Chapter_24.pdf

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CHAPTER 24 - ELECTRICAL POWER TABLE OF CONTENTS REFERENCE CHAPTER 24 24-00-00 24-00-00 PB 001 24-00-00-11200-C 24-00-00-11200-H 24-00-00-13600-A 24-00-00-13700-A 24-00-00-13700-D 24-00-00-13800-B 24-00-00-15500-B 24-00-00-18300-B 24-00-00 PB 501 24-00-00-710-003-A 24-00-00 PB 601

ELECTRICAL POWER - GENERAL ELECTRICAL POWER - GENERAL - DESCRIPTION AND OPERATION Electrical Power - General Schematic Electrical Power - General Schematic Electrical Power - Component Location Control and Indicating - Component Location Control and Indicating - Component Location AC Generation and Distribution - Schematic DC Generation and Distribution - Schematic Lower ECAM Display Unit - ELEC Page ELECTRICAL POWER - GENERAL - ADJUSTMENT/TEST Integrity Test of the Electrical Power ELECTRICAL POWER - GENERAL - INSPECTION/CHECK

24-00-00-200-003-A

General - Inspection/Check of the Electrical Circuits and Equipment

24-00-00-200-004-A

Opening and Closing of all Circuit Breakers with Electrical Circuits DeEnergized

24-20-00 24-20-00 PB 001 24-20-00-12400-B 24-20-00-12500-A 24-20-00-13000-A 24-20-00 PB 401 24-20-00-040-001-A 24-20-00-991-00200-A 24-20-00-991-00300-A 24-20-00-991-00400-A 24-20-00-040-002-A 24-20-00-991-00100-A 24-20-00-991-00100-C 24-20-00-440-002-A 24-21-00 24-21-00 PB 001 CONF 13 24-21-00-12300-A 24-21-00-12400-A 24-21-00-12500-A

AES

SUBJECT

AC GENERATION AC GENERATION - DESCRIPTION AND OPERATION Main Components - Component Location Main Components - Component Location Spare Fuse - Component Location AC GENERATION - DEACTIVATION/REACTIVATION Check of the AC Main Generation Maintenance Condition Oil Consumption of the APU GTCP 36-300 Oil Consumption of the APU APS 3200 Oil Consumption of the APU 131-9(A) RAT Extension Control - Check of the RAT Manual Extension RAT Control RAT control Reactivation of the RAT Extension Control INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) DESCRIPTION AND OPERATION IDG Attachment to the Gearbox IDG Location in Nacelle IDG - Interface Accessories

T.O.C.

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-21-00-12600-A 24-21-00-12800-A 24-21-00-19900-A 24-21-00-21400-A 24-21-00-21600-A 24-21-00-24600-A 24-21-00-24700-A 24-21-00-24800-A 24-21-00-24900-A 24-21-00-25000-A 24-21-00 PB 201 CONF 13 24-21-00-600-040-A

SUBJECT ELEC Control Panel - Location Fuel-Cooled IDG Oil Cooler and Cables - Location IDG - Speed Regulation Loop IDG Oil System - Schematic IDG - Internal Schematic IDG System - Generator Drive Control and Indicating IDG 1 Oil Low Pressure - Upper and Lower ECAM Display Units IDG 1 Oil Overheat Advisory - Upper and Lower ECAM Display Units IDG 1 Oil Overheat - Upper and Lower ECAM Display Units IDG 1 Disconnect - Lower ECAM Display Unit INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) MAINTENANCE PRACTICES Preservation/Storage/Return to Service of the IDG

24-21-00 PB 301 CONF 13

INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) - SERVICING

24-21-00-612-044-A 24-21-00-991-90000-A 24-21-00-612-044-A-01

Servicing of the IDG after Oil Chemical Contamination Servicing of IDG after Oil Chemical Contamination Servicing of the IDG after Oil Chemical Contamination and Extension of the Oil-Filter Differential-Pressure Indicator (DPI)

24-21-00-991-90900-A 24-21-00-920-041-A

Drain IDG Oil System, Discard Filter Element(s) and Replenish

24-21-00-991-91000-B 24-21-00-612-047-A 24-21-00-991-91100-A

IDG Oil Filter IDG Oil-Type Change Oil Type Change - IDG

24-21-00 PB 501 CONF 13

INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) ADJUSTMENT/TEST

24-21-00-710-042-A

Operational Test of the IDG Disconnect and Reconnect (Reset) Function Engine Static

24-21-00-730-041-A

System Test of the IDG Frequency (P/N 766219)

24-21-00-991-92100-A 24-21-00-720-042-A 24-21-00 PB 601 CONF 13 24-21-00-210-045-A 24-21-00-210-048-A 24-21-00-210-048-A-01 24-21-00-991-20000-B 24-21-15 24-21-15 PB 401 CONF 13 24-21-15-000-010-A 24-21-15-991-15000-A

AES

Servicing of the IDG after Oil Contamination and with the DPI Out

Governor Adjustment Screw - IDG Operational Test of the IDG Disconnect and Reconnect (Reset) Function Engine in Operation INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) INSPECTION/CHECK Inspection of the Filter Element(s) Visual Inspection of the IDG for Oil Leaks and Check of the Electrical Circuits Visual Inspection of the IDG for Oil Leakage Engine Static and Check of the Electrical Circuits Connection of the Test Tool on the IDG THERMOCOUPLE - IDG OIL TEMPERATURE THERMOCOUPLE - IDG OIL TEMPERATURE REMOVAL/INSTALLATION Removal of the IDG Oil Temperature Thermocouple IDG Oil Temperature thermocouple

T.O.C.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-21-15-400-010-A 24-21-41 24-21-41 PB 401 CONF 13 24-21-41-000-010-A

SUBJECT Installation of the IDG Oil Temperature Thermocouple ADAPTER - QUICK ATTACH/DETACH, IDG COUPLING - QAD, IDG - REMOVAL/INSTALLATION Removal of the Quick Attach/Detach (QAD) Adapter of the IDG

24-21-41-991-15000-A

Quick Attach/Detach (QAD) Adapter (Coupling)

24-21-41-991-15200-A

Removal of the QAD Adapter (Coupling)

24-21-41-400-010-A 24-21-41 PB 601 CONF 13 24-21-41-200-010-A 24-21-41-991-15100-A 24-21-42 24-21-42 PB 401 CONF 13 24-21-42-000-010-B 24-21-42-991-15000-A 24-21-42-991-15300-A 24-21-42-991-15100-A 24-21-42-991-15200-B 24-21-42-400-010-B 24-21-42 PB 701 CONF 13

Installation of the Quick Attach/Detach (QAD) Adapter of the IDG COUPLING - QAD, IDG - INSPECTION/CHECK Torque Check of the Quick Attach-Detach (QAD) Adapter Tension-Bolt IDG QAD Coupling COOLER - FUEL COOLED IDG OIL IDG OIL COOLER - FUEL COOLED - REMOVAL/INSTALLATION Removal of the Fuel-Cooled IDG Oil-Cooler Fuel-Cooled IDG Oil-Cooler Fuel-Cooled IDG Oil-Cooler Fuel-Cooled IDG Oil-Cooler Fuel-Cooled IDG Oil-Cooler Installation of the Fuel-Cooled IDG Oil-Cooler IDG OIL COOLER - FUEL COOLED - CLEANING/PAINTING

24-21-42-100-040-A 24-21-43 24-21-43 PB 401 CONF 13

Cleaning of the Fuel Cooled IDG Oil Cooler IDG - CABLES IDG - CABLES - REMOVAL/INSTALLATION

24-21-43-000-010-A 24-21-43-991-15000-A 24-21-43-400-010-A 24-21-49 24-21-49 PB 401 CONF 13

Removal of the IDG Cables IDG Cables Installation of the IDG Cables TUBING - IDG COOLER OIL TUBING - IDG COOLER OIL - REMOVAL/INSTALLATION

24-21-49-000-041-A 24-21-49-991-90100-A 24-21-49-400-041-A 24-21-49 PB 601 CONF 13 24-21-49-200-010-A 24-21-49-991-15000-A 24-21-51 24-21-51 PB 401 CONF 13 24-21-51-000-010-A

AES

Removal of the Tubings - IDG Cooling Oil Tubings - IDG Cooling Oil Installation of the Tubing - IDG Cooler Oil TUBING - IDG COOLER OIL - INSPECTION/CHECK General Check of the IDG Oil Cooling Tubes IDG Oil-Cooling Tubes GENERATOR - INTEGRATED DRIVE (IDG) GENERATOR - INTEGRATED DRIVE (IDG) REMOVAL/INSTALLATION Removal of the Integrated Drive Generator -IDG 1(2)

24-21-51-991-15200-A

Integrated Drive Generator (IDG)

24-21-51-991-15100-A

Integrated Drive Generator (IDG)

24-21-51-991-15000-A

Integrated Drive Generator (IDG)

24-21-51-400-010-A

Installation of the Integrated Drive Generator -IDG 1(2)

24-21-51-000-011-A

Removal of the IDG Oil Filter(s)

T.O.C.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-21-51-991-15400-B 24-21-51-400-011-A 24-21-51 PB 601 CONF 13

SUBJECT IDG Oil Filter Installation of the IDG Oil Filter(s) GENERATOR - INTEGRATED DRIVE (IDG) - INSPECTION/CHECK

24-21-51-200-010-A

Check of the Oil Level and Filter Differential Pressure Indicator (DPI)

24-21-51-200-011-A

Check IDG Oil Filter Differential Pressure Indicator (DPI)

24-21-51-991-15300-A

Differential Pressure Indicator (DPI) of the Oil Filter

24-22-00 24-22-00 PB 001 24-22-00-12400-A 24-22-00-12400-B 24-22-00-12500-B 24-22-00-13700-C

AC MAIN GENERATION AC MAIN GENERATION - DESCRIPTION AND OPERATION AC Main Generation - Component Location AC Main Generation - Component Location AC Main Generation - Component Location AC Main Generation (Normal Configuration) - General Schematic

24-22-00-13700-H

AC Main Generation (Normal Configuration) - General Schematic

24-22-00-15500-A 24-22-00-15700-B 24-22-00-15800-A 24-22-00-16000-A 24-22-00-17900-A 24-22-00-19500-E

Zone of Protection Electrical Generation Interface Unit - Schematic Diagram Flip-Flop Circuit - Block Diagram SDAC Communication - Block Diagram Current Transformers - Block Diagram AC Main Generation Channel 1 - Schematic Diagram

24-22-00-19600-B

GLC/BTC Logic - Schematic Diagram

24-22-00-19700-A 24-22-00-19900-A 24-22-00-20000-A 24-22-00-20100-A

GLC-1 Supply - Schematic Diagram GEN 1 FAULT - Upper and Lower ECAM Display Unit GEN 1 OFF - Upper and Lower ECAM Display Unit GEN 2 OFF _ Upper and Lower ECAM Display Unit

24-22-00-20500-A 24-22-00-20800-C 24-22-00-21000-A 24-22-00-21100-A 24-22-00-21500-B

BTC-1 Supply - Schematic Diagram BTC-2 Supply - Schematic Diagram AC BUS 1 Fault - Upper and Lower ECAM Display Unit AC BUS 2 Fault - Upper and Lower ECAM Display Unit Smoke Detection - Upper and Lower ECAM Display Unit

24-22-00 PB 501 24-22-00-710-001-A 24-22-00-710-002-A 24-22-17 24-22-17 PB 401

Operational Test of the Generator Line Contactor (GLC-1) Opening in the Smoke Procedure Operational Test of the Transfer Inhibition CURRENT TRANSFORMER - AC CURRENT TRANSFORMER - AC - REMOVAL/INSTALLATION

24-22-17-000-001-A 24-22-17-991-00300-A

Removal of the AC Current Transformers AC Current Transformer (42XU3, 42XU4)

24-22-17-991-00400-A

AC Current Transformer (42XU1, 42XU2)

24-22-17-991-00300-B

AC Current Transformer (42XU3, 42XU4)

24-22-17-991-00400-B

AC Current Transformer (42XU1, 42XU2)

24-22-17-400-001-A

AES

AC MAIN GENERATION - ADJUSTMENT/TEST

Installation of the AC Current Transformers

T.O.C.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-22-17-000-002-A 24-22-17-991-00200-A

SUBJECT Removal of the AC Current Transformers AC Current Transformer (41XU1, 41XU2)

24-22-17-400-002-A 24-22-17-000-003-A 24-22-17-991-00500-B

Installation of the AC Current Transformers Removal of the AC Current Transformers AC Current Transformer (51XU1, 51XU2)

24-22-17-400-003-A 24-22-18 24-22-18 PB 401 24-22-18-000-001-A 24-22-18-991-00100-A 24-22-18-400-001-A 24-22-33 24-22-33 PB 401 24-22-33-000-001-A 24-22-33-991-00100-A 24-22-33-400-002-A 24-22-34 24-22-34 PB 401 24-22-34-000-001-A 24-22-34-991-00100-A 24-22-34-400-001-A 24-22-51 24-22-51 PB 401 24-22-51-000-001-A 24-22-51-991-00100-A 24-22-51-991-00100-B 24-22-51-400-001-A 24-22-51 PB 601 24-22-51-200-001-A 24-22-55 24-22-55 PB 401 24-22-55-000-001-A 24-22-55-991-00100-A 24-22-55-991-00100-B 24-22-55-400-002-A

Installation of the AC Current Transformers SENSOR - TDC AC SENSOR - TDC AC - REMOVAL/INSTALLATION Removal of the TDC AC Sensor 1(2) Time Delay Closing (TDC) AC Sensor Installation of the TDC AC Sensor 1(2) ELECTRICAL GENERATION INTERFACE UNIT (EGIU) ELECTRICAL GENERATION INTERFACE UNIT (EGIU) REMOVAL/INSTALLATION Removal of the EGIU-1(2) Electrical Generation Interface Unit 1(2) Installation of the EGIU-1(2) CONTROL UNIT - GENERATOR (GCU) CONTROL UNIT - GENERATOR (GCU) - REMOVAL/INSTALLATION Removal of the GCU-1(2) Generator Control Unit 1(2) GCU-1(2) Installation of the GCU-1(2) MODULE - LIGHTNING PROTECTION MODULE - LIGHTNING PROTECTION - REMOVAL/INSTALLATION Removal of the Lightning Protection Modules Lightning Protection Module Lightning Protection Module Installation of the Lightning Protection Modules MODULE - LIGHTNING PROTECTION - INSPECTION/CHECK Check of the Lightning Protection Modules CONTACTOR CONTACTOR - REMOVAL/INSTALLATION Removal of the Contactors Contactors Contactors Installation of the Contactors

24-23-00 24-23-00 PB 001 24-23-00-12300-A

AC AUXILIARY GENERATION AC AUXILIARY GENERATION - DESCRIPTION AND OPERATION AC Auxiliary Generation (APU Generator GCU) Component Location

24-23-00-12300-B

AC Auxiliary Generation (APU Generator GCU) Component Location

24-23-00-12400-A

AC Auxiliary Generation (APU Generator GCU) Component Location

AES

T.O.C.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-23-00-13800-C 24-23-00-13800-G 24-23-00-16800-A 24-23-00-18300-E 24-23-00-18500-A 24-23-00-18700-A 24-23-00 PB 401

SUBJECT APU Generator Configuration - Block Diagram APU Generator Configuration - Block Diagram Current Transformers - Block Diagram Auxiliary Generation Operation - Schematic Diagram GLC - APU Supply - Schematic Diagram APU GEN FAULT - Upper and Lower ECAM Display Unit AC AUXILIARY GENERATION - DEACTIVATION/REACTIVATION

24-23-00-040-001-A 24-23-00-991-00100-A 24-23-00-440-001-A 24-23-00-040-002-A 24-23-00-991-00200-A 24-23-00-440-002-A 24-23-17 24-23-17 PB 401

Deactivation of the APU Generator by Installation of the Substitution Kit Components for Flight without an APU Generator Installed Reactivation of the APU Generator after Removal of the Substitution Kit Deactivation of the APU Generator by Removal of the Quill Shaft APU Generator without Quill Shaft Reactivation of the APU Generator after Quill Shaft Removal CURRENT TRANSFORMER - AC CURRENT TRANSFORMER - AC - REMOVAL/INSTALLATION

24-23-17-000-001-A 24-23-17-991-00300-A 24-23-17-991-00400-A 24-23-17-991-00400-B 24-23-17-400-001-A 24-23-34

Removal of the AC Current Transformer AC Current Transformer - Block Diagram AC Current Transformer AC Current Transformer Installation of the AC Current Transformer CONTROL UNIT - GENERATOR (GCU)

24-23-34 PB 401 24-23-34-000-001-A 24-23-34-991-00100-A

CONTROL UNIT - GENERATOR (GCU) - REMOVAL/INSTALLATION Removal of the GCU-APU APU Generator Control Unit (GCU)

24-23-34-400-001-A 24-23-51 24-23-51 PB 401

Installation of the GCU-APU GENERATOR - APU GENERATOR - APU - REMOVAL/INSTALLATION

24-23-51-000-001-A 24-23-51-991-00100-B 24-23-51-991-00300-B 24-23-51-000-001-A-01 24-23-51-991-00500-B 24-23-51-991-00600-B 24-23-51-400-001-A 24-23-51-400-001-A-01 24-23-55 24-23-55 PB 401

Removal of the APU Generator APU Generator 8XS APU Generator Safety Cable Removal of the APU Generator with the Minilift Hoist APU Generator 8XS APU Generator Hoist Installation of the APU Generator Installation of the APU Generator with the Minilift Hoist CONTACTOR CONTACTOR - REMOVAL/INSTALLATION

24-23-55-000-001-A 24-23-55-991-00100-A 24-23-55-991-00100-B 24-23-55-400-001-A 24-24-00 24-24-00 PB 001

AES

Removal of the APU GLC Contactor Contactor Installation of the APU GLC AC EMERGENCY GENERATION AC EMERGENCY GENERATION - DESCRIPTION AND OPERATION

T.O.C.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-24-00-12300-B 24-24-00-12400-A 24-24-00-12500-A 24-24-00-13900-C 24-24-00-13900-D 24-24-00-17000-D 24-24-00-17100-C

SUBJECT AC Emergency Generation - Component Location AC Emergency Generation - Component Location AC Emergency Generation - Component Location Electrical Emergency Generating System - Schematic Electrical Emergency Generating System - Schematic Electrical Emergency Switching - Schematic EMER & AC ESS BUS Contactors Control - Logic Diagram

24-24-00-17200-D

RAT Extension Logic & CSM/G Control Logic - Schematic

24-24-00-17200-E

RAT Extension Logic and CSM/G Control Logic - Schematic

24-24-00-17400-F 24-24-00-17400-G 24-24-00-17600-B 24-24-00-18000-B

24-24-00-18300-A

Electrical Emergency Generation System - Control System Electrical Emergency Generation System - Control System Test Procedure for GCU EMER by MCDU Electrical Emergency Configuration - Upper and Lower ECAM Display Unit Electrical Emergency Configuration - Upper and Lower ECAM Display Unit ELectrical Emergency Configuration During RAT Deployment and in Landing Gear Extented Configuration ESS BUSES ON BAT - Upper and Lower ECAM Display Unit

24-24-00-18500-B

Electrical Emergency Configuration with CSM/G Running

24-24-00-18700-B 24-24-00-18800-A 24-24-00-18800-B 24-24-00-18900-A 24-24-00-18900-B 24-24-00-19000-A 24-24-00-19000-B 24-24-00-19100-A 24-24-00-19100-B 24-24-00-19200-A 24-24-00-19200-B 24-24-00-19300-C 24-24-00-19300-D 24-24-00-19700-B 24-24-00-19800-B

Electrical Emergency Configuration on the Ground with speed < 50kts Available Functions in Emergency Configuration Available Functions in Emergency Configuration Available Functions in Emergency Configuration Available Functions in Emergency Configuration Available Functions in Emergency Configuration Available Functions in Emergency Configuration Available Functions in Emergency Configuration Available Functions in Emergency Configuration Available Functions in Emergency Configuration Available Functions IN Emergency Configuration Available Functions in Emergency Configuration Available Functions in Emergency Configuration Smoke Detection - Upper and Lower ECAM Display Unit Electrical Smoke Configuration

24-24-00-18000-C 24-24-00-18200-B

24-24-00 PB 501 24-24-00-710-001-A

Operational Test of the Emergency Generation System

24-24-00-710-002-A

Operational Test of the Emergency Generator Control Unit (GCU) from Centralized Fault Display System (CFDS)

24-24-34 24-24-34 PB 401 24-24-34-000-001-A

AES

AC EMERGENCY GENERATION - ADJUSTMENT/TEST

CONTROL UNIT - CSM/G CONTROL UNIT - CSM/G - REMOVAL/INSTALLATION Removal of the CSM/G Control Unit

T.O.C.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-24-34-991-00100-A 24-24-34-400-001-A 24-24-51 24-24-51 PB 401 24-24-51-000-001-A 24-24-51-991-00100-A 24-24-51-400-001-A 24-24-55 24-24-55 PB 401

Installation of the CSM/G Control Unit GENERATOR - CONSTANT SPEED MOTOR (CSM/G) GENERATOR - CONSTANT SPEED MOTOR (CSM/G) REMOVAL/INSTALLATION Removal of the Constant Speed Motor/Generator (CSM/G) Constant Speed Motor/Generator - CSM/G 8XE. Installation of the Constant Speed Motor/Generator (CSM/G) CONTACTOR CONTACTOR - REMOVAL/INSTALLATION

24-24-55-000-001-A

Removal of the Emergency Generator Line Contactor (EMER GLC)

24-24-55-991-00100-A 24-24-55-400-001-A

Contactor Installation of the Emergency Generator Line Contactor (EMER GLC)

24-24-55-000-002-A 24-24-55-991-00300-A 24-24-55-400-002-A

Removal of the AC ESS BUS Contactor Contactor Installation of the AC ESS BUS Contactor

24-25-00 24-25-00 PB 001 24-25-00-12400-A 24-25-00-12500-A 24-25-00-13800-C 24-25-00-13800-F 24-25-00 PB 501 24-25-00-710-001-A 24-25-55 24-25-55 PB 401 24-25-55-000-001-A 24-25-55-991-00100-A 24-25-55-400-001-A 24-26-00 24-26-00 PB 001 24-26-00-12500-A 24-26-00-12500-B 24-26-00-13800-E 24-26-00-13800-N 24-26-00-15600-A 24-26-00 PB 501 24-26-00-710-001-A

AES

SUBJECT CSM/G Control Unit

AC ESSENTIAL GENERATION SWITCHING AC ESSENTIAL GENERATION SWITCHING - DESCRIPTION AND OPERATION AC Essential Generation Switching - Component Location AC Essential Generation Switching - Component Location Loss of AC Normal BUS 1XP - Block Diagram Control and Indicating Circuits Loss of AC Normal BUS 1XP - Block Diagram Control and Indicating Circuits AC ESSENTIAL GENERATION SWITCHING - ADJUSTMENT/TEST Operational Test of the AC Essential-Generation Switching CONTACTOR CONTACTOR - REMOVAL/INSTALLATION Removal of the AC Essential Bus Switching Contactor Contactor Installation of the AC Essential Bus Switching Contactor GALLEY SUPPLY CONTROL GALLEY SUPPLY CONTROL - DESCRIPTION AND OPERATION Galley Supply Control - Component Location Galley Supply Control - Component Location Galley Supply Control - Block Diagram Galley Supply Control - Block Diagram Overload - Upper and Lower ECAM Display Unit GALLEY SUPPLY CONTROL - ADJUSTMENT/TEST Operational Test of the Manual and Automatic Shedding of the Galleys

T.O.C.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-26-00-710-002-A 24-27-00 24-27-00 PB 001 24-27-00-12300-A 24-27-00 PB 501 24-27-00-710-001-A 24-27-00-710-002-A 24-28-00 24-28-00 PB 001 24-28-00-12300-B 24-28-00-12400-A 24-28-00-14900-A 24-28-00 PB 501 24-28-00-710-001-A

SUBJECT Operational Test of the Manual and Automatic Galley and Bus Shedding AC GENERATION MONITORING AND INDICATING AC GENERATION MONITORING AND INDICATING - DESCRIPTION AND OPERATION AC Generation Monitoring and Indicating - ECAM AC GENERATION MONITORING AND INDICATING ADJUSTMENT/TEST Operational Test of the GEN FAULT Warning Operational Test of the Automatic Galley Shedding STATIC INVERTER STATIC INVERTER - DESCRIPTION AND OPERATION Contactor and Fuse - Component Location Static Inverter - Component Location Static Inverter - Schematic Diagram STATIC INVERTER - ADJUSTMENT/TEST

24-28-51 24-28-51 PB 401

Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the External Power Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the APU STATIC INVERTER STATIC INVERTER - REMOVAL/INSTALLATION

24-28-51-000-001-A 24-28-51-991-00100-A 24-28-51-400-001-A 24-28-55 24-28-55 PB 401

Removal of the Static Inverter Static Inverter Installation of the Static Inverter CONTACTOR CONTACTOR - REMOVAL/INSTALLATION

24-28-00-710-001-A-01

24-28-55-000-001-A 24-28-55-991-00100-B 24-28-55-400-001-A 24-30-00 24-30-00 PB 001 24-30-00-11200-B 24-30-00-11200-C 24-30-00-11900-B 24-30-00-12300-B 24-30-00-13800-B 24-30-00-14400-A 24-30-00-15600-A 24-30-00 PB 401 24-30-00-040-001-A

AES

Removal of the Static Inverter Contactor Static Inverter Contactor Installation of the Static Inverter Contactor DC GENERATION DC GENERATION - DESCRIPTION AND OPERATION DC Generation and Distribution - General DC Generation and Distribution - General Loss of Transformer Rectifier 1 - Block Diagram Loss of Transformer Rectifier 2 - Block Diagram DC Generation - Component Location Spare Fuses - Component Location CFDS Architecture (Liaison with TR’s and BCL’s) DC GENERATION - DEACTIVATION/REACTIVATION Perform a Charging Cycle on the Battery Associated With the Operative Battery Charge Limiter (BCL)

T.O.C.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-30-00-440-001-A 24-30-00-040-002-A 24-30-00-440-002-A 24-30-00 PB 501 24-30-00-710-001-A

24-32-00 24-32-00 PB 001 24-32-00-12400-A

SUBJECT Reactivation of the Battery Charge Limiter 1(2) Deactivation of the Transformer Rectifier TR2 Reactivation of the Transformer Rectifier TR2 DC GENERATION - ADJUSTMENT/TEST Operational Test of the Emergency Generation System with One Normal Transformer Rectifier (TR) Failed DC MAIN GENERATION DC MAIN GENERATION - DESCRIPTION AND OPERATION DC Main Generation (TR) - Component Location

24-32-00-12400-B

DC Main Generation (TR) - Component Location

24-32-00-13800-B

Transformer Rectifier 1 (TR1) - Component Description

24-32-00-13900-A

Transformer Rectifier 2 (TR2) - Component Description

24-32-00-14000-A

Transformer Rectifier Contactor Control - Simplified Logic

24-32-00-16800-A

TR1 Fault (Class 1 - Level 1) - ECAM

24-32-00-16900-A 24-32-00-17000-B 24-32-00 PB 501

Normal Operation - Lower ECAM Display unit TR Reset Procedure DC MAIN GENERATION - ADJUSTMENT/TEST

24-32-00-710-001-A 24-32-51 24-32-51 PB 401

Operational Test of the DC Generation Switching TRANSFORMER RECTIFIER TRANSFORMER RECTIFIER - REMOVAL/INSTALLATION

24-32-51-000-001-A 24-32-51-991-00100-A 24-32-51-400-001-A 24-32-55 24-32-55 PB 401

Removal of the Transformer Rectifier Transformer Rectifier Installation of the Transformer Rectifier CONTACTOR CONTACTOR - REMOVAL/INSTALLATION

24-32-55-000-001-A 24-32-55-991-00100-A 24-32-55-991-00100-B 24-32-55-991-00200-A 24-32-55-991-00300-A 24-32-55-991-00200-B 24-32-55-991-00300-B 24-32-55-400-001-A

24-34-00 24-34-00 PB 001 24-34-00-12400-B 24-34-00-14300-B 24-34-00 PB 501 24-34-00-710-001-A

AES

Removal of the TR 1 and TR 2 Contactors and the TR 2/AC Service Bus Normal Supply Contactor Transformer Rectifier Contactors - Location Transformer Rectifier Contactors - Location TR 2/AC Service Bus Normal Supply Contactor TR 1 and TR 2 Contactors TR 2/AC Service Bus Normal Supply Contactor TR 1 and TR 2 Contactors Installation of the TR 1 and TR 2 Contactors and the TR 2/AC Service Bus Normal Supply Contactor DC EMERGENCY GENERATION DC EMERGENCY GENERATION - DESCRIPTION AND OPERATION DC Emergency Generation - Component Location Essential TR Contactor-Control - Simplified Logic DC EMERGENCY GENERATION - ADJUSTMENT/TEST Operational Test of the DC EMER CONFIG Caution

T.O.C.

