origin.The Maintenance BITE completes the operational BITEand performs a self-test of the GCU to provide anindication of system integrity. Only the 7 last legfaults are kept in the non volatile memory.



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GENERATOR CONTROL UNIT (GCU 1/2) D/O - BITE


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SELF EXAMINATION

What is the condition of the exciter field when thegenerator starts running?

A - Not electrically supplied.B - Reduced.C - Increased.

What happens when a generator fault is detected?A - The exciter field is no longer supplied

and the GCR trips.B - The exciter field is still supplied and

the GCR stays closed.C - The exciter field is increased and the

GCR trips.

What is the configuration of the electrical networkwhen a zone 1 differential protection has occuredon GEN 1?

A - The whole electrical network is stilloperational.

B - AC BUS 1 is lost.C - AC BUS 2 is lost.

What is the configuration of the electrical networkwhen a zone 2 differential protection has occuredon GEN 1?

A - The whole electrical network is stilloperational.

B - AC BUS 1 is lost.C - AC BUS 2 is lost.

How is a differential protection trip reset?A - At any time from the front face of the

GCU.B - At any time from the corresponding GEN

pushbutton.C - Two reset actions maximum from the

corresponding GEN pushbutton.

What happens if an overload warning occurs?A - The GCR and PR relays stay energized.B - The GCR and PR relays are de-energized.C - The GCR relay stays energized and PR

relay is de-energized.

What happens if a parallel feeder becomes open?A - The GCR relay and the GLC stay closed.B - The GCR relay stays closed and the GLC

opens.C - The GCR relay and the GLC are opened.

TMUELAL01 LEVEL 3


Nov 30/95


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24-22-00 BUS TIE LOGIC

CONTENTS:External Power ONAPU Gen and IDG 2 ONIDG 1 Gen ONNormal ConfigurationSelf Examination

TMUELAM02 LEVEL 3



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BUS TIE LOGIC

The transfer circuit enables to supply both or eitherAC electrical network from one of the four powersources via Bus Tie Contactors.

EXTERNAL POWER ON

With the battery pushbuttons in the OFF position, assoon as the external power is available and selectedON, the Ground Power Control Unit supplies Bus TieContactor 1.BTC 1 being closed, the BAT BUS 3PP is supplied allowingBTC 2 to be energized. The whole aircraft electricalnetwork is supplied by the External Power.

APU GEN AND IDG 2 ON

With APU generator ON and IDG 2 generator ON, the BusTie Contactor 1 is energized and Bus Tie Contactor 2is deenergized.AC BUS 1 is supplied from APU GEN.AC BUS 2 is supplied from IDG 2.

IDG 1 GEN ON

With only the IDG 1 generator ON, both Bus TieContactors are energized.The whole aircraft electrical network is supplied fromthe IDG 1 generator. When the Bus Tie pushbutton isset to OFF ( release out ) , both BTCs are deenergizedand IDG 1 Generator supplies AC BUS 1. AC BUS 2 islost.

NORMAL CONFIGURATION

In normal configuration both Bus Tie Contactors aredeenergized.IDG 1 generator supplies AC BUS 1.IDG 2 generator supplies AC BUS 2.

TMUELAM02-T01 LEVEL 3



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BUS TIE LOGIC

TMUELAM02-P01 LEVEL 3



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SELF EXAMINATION

What is the configuration if both BTCs are open?A - APU GEN supplies AC BUS 1 and EXT PWR

supplies AC BUS 2.B - APU GEN supplies AC BUS 1 and GEN 2

supplies AC BUS 2.C - GEN 1 suppplies AC BUS 1 and GEN 2

supplies AC BUS 2.

What is the configuration if BTC 1 is open and BTC2 is closed?

A - GEN 1 supplies AC BUS 1 and EXT PWRsupplies AC BUS 2.

B - APU GEN supplies AC BUS 1 and EXT PWRsupplies AC BUS 2.

C - EXT PWR supplies AC BUS 1 and GEN 2supplies AC BUS 2.

What is the configuration if both BTCs are closed?A - GEN 1 supplies AC BUS 1 and GEN 2

supplies AC BUS 2.B - APU GEN or EXT PWR or one GEN supplies

AC BUS 1 and AC BUS 2.C - APU GEN supplies AC BUS 1 and EXT PWR

supplies AC BUS 2.

TMUELAM02 LEVEL 3



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24-22-00 MAIN GENERATION COMPONENTS

CONTENTS:Generator Control UnitBus Tie Contactor - Generator Line ContactorAuto Transformer6 Hole Current Transformer3 Hole Current Transformer

TMUELAN01 LEVEL 3

EFFECTIVITY 24-22-00 Page 11Apr 30/96


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MAIN GENERATION COMPONENTS

GENERATOR CONTROL UNIT

IDENTIFICATIONFIN: 1XU1 (GCU1), 1XU2 (GCU2)

LOCATIONZONE: 121

COMPONENT DESCRIPTIONThe 3 GCUs are identical and interchangeable. The GCUfunctions (GCU 1,2 and APU) are selected by pinprogramming.

TMUELAN01-T01 LEVEL 3



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TMUELAN01-P01 LEVEL 3

MAIN GENERATION COMPONENTS - GENERATOR CONTROL UNIT



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BUS TIE CONTACTOR - GENERATOR LINE CONTACTOR

IDENTIFICATIONFIN: 9XU1 (GLC1), 11XU1 (BTC1), 9XU2 (GLC2), 11XU2(BTC2)

LOCATIONZONE: 212

COMPONENT DESCRIPTIONThey are Plug Type Contactors.




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MAIN GENERATION COMPONENTS - BUS TIE CONTACTOR - GENERATOR LINE CONTACTOR




UC64200



AUTO TRANSFORMER

IDENTIFICATIONFIN: 15XN1 (15XN2)

LOCATIONZONE: 212

COMPONENT DESCRIPTIONA 115/26 V single phase autotransformer, supplyingnormal 26V/400Hz sub-busbars (131XP-A and 231XP-A),is connected to each main busbar (AC BUS1: 1XP and ACBUS2: 2XP)




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MAIN GENERATION COMPONENTS - AUTO TRANSFORMER



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6 HOLE CURRENT TRANSFORMER

IDENTIFICATIONFIN: 41XU1 (41XU2)

LOCATIONZONE: 131

COMPONENT DESCRIPTIONThe 6 hole Current Transformer assembly contains sixtoroidal transformers, one for each of the parallelpower feeder cables.The 2 Current Transformers foreach phase are connected in electrical opposition toeach other within the Current Transformer assembly.The6 hole Current Transformer assembly senses openparallel feeders.




UC64200


MAIN GENERATION COMPONENTS - 6 HOLE CURRENT TRANSFORMER




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3 HOLE CURRENT TRANSFORMER


LOCATIONZONE: 212

COMPONENT DESCRIPTIONThe 3 hole Current Transformer assembly contains threetoroidal transformers: one for each of the power feedercables. The line Current Transformers work inconjunction with the generator Current Transformer toprovide differential current, fault sensing andovercurrent sensing




UC64200


MAIN GENERATION COMPONENTS - 3 HOLE CURRENT TRANSFORMER




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TMUELAN01 LEVEL 3



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24-23-00 AC GENERATION - AC AUXILIARYGENERATION D/O

CONTENTS:GeneratorGenerator Control Unit SupplyGenerator Operation ControlGenerator MonitoringGenerator ResetGenerator Temperature MonitoringSelf Examination

TMUELAO02 LEVEL 3



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AC GENERATION - AC AUXILIARY GENERATION D/O

GENERATOR

The APU generator operation principle and the outputcharacteristics are identical to those of the IDGgenerator.The APU directly drives the APU generator at a nominal24000 RPM constant speed.The cooling circuit is common to the APU and to thegenerator.

GENERATOR CONTROL UNIT SUPPLY

The Generator Control Unit supply operation principleis identical to that of the AC Main generation.


The generator is controlled by the APU generationpushbutton. When pressed in, if the APU speed is highenough, the generator is energized.When the APU is available, the APU Ready signal allowsthe Power Relay to be energized via the protectionmodule (Delivered Parameters correct). The APUGenerator Line Contactor (GLC 3) is energized througha priority logic (GLC, BTC, EPC logic).


The generator monitoring operation is identical tothat of the IDG generator.The monitoring system (FAULT light and ECAM system)is inhibited as long as the APU is not available.

GENERATOR RESET

When the APU generator pushbutton is released out aftera fault detection, the Generator Control Unit is reset.The Generator Control Relay (GCR) and the Power Readyrelay (PR) are reset.

GENERATOR TEMPERATURE MONITORING

A temperature sensor is incorporated in the auxiliarygenerator to monitor the oil outlet temperature.The temperature sensor is connected to the ElectronicControl Box (ECB) to shut down the APU in case ofexcessive temperature.

TMUELAO02-T01 LEVEL 3



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AC GENERATION - AC AUXILIARY GENERATION D/OTMUELAO02-P01 LEVEL 3



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SELF EXAMINATION

When does the APU GEN FAULT light come on?A - When the APU is shut down.B - When a fault is detected.C - Both.

Where is the APU generator oil outlet temperaturesignal sent to?

A - To the ECB.B - Directly to the GCU.C - To the GCU through the ECB.

TMUELAO02 LEVEL 3



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24-23-00 AUXILIARY GENERATION COMPONENTS

CONTENTS:Generator Control Unit 3APU Line ContactorAPU GeneratorAPU Generator Substitution Kit

TMUELAQ01 LEVEL 3



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AUXILIARY GENERATION COMPONENTS

GENERATOR CONTROL UNIT 3

IDENTIFICATIONFIN: 1XS

LOCATIONZONE: 121

COMPONENT DESCRIPTIONThis 3 GCUs are identical and interchangeable. The GCUfunctions (GCU 1, 2 and GCU APU) are selected by pinprogramming.

TMUELAQ01-T01 LEVEL 3



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AUXILIARY GENERATION COMPONENTS - GENERATOR CONTROL UNIT 3

TMUELAQ01-P01 LEVEL 3



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APU LINE CONTACTOR


LOCATIONZONE: 212

COMPONENT DESCRIPTIONIt is of the plug type.