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-34-51 24-34-51 PB 401

SUBJECT TRANSFORMER RECTIFIER TRANSFORMER RECTIFIER - REMOVAL/INSTALLATION

24-34-51-000-001-A 24-34-51-991-00200-A 24-34-51-400-001-A 24-34-55 24-34-55 PB 401

Removal of the Essential Transformer Rectifier Essential Transformer Rectifier Installation of the Essential Transformer Rectifier CONTACTOR CONTACTOR - REMOVAL/INSTALLATION

24-34-55-000-001-A 24-34-55-991-00100-B 24-34-55-400-001-A 24-35-00 24-35-00 PB 001 24-35-00-12500-C 24-35-00-12500-D 24-35-00-14200-B 24-35-00-14300-B 24-35-55 24-35-55 PB 401 24-35-55-000-001-A 24-35-55-991-00500-A 24-35-55-991-00500-B 24-35-55-400-001-A 24-35-55-000-002-A 24-35-55-991-00600-A 24-35-55-400-002-A 24-37-00 24-37-00 PB 001 24-37-00-12400-A 24-37-21 24-37-21 PB 401 24-37-21-000-001-A 24-37-21-991-00100-A 24-37-21-400-001-A 24-38-00 24-38-00 PB 001 24-38-00-12600-B 24-38-00-12700-B 24-38-00-12800-A

AES

Removal of the Essential TR Contactor Essential TR Contactor Installation of the Essential TR Contactor DC ESSENTIAL & NORMAL GENERATION SWITCHING DC ESSENTIAL & NORMAL GENERATION SWITCHING DESCRIPTION AND OPERATION DC Essential & Normal Generation Switching - Component Location DC Essential & Normal Generation Switching - Component Location DC NORM BUS SWITCHING Contactor Control - Simplified Logic DC ESS BUS SPLY Contactor Control - Simplified Logic CONTACTOR CONTACTOR - REMOVAL/INSTALLATION Removal of the Contactor Contactors Contactors Installation of the Contactor Removal of the Contactor Contactor Installation of the Contactor DC GENERATION MONITORING AND INDICATING DC GENERATION MONITORING AND INDICATING - DESCRIPTION AND OPERATION DC Generation Monitoring and Indicating - Component Location VOLTMETER VOLTMETER - REMOVAL/INSTALLATION Removal of the Voltmeters Voltmeters of Batteries Installation of the Voltmeters DC GENERATION - BATTERIES DC GENERATION - BATTERIES - DESCRIPTION AND OPERATION DC Generation - Batteries - Component Location DC Generation - Batteries - Component Location DC Generation - Battery Shunt - Component Location

T.O.C.

Page 11 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-38-00-16300-C 24-38-00-16300-D 24-38-00-20100-A 24-38-00-20200-A 24-38-00-20400-B 24-38-00 PB 501

SUBJECT Battery Charge Limiter (BCL1) - Schematic Simplified Cockpit Compartment Controls and Indicating Battery Charge Limiter (BCL1) - Shematic Simplified Cockpit Compartment Controls and Indicating BAT 1 FAULT - Lower and Upper ECAM Display Unit BAT 2 FAULT - Lower and Upper ECAM Display Unit Maintenance Test Procedure for BCL DC GENERATION - BATTERIES - ADJUSTMENT/TEST

24-38-00-710-001-A

Operational Test of the Battery Charge Limiter (BCL), (with the CFDS)

24-38-00-710-001-A-01

Operational Test of the Battery Charge Limiter (BCL), (without the CFDS)

24-38-00 PB 601 24-38-00-210-001-A 24-38-34 24-38-34 PB 401 24-38-34-000-001-A 24-38-34-991-00100-A 24-38-34-400-001-A 24-38-51 24-38-51 PB 401 24-38-51-000-001-A 24-38-51-991-00100-A 24-38-51-991-00100-B 24-38-51-400-001-A 24-38-51 PB 601 24-38-51-280-001-A 24-38-54 24-38-54 PB 401 24-38-54-000-001-A 24-38-54-991-00100-A 24-38-54-400-001-A 24-38-55 24-38-55 PB 401 24-38-55-000-001-A 24-38-55-991-00100-B 24-38-55-400-001-A

DC GENERATION - BATTERIES - INSPECTION/CHECK Visual Inspection of the Batteries CHARGE LIMITER - BATTERY (BCL) CHARGE LIMITER - BATTERY (BCL) - REMOVAL/INSTALLATION Removal of the Battery Charge Limiter (BCL) Battery Charge Limiter Installation of the Battery Charge Limiter (BCL) BATTERY BATTERY - REMOVAL/INSTALLATION Removal of the Batteries Batteries Batteries Installation of the Batteries BATTERY - INSPECTION/CHECK Removal of the Batteries 1 and 2 for Restoration SHUNT - BATTERY SHUNT - BATTERY - REMOVAL/INSTALLATION Removal of the Battery Shunt Battery Shunt (3PB1, 3PB2) Installation of the Battery Shunt CONTACTOR CONTACTOR - REMOVAL/INSTALLATION Removal of the Battery Line Contactor Contactors Installation of the Battery Line Contactor

24-40-00 24-40-00 PB 001 24-40-00-12300-A

EXTERNAL POWER EXTERNAL POWER - DESCRIPTION AND OPERATION Main Components - Component Location

24-41-00 24-41-00 PB 001

AC EXTERNAL POWER CONTROL AC EXTERNAL POWER CONTROL - DESCRIPTION AND OPERATION

AES

T.O.C.

Page 12 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-41-00-12300-A

SUBJECT AC External Power Control (GPCU) - Component Location

24-41-00-12300-B

AC External Power Control (GPCU) - Component Location

24-41-00-12400-A

AC External Power Control (GPCU) - Component Location

24-41-00-14300-C 24-41-00-14300-G

External Power Configuration - Block Diagram External Power Configuration - Block Diagram

24-41-00-14400-B

Ground Power Control Unit (GPCU) - Schematic Diagram

24-41-00-17800-A

External Power Contactor (EPC) Supply - Schematic Diagram

24-41-00-18600-A 24-41-00-19200-B 24-41-00 PB 201 24-41-00-861-002-A 24-41-00-991-00100-A 24-41-00-861-002-A-01

Communication - Block Diagram Reading of Class 3 Faults on MCDU AC EXTERNAL POWER CONTROL - MAINTENANCE PRACTICES Energize the Aircraft Electrical Circuits from the External Power External Power Receptacle - Location Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-01 24-41-00-862-002-A-02 24-41-00 PB 401 24-41-00-040-001-A 24-41-00-991-00200-A 24-41-00 PB 501 24-41-00-740-004-A 24-41-34 24-41-34 PB 401 24-41-34-000-001-A 24-41-34-991-00100-A 24-41-34-400-001-A

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) AC EXTERNAL POWER CONTROL - DEACTIVATION/REACTIVATION Visual Inspection of the External Power Receptacle External Power Receptacle AC EXTERNAL POWER CONTROL - ADJUSTMENT/TEST Operational Check of the GPCU via the CFDS CONTROL UNIT - GROUND POWER (GPCU OR GAPCU) CONTROL UNIT - GROUND POWER (GPCU OR GAPCU) REMOVAL/INSTALLATION Removal of the Ground Power Control Unit (GPCU) Ground Power Control Unit (GPCU) Installation of the Ground Power Control Unit (GPCU)

24-41-51 24-41-51 PB 401

RECEPTACLE - EXTERNAL POWER RECEPTACLE - EXTERNAL POWER - REMOVAL/INSTALLATION

24-41-51-000-001-A 24-41-51-991-00100-A 24-41-51-400-001-A 24-41-55 24-41-55 PB 401

Removal of the External Power Receptacle External Power Receptacle Installation of the External Power Receptacle CONTACTOR CONTACTOR - REMOVAL/INSTALLATION

24-41-55-000-001-A

Removal of the External Power Contactor (EPC)

24-41-55-991-00100-A 24-41-55-991-00100-B 24-41-55-400-001-A

Contactor Contactor Installation of the External Power Contactor (EPC)

24-42-00

AES

AC GROUND SERVICE BUS CONTROL

T.O.C.

Page 13 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-42-00 PB 001

24-42-55 24-42-55 PB 401

SUBJECT AC GROUND SERVICE BUS CONTROL - DESCRIPTION AND OPERATION AC Ground Service Network - Block Diagram AC Ground Service Network - Block Diagram AC Ground Service Bus - Component Location AC Ground Service Bus - Component Location AC Ground Service Bus Control - Schematic Diagram AC Ground Service Bus Control - Schematic Diagram AC GROUND SERVICE BUS CONTROL - MAINTENANCE PRACTICES Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power CONTACTOR CONTACTOR - REMOVAL/INSTALLATION

24-42-55-000-001-A 24-42-55-991-00100-A 24-42-55-991-00100-B 24-42-55-400-001-A 24-42-58 24-42-58 PB 401

Removal of the Contactors Contactors Contactors Installation of the Contactors MODULE MODULE - REMOVAL/INSTALLATION

24-42-00-11200-A 24-42-00-11200-E 24-42-00-12400-A 24-42-00-12400-D 24-42-00-15000-A 24-42-00-15000-E 24-42-00 PB 201 24-42-00-861-001-A 24-42-00-862-001-A

24-42-58-000-001-A 24-42-58-991-00100-A 24-42-58-400-001-A 24-43-00 24-43-00 PB 001 24-43-00-11200-B 24-43-00-12500-A 24-43-00-12500-B 24-43-55 24-43-55 PB 401 24-43-55-000-001-A 24-43-55-991-00100-A 24-43-55-991-00100-B 24-43-55-400-001-A 24-50-00 24-50-00 PB 001 24-50-00-11200-F 24-50-00-11200-U 24-50-00-12700-B 24-50-00-12700-C

AES

Removal of the AC Service Bus Contactor Module AC Service Bus Contactor Module Installation of the AC Service Bus Contactor Module DC GROUND SERVICE BUS CONTROL DC GROUND SERVICE BUS CONTROL - DESCRIPTION AND OPERATION Ground Service Network-General DC Ground Service Bus Control-Component Location DC Ground Service Bus Control - Component Location CONTACTOR CONTACTOR - REMOVAL/INSTALLATION Removal of the DC Service Bus Ground Supply Contactor Contactor Contactor Installation of the DC Service Bus Ground Supply Contactor AC ELECTRICAL LOAD DISTRIBUTION AC ELECTRICAL LOAD DISTRIBUTION - DESCRIPTION AND OPERATION AC Electrical Load Distribution - General AC Electrical Load Distribution - General AC Power Distribution Contactors - Component Location AC Power Distribution Contactors - Component Location

T.O.C.

Page 14 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-50-00-14600-C

SUBJECT Normal Flight Configuration for the Whole Network (AC/DC)

24-50-00-14600-H

Normal Flight Configuration for the Whole Network (AC/DC)

24-50-00-14700-C

Emergency Configuration for the Whole Network (AC/DC)

24-50-00-14700-G

Emergency Configuration for the Whole Network (AC/DC)

24-50-00-14800-C

Smoke Configuration for the Whole Network (AC/DC)

24-50-00-14800-G

Smoke Configuration for the Whole Network (AC/DC)

24-50-00-16200-B

Provision for C/B(s) Installation on the Panel 49VU

24-50-00-16400-A

Provision for C/B(s) Installation on the Panels 105VU and 106VU

24-50-00-16700-A

Provision for C/B(s) Installation on the Panel 121VU

24-50-00-16800-A

Provision for C/B(s) Installation on the Panel 122VU

24-50-00-16900-A

Provision for C/B(s) Installation on the Panel 123VU

24-50-00-17000-A

Provision for C/B(s) Installation on the Panels 124VU and 125VU

24-50-00-17200-A

Provision for C/B(s) Installation on the Panel 2000VU

24-50-00-17400-A

Provision for C/B(s) Installation on the Panel 2001VU

24-50-00 PB 401 24-50-00-040-001-A

Deactivation of the C/B TRIPPED Warning on the Upper ECAM DU

24-50-00-440-001-A

Reactivation of the C/B TRIPPED Warning on the Upper ECAM DU

24-51-00 24-51-00 PB 001 24-51-00-11200-A 24-51-00-11200-F 24-51-00-12400-A 24-51-00-12400-D 24-51-00-12500-A 24-51-00-13800-B 24-51-00 PB 401 24-51-00-040-001-A 24-51-00-440-001-A 24-51-00 PB 501 24-51-00-710-001-A 24-51-51 24-51-51 PB 401

AC MAIN DISTRIBUTION AC MAIN DISTRIBUTION - DESCRIPTION AND OPERATION AC Main Distribution - Block Diagram AC Main Distribution - Block Diagram AC Main Distribution - Component Location AC Main Distribution - Component Location AC Main Distribution - Component Location AC Main Distribution - ECAM Warnings AC MAIN DISTRIBUTION - DEACTIVATION/REACTIVATION Deactivation of the Galley Supply System Reactivation of the Galley Supply System AC MAIN DISTRIBUTION - ADJUSTMENT/TEST Operational Test of the Commercial Electrical Load Shedding TRANSFORMER - 115/26VAC TRANSFORMER - 115/26VAC - REMOVAL/INSTALLATION

24-51-51-000-001-A

Removal of the 115/26VAC Autotransformer

24-51-51-991-00100-A 24-51-51-400-001-A

Autotransformers Installation of the 115/26VAC Autotransformer

24-51-55 24-51-55 PB 401 24-51-55-000-001-A 24-51-55-991-00100-A

AES

AC ELECTRICAL LOAD DISTRIBUTION DEACTIVATION/REACTIVATION

CONTACTOR CONTACTOR - REMOVAL/INSTALLATION Removal of the AC Service Bus Normal Supply Contactor Contactor

T.O.C.

Page 15 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-51-55-991-00100-B 24-51-55-400-001-A 24-51-55-000-002-A 24-51-55-991-00300-B 24-51-55-400-002-A 24-52-00 24-52-00 PB 001 24-52-00-11200-B 24-52-00-12400-A 24-52-00-12500-A 24-52-00-13900-A 24-52-00-14000-A 24-52-00-14100-A 24-52-51 24-52-51 PB 401

AC ESSENTIAL DISTRIBUTION AC ESSENTIAL DISTRIBUTION - DESCRIPTION AND OPERATION AC Essential Distribution - Block Diagram AC Essential Distribution - Component Location AC Essential Distribution - Component Location AC Essential Distribution - ECAM Warnings 115 VAC SHED BUS - Upper and Lower ECAM Display Unit Loss of the 115 VAC ESS BUS (Class 1 - Level 2) TRANSFORMER - 115/26VAC TRANSFORMER - 115/26VAC - REMOVAL/INSTALLATION

24-52-51-000-001-A

Removal of the Essential 115/26VAC Autotransformer

24-52-51-991-00100-A 24-52-51-400-001-A

AutoTransformer Installation of the Essential 115/26VAC Autotransformer

24-52-55 24-52-55 PB 401 24-52-55-000-001-A 24-52-55-991-00100-A 24-52-55-400-001-A 24-56-00 24-56-00 PB 001 24-56-00-12300-B 24-56-00-14600-B 24-56-00-14600-H 24-56-00 PB 401 24-56-00-040-001-A 24-56-00-040-002-A 24-56-00-040-003-A 24-56-00-440-001-A 24-56-00-440-002-A 24-56-00-440-003-A 24-56-00 PB 501 24-56-00-710-001-A 24-56-55 24-56-55 PB 401 24-56-55-000-001-A 24-56-55-991-00100-A

AES

SUBJECT Contactor Installation of the AC Service Bus Normal Supply Contactor Removal of the Contactor Contactor Installation of the Contactor

CONTACTOR CONTACTOR - REMOVAL/INSTALLATION Removal of the AC Shed Essential Bus Contactor AC SHED ESS BUS Contactor Installation of the AC Shed Essential Bus Contactor GALLEY SUPPLY GALLEY SUPPLY - DESCRIPTION AND OPERATION Galley Supply - Component Location Galley Power Supply and Distribution - Schematic Galley Power Supply and Distribution - Schematic GALLEY SUPPLY - DEACTIVATION/REACTIVATION Deactivation of the Galley Supply System Deactivation of the Galley Supply System Deactivation of the Galley Supply System Reactivation of the Galley Supply System Reactivation of the Galley Supply System Reactivation of the Galley Supply System GALLEY SUPPLY - ADJUSTMENT/TEST Operational Test of the Galley Supply CONTACTOR - GALLEY SUPPLY CONTACTOR - GALLEY SUPPLY - REMOVAL/INSTALLATION Removal of the Micro Contactor Located in the Panel 200VU Micro Contactor Located in the Panel 200VU

T.O.C.

Page 16 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-56-55-400-001-A 24-56-55-000-002-A 24-56-55-991-00200-A 24-56-55-400-002-A 24-56-55-000-003-A 24-56-55-991-00300-E 24-56-55-400-003-A

24-60-00 24-60-00 PB 001 24-60-00-11300-B 24-60-00-11300-C 24-60-00-12600-B 24-60-00-12800-A 24-60-00-14400-A

SUBJECT Installation of the Micro Contactor Located in the Panel 200VU Removal of the Contactor Located in the Panel 200VU Contactor Located in the Panel 200VU Installation of the Contactor Located in the Panel 200VU Removal of the Micro Contactor or/and Contactor Located in the Panel 200VU Micro Contactor or/and Contactor Located in the Panel 200VU Installation of the Micro Contactor or/and Contactor Located in the Panel 200VU DC ELECTRICAL LOAD DISTRIBUTION DC ELECTRICAL LOAD DISTRIBUTION - DESCRIPTION AND OPERATION DC Electrical Load Distribution - General DC Electrical Load Distribution - General DC Electrical Load Distribution - Component Location Spare Fuse - Component Location DC EMER CONFIG - Upper and Lower ECAM Display Unit

24-60-00-14500-A

DC Emergency Configuration - Supply of the Network by the CSM/G

24-60-00-14600-A

DC Emergency Configuration - Supply of the Network with the Landing Gear Extended

24-61-00 24-61-00 PB 001 24-61-00-11200-B 24-61-00-11200-C 24-61-00-12500-A 24-61-00-12500-B 24-61-00-13700-A 24-61-00-13800-A 24-61-00-13900-A 24-61-00-14000-A 24-61-00-14100-A 24-61-55 24-61-55 PB 401

DC MAIN DISTRIBUTION DC MAIN DISTRIBUTION - DESCRIPTION AND OPERATION DC Main Distribution - General DC Main Distribution - General DC Main Distribution - Component Location DC Main Distribution - Component Location DC Main Distribution - ECAM Warnings DC BUS 1 FAULT - Upper and Lower ECAM display Unit DC BUS 2 FAULT - Upper and Lower ECAM Display Unit DC BUS 1 and DC BUS 2 FAULT - Upper and Lower ECAM Display Unit DC BAT BUS FAULT - Upper and Lower ECAM Display Unit CONTACTOR CONTACTOR - REMOVAL/INSTALLATION

24-61-55-000-001-A 24-61-55-991-00100-A 24-61-55-991-00100-B 24-61-55-400-001-A 24-61-55-000-002-A 24-61-55-991-00300-B 24-61-55-400-002-A 24-61-58 24-61-58 PB 401

Removal of the DC Service Bus Normal Supply Contactor Contactor Contactor Installation of the DC Service Bus Normal Supply Contactor Removal of the DC Shed-Bus Normal-Supply Contactor Contactor Installation of the DC Shed-Bus Normal-Supply Contactor MODULE MODULE - REMOVAL/INSTALLATION

AES

T.O.C.

Page 17 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-61-58-000-001-A 24-61-58-991-00100-A 24-61-58-400-001-A 24-61-58-000-002-A 24-61-58-991-00200-A 24-61-58-400-002-A 24-62-00 24-62-00 PB 001 24-62-00-11200-B 24-62-00-12400-B 24-62-00-13800-A 24-62-00-13900-A 24-62-00-14000-A 24-62-55 24-62-55 PB 401 24-62-55-000-001-A 24-62-55-991-00100-B 24-62-55-400-001-A 24-67-00 24-67-00 PB 001 24-67-00-11200-C 24-67-00-12500-B 24-92-00 24-92-00 PB 401 24-92-00-000-001-A 24-92-00-991-04000-A 24-92-00-400-001-A 24-92-00-000-002-A 24-92-00-991-04200-B 24-92-00-400-002-A 24-92-00 PB 601 24-92-00-210-003-A 24-92-00-991-00500-A 24-92-00-991-00600-A 24-92-00-991-00700-A 24-92-00-210-004-A 24-92-00-991-00800-A 24-92-00-991-00900-A

AES

SUBJECT Removal of the DC Bus 1 Contactor Module DC Bus 1 Contactor Module Installation of the DC Bus 1 Contactor Module Removal of the DC Bus 2 Contactor Module DC Bus 2 Contactor Module Installation of the DC Bus 2 Contactor Module DC ESSENTIAL DISTRIBUTION DC ESSENTIAL DISTRIBUTION - DESCRIPTION AND OPERATION DC Essential Distribution - General DC Essential Distribution - Component Location DC Essential Distribution - ECAM Warnings DC ESS BUS FAULT - Upper and Lower ECAM Display Unit DC ESS BUS SHED - Upper and Lower ECAM Display Unit CONTACTOR CONTACTOR - REMOVAL/INSTALLATION Removal of the DC Shed Essential Bus Contactor DC Shed Essential Bus Contactor Installation of the DC Shed Essential Bus Contactor REFUELING ON BATTERY REFUELING ON BATTERY - DESCRIPTION AND OPERATION Refueling on Battery - Simplified Schematic Refuel/Defuel Panel - Component Location ELECTRICAL ROUTING ELECTRICAL ROUTING - DEACTIVATION/REACTIVATION Removal of the IDG Feeders from the Pylon IDG Feeders on the Pylon Installation of the IDG Feeders on the Pylon Removal of the IDG Feeders from the Wing and the Pylon IDG Feeders Installation of the IDG Feeders on the Wing and the Pylon ELECTRICAL ROUTING - INSPECTION/CHECK Inspection of the End Fittings of Electrical Conduits in Wing Inboard Leading- Edge Electrical Harness Conduits - Corrosion Protection Typical Fittings Location of Conduit Fittings Inspection of the End Fittings of Electrical Conduits in Wing Outboard Leading-Edge Electrical Harness Conduits - Corrosion Protection Location of Conduit Fittings

T.O.C.

Page 18 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-92-00-210-005-A 24-92-00-991-01000-A 24-92-00-991-01100-A 24-92-00-210-006-A 24-92-00-991-01200-A 24-92-00-991-01300-C 24-92-00-210-007-A 24-92-00-991-01400-A 24-92-00-991-01500-A 24-92-00-210-008-A 24-92-00-991-01600-A 24-92-00-991-01700-A 24-92-00-210-010-A 24-92-00-991-02000-A 24-92-00-991-02100-A 24-92-00-210-011-A 24-92-00-991-02200-A 24-92-00-991-02300-A 24-92-00-210-012-A 24-92-00-991-02400-A 24-92-00-991-02500-A 24-92-00-210-013-A 24-92-00-991-02600-A 24-92-00-991-02700-D 24-92-00-210-014-A

Electrical Harness Conduits - Corrosion Protection Location of Conduit Fittings Inspection of the End Fittings of Electrical Conduits in Vertical Stabilizer Leading-Edge Electrical Harness Conduits - Corrosion Protection Location of Conduit Fittings Inspection of the End Fittings of Electrical Conduits in Flap Track No. 2 Fairing Electrical Harness Conduits - Corrosion Protection Location of Conduit Fittings Inspection of the End Fittings of Electrical Conduits in the Main Landing Gear (MLG) Well and False Spar Box

24-92-00-991-02800-A 24-92-00-991-02900-A 24-92-00-991-03000-C 24-92-00-210-015-A

Electrical Harness Conduits - Corrosion Protection Location of Conduit Fittings Location of Conduit Fittings Inspection of tne End Fittings of Electrical Conduits in the Dry Bay (Outboard)

24-92-00-991-03100-A 24-92-00-210-018-A

Electrical Harness Conduits - Corrosion Protection General Visual Inspection of Elements Fitted on the Following Harnesses: 405VB to 409VB (LH side) and 400VB to 404VB (RH side) Electrical Harnesses - Inspection Electrical Harnesses - Inspection General Visual Inspection of Elements Fitted on the Following Harnesses: 4202VB, 4204VB

24-92-00-991-03200-A 24-92-00-991-03800-B 24-92-00-210-019-A

AES

SUBJECT Inspection of the End Fittings of Electrical Conduits in the Wing Tip Electrical Harness Conduits Location of Conduit Fittings Inspection of the End Fittings of Electrical Conduits in Wing Outboard Trailing -Edge Electrical Harness Conduits - Corrosion Protection Location of Conduit Fittings Inspection of the End Fittings of Electrical Conduits in the Air Conditioning Compartment Electrical Harness Conduits - Corrosion Protection Location of Conduit Fittings Inspection of the End Fittings of electrical Conduits in Vertical Stabilizer Trailing-Edge Electrical Harness Conduits - Corrosion Protection Location of Conduit Fittings Inspection of the End Fittings of Electrical Conduits in the Fuselage Tail Area Electrical Harness Conduits - Corrosion Protection Location of Conduit Fittings Inspection of the End Fittings of Electrical Conduits in Trimmable Horizontal Stabilizer (THS)

T.O.C.

Page 19 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-92-00-991-03300-A 24-92-00-210-020-A 24-92-00-991-03400-A 24-92-00-210-021-A 24-92-00-991-03500-A 24-92-00-210-023-A 24-92-00-991-03700-A 24-92-00-210-024-A 24-92-00-991-09000-A 24-92-00-210-025-A 24-92-00-991-04300-A 24-92-00-220-001-A 24-92-00-991-04400-B 24-92-00-991-10600-A

Tail Cone and APU Accessory Compartment - Inspection Area - Zones 315-316 Detailed Inspection of EWIS Installed in the Upper Forward Pylon (EWIS) Upper Forward Pylon - Access Panels Upper Forward Pylon - Inspection Area - Zones 413-414-423-424

24-92-00-220-003-A

Detailed Inspection of EWIS in the Fan and Accessory Gear Box (EWIS)

24-92-00-991-04600-B

Fan and Accessory Gear Box - Access

24-92-00-220-004-A

Detailed Inspection of EWIS Installed in the Hot Section (EWIS)

24-92-00-991-04700-B 24-92-00-210-026-A

Hot Section - Access General Visual Inspection of EWIS installed in the Wing Center Box (EWIS)

24-92-00-991-04800-A 24-92-00-210-027-A

Wing Center Box - Access - Zones 141-142 General Visual Inspection of EWIS Installed in the Forward Avionic Compartment (EWIS)

24-92-00-991-06100-A 24-92-00-991-11000-A 24-92-00-210-028-A

Forward Avionic Compartment - Access Forward Avionic Compartment - Inspection Area - Zones 121-122 General Visual Inspection of 90VU, 108VU and 109VU in the Forward Avionic Compartment (EWIS) 90VU, 108VU and 109VU Location Detailed Inspection of G, E and P Routes in the Forward Avionic Compartment (EWIS)

24-92-00-991-05300-A 24-92-00-220-005-A 24-92-00-210-029-A 24-92-00-991-05500-A 24-92-00-210-030-A 24-92-00-991-05800-A 24-92-00-210-031-A 24-92-00-991-06200-A

AES

SUBJECT Electrical Harnesses - Inspection General Visual Inspection of Elements Fitted on the Following Harnesses: 4202VB, 4204VB Electrical Harnesses - Inspection General Visual Inspection of Elements Fitted on the Following Harnesses: 4202VB, 4204VB Electrical Harnesses - Inspection Check that Connector is Correctly Tightened by Measurement of the Resistance with a Loop Tester Location of the Loop Tester Measurement Points Detailed Inspection of the Bonding Leads Installed on the Movable Surfaces Bonding Leads located on Movable Surfaces General Visual Inspection of G and P Routes Installed in the Tail Cone and APU Accessory Compartment (EWIS)

General Visual Inspection of EWIS of the 2000VU (EWIS) Forward Cabin Overhead Compartment - Inspection Area -Zones 223-224 General Visual Inspection of 105VU, 106VU, 103VU, 107VU and 70VU Installed in the Lateral Avionic Compartment (EWIS) 105VU, 106VU, 103VU, 107VU and 70VU - Location General Visual Inspection of G Route(s) Installed at FR47 (EWIS) Center Passenger Compartment - Inspection -Route 6G

T.O.C.

Page 20 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-92-00-210-033-A

SUBJECT General Visual Inspection of EWIS Installed in the Rear Avionic Compartment (EWIS)

24-92-00-991-07700-C 24-92-00-991-11300-B 24-92-00-220-007-A

Rear Avionic Compartment - Access Rear Avionic Compartment - Inspection Area - Zones 127-128 Detailed Inspection of G, E and P Routes Installed in the Rear Avionic Compartment (EWIS)

24-92-00-210-034-A

General Visual Inspection of 63VU, 80VU, 187VU and 188VU Installed in the Rear Avionic Compartment (EWIS) 63VU, 80VU, 187VU and 188VU - Location General Visual Inspection of EWIS of the 49VU and the 120VU (EWIS) 49VU and 120VU - Location General Visual Inspection of EWIS Between Seat and A/C Installed in the Forward Passenger Compartment (EWIS)

24-92-00-991-07900-A 24-92-00-210-035-A 24-92-00-991-08200-A 24-92-00-210-036-A 24-92-00-991-08300-A 24-92-00-210-810-A

Forward Passenger Compartment - Inspection Area - Zones 231-232 General Visual Inspection of All G and P Routes Installed in the Forward Passenger Overhead-Compartment (EWIS)

24-92-00-991-16000-A

Forward Passenger Overhead-Compartment - Access Panels - Zones 233-234 Forward Passenger Overhead-Compartment - Inspection Area - Zones 233-234 General Visual Inspection of EWIS Connections Between Seats and A/C Installed in the Center Passenger Compartment (EWIS)

24-92-00-991-16100-A 24-92-00-210-037-A 24-92-00-991-08400-A 24-92-00-210-039-A 24-92-00-991-09300-A

General Visual Inspection of EWIS connections Between Seats and A/C Installed in the Aft Passenger Compartment (EWIS) Aft Passenger Compartment - Inspection Area - Zones 251-252

24-92-00-210-040-A

General Visual Inspection of EWIS Connections Between Seats and A/C Installed in the Aft Cabin Utility (EWIS)

24-92-00-991-09500-A 24-92-00-210-041-A

Aft Cabin Utility - Inspection Area - Zones 261-262 General Visual Inspection of G and P Routes Installed in the Center Passenger Overhead Compartment (EWIS)

24-92-00-991-09800-A 24-92-00-991-09900-A 24-92-00-210-042-A

AES

Center Passenger Compartment - Inspection Area - Zones 241-242

Center Passenger Overhead-Compartment - Inspection Area - Zones 243-244 Center Passenger Overhead-Compartment - Access Panels - Zones 243-244 General Visual Inspection of G and P Routes Installed in the Aft Passenger Overhead-Compartment (EWIS)

24-92-00-991-10000-A 24-92-00-991-10100-A 24-92-00-210-043-A

Aft Passenger Overhead-Compartment - Inspection Area -Zones 253-254 Aft Passenger Overhead-Compartment - Access Panels - Zones 253-254 General Visual Inspection of G and P Routes Installed in the Aft Cabin Overhead-Compartment (EWIS)

24-92-00-991-11500-A 24-92-00-991-11600-A 24-92-00-210-044-A

Aft Cabin Overhead-Compartment - Inspection Area - Zones 261-262 Aft Cabin Overhead-Compartment - Access Panels - Zones 261-262 General Visual Inspection of P Route Installed in the Aft Cabin UtilityArea (EWIS)

T.O.C.

Page 21 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-92-00-991-11800-A 24-92-00-991-11900-A 24-92-00-210-045-A 24-92-00-991-12100-A 24-92-00-210-801-A 24-92-00-991-13100-A 24-92-00-991-13500-A 24-92-00-991-13600-A 24-92-00-210-802-A 24-92-00-991-13800-A 24-92-00-991-13900-A 24-92-00-210-803-A

General Visual Inspection of EWIS of 2001VU (EWIS) Forward Cabin Overhead-Compartment - Inspection Area - Zones 263-264 General Visual Inspection of All Exposed EWIS Within the Wing Fuel Tank (EWIS) Wing Fuel Tank - Inspection Area - Zones 540-640 Wing Fuel Tank - Access Panels - Zone 540 Wing Fuel Tank - Access Panels - Zone 640 General Visual Inspection of All Exposed EWIS Within the Vent Surge Tank (EWIS) Vent Surge Tank - Access Panels - Zones 550-650 Vent Surge Tank - Inspection Area - Zones 550-650 General Visual Inspection of All Exposed EWIS Within Dry Bay (Outboard)(EWIS)

24-92-00-991-14000-A

Dry Bay (Outboard) - Access Panels - Zones 560-660

24-92-00-991-14100-A

Dry Bay (Outboard) - Inspection Area - Zones 560-660

24-92-00-210-804-A

General Visual Inspection of P Route Pump Feeder EWIS (EWIS)

24-92-00-991-14200-A 24-92-00-210-805-A

MLG Bay - Inspection Area - Zones 571-671 General Visual Inspection of G, E and P Routes Installed in the Forward Cargo Compartment (EWIS)

24-92-00-991-14600-A

Forward Cargo Compartment - Inspection Area - Zones 131-132

24-92-00-210-806-A

General Visual Inspection of P Route(s) Installed in the Aft Cargo Compartment (EWIS)

24-92-00-991-14700-A 24-92-00-210-808-A

Aft Cargo Compartment - Inspection Area - Zones 151-152 General Visual Inspection of EWIS Installed in the Lateral Avionic Compartment (EWIS)

24-92-00-991-15600-A 24-92-00-220-008-A

Lateral Avionic Compartment - Inspection Area - Zones 125-126 Detailed Inspection of G, E and P Routes Installed in the Lateral Avionic Compartment (EWIS)

24-92-00-210-812-A

Visual Inspection of EWIS Installed in the Forward Pylon After an Engine Bleed Leak (EWIS)

24-92-00-991-16400-A 24-92-00-210-813-A

Visual Inspection of the Wiring Installed in the Forward Pylon Between Rib01 and Rib07 at Zone B2 General Visual Inspection of EWIS Installed in the Keel Beam Area of MLG-Well and Hydraulic Compartment (EWIS)

24-92-00-991-16600-A 24-92-00-210-814-A

Aft Cargo Compartment - Inspection Area - Zones 147-148 General Visual Inspection of P Routes Installed in Bulk Cargo Compartment (EWIS)

24-92-00-991-16700-A 24-92-00-210-815-A

Bulk Cargo Compartment - Inspection Area - Zones 161-162 General Visual Inspection of G Routes Installed in Inboard-Fixed-Leading Edge Structure (EWIS)

24-92-00-991-16500-A

AES

SUBJECT Aft Cabin Utility Area - Inspection Area - Zones 261-262 Aft Cabin Utility-Area - Access Panels - Zones 261-262

Access Panels - Wing Upper and Lower Surfaces

T.O.C.

Page 22 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-92-00 PB 701 24-92-00-100-001-A 24-92-00-991-04900-A 24-92-00-991-05000-A 24-92-00-100-002-A 24-92-00-991-05100-A 24-92-00-991-05200-A 24-92-00-100-003-A 24-92-00-991-05600-A 24-92-00-991-05700-A

Cleaning of EWIS Installed in the Aft Cabin Underfloor Compartment (Only If Contaminated)(EWIS) Aft Cabin Underfloor Compartment - Access Panels - Zones 171-172 Aft Cabin Underfloor Compartment - Cleaning Area - Zones 171-172 Cleaning of EWIS Installed in the Forward Passenger Compartment (Only If Contaminated)(EWIS) Forward Passenger Compartment - Cleaning Area - Zones 231-232 Forward Passenger Compartment - Access Panels - Zones 231-232 Cleaning of EWIS installed in the Center Passenger Compartment (Only If Contaminated)(EWIS) Center Passenger Compartment - Cleaning Area - Zones 241-242 Center Passenger Compartment - Access Panels - Zones 241-242

24-92-00-100-004-A

Cleaning of EWIS Installed in the Forward Avionic Compartment (Only If Contaminated)(EWIS)

24-92-00-991-05400-A 24-92-00-991-11700-A 24-92-00-100-005-A

Forward Avionic Compartment - Access Forward Avionic Compartment - Cleaning Area - Zones 121-122 Cleaning of EWIS Installed in the Forward Passenger Overhead Compartment (Only If Contaminated)(EWIS)

24-92-00-991-05900-A 24-92-00-991-06000-A 24-92-00-100-007-A 24-92-00-991-06500-A 24-92-00-991-06600-B 24-92-00-100-009-A 24-92-00-991-06900-A 24-92-00-991-07000-A 24-92-00-100-010-A 24-92-00-991-07300-A 24-92-00-991-11100-A 24-92-00-100-013-A 24-92-00-991-07800-E 24-92-00-100-015-A 24-92-00-991-08700-A 24-92-00-100-016-A 24-92-00-991-08800-A

AES

SUBJECT ELECTRICAL ROUTING - CLEANING/PAINTING

Forward Passenger Overhead Compartment - Cleaning - Zones 233-234 Forward Passenger Overhead-Compartment - Access Panels - Zones 231-232 Cleaning of EWIS Installed in the Forward Cabin Utility-Area (Only If Contaminated)(EWIS) Forward Cabin Utility-Area - Cleaning Area - Zones 221-222 Forward Cabin Utility-Area - Access Panels - Zones 221-222 Cleaning of EWIS Installed in the Center Passenger OverheadCompartment (Only If Contaminated)(EWIS) Center Passenger Overhead-Compartment - Cleaning Area - Zones 243-244 Center Passenger Overhead-Compartment - Access Panels - Zones 243-244 Cleaning of EWIS Installed in the Forward Cabin Overhead-Compartment (Only If Contaminated)(EWIS) Forward Cabin Overhead-Compartment - Cleaning Area - Zones 223-224 Forward Cabin Overhead-Compartment - Access Panels - Zones 223-224 Cleaning of EWIS Installed in the Rear Avionic Compartment (Only If Contaminated)(EWIS) Rear Avionic Compartment - Access Cleaning of EWIS Installed in the Zone Under Cabin Floor (Only If Contaminated)(EWIS) Zone Under Cabin Floor - Cleaning Area - Zones 145-146 Cleaning of EWIS Installed in the Cockpit (Only If Contaminated)(EWIS) Cockpit - Sidewall Panels and Ceiling Panels - Zones 211-212

T.O.C.

Page 23 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-92-00-991-13000-A 24-92-00-100-017-A 24-92-00-991-08900-A 24-92-00-100-019-A 24-92-00-991-09600-A 24-92-00-991-09700-A 24-92-00-100-021-A 24-92-00-991-10200-A 24-92-00-991-10300-A 24-92-00-100-022-A 24-92-00-991-10400-A 24-92-00-991-10500-A

Cleaning of EWIS Installed in 49VU and 120VU (Only If Contaminated)(EWIS) 49VU and 120VU - Location Cleaning of EWIS Installed in the Aft Passenger Compartment (Only If Contaminated)(EWIS) Aft Passenger Compartment - Cleaning Area - Zones 251-252 Aft Passenger Compartment - Access Panels - Zones 251-252 Cleaning of EWIS Installed in the Aft Passenger Overhead-Compartment (Only If Contaminated)(EWIS) Aft Passenger Overhead-Compartment - Cleaning Area - Zones 253-254 Aft Passenger Overhead-Compartment - Access Panels - Zones 253-254 Cleaning of EWIS Installed in the Aft Cabin Utility-Area (Only If Contaminated)(EWIS) Aft Cabin Utility-Area - Cleaning Area - Zones 261-262 Aft Cabin Utility-Area - Access Panels - Zones 261-262

24-92-00-100-023-A

Cleaning of EWIS Installed in the Aft Cabin Overhead-Compartment (Only IF Contaminated)(EWIS)

24-92-00-991-10800-A 24-92-00-991-10900-A 24-92-00-100-024-A

Aft Cabin Overhead Compartment - Cleaning Area - Zones 263-264 Aft Cabin Overhead Compartment - Access Panels -Zones 263-264 Cleaning of EWIS Installed in the Underfloor Bay of Forward Cargo Compartment (Only If Contaminated)(EWIS)

24-92-00-991-12200-A 24-92-00-100-025-A 24-92-00-991-14400-A

Forward Cargo Compartment - Cleaning Area - Zones 133-134 Cleaning of EWIS Installed in the Forward Cargo Compartment (Only IF Contaminated)(EWIS) Forward Cargo Compartment - Cleaning Area - Zones 131-132

24-92-00-100-026-A

Cleaning of EWIS Installed in the Aft Cargo Compartment (Only IF Contaminated)(EWIS)

24-92-00-991-14500-A 24-92-00-100-027-A

Aft Cargo Compartment - Cleaning Area - Zones 151-152 Cleaning of EWIS Installed in the Air Conditioning Compartment and Fairings (Only If Contaminated)(EWIS)

24-92-00-991-14800-A 24-92-00-991-15000-A 24-92-00-991-15100-A 24-92-00-100-029-A 24-92-00-991-15200-A 24-92-00-100-030-A 24-92-00-991-15300-A

AES

SUBJECT Cockpit - Cleaning Area - Zones 211-212

Air Conditioning Compartment and Fairings - Access Panels on the Left Side Air Conditioning Compartment and Fairings - Access Panels on the Right Side Air Conditioning Compartment and Fairings - Cleaning Area - Zones 191-192 Cleaning of EWIS Installed in the Bay Behind FWD Cargo Compartment (Only If Contaminated)(EWIS) Bay Behind FWD Cargo Compartment - Cleaning Area - Zones 137-138 Cleaning of EWIS Installed in the Bulk Cargo Compartment (Only If Contaminated)(EWIS) Bulk Cargo Compartment - Cleaning Area - Zones 161-162

T.O.C.

Page 24 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 24-92-00-100-031-A 24-92-00-991-15500-A

AES

SUBJECT Cleaning of EWIS Installed in the Lateral Avionic Compartment (Only If contaminated)(EWIS) Lateral Avionic Compartment - Cleaning Area - Zones 125-126

T.O.C.

Page 25 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

ELECTRICAL POWER - GENERAL - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General

** On A/C 003-004 (Ref. Fig. 24-00-00-11200-C - Electrical Power - General Schematic) ** On A/C 005-099 (Ref. Fig. 24-00-00-11200-H - Electrical Power - General Schematic) ** On A/C ALL

AES

A.

Generation Two Integrated Drive Generators (IDG) normally supply the aircraft electrical power in flight ; each engine drives one generator. The APU drives a third, auxiliary, generator (APU GEN) which can replace either main generator (GEN 1 or GEN 2). The generators supply the distribution network with alternating current. Two Transformer Rectifiers (TR) supply, in normal configuration, the distribution network with direct current. In the event of major failure, a constant-speed hydraulic motor drives an emergency generator (CSM/G) to supply the systems required for aircraft control. On the ground, an electrical Ground Power Unit (GPU) can supply the aircraft. The APU GEN can also be an independant power source.

B.

General Arrangement of the Distribution Network In normal flight configuration, each IDG supplies its own distribution network via its Line Contactor (GLC). The two IDGs are never electrically coupled. The distribution network 1 consists of: . the Alternating Current Bus 1 (AC BUS 1), . the Alternating Current Essential Bus (AC ESS BUS), . the Alternating Current Sheddable Essential Bus (AC SHED ESS BUS). The distribution network 2 corresponds to the Alternating Current Bus 2 (AC BUS 2). The TR 1 powered from the AC BUS 1 supplies through its contactor: . the Direct Current Bus 1 (DC BUS 1), . the Direct Current Battery Bus (DC BAT BUS), . the Direct Current Essential Bus (DC ESS BUS), . the Direct Current Sheddable Essential Bus (DC SHED ESS BUS). Two batteries are associated with the DC BAT BUS. The TR 2 powered from the AC BUS 2 supplies the Direct Current Bus 2 (DC BUS 2) through its contactor. In case of loss of the TR 1 or the TR 2, a third Essential Transformer Rectifier (ESS TR) powered from the AC BUS 1, supplies through its contactor: . the DC ESS BUS, . the DC SHED ESS BUS. In certain failure configurations, the AC ESS BUS and the AC SHED ESS BUS plus, via the ESS TR, the DC ESS BUS and the DC SHED ESS BUS can be supplied by: . the AC BUS 2 if the AC BUS 1 is lost, . the CSM/G more especially in emergency configuration or smoke emergency configuration.

24-00-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Two sheddable AC and DC busbars are powered respectively by the GLC 2 and the TR 2 and controlled by two contactors. These AC busbars are automatically shedded in the single generator configuration and the DC busbars in the single generator and single TR configurations.

AES

24-00-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location A.

Main Component Location (Ref. Fig. 24-00-00-13600-A - Electrical Power - Component Location) ** On A/C 003-004 (Ref. Fig. 24-00-00-13700-A - Control and Indicating - Component Location) ** On A/C 005-099 (Ref. Fig. 24-00-00-13700-D - Control and Indicating - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS ATA REF. DOOR

** On A/C ALL 1PE 3XB 1XE

TR-ESS STAT INV CONTROL UNIT-CSM/G

125 126 125

24-34-51 24-28-51 24-24-34

8XE

CSM/G

148

24-24-51

1XG GPCU 20XG RCPT-EXT PWR 1XS GCU-APU ** On A/C 003-007

92VU 91VU

122 120 121

121AL

24-41-34 24-41-51 24-23-34

8XS GEN-APU ** On A/C 008-099

310

24-23-51

8XS ** On A/C ALL

GEN-APU

316

24-23-51

1XU1 1XU2 22XU1 22XU2 4000XU

GCU-1 GCU-2 EGIU-1 EGIU-2 IDG

121 121 121 122 445

24-22-34 24-22-34 24-22-33 24-22-33 24-21-51

AES

91VU 91VU 95VU 96VU

24-00-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description A.

AC Generation and Distribution (Ref. Fig. 24-00-00-13800-B - AC Generation and Distribution - Schematic) (1) Generation (a) Main generator and APU GEN drive: . Each main generator is driven by an engine HP compressor via an accessory gearbox and an integrated hydromechanical speed regulator which transforms the engine variable speed into constant speed for the generator. In the event of mechanical failure, the IDG pushbutton switch protected by a guard and located on the ELEC panel on the overhead panel, serves to disconnect the IDG. The disconnection mechanism can be reset on the ground only with the engine shut down. . The APU directly drives the APU GEN at constant speed. This maintains the generator frequency constant. (b) Main Generator, APU GEN and Generator Control Unit (GCU) Each generator is controlled, via a GCU, by a GEN pushbutton switch located on the ELEC panel on the overhead panel. The leading particulars of the generator are: . nominal power: 90 KVA at the POR, . voltage: 115 V/200 V, three-phase, 400 Hz. The main functions of the GCU are: . to regulate the generator voltage by the field current, . to protect the network and the generator by control of the associated GLC and the generator field current, . to provide BITE information to the Ground Power Control Unit (GPCU), . to control the warnings associated with the corresponding channel. Each GCU includes a BITE and self monitoring system which: . analyzes most of the faults that affect the channel, . memorizes the corresponding data in a non-volatile memory. In addition the lower ECAM display unit receives the electrical parameters and warnings dealing with the channel concerned. This data transmission is effected via the Electrical Generation Interface Unit (EGIU). (c) Electrical Generation Interface Unit (EGIU) The main function of the EGIU is to process the parameters from the GCU and associated generator. The EGIU then transmits the information to the cockpit (ECAM) via the System Data Acquisition Concentrators (SDACs). Two EGIUs are installed on the aircraft. One EGIU is associated with the GCU1 and the GPCU. This EGIU receives parameters in analog and discrete form: . GEN1 on channel 1 and, . external power on channel 2. Each channel sends its own parameters to SDAC1 and SDAC2 through two isolated ARINC 429 data links. The second EGIU is connected in the same manner to generator 2 and to the APU generator. (d) CSM/G drive In emergency conditions, a hydraulic motor speed-controlled by a servo-valve speed regulator drives the CSM/G. The regulator uses the oil flow from the Blue Hydraulic system to maintain the CSM/G at a constant speed.

AES

24-00-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL In normal conditions, an electric pump supplies the Blue hydraulic system. In emergency conditions, the Ram Air Turbine (RAT) supplies the Blue system. (e) CSM/G and CSM/G control unit Loss of the AC BUS 1 and AC BUS 2 automatically controls the RAT and the CSM/G. The MAN ON guarded pushbutton switch located on the EMER ELEC PWR panel on the cockpit overhead panel serves to manually control the RAT and the CSM/G. This control is redundant with the automatic RAT deployment logic. The CSM/G control unit enables full control of the CSM/G. The leading particulars are : . Nominal Power : 5KVA at POR . Voltage : 115/200VAC, three-phase, 400 Hz. The main functions of the control unit are : . to control the servo-valve excitation for speed regulation . to control the generator voltage by regulation of the field current . to protect the network and the generator by control of the associated GLC and the generator field current . to limit the power delivered at low aircraft speed by limitation of the field current (with respect to the RAT characteristics). The EMER GEN TEST guarded pushbutton switch on the EMER ELEC PWR panel allows to test the CSM/G on the ground, with the Blue electric pump running. (f) Static inverter The static inverter of 350 VA nominal power transforms the direct current voltage from the BAT BUS into a single phase, 115V 400Hz, alternating current. The static inverter is automatically activated in the event of loss of the AC BUS 1 and AC BUS 2. For maintenance purposes, the static inverter delivers FAULT indication to the centralized fault display system (CFDS) through the two battery charge limiters (BCL), (Ref. Para. 3. A. (2)). (2) Transfer Circuit The transfer circuit enables supply of either AC electrical network or both from one of the four power sources (GEN 1, GEN 2, APU GEN, EXT PWR) via the Bus Transfer Contactors (BTC). BTC control is entirely automatic and depends on the availability of these sources and the correct condition of each network. The BTC 1 closes, if no interlock condition exists on the GCU 1: . when the GEN 1 is not available, in order to supply the network 1 from another power source (GEN 2 APU GEN or EXT PWR), . to supply the network 2 from the GEN 1, if the GEN 2, APU GEN and EXT PWR are not available. The BTC 2 control is symmetrical to BTC 1. The GCU 1 or GCU 2 enables closure of the BTC 1 or BTC 2 if no undervoltage condition and no ”GLC welded” failure occurred (Ref. 24-22-00-00). The networks 1 and 2 are supplied in priority order: . by the corresponding generator, . by the ground power unit, . by the APU GEN, . or by the other generator. NOTE :

Locking of the two BTCs and isolation of the two channels is possible by action on the BUS TIE pushbutton switch; this control is located on the ELEC panel on the cockpit overhead panel.

** On A/C 003-004 (3) Distribution The alternating current distribution network comprises three independent parts. The network 1 mainly comprises the AC BUS 1, the AC ESS BUS and the AC SHED ESS BUS which are three-phase, 115 V/400 Hz busses.

AES

24-00-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL The AC BUS 1 supplies the essential busses in series. The AC BUS 1 and the AC ESS BUS also deliver 26 V/400 Hz power supply through their 115/26 V transformer. In the event of AC BUS 1 loss, AC ESS BUS and the AC SHED ESS BUS can be manually restored by the transfer of power supply directly from the AC BUS 2. It is possible to perform the transfer by action on the AC ESS FEED pushbutton switch on the ELEC panel, after illumination of the FAULT legend. In the event of AC BUS 1 and AC BUS 2 loss (emergency configuration), the AC ESS BUS and AC SHED ESS BUS are restored on the CSM/G when the RAT hydraulic power is available. When landing gear is extended, AC ESS BUS and AC STAT INV BUS are supplied by battery 1 via the static inverter. The network 2 includes the AC BUS 2 which is a three-phase, 115 V/400 Hz bus. It also delivers 26 V/400 Hz power supply through a 115/26 V transformer. NOTE :

To carry out ground service operations (Ref. Para. C.), the external power receptacle provides independent and direct supply to a part of the network 2.

** On A/C 005-099 (4) Distribution The alternating current distribution network comprises three independent parts. The network 1 mainly comprises the AC BUS 1, the AC ESS BUS and the AC SHED ESS BUS which are three-phase, 115 V/400 Hz busses. The AC BUS 1 supplies the essential busses in series. The AC BUS 1 and the AC ESS BUS also deliver 26 V/400 Hz power supply through their 115/26 V transformer. In the event of AC BUS 1 loss, AC ESS BUS and the AC SHED ESS BUS can be manually restored by the transfer of power supply directly from the AC BUS 2. It is possible to perform the transfer by action on the AC ESS FEED pushbutton switch on the ELEC panel, after illumination of the FAULT legend. In the event of AC BUS 1 and AC BUS 2 loss (emergency configuration), the AC ESS BUS and AC SHED ESS BUS are restored on the CSM/G when the RAT hydraulic power is available. During RAT deployment or when the following two conditions are both met: . main landing gear compressed, . and A/C speed below 100 Knots, AC ESS BUS and AC STAT INV BUS are supplied by battery 1 via the static inverter. The network 2 includes the AC BUS 2 which is a three-phase, 115 VAC/400 Hz bus. It also delivers 26 VAC/400 Hz power supply through a 115/26 VAC transformer. NOTE :

To carry out ground service operations (Ref. Para. C.), the external power receptacle provides independent and direct supply to a part of the network 2.

** On A/C ALL B.

DC Generation and Distribution (Ref. Fig. 24-00-00-15500-B - DC Generation and Distribution - Schematic) (1) DC Power Sources The power sources of direct current are: . three identical transformer rectifiers and two identical batteries. In normal configuration, the two normal TRs (TR 1 and TR 2) and possibly the batteries supply direct current. In the event of loss of one or both TR, part of the DC network is transferred to the ESS TR. (a) TR Each TR transforms the three-phase alternating current into direct current (28VDC).

AES

24-00-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 1

TR1 and TR2 Upon energization, the two normal TRs operate and supply the DC network via a contactor controlled by the internal TR logic. In case of failure, the TR sends a FAULT signal to the CFDS for maintenance purposes.

2

Essential TR Upon energization, the essential TR operates and supplies the DC network via a contactor. To reset the TR push the TR RST pushbutton switch 15PU located on the relay box 103VU.In addition,the TR sends its electrical parameters to the lower ECAM display unit. In addition, the TR sends its electrical parameters to the lower ECAM display unit.

(b) Batteries Each of the two batteries has a nominal 23 AH capacity and a 24 VDC voltage. The main functions of the batteries are: . to start the APU in flight and on the ground, . to supply the essential network in some configurations. A BCL controls each battery contactor when the BAT pushbutton switch is in the AUTO configuration. In addition, each BCL includes a BITE and a self monitoring system which analyzes internal and peripherical fault information. Initiation of the test is possible via the CFDS or at each power up on ground. Each BCL delivers electrical parameters and warnings concerning each battery to the lower ECAM display unit. ** On A/C 003-004 (2) Distribution The direct current distribution network is divided into two parts. The network 1 comprises the DC BUS 1, the DC BAT BUS, the DC ESS BUS and the DC SHED ESS BUS. The TR 1 supplies the network 1. The network 2 comprises the DC BUS 2. The TR 2 supplies the network 2. In the event of TR 1 loss, the TR 2 automatically restores supply to the DC BUS 1 and the DC BAT BUS. The DC ESS BUS and the DC SHED ESS BUS are automatically transferred to the ESS TR. The AC BUS 1 supplies the ESS TR. The TR 2 loss leads to the symmetrical recovery of the DC BUS 2 from the TR 1 and the same transfer for the DC ESS BUS and the DC SHED ESS BUS. In the event of TR 1 and TR 2 loss (DC BUS 1 and 2 loss), the DC ESS BUS and the DC SHED ESS BUS are supplied from the ESS TR. In case of loss of AC BUS 1 and AC BUS 2 (emergency configuration), DC ESS BUS and DC SHED ESS BUS are recovered by the CSM/G (via the ESS TR) when the RAT hydraulic generation is available. When landing gear is extented, DC ESS BUS only is supplied by battery 2. NOTE :

The external power receptacle directly energizes the TR 2 which can independently supply a part of the DC normal network. (Ground service configuration).

** On A/C 005-099 (3) Distribution The direct current distribution network is divided into two parts. The network 1 comprises the DC BUS 1, the DC BAT BUS, the DC ESS BUS and the DC SHED ESS BUS. The TR 1 supplies the network 1. The network 2 comprises the DC BUS 2. The TR 2 supplies the network 2. In the event of TR 1 loss, the TR 2 automatically restores supply to the DC BUS 1 and the DC BAT BUS. The DC ESS BUS and the DC SHED ESS BUS are automatically transferred to the ESS TR. The AC BUS 1 supplies the ESS TR.

AES

24-00-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL The TR 2 loss leads to the symmetrical recovery of the DC BUS 2 from the TR 1 and the same transfer for the DC ESS BUS and the DC SHED ESS BUS. In the event of TR 1 and TR 2 loss (DC BUS 1 and 2 loss), the DC ESS BUS and the DC SHED ESS BUS are supplied from the ESS TR. In case of loss of AC BUS 1 and AC BUS 2 (emergency configuration), DC ESS BUS and DC SHED ESS BUS are recovered by the CSM/G (via the ESS TR) when the RAT hydraulic generation is available. During RAT deployment or when the following two conditions are both met: . main landing gear compressed, . and A/C speed below 100 Knots, DC ESS BUS only is supplied by battery 2. NOTE :

The external power receptacle directly energizes the TR 2 which can independently supply a part of the DC normal network. (Ground service configuration).

** On A/C ALL C.

Power Supply Via the External Power Receptacle (Ref. Fig. 24-00-00-13800-B - AC Generation and Distribution - Schematic) (1) AC External Power Control Supply An external power receptacle located in front of the nose landing gear well enables power supply of the aircraft network. This is performed by means of the three-phase, 400 Hz, 115/200 V ground power unit. External power supply is controlled from the ELEC panel on the cockpit overhead panel and via the GPCU. The GPCU includes a BITE and a self monitoring system which analyzes most of the faults which may affect the channel. The system memorizes the corresponding information in a non-volatile memory. This memory also memorizes the fault information from each main GCU. Finally, the GPCU delivers all fault information to the CFDS. The test is initialized: . either on the ground by the CFDS, . or automatically at each power-up. Each main GCU or APU GEN GCU then receives the test request. In addition, the GPCU delivers electrical parameters relative to its channel to the EGIU 1, channel 2. (2) Ground Service Bus Control

** On A/C 003-004 (Ref. Fig. 24-00-00-13700-A - Control and Indicating - Component Location) ** On A/C 005-099 (Ref. Fig. 24-00-00-13700-D - Control and Indicating - Component Location) It is possible to supply a part of the aircraft electrical network as follows, directly from the external power receptacle, to carry out ground service operations : . supply of part of the AC network (AC SVCE busses), . supply of part of the DC network (DC SVCE busses), without energization of the whole aircraft electrical network. The MAINT BUS switch located on the panel 2000VU controls the supply of the ground service network.

AES

24-00-00 PB001

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Controls and Indications Related to Electrical Generation and Distribution

** On A/C 003-004 (Ref. Fig. 24-00-00-13700-A - Control and Indicating - Component Location) ** On A/C 005-099 (Ref. Fig. 24-00-00-13700-D - Control and Indicating - Component Location) Controls and indications related to electrical generation and distribution are on: . the ELEC control panels, . the ECAM display units, . the forward entryway circuit breaker panel (2000VU), . the CFDS. ** On A/C ALL A.