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AUXILIARY GENERATION COMPONENTS - APU LINE CONTACTOR




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APU GENERATOR


LOCATIONZONE: 316

COMPONENT DESCRIPTIONInput speed 24000 RPM.Weight: 22.32 kg [49.16 lbs]The APU gearbox provides the oil for cooling andlubrication of the generator.The cooling circuit is common to the APU and thegenerator.




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AUXILIARY GENERATION COMPONENTS - APU GENERATOR




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APU GENERATOR SUBSTITUTION KIT

With the APU generator removed and the replacementgenerator not available a substitution kit consistingof a cover assembly and a cable support assembly mustbe installed on the APU.




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AUXILIARY GENERATION COMPONENTS - APU GENERATOR SUBSTITUTION KIT




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TMUELAQ01 LEVEL 3



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24-24-00 EMERGENCY GENERATOR PRESENTATION

CONTENTS:GeneratorCSM/G Control Unit SupplyGenerator Operation ControlGenerator MonitoringSelf Examination

TMUELAS01 LEVEL 3



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EMERGENCY GENERATOR PRESENTATION

GENERATOR

The Constant Speed Motor/Generator consists of ahydraulic motor which drives a generator.The hydraulic motor is pressurized by the bluehydraulic system through an integrated solenoid valve.The hydraulic motor speed is regulated by a servovalve.The generator operation principle is identical to thatof the main or auxiliary generation. The generatoroutput characteristics are:

- three phase 115/200V. 400Hz (12000RPM)- output power: 5KVA continuously

CSM/G CONTROL UNIT SUPPLY

The Permanent Magnet Generator supplies the ConstantSpeed Motor/Generator control unit and the exciterfield through a voltage regulation module.The voltage regulation module maintains the Point OfRegulation (POR) at a nominal voltage value.

TMUELAS01-T01 LEVEL 3



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EMERGENCY GENERATOR PRESENTATIONTMUELAS01-P01 LEVEL 3



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As the Emergency AC generator parameters are correct,the Emergency Generator Line Contactor is supplied bythe Constant Speed Motor/Generator control unit.The Emergency AC generator has priority to supply theAC and DC ESSential Buses. (Contactors 3XC1 and 3XC2are de-energized).




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EMERGENCY GENERATOR PRESENTATION - GENERATOR OPERATION CONTROLTMUELAS01-P02 LEVEL 3



UC64200




The Constant Speed Motor/Generator operation ismonitored by the red FAULT light.The FAULT light activation is controlled by eitherBattery Charge Limiter (BCL1 or 2).The loss of ESS TR output causes the fault light tocome on.




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EMERGENCY GENERATOR PRESENTATION - GENERATOR MONITORINGTMUELAS01-P03 LEVEL 3



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SELF EXAMINATION

With the Landing Gear uplocked, and after AC Bus 1and 2 failures, when does the RAT and EMER GENFAULT light come on?

A - When the static inverter is lost.B - When the AC and DC ESS buses are lost.C - When the ESS TR is lost.

When does the CSM/G supply the DC and AC ESS buses?A - When AC Bus 1 or 2 is lost.B - When the Emergency Generator parameters

are correct.C - As soon as BAT 2 is lost.

TMUELAS01 LEVEL 3



UC64200



24-24-00 EMERGENCY ELECTRICAL POWER LOGICDESCRIPTION

CONTENTS:Emergency Generation Automatic OperationEmergency Generation Manual Operation In FlightEmergency Generation Manual Operation On GroundEmergency Generator TestSelf Examination

TMUELE501 LEVEL 1



UC64200


EMERGENCY ELECTRICAL POWER LOGIC DESCRIPTION

EMERGENCY GENERATION AUTOMATIC OPERATION

If AC BUS 1 and 2 are lost above a given airspeed(100Kt), the Ram Air Turbine will extend automaticallyeven if power is lost during the air data check ofairspeed.

As the AC generator is not yet available, the AC ESSBUS and DC ESS BUS are respectively supplied by theSTATIC INVERTER and the BATTERY 2.

The activation of the emergency generator via the bluehydraulic system takes place only if the landing gearis up.

As the nose landing gear is no longer uplocked, theAC ESS BUS and DC ESS BUS are respectively suppliedby the STATIC INVERTER and the BATTERY 2.

After a landing gear extension/retraction in emergencyelectrical configuration (during a GO-AROUND forinstance), the EMER ELEC POWER MAN ON pushbutton mustbe used in order to recover the essential network.

With the EMER ELEC PWR MAN ON pushbutton pressed inthe AC ESS BUS and DC ESS BUS are supplied by theemergency generator.




UC64200


EMERGENCY GENERATION AUTOMATIC OPERATIONTMUELE501-P01 LEVEL 1



UC64200



EMERGENCY GENERATION MANUAL OPERATION IN FLIGHT

A dual generator failure occurs and the Ram Air Turbinedoes not extend. FAULT light comes on red on the EMERELEC PWR panel. The Ram Air Turbine must be extended to power theemergency generator. This is done by pressing in theguarded MAN ON pushbutton on the emergency electricalpower panel.Here again, the EMER ELEC PWR/MAN ON pushbutton mustbe used to recover the essential network from theemergency generator, after a landing gearextension/retraction.




UC64200


EMERGENCY GENERATION AUTOMATIC OPERATION IN FLIGHTTMUELE501-P02 LEVEL 1



UC64200



EMERGENCY GENERATION MANUAL OPERATION ON GROUND

CAUTION :If the MAN ON pushbutton is pressed in on ground theRAT extends but does not run.

WARNING :Even in cold aircraft configuration the MAN ONpushbutton is still active.




UC64200


EMERGENCY GENERATION MANUAL OPERATION ON GROUNDTMUELE501-P03 LEVEL 1



UC64200



Emergency Generator Test

The emergency generator operational test is carriedout to check the emergency generator parameters andthe corresponding network supply.For test purposes the blue hydraulic system must bepressurized from the BLUE PUMP OVRD pushbutton and theEMER GEN TEST pushbutton must be held pressed in.As the Emergency generator is connected, check thegenerator parameters on the ECAM display.




UC64200


EMERGENCY GENERATOR TESTTMUELE501-P04 LEVEL 1



UC64200


SELF EXAMINATION

After activation of the blue pump what happensduring the EMER GEN test ?

A - The Ram Air Turbine is extended.B - The emergency generator comes on line.C - The RAT is extended and the emergency

generator comes on line.

On ground, in a cold aircraft configuration whatdoes the activation of the RAT & EMER GEN MAN ONpushbutton cause ?

A - Ram Air Turbine extensionB - NothingC - Emergency generator activation

TMUELE501 LEVEL 1



UC64200



24-24-00 EMERGENCY ELECTRICAL POWER LOGICDESCRIPTION

CONTENTS:Emergency Generation Automatic OperationEmergency Generation Manual Operation In FlightEmergency Generation Manual Operation On GroundEmergency Generator TestSelf Examination

TMUELE502 LEVEL 1



UC64200



EMERGENCY GENERATION AUTOMATIC OPERATION

If AC BUS 1 and 2 are lost above a given airspeed, theRam Air Turbine will extend automatically.As the AC generator is not yet available, the AC ESSBUS and DC ESS BUS are respectively supplied by theSTATIC INVERTER and the BATTERY 2.When the EMER GEN is available, it supplies the AC ESSBUS and DC ESS BUS.




UC64200


EMERGENCY GENERATION AUTOMATIC OPERATIONTMUELE502-P01 LEVEL 1



UC64200



EMERGENCY GENERATION MANUAL OPERATION IN FLIGHT

A dual generator failure occurs and the Ram Air Turbinedoes not extend. FAULT light comes on red on the EMERELEC PWR panel.The RAM Air Turbine must be extended to power theemergency generator. This is done by pressing in theguarded MAN ON pushbutton on the emergency electricalpower panel.




UC64200


EMERGENCY GENERATION MANUAL OPERATION IN FLIGHTTMUELE502-P02 LEVEL 1



UC64200



EMERGENCY GENERATION MANUAL OPERATION ON GROUND

CAUTION :If the MAN ON pushbutton is pressed in on ground theRAT extends but does not run.

WARNING :Even in cold aircraft configuration the MAN ONpushbutton is still active.




UC64200


EMERGENCY GENERATION MANUAL OPERATION ON GROUNDTMUELE502-P03 LEVEL 1



UC64200



Emergency Generator Test

The emergency generator operational test is carriedout to check the emergency generator parameters andthe corresponding network supply.For test purposes the blue hydraulic system must bepressurized from the BLUE PUMP OVRD pushbutton and theEMER GEN TEST pushbutton must be held pressed in.As the Emergency generator is connected,check thegenerator parameters on the ECAM ELEC page.




UC64200


EMERGENCY GENERATOR TESTTMUELE502-P04 LEVEL 1



UC64200


SELF EXAMINATION

After activation of the blue pump what happensduring the EMER GEN test ?

A - The Ram Air Turbine is extended.B - The emergency generator comes on line.C - The RAT is extended and the emergency

generator comes on line.

On ground, in a cold aircraft configuration whatdoes the activation of the RAT & EMER GEN MAN ONpushbutton cause ?

A - Ram Air Turbine extensionB - NothingC - Emergency generator activation

TMUELE502 LEVEL 1



UC64200



24-24-00 RAM AIR TURBINE ACTIVATION

CONTENTS:Automatic ActivationManual ActivationManual Activation From Hyd PanelSelf Examination

TMUELAR01 LEVEL 3



UC64200


RAM AIR TURBINE ACTIVATION

AUTOMATIC ACTIVATION

When speed is higher than 100 knots and when the 2 ACmain buses are lost, the Ram Air Turbine solenoid 1is energized by HOT BATTERY BUS 1 and the Ram AirTurbine extends automatically.In addition, the Constant Speed Motor/GeneratorControl Unit activates the constant Speed MotorGenerator solenoid valve using battery 2. If the noselanding gear is locked up, the generator startsrunning.After a time delay, the Ram Air Turbine solenoid 1 isdeenergized and the Constant Speed Motor/Generatorsolenoid valve is supplied by the Permanent MagnetGenerator.