MAINT BUS Switch

** On A/C 003-004 (Ref. Fig. 24-00-00-13700-A - Control and Indicating - Component Location) ** On A/C 005-099 (Ref. Fig. 24-00-00-13700-D - Control and Indicating - Component Location) This switch is located on the panel 2000VU. It controls power supply of the AC and DC ground/flight network. ON: This network is supplied in priority as follows: . by the aircraft network if it is energized, . or by the electrical ground power unit, via the external power receptacle. OFF: This network is supplied by the main electrical network. ** On A/C ALL B.

Central Warning System (Ref. Fig. 24-00-00-18300-B - Lower ECAM Display Unit - ELEC Page) The block diagram of the electrical generation appears on the lower ECAM display unit (Ref. 24-27-00-00).

C.

AES

Centralized Fault Display System (CFDS) Line maintenance of the electronic systems is based on the use of the CFDS. The purpose of the CFDS is to give to maintenance technicians a central maintenance aid. The CFDS enables intervention at system or subsystem level from the Multipurpose Control and Display Units (MCDUs) located in the cockpit. From the MCDUs it is possible: . to read the maintenance information, . to initiate various tests. The electrical components connected to the CFDS are: . the GPCU, . the BCLs, . the emergency GCU, . the TRs. The GPCU and BCLs can memorize fault codes and communicate with the CFDIU via ARINC 429 buses. The emergency GCU and the three TRs are connected to the CFDIU by a discrete link: it is thus possible to know only the status of these systems (OK or faulty) during SYSTEM REPORT/TEST sequence.

24-00-00 PB001

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL NOTE :

AES

The GCU1, the GCU2 and the APU GCU are continuously monitored by the GPCU. The GPCU can then transmit to the CFDIU all the failure messages corresponding to the failure codes recorded by these GCUs and the GPCU.

24-00-00 PB001

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 1

BAT 1

DC BUS 1

BAT

2

801PP

BAT 2

FAULT

FAULT

OFF

OFF

V

DC BUS 2 V

E L E C

FAULT OFF

A U T O

AC BUS 1

FAULT

ALTN

AC ESS BUS

A U T O

IDG 2

GEN 1

APU GEN

EXT PWR

GEN 2

FAULT

FAULT

AVAIL

FAULT

OFF

OFF

ON

OFF

OFF

PANEL 35VU

6XE 1PB2

R

BL

GEN 1 LINE

103PP

3PN1

SMOKE

12PB2 4PB2

MAN ON RAT & R EMER GEN FAULT B

OFF

101PP

1PN1

4PB1

6PB1

BAT BUS

3PP

1PC1

2PR

704PP

5PU1

401PP

501PP

5PR

701PP 703PP BAT1 2PB1

8PR 6PN

601PP 602PP

202PP

1PN2 DC BUS 2

28VDC

204PP

3PN2

1PC2

2PP

DC SVCE BUS 7PN

28VDC

28VDC 3PX

6PH

2XB

115

6PP

8PN

5XB

28

4PP

206PP

1PR SHUNT 3PB1

DC ESS BUS

4PC

208PP

SHUNT 3PB2

28VDC 3XB

STATIC INV

5PU2

901XP

12XB 1PU1 TR1

8PH

502PP

12PB1 5PB1

1PP 28VDC

702PP

BAT2 2PB2

A U T O

8PP 28VDC

20PC

6PB2

BCL−1

DC SHED ESS BUS

APU START 49 − 42 − 00

5KA

10KA

CSM/G CONTROL UNIT

1PB1

PANEL 21VU

DC BUS 1

5PB2

BCL−2

FAULT

EMER ELEC PWR

EMER GEN TEST

6KA

11PB

E L E C

AC BUS 2

BUS TIE

IDG 1 R

301PP

FAULT

GALLEY

3PE

801XP AC ELECTRICAL LOAD DISTRIBUTION 24−50−00

1PX

AC ELECTRICAL LOAD DISTRIBUTION 24−50−00

AC SHED ESS BUS 8XP 115V AC

110XP 7XN1

2PU1

15XN1

115VAC

5XN2

5XH

103XP 101XP

AC ESS BUS

231XP−A

26V 15XN2

401XP

204XP

3XN2

115V AC

1XN1 1XP

431XP−A

26V

4XH

3XN1

AC BUS 1

7XN2

131XP−A

26V

5XN1

2XC

AC BUS 2

2XP 115VAC

3XC 3xc2 15XE 15xe2

GLC−1 9XU1 GCU−1 1XU1

AES

BTC−1 11XU1 FUEL PUMPS 28−21−00 GCU−APU

GEN 1

4000XU

1XS

FIGURE 24-00-00-11200-C SHEET 1 Electrical Power - General Schematic

APU GEN

8XS

GPCU 1XG

24-00-00 PB001

2PU2

14PU

10XN

12XN

3801GX 3805GX

216XP 212XP

4PE

ELEC PUMP−Y 29 − 24 − 00

15xe1 EPC 3XG

GLC−APU 3XS

214XP

1XN2

1XC 3xc1

4XX

202XP

4XP

1PE ESS TR

1PU2 TR2

210XP

8XH

BTC−2 11XU2

GLC−2 9XU2

1XX

14XX

2XX

12XX

3802GX 3806GX EXTERNAL POWER RECEPTACLE

Page 11 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 4000XU 2

GLC−EMERG 2XE

CSM/G CONTROL UNIT CSM/G 1XE

8XE

N_MM_240000_0_ACL0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 COMMERCIAL

BAT

2

35VU

BAT 2

FAULT

FAULT

OFF

OFF

FAULT

AC ESS BUS

ALTN

AC ESS FEED V

GALLEY FAULT OFF

A U T O

AC BUS 1

IDG 1

FAULT

APU GEN

OFF

A U T O

AC BUS 2

6XE

IDG 2 EXT PWR

1PB2

GEN 2

FAULT

FAULT

AVAIL

FAULT

OFF

OFF

ON

OFF

PANEL 35VU BL

103PP

GEN 1 LINE SMOKE

FAULT

12PB2 4PB2 1PB1

1PN1

MAN ON RAT & R EMER GEN

12PB1 5PB1

4PB1

6PB1

DC SHED ESS BUS

8PP 28VDC

20PC

401PP 502PP

704PP

501PP

701PP 703PP BAT1 2PB1

8PH

2PR

702PP

BAT2 2PB2

BCL−1

APU START 49 − 42 − 00

5KA

10KA

6KA

CSM/G CONTROL UNIT

6PB2

A U T O

FAULT B

OFF

101PP

5PB2

BCL−2

EMER ELEC PWR

EMER GEN TEST

3PN1

301PP

11PB

E L E C

BUS TIE

GEN 1

801PP

DC BUS 2

V

OFF

E L E C

1

BAT 1

DC BUS 1

5PR

SHUNT 3PB2

206PP

6PN

601PP

204PP

3PN2 SHUNT 3PB1

4PP 28VDC

208PP

8PR

1PR

DC ESS BUS

4PC

602PP 202PP

1PN2

PANEL 21VU 1PP

DC BUS 1

BAT BUS

1PC1

28VDC

3PP 28VDC

DC BUS 2

1PC2

2PP

DC SVCE BUS 7PN

28VDC

3PX 3XB

5PU1

STATIC INV

11PN

6PH

2XB

115

AC ELECTRICAL LOAD DISTRIBUTION 24−50−00

AC ELECTRICAL LOAD DISTRIBUTION 24−50−00 220XP

AC SHED ESS BUS 8XP 115VAC

7XN1

8XH

131XP−A

26V

5XN1

2PU1

110XP

21XN1

15XN1

101XP AC BUS 1

1XP

7XN2

21XN2

AC ESS BUS

210XP 231XP−A

26V

204XP

AC BUS 2

2XP 115VAC

3XC 3xc2

15xe2

GCU−1 1XU1

BTC−1 11XU1 FUEL PUMPS 28−21−00 GCU−APU

GEN 1

4000XU

1XS

APU GEN

8XS

GPCU 1XG

2PU2

14PU

10XN

12XN

3801GX 3805GX

16XX

214XP

216XP 212XP

4PE

ELEC PUMP−Y 29 − 24 − 00

15xe1 EPC 3XG

GLC−APU 3XS

4XX

1XN2

15XE

GLC−1 9XU1

1PE ESS TR

1PU2 TR2

202XP

4XP

2XC 3xc1

1PX

3XN2

1XC

115VAC

5PU2

218XP

15XN2

401XP 115VAC

1XN1

27XN

5XN2

5XH

103XP

3XN1

28XN

431XP−A

26V

4XH

212PP 3PE

801XP

1PU1 TR1

10PN

901XP

12XB

28VDC

210PP

5XB

28

6PP

8PN

BTC−2 11XU2

GLC−2 9XU2

1XX

14XX

2XX

12XX

3802GX 3806GX EXTERNAL POWER RECEPTACLE

GCU−2 1XU2

GEN 4000XU 2

GLC−EMERG 2XE

CSM/G CONTROL UNIT CSM/G 1XE

8XE

N_MM_240000_0_ACW0_01_00

AES

FIGURE 24-00-00-11200-H SHEET 1 Electrical Power - General Schematic

24-00-00 PB001

Page 12 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL (IDG 2) 4000XU

A 8XS 1XU2 1XS

90VU 1XG

1XU1

8XE

4000XU (IDG 1)

20XG

22XU2

22XU1

ACCESS DOOR

RADOME

FR3 109VU FR5

811

FWD ELECTRONIC RACK 90VU

A

108VU FR9 1XE 1PE

103VU

105VU

FR11

TR

BAT 1

TR

FR13

822

BCL1

812

BCL2

FR15

106VU

70VU

BAT 2

107VU

3XB

NOSE LDG/GR WELL

824 FR23

187VU

63VU

188VU

AFT ELECTRONIC RACK 80VU N_MM_240000_0_AAL0_01_00

AES

FIGURE 24-00-00-13600-A SHEET 1 Electrical Power - Component Location

24-00-00 PB001

Page 13 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

A

PANEL 35VU

.

GALLEY

E L E C

OFF

BAT

2

FAULT

FAULT

OFF

OFF

v

BAT2

DC BUS 2

2000VU CIRCUIT BREAKER PANEL .

v

AC BUS 1

AC ESS BUS

ALTN

AC BUS 2

BUS TIE

IDG 1 R

GEN 1

APU GEN

FAULT

FAULT OFF

OFF

A U T O

90

CL

FAULT

A U T O

FAULT

1

BAT 1

DC BUS 1

B

IDG 2 EXT PWR

GEN 2

R

FAULT

AVAIL

FAULT

FAULT

OFF

ON

OFF

N1

4 6 8 2 10 0 72 5

E L E C

EGT

6 8

4 2

t

EMER ELEC PWR

GEN 1

RAT & EMER GEN

LINE

SMOKE

6 8

F .FLOM

c/h

2200 2200 6200

1500 mc

6200

T . FUEL = 1 3900

10 SLP19

FLAP9

0

95 0

N2

SEAT BELT NO SMOKING

IGNITION ANTI ICI APU AVAIL MAX COOL

PANEL 21VU

BL

4

0 130

85 0

EMER GEN TEST

4 6 8 2 10 0 72 5

2

10 0 130

E

t

MAN ON

R

FAULT

A U T O

OFF

A

4WT1

E D

DU ECAM,UPPER

C

B

SYSTEM REPORT / TEST

C

ELEC GPCU

TR 1

GCU EMER

TR 2

BAT CH LIM 1

TR 3

ELEC

D D

BAT CH LIM 2

BAT 1

28 150

V

BAT 2

DC BAT

A

28 150

V A

DC 2

DC 1 DC ESS TR 1

28 150

RETURN

DIR

PROG

PERF

INIT

F−PLN

RAD NAV

FUEL PRED

SEC F−PLN

MCDU MENU

A

B

C

D

E

NEXT PAGE

F

G

H

I

J

1

2

3

K

L

M

N

O

4

5

6

P

Q

R

S

T

7

8

9

U

V

W

X

Y

Z

−

+

OVFY

CLR

0

/

TR 2 ESS TR

28 150

EMER GEN

A

AC 1

DATA

AIR PORT

.

V

AC 2

AC ESS

GEN 2

GEN 1

26 % 116 V 4 0 0 HZ IDG 1 °C 90 TAT + 19 °C SAT + 18 °C

V A

APU

26 % 116 V 4 00 HZ 8 0 °C IDG 2 G . W. C. G .

60 300 28 1 %

KG

4WT2 DU−ECAM,LOWER

MCDU

N_MM_240000_0_AEM0_01_00

AES

FIGURE 24-00-00-13700-A SHEET 1 Control and Indicating - Component Location

24-00-00 PB001

Page 14 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

A

PANEL 35VU COMMERCIAL

BAT 1

DC BUS 1

1

BAT

B 2

35VU

BAT 2

DC BUS 2

FAULT FAULT

.

OFF

E L E C

V

OFF

OFF

V

GALLEY

FAULT OFF

AC BUS 1

A U T O

2000VU CIRCUIT BREAKER PANEL

AC ESS FEED

.

FAULT ALTN

AC ESS BUS

AC BUS 2

BUS TIE

IDG 1

FAULT

A U T O

GEN 2

FAULT

AVAIL

FAULT

OFF

ON

OFF

APU GEN

FAULT OFF

OFF

4 6 8 2 10 0 72 5

IDG 2 EXT PWR

GEN 1

90

CL

E L E C FAULT

4 2

2

EGT

6 8

t

0 130

E EMER ELEC PWR

BL

GEN 1

RAT & EMER GEN

LINE

SMOKE

4

A U T O

A

6200

95

N2

SLP19

FLAP9

0

0

SEAT BELT NO SMOKING

4WT1

E D

DU ECAM,UPPER

C

B

SYSTEM REPORT / TEST

C

ELEC TR 1 TR 2

D

TR 3

BCL 1

mc

T .FUEL= 13900

R

FAULT

GCU EMER

1500

10 0 130

0

6200

MAN ON

OFF

AC GEN

6 8

IGNITION ANTI ICI APU AVAIL MAX COOL

PANEL 21VU EMER GEN TEST

4 6 8 10 0 72 5

2

10

85

t

N1

BAT 1

ELEC

D

BCL 2

28 V 150 A

DC BAT

BAT 2 28 V 150 A

DC 2

DC 1 DC ESS TR 1

28 V 150 A

RETURN

PROG

PERF

INIT

F−PLN

RAD NAV

FUEL PRED

SEC F−PLN

AIR PORT NEXT PAGE

A

B

AC 1

DATA MCDU MENU

C

D

F

G

H

I

J

2

3

K

L

M

N

O

4

5

6

P

Q

R

S

T

7

8

9

U

V

W

X

Y

/

Z

−

+

OVFY

CLR

.

0

APU

26 % 116 V 4 0 0 HZ IDG 1 °C90 TAT SAT

TR 2 28 V 150 A

AC 2 GEN 2

GEN 1

E

1

EMER GEN

AC ESS

+ +

DIR

ESS TR

19 °C 18 °C

26 % 116 V 4 0 0 HZ 80 °C IDG 2 G.W. 60300 KG C.G. 28 1 %

4WT2 DU ECAM,LOWER

MCDU

N_MM_240000_0_AEQ0_01_00

AES

FIGURE 24-00-00-13700-D SHEET 1 Control and Indicating - Component Location

24-00-00 PB001

Page 15 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL IDG 1

R

GEN 1

FAULT

FAULT OFF

GLC −1 GEN

TR 1

115 VAC BUS 1−1XP

BTC −1

1

GEN 1 LINE

GCU −1

BUS TIE A U T O

SMOKE OFF

OFF

GEN 2

IDG 2 R FAULT

FAULT OFF

115 VAC BUS 2−2XP

GLC −2 GEN

2

TR 2

BTC −2

GCU −2 APU GEN FAULT OFF

GLC −APU

APU GEN

115 VAC SVCE BUS 2− 212XP− 214XP 216XP −C

GCU −APU EPC

901XP AC STAT INV

EXT PWR GPCU

AC ESS FEED FAULT ALTN

EXT PWR

AC ESS BUS SWITCHING CNTOR

115 VAC SHED ESS BUS− 115 VAC 8XP ESS BUS−4XP

AVAIL ON

BL

EMER GEN TEST

STAT INV AC ESS BUS EMER CNTR ESS TR

GLC −EMERG CSM/G

CSM/G CONTROL UNIT

N_MM_240000_0_AGL0_01_00

AES

FIGURE 24-00-00-13800-B SHEET 1 AC Generation and Distribution - Schematic

24-00-00 PB001

Page 16 May 01/12 Revision n˚: 40

AES

FIGURE 24-00-00-15500-B SHEET 1 DC Generation and Distribution - Schematic ESS TR

115 VAC 115 VAC ESS BUS − 4XP SHED ESS BUS− 8XP

AC ESS BUS EMER CNTR

AC ESS BUS SWITCHING CNTOR

28 VDC BUS 2 − 2PP

DC NORM BUS 1 SWITCHING CNTOR

DC NORM BUS 2 SWITCHING CNTOR

28 VDC BUS 1 − 1PP

DC ESS BUS SPLY CNTOR

28 VDC SVCE BUS − 6PP

TR 2

115 VAC BUS 2 − 2XP

115 VAC SVCE BUS 2 212XP 214XP 216XP − C

TR 1 CNTOR

TR 1

115 VAC BUS 1 − 1XP

BCL

BCL

28 VDC ESS BUS − 4PP

901XP AC STAT INV

28 VDC BAT BUS − 3PP

28 VDC SHED ESS BUS − 8PP

STAT INV

28 VDC HOT BUS 702PP

1 OFF

FAULT

STAT INV CNTR

OFF

FAULT

BAT 2

BAT 2

BAT 1

V

BAT 1

703PP

704PP

28 VDC HOT BUS − 701PP

V

BAT 2

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_240000_0_AJL0_01_00

24-00-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

1 − TR2 (W) (A) IF VOLTAGE OR VOLTAGE

9 − IDG: (W) IN NORMAL CONFIGURATION (A)WHEN IDG DISCONNECTED OR IDG OUTLET TEMP 180° C OR IDG OIL LOW PRESS

25 V 31 V

2 − EMER GEN VOLTAGE AND FREQUENCY (SAME AS 11, 10) NOT DISPLAYED WHEN EMER GEN OFF

10 − GENERATOR FREQUENCY (G) (A) WHEN FREQUENCY 390 HZ OR FREQUENCY 410 HZ 11 − GENERATOR VOLTAGE (G) (A) WHEN VOLTAGE 110 V OR VOLTAGE 120 V 12 − GENERATOR LOAD (G) (A) WHEN OVERLOAD

3 − "1" OR "2" (W) (A) WHEN ENG 1 OR 2 CORE SPEED IS BELOW IDLE 4 − EXT PWR (W) WHEN AVAILABLE VOLTAGE AND FREQUENCY (SAME AS 11, 10) NOT DISPLAYED WHEN EXT PWR NOT AVAILABLE 5 − APU GEN LOAD, VOLTAGE AND FREQUENCY (SAME AS 12, 11, 10) OFF REPLACES THESE INDICATIONS WHEN APU GEN PUSHBUTTON SWITCH IS SELECTED OFF NOT DISPLAYED WHEN APU MASTER SWITCH IS IN OFF POSITION 6 − GALLEY SHED (W) WHEN GALLEY SHED NOT DISPLAYED IN NORMAL OPERATION 7 − IDG OUTLET OIL TEMPERATURE (G) FLASHES WHEN T° 147° C (A) WHEN T° 180° C

13 − GEN (W) (A) WHEN GEN PUSHBUTTON SWITCH SELECTED OFF OR F 390 HZ OR F 410 HZ OR V 110 V OR V 120 V OR GEN OVERLOAD 14 − BUSBARS (G) WHEN SUPPLIED (A) WHEN NOT SUPPLIED

8 − LO PR OR DISC (NOT DISPLAYED IN NORMAL CONFIGURATION)

4WT2 DU−ECAM, LOWER

ELEC

BAT 1 28 V 150 A

DC 2 DC ESS SHED ESS TR EMERG GEN 28 V 116 V 130 A 400 HZ

TR 1 28 V 150 A 14

AC 1

13

GEN 1 26 % 116 V 400 HZ

11 10 9

BAT 2 28 V 150 A

DC 1

14

12

DC BAT

GALLEY SHED

APU 26 % 116 V 400 HZ

7

AC 2

EXT PWR 116 V 400 HZ

GEN 2 26 % 116 V 400 HZ

115°C IDG 2 DISC

6

5

1 2

AC ESS SHED

IDG 1°C 110 LO PR

8

TR 2 28 V 150 A

3

3

4 N_MM_240000_0_ALL0_01_00

AES

FIGURE 24-00-00-18300-B SHEET 1 Lower ECAM Display Unit - ELEC Page

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 15 − BAT 2 VOLTAGE (G) (A) WHEN VOLTAGE OR VOLTAGE

21 − STATIC INVERTER VOLTAGE (G) (A) WHEN VOLTAGE 110 V OR VOLTAGE 120 V

25 V 31 V

22 − STATIC INVERTER FREQUENCY (G) (A) WHEN FREQUENCY 390 HZ OR FREQUENCY 410 HZ

16 − BAT 2 CURRENT (G) (A) WHEN CURRENT 5 A OFF REPLACES THESE INDICATIONS WHEN BAT PUSHBUTTON SWITCH IS SELECTED OFF 17 − TR VOLTAGE (G) (A) IF VOLTAGE OR VOLTAGE

23 − ESS TR CURRENT (G) NOT DISPLAYED IN NORMAL CONFIGURATION

25 V 31 V

24 − ESS TR VOLTAGE (G) (A) IF VOLTAGE OR VOLTAGE

18 − TR CURRENT (G)

25 V 31 V

NOT DISPLAYED IN NORMAL CONFIGURATION

19 − SHED (A) DISPLAYED WHEN SHED ESS BUSSES ARE SHEDDED

25 − BAT 1

CHARGE DISCHARGE

20 − STATIC INVERTER (W) 26 − DC BAT : (G) (A) WHEN VOLTAGE 110 V OR VOLTAGE 120 V OR WHEN FREQUENCY 390 HZ OR FREQUENCY 410 HZ

WHEN THE VOLTAGE OF THE BATTERY BUS 3PP IS 25 V

(A)

WHEN THE VOLTAGES FROM THE BCL1 AND BCL2 ARE BOTH 25 V

IS

REPLACED BY (A) XX WHEN BOTH VOLTAGES FROM THE BCL1 AND BCL2 ARE NOT AVAILABLE (THE BAT1 AND THE BAT2 P/BSW ARE RELEASED)

LEGEND (A) AMBER (G) GREEN (W) WHITE

24

ELEC

25

BAT 1 28 V 150 A

26

DC BAT

BAT 2 28 V 150 A

DC 1 TR 1 28 V 150 A 23

15 16 DC 2

DC ESS SHED ESS TR EMER GEN 28V 116 V 400 HZ 130 A

AC 1

TR 2 28 V 150 A

17 18

AC 2

AC ESS SHED

19

GEN 1 GEN 2 STAT INV 26 % APU 26 % GALLEY 115 V 26 % 116 V 116 V SHED 400 HZ 400 HZ 116 V 400 HZ 400 HZ IDG 1°C 110 115°C IDG 2 LO PR DISC

20

4WT2 DU−ECAM, LOWER 21 22 N_MM_240000_0_ALL0_02_00

AES

FIGURE 24-00-00-18300-B SHEET 2 Lower ECAM Display Unit - ELEC Page

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

ELECTRICAL POWER - GENERAL - ADJUSTMENT/TEST ** On A/C ALL Task 24-00-00-710-003-A Integrity Test of the Electrical Power 1.

Reason for the Job To ensure aircraft safety after maintenance work on the wiring.

2.

Job Set-up Information A.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-32-00-860-004-A

Procedure to Get Access to the SYSTEM REPORT/TEST/ELEC Page

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

3.

Job Set-up Subtask 24-00-00-860-056-A A.

Aircraft Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

On the ECAM control panel, push the ELEC key (on the lower ECAM DU, the ELEC page comes into view).

(4)

On the MCDU, get the system REPORT/TEST/ELEC page (Ref. TASK 31-32-00-860-004-A).

(5)

Make sure that the AC ESS FEED, BUS TIE and GALLEY pushbutton switches are pushed.

Subtask 24-00-00-865-061-A B.

Make sure that this(these) circuit breaker(s) is(are) closed:

49VU

PANEL

DESIGNATION SDAC/1 AND 2/28VDC/ESS BUS

12WV

F05

106VU

DC BUS/1 AND 2/MONG

68WV

C03

122VU

ELEC/BUS/2XP/CTL

17XN2

V27

122VU

ELEC/AC/BUS1/CTL

17XN1

V25

AES

FIN

LOCATION

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

122VU

PANEL

DESIGNATION ELEC/CNTOR/DC/BUS/TIE1

9PC

FIN W25

LOCATION

122VU

ELEC/EXT PWR/LT CLT/NOT IN/USE

6XG

X30

122VU

ELEC/TR2/MONG

3PU2

X26

122VU

ELEC/TR1/MONG

3PU1

X25

ELEC/GALLEY/GND/FLT/LOGIC

7XA

S24

ELEC/GALY & CAB/GND/FLT/LOGIC

7XA

S24

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

123VU

TR1/SPLY

2PU1

AB10

123VU

TR2/214XP/SPLY

2PU2

AB04

124VU

TR2/CNTOR/SPLY

4PU2

BC01

125VU

TR1/CNTOR/SPLY

4PU1

CF01

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

4.

Procedure Subtask 24-00-00-710-050-A A.

Energization of the Aircraft with the Batteries 1 and 2

ACTION 1.On the ELEC control panel 35VU: . Release the EXT POWER pushbutton switch. . Release the BAT 1 and BAT 2 pushbutton switches.

RESULT On the ELEC control panel 35VU: . The AVAIL legend of the EXT POWER pushbutton switch comes on. . The battery voltmeters show a value higher than 25 volts. 2.On the EMER ELEC PWR section of the panel 21VU: Wait until the PFD and the upper ECAM DU images come . Open the guard, push and hold the EMER GEN TEST into view. pushbutton switch. 3.On the ECAM control panel: On the upper ECAM DU, on the ELEC page: . Push and hold the ELEC key. . The STAT INV indications come into view (115V, 400Hz). . The BAT indications come into view (24V, 20A) (values are given for information). 4.Release the ELEC key of the ECAM control panel and the EMER GEN TEST pushbutton switch of the EMER ELEC PWR section of the panel 21VU. Subtask 24-00-00-710-051-A B.

Ground Service Configuration

ACTION 1.On the control panel 2000VU: . set the MAINT BUS switch to ON

AES

RESULT In the right avionics compartment: . the TR2 operates.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 2.On the panel 122VU: . open then close the circuit breaker 6XG.

RESULT In the right avionics compartment . the TR2 does not operate.

Subtask 24-00-00-710-052-A C.

Loss of the Busbars 1XP and 2XP

ACTION 1.On the ELEC control panel 35VU: . push the EXT POWER pushbutton switch.

RESULT On the ELEC control panel 35VU: . the AVAIL legend of the EXT POWER pushbutton switch goes off.

2.On the panel 122VU: . open the circuit breaker 17XN1.

On . . .

the lower ECAM DU, on the ELEC page: the AC1 busbar indication comes on amber the DC2 busbar energizes the DC BAT busbar the ESS TR busbar energizes the DC ESS busbar.

On the upper ECAM DU: . the AC BUS1 FAULT warning comes into view. 3.On the panel 122VU: . close the circuit breaker 17XN1.

On . . .

the lower ECAM DU, on the ELEC page: the AC1 busbar indication becomes green the DC1 busbar energizes the DC BAT busbar the ESS TR busbar energizes the DC ESS busbar.

On the upper ECAM DU: . the AC BUS1 FAULT warning goes out of view. 4.On the panel 123VU: . open then close the circuit breaker 1XC.

On the lower ECAM DU, on the ELEC page: . the DC1 busbar energizes the DC ESS busbar.

5.On the panel 122VU: . open the circuit breaker 17XN2.

On the lower ECAM DU, on the ELEC page: . the AC2 busbar indication comes on amber. On the upper ECAM DU: . the AC BUS2 FAULT warning comes into view.

6.On the panel 122VU: . close the circuit breaker 17XN2.

On the lower ECAM DU, on the ELEC page: . the AC2 busbar indication becomes green. On the upper ECAM DU: . the AC BUS2 FAULT warning goes out of view.

Subtask 24-00-00-710-053-A D.

Transfer Logic of the Busbar 4XP ACTION

1.On the panel 123VU: . open the circuit breaker 1XC.

RESULT On the lower ECAM DU, on the ELEC page: . the AC ESS busbar indication comes on amber . the SHED indication comes into view under the AC ESS busbar indication. On the lower ECAM DU: . the AC ESS BUS FAULT and AC ESS FEED .... ALTN warnings come into view. On the ELEC control panel 35VU: . the FAULT legend of the AC ESS FEED pushbutton switch comes on.

AES

24-00-00 PB501

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 2.On the ELEC control panel 35VU: . release the AC ESS FEED pushbutton switch.

RESULT On the ELEC control panel 35VU: . the FAULT legend of the AC ESS FEED pusbutton switch goes off and the ALTN legend comes on. On the lower ECAM DU, on the ELEC page: . the AC ESS busbar indication becomes green . the SHED indication goes out of view. On the upper ECAM DU: . the AC ESS BUS FAULT and AC ESS FEED .... ALTN warnings go out of view.

3.On the panel 123VU: . open the circuit breaker 2XC.

On the ELEC control panel 35VU: . the FAULT legend of the AC ESS FEED pushbutton switch comes on and the ALTN legend stays on. On the lower ECAM DU, on the ELEC page: . the AC ESS busbar indication becomes amber . the SHED indication comes into view under the AC ESS busbar indication. On the upper ECAM DU: . the AC ESS BUS FAULT warning comes into view.

4.On the panel 123VU: . close the circuit breaker 2XC.

On the ELEC control panel 35VU: . the FAULT legend of the AC ESS FEED pushbutton switch goes off and the ALTN legend stays on. On the lower ECAM DU, on the ELEC page: . the AC ESS busbar indication becomes green . the SHED indication goes out of view. On the upper ECAM DU: . the AC ESS BUS FAULT warning goes out of view.

5.On the panel 123VU: . close the circuit breaker 1XC. 6.On the ELEC control panel 35VU: . push the AC ESS FEED pushbutton switch.

No change. On the ELEC control panel 35VU: . the ALTN legend of the AC ESS FEED pushbutton switch goes off. On the lower ECAM DU, on the ELEC page: . the line between the AC2 and the AC ESS busbar indications goes out of view . the line between the AC1 and the AC ESS busbar indications comes into view.

Subtask 24-00-00-710-054-A E.

Loss of the Electrical Network with the BUS TIE Pushbutton Switch

ACTION 1.On the ELEC control panel 35VU: . Release the BUS TIE pushbutton switch.

AES

RESULT On the ELEC control panel 35VU: . The OFF legend of the BUS TIE pushbutton switch comes on. Make sure that the lower and upper ECAM DUs are deenergized.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 2.On the ELEC control panel 35VU: . Push the BUS TIE pushbutton switch.

RESULT On the ELEC control panel 35VU: . The OFF legend of the BUS TIE pushbutton switch goes off. Make sure that the lower and upper ECAM DUs are energized again.

Subtask 24-00-00-710-055-A F.

Galley Shedding Logic ACTION

1.On the panel 122VU: . open the circuit breaker 7XA.

RESULT On the lower ECAM DU, on the ELEC page: . the GALLEY SHED indication comes into view.

2.On the panel 122VU: . close the circuit breaker 7XA.

On the lower ECAM DU, on the ELEC page: . the GALLEY SHED indication goes out of view.

3.On the ELEC control panel 35VU: . release the GALLEY pushbutton switch. 4.On the ELEC control panel 35VU: . push the GALLEY pushbutton switch.

On . On .

the lower ECAM DU, on the ELEC page: the GALLEY SHED indication comes into view. the lower ECAM DU, on the ELEC page: the GALLEY SHED indication goes out of view.

Subtask 24-00-00-710-056-A G.

Transfer Logic of the DC Electrical Network NOTE :

This test is for the system 1. For the other system(s), use the indications between parentheses.

ACTION 1.On the panel 122VU: . open the circuit breaker 3PU1 (3PU2).

RESULT On the lower ECAM DU, on the ELEC page: . no change.

2.On the panel 125VU (124VU): . Open the circuit breaker 4PU1 (4PU2).

On the lower ECAM DU, on the ELEC page: . The TR1 (2) stops to energize the DC1 (2) busbar . The DC1 (2) busbar indication stays amber for 5 seconds . The TR1 (2) voltage parameter is between 29V and 31V. . The TR1 (2) current parameter is less than 5A. . The DC2 (1) busbar energizes the DC1 (2) busbar through the DC BAT busbar . The ESS TR energizes the DC ESS busbar. On the upper ECAM DU: . The TR1 (2) warning comes into view.

3.On the panels 122VU and 125VU (122VU, 124VU): . Close the circuit breakers 3PU1 (2) and 4PU1 (2).

No change.

4.On the MCDU, on the ELEC page: . Push the line key adjacent to the TR1 (2) indication.

On the MCDU: . The TR1 (2) pages comes into view.

.

On . On . .

AES

push the line key adjacent to the RESET indication.

the MCDU: The NO FAULT indication comes into view. the lower ECAM DU, on the ELEC page: The TR1 (2) energizes the DC1 (2) busbar The ESS TR continues to energize the DC ESS busbar.

24-00-00 PB501

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION

RESULT On the upper ECAM DU: . The TR1 (2) FAULT warning goes out of view.

5.On the panel 125VU: . Open then close the circuit breaker 1XC.

On the lower ECAM DU, on the ELEC page: . The DC1 busbar energizes the DC ESS busbar.

6.On the panel 123VU: . Open the circuit breaker 2PU1 (2).

On the lower ECAM DU, on the ELEC page: . The TR1 (2) stops to energize the DC1 (2) busbar . The DC1 (2) busbar indication stays amber for 5 seconds . The TR1 (2) voltage parameter is approximately 0V. . The TR1 (2) current parameter is less than 5A. . The DC2 (1) busbar energizes the DC1 (2) busbar through the DC BAT busbar . The ESS TR energizes the DC ESS busbar. On the upper ECAM DU: . The TR1 (2) FAULT warning comes into view.

7.On the panel 123VU: . Close the circuit breaker 2PU1 (2).

On the lower ECAM DU, on the ELEC page: . The TR1 (2) voltage parameter is between 29V and 31V. . The TR1 (2) current parameter is less than 5A.

8.On the MCDU, on the ELEC page: . Push the line key adjacent to the TR1 (2) indication.

On the MCDU: . The TR1 (2) page comes into view.

.

On . On . .

Push the line key adjacent to the RESET indication.

the MCDU: The NO FAULT indication comes into view. the SD, on the ELEC page: The TR1 (2) energizes the DC1 (2) busbar The ESS TR continues to energize the DC ESS busbar.

On the upper ECAM DU: . The TR1 (2) FAULT warning goes out of view. 9.On the panel 125VU: . Open then close the circuit breaker 1XC.

On the lower ECAM DU, on the ELEC page: . The DC1 busbar energizes the DC ESS busbar.

10.On the panel 122VU: . Open the circuit breaker 9PC.

On the lower ECAM DU, on the ELEC page: . The DC2 busbar energizes the DC BAT busbar (the DC1 busbar stops to energize The DC BAT busbar) . The ESS TR energizes the DC ESS busbar.

11.On the control panel 122VU: . Close the circuit breaker 9PC.

On the lower ECAM DU, on the ELEC page: . The DC1 busbar energizes the DC BAT busbar . The ESS TR energizes the DC ESS busbar.

12.On the panel 125VU: . Open then close the circuit breaker 1XC.

On the lower ECAM DU, on the ELEC page: . The DC1 busbar energizes the DC ESS busbar.

Subtask 24-00-00-710-057-A H.

Test of the DC EMER CONFIG Warning

ACTION 1.On the panels 106VU and 49VU: . open the circuit breakers 68WV and 12WV.

AES

RESULT On the lower ECAM DU, on the ELEC page: . the DC ESS busbar indication comes on amber.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION

2.On the panels 106VU and 49VU: . close the circuit breakers 68WV and 12WV.

RESULT On the upper ECAM DU: . the DC EMER CONFIG and EMER ELEC PWR ... MAN ON warnings come into view. On the lower ECAM DU, on the ELEC page: . the DC ESS busbar indication becomes green. On the upper ECAM DU: . the DC EMER CONFIG and EMER ELEC PWR ... MAN ON warnings go out of view.

Subtask 24-00-00-710-058-A J.

Emergency Logic with the Batteries

ACTION 1.Make sure that the voltage of the batteries 1 and 2 is more than 25.5V. 2.On the ELEC control panel 35VU: . Release then push the BAT1 pusbutton switch.

3.On the ELEC control panel 35VU: . Release then push the BAT2 pushbutton switch.

4.On the ELEC control panel 35VU: . Release the BAT1 and BAT2 pusbutton switches. On the EMER ELEC PWR control panel 21VU: . Push and hold the EMER GEN TEST pushbutton switch. On the ELEC control panel 35VU: . Release the BUS TIE pushbutton switch. On the ECAM control panel . Push and hold the ELEC KEY.

RESULT

On the lower ECAM DU, on the ELEC page: . The green line between the DC BAT busbar and the BAT1 indications come into view . The load current is < 150A then decreases . The green line goes out of view when the load current is < 4A. On the lower ECAM DU, on the ELEC page: . The green line between the DC BAT busbar and the BAT2 indications comes into view . The load current is < 150A then decreases . The green line goes out of view when the load current is < 4A. On the ELEC control panel 35VU: . The OFF legend of the BAT1 and BAT2 pushbutton switches comes on.

Total loss of the normal electrical network. On the upper ECAM DU: . The AC ESS and the DC ESS busbar indications come on green. . The SHED indication comes into view under the AC ESS and the DC ESS busbar indications . The STAT INV indication is shown white . The STAT INV parameters (115V, 400Hz) are shown green.

5.On the ELEC control panel 35VU: . Push the BUS TIE pushbutton switch . Push the BAT1 and BAT2 pushbutton switches.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION On the EMER ELEC PWR control panel 21VU: . Release the EMER GEN TEST pushbutton switch.

RESULT The normal electrical network is energized again. On the ELEC control panel 35VU: . The OFF legend of the BAT1 and BAT2 pushbutton switches goes off.

6.On the MCDU: . Push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. 5.

Close-up Subtask 24-00-00-860-057-A A.

AES

Put the Aircraft back to its initial Configuration (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

ELECTRICAL POWER - GENERAL - INSPECTION/CHECK ** On A/C ALL Task 24-00-00-200-003-A General - Inspection/Check of the Electrical Circuits and Equipment WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. 1.

Reason for the Job The inspection/check procedure of electrical circuit includes two different operations: . A fast inspection, which includes a visual examination of all visible components without component removal. . A detailed inspection during which components are removed. Thus you can see the other components which are behind and do a detailed visual inspection of all components of the system.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 2 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels

ZONE/ACCESS 121AL, 811, 812, 822 FOR FIN 1000EM1(ENGINE-1)

ZONE DESCRIPTION

437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR C.

Referenced Information

REFERENCE 71-13-00-010-010-A

DESIGNATION Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

3.

Job Set-up Subtask 24-00-00-860-055-A A.

AES

Aircraft Maintenance Configuration (1)

In the cockpit, put a WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on the panels 35VU, 211VU and 115VU.

(2)

Put a WARNING NOTICE(S) on the door 121AL to tell persons not to connect the external power receptacle.

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Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-00-00-941-057-A B.

Get access to the Avionics Compartment (1)

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the doors 811, 812 and 822 of the electronics compartment and at the door 121AL which gives access to the external power receptacle.

Subtask 24-00-00-010-051-B C.

Get Access (1)

4.

Open the fan cowl doors (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Procedure Subtask 24-00-00-210-065-A A.

Fast Inspection (1)

Do . . . . .

a check of the general outer condition and attachment of these components: Panels and their equipment Electrical connectors Rack-mounted system components Indicators Electrical bonding leads.

(2)

Check the condition of all wiring (for signs of ageing, alteration, overheating, scaling and deformation which can cause a decrease of wiring performance).

(3)

Replace defective components.

Subtask 24-00-00-210-066-A B.

Detailed Inspection (1)

Open ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE and casings, remove or open panels and shields and, if necessary, remove components which are in front of other components, to gain access to wiring, plugs, electrical connections and the different system components.

(2)

Components

(3)

(4)

(a)

Remove dust with a vacuum cleaner and clean other dirt if necessary.

(b)

Do a check of labels and their identification.

(c)

Do a check of attachment and general condition of components.

Wiring (a)

Do a check of identification sleeves or labels protective coatings, insulation and protective fittings for correct condition.

(b)

Do a check of the condition of wiring (for signs of ageing, alteration, overheating, scaling and deformation which can cause a decrease of wiring performance).

Electrical connectors (a)

AES

Disconnect plugs, do a check of their physical and electrical condition. Make sure that there are no signs of oxidation or corrosion, replace defective components (seals, gaskets, grommets, ferrules etc...).

24-00-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b)

Do a check of the tightness of connections to all electrical accessories, ground bonding leads, ground leads, busbars and terminal bars.

(c)

Do a check of tightness of non-safetied connectors.

(d)

Do a check of the condition of electrical connector protections in the hydraulics compartment.

Subtask 24-00-00-020-053-A C.

Replacement of the Defective Components (1)

Replace defective components.

Subtask 24-00-00-420-053-A D.

Installation of the Removed Components (1)

5.

Install removed components and put back all equipment in operating condition.

Close-up Subtask 24-00-00-865-059-A A.

Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) (circuit breaker(s) with dark-gray extension caps):

49VU

PANEL

DESIGNATION ENGINE/1 AND 2/IGN/SYS A

1JH

FIN A03

LOCATION

121VU

ENGINE/IGN/ENG2/SYS B

3JH2

P42

121VU

ENGINE/IGN/ENG1/SYS B

3JH1

P41

121VU

ENGINE/IGN/ENG2/SYS A BAT

2JH2

P40

121VU

ENGINE/IGN/ENG1/SYS A BAT

2JH1

P39

Subtask 24-00-00-410-057-A B.

Close the access doors 811 812 822 121AL.

Subtask 24-00-00-410-058-B C.

Close Access (1)

Close the fan cowl doors (Ref. TASK 71-13-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Subtask 24-00-00-942-054-A D.

AES

Put the aircraft back to its initial configuration. (1)

Remove the warning notice(s).

(2)

Remove the access platform(s).

24-00-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-00-00-200-004-A Opening and Closing of all Circuit Breakers with Electrical Circuits De-Energized 1.

Reason for the Job (Ref. MPD 24-00-00-17-) ELECTRICAL POWER, OPENING AND CLOSING OF ALL CIRCUIT BREAKERS. This task gives the procedure to do an opening and closing cycle of the circuit breakers to: . Have a better reliability . Decrease the number of maintenance problems . Decrease the effects of circuit breaker aging.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

100 200 121AL C.

DESIGNATION

ZONE DESCRIPTION LOWER HALF FUSELAGE INCLUDING RADOME UPPER HALF FUSELAGE

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-21-00-750-002-A

Procedure to set the Clock

3.

Job Set-up Subtask 24-00-00-860-058-A A.

4.

Aircraft Maintenance Configuration (1)

In the cockpit, put a WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on the panels 35VU, 211VU and 115VU.

(2)

Put a WARNING NOTICE(S) in position on the door 121AL to tell persons not to connect the external power receptacle.

(3)

Make sure the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Procedure Subtask 24-00-00-210-067-A A.

Opening and Closing of Circuit Breakers NOTE :

AES

Open and close the circuit breakers with the aircraft electrical circuit de-energized.

24-00-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (1)

5.

Open and close each circuit breaker on these panels: (a)

In . . . . . .

the cockpit: 49VU 121VU 122VU 123VU 124VU 125VU.

(b)

In the avionics compartment: . 105VU . 106VU.

(c)

In the cabin: . 2000VU . 2001VU.

Close-up Subtask 24-00-00-750-050-A A.

Adjustment of the Clock (1)

Adjust the clock, if necessary (Ref. TASK 31-21-00-750-002-A).

Subtask 24-00-00-942-055-A B.

AES

Put the aircraft back to its initial configuration. (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the warning notice(s).

24-00-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC GENERATION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General

** On A/C 003-004 The AC generation consists of: . two Integrated Drive Generators (IDG) (Ref. 24-21-00-00-13), . a main generation corresponding to the two IDG channels and to the transfer circuit (Ref. 24-22-00-00), . an auxiliary generation corresponding to the APU generator and its channel (Ref. 24-23-00-00), . an emergency generation corresponding to the constant speed motor/ generator, its associated GCU and its channel (Ref. 24-24-00-00), . the essential generation switching (Ref. 24-25-00-00), . the control circuits for galley supply, . the monitoring and indicating circuits for the cockpit. ** On A/C 005-099 The AC generation consists of: . two Integrated Drive Generators (IDG) (Ref. 24-21-00-00-13), . a main generation corresponding to the two IDG channels and to the transfer circuit (Ref. 24-22-00-00), . an auxiliary generation corresponding to the APU generator and its channel (Ref. 24-23-00-00), . an emergency generation corresponding to the constant speed motor/generator, its associated GCU and its channel (Ref. 24-24-00-00), . the essential generation switching (Ref. 24-25-00-00), . the control circuits for galley and sheddable busbars supply (Ref. 24-26-00-00), . the monitoring and indicating circuits for the cockpit.

AES

24-20-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-20-00-12400-B - Main Components - Component Location) (Ref. Fig. 24-20-00-12500-A - Main Components - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

2XA

P/BSW-ELEC/GALLEY

35VU

2XB 3XB 3XC 11XC

CNTOR-STAT INV STAT INV CNTOR-AC ESS BUS SWITCHING P/BSW-ELEC/AC ESS FEED

105VU

1XE

CONTROL UNIT-CSM/G

2XE 8XE

GLC-EMER CSM/G

14XE 15XE 23XE

ZONE ACCESS ATA REF. DOOR 210 24-26-00 126 126 125 210

24-28-55 24-28-51 24-25-55 24-25-00

125

24-24-34

106VU

125 148

24-24-55 24-24-51

ANN-EMER ELEC PWR/RAT/&/EMER GEN

21VU

211

24-24-00

106VU 21VU

125 211

24-24-55 24-24-00

24XE

CNTOR-AC ESS BUS SWITCHING P/BSW-EMER ELEC PWR/EMER GEN TEST P/BSW-EMER ELEC PWR/MAN ON

21VU

211

24-24-00

1XS 2XS

GCU-APU P/BSW-ELEC/APU GEN

91VU 35VU

121 210

24-23-34 24-23-00

120VU

212

24-23-55

8XS GEN-APU ** On A/C 008-099

310

24-23-51

8XS ** On A/C ALL

GEN-APU

316

24-23-51

42XS 5XT

CT-AC, APU GEN P/BSW-ELEC/IDG 1

120VU 35VU

212 210

24-23-17 24-21-00

6XT

P/BSW-ELEC/IDG 2

35VU

210

24-21-00

1XU1 1XU2 3XU1

GCU-1 GCU-2 P/BSW-ELEC/GEN 1

91VU 91VU 35VU

121 121 210

24-22-34 24-22-34 24-21-00

3XU2

P/BSW-ELEC/GEN 2

35VU

210

24-21-00

9XU1 9XU2 11XU1 11XU2 13XU

GLC-1 GLC-2 BTC-1 BTC-2 P/BSW-EMER ELEC PWR/GEN1 LINE

120VU 120VU 120VU 120VU 21VU

212 212 212 212 211

24-22-55 24-22-55 24-22-55 24-22-55 24-21-00

22XU1 22XU2 41XU1 41XU2

EGIU-1 EGIU-2 CT-AC, 1 CT-AC, 2

95VU 96VU

121 122 131 132

24-22-33 24-22-33 24-22-17 24-22-17

3XS GLC-APU ** On A/C 003-007

AES

106VU 35VU

24-20-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL FIN 42XU1 42XU2 42XU3 42XU4 50XU1 50XU2 4000XU ** On A/C 005-099

FUNCTIONAL DESIGNATION CT-AC, 1 CT-AC, 2 CT-AC, 1 CT-AC, 2 SENSOR-TDC AC, 1 SENSOR-TDC AC, 2 IDG

PANEL 120VU 120VU 120VU 120VU 103VU 103VU

ZONE ACCESS DOOR 212 212 212 212 126 126 445

ATA REF. 24-22-17 24-22-17 24-22-17 24-22-17 24-22-18 24-22-18 24-21-51

51XU1 CT 212 24-22-17 51XU2 CT 212 24-22-17 ------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA I I I I DOOR I REF. ------------------------------------------------------------------------------5XB HOLDER-FUSE 105VU 126 822 24-28-00 5XB1 FUSE-AC STAT INV BUS SPLY 105VU 126 822 24-28-00 ** On A/C ALL A.

Spare Fuse (Ref. Fig. 24-20-00-13000-A - Spare Fuse - Component Location) If fuse 5XB1 melts, you can replace it by a spare 80A fuse which is on the left side panel, in the cockpit.

AES

24-20-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL (IDG2) 4000XU 8XS

A 1XU2

8XE

1XS

90VU 1XG

1XU1

4000XU

20XG

(IDG1)

22XU2

RADOME

22XU1

ACCESS DOOR

FR3 109VU FR5

811

FWD ELECTRONIC RACK 90VU

A

108VU FR9

103VU

105VU

FR11

TR

BAT 1

TR

FR13

BCL1 BCL2

812 FR15

106VU

70VU 822

BAT 2

107VU

3XB

NOSE LDG/GR WELL

824 FR23

187VU

63VU

188VU

AFT ELECTRONIC RACK 80VU

N_MM_242000_0_AAL0_01_00

AES

FIGURE 24-20-00-12400-B SHEET 1 Main Components - Component Location

24-20-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR12 FR14 FR13 FR15

FR5 FR3

FR16 FR20

811

822

812 841

120VU

49VU

122VU

21VU

35VU 121VU 25VU 125VU 123VU

4WT2

124VU

4WT1

90VU

FR16 106VU FR9 N_MM_242000_0_ACM0_01_00

AES

FIGURE 24-20-00-12500-A SHEET 1 Main Components - Component Location

24-20-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A FR13

FR1

B

B

SPARE FUSE

N_MM_242000_0_AEL0_01_00

AES

FIGURE 24-20-00-13000-A SHEET 1 Spare Fuse - Component Location

24-20-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC GENERATION - DEACTIVATION/REACTIVATION ** On A/C ALL Task 24-20-00-040-001-A Check of the AC Main Generation Maintenance Condition CAUTION :

NOTE : 1.

MAKE SURE THAT THE IDG DOES NOT OPERATE FOR MORE THAN 50 HOURS IN THE DISCONNECTED MODE. IF THE IDG OPERATES FOR 50 HOURS IN THE DISCONNECTED MODE, IT WILL BE NECESSARY TO : REPLACE THE IDG. SEND THE REMOVED IDG FOR A SHOP INSPECTION. THERE IS A RISK OF DAMAGE TO THE BALL BEARING ASSEMBLY ON THE IMPUT SHAFT. The procedure is the same for IDG1 (IDG2).

Reason for the Job MMEL 24-22-01A AC Main Generation (IDG, GCU, Line Contactor) (Old MMEL ref: 24-20-01)

2.

Job Set-up Information A.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

** On A/C 006-099 49-00-00-860-005-A

APU Start by External Power

49-00-00-860-005-A-01

APU Start by Batteries

49-00-00-860-006-A

APU Shutdown by External Power

49-00-00-860-006-A-01

APU Shutdown by Batteries

** On A/C 003-005 49-00-00-860-008-A

APU Start by External Power

49-00-00-860-008-A-01

APU Start by Batteries

49-00-00-860-009-A

APU Shutdown by External Power (131-9(A))

49-00-00-860-009-A-01

APU Shutdown by Batteries (131-9(A))

** On A/C 006-099 49-90-00-600-004-A

AES

Check Oil Level and Replenish (APS 3200)

24-20-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE ** On A/C 003-005 49-90-00-600-007-A

DESIGNATION Check Oil Level and Replenish (131-9(A))

(Ref. Fig. 24-20-00-991-00200-A - Oil Consumption of the APU GTCP 36-300) (Ref. Fig. 24-20-00-991-00300-A - Oil Consumption of the APU APS 3200) (Ref. Fig. 24-20-00-991-00400-A - Oil Consumption of the APU 131-9(A)) 3.

Job Set-up ** On A/C ALL Subtask 24-20-00-860-050-A A.

4.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

Procedure Subtask 24-20-00-040-051-C A.

Fuel recirculation Check (1)

On the ECAM control panel, push the STS key.

(2)

On the lower ECAM display unit, make sure that the ”ENG 1(2) FADEC” message does not come into view on the STATUS page. (a)

(3)

If the message comes into view for the engine with the IDG in operation: . Make sure that none of the messages that follow come into view: . ACOC OIL TEMP TC/HC/EEC . IDG OIL TEMP TC/HC/EEC . ACOC AIR MOD VLV/HC/EEC . FUEL DIV RET VLV/HC/EEC . HMS FUEL OVTMP . HMS ENG OIL OVTMP . HMS IDG OIL OVTMP . HMS IDG OVTMP W/RECIRC . FUEL DIV RET VLV/EEC

On the maintenance panel 50VU: . Release the ENG/FADEC GND PWR/1(2) pushbutton switch(es) (the ON legend(s) come(s) on).

Subtask 24-20-00-710-050-A B.

Do this test:

ACTION 1.On one MCDU, get the SYSTEM REPORT/TEST ENG menu page. 2.On the MCDU, on the ENG menu page: . push the line key adjacent to the FADEC 1A(2A) indication.

AES

RESULT

On the MCDU: . the FADEC 1A(2A) page comes into view.

24-20-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION RESULT 3.On the FADEC 1A(2A) page: On the MCDU: . push the line key adjacent to the LAST LEG REPORT . make sure that there is no message related to the indication. control system of the fuel return valve. 4.On the MCDU: . push the line key adjacent to the RETURN indication until the ENG menu page comes into view. 5.On the MCDU, on the ENG menu page: . push the line key adjacent to the FADEC 1B(2B) indication. 6.On the FADEC 1B(2B) page: . push the line key adjacent to the LAST LEG REPORT indication.

On the MCDU: . the FADEC 1B(2B) page comes into view. On the MCDU: . make sure that there is no message related to the control system of the fuel return valve.

7.On the MCDU: . push the MCDU MENU mode key. Subtask 24-20-00-210-053-A C.

Check of the APU Oil Consumption (1)

If you do a regular monitoring of the APU oil consumption, make sure that the APU oil quantity is sufficient for the flight: .

.

. (2)

For the GTCP 36-300 (Ref. Fig. 24-20-00-991-00200-A - Oil Consumption of the APU GTCP 36-300) or For the APS 3200 (Ref. Fig. 24-20-00-991-00300-A - Oil Consumption of the APU APS 3200) or For the 131-9(A) (Ref. Fig. 24-20-00-991-00400-A - Oil Consumption of the APU 131-9(A))

If you do not do a regular monitoring of the APU oil consumption, do the steps that follow to make sure that the APU oil quantity is sufficient for the flight: (a)

(b)

Make sure that APU LOW OIL LEVEL indication is not shown: 1

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

2

On the ECAM control panel, push the APU key (on the lower ECAM DU, the APU page comes into view).

3

Make sure that the APU LOW OIL LEVEL indication is not shown.

4

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

Make sure that there are no oil leaks: 1

Start and operate the APU: . .

.

AES

For the GTCP 36-300 (Ref. AMM 49-00-00-860-003) , or For the APS 3200 ** On A/C 006-099 (Ref. TASK 49-00-00-860-005-A) or (Ref. TASK 49-00-00-860-005-A-01), or For the 131-9(A)

24-20-00 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-00-00-860-008-A)(Ref. TASK 49-00-00-860-008-A-01). 2

3

During APU operation: . Do a check for oil smell in the passenger compartement. . Do a check for white smoke from the APU exhaust. NOTE :

An oil smell in the passenger compartement shows that there is an internal and/or external oil leakage.

NOTE :

Smoke from APU exhaust shows that there is an internal oil leakage.

Stop the APU: . .

.

(c)

For the GTCP 36-300 (Ref. AMM 49-00-00-860-004) , or For the APS 3200 ** On A/C 006-099 (Ref. TASK 49-00-00-860-006-A) or (Ref. TASK 49-00-00-860-006-A-01), or For the 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-00-00-860-009-A)(Ref. TASK 49-00-00-860-009-A-01).

Make sure that the APU oil is at maximum level: . .

.

For the GTCP 36-300 (Ref. AMM 49-90-00-600-001) , or For the APS 3200 ** On A/C 006-099 (Ref. TASK 49-90-00-600-004-A), or For the 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-90-00-600-007-A).

NOTE : 5.

During the oil level check, make sure that there is no external oil leakage in the APU compartement.

Close-up ** On A/C ALL Subtask 24-20-00-860-051-A A.

AES

Put the aircraft back to its initial configuration. (1)

On the panel 50VU: . push the ENG/FADEC GND PWR/1(2) pushbutton switch(es) (the ON legend(s) go(es) off).

(2)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(3)

Make an entry in the log book.

(4)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-20-00 PB401

Page 4 May 01/12 Revision n˚: 40

AES

FIGURE 24-20-00-991-00200-A SHEET 1 Oil Consumption of the APU GTCP 36-300 0

2

6

1.5

0.5

8

2.0

4

10

2.5

1.0

12

3.0

18

4.5

14

20

5.0

3.5

22

5.5

16

24

6.0

4.0

26

6.5

10

24-20-00 PB401 30

GRAPH A

40

50

60

70

80

90

OIL QUANTITY IN THE APU OIL RESERVOIR IS SUFFICIENT FOR MINIMUM 10 HOURS APU OPERATION WITHOUT PREFLIGHT SERVICE IF NO "LOW OIL LEVEL" INDICATION IS SHOWN.

APU OPERATING TIME (HOURS)

20

GRAPH B

OIL QUANTITY IN THE APU OIL RESERVOIR IS SUFFICIENT FOR 10 HOURS APU OPERATION IF SERVICED BEFORE FLIGHT TO THE "FULL" MARK ON THE OIL SIGHT GLASS.

OIL QUANTITY IN THE APU OIL RESERVOIR IS NOT SUFFICIENT FOR 10 HOURS APU OPERATION

(US. GALLONS) (QUARTS)

100

1.9

3.8

5.7

7.6

9.5

11.4

13.3

15.1

17.0

18.9

20.8

22.7

24.6

(LITRES)

THE ADDED OIL (CUMULATIVE) (VERTICAL SCALE) IS THE TOTAL QUANTITY OF OIL WHICH WAS ADDED TO THE APU OIL RESERVOIR IN ORDER TO COMPENSATE FOR THE APU OIL CONSUMPTION DURING AN APU OPERATING TIME PERIOD (HORIZONTAL SCALE).