TMUELAR01-T01 LEVEL 3



UC64200


RAM AIR TURBINE ACTIVATION - AUTOMATIC ACTIVATIONTMUELAR01-P01 LEVEL 3



UC64200



MANUAL ACTIVATION

When the EMER ELEC PWR MAN ON pushbutton is pressedin, the Ram Air Turbine solenoid 2 is energized bybattery 2 and the Ram Air Turbine extends.In addition, the Constant Speed Motor/GeneratorControl Unit activates the CSM/G solenoid valve usingbattery 2. If the nose landing gear is locked up thegenerator starts running.When the EMER ELEC PWR MAN ON pushbutton is releasedout, the Ram Air Turbine solenoid 2 is deenergized.The CSM/G solenoid valve is supplied by the PermanentMagnet Generator.




UC64200


TMUELAR01-P02 LEVEL 3

RAM AIR TURBINE ACTIVATION - MANUAL ACTIVATION



UC64200



MANUAL ACTIVATION FROM HYDRAULIC PANEL

The RAT MAN ON pushbutton on the Blue Hydraulic Panelenables to extend the Ram Air Turbine for hydraulicpower supply only.




UC64200


TMUELAR01-P03 LEVEL 3

RAM AIR TURBINE ACTIVATION - MANUAL ACTIVATION FROM HYDRAULIC PANEL



UC64200


SELF EXAMINATION

How is the RAT extension system controlled?A - By means of two solenoids energized at

the same time.B - By means of two solenoids.C - By means of one solenoid only.

What are the RAT solenoids supplied by?A - Battery or Hot Bat Bus.B - DC Bat Bus.C - DC Bus 1 or 2.

TMUELAR01 LEVEL 3



UC64200



24-24-00 CSM/G CONTROL UNIT

CONTENTS:Generator ControlSpeed RegulationVoltage RegulationGenerator MonitoringBITESelf Examination

TMUELAT01 LEVEL 3



UC64200


CSM/G CONTROL UNIT

GENERATOR CONTROL

The automatic control logic being set, the solenoidcontrol valve is supplied by battery 2 through theControl Unit.The solenoid control valve can also be controlled, inmanual mode, by the EMER ELEC MAN ON pushbutton.As soon as the Permanent Magnet Generator is available,it takes over the solenoid control valve power supply.The Time Delay Opening (TDO) relay is de-energized toallow the Solenoid Control valve power supply changeover from Battery 2 to the PMG.

SPEED REGULATION

The servovalve which regulates the hydraulic motorspeed is electrically controlled by the SpeedRegulation module of the Control Unit.The GCU maintains the CSM/G at constant speed bymonitoring the frequency of the PMG and comparing itwith a controlled reference. The resulting frequencyerror is then used to drive the CSM/G servo-valve viathe speed regulation module.

VOLTAGE REGULATION

The Permanent Magnet Generator supplies the exciterfield through a Voltage Regulation module.The Voltage Regulation module maintains the Point OfRegulation (POR) at the nominal voltage value (115/220VAC). The POR is a voltage pick up made at the linecontactor level(2XE) in the 106VU(upstream of thecontactor).

GENERATION MONITORING

The Control Unit protection module protects the networkand the generator by controlling the associatedGenerator Line Contactor, the generator field currentand the solenoid control valve.The control Unit protections are the following:

- Over/Under voltage.- Over/Under frequency.- Shorted PMG.- Fast overspeed shutdown.

As the generator is lost, the ESS TR is no longersupplied, thus the RAT and EMER GEN FAULT light comeson.When the nose landing gear is selected DOWN the ControlUnit protection module deenergizes the solenoidcontrol valve.After a landing gear extension/retraction sequence,the EMER ELEC PWR MAN ON pushbutton must be pressedin to reset the protection module and to recover theSolenoid Control valve power supply.

BITE

For test purposes, the Constant Speed Motor/GeneratorControl Unit is connected to the Centralized FaultDisplay Interface Unit by two discrete links.

TMUELAT01-T01 LEVEL 3



UC64200


CSM/G CONTROL UNITTMUELAT01-P01 LEVEL 3



UC64200


SELF EXAMINATION

What is the solenoid control valve normallysupplied by when the Constant Speed Motor/Generatoris on line?

A - The CSM/G PMG.B - Battery 2.C - The DC BAT BUS.

What does the Constant Speed Motor/Generatorcontrol unit control when a fault has been detected?

A - The solenoid control valve, the exciterfield and the Generator Line Contactorto off.

B - The exciter field to on, the GeneratorLine Contactor to off and the generatorspeed to low speed.

C - The solenoid control valve to off, theGenerator Line Contactor to on, theexciter field to off.

TMUELAT01 LEVEL 3



UC64200



24-24-00 CSM/G OPERATIONAL TEST -ELECTRICAL CIRCUIT

CONTENTS:Test Pushbutton Pressed-InTest Pushbutton Released-Out

TMUELAV01 LEVEL 3



UC64200


CSM/G OPERATIONAL TEST - ELECTRICAL CIRCUIT

TEST PUSHBUTTON PRESSED-IN

In this configuration, relay 16XE is energized tosimulate AC BUS 1 and 2 loss and speed > 100 Kt. Atthe same time, relay 3PH is de-energized to simulatenose landing gear locked up. The solenoid valve issupplied.After a time delay (relay 22XE), the PMG supplies thesolenoid control valve.

TMUELAV01-T01 LEVEL 3



UC64200


TMUELAV01-P01 LEVEL 3

CSM/G OPERATIONAL TEST - ELECTRICAL CIRCUIT - TEST PUSHBUTTON PRESSED-IN



UC64200


CSM/G OPERATIONAL TEST - ELECTRICAL CIRCUIT

TEST PUSHBUTTON PRESSED-IN

In this configuration, the CSM/G control unitprotection module is tripped (relay 3PH) to stop thegenerator operation.

TMUELAV01-T02 LEVEL 3



UC64200


CSM/G OPERATIONAL TEST - ELECTRICAL CIRCUIT - TEST PUSHBUTTON RELEASED-OUTTMUELAV01-P02 LEVEL 3



UC64200



TMUELAV01 LEVEL 3



UC64200



24-24-00 EMERGENCY GENERATION COMPONENTS

CONTENTS:Constant Speed Motor/GeneratorConstant Speed Motor/Generator Control UnitEmergency Generator Line ContactorContactor 15XEContactor 3XCAutotransformer

TMUELAX01 LEVEL 3



UC64200


EMERGENCY GENERATION COMPONENTS

CONSTANT SPEED MOTOR/GENERATOR

IDENTIFICATIONFIN: 8XE

LOCATIONZONE: 148

COMPONENT DESCRIPTIONThis unit includes a hydraulic motor powered by theblue hydraulic system.

- Output power of 5 KVA.- Output frequency 400 Hz.- Output voltage 115 VAC.- Weight : 9.05 Kg (19.96 lbs).

TMUELAX01-T01 LEVEL 3



UC64200


EMERGENCY GENERATION COMPONENTS - CONSTANT SPEED MOTOR/GENERATOR

TMUELAX01-P01 LEVEL 3



UC64200



CONSTANT SPEED MOTOR/GENERATOR CONTROL UNIT


LOCATIONZONE: 125

COMPONENT DESCRIPTIONThis unit:

- controls the servo-valve excitation for speedregulation.

- controls the generator voltage.- protects the network and the generator bycontrolling line contactors.




UC64200


EMERGENCY GENERATION COMPONENTS - CONSTANT SPEED MOTOR/GENERATOR CONTROL UNIT




UC64200



EMERGENCY GENERATOR LINE CONTACTOR


LOCATIONZONE: 125

COMPONENT DESCRIPTIONThis contactor, controlled by the CSM/G control unit,supplies the network in emergency conditions.




UC64200


EMERGENCY GENERATION COMPONENTS - EMERGENCY GENERATOR LINE CONTACTOR




UC64200



CONTACTOR 15XE


LOCATIONZONE: 125

COMPONENT DESCRIPTIONIn emergency conditions, this contactor, located in106VU, allows the supply of AC ESSENTIAL Bus from theCSM/G.




UC64200


EMERGENCY GENERATION COMPONENTS - CONTACTOR 15XE




UC64200



CONTACTOR 3XC

IDENTIFICATIONFIN: 3XC

LOCATIONZONE: 125

COMPONENT DESCRIPTIONIn normal conditions, this contactor allows the supplyof AC ESS Bus by AC BUS1 and by AC BUS2 if AC BUS1 islost.




UC64200


EMERGENCY GENERATION COMPONENTS - CONTACTOR 3XC




UC64200



AUTOTRANSFORMER

IDENTIFICATIONFIN: 5XH

LOCATIONZONE: 125

COMPONENT DESCRIPTIONA 115/26 V single phase autotransformer, supplying anessential 26V/400 Hz sub-busbar (431XP-A), isconnected to the essential busbar (AC ESS BUS, 4XP).




UC64200


EMERGENCY GENERATION COMPONENTS - AUTOTRANSFORMER




UC64200



TMUELAX01 LEVEL 3



UC64200



24-28-00 AC GENERATION - STATIC INVERTERD/O

CONTENTS:GeneralEmergency Configuration (V above 100 Kts)Emergency Configuration (V between 50 and 100 Kts)Emergency Configuration (V below 50 Kts)MonitoringTestSelf Examination

TMUELBC01 LEVEL 3



UC64200


AC GENERATION - STATIC INVERTER D/O

GENERAL

A Static Inverter transforms the direct current frombattery 1 into a single phase alternating current.The Static Inverter characteristics are:

- 1 KVA nominal power.- 115V, 400Hz, single phase.

The Static Inverter is used in the following cases:- APU start (supply of fuel pump).- Ram Air Turbine deployment.- Engine start on battery (ignition).- Emergency configuration.

TMUELBC01-T01 LEVEL 3



UC64200


AC GENERATION - STATIC INVERTER D/O - GENERALTMUELBC01-P01 LEVEL 3



UC64200



EMERGENCY CONFIGURATION (V above 100 Kts)

In this configuration the Constant SpeedMotor/Generator supplies the AC ESSential Bus and DCESSential Bus through the Essential Rectifier unit.The Static Inverter is not electrically supplied.




UC64200


AC GENERATION - STATIC INVERTER D/O - EMERGENCY CONFIGURATION (V above 100 Kts)TMUELBC01-P02 LEVEL 3



UC64200



EMERGENCY CONFIGURATION (V between 50 and 100 Kts)

In this configuration the Emergency Generator is nolonger connected to the aircraft network. The ACESSential Bus is supplied by the Static Inverter whichis supplied from battery 1.On the other hand, the DC ESSential Bus is directlysupplied by battery 2.The AC STATIC Inverter Bus is also supplied by theStatic Inverter. This bus is used for the APU fuelpump supply.The DC and AC SHED ESSential Buses (circuits PH andXH) are no longer supplied.