NOTE:

OIL CONSUMPTION IS THE TERM USED FOR THE INTERNAL LOSS OF OIL FROM BEARING SEALS AND AIR/OIL SEPARATOR DURING APU OPERATION. EXTERNAL LEAKS ARE NOT PERMITTED. YOU MUST CORRECT EXTERNAL LEAKS AND CLEAN THE APU, APU COMPARTMENT AND APU AIR INTAKE IMMEDIATELY IF CONTAMINATED. IF THE OIL CONSUMPTION IS HIGHER THAN THE "GRAPH A" LIMIT, OR THERE IS A SUDDEN INCREASE IN OIL CONSUMPTION, YOU MUST DO THE OIL CONSUMPTION MONITORING VERY CAREFULLY TO PREVENT BAD APU DAMAGE.

CAUTION:

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

ADDED OIL (CUMULATIVE)

N_MM_242000_4_AAM0_01_00

Page 5 May 01/12 Revision n˚: 40

AES

FIGURE 24-20-00-991-00300-A SHEET 1 Oil Consumption of the APU APS 3200 0

2

6

1.5

0.5

8

2.0

4

10

2.5

1.0

12

3.0

18

4.5

14

20

5.0

3.5

22

5.5

16

24

6.0

4.0

26

6.5

10

24-20-00 PB401 30

40

50

60

70

80

90

OIL QUANTITY IN THE APU OIL RESERVOIR IS SUFFICIENT FOR MINIMUM 10 HOURS APU OPERATION WITHOUT PREFLIGHT SERVICE IF NO "LOW OIL LEVEL" INDICATION IS SHOWN.

GRAPH A

APU OPERATING TIME (HOURS)

20

GRAPH B

OIL QUANTITY IN THE APU OIL RESERVOIR IS SUFFICIENT FOR 10 HOURS APU OPERATIO IF SERVICED BEFORE FLIGHT TO THE "FULL" MARK ON THE OIL SIGHT GLASS.

OIL QUANTITY IN THE APU OIL RESERVOIR IS NOT SUFFICIENT FOR 10 HOURS APU OPERATION

(US. GALLONS) (QUARTS)

100

1.9

3.8

5.7

7.6

9.5

11.4

13.3

15.1

17.0

18.9

20.8

22.7

24.6

(LITRES)

THE ADDED OIL (CUMULATIVE) (VERTICAL SCALE) IS THE TOTAL QUANTITY OF OIL WHICH WAS ADDED TO THE APU OIL RESERVOIR IN ORDER TO COMPENSATE FOR THE APU OIL CONSUMPTION DURING AN APU OPERATING TIME PERIOD (HORIZONTAL SCALE).

NOTE:

OIL CONSUMPTION IS THE TERM USED FOR THE INTERNAL LOSS OF OIL FROM BEARING SEALS AND AIR/OIL SEPARATOR DURING APU OPERATION. EXTERNAL LEAKS ARE NOT PERMITTED. YOU MUST CORRECT EXTERNAL LEAKS AND CLEAN THE APU, APU COMPARTMENT AND APU AIR INTAKE IMMEDIATELY IF CONTAMINATED. IF THE OIL CONSUMPTION IS HIGHER THAN THE "GRAPH A" LIMIT, OR THERE IS A SUDDEN INCREASE IN OIL CONSUMPTION, YOU MUST DO THE OIL CONSUMPTION MONITORING VERY CAREFULLY TO PREVENT BAD APU DAMAGE.

CAUTION:

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

ADDED OIL (CUMULATIVE)

N_MM_242000_4_ABM0_01_00

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

CUMULATIVE OIL ADDED QUARTS (GALLONS)

QUARTS (US GALLONS)

LITERS

20 (4.16)

18.9

18 (3.74)

17.0

16 (3.32)

15.1

UNSATISFACTORY CONSUMPTION

14 (2.9) 12 (2.51)

13.2 UNUSUAL OIL CONSUMPTION USE APU ONLY WHEN OIL IS FILLED BEFORE EACH FLIGHT

0.196qt/hr (185cc/hr)

10 (2.07)

11.4 9.4 7.6

8 (1.67) 6 (1.25)

5.7

0.099qt/hr (93cc/hr)

4 (0.84)

3.8

SATISFACTORY CONSUMPTION

2 (0.42)

1.9

0.0

0.0 10

20

30

40

50

60

70

80

90

100

APU OPERATING TIME (HOURS)

NOTE: MAXIMUM OIL CONSUMPTION FOR NEW OR NEWLY OVERHAULED APU IS 0.007qt(6.5cc)AN HOUR

N_MM_242000_4_ACM0_01_00

AES

FIGURE 24-20-00-991-00400-A SHEET 1 Oil Consumption of the APU 131-9(A)

24-20-00 PB401

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-20-00-040-002-A RAT Extension Control - Check of the RAT Manual Extension WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT THE CONTROLS AGREE WITH THE POSITION OF THE ITEMS THEY OPERATE BEFORE YOU PRESSURIZE A HYDRAULIC SYSTEM. UNWANTED MOVEMENT OF HYDRAULICALLY OPERATED ITEMS CAN CAUSE SERIOUS INJURY AND/OR DAMAGE. 1.

Reason for the Job MMEL 24-24-02A RAT Extension Automatic Control (Old MMEL ref: 24-20-06-A))

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

SAFETY BARRIER(S)

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

812 C.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

29-10-00-863-003-A

Pressurize the Blue Hydraulic System with a Ground Power Supply

29-10-00-863-003-A-01

Pressurize the Blue Hydraulic System with the Blue Electric Pump

29-10-00-864-003-A

Depressurize the Blue Hydraulic System

** On A/C 003-004 29-22-00-869-001-A

Extension of the Ram Air Turbine (RAT) on the Ground

29-22-00-869-002-A

Retraction of the Ram Air Turbine (RAT) on the Ground

AES

24-20-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE ** On A/C 005-099

DESIGNATION

29-22-00-869-005-A

Extension of the Ram Air Turbine (RAT) on the Ground

29-22-00-869-006-A

Retraction of the Ram Air Turbine (RAT) on the Ground

(Ref. Fig. 24-20-00-991-00100-A - RAT Control) (Ref. Fig. 24-20-00-991-00100-C - RAT control) 3.

Job Set-up ** On A/C ALL Subtask 24-20-00-860-053-A A.

Aircraft Maintenance Configuration (1)

Make sure that the WARNING NOTICE(S) are in position.

(2)

Put the safety barriers in position.

(3)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(4)

Pressurize the Blue hydraulic system (Ref. TASK 29-10-00-863-003-A) or (Ref. TASK 29-10-00-863-003-A-01).

Subtask 24-20-00-010-050-A B.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access door 812 of the avionics compartment.

(2)

Open the access door 812.

Subtask 24-20-00-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

106VU 4.

DESIGNATION CSM/G /EV/MAN/SPLY

FIN 6XE

LOCATION B04

Procedure

** On A/C 003-004 (Ref. Fig. 24-20-00-991-00100-A - RAT Control) ** On A/C 005-099 (Ref. Fig. 24-20-00-991-00100-C - RAT control) WARNING : MAKE SURE THAT THE RAT TRAVEL RANGE IS CLEAR BEFORE YOU EXTEND/RETRACT THE RAT.

AES

24-20-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 Subtask 24-20-00-710-053-A A.

Extension of the RAT (1)

Do the extension of the Ram Air Turbine (RAT) on the ground (Ref. TASK 29-22-00-869-001-A).

Subtask 24-20-00-710-054-A B.

Retraction of the RAT (1)

Do the retraction of the Ram Air Turbine (RAT) on the ground (Ref. TASK 29-22-00-869-002-A).

** On A/C 005-099 Subtask 24-20-00-710-053-B A.

Extension of the RAT (1)

Do the extension of the Ram Air Turbine (RAT) on the ground (Ref. TASK 29-22-00-869-005-A).

Subtask 24-20-00-710-054-B B.

Retraction of the RAT (1)

5.

Do the retraction of the Ram Air Turbine (RAT) on the ground (Ref. TASK 29-22-00-869-006-A).

Close-up ** On A/C ALL Subtask 24-20-00-860-052-A A.

Put the aircraft back to its initial configuration. (1)

Depressurize the Blue hydraulic system (Ref. TASK 29-10-00-864-003-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

(3)

Remove the warning notice(s).

(4)

Remove the safety barriers.

Subtask 24-20-00-410-050-A B.

AES

Close Access (1)

Close the access door 812.

(2)

Remove the access platform(s).

24-20-00 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 40VU

21VU

B A 197EB 195CB 21VU FR42

A

EMER GEN TEST

FR41

EMER ELEC PWR RAT & EMER GEN

MAN ON

A U T O

FAULT

24XE

B

WARNING

TEST ARM

INDEX LOCK MECHANISM

STOW

GROUND CHECK

RAT GROUND CONTROL UNIT

N_MM_242000_4_AAA0_01_00

AES

FIGURE 24-20-00-991-00100-A SHEET 1 RAT Control

24-20-00 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Z195

21VU

B

A A

21VU EMER GEN TEST

EMER ELEC PWR RAT & EMER GEN

MAN ON

A U T O

FAULT

C 24XE

B INDICATION LIGHTS

C INTERLOCK ACTUATOR PRESSURE WARNING

RAT STOWED

RESET O N

LOCKING MECHANISM

STOW

LAMP TEST

28V DC

O F F

J2

N_MM_242000_4_AAC0_01_00

AES

FIGURE 24-20-00-991-00100-C SHEET 1 RAT control

24-20-00 PB401

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-20-00-440-002-A Reactivation of the RAT Extension Control 1.

Reason for the Job MMEL 24-24-02A RAT Extension Automatic Control (Old MMEL ref: 24-20-06-A))

2.

Job Set-up Information A.

Referenced Information

REFERENCE ** On A/C 003-004 29-22-00-710-001-A

DESIGNATION Operational Check of Ram Air Turbine (RAT) Automatic Deployment

** On A/C 005-099 29-22-00-710-006-A 3.

Operational Check of Ram Air Turbine Automatic Deployment

Job Set-up ** On A/C ALL Subtask 24-20-00-860-056-A A.

4.

Not Applicable

Procedure ** On A/C 003-004 Subtask 24-20-00-710-055-A A.

Do the operational test of the RAT automatic extension (Ref. TASK 29-22-00-710-001-A).

** On A/C 005-099 Subtask 24-20-00-710-055-B A. 5.

Do the operational test of the RAT automatic extension (Ref. TASK 29-22-00-710-006-A).

Close-up ** On A/C ALL Subtask 24-20-00-860-055-A A.

AES

Make sure that the work area is clean and clear of tool(s) and other items.

24-20-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) DESCRIPTION AND OPERATION ** On A/C ALL 1.

General Each engine (HP rotor) drives its associated Integrated Drive Generator (IDG) through the accessory gearbox. The drive speed varies according to the engine rating. The IDG provides a 115/200VAC, 3-phase, 400 Hz AC supply. The IDG has two parts: the Constant-Speed Drive (CSD) and the generator. The hydromechanical Constant-Speed Drive (CSD) drives the AC generator at constant speed.

AES

24-21-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-21-00-12400-A - IDG Location in Nacelle) (Ref. Fig. 24-21-00-12300-A - IDG Attachment to the Gearbox) (Ref. Fig. 24-21-00-12600-A - ELEC Control Panel - Location) (Ref. Fig. 24-21-00-12800-A - Fuel-Cooled IDG Oil Cooler and Cables - Location) The IDG system is attached to the engine fan case: . the IDG is installed on the engine gearbox pad; it is attached by means of a Quick Attach Detach (QAD) adapter, . the IDG cables are between the IDG and the electrical receptacle on the aircraft pylon, . the fuel-cooled IDG oil cooler is a part of the engine heat management system, . the fuel-cooled IDG oil cooler tubes connect the IDG to the fuel-cooled IDG oil cooler, . the IDG oil temperature thermocouple is installed in the fuel-cooled IDG oil cooler. FIN

5XT

P/BSW-ELEC/IDG 1

35VU

ZONE ACCESS ATA REF. DOOR 210 24-21-00

6XT

P/BSW-ELEC/IDG 2

35VU

210

24-21-00

4000XU 4015KS 6003EM

IDG THERMOCOUPLE-IDG OIL TEMPERATURE FCOC

445 410 435

24-21-51 24-21-15 79-21-43

AES

FUNCTIONAL DESIGNATION

PANEL

437AL

24-21-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description A.

Integrated Drive Generator (IDG) (1) The IDG converts the variable-speed shaft power directly into constant frequency 400 Hz AC electrical power. The Constant Speed Drive (CSD), in the IDG, drives the AC generator at constant speed. Thus, the AC generator produces constant frequency power.

B.

Fuel-Cooled IDG Oil Cooler (1) The fuel-cooled IDG oil cooler cools the IDG oil and limits the IDG inlet temperature. As the oil goes through the oil cooler, heat is transferred from the oil to the fuel. Then the cooled oil returns to the IDG. NOTE :

C.

The normal IDG oil-inlet temperature is between 70 deg.C and 105 deg.C.

Generator Control Unit (GCU) Each GCU controls its dedicated IDG: . IDG 1: GCU 1 . IDG 2: GCU 2 The GCU has these main functions: . regulation of the generator voltage at Point Of Regulation (POR) . monitoring and protection of the system.

D. IDG Pushbutton Switches If an IDG is faulty (overheat or abnormal oil low pressure), the FAULT legend of the IDG pushbutton switch comes on. The pilot must then open the safety guard and push the IDG pushbutton switch. This action results in the mechanical disconnection of the faulty IDG. NOTE :

AES

With engine stopped, the IDG cannot be disconnected. An underspeed condition inhibits the disconnection.

24-21-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Power Supply A.

Circuit Breakers

122VU

PANEL

DESIGNATION ELEC/IDG1/DISC

1XT

T24

122VU

ELEC/IDG2/DISC

2XT

T25

AES

FIN

LOCATION

24-21-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 5.

Interface A.

Generator Control Unit (1) Input data Each GCU receives the following signals from its dedicated IDG: . oil inlet temperature, . oil outlet temperature, . low oil pressure, . PMG 3 phase output voltage, . CT 3 phase signal. (2) Output data Each GCU provides the following output analog data to the SDACs, through the ARINC 429 link: . IDG oil output temperature, . IDG oil inlet temperature, . AC load at POR, . AC frequency (phase A) . AC voltage (phase A) at POR. It provides also to the SDACs the following discrete information through ARINC 429 link: . overload warning, . generator fault, . IDG disconnect status, . IDG disconnect pushbutton position, . IDG oil outlet overheat, . IDG oil low pressure, . GEN pushbutton switch position.

AES

24-21-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 6.

Description A.

Description of the IDG (Ref. Fig. 24-21-00-12500-A - IDG - Interface Accessories) (1) Electrical circuit . hook-up of the electrical wiring, . location of the electrical connectors. (2) Maintenance . oil replenishing . oil drainage . oil level check . filter . disconnect reset handle. (3) Inspection . Differential Pressure Indicator (DPI) of the oil filter on the IDG oil-out line. (4) Cooling system . oil inlet port, . oil outlet port.

B.

Quick Attach Detach (QAD) Adapter The IDG is installed on the engine gearbox pad. It is attached to the gearbox by means of a QAD adapter with a tension bolt.

C.

Drive A mechanical epicyclic differential-gear transmits power to the generator of the IDG. The speed of mechanically-coupled twin hydraulic-sub-assemblies modify the differential-gear output speed. Each sub-assembly consists of a hydraulic swashplate pump/motor: one with a fixed and the other with a variable swash angle. The input shaft has a shear neck. Its primary duty is to protect the engine gearbox. But it is also used to protect the IDG against damage. (Ref. Fig. 24-21-00-19900-A - IDG - Speed Regulation Loop) This figure shows the speed regulation loop.

D. Generator The generator is a three-stage assembly which has three machines connected in cascade. The first machine (Pilot Exciter (PE)) is a twelve-pole Permanent Magnet Generator (PMG). Its rotor is constructed of small Rare Earth Cobalt magnets. The output from the PE stator winding: . has a generator excitation function, . provides power for other components of the electrical system (supply of the GCU, EGIU and the external relays and contactors).The generator is thus ”self-flashing” and ”self-sufficient”. The second machine (Main Exciter (ME)), ten-pole stator, receives its field excitation from the pilot exciter via the voltage regulator in the GCU: this creates a stationary field. Rotating diodes rectify the three phase output of the main exciter rotor. The resulting DC current feeds the third machine (main alternator) rotor winding. Thus, the main alternator receives excitation for the rotating salient four-pole field from the rectified output of the main exciter. The main alternator has a three-phase star-connected stator winding. The three phases and star point neutral are taken to the generator output terminal block. The generator is designed for use with an external voltage regulator which is part of the GCU. The GCU: . rectifies the output of the pilot exciter, . regulates the excitation current to the main exciter field winding.

AES

24-21-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL The IDG generator contains three shielded toroidal current-transformers combined into one assembly. The current transformers provide outputs proportional to the current in the links connecting the neutral ends of the main stator windings to the neutral terminal. They are designed for use in conjunction with the differential feeder current protection circuit in the GCU. The secondary windings of these transformers are connected to the IDG electrical connector A (refer to paragraph E below). E.

Electrical Connectors (Ref. Fig. 24-21-00-21600-A - IDG - Internal Schematic) There are three differently-sized electrical connectors on the IDG. (1) Connector A The following internal components are connected to it: . the Main Exciter (ME) . three current transformers . the disconnect solenoid. (2) Connector B The following internal component are connected to it: . the PMG stator . the oil-in and oil-out temperature bulbs . the input speed sensor. (3) Connector C Only one internal component is connected to it: . the charge pressure switch.

F.

IDG Oil System A fuel-cooled IDG oil cooler located near the IDG is used to cool the IDG oil. The schematic of the IDG oil system is shown on figure (Ref. Fig. 24-21-00-21400-A - IDG Oil System - Schematic) (1) IDG oil system operation The IDG has a self-contained oil system except for the fuel-cooled IDG oil cooler. Positive displacement scavenge-pumps deliver the oil (via the IDG oil filter) to the fuel-cooled IDG oil cooler and return it to the IDG. The lubrication jets are individually supplied. The dearator provides the inlet of the charge pump with cleaned, cooled and deaerated oil. The charge pump pressurizes the oil against the charge relief valve. It thus provides regulated supply pressures to: . the differential hydraulic units, . the control piston, . the generator, . the governor, . the various lubrication and cooling nozzles. The oil filter has a Differential Pressure Indicator (DPI) to show when it is necessary to replace the filter element. The sensing device for the differential pressure is automatically neutralized during cold oil running conditions: this avoids spurious indications due to high oil viscosity. Similarly, a cooler by passvalve is fitted in the IDG. When pressure rises, the valve opens so the cooler is bypassed during cold oil operation. A scavenge pump relief-valve limits the supply pressure of the scavenge system. A vent valve releases internal case pressure if necessary.

AES

24-21-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2) IDG oil-pressure fill A quick fill coupling installed on the transmission casing enables pressure filling or topping up the unit with oil. The oil thus introduced flows to the transmission via the filter and external cooler circuit. This ensures: . the priming of the external circuit, . the filtration of any oil introduced. An internal standpipe connected to an overflow drain ensures a correct quantity of oil. NOTE :

Motoring is not necessary for oil level check or oil replenishment.

(3) Oil filter differential pressure indicator The scavenge filter is fitted with an oil filter differential pressure indicator. The indicator shows when the filter element requires replacement. The sensing device for the oil filter differential pressure indicator is automatically inhibited during cold oil running conditions. This avoids spurious operation due to high oil viscosity. (4) Oil level check The oil level can be read on the vertical sight glass. Servicing is performed according to the oil level position in zones determined by different colors (red, yellow, green). (5) Disconnect reset handle A mechanical reset handle is fitted to the IDG. The handle enables the drive to be reconnected while the engine is shut down and stationary on the ground. G.

IDG Feeder Cables (1) The terminals on each end of the IDG feeder cables are different. On one end, they connect to the IDG, while on the other end they connect to the aircraft pylon electrical-connector.

H. Fuel-Cooled IDG Oil Cooler Tubes (1) All six IDG oil-cooler tubes are rigid metal tubes. The tubes which attach to the fuel-cooled IDG oil cooler have a three-bolt flange connection at one end. The three-bolt flange connections have an alignment boss and a groove for the installation of a seal ring. All the other ends of the tubes have the usual (male or female) flareless tube connections. Three of the tubes are 0.625in. in diameter and three are 0.75in. in diameter. Four of the tubes also have support brackets attached to them: two tubes have one bracket each and two tubes have three brackets each. J.

IDG Oil Temperature Thermocouple (1) The thermocouple has a two-bolt installation flange, an electrical receptacle and a thermocouple protection cover. The unit is a sealed assembly and it cannot be disassembled. The electrical receptacle connects with an electrical connector from the engine electrical harness. The thermocouple assembly attaches to the fuelcooled IDG oil cooler with the two-bolt flange. The cover seals the unit from the oil and protects it from contamination and other damage.

AES

24-21-00 PB001

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 7.

Operation/Control and Indicating A.

Fuel-Cooled IDG Oil Cooler The fuel-cooled IDG oil cooler is monitored by the IDG oil-temperature thermocouple to keep the IDG oil temperature in the tolerance.

B.

IDG Oil Temperature Thermocouple (1) The thermocouple is a device which changes a temperature input into an electrical output. It gives an electrical output to the EEC, in relation to the temperature of the oil in the fuel-cooled IDG oil cooler. When the temperature of the oil changes, the electrical output of the thermocouple changes. The electrical output of the thermocouple changes in relation to the oil temperature input. NOTE :

C.

For the EEC, see 73-20-00

Monitoring of the Oil System Operation (Ref. Fig. 24-21-00-24600-A - IDG System - Generator Drive Control and Indicating) (Ref. Fig. 24-21-00-24700-A - IDG 1 Oil Low Pressure - Upper and Lower ECAM Display Units) An oil temperature sensor monitors the oil inlet temperature and an other one, the oil outlet temperature. The second provides ADVISORY oil temperature and oil overheat detection. A pressure switch operates in the event of a low charge oil pressure. In case of: . abnormally low oil-pressure or, . IDG oil overheat (outlet temperature > or = 185 ˚C), the warnings are provided to the cockpit (FAULT legend on the corresponding IDG pushbutton switch, MASTER CAUT light, single chime and messages on the ECAM upper display unit and ECAM lower display unit. (Ref. Fig. 24-21-00-24700-A - IDG 1 Oil Low Pressure - Upper and Lower ECAM Display Units) (Ref. Fig. 24-21-00-24800-A - IDG 1 Oil Overheat Advisory - Upper and Lower ECAM Display Units) (Ref. Fig. 24-21-00-24900-A - IDG 1 Oil Overheat - Upper and Lower ECAM Display Units) The oil outlet temperature is displayed on the ELEC page on the lower ECAM display unit. NOTE :

When the oil temperature reaches a predetermined value (147 ˚C) , an advisory mode is available on the lower ECAM display unit.

D. Disconnection (Ref. Fig. 24-21-00-25000-A - IDG 1 Disconnect - Lower ECAM Display Unit) To disconnect a faulty IDG, it is necessary to open the safety guard and push the ELEC/IDG pushbutton switch. When the IDG is disconnected, the white OFF legend of the ELEC/IDG pushbutton switch comes on. The DISC indication is also displayed on the ELEC page on the lower ECAM display unit. NOTE :

AES

The IDG disconnection is irreversible in flight. The IDG cannot be disconnected below the underspeed threshold. The IDG must not operate for more than 50 hours in the disconnected mode. If the IDG operates for more than 50 hours in the disconnected mode, it will be necessary to replace it and send the removed IDG for a shop inspection. This is because there is a risk of damage to the ball bearing assembly on the input shaft.

24-21-00 PB001

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL E.

Reconnection of the IDG A mechanical reset handle is fitted to the IDG. The handle is used to reconnect the drive while the engine is stationary on the ground. NOTE :

F.

AES

The system can only be reconnected on the ground with the related engine shut down.

Oil Filter A clogged filter indication is provided by a local visual differential pressure indicator (DPI). The indicator is installed opposite the drive end of the IDG.

24-21-00 PB001

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A A

B

B

QAD ADAPTER

SCREW

TENSION BOLT N_MM_242100_0_XAM0_01_00

AES

FIGURE 24-21-00-12300-A SHEET 1 IDG Attachment to the Gearbox

24-21-00 PB001

Page 11 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

4000XU

N_MM_242100_0_XCM0_01_00

AES

FIGURE 24-21-00-12400-A SHEET 1 IDG Location in Nacelle

24-21-00 PB001

Page 12 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

QUAD ADAPTER IDG

GEARBOX

FWD

ELECTRICAL CONNECTOR DPI BUTTON 4000XUC (SILVER END, RED ELECTRICAL CYLINDRICAL SIDE) OVERFLOW DRAIN PORT CONNECTOR PUSH TO VENT 4000XUA VALVE PRESSURE FILL PORT SIGHT GLASS

OIL FILTER

CASE DRAIN PLUG

DISCONNECT RESET RING ELECTRICAL CONNECTOR 4000XUB TERMINAL BLOCK

OIL OUT PORT OIL IN PORT

N_MM_242100_0_XGM0_01_00

AES

FIGURE 24-21-00-12500-A SHEET 1 IDG - Interface Accessories

24-21-00 PB001

Page 13 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

4WT1

4WT2

A

PANEL 35VU DC BUS 1

1

BAT 1

FAULT

v

GALLEY FAULT

E L E C

OFF

A U T O

AC BUS 1

OFF

BAT

2

BAT 2

DC BUS 2

FAULT

v

OFF

FAULT ALTN

AC ESS BUS

AC BUS 2

BUS TIE

IDG 1

R

GEN 1

APU GEN

FAULT

FAULT OFF

ON

A U T O

IDG 2 EXT PWR

GEN 2

R

FAULT

AVAIL

FAULT

FAULT

OFF

ON

ON

5XT

E L E C

6XT

N_MM_242100_0_XJM0_01_00

AES

FIGURE 24-21-00-12600-A SHEET 1 ELEC Control Panel - Location

24-21-00 PB001

Page 14 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

B A

ELECTRICAL CONNECTOR

B COOLER

OIL TUBINGS

IDG IDG CABLES

IDG TERMINAL COVER

N_MM_242100_0_XDM0_01_00

AES

FIGURE 24-21-00-12800-A SHEET 1 Fuel-Cooled IDG Oil Cooler and Cables - Location

24-21-00 PB001

Page 15 May 01/12 Revision n˚: 40

VARIABLE SPEED INPUT

AES

FIGURE 24-21-00-19900-A SHEET 1 IDG - Speed Regulation Loop SWASHPLATE CONTROL PISTON

VARIABLE DISPLACEMENT HYDRAULIC PUMP

INPUT STEPUP GEAR

CSD OUTPUT CONTROLLED AT 12000 RPM

OIL PUMP

GOVERNOR

FIXED DISPLACEMENT HYDRAULIC MOTOR

DIFFERENTIAL GEAR

HYDROMECHANICAL CONSTANT SPEED DRIVE

GCU

3 PHASE 1200HZ PMG

VOLTAGE SENSING

3 PHASE 400HZ GENERATOR

FIXED SPEED GENERATOR

115/200V 90KVA OUTPUT

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

SPEED REGULATION LOOP

N_MM_242100_0_XLM0_01_00

24-21-00 PB001

Page 16 May 01/12 Revision n˚: 40

AES

FUEL TO ENGINE

FUEL−COOLED IDG OIL COOLER

OIL OUT PORT

OIL IN PORT

FIGURE 24-21-00-21400-A SHEET 1 IDG Oil System - Schematic

24-21-00 PB001

ROTATING DEAERATOR

DIFERENTIAL PRESSURE INDICATOR (DPI) BUTTON

OIL OUT TEMP BULB

COOLERS BY PASS VALVE

OIL IN TEMP BULB

OIL FILTER

PRESSURE PRESSURE RELIEF FILL PORT VALVE

CHARGE PRESSURE SWITCH

LUBE CIRCUIT

CHARGE PUMP

CHARGE RELIEF VALVE

DPI BUTTON

CASE DRAIN PLUG

OVERFLOW DRAIN PORT

SCAVENGE PUMP

FILTER BY PASS VALVE

INVERSION SCAVENGE PUMP

GOVERNOR

CONTROL CYLINDER

HYDRAULIC TRIM UNITS

DIFFERENTIAL

GENERATOR

VENT VALVE

SIGHT GLASS

IDG

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242100_0_XNM0_01_00

Page 17 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL EXCITER ARMATURE EXCITER FIELD

MAIN GENERATOR FIELD

ROTATING RECTIFIERS MAIN GENERATOR ARMATURE

N

H1 X1 H1 X1 H1 X1

CONNECTOR A ØC ØB

T3 T2

TERMINAL BLOCK

T1 CURRENT TRANSFORMERS (3)

ØA

DISCONNECT SOLENOID

CONNECTOR B INPUT SPEED SENSOR

+ OIL IN TEMPERATURE BULB

− +

OIL OUT TEMPERATURE BULB PMG ARMATURE

CONNECTOR C CHARGE PRESSURE SWITCH 4000XU−IDG N_MM_242100_0_XMM0_01_00

AES

FIGURE 24-21-00-21600-A SHEET 1 IDG - Internal Schematic

24-21-00 PB001

Page 18 May 01/12 Revision n˚: 40

AES

FIGURE 24-21-00-24600-A SHEET 1 IDG System - Generator Drive Control and Indicating

4000XU IDG

OIL OUT TEMP BULB

GENERATOR

DISCONNECT SOLENOID

INPUT SPEED SENSOR

CHARGE PRESSURE SWITCH

OIL SYSTEM

OIL IN TEMP BULB

DRIVE

OIL OUT PORT

OIL IN PORT

FUEL−COOLED IDG OIL COOLER

24-21-00 PB001

IDG 1 FAULT

R

PANEL 35VU

1XU1 GCU−1

LOW SPEED

LOW PRESSURE

OVERHEAT TEMP 185°C

OIL OUTLET TEMP

OIL INLET TEMP

GCUI

EGIU

ECAM

SYSTEM DISPLAY

MASTER CAUT

E/W DISPLAY

SINGLE CHIME

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242100_0_XQM0_01_00

Page 19 May 01/12 Revision n˚: 40

AES

FIGURE 24-21-00-24700-A SHEET 1 IDG 1 Oil Low Pressure - Upper and Lower ECAM Display Units

ACTION ON CLEAR P/BSW ON ECAM CP

ACTION ON IDG1 P/BSW

MANUEL CREW ACTION

− AUTOMATIC TRANSFER OF NETWORK 1 ON ANOTHER POWER SOURCE (GEN 2)

− GEN 1 FAULT

− IDG1 DISCONNECTED

CONFIG. SYSTEM

FAULT

24-21-00 PB001 OFF

FAULT

GEN 1

FAULT

AMBER "FAULT"

R

IDG1

AMBER "FAULT"

R

IDG1

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

ELEC

NORMAL CONFIG.

NORMAL CONFIG.

IDG1 OIL LO PR

ELEC IDG1 OIL LO PR IDG1........................OFF

ECAM UPPER DISPLAY

IDG 1 OIL LOW PRESSURE (CLASS 1 − LEVEL 2)

TO FL 310

APU START UP

TO FL 350

APU GEN UP

STATUS

MAIN GALLEY

GEN 1

INOP SYS:

SEE TWO PAGES FARTHER

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242100_0_XSM0_01_00

Page 20 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

DC BAT

BAT 2 28V 0A

DC 1

DC 2 DC ESS

TR 1 28V 110A

AC 1

GEN 1 62% 11 6 V 400 HZ

ESS TR

EMER GEN

AC ESS

APU GEN

IDG 1 °C110 LOPR

TR 2 28V 82A

AC 2

GEN 2 60% 11 6 V 400 HZ 110°C IDG 2

4WT2 DU−ECAM, LOWER

N_MM_242100_0_XSM0_02_00

AES

FIGURE 24-21-00-24700-A SHEET 2 IDG 1 Oil Low Pressure - Upper and Lower ECAM Display Units

24-21-00 PB001

Page 21 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

STS

SEE FOLLOWING PAGE

NORMAL CONFIG.

ECAM UPPER DISPLAY WARNING MANUAL CREW ACTION

CONFIG. SYSTEM

OVHD SYST PANEL IND.

IDG 1 OIL OVERHEAT ADVISORY

ECAM LOWER DISPLAY

** On A/C ALL

N_MM_242100_0_XYM0_01_00

AES

FIGURE 24-21-00-24800-A SHEET 1 IDG 1 Oil Overheat Advisory - Upper and Lower ECAM Display Units

24-21-00 PB001

Page 22 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

DC BAT

BAT 2 28V 0A

DC 1

DC 2 DC ESS

TR 1 28V 110A

AC 1

GEN 1 62% 11 6 V 400 HZ IDG 1

ESS TR

EMER GEN

AC ESS

APU GEN

°C170

TR 2 28V 82A

AC 2

GEN 2 60% 11 6 V 400 HZ 110°C IDG 2

4WT2 DU−ECAM, LOWER

N_MM_242100_0_XYM0_02_00

AES

FIGURE 24-21-00-24800-A SHEET 2 IDG 1 Oil Overheat Advisory - Upper and Lower ECAM Display Units

24-21-00 PB001

Page 23 May 01/12 Revision n˚: 40

AES

FIGURE 24-21-00-24900-A SHEET 1 IDG 1 Oil Overheat - Upper and Lower ECAM Display Units

ACTION ON CLEAR P/BSW ON ECAM CP

ACTION ON IDG1 P/BSW

MANUEL CREW ACTION

− AUTOMATIC TRANSFER OF NETWORK 1 ON ANOTHER POWER SOURCE (GEN 2)

− GEN 1 FAULT

− IDG1 DISCONNECTED

CONFIG. SYSTEM

FAULT

24-21-00 PB001 OFF

FAULT

GEN 1

FAULT

AMBER "FAULT"

R

IDG1

AMBER "FAULT"

R

IDG1

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

ELEC

NORMAL CONFIG.

IDG1 OIL OVHT

ELEC IDG1 OIL OVHT IDG1......................OFF

ECAM UPPER DISPLAY

IDG 1 OIL OVERHEAT (CLASS 1 − LEVEL 2)

TO FL 350

APU GEN UP

STATUS

MAIN GALLEY

GEN 1

INOP SYS:

SEE TWO PAGES FARTHER

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242100_0_YCM0_01_00

Page 24 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

DC BAT

BAT 2 28V 0A

DC 1

DC 2 DC ESS

TR 1 28V 110A

AC 1

GEN 1 62% 11 6 V 400 HZ

ESS TR

EMER GEN

AC ESS

APU GEN

IDG 1 °C190

TR 2 28V 82A

AC 2

GEN 2 60% 11 6 V 400 HZ 110°C IDG 2

4WT2 DU−ECAM, LOWER

N_MM_242100_0_YCM0_02_00

AES

FIGURE 24-21-00-24900-A SHEET 2 IDG 1 Oil Overheat - Upper and Lower ECAM Display Units

24-21-00 PB001

Page 25 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

DC BAT

BAT 2 28V 0A

DC 1

DC 2 DC ESS

TR 1 28V 110A

AC 1

AC ESS

GEN 1

APU GEN

00%

00V 0 0 HZ

IDG 1 DISC

TR 2 28V 82A

EMER GEN

ESS TR

°C110

AC 2

GEN 2 96% 11 6 V 400 HZ 110°C

IDG 2

DU − ECAM, LOWER

N_MM_242100_0_YGM0_01_00

AES

FIGURE 24-21-00-25000-A SHEET 1 IDG 1 Disconnect - Lower ECAM Display Unit

24-21-00 PB001

Page 26 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) MAINTENANCE PRACTICES ** On A/C ALL Task 24-21-00-600-040-A Preservation/Storage/Return to Service of the IDG 1.

Reason for the Job Preservation of the IDG prevents corrosion and deterioration when the IDG is in storage for a short period (less than two years). The preservation procedure will give maximum protection to the IDG. You must do it in clean and dry conditions.

2.

Job Set-up Information A.

Consumable Materials

REFERENCE Material No: 15-009 B.

DESIGNATION STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 438AL, 447AL, 448AR C.

Referenced Information

REFERENCE 12-13-24-612-011-A 12-13-24-680-010-A

DESIGNATION IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check Draining of the Oil from the IDG

24-21-51-000-010-A

Removal of the Integrated Drive Generator -IDG 1(2)

24-21-51-000-011-A

Removal of the IDG Oil Filter(s)

24-21-51-400-010-A

Installation of the Integrated Drive Generator -IDG 1(2)

24-21-51-400-011-A

Installation of the IDG Oil Filter(s)

71-00-00-710-043-A

Normal Engine Automatic Start Procedure

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

3.

Job Set-up Subtask 24-21-00-010-094-A A.

Open the fan cowl doors (Ref. TASK 71-13-00-010-010-A): (1)

AES

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

24-21-00 PB201

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2) 4.

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Procedure Subtask 24-21-00-620-050-A A.

IDG Preservation (1)

Remove the IDG (Ref. TASK 24-21-51-000-010-A)

(2)

Do an inspection of the external surfaces of the IDG for missing paint. (a)

(3)

If necessary, return the IDG to the overhaul facility to repair the paint work.

Protection of the IDG. (a)

Apply adhesive tape on the input spline, the O-ring, the input seal area and the valves that are on the periphery of the input pad. Do not remove the input flange, gasket or screws.

(b)

Apply STORAGE PRESERVATION (Material No: 15-009) on the input face and the input pad area.

(c)

Remove the adhesive tape.

(4)

Install the IDG (Ref. TASK 24-21-51-400-010-A).

(5)

Replace the IDG filter (Ref. TASK 24-21-51-000-011-A) and (Ref. TASK 24-21-51-400-011-A).

(6)

Fill the IDG with oil (Ref. TASK 12-13-24-612-011-A).

(7)

Start the engine to make sure that oil flows through the IDG and the external circuit (Ref. TASK 71-00-00-710-043-A).

(8)

Open the drains of the input pad seal to drain unwanted fluids (condensation water or remaining engine washing fluids).

(9)

At intervals, do an inspection for external corrosion damage. Do steps 1 to 3 again as necessary. NOTE :

We recommend that you do this inspection: . a minimum of one time each year or . when you do usual engine maintenance and/or inspections. But it is possible to change the frequency of the intervals (use your experience and the location of storage to make the decision).

Subtask 24-21-00-630-050-A B.

5.

Return to Service (1)

Do a visual inspection of all the external surfaces of the IDG for damage.

(2)

Drain the IDG (Ref. TASK 12-13-24-680-010-A).

(3)

Replace the filter (Ref. TASK 24-21-51-000-011-A) and (Ref. TASK 24-21-51-400-011-A).

(4)

Fill the IDG with oil (Ref. TASK 12-13-24-612-011-A).

(5)

Start the engine to make sure that the IDG operates correctly (Ref. TASK 71-00-00-710-043-A).

Close-up Subtask 24-21-00-410-093-A A.

Close Access (1)

AES

Make sure that the work area is clean and clear of tool(s) and other items.

24-21-00 PB201

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

(3)

AES

Close the fan cowl doors (Ref. TASK 71-13-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

(b)

FOR 1000EM2 (ENGINE-2) 438AL 448AR.

Remove the warning notice(s).

24-21-00 PB201

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) SERVICING ** On A/C ALL Task 24-21-00-612-044-A Servicing of the IDG after Oil Chemical Contamination WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. WARNING : WEAR GOGGLES, INSULATED GLOVES AND OTHER PROTECTIVE CLOTHES. HOT OIL CAN BURN YOUR EYES AND SKIN. IF OIL TOUCHES YOUR EYES OR SKIN, GET MEDICAL AID. CAUTION :

DO NOT OPERATE THE IDG: IF IT CONTAINS TOO MUCH OIL IF IT DOES NOT CONTAIN ENOUGH OIL IF YOU DO, YOU CAN CAUSE DAMAGE TO THE IDG.

CAUTION :

USE ONLY NEW CANS OF OIL WHEN YOU FILL THE IDG WITH OIL OR ADD OIL TO THE IDG. THE CONTAMINATION IN OIL THAT STAYS IN OPEN CANS CAN CAUSE FAST DETERIORATION OF THE OIL AND WILL DECREASE THE LIFE OF THE IDG.

CAUTION :

DO NOT USE SOLVENTS THAT CONTAIN CHLORINE TO CLEAN THE EQUIPMENT (PUMP, HOSES, TANK AND FUNNEL) USED TO FILL THE IDG WITH OIL. CHLORINE CONTAMINATION OF THE OIL CAN CAUSE FAST DETERIORATION OF THE OIL AND WILL DECREASE THE LIFE OF THE IDG.

CAUTION :

DO NOT DO THE SERVICING OF A DISCONNECTED IDG. CONTINUED OPERATION OF A DEFECTIVE IDG CAN CAUSE DAMAGE.

1.

Reason for the Job You must do this procedure to clean the IDG and the external lines.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR CONTAINER 10 L(2 1/2 USGAL)

No specific

AR

FILLING EQUIPMENT - TANK OIL, DH13PM TYP

No specific

AR

HOSE - DRAIN

No specific

AR

WARNING NOTICE(S)

No specific

B.

Consumable Materials

REFERENCE Material No: V02-119

AES

Torque wrench: range to between 30.00 and 220.00 LBF.IN (0.34 and 2.60 M.DAN)

DESIGNATION corrosion resistant steel lockwire

24-21-00 PB301

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE Material No: 03-002 C.

DESIGNATION OILS LUBRICATING OIL TURBINE ENGINE SYNT BASE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 438AL, 447AL, 448AR D.

Expendable Parts

FIG.ITEM 2

DESIGNATION

IPC-CSN 24-21-51-81-020

O-ring E.

Referenced Information

REFERENCE 12-13-24-612-011-A 24-21-00-612-047-A

DESIGNATION IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check IDG Oil-Type Change

24-21-51-000-011-A

Removal of the IDG Oil Filter(s)

24-21-51-400-011-A

Installation of the IDG Oil Filter(s)

24-42-00-861-001-A

Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

71-00-00-710-018-A 71-00-00-710-043-A

Discontinued Start, Restart and Shutdown Procedures Normal Engine Automatic Start Procedure

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-00-991-90000-A - Servicing of IDG after Oil Chemical Contamination) 3.

Job Set-up Subtask 24-21-00-861-061-A A.

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

Subtask 24-21-00-941-061-A B.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

AES

Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

24-21-00 PB301

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-00-010-067-A C.

4.

Open the fan cowl doors (Ref. TASK 71-13-00-010-010-A): (1)

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

(2)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Procedure (Ref. Fig. 24-21-00-991-90000-A - Servicing of IDG after Oil Chemical Contamination) Subtask 24-21-00-864-052-A A.

Depressurization of the IDG Case WARNING : POINT THE OVERFLOW DRAIN HOSE INTO A CONTAINER WHEN YOU CONNECT THE HOSE TO THE OVERFLOW DRAIN HALF-COUPLING. THIS WILL PREVENT BURNS FROM THE HOT OIL SPRAY. HOT OIL CAN CAUSE BURNS TO EYES AND SKIN. CAUTION :

DO NOT USE DEVICES OTHER THAN THE APPROVED OVERFLOW DRAIN-HOSE FITTING. HARD METAL OBJECTS SUCH AS SCREWDRIVERS CAN CAUSE DAMAGE TO THE OVERFLOW DRAIN HALF-COUPLING SEAT.

CAUTION :

MAKE SURE YOU CONNECT THE HOSE OF THE OVERFLOW DRAIN HALF- COUPLING CORRECTLY. THIS HOSE LETS THE OIL IN THE IDG DRAIN TO THE CORRECT LEVEL. IF THERE IS TOO MUCH OIL IN THE IDG THE IDG WILL BECOME TOO HOT.

(1)

Put a CONTAINER 10 L(2 1/2 USGAL) (9) below the IDG (7).

(2)

Remove the dust cap (3) from the overflow drain half-coupling (5).

(3)

Put the end of the HOSE - DRAIN (8) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP in the container (9).

(4)

Do this step to depressurize the IDG case: (a)

Connect the overflow drain hose (8) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP to the overflow drain half-coupling (5). NOTE :

Some oil can come out of the overflow drain hose (8) of the FILLING EQUIPMENT TANK OIL, DH13PM TYP when you connect it.

Subtask 24-21-00-680-053-C B.

Draining of the Oil WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU. (1)

Cut and remove the lockwire from the case drain plug (1). NOTE :

AES

Approximately 3.965 l (1.0474 USgal) of oil will flow into the container.

(2)

Remove the case drain plug (1).

(3)

Remove the O-ring (2) and discard it.

(4)

Drain the oil.

24-21-00 PB301

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-00-920-054-A C.

Replace the IDG oil filter (Ref. TASK 24-21-51-000-011-A) and (Ref. TASK 24-21-51-400-011-A).

Subtask 24-21-00-640-054-A D.

Lubricate the new (IPC-CSN 24-21-51-81) O-ring (2) with OILS (Material No: 03-002) .

Subtask 24-21-00-420-058-A E.

Installation of the Case Drain Plug (1)

Install the new O-ring (2) on the case drain plug (1).

(2)

Install the case drain plug (1).

(3)

TORQUE the case drain plug (1) to between 55 and 75 LBF.IN (0.62 and 0.85 M.DAN).

(4)

Safety the case drain plug (1) with corrosion resistant steel lockwire (Material No: V02-119) .

Subtask 24-21-00-612-054-A CAUTION :

F.

USE ONLY APPROVED TYPES/BRANDS OF LUBRICANTS. DO NOT MIX TYPES//BRANDS OF LUBRICANTS.

Filling of the IDG with Oil NOTE :

In case of OIL type/brand change, refer to (Ref. TASK 24-21-00-612-047-A).

NOTE :

In rain, fog or wet conditions, be careful to prevent water contamination of the IDG oil during the filling procedure.

NOTE :

The AMM 20-34-00 gives a list of oil brand names approved for the IDG.

(1)

Remove the dust cap (4) from the pressure fill half-coupling (6).

(2)

Connect the pressure fill hose (10) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP to the pressure fill half-coupling (6).

(3)

Fill the IDG with filtered OILS (Material No: 03-002) at a maximum pressure of 35 psi (2.41 bar).

(4)

Stop the filling procedure when the quantity of oil collected from the overflow drain hose (8) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP is 0.95 l (0.25 USgal) minimum.

Subtask 24-21-00-020-076-A G.

Removal of the Hoses (1)

Disconnect the pressure fill hose (10) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP from the pressure fill half-coupling (6).

(2)

Install the dust cap (4) on the pressure fill half-coupling (6).

(3)

When only drops of oil come out of the overflow drain hose (8) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP , disconnect the hose (8).

(4)

Install the dust cap (3) on the overflow drain half-coupling (5).

Subtask 24-21-00-710-057-A H.

Operation of the Engine (1)

Start the related engine (Ref. TASK 71-00-00-710-043-A) until the oil temperature of the IDG is 175 deg.F (80 deg.C). NOTE :

AES

You can read the oil temperature on the ELEC page of the lower ECAM DU.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Stop the engine (Ref. TASK 71-00-00-710-018-A).

Subtask 24-21-00-680-054-A J.

Do the steps 4.A thru 4.E. again.

Subtask 24-21-00-612-062-A K. 5.

Fill the IDG with oil or add oil to the IDG after a level check (Ref. TASK 12-13-24-612-011-A).

Close-up Subtask 24-21-00-410-067-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowl doors (Ref. TASK 71-13-00-410-010-A):

(3)

(a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

(b)

FOR 1000EM2 (ENGINE-2) 438AL 448AR.

Remove the warning notice(s).

Subtask 24-21-00-862-060-A B.

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

24-21-00 PB301

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

FWD ENGINE GEARBOX

B

A

B

ENGINE GEARBOX

7

6 5 2 3 10 PRESSURE FILL HOSE

1

4 9 CONTAINER

8 OVERFLOW DRAIN HOSE N_MM_242100_3_XAM0_01_00

AES

FIGURE 24-21-00-991-90000-A SHEET 1 Servicing of IDG after Oil Chemical Contamination

24-21-00 PB301

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-00-612-044-A-01 Servicing of the IDG after Oil Chemical Contamination and Extension of the Oil-Filter Differential-Pressure Indicator (DPI) WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. WARNING : WEAR GOGGLES, INSULATED GLOVES AND OTHER PROTECTIVE CLOTHES. HOT OIL CAN BURN YOUR EYES AND SKIN. IF OIL TOUCHES YOUR EYES OR SKIN, GET MEDICAL AID. CAUTION :

DO NOT OPERATE THE IDG: IF IT CONTAINS TOO MUCH OIL IF IT DOES NOT CONTAIN ENOUGH OIL IF YOU DO, YOU CAN CAUSE DAMAGE TO THE IDG.

CAUTION :

USE ONLY NEW CANS OF OIL WHEN YOU FILL THE IDG WITH OIL OR ADD OIL TO THE IDG. THE CONTAMINATION IN OIL THAT STAYS IN OPEN CANS CAN CAUSE FAST DETERIORATION OF THE OIL AND WILL DECREASE THE LIFE OF THE IDG.

CAUTION :

DO NOT USE SOLVENTS THAT CONTAIN CHLORINE TO CLEAN THE EQUIPMENT (PUMP, HOSES, TANK AND FUNNEL) USED TO FILL THE IDG WITH OIL. CHLORINE CONTAMINATION OF THE OIL CAN CAUSE FAST DETERIORATION OF THE OIL AND WILL DECREASE THE LIFE OF THE IDG.

1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR CONTAINER 10 L(2 1/2 USGAL)

No specific

AR

FILLING EQUIPMENT - TANK OIL, DH13PM TYP

No specific

AR

WARNING NOTICE(S)

No specific

B.

Torque wrench: range to between 180.00 and 1800.00 LBF.IN (2.00 and 20.00 M.DAN)

Consumable Materials

REFERENCE Material No: 03-002 C.

DESIGNATION OILS LUBRICATING OIL TURBINE ENGINE SYNT BASE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 438AL, 447AL, 448AR

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL D.

Referenced Information

REFERENCE 12-13-24-612-011-A 24-21-42-000-010-B 24-21-42-400-010-B 24-21-51-000-010-A

DESIGNATION IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check Removal of the Fuel-Cooled IDG Oil-Cooler Installation of the Fuel-Cooled IDG Oil-Cooler Removal of the Integrated Drive Generator -IDG 1(2)

24-21-51-400-010-A

Installation of the Integrated Drive Generator -IDG 1(2)

24-42-00-861-001-A

Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-00-991-90900-A - Servicing of the IDG after Oil Contamination and with the DPI Out) 3.

Job Set-up Subtask 24-21-00-861-057-A A.

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

Subtask 24-21-00-941-062-A B.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-21-00-010-068-A C.

4.

Open the fan cowl doors (Ref. TASK 71-13-00-010-010-A): (1)

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

(2)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Procedure (Ref. Fig. 24-21-00-991-90900-A - Servicing of the IDG after Oil Contamination and with the DPI Out) Subtask 24-21-00-020-060-A A.

Removal of the IDG and IDG Oil-Cooler Assembly (1)

Remove the IDG (Ref. TASK 24-21-51-000-010-A).

(2)

If the cause of contamination is a fuel leak of the IDG oil-cooler assembly: (a)

AES

Remove the IDG oil-cooler assembly (Ref. TASK 24-21-42-000-010-B).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-00-420-064-A B.

Installation of a New IDG and IDG Oil-Cooler Assembly (1)

Install a new IDG (Ref. TASK 24-21-51-400-010-A).

(2)

Do not connect the oil-in tube (2) to the oil-in port (3) at this time.

(3)

If the cause of contamination is a fuel leak of the IDG oil-cooler assembly: (a)

Install a new IDG oil-cooler assembly (Ref. TASK 24-21-42-400-010-B).

Subtask 24-21-00-612-059-A CAUTION :

C.

USE ONLY APPROVED TYPES/BRANDS OF LUBRICANTS. DO NOT MIX TYPES//BRANDS OF LUBRICANTS.

Flushing of the External Lines NOTE :

Approximately 1.5 USgal (5.7 l) of oil will flow into the container.

(1)

Put the end of the IDG oil-in tube (2) in a CONTAINER 10 L(2 1/2 USGAL).

(2)

Remove the dust cap (4) from the pressure fill half-coupling (1).

(3)

Connect the pressure fill hose (5) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP to the pressure fill half-coupling (1).

(4)

Use a pump to fill the IDG with filtered OILS (Material No: 03-002) until: . the color of the oil that flows from the IDG oil-in line (2) is the same as the color of the oil that you put into the IDG, . or until you collect 3.8 l (1.0038 USgal) to 5.7 l (1.5058 USgal) of oil from the oil-in line (2).

Subtask 24-21-00-420-060-A D.

Connection of the IDG Oil-in line CAUTION :

(1)

USE TWO WRENCHES TO HOLD THE FITTINGS WHEN YOU TORQUE THE OIL-IN AND OIL-OUT LINES. IF NOT YOU CAN TRANSMIT TOO MUCH TORQUE TO THE IDG FITTINGS AND CAUSE DAMAGE TO THE IDG BOSSES.

Connect the IDG oil-in line (2) to the oil-in port (3). Use two wrenches, one to hold and the other to TORQUE the IDG oil-in line (2) to between 844 and 945 LBF.IN (9.54 and 10.68 M.DAN).

Subtask 24-21-00-612-060-A E. 5.

Fill the IDG with oil or add oil into IDG after a level check (Ref. TASK 12-13-24-612-011-A).

Close-up Subtask 24-21-00-410-068-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowl doors (Ref. TASK 71-13-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

(b)

FOR 1000EM2 (ENGINE-2) 438AL 448AR.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the warning notice(s).

Subtask 24-21-00-862-057-A B.

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

24-21-00 PB301

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A ENGINE GEARBOX

A

3

DIFFERENTIAL PRESSURE INDICATOR(DPI)

1 5 PRESSURE FILL HOSE

B 4

B IDG OIL COOLER

2

CONTAINER N_MM_242100_3_XCM0_01_00

AES

FIGURE 24-21-00-991-90900-A SHEET 1 Servicing of the IDG after Oil Contamination and with the DPI Out

24-21-00 PB301

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-00-920-041-A Drain IDG Oil System, Discard Filter Element(s) and Replenish WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. WARNING : WEAR GOGGLES, INSULATED GLOVES AND OTHER PROTECTIVE CLOTHES. HOT OIL CAN BURN YOUR EYES AND SKIN. IF OIL TOUCHES YOUR EYES OR SKIN, GET MEDICAL AID. CAUTION :

USE ONLY NEW CANS OF OIL WHEN YOU FILL THE IDG WITH OIL OR ADD OIL TO THE IDG. THE CONTAMINATION IN OIL THAT STAYS IN OPEN CANS CAN CAUSE FAST DETERIORATION OF THE OIL AND WILL DECREASE THE LIFE OF THE IDG.

CAUTION :

DO NOT USE SOLVENTS THAT CONTAIN CHLORINE TO CLEAN THE EQUIPMENT (PUMP, HOSES, TANK AND FUNNEL) USED TO FILL THE IDG WITH OIL. CHLORINE CONTAMINATION OF THE OIL CAN CAUSE FAST DETERIORATION OF THE OIL AND WILL DECREASE THE LIFE OF THE IDG.

CAUTION :

DO NOT OPERATE THE IDG: IF IT CONTAINS TOO MUCH OIL IF IT DOES NOT CONTAIN ENOUGH OIL IF YOU DO, YOU CAN CAUSE DAMAGE TO THE IDG.

CAUTION :

DO NOT DO THE SERVICING OF A DISCONNECTED IDG. CONTINUED OPERATION OF A DEFECTIVE IDG CAN CAUSE DAMAGE.

1.

Reason for the Job (Ref. MPD 24-21-00-08-) - REMOVE AND DISCARD SCAVENGE FILTER ELEMENT - DRAIN AND REPLENISH OIL SYSTEM (Ref. MPD 24-20-00-22-) - REMOVE AND DISCARD SCAVENGE AND CHARGE FILTER ELEMENTS, - DRAIN AND REPLENISH OIL SYSTEM To drain the IDG, replace the IDG oil filter element(s) and fill the IDG with oil.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR CONTAINER 10 L(2 1/2 USGAL)

No specific

AR

FILLING EQUIPMENT - TANK OIL, DH13PM TYP

No specific

AR

WARNING NOTICE(S)

No specific

AES

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

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Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL B.

Consumable Materials

REFERENCE Material No: V02-119 Material No: 03-002 C.

DESIGNATION corrosion resistant steel lockwire OILS LUBRICATING OIL TURBINE ENGINE SYNT BASE

Work Zones and Access Panels ZONE/ACCESS

438 448 FOR FIN 1000EM1(ENGINE-1)

ZONE DESCRIPTION FAN COWL FAN COWL

437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR D.

Expendable Parts

FIG.ITEM

DESIGNATION

IPC-CSN 24-21-51-81-020

2

O-ring

8

O-ring

24-21-51-81-160

9 10

filter element O-ring

24-21-51-81-170 24-21-51-81-180

E.

Referenced Information

REFERENCE 12-32-24-281-001-A

DESIGNATION Sampling of the IDG Oil for Analysis

24-21-00-210-045-A

Inspection of the Filter Element(s)

24-21-00-612-044-A

Servicing of the IDG after Oil Chemical Contamination

24-21-00-612-044-A-01

Servicing of the IDG after Oil Chemical Contamination and Extension of the OilFilter Differential-Pressure Indicator (DPI)

24-42-00-861-001-A

Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

71-00-00-710-043-A

Normal Engine Automatic Start Procedure

71-00-00-710-045-A

Test No.1 : Dry Motor Leak Check

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-00-991-91000-B - IDG Oil Filter) 3.

Job Set-up Subtask 24-21-00-861-054-A A.

AES

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

24-21-00 PB301

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-00-941-052-A B.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-21-00-010-059-A C.

4.

Open the fan cowl doors (Ref. TASK 71-13-00-010-010-A): (1)

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

(2)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Procedure (Ref. Fig. 24-21-00-991-91000-B - IDG Oil Filter) Subtask 24-21-00-864-057-A A.

Depressurization of the IDG Case WARNING : POINT THE OVERFLOW DRAIN HOSE INTO A CONTAINER WHEN YOU CONNECT THE HOSE TO THE OVERFLOW DRAIN HALF-COUPLING. THIS WILL PREVENT BURNS FROM THE HOT OIL SPRAY. HOT OIL CAN CAUSE BURNS TO EYES AND SKIN. CAUTION :

DO NOT USE DEVICES OTHER THAN THE APPROVED OVERFLOW DRAIN-HOSE FITTING. HARD METAL OBJECTS SUCH AS SCREWDRIVERS CAN CAUSE DAMAGE TO THE OVERFLOW DRAIN HALF-COUPLING SEAT.

(1)

Put a CONTAINER 10 L(2 1/2 USGAL) (14) below the IDG.

(2)

Remove the dust cap (3) from the overflow drain half-coupling (5).

(3)

Put the end of the overflow drain hose (13) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP in the container (14).

(4)

Do this step to depressurize the IDG case: (a)

Connect the overflow drain hose (13) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP to the overflow drain half-coupling (5). NOTE :

AES

Some oil can come out of the overflow drain hose (13) of the FILLING EQUIPMENT TANK OIL, DH13PM TYP when you connect it.

24-21-00 PB301

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-00-680-056-C B.

Draining of the Oil WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU. (1)

Cut and remove the lockwire from the case drain plug (1). NOTE :

Approximately 3.965 l (1.0474 USgal) of oil will flow into the container.