UC64200


AC GENERATION - STATIC INVERTER D/O - EMERGENCY CONFIGURATION (V between 50 and 100 Kts)TMUELBC01-P03 LEVEL 3



UC64200



EMERGENCY CONFIGURATION (V below 50 Kts)

In this configuration the AC ESSential Bus is no longerconnected to the Static Inverter.The DC ESS Bus and the AC STATIC INVerter Bus remainsupplied.




UC64200


AC GENERATION - STATIC INVERTER D/O - EMERGENCY CONFIGURATION (V below 50 Kts)TMUELBC01-P04 LEVEL 3



UC64200



MONITORING

Static Inverter faults are signalled to the BatteryCharge Limiter.The Battery Charge Limiter (BCL) memorizes the faultsas Class 1 failures, which will be displayed on theECAM upper display when the aircraft electrical networkis supplied.The following Static Inverter parameters aremonitored:

- overheat,- output/input overvoltage,- input undervoltage.




UC64200


AC GENERATION - STATIC INVERTER D/O - MONITORINGTMUELBC01-P05 LEVEL 3



UC64200



TEST

To perform the Static Inverter test, the EMER GEN TESTpushbutton is pressed in. This simulates an aircraftspeed above 50 knots.The Static Inverter parameters have to be checked onthe ECAM system.




UC64200


AC GENERATION - STATIC INVERTER D/O - TESTTMUELBC01-P06 LEVEL 3



UC64200


SELF EXAMINATION

In emergency configuration with an aircraft speedbelow 50 kts, what is the condition of the aircraftelectrical network?

A - AC ESS BUS, DC ESS BUS and AC STATICINVERTER BUS are supplied.

B - DC ESS BUS, AC STATIC INVERTER BUS andDC BAT BUS are supplied.

C - AC ESS BUS, AC STATIC INVERTER BUS andDC BAT BUS are supplied.

To which computer is a static inverter fault signalsent to?

A - Ground Power Control Unit.B - Generator Control Unit.C - Battery Charge Limiter.

TMUELBC01 LEVEL 3



UC64200



24-28-00 STATIC INVERTER COMPONENTS

CONTENTS:Static InverterContactor 2XBContactor 8PHContactor 8XH

TMUELBF01 LEVEL 3



UC64200


STATIC INVERTER COMPONENTS

STATIC INVERTER

IDENTIFICATIONFIN: 3XB

LOCATIONZONE: 126

COMPONENT DESCRIPTIONThis unit transforms the Direct Current from thebattery bus into a single phase 115V/400HZ AlternatingCurrent.

TMUELBF01-T01 LEVEL 3



UC64200


STATIC INVERTER COMPONENTS - STATIC INVERTER

TMUELBF01-P01 LEVEL 3



UC64200



CONTACTOR 2XB

IDENTIFICATIONFIN: 2XB

LOCATIONZONE: 126

COMPONENT DESCRIPTIONThis contactor allows the supply of the static inverterfrom the BAT1.




UC64200


STATIC INVERTER COMPONENTS - CONTACTOR 2XB




UC64200



CONTACTOR 8PH

IDENTIFICATIONFIN: 8PH

LOCATIONZONE: 125

COMPONENT DESCRIPTIONThis contactor allows the DC SHEDDABLE ESSENTIAL Busto be supplied.




UC64200


STATIC INVERTER COMPONENTS - CONTACTOR 8PH




UC64200



CONTACTOR 8XH

IDENTIFICATIONFIN: 8XH

LOCATIONZONE: 125

COMPONENT DESCRIPTIONWhen closed, this contactor allows the AC ESSENTIALSHEDDABLE Bus to be supplied by the AC ESSENTIAL Bus.




UC64200


STATIC INVERTER COMPONENTS - CONTACTOR 8XH




UC64200



TMUELBF01 LEVEL 3



UC64200



24-25-00 AC ESSENTIAL BUS SWITCHING

CONTENTS:Normal ConfigurationAC Bus 1 LossAC Bus 1 And 2 LossSelf Examination

TMUELAW02 LEVEL 3



UC64200


AC ESSENTIAL BUS SWITCHING


In the normal configuration, the aircraft electricalnetwork is normally supplied and the AC ESSential Busis directly connected to AC Bus 1.

TMUELAW02-T01 LEVEL 3



UC64200


AC ESSENTIAL BUS SWITCHING - NORMAL CONFIGURATION

TMUELAW02-P01 LEVEL 3



UC64200



AC BUS 1 LOSS

In this configuration, the AC ESSential Bus is nolonger supplied.When the AC ESS FEED pushbutton is released out, theAC ESSential Bus supply is recovered from AC Bus 2.The FAULT light goes off and the white ALTN light comeson.




UC64200


AC ESSENTIAL BUS SWITCHING - AC BUS 1 LOSS




UC64200



AC BUS 1 AND 2 LOSS

In this configuration, the AC Emergency generator isconnected to the AC ESSential Bus.The ESS TR is supplied.




UC64200


AC ESSENTIAL BUS SWITCHING - AC BUS 1 AND 2 LOSS




UC64200


SELF EXAMINATION

In the normal configuration, which of the followingsupplies the AC ESS Bus?

A - AC Bus 2.B - Emerg. Generator.C - AC Bus 1.

What happens with the aircraft electrical networknormally supplied, and the AC ESS FEED pushbuttonreleased out (ALTN)?

A - AC ESS Bus is supplied by the EMERG GEN.B - AC ESS Bus is supplied by AC Bus 1.C - AC ESS Bus is supplied by AC Bus 2.

TMUELAW02 LEVEL 3



UC64200



24-00-00 FUEL PUMPS ELECTRICAL POWERSUPPLY IN SMOKE CONFIGURATION

CONTENTS:Normal Electrical SupplySmoke WarningEMER ELEC GEN 1 LINE OFFEMER ELEC PWR MAN ONGEN 2 OFF

TMUELE802 LEVEL 1



UC64200


FUEL PUMPS ELECTRICAL POWER SUPPLY IN SMOKE CONFIGURATION

NORMAL ELECTRICAL SUPPLY

Here is the normal electrical supply of the wing fuelpumps. Left pump 1 and right pump 1 are supplied byAC BUS 1.




UC64200


NORMAL ELECTRICAL SUPPLYTMUELE802-P01 LEVEL 1



UC64200



SMOKE WARNING

If an avionics smoke warning occurs and smoke isconfirmed, several actions have to be taken by thecockpit crew concerning mainly the ventilation andcommunication systems.If the smoke warning remains 5mn after actions on theventilation and communication systems, the followingprocedure must be applied.




UC64200


SMOKE WARNINGTMUELE802-P02 LEVEL 1



UC64200



1 - EMER ELEC GEN 1 LINE OFF

GEN 1 LINE contactor opens. GEN 1 remains energizedand supplies one fuel pump in each wing tank. AC BUS1 is supplied by GEN 2 through Bus Tie Contactors.




UC64200


EMER ELEC GEN 1 LINE OFFTMUELE802-P03 LEVEL 1



UC64200



2 - EMER ELEC PWR MAN ON

The RAT is extended and the emergency generator isconnected to the aircraft network by its control unit,when the parameters are correct. The emergencygenerator then supplies the AC ESS bus and DC ESS busthrough ESS TR.




UC64200


EMER ELEC PWR MAN ONTMUELE802-P04 LEVEL 1



UC64200



3 - GEN 2 OFF

When EMER GEN AVAIL: GEN 2 OFF

Note: Before L/G extension, GEN 2 and EMER ELEC GEN 1 LINE must to be set to ON.




UC64200



GEN2 OFF



UC64200



TMUELE802 LEVEL 1



UC64200



24-00-00 AC/DC SHEDDABLE BUS SUPPLY

CONTENTS:Normal ConfigurationEmergency ConfigurationCabin System Shedding

TMUELBE02 LEVEL 3



UC64200


AC/DC SHEDDABLE BUS SUPPLY


The AC and DC Sheddable buses are supplied by thecorresponding Essential buses.

TMUELBE02-T01 LEVEL 3



UC64200


AC/DC SHEDDABLE BUS SUPPLY - NORMAL CONFIGURATION

TMUELBE02-P01 LEVEL 3



UC64200



EMERGENCY CONFIGURATION

In emergency configuration and CSM/G not available theStatic Inverter supplies the AC electrical system.The ESS Sheddable buses are no longer supplied duringStatic Inverter operation (relays 2XB and 6XBenergized).The AC and DC sheddable buses are also disconnectedduring a CSM/G operational test. (relays 16XE and 21XErelays).




UC64200



AC/DC SHEDDABLE BUS SUPPLY - EMERGENCY CONFIGURATION



UC64200



CABIN SYSTEM SHEDDING

AC and DC sheddable buses are installed in panels 120VUand 2000VU for cabin related systems.All sheddable buses are off in single generatoroperation (10XA de-energized).Only the DC buses are shed in single TR operation (1PC2energized).If the GALY & CAB p/b (2XA) is released all these busesand all galleys are shed.




UC64200



AC/DC SHEDDABLE BUS SUPPLY - CABIN SYSTEM SHEDDING



UC64200



TMUELBE02 LEVEL 3



UC64200



24-40-00 EXTERNAL POWER - GENERALDESCRIPTION

CONTENTS:Normal ParametersAbnormal ParametersSelf Examination

TMUELAY01 LEVEL 2



UC64200


EXTERNAL POWER - GENERAL DESCRIPTION

The aircraft network can be supplied by a Ground PowerUnit connected to an external receptacle locatedforward of the Nose Landing Gear well.

NORMAL PARAMETERS

If the External Power parameters are correct, theindicator lights on the external power receptacle andthe EXTERNAL POWER AVAILABLE light on the cockpitoverhead panel come on.The Ground Power parameters are monitored by the GroundPower Control Unit (GPCU) which activates the indicatorlights. With such indications the Ground Cart cansupply the aircraft network.As soon as the External Power pushbutton is pressedin, the Ground Power Control Unit closes the ExternalPower Contactor to supply the aircraft electricalnetwork.The Bus Tie Contactors (BTC 1 and BTC 2) close onlyif no engine generators are on line.

ABNORMAL PARAMETERS

If any external power parameter is not correct, theindicator lights stay off.The external power cannot be connected to the aircraftnetwork.The detection of a GPCU fault causes the EPC to open.

TMUELAY01-T01 LEVEL 2



UC64200


EXTERNAL POWER - GENERAL DESCRIPTION

TMUELAY01-P01 LEVEL 2



UC64200


SELF EXAMINATION

With the engine generators on line, what does theEXT PWR ON light indicate when lit?

A - The external ground cart is supplyingthe AC BUS 1 and 2.

B - The External Power Contactor iscontrolled to close.

C - The external ground cart is supplyingthe AC/DC ground service buses.

What does the EXT PWR AVAIL light indicate when lit?A - The Ground Power Control Unit has

tripped the external ground cart.B - The external ground cart is connected to

the aircraft network.C - The external ground cart can be

connected to the aircraft network.

TMUELAY01 LEVEL 2



UC64200



24-41-00 EXTERNAL POWER SYSTEM D/O

CONTENTS:Ground CartOperation ControlProtectionSelf Examination

TMUELAZ02 LEVEL 2



UC64200


EXTERNAL POWER SYSTEM D/O

GROUND CART

The Ground Cart is plugged into the aircraft by meansof a standard 6 pin connector.

TMUELAZ02-T01 LEVEL 2



UC64200


EXTERNAL POWER SYSTEM D/O - GROUND CART

TMUELAZ02-P01 LEVEL 2



UC64200



OPERATION CONTROL (1)

With the Ground Cart running and switched on, theGround Power Control Unit allows the activation of theindicator lights through the Pin Monitoring Relay andthe Power Ready relay.




UC64200


EXTERNAL POWER SYSTEM D/O - OPERATION CONTROL (1)




UC64200



OPERATION CONTROL (2)

The External Power Contactor is energized through aBus Tie Contactor/Generator Line Contactor logic, bypressing the External Power pushbutton.In the cockpit, the EXT PWR AVAIL light goes off aswell as the NOT IN USE light on the external powerreceptacle.




UC64200


EXTERNAL POWER SYSTEM D/O - OPERATION CONTROL (2)




UC64200



PROTECTION

In case of Ground Cart malfunction, the ProtectionModule integrated in the Ground Power Control Unittrips the Power Ready relay which opens the ExternalPower Contactor.In the same way, a faulty Ground Cart cannot beconnected to the aircraft network. In this case, thereis no indication at all.




UC64200


EXTERNAL POWER SYSTEM D/O - PROTECTION




UC64200


SELF EXAMINATION

The Ground Cart is running and switched on, the EXTPWR pushbutton is pressed in and there is noindication. What does that configuration mean?

A - The GPCU is supplied and the EPC is open.B - The GPCU is not supplied and the EPC is

open.C - The GPCU is supplied and the EPC is

closed.

What is the indication on the external powerreceptacle when the ground cart is connected to theaircraft network?

A - NOT IN USE light ON and AVAIL light ON.B - NOT IN USE light OFF and AVAIL light ON.C - NOT IN USE light OFF and AVAIL light OFF.

TMUELAZ02 LEVEL 2



UC64200



24-41-00 GROUND POWER CONTROL UNIT (GPCU)D/O

CONTENTS:SupplyMonitoringBITESelf Examination

TMUELBA01 LEVEL 3



UC64200


GROUND POWER CONTROL UNIT (GPCU) D/O

SUPPLY

The Ground Power Control Unit is supplied by the GroundCart through the External Power receptacle andanalyses the voltage inputs.The Pin Monitoring Relay (PMR) is energized under thefollowing conditions:

- Ground Cart plugged in and running (voltage atpin E between 5 and 42 volts).

- and Ground Cart switched ON (voltage at pin Fbelow 42 volts and AC voltage at pins A, B andC within the limits).

If the delivered parameters are correct, the GroundPower Control Unit allows the External Power Contactorto be controlled.Two conditions must be fulfilled to energize the PowerReady relay (PR):

- valid EP (External Power) Interlock.- and delivered parameters within the limits.

MONITORING

The Ground Power Control Unit monitors the AC and DCparameters.AC protections are:

- over/under voltage.- over/under frequency.- Incorrect Phase Sequence (IPS).

DC protection is provided by External Power Receptaclepin voltage monitoring.The protection system also includes a GPCU InternalFault detection device.

BITE

The Ground Power Control Unit contains an internalBITE system to help in system trouble-shooting. TheBITE system detects and isolates active and passivefailures.The BITE system consists of two sections:

- operational BITE.- maintenance BITE.

The operational BITE identifies the protection,analyses the conditions and determines the faultorigin.The maintenance BITE completes the operational BITEand performs a self test to provide an indication ofsystem integrity in ground mode only.A Class 2 failure signal is sent to the ElectricalGeneration Interface Unit in order to display GroundPower Control Unit message on the ECAM status page.The CFDS class 2 message is labelled as:IDG 1 (2) HIGH DELTA TEMPTo enable the 3 Generator Control Units to dialoguewith the Centralized Fault Display Interface Unit(CFDIU) through the Ground Power Control Unit (GPCU),the GPCU receives a back-up supply from the DC BAT BUS(301PP).

TMUELBA01-T01 LEVEL 3



UC64200


GROUND POWER CONTROL UNIT (GPCU) D/O

TMUELBA01-P01 LEVEL 3



UC64200


SELF EXAMINATION

What does the Pin Monitoring Relay (PMR) within theGround Power Control Unit ( GPCU ) monitor?

A - The voltage and frequency.B - The correct phase sequence.c - The pin DC voltage at the External Power

Receptacle.

Is the Ground Power Control Unit supplied inflight?

A - Yes from the DC BAT BUS.B - No.C - Yes from the DC GROUND SERVICE BUS.

When the aircraft is on ground, with the externalGround Cart connected, where is the Ground PowerControl Unit supplied from?

A - The Ground Cart and the DC BAT BUS.B - The DC BAT BUS only.c - The Ground Cart only.

TMUELBA01 LEVEL 3



UC64200



24-41-00 EXTERNAL POWER COMPONENTS

CONTENTS:External Power ContactorGround Power Control UnitExternal Power Receptacle

TMUELBB01 LEVEL 3



UC64200


EXTERNAL POWER COMPONENTS

EXTERNAL POWER CONTACTOR

IDENTIFICATIONFIN : 3XG

LOCATIONZONE : 212

COMPONENT DESCRIPTIONIt is a plug type contactor.

TMUELBB01-T01 LEVEL 3



UC64200


EXTERNAL POWER COMPONENTS - EXTERNAL POWER CONTACTOR

TMUELBB01-P01 LEVEL 3



UC64200



GROUND POWER CONTROL UNIT


LOCATIONZONE : 122




UC64200


EXTERNAL POWER COMPONENTS - GROUND POWER CONTROL UNIT




UC64200



EXTERNAL POWER RECEPTACLE - VIEW FROM INSIDE


LOCATIONZONE : 121




UC64200



EXTERNAL POWER COMPONENTS - EXTERNAL POWER RECEPTACLE - VIEW FROM INSIDE



UC64200



TMUELBB01 LEVEL 3



UC64200



24-42-00 AC/DC GROUND SERVICEDISTRIBUTION - ELECTRICAL CIRCUIT

CONTENTS:EXT PWR Pushbutton ONMAINT BUS Switch ONTR2 Failure

TMUELBJ01 LEVEL 3



UC64200


AC/DC GROUND SERVICE DISTRIBUTION - ELECTRICAL CIRCUIT

EXT PWR PUSHBUTTON ON

The whole aircraft electrical network is suppliedincluding the AC and DC GRND FLT Buses.

TMUELBJ01-T01 LEVEL 3



UC64200


AC/DC GROUND SERVICE DISTRIBUTION - ELECTRICAL CIRCUIT - EXT PWR PUSHBUTTON ONTMUELBJ01-P01 LEVEL 3



UC64200



MAINT BUS SWITCH ON

External power is available but not in use.Only the AC and DC GRND Buses are supplied.

NOTE: If External Power is in use, an action on theMAINT BUS SWITCH has no effect except for MAINTBUS SWITCH to be on: AC and DC GRND Buses arealready supplied.




UC64200


AC/DC GROUND SERVICE DISTRIBUTION - ELECTRICAL CIRCUIT - MAINT BUS SWITCH ON TMUELBJ01-P02 LEVEL 3



UC64200



TR2 FAILURE

If TR2 fails, the AC and DC GRND FLT Buses are lost.




UC64200


AC/DC GROUND SERVICE DISTRIBUTION - ELECTRICAL CIRCUIT - TR2 FAILURETMUELBJ01-P03 LEVEL 3



UC64200



TMUELBJ01 LEVEL 3



UC64200



24-00-00 DC GENERATION COMPONENTS

CONTENTS:Contactor 14 PUContactors 12 XX 14 XXContactor 3 PXContactor 8 PNContactor 12 XN

TMUELBO01 LEVEL 3



UC64200


DC GENERATION COMPONENTS

CONTACTOR 14 PU

IDENTIFICATIONFIN: 14PU

LOCATIONZONE: 212

COMPONENT DESCRIPTIONThis contactor when closed allows AC service BUS andTR2 normal supply.

TMUELBO01-T01 LEVEL 3



UC64200


DC GENERATION COMPONENTS - CONTACTOR 14 PU

TMUELBO01-P01 LEVEL 3



UC64200


CONTACTORS 12 XX 14 XX

IDENTIFICATIONFIN: 12XX, 14XX

LOCATIONZONE: 212

COMPONENT DESCRIPTIONThey are plug type contactors.




UC64200



DC GENERATION COMPONENTS - CONTACTORS 12 XX 14 XX



UC64200


CONTACTOR 3 PX

IDENTIFICATIONFIN: 3PX

LOCATIONZONE: 212

COMPONENT DESCRIPTIONIt is a plug type contactor.




UC64200



DC GENERATION COMPONENTS - CONTACTOR 3 PX



UC64200


CONTACTOR 8 PN

IDENTIFICATIONFIN: 8PN

LOCATIONZONE: 212

COMPONENT DESCRIPTIONThis contactor allows the DC SERVICE Bus normal supply.




UC64200


DC GENERATION COMPONENTS - CONTACTOR 8 PN




UC64200


CONTACTOR 12 XN

IDENTIFICATIONFIN: 12XN

LOCATIONZONE: 212




UC64200


DC GENERATION COMPONENTS - CONTACTOR 12 XN




UC64200



TMUELBO01 LEVEL 3



UC64200



24-32-00 DC GENERATION - DC MAINGENERATION D/O

CONTENTS:Transformer RectifiersBatteriesDistributionTransformer Rectifier OperationBattery OperationBattery Charge Limiter FunctionsSelf Examination

TMUELBK01 LEVEL 3



UC64200


DC GENERATION - DC MAIN GENERATION D/O

TRANSFORMER RECTIFIERS

There are three identical Transformer Rectifiers (TR1,TR2, and ESSential TR).Each Transformer Rectifier (TR) converts the threephase AC into 28 VDC.

BATTERIES

There are two identical nickel-cadmium batteries of20 cells each.If the battery voltage is below 25 VDC, when no otherelectrical source is available, a charging cycle isneeded by setting the BAT P/B to ON and supplying theDC normal network to permit charging.The nominal capacity of each battery is 23 Ah.

DISTRIBUTION

TR1, powered from AC BUS 1, supplies DC BUS 1 and DCBAT BUS.TR2, powered from AC BUS 2, supplies DC BUS 2.The ESS TR is either supplied from the AC ESS BUS orthe EMERGENCY GENERATOR. It can supply the DC ESS BUSand the DC ESSENTIAL SHEDDABLE BUS when required.The two batteries are connected to the DC BAT BUS.Battery 1 can also supply the static inverter andBattery 2 can supply the DC ESS BUS.

TRANSFORMER RECTIFIER OPERATION

The Transformer Rectifiers start to operate as soonas they are supplied by the associated AC busbar.Automatic switching is provided in case of TR1 or TR2failure, to guarantee power supply to all affected DCbusbars.

BATTERY OPERATION

Battery 1 and Battery 2 are charged from DC BAT BUSthrough contactors.These contactors are controlled by the Battery ChargeLimiters (BCL).

BATTERY CHARGE LIMITER FUNCTIONS

Each BCL controls its battery contactor. The BCLs areidentical and interchangeable.The battery contactors are controlled in order to:

- ensure automatic battery connection forcharging,

- protect the battery against thermal runawayand short circuit,

- prevent complete discharging.

TMUELBK01-T01 LEVEL 3



UC64200


DC GENERATION - DC MAIN GENERATION D/OTMUELBK01-P01 LEVEL 3



UC64200


SELF EXAMINATION

Which power source supplies the ESS TR?A - AC BUS 1 or AC BUS 2.B - AC BUS 1 AND AC BUS 2.C - AC ESS BUS or EMERGENCY GENERATOR.

Which equipment controls the battery contactor?A - GCUB - BCLC - Static Inverter.

TMUELBK01 LEVEL 3



UC64200



24-35-00 DC NORMAL AND ESSENTIALGENERATION SWITCHING D/O

CONTENTS:Normal ConfigurationTR1 LossTR2 LossSelf Examination

TMUELBM01 LEVEL 3

EFFECTIVITY 24-35-00 Page 1Feb 30/96


UC64200


DC NORMAL AND ESSENTIAL GENERATION SWITCHING D/O


In normal configuration TR 1 supplies successively DCBUS 1, DC BAT BUS, DC ESSENTIAL BUS and DC ESSENTIALSHED BUS.TR 2 supplies only DC BUS 2.

TMUELBM01-T01 LEVEL 3



UC64200


DC NORMAL AND ESSENTIAL GENERATION SWITCHING D/O - NORMAL CONFIGURATION

TMUELBM01-P01 LEVEL 3



UC64200



TR1 LOSS

If TR1 fails, TR2 automatically supplies DC BAT BUSand DC BUS 1 through DC BUS 2.The DC ESSENTIAL BUS supply is automaticallytransferred from DC BAT BUS to AC ESSENTIAL BUS throughthe ESSENTIAL Transformer Rectifier.




UC64200


DC NORMAL AND ESSENTIAL GENERATION SWITCHING D/O - TR1 LOSS




UC64200



TR2 LOSS

If TR 2 fails, TR 1 automatically supplies DC BUS 2through DC BUS 1 and DC BAT BUS.The DC ESSENTIAL BUS supply is automaticallytransferred from DC BAT BUS to AC ESSENTIAL BUS throughthe ESSENTIAL Transformer Rectifier.




UC64200


DC NORMAL AND ESSENTIAL GENERATION SWITCHING D/O - TR2 LOSS




UC64200


SELF EXAMINATION

What is the DC ESS network power source if TR 1 hasfailed?

A - AC ESS BUSB - DC BAT BUSC - CSM/G

What is the DC ESS Bus supply if TR 2 has failed?A - TR 1B - ESS TRC - BAT 2

TMUELBM01 LEVEL 3



UC64200



24-35-00 DC NORMAL AND ESS GENERATIONSWITCHING - ELECTRICAL CIRCUIT

CONTENTS:Normal ConfigurationTR1 or TR2 LossDC Bus Tie Failure

TMUELBN01 LEVEL 3



UC64200


DC NORMAL AND ESS GENERATION SWITCHING-ELECTRICAL CIRCUIT


TMUELBN01-T01 LEVEL 3



UC64200


DC NORMAL AND ESS GENERATION SWITCHING - ELECTRICAL CIRCUIT - NORMAL CONFIGURATION

TMUELBN01-P01 LEVEL 3



UC64200


DC NORMAL AND ESS GENERATION SWITCHING-ELECTRICAL CIRCUIT

TR1 OR TR2 LOSS

This configuration shows a TR1 loss.




UC64200


DC NORMAL AND ESS GENERATION SWITCHING - ELECTRICAL CIRCUIT - TR1 OR TR2 LOSS




UC64200


NORMAL AND ESS GENERATION SWITCHING-ELECTRICAL CIRCUIT

DC BUS TIE FAILURE

In the event of a DC bus tie contactor failure (4PCor 1PC1) the DC ESS bus supply is recovered from theESS TR. The DC BUS TIE class 2 failure message isdisplayed on the ECAM status page.




UC64200


DC NORMAL AND ESS GENERATION SWITCHING - ELECTRICAL CIRCUIT - DC BUS TIE FAILURE




UC64200



TMUELBN01 LEVEL 3



UC64200



24-32-00 DC GENERATION - TRANSFORMERRECTIFIER D/O

CONTENTS:GeneralTR ProtectionTR1 Normal ConfigurationTR1 Abnormal ConfigurationTR1 Reset ConfigurationTR2Essential TRSelf Examination

TMUELBL01 LEVEL 3



UC64200


DC GENERATION - TRANSFORMER RECTIFIER D/O

GENERAL

Three identical Tranformer Rectifiers (TR) are fittedon the aircraft. They operate as soon as they aresupplied. The Transformer Rectifiers (TR) are suppliedwith three phase 115 V/400 Hz.Each TR controls its contactor via an internal logic.

TR PROTECTION

Each Transformer Rectifier control logic consists ofan overheat protection and a minimum current flowdetection to isolate the distribution circuit from theTransformer Rectifier.

TR1 NORMAL CONFIGURATION

As soon as AC Bus1 is supplied, the TransformerRectifier output is delivered to the DC Bus through acontrol contactor which is energized by the TRprotection module.The protection module is supplied by DC Bus 2 (204PP).The Transformer Rectifier current, voltage as well asthe TR contactor position indications are sent to theECAM system via SDAC 1 and 2.

TMUELBL01-T01 LEVEL 3



UC64200


DC GENERATION - TRANSFORMER RECTIFIER D/OTMUELBL01-P01 LEVEL 3



UC64200



TR1 ABNORMAL CONFIGURATION

In the event of a TR fault detection, the DC bus 1control contactor is no longer energized.The fault signals are sent to the ECAM system, theCFDIU and to the DC normal generation switching system(1PC1-1PC2)




UC64200


DC GENERATION - TRANSFORMER RECTIFIER D/O - TR1 ABNORMAL CONFIGURATIONTMUELBL01-P02 LEVEL 3



UC64200



TR1 RESET CONFIGURATION

When the fault disappears, the TR remains deactivated.Reset action is necessary for TR reactivation.The Transformer Rectifier protection reset is possibleeither from the Centralized Fault Display System viaMCDU or from the pusbutton located in the avionicsbay.




UC64200


DC GENERATION - TRANSFORMER RECTIFIER D/O - TR1 RESET CONFIGURATIONTMUELBL01-P03 LEVEL 3



UC64200



TR2

The operation of TR2 is identical to that of TR1.When AC and DC GRND FLT Buses are only supplied byexternal power, the TR2 minimum current detectionsystem is inhibited.




UC64200


DC GENERATION - TRANSFORMER RECTIFIER D/O - TR2TMUELBL01-P04 LEVEL 3



UC64200



ESSENTIAL TR

The essential TR operation is identical to that of TR1and TR2.ESS TR fault signals are sent to Flight WarningComputer 1 and 2.




UC64200


DC GENERATION - TRANSFORMER RECTIFIER D/O - ESSENTIAL TRTMUELBL01-P05 LEVEL 3



UC64200


SELF EXAMINATION

What are the protections for a TransformerRectifier unit?

A - Overheat and minimum current detection.B - Overheat and overvoltage detection.C - Overheat and overcurrent detection.

How can a Tranformer Rectifier unit be reset?A - Either from the Battery Charge Limiter

or a pushbutton in the avionics bay.B - Either from a pusbutton in the avionics

bay or automatically at power up.C - Either from the Centralized Fault

Display System or a pushbutton in theavionics bay.

When is the TR2 minimum current detection systeminhibited?

A - On ground when the aircraft electricalnetwork is supplied by the APU generator.

B - On ground when the AC and DC GRND FLTBuses are only supplied by externalpower.

C - On ground when the AC and DC GRND FLTBuses are supplied by external power.

TMUELBL01 LEVEL 3



UC64200



24-00-00 DC MAIN GENERATION COMPONENTS

CONTENTS:Main TRsContactor 3PEContactors 5PU1-5PU2Contactors 1PC1-1PC2Contactor 4PCESS TR

TMUELBP01 LEVEL 3



UC64200


DC MAIN GENERATION COMPONENTS

MAIN TRs

IDENTIFICATIONFIN: 1PU 1/2

LOCATIONZONE: 126

COMPONENT DESCRIPTIONMain TRs are ventilated by the aircraft ventilationnetwork. Power delivered: 28VDC-200AWeight: 5 kgDC voltage:

- 30.2V with no load- 27.5V at 200A

TMUELBP01-T01 LEVEL 3



UC64200


DC MAIN GENERATION COMPONENTS - MAIN TRs

TMUELBP01-P01 LEVEL 3



UC64200



CONTACTOR 3PE

IDENTIFICATIONFIN: 3PE

LOCATIONZONE: 125

COMPONENT DESCRIPTIONThis contactor, controlled by its transformerrectifier via an internal TR logic makes DC poweravailable for DC ESS BUS.




UC64200


DC MAIN GENERATION COMPONENTS - CONTACTOR 3PE




UC64200



CONTACTORS 5PU1-5PU2

IDENTIFICATIONFIN: 5PU 1/2

LOCATIONZONE: 212

COMPONENT DESCRIPTIONThese contactors, controlled by their TransformerRectifiers via an internal TR logic make DC poweravailable for its DC BUS.




UC64200


DC MAIN GENERATION COMPONENTS - CONTACTORS 5PU1-5PU2




UC64200



CONTACTORS 1PC1-1PC2

IDENTIFICATIONFIN: 1PC 1/2

LOCATIONZONE: 212

COMPONENT DESCRIPTIONThese contactors allow respectively DC BUS1 and DCBUS2 switching.




UC64200


DC MAIN GENERATION COMPONENTS - CONTACTORS 1PC1-1PC2




UC64200



CONTACTOR 4PC

IDENTIFICATIONFIN: 4PC

LOCATIONZONE: 125

COMPONENT DESCRIPTIONThis contactor supplies, in some cases, the DC ESS busbar.




UC64200


DC MAIN GENERATION COMPONENTS - CONTACTOR 4PC




UC64200



ESS TR

IDENTIFICATIONFIN: 1PE

LOCATIONZONE: 125

COMPONENT DESCRIPTIONPower delivered: 28VDC-200AWeight: 5 kgDC voltage:

- 30.2 v with no load- 27.5 v at 200A




UC64200


DC MAIN GENERATION COMPONENTS - ESS TR




UC64200



TMUELBP01 LEVEL 3



UC64200



24-38-00 BATTERY SYSTEM D/O

CONTENTS:GeneralBattery DescriptionBattery ControlIndicating/MonitoringSelf Examination

TMUELBQ02 LEVEL 3



UC64200


BATTERY SYSTEM D/O

GENERAL

The battery system is composed of two batteries whichare mainly used to start the APU and supply AC and DCessential network in emergency configuration.

Each battery is associated to one Battery ChargeLimiter (BCL). The BCL ensures battery charge andbattery protection by controlling the batterycontactor.

BATTERY DESCRIPTION

The two batteries are identical and interchangeable.Each battery is ventilated by two ducts. Thedifferential pressure between the cabin and the outsideis used to provide battery ventilation.

Each battery has 20 nickel cadmium cells in a stainlesssteel case. Each cell can be removed separately.

Battery nominal voltage: 24 VDC.Battery nominal capacity: 23 Ah.

BATTERY CONTROL

Each battery is associated to a Battery Charge Limiterwhich is controlled by the corresponding batterypushbutton.

When the BAT pushbutton is pressed in (AUTO position),the BCL controls the battery coupling / uncoupling.When released out, the battery is uncoupled from thenetwork and the white OFF light comes on.

NOTE: In flight, in normal configuration, thebatteries are uncoupled from the network.

INDICATING/MONITORING

Battery parameters such as voltage, current andwarnings are displayed by the ECAM.The voltmeters, located on the main control panel,give battery voltage indication even in a cold aircraftconfiguration.

The BCLs monitor the charge of the batteries.In the event of battery thermal runaway or internalshort circuit, the battery is isolated, the amber FAULTlight comes on and the ECAM system is activated.System failures and BITE data are sent to theCentralized Fault Display System (CFDS).

TMUELBQ02-T01 LEVEL 3



UC64200


BATTERY SYSTEM D/OTMUELBQ02-P01 LEVEL 3



UC64200


SELF EXAMINATION

In cold aircraft configuration (no AC and DCsupply), where is (are) the battery indication(s)displayed?

A - On the ECAM.B - On the ELEC PWR control panel.C - There is no indication.

When does the BAT FAULT light come on?A - When the BAT pushbutton is set to OFF.B - When the discharge current is too high.C - When a thermal runaway or an internal

short circuit occurs.

TMUELBQ02 LEVEL 3



UC64200



24-38-00 BATTERY CHARGE LIMITER FUNCTIONS

CONTENTS:Battery Charge Control and MonitoringBattery ProtectionEmergency ConfigurationAPU StartTestSelf Examination

TMUELBR01 LEVEL 3

EFFECTIVITY 24-38-00 Page 1Dec 31/95


UC64200



BATTERY CHARGE CONTROL AND MONITORING

The Battery Charge Limiter controls the battery chargecycle.The battery charge cycle begins when the batteryvoltage is lower than 26.5V and stops when the batterycharge current is lower than 4 Amps.The Battery Charge Limiter isolates the DC BAT BUSfrom the battery in case of thermal runaway detectionor an internal short circuit.The fault detection signal allows the activation ofthe BAT1 amber FAULT light, the ECAM system and theCFDS.

BATTERY PROTECTION

In order to keep the integrity of the HOT BUS, in theevent of short circuit in the DC network, the BatteryCharge Limiter isolates the battery from itsdistribution network.On ground the batteries are automatically isolatedwhen battery voltage decreases to 22V for 1 second.

EMERGENCY CONFIGURATION

The batteries are connected to the BATTERY BUS afterlanding in emergency configuration.The battery contactors are closed by the BCL when theaircraft speed is lower than 100 Kts.

APU START

When the APU start sequence is initated, the DC networkis connected to the batteries in order to withstandthe high APU starter motor demand.In flight, in electrical emergency configuration, theAPU start sequence is inhibited until the CSM/G iscoupled to the network or after 45 seconds. The APUstart sequence is also inhibited in emergencyconfiguration when the landing gear is extended.

TEST

On ground the BITE allows to perform a test of theBattery Charge Limiter at each power up, and a testfrom the Centralized Fault Display System.During the test initiated from the MCDU, the BAT amberFAULT light and the RAT & EMER GEN red FAULT lightcome on for 6 seconds.

TMUELBR01-T01 LEVEL 3



UC64200


TMUELBR01-P01 LEVEL 3




UC64200


SELF EXAMINATION

What is the DC network configuration in flight inelectrical emergency configuration during APU startsequence?

A - BAT BUS disconnected from the batteries. B - BAT BUS connected to the batteries. C - BAT BUS connected to BAT1 only.

When does the LOW BAT voltage detection systemoperate?

A - On ground, with the BAT (1/2)pushbutton in the AUTO position.

B - In flight, with the BAT pushbutton inthe AUTO position.

C - On ground, with the BAT pushbutton inthe OFF position.

TMUELBR01 LEVEL 3



UC64200



24-38-00 BATTERY COMPONENTS

CONTENTS:VoltmetersBatteriesContactorsBattery Charge Limiters

TMUELBT02 LEVEL 3



UC64200


BATTERY COMPONENTS

VOLTMETERS

IDENTIFICATIONFIN: 3PV1, 3PV2

LOCATIONZONE: 211

COMPONENT DESCRIPTIONThe voltmeters, located on the overhead panel, indicateto the flight crew the voltage of hot busses.The digital display is a Liquid Crystal Display unitwhich includes a lighting system.

TMUELBT02-T01 LEVEL 3



UC64200


BATTERY COMPONENTS - VOLTMETERS

TMUELBT02-P01 LEVEL 3



UC64200


BATTERY COMPONENTS

BATTERIES

IDENTIFICATIONFIN: 2PB1, 2PB2

LOCATIONZONE: 126

COMPONENT DESCRIPTIONEach battery of the nickel-cadmium type is composedof twenty elements housed in a stainless steel case.

- Nominal voltage: 24 VDC.- Nominal capacity: 23 Ah.




UC64200


BATTERY COMPONENTS - BATTERIES




UC64200


BATTERY COMPONENTS

CONTACTORS


LOCATIONZONE: 126

COMPONENT DESCRIPTIONThe battery contactors are controlled by Battery ChargeLimiters.




UC64200


BATTERY COMPONENTS - CONTACTORS




UC64200


BATTERY COMPONENTS

BATTERY CHARGE LIMITERS


LOCATIONZONE: 126

COMPONENT DESCRIPTIONThe main function of the Battery Charge Limiters isto control the battery contactors.They also have three auxiliary functions:

- RAT and EMER GEN FAULT control,- Inhibition of APU start sequence,- Static inverter monitoring.




UC64200


BATTERY COMPONENTS - BATTERY CHARGE LIMITERS




UC64200



TMUELBT02 LEVEL 3



UC64200



24-56-00 GALLEY SUPPLY

CONTENTS:Electrical SupplyControlsLoad MonitoringAuto SheddingSelf Examination

TMUELBG02 LEVEL 3



UC64200


GALLEY SUPPLY

ELECTRICAL SUPPLY

The power supply provides the galleys with 115 VoltsAC.There are 50 KVA available for all the galleys. Thispower is divided into two parts: the AFT galley powerwith 30 KVA and the FWD galley power with 20 KVA.

TMUELBG02-T01 LEVEL 3



UC64200


ELECTRICAL SUPPLYTMUELBG02-P01 LEVEL 3



UC64200


GALLEY SUPPLY

CONTROLS

EXT PWR OR APU GEN SUPPLYWith the GALLEY pushbutton in the AUTO position andthe electrical network supplied by either the GroundCart or the APU, all the galleys are supplied.The galleys are cut off by releasing out the GALLEYpushbutton (OFF light on) .




UC64200


CONTROLS - EXTERNAL POWER OR APU GEN SUPPLYTMUELBG02-P02 LEVEL 3



UC64200


GALLEY SUPPLY

CONTROLS

IDG1 AND IDG2 SUPPLYWith the aircraft electrical network supplied by bothIntegrated Drive Generators, the galleys are supplied.In flight, two generators are required to supply thewhole galley network :

- -two IDGs or -IDG1(2) and APU GEN .

NOTE : on ground, with no APU and no external power,two IDGs are also required to supply the whole galleynetwork.




UC64200


CONTROLS - IDG1 AND IDG2 SUPPLYTMUELBG02-P03 LEVEL 3



UC64200


GALLEY SUPPLY

LOAD MONITORING

If the Generator Control Unit detects a generatoroverload, the GALLEY FAULT light comes on. In thiscase the galleys have to be manually cut off.The ECAM system is activated through the EGIUs.




UC64200


LOAD MONITORINGTMUELBG02-P04 LEVEL 3



UC64200


GALLEY SUPPLY

AUTO SHEDDING

APU SUPPLY ON GROUNDOn ground, in case of APU generator overload, the wholegalley network is automatically shed.At the same time, the Galley FAULT light comes on andthe ECAM system is triggered.




UC64200


AUTO SHEDDING - APU SUPPLY ON GROUNDTMUELBG02-P05 LEVEL 3



UC64200


GALLEY SUPPLY

AUTO SHEDDING

ONE GEN SUPPLY IN FLIGHTIn flight, in single generator operationconfiguration, the power fed to the galleys is limitedto 10 KVA : 5 KVA for FWD galleys and 5 KVA for AFTgalleys.The GALLEY SHED indication is displayed on the ELECECAM page.




UC64200


AUTO SHEDDING - ONE GEN SUPPLY IN FLIGHTTMUELBG02-P06 LEVEL 3



UC64200


SELF EXAMINATION

In which of the following configurations is the wholegalley network shed when an overload occurs ?

- A - In flight with two IDG supply.- B - On ground with APU supply only.- C - On ground with EXT PWR only.

What does the GALLEY FAULT light indicate ?- A - The AFT galley has been shed.- B - The galleys have been shed.- C - An overload on any generator (APU or IDG).

TMUELBG02 LEVEL 3



UC64200



24-56-00 GALLEY SUPPLY COMPONENTS

CONTENTS:Galley Supply Contactors

TMUELBH02 LEVEL 3

EFFECTIVITY 24-56-00 Page 1May 31/96


UC64200


GALLEY SUPPLY COMPONENTS

GALLEY SUPPLY CONTACTORS

IDENTIFICATIONFIN: 4MC, 5MC, 6MC, 13MC, 15MC, 17MC

LOCATIONZONE: 220

TMUELBH02-T01 LEVEL 3



UC64200


GALLEY SUPPLY COMPONENTS - GALLEY SUPPLY CONTACTORS

TMUELBH02-P01 LEVEL 3



UC64200



TMUELBH02 LEVEL 3



UC64200



24-67-00 REFUELING ON BATTERY

CONTENTS:GeneralGround Service ConfigurationBattery Only ConfigurationSelf Examination

TMUELCB02 LEVEL 3



UC64200


REFUELING ON BATTERY

GENERAL

The refueling electrical network consists of busbars501PP and 502PP. It is supplied as soon as the refueldoor located on the fuselage below the right wing isopened.Two supplies are then possible:

- 28VDC service bus 601PP (supplied from normalnetwork or via MAINT BUS switch).

- Hot bus 701PP if no other power isavailable.

TMUELCB02-T01 LEVEL 3



UC64200


GENERALTMUELCB02-P01 LEVEL 3



UC64200



GROUND SERVICE CONFIGURATION

NOTE: MAINT BUS switch is set to ON.As soon as refuel door is opened, relay 8PR is energizedby service bus 601PP via relay 5PR.Refueling busbars 501PP and 502PP are then suppliedby service bus 601PP via relay 8PR.NOTE: in normal supply configuration, contactor 3PX

is opened and contactor 8PN is closed.




UC64200


GROUND SERVICE CONFIGURATIONTMUELCB02-P02 LEVEL 3



UC64200



BATTERY ONLY CONFIGURATION

When spring loaded switch 10PR is set to ON and refueldoor open, relay 5PR is energized by HOT BUS 701PP.Relay 8PR is energized, allowing refueling busbars tobe supplied by HOT BUS 701PP.Relay 11PR is energized by 501PP via mode selector 3QUso that relay 5PR remains energized.Time delay closing relay 12PR is energized by 701PP.When it closes after 10mn, refueling power isautomatically cut off even if refuel door is stillopen.




UC64200


BATTERY ONLY CONFIGURATIONTMUELCB02-P03 LEVEL 3



UC64200


SELF EXAMINATION

In which configuration is refueling power supplyautomatically cut off ten minutes after?

A - Refueling busbars supplied by servicebus 601PP.

B - Refueling busbars supplied by hot bus701PP.

C - Both configurations.

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24-22-00 ELECTRICAL GENERATION INTERFACEUNIT (EGIU)

CONTENTS:PresentationIDG1 or IDG2APU GENExternal Power

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ELECTRICAL GENERATION INTERFACE UNIT (EGIU)

PRESENTATION

The function of the Electrical Generation InterfaceUnit is to convert analog and discrete signals fromthe Generator Control Unit and Ground Power ControlUnit into ARINC 429 data.Two identical EGIUs are used.Each one consists of two isolated channels:

- channel 1 is allocated to IDG1 or IDG2.- channel 2 is allocated to APU Generator orExternal Power.

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ELECTRICAL GENERATION INTERFACE UNIT (EGIU) - PRESENTATION

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IDG1 OR IDG2

The information provided to the SDAC is shown on thescreen.The parameters are displayed on the ECAM system.




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ELECTRICAL GENERATION INTERFACE UNIT (EGIU) - IDG1 OR IDG2




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APU GEN





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ELECTRICAL GENERATION INTERFACE UNIT (EGIU) - APU GEN




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EXTERNAL POWER


NOTE: the Flip Flop circuit in the EGIU memorizes thecontrol signal from the EXT PWR pushbutton switch(the pushbutton switch not being mechanicallylatch-in: a first press switches the externalpower "ON", a second press switches it "AVAIL").The Flip Flop circuit allows the latching of theExternal Power Contactor auxiliary relay. Theinformation "External Power ON" is thus providedto the SDACs.




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ELECTRICAL GENERATION INTERFACE UNIT (EGIU) - EXTERNAL POWER




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24-22-00 ECAM ELECTRICAL POWER INTERFACECOMPONENTS

CONTENTS:ELECTRICAL GENERATION INTERFACE UNIT (EGIU)

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ECAM ELECTRICAL POWER INTERFACE COMPONENTS

EGIU


LOCATIONZONE: 121

COMPONENT DESCRIPTIONThe EGIU transmits the main parameters from theGenerators Control Units to the System Data AcquisitionConcentrators via ARINC 429 data links.

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ECAM ELECTRICAL POWER INTERFACE COMPONENTS - EGIU

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24-00-00 AC/DC BUS OFF WARNINGS LOGICS

CONTENTS:AC MainAC ESSDC MainDC ESS

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AC/DC BUS OFF WARNINGS LOGICS

AC MAIN

The ECAM is activated as soon as the correspondingsub-busbar is no longer supplied.

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AC/DC BUS OFF WARNINGS LOGICS - AC MAINTMUELBY01-P01 LEVEL 3



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AC ESS

The ECAM is activated as soon as the correspondingbusbar or sub-busbar is no longer supplied.




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AC/DC BUS OFF WARNINGS LOGICS - AC ESSTMUELBY01-P02 LEVEL 3



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DC MAIN

The ECAM warning is activated as soon as thecorresponding sub-busbar is no longer supplied.




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AC/DC BUS OFF WARNINGS LOGICS - DC MAINTMUELBY01-P03 LEVEL 3



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DC ESS

The ECAM system is activated when:- The sub-busbar is lost.- The DC ESS BUS SHED contactor (8PH) is open.




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AC/DC BUS OFF WARNINGS LOGICS - DC ESSTMUELBY01-P04 LEVEL 3



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24-41-00 AC GENERATION INTERFACES

CONTENTS:GENERATOR CONTROL UNIT/GROUND POWER CONTROL UNITGROUND POWER CONTROL UNIT / CENTRALIZED FAULT DISPLAYSYSTEM

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AC GENERATION INTERFACES

GENERATOR CONTROL UNIT/GROUND POWER CONTROL UNIT

The GPCU is the interface between the GCUs and theCFDIU.The Ground Power Control Unit receives the faultinformation from the Generator Control Units, compilesthem with its own failures and transmits them to theCentralized Fault Display Interface Unit.The GPCU receives hexadecimal coded fault informationthrough RS422 data links and transmits a failure listin clear language.

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AC GENERATION INTERFACES - GCU/GPCU

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AC GENERATION INTERFACES

GROUND POWER CONTROL UNIT/CENTRALIZED FAULT DISPLAYSYSTEM

The Ground Power Control Unit transmits the faultmessage in clear english language to the CentralizedFault Display Interface Unit by an ARINC 429 outputsbus.The maintenance test can be performed only on groundwith engines shut down. It is initiated either:

- automatically at each GPCU power-up- or manually from the MCDU

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AC GENERATION INTERFACES - GPCU/CFDS

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24-00-00 CFDS SPECIFIC PAGE PRESENTATION

CONTENTS:Transformer Rectifier Unit(TR)TR Effective ResetTR Impossible Reset

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CFDS SPECIFIC PAGE PRESENTATION

TRANSFORMER RECTIFIER UNIT (TR)

TR1, TR2 and TR3 have the same function.Thus, only TR1 is shown on the MCDU.The Transformer Rectifier protection modulede-energizes the DC bus control contactor in case ofno current flow (1A/TD=500ms) or overheat detection(171°c).When the fault disappears, the TR remains deactivated:a RESET action is necessary to reactivate the TR.2 cases are possible:

- RESET effective,- RESET impossible.

TR EFFECTIVE RESET

If the fault detected by the TR1 protection module hasdisappeared, the TR1 reset is effective, the TR1protection module energizes TR1 control contactor.

TR IMPOSSIBLE RESET

If the fault detected by the TR1 protection module isstill active, TR1 RESET is impossible, the TR1 controlcontactor stays de-energized (a trouble shootingprocedure is necessary).

Note: If the CFDS is not available, the TR protectionmodule can be reset from the pushbutton locatedin the avionics bay.

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CFDS SPECIFIC PAGE PRESENTATIONTMUELSP02-P01 LEVEL 3



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THIS PAGE INTENTIONALLY BLANK

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24 Electrical Power

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