(2)

Remove the case drain plug (1).

(3)

Remove the O-ring (2) and discard it.

(4)

Drain the oil. NOTE :

If the drained oil has a fuel odor, do the servicing of the IDG after oil chemical contamination (Ref. TASK 24-21-00-612-044-A) or (Ref. TASK 24-21-00-612-044-A-01). If you think that the condition of the drained oil is not correct, do a sampling of the IDG oil for analysis (Ref. TASK 12-32-24-281-001-A).

Subtask 24-21-00-020-052-A C.

Removal of the IDG Oil Filter WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU. (1)

Cut and remove the lockwire from the filter cover (7). NOTE :

Put a container 5.7 l (1.5 USgal) below the filter cavity.

(2)

Remove the filter cover (7).

(3)

Remove and discard the O-ring (8) from the filter cover (7).

(4)

Remove the filter element (9).

(5)

Remove and discard the O-ring (10) from the filter element (9).

(6)

Install a blanking plug on the filter cavity port.

Subtask 24-21-00-210-054-A D.

Inspection of the IDG Oil Filter(s) (1)

Do the inspection of the filter element(s) (Ref. TASK 24-21-00-210-045-A). NOTE :

We recommend that you do a visual inspection of the IDG oil filter(s) for possible contamination, debris.

Subtask 24-21-00-640-052-A E.

AES

Lubrication of the Expendable Parts (1)

Lubricate the new O-ring (10) with OILS (Material No: 03-002) .

(2)

Lubricate the new O-ring (8) with OILS (Material No: 03-002) .

(3)

Lubricate the new O-ring (2) with OILS (Material No: 03-002) .

24-21-00 PB301

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-00-420-067-A F.

Installation of the Case Drain Plug WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU. (1)

Install the new (IPC-CSN 24-21-51-81) O-ring (2) on the case drain plug (1).

(2)

Install the case drain plug (1).

(3)

TORQUE the case drain plug (1) to between 0.62 and 0.85 M.DAN (54.87 and 75.22 LBF.IN).

(4)

Safety the case drain plug (1) with corrosion resistant steel lockwire (Material No: V02-119) .

Subtask 24-21-00-420-051-A G.

Installation of the IDG Oil Filter WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU. CAUTION :

MAKE SURE THE COMPONENTS ARE SEATED IN THE IDG SCAVENGE FILTER CAVITY BEFORE YOU INSTALL THE FILTER COVER. DO NOT TIGHTEN THE FILTER COVER SCREWS TO FORCE THE FILTER COMPONENTS INTO THE HOUSING.

(1)

Install the new (IPC-CSN 24-21-51-81) O-ring (10) on the filter element (9).

(2)

Install the new (IPC-CSN 24-21-51-81) O-ring (8) on the filter cover (7).

(3)

Remove the blanking plug from the filter cavity port.

(4)

Put the new (IPC-CSN 24-21-51-81) filter element (9) in the filter cavity.

(5)

Install the filter cover (7).

(6)

TORQUE the filter cover (7) to between 1.76 and 2.03 M.DAN (12.98 and 14.97 LBF.FT).

(7)

Safety the filter cover (7) with corrosion resistant steel lockwire (Material No: V02-119) .

Subtask 24-21-00-612-051-A CAUTION :

H.

USE ONLY APPROVED TYPES/BRANDS OF LUBRICANTS. DO NOT MIX TYPES//BRANDS OF LUBRICANTS.

Filling of the IDG with Oil NOTE :

In rain, fog or wet conditions, be careful to prevent water contamination of the IDG oil during the filling procedure.

(1)

Remove the dust cap (4) from the pressure fill half-coupling (6).

(2)

Connect the pressure fill hose (11) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP to the pressure fill half-coupling (6).

(3)

Fill the IDG with filtered OILS (Material No: 03-002) at a maximum pressure of 35 psi (2.41 bar). NOTE :

(4)

AES

The AMM 20-34-00 gives a list of oil brand names approved for the IDG.

Stop the filling procedure when the quantity of oil collected from the overflow drain hose (13) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP is 0.95 l (0.25 USgal) minimum.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-00-020-074-A J.

Removal of the Hoses (1)

Disconnect the pressure fill hose (11) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP from the pressure fill half-coupling (6).

(2)

Install the dust cap (4) on the pressure fill half-coupling (6).

(3)

When only drops of oil come out of the overflow drain hose (13) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP , disconnect the hose (13).

(4)

Install the dust cap (3) on the overflow drain half-coupling (5).

Subtask 24-21-00-710-063-A K.

If you replaced a part of the oil system (filter, external system component, drain plug), do dry motoring for a leak check before inspection (Ref. TASK 71-00-00-710-045-A).

Subtask 24-21-00-210-055-A L.

Inspection of the Oil Level NOTE :

(1)

To fill the external oil system to its maximum level before the oil level check, it is necessary to: . Dry-motor the engine (Ref. TASK 71-00-00-710-045-A) for two minutes, or to . Operate the engine at minimum idle (Ref. TASK 71-00-00-710-043-A).

Inspection of the oil level after dry motoring. CAUTION :

(2)

IF YOU DRY-MOTOR THE ENGINE, MAKE SURE THAT THE OIL LEVEL IS STABLE BEFORE YOU DO THE INSPECTION. IN AMBIENT AIR TEMPERATURES OF LESS THAN 20˚C, THE OIL LEVEL WILL BECOME STABLE ONLY AFTER 30 MINUTES. THUS THE LEVEL INDICATIONS ON THE SIGHTGLASS WILL NOT BE CORRECT BEFORE THE END OF THIS PERIOD. IF YOU ADD OIL WHEN IT IS NOT NECESSARY, THERE IS A RISK THAT YOU WILL CAUSE FAILURE OF THE IDG.

(a)

Let the oil in the IDG become stable.

(b)

Look at the oil level . if the oil level is . if the oil level is . if the oil level is

Inspection of the oil level after an engine start (alternative procedure). (a)

Let the oil in the IDG become stable for 5 minutes.

(b)

Look at the oil level sight-glass of the IDG: . if the oil level is in the green or yellow band, oil servicing is not necessary, NOTE :

. . 5.

sight-glass of the IDG: at or near the top of the green band, oil servicing is not necessary, below the green band, do the steps 4.A., 4.H. and 4.J. again, above the green band, do the steps 4.A. and 4.J. again.

If the oil level is below the middle of the green band, we recommend that you do the top up.

if the oil level is below the green band, do the steps 4.A., 4.H. and 4.J. again, if the oil level above the yellow band, do the steps 4.A. and 4.J. again.

Close-up Subtask 24-21-00-410-059-A A.

Close Access (1)

AES

Make sure that the work area is clean and clear of tool(s) and other items.

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Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

(3)

Close the fan cowl doors (Ref. TASK 71-13-00-410-010-A) (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Remove the warning notice(s).

Subtask 24-21-00-862-054-A B.

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

24-21-00 PB301

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A ENGINE GEARBOX

B

12 OIL LEVEL SIGHT GLASS 6 5

2 10

9

3 4

1 PRESSURE FILL HOSE 11

8

13 OVERFLOW DRAIN HOSE

7

14 CONTAINER

N_MM_242100_3_XGN0_01_00

AES

FIGURE 24-21-00-991-91000-B SHEET 1 IDG Oil Filter

24-21-00 PB301

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL CORRECTLY FILLED IDG

B

B

AFTER SERVICING OR ENGINE SHUTDOWN (COLD OIL/IDG)

AFTER ENGINE SHUTDOWN (HOT OIL/IDG)

OVER FULL

OVER FULL

RED YELLOW

RED YELLOW

GREEN

GREEN

RED

RED

ADD OIL

ADD OIL

V2500

V2500

OIL LEVEL MUST BE AT OR NEAR THE LINE BETWEEN THE YELLOW BAND AND THE GREEN BAND

OIL LEVEL CAN BE IN THE GREEN BAND OR THE YELLOW BAND

INCORRECTLY FILLED IDG

B AFTER SERVICING OR ENGINE SHUTDOWN (COLD OIL/IDG) OVER FULL

AT ALL TIMES (HOT OR COLD OIL/IDG) OVER FULL

OVER FULL

RED YELLOW

RED YELLOW

RED YELLOW

GREEN

GREEN

GREEN

RED

RED

RED

ADD OIL

V2500

ADD OIL

V2500

THE OIL LEVEL MUST NOT BE IN THE YELLOW BAND BUT IT CAN BE IMMEDIATELY ABOVE THE LOWER LIMIT OF THE YELLOW BAND BECAUSE OF THE AIRCRAFT RAMP ANGLE ACTION:

B

DO THE IDG SERVICING TO GET THE CORRECT IDG OIL LEVEL.

ADD OIL

V2500

THE OIL LEVEL MUST NOT BE IN THE RED BAND

ACTION:

PERFORM IDG OIL SERVICING TO GET THE CORRECT IDG OIL LEVEL.

N_MM_242100_3_XGN0_02_00

AES

FIGURE 24-21-00-991-91000-B SHEET 2 IDG Oil Filter

24-21-00 PB301

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-00-612-047-A IDG Oil-Type Change WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. WARNING : WEAR GOGGLES, INSULATED GLOVES AND OTHER PROTECTIVE CLOTHES. HOT OIL CAN BURN YOUR EYES AND SKIN. IF OIL TOUCHES YOUR EYES OR SKIN, GET MEDICAL AID. CAUTION :

DO NOT OPERATE THE IDG: IF IT CONTAINS TOO MUCH OIL IF IT DOES NOT CONTAIN ENOUGH OIL IF YOU DO, YOU CAN CAUSE DAMAGE TO THE IDG.

CAUTION :

USE ONLY NEW CANS OF OIL WHEN YOU FILL THE IDG WITH OIL OR ADD OIL TO THE IDG. THE CONTAMINATION IN OIL THAT STAYS IN OPEN CANS CAN CAUSE FAST DETERIORATION OF THE OIL AND WILL DECREASE THE LIFE OF THE IDG.

CAUTION :

DO NOT USE SOLVENTS THAT CONTAIN CHLORINE TO CLEAN THE EQUIPMENT (PUMP, HOSES, TANK AND FUNNEL) USED TO FILL THE IDG WITH OIL. CHLORINE CONTAMINATION OF THE OIL CAN CAUSE FAST DETERIORATION OF THE OIL AND WILL DECREASE THE LIFE OF THE IDG.

CAUTION :

DO NOT DO THE SERVICING OF A DISCONNECTED IDG. CONTINUED OPERATION OF A DEFECTIVE IDG CAN CAUSE DAMAGE.

1.

Reason for the Job You must do this procedure to flush the IDG and the external lines with a new type of oil.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR CONTAINER 10 L(2 1/2 USGAL)

No specific

AR

FILLING EQUIPMENT - TANK OIL, DH13PM TYP

No specific

AR

WARNING NOTICE(S)

No specific

B.

Torque wrench: range to between 30.00 and 220.00 LBF.IN (0.34 and 2.60 M.DAN)

Consumable Materials

REFERENCE Material No: V02-119 Material No: 03-002 C.

DESIGNATION corrosion resistant steel lockwire OILS LUBRICATING OIL TURBINE ENGINE SYNT BASE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1)

AES

24-21-00 PB301

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ZONE/ACCESS

ZONE DESCRIPTION

437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR D.

Expendable Parts

FIG.ITEM 2

DESIGNATION

IPC-CSN 24-21-51-81-020

O-ring E.

Referenced Information

REFERENCE 12-13-24-612-011-A 24-21-51-000-011-A

DESIGNATION IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check Removal of the IDG Oil Filter(s)

24-21-51-400-011-A

Installation of the IDG Oil Filter(s)

24-42-00-861-001-A

Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

71-00-00-710-043-A

Normal Engine Automatic Start Procedure

71-00-00-710-045-A

Test No.1 : Dry Motor Leak Check

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-00-991-91100-A - Oil Type Change - IDG) 3.

Job Set-up Subtask 24-21-00-861-064-A A.

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

Subtask 24-21-00-941-072-A B.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-21-00-010-082-A C.

AES

Open the fan cowl doors (Ref. TASK 71-13-00-010-010-A): (1)

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

(2)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-21-00-991-91100-A - Oil Type Change - IDG) Subtask 24-21-00-864-060-A A.

Depressurization of the IDG Case WARNING : POINT THE OVERFLOW DRAIN HOSE INTO A CONTAINER WHEN YOU CONNECT THE HOSE TO THE OVERFLOW DRAIN HALF-COUPLING. THIS WILL PREVENT BURNS FROM THE HOT OIL SPRAY. HOT OIL CAN CAUSE BURNS TO EYES AND SKIN. CAUTION :

DO NOT USE DEVICES OTHER THAN THE APPROVED OVERFLOW DRAIN-HOSE FITTING. HARD METAL OBJECTS SUCH AS SCREWDRIVERS CAN CAUSE DAMAGE TO THE OVERFLOW DRAIN HALF-COUPLING SEAT.

CAUTION :

MAKE SURE YOU CONNECT THE HOSE OF THE OVERFLOW DRAIN HALF- COUPLING CORRECTLY. THIS HOSE LETS THE OIL IN THE IDG DRAIN TO THE CORRECT LEVEL. IF THERE IS TOO MUCH OIL IN THE IDG THE IDG WILL BECOME TOO HOT.

(1)

Put a CONTAINER 10 L(2 1/2 USGAL) (9) below the IDG (7).

(2)

Remove the dust cap (3) from the overflow drain half-coupling (5).

(3)

Put the end of the overflow drain hose (8) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP in the container (9).

(4)

Do this step to depressurize the IDG case: (a)

Connect the overflow drain hose (8) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP to the overflow drain half-coupling (5). NOTE :

Some oil can come out of the overflow drain hose (8) of the FILLING EQUIPMENT TANK OIL, DH13PM TYP when you connect it.

Subtask 24-21-00-680-063-C B.

Draining of the Oil WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU. (1)

Cut and remove the lockwire from the case drain plug (1). NOTE :

Approximately 3.925 l (1.0369 USgal) of oil will flow into the container.

(2)

Remove the case drain plug (1).

(3)

Remove the O-ring (2) and discard it.

(4)

Drain the oil.

Subtask 24-21-00-920-057-A C.

Replace the IDG oil filter(s) (Ref. TASK 24-21-51-000-011-A) and (Ref. TASK 24-21-51-400-011-A).

Subtask 24-21-00-612-081-A D.

Flushing of the IDG NOTE :

AES

Approximately 3.8 l (1 USgal) of oil will flow into the container.

24-21-00 PB301

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (1)

Remove the dust cap (4) from the pressure fill half-coupling (6).

(2)

Connect the pressure fill hose (10) of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP to the pressure fill half-coupling (6).

(3)

Use a pump to fill the IDG with filtered OILS (Material No: 03-002) until: . the color of the oil that flows from the case drain is the same as the color of the oil that you put into the IDG, . or until you collect 3.8 l (1 USgal) of oil from the case drain.

Subtask 24-21-00-640-059-A E.

Lubricate the new (IPC-CSN 24-21-51-81) O-ring (2) with OILS (Material No: 03-002) .

Subtask 24-21-00-420-078-A F.

Installation of the Case Drain Plug (1)

Install the new O-ring (2) on the case drain plug (1).

(2)

Install the case drain plug (1).

(3)

TORQUE the case drain plug (1) to between 55 and 75 LBF.IN (0.62 and 0.85 M.DAN).

(4)

Safety the case drain plug (1) with corrosion resistant steel lockwire (Material No: V02-119) .

Subtask 24-21-00-612-082-A G.

Fill the IDG with oil or add oil to the IDG after a level check (Ref. TASK 12-13-24-612-011-A).

Subtask 24-21-00-720-056-A H.

Do dry motoring (Ref. TASK 71-00-00-710-045-A) and make sure that there are no oil leaks at the cover of the IDG oil filter. NOTE :

We recommend that you do a visual inspection to make sure that there are no oil leaks at the cover of the IDG oil filter. Do this inspection at the subsequent engine start, at minimum idle (Ref. TASK 71-00-00-710-043-A). At this time, the oil pressure in the lubrication system and the cooling system of the IDG is higher and the oil circulation time is longer.

Subtask 24-21-00-210-076-A J.

Inspection of the Oil Level after Dry Motoring (1)

Let the oil in the IDG become stable for 5 minutes.

(2)

Look at the oil level sight-glass of the IDG: . if the oil level is in the green band, oil servicing is not necessary, . if the oil level is below the green band or above the green band, fill the IDG with oil or add oil to the IDG after a level check (Ref. TASK 12-13-24-612-011-A).

Subtask 24-21-00-210-077-A K.

AES

Inspection of the Oil Level after an Engine Start (Alternative Procedure) (1)

Let the oil at or near the top of the IDG become stable for 5 minutes.

(2)

Look at the oil level sight-glass of the IDG: . if the oil level is in the green or yellow band, oil servicing is not necessary, . if the oil level is below the green band or above the yellow band, fill the IDG with oil or add oil after a level check (Ref. TASK 12-13-24-612-011-A).

24-21-00 PB301

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-21-00-410-081-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowl doors (Ref. TASK 71-13-00-410-010-A).

(3)

(a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Remove the warning notice(s).

Subtask 24-21-00-862-063-A B.

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

24-21-00 PB301

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

FWD ENGINE GEARBOX

B

A

B

ENGINE GEARBOX

7

6 5 2 3 10 PRESSURE FILL HOSE

1

4 9 CONTAINER

8 OVERFLOW DRAIN HOSE N_MM_242100_3_XBM0_01_00

AES

FIGURE 24-21-00-991-91100-A SHEET 1 Oil Type Change - IDG

24-21-00 PB301

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) ADJUSTMENT/TEST ** On A/C ALL Task 24-21-00-710-042-A Operational Test of the IDG Disconnect and Reconnect (Reset) Function - Engine Static WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. 1.

Reason for the Job (Ref. MPD 24-21-00-09-) OPERATIONAL CHECK OF INTEGRATED DRIVE GENERATOR (IDG) DISCONNECT AND RECONNECT FUNCTION. To do a check of the IDG disconnect system and reset system.

2.

NOTE :

This procedure is specially applicable for an engine replacement. It is also applicable for an IDG replacement.

NOTE :

There is an alternative method for this procedure. For the other method, refer to (Ref. TASK 24-21-00-720-042).

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

438 448 FOR FIN 1000EM1(ENGINE-1)

ZONE DESCRIPTION FAN COWL FAN COWL

438AR FOR FIN 1000EM2(ENGINE-2) 448AR B.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

AES

24-21-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-21-00-861-051-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A)

(3)

On the ECAM control panel, push the ELEC key to get the ELEC page.

Subtask 24-21-00-010-051-A B.

Open the right fan-cowl door (Ref. TASK 71-13-00-010-010-A): (1)

FOR 1000EM1 (ENGINE-1) 438AR,

(2)

FOR 1000EM2 (ENGINE-2) 448AR.

Subtask 24-21-00-865-054-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

122VU

DESIGNATION ELEC/IDG2/DISC

FIN

LOCATION

2XT

T25

122VU

ELEC/IDG1/DISC

1XT

T24

Subtask 24-21-00-865-055-A D.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

DESIGNATION

FIN

LOCATION

122VU

ELEC/GCU/2

2XU2

T27

122VU

ELEC/GCU/1

2XU1

T26

4.

Procedure CAUTION :

ENGAGE THE IDG DISCONNECT MECHANISM WITH THE DISCONNECT RESET RING BEFORE YOU START THE ENGINE. IF NOT YOU WILL CAUSE DAMAGE TO THE DOG TEETH, AT ENGINE START.

CAUTION :

DO NOT PUSH THE IDG DISCONNECT PUSHBUTTON SWITCH FOR MORE THAN 3 SECONDS. THERE MUST BE AT LEAST 60 SECONDS BETWEEN TWO OPERATIONS OF THE SWITCH. THIS IS TO PREVENT DAMAGE TO THE DISCONNECT SOLENOID WHICH WILL BECOME TOO HOT.

Subtask 24-21-00-710-051-A A.

Operational Test of the IDG Disconnect and Reconnect (Reset) Function NOTE :

AES

This test is for the system 1. For the other system(s), use the indications between the parentheses.

24-21-00 PB501

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 1.On the ELEC control panel 35VU: . Lift the guard and push the IDG1(2) pushbutton switch. 2.On the IDG 1(2): . Slowly pull out the disconnect reset ring to the full limit of travel. Monitor the hand force that is necessary: this force must not to be too high. The disconnect mechanism must move freely without hard points. Let the disconnect reset ring go slowly back to the initial position. CAUTION :

MAKE SURE THAT THERE IS CORRECT RESET OF THE IDG DISCONNECT MECHANISM. IF THE RESET IS NOT CORRECT, YOU MUST REMOVE AND REPLACE THE IDG BEFORE THE NEXT FLIGHT.

RESULT

On the IDG 1(2): . If you feel a click while you hold the disconnect reset ring, this shows that the disconnect function operates correctly.

On the IDG 1(2): . The force is much less than in step 2. . There is no click.

3.On the IDG 1(2): . Again slowly pull out the disconnect reset ring to the full limit of travel. 4.On the panel 35VU: . Lower the safety guard. NOTE :

Make sure that the CFDS message IDG 1(2) DISCONNECT goes out of view after the first engine start.

NOTE :

When you do the first engine start, make sure that the related engine electrical-generation system operates correctly.

5.

Close-up Subtask 24-21-00-410-051-A A.

Close the right fan-cowl door (Ref. TASK 71-13-00-410-010-A): (1)

FOR 1000EM1 (ENGINE-1) 438AR,

(2)

FOR 1000EM2 (ENGINE-2) 448AR

Subtask 24-21-00-865-056-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

DESIGNATION

FIN

LOCATION

122VU

ELEC/GCU/2

2XU2

T27

122VU

ELEC/GCU/1

2XU1

T26

AES

24-21-00 PB501

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-00-862-051-A C.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-21-00 PB501

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-00-730-041-A System Test of the IDG Frequency (P/N 766219) WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. 1.

Reason for the Job Make sure that the steady-state operating frequency of the IDG is between 390 and 410 Hz. If the frequency of the IDG is out of the specified limits, but is between 380 and 420 Hz, the display of the IDG frequency on the ECAM ELEC page becomes amber. Adjust the frequency as given in the procedure that follows. If the frequency of the IDG is out of the limits 380 - 420 Hz, replace the IDG. NOTE :

2.

The adjustment of the frequency is permitted only one time each 400FH. If you adjust the governor, make an entry in the aircraft technical logbook.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR B.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

71-00-00-710-018-A 71-00-00-710-043-A

Discontinued Start, Restart and Shutdown Procedures Normal Engine Automatic Start Procedure

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-00-991-92100-A - Governor Adjustment Screw - IDG) 3.

Job Set-up Subtask 24-21-00-010-057-A A.

Open the fan cowl doors (Ref. TASK 71-13-00-010-010-A): (1)

AES

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

24-21-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Subtask 24-21-00-860-057-A B.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

On the ECAM control panel, get the ELEC page.

(4)

Start the related engine (Ref. TASK 71-00-00-710-043-A).

Subtask 24-21-00-865-058-A C.

Make sure that this(these) circuit breaker(s) is(are) closed:

PANEL FOR FIN 1000EM1 122VU

ELEC/IDG1/DISC

1XT

T24

FOR FIN 1000EM2 122VU

ELEC/IDG2/DISC

2XT

T25

4.

DESIGNATION

FIN

LOCATION

Procedure (Ref. Fig. 24-21-00-991-92100-A - Governor Adjustment Screw - IDG) Subtask 24-21-00-730-051-A WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU. CAUTION :

A.

DO NOT ADJUST THE GOVERNOR MORE THAN 1 TIME EACH 400 FH. IF YOU ADJUST THE GOVERNOR, MAKE AN ENTRY IN THE AIRCRAFT TECHNICAL LOGBOOK.

Test of the IDG Frequency

ACTION 1.On the ECAM control panel: . get the ELEC page

RESULT On the lower ECAM display unit: . read the operating frequency of the generator (IDG1 or IDG2) to calculate the value of the necessary adjustment. NOTE :

AES

The normal operating frequency of the generator is 400 + or - 5 Hertz.

24-21-00 PB501

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 2.Shut down the engine (Ref. TASK 71-00-00-710-018-A). . remove the lockwire from the governor adjustment screw (2), . adjust the frequency to 400 + or - 1 Hertz. To do this, turn the adjustment screw (2): . clockwise to decrease the frequency, . or counterclockwise to increase the frequency. NOTE :

RESULT

One full turn of the adjustment screw changes the frequency by 3 to 3.5 Hertz.

3.Start the related engine (Ref. TASK 71-00-00-710-043A)

On the lower ECAM display unit: . check the frequency. NOTE :

If necessary, shut down the engine and repeat the adjustment procedure from step 2.

4.Shut down the engine (Ref. TASK 71-00-00-710-018-A). 5.Safety the adjustment screw (2) with lockwire. Do this carefully not to change the setting of the adjustment screw. 5.

Close-up Subtask 24-21-00-860-056-A A.

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Subtask 24-21-00-410-057-A B.

AES

Close the fan cowl doors (Ref. TASK 71-13-00-410-010-A): (1)

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

(2)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

24-21-00 PB501

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FWD ENGINE GEARBOX

B

B

ENGINE GEARBOX

2

1

N_MM_242100_5_XAM0_01_00

AES

FIGURE 24-21-00-991-92100-A SHEET 1 Governor Adjustment Screw - IDG

24-21-00 PB501

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-00-720-042-A Operational Test of the IDG Disconnect and Reconnect (Reset) Function - Engine in Operation WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. 1.

Reason for the Job To do a check of the IDG disconnect system and reset system.

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 438AR FOR FIN 1000EM2(ENGINE-2) 448AR B.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A 71-00-00-710-018-A 71-00-00-710-043-A

EIS Start Procedure EIS Stop Procedure Discontinued Start, Restart and Shutdown Procedures Normal Engine Automatic Start Procedure

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

3.

Job Set-up Subtask 24-21-00-860-053-A A.

AES

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

On the ECAM control panel, push the ELEC key to get the ELEC page.

(4)

Start the engine 1(2) (Ref. TASK 71-00-00-710-043-A).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-00-865-059-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

122VU

DESIGNATION ELEC/IDG2/DISC

2XT

T25

122VU

ELEC/IDG1/DISC

1XT

T24

4.

FIN

LOCATION

Procedure CAUTION :

DO NOT PUSH THE IDG DISCONNECT PUSHBUTTON SWITCH IF THE ENGINE SPEED IS LESS THAN IDLE SPEED. IF YOU DO, YOU WILL CAUSE DAMAGE TO THE JAW TEETH, AT ENGINE START.

CAUTION :

DO NOT PUSH THE IDG DISCONNECT PUSHBUTTON SWITCH FOR MORE THAN 3 SECONDS. THERE MUST BE AT LEAST 60 SECONDS BETWEEN TWO OPERATIONS OF THE SWITCH. THIS IS TO PREVENT DAMAGE TO THE DISCONNECT SOLENOID WHICH WILL BECOME TOO HOT.

Subtask 24-21-00-720-052-A A.

Operational Test of the IDG Disconnect Function - Engine in Operation NOTE :

This test is for the system 1. For the other system(s), use the indications between the parentheses.

ACTION 1.With the engines at idle speed, on the ELEC control panel 35VU: . lift the guard and push the IDG1(2) pushbutton switch.

2.On the ELEC control panel 35VU: Release the GEN1(2) pushbutton switch.

RESULT On the ELEC control panel 35VU: . the FAULT legend of the related GEN pushbutton switch comes on On the lower ECAM display unit, on the ELEC page: . the load, voltage and frequency parameters of the related generator are zero, . the amber DISC indication comes into view under the indication IDG, . the external power energizes the aircraft electrical circuits. On the ELEC control panel 35VU: . the FAULT legend of the related GEN pushbutton switch goes off,

3.On the ELEC control panel 35VU: Push the guard of the IDG 1(2) pushbutton switch back in position. Subtask 24-21-00-710-055-A B.

Reset of the system (1)

Stop the engine (Ref. TASK 71-00-00-710-018-A).

Subtask 24-21-00-010-064-A C.

Open the right fan-cowl door (Ref. TASK 71-13-00-010-010-A): (1)

AES

FOR 1000EM1 (ENGINE-1) 438AR

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

FOR 1000EM2 (ENGINE-2) 448AR

Subtask 24-21-00-720-053-A D.

Reset of the IDG 1(2) Disconnect System CAUTION :

MAKE SURE THE ENGINE IS STOPPED BEFORE YOU PULL THE DISCONNECT RESET RING. IF NOT YOU WILL CAUSE DAMAGE TO THE JAW TEETH.

CAUTION :

MAKE SURE THAT THERE IS CORRECT RESET OF THE IDG DISCONNECT MECHANISM. IF THE RESET IS NOT CORRECT, YOU MUST REMOVE AND REPLACE THE IDG BEFORE THE NEXT FLIGHT.

(1)

Slowly, pull out the disconnect reset ring to the full limit of travel. Monitor the hand force that is necessary: this force must not be too high. The disconnect mechanism must move freely without hard points. NOTE :

(2)

Let the disconnect reset ring go slowly back to the initial position.

(3)

Again, slowly pull out the disconnect reset ring to the full limit of travel. Monitor the hand force that is necessary. If the reset of the disconnect mechanism is correct, This force will be much less than in step (1). Also there will be no indication of the reset of the disconnect mechanism.

(4)

On the ELEC control panel 35VU, push the GEN 1(2) pushbutton switch (the FAULT legend comes on).

(5)

When you do the first engine start-up, make sure that the related electrical generation system operates correctly NOTE :

5.

The disconnect solenoid will make a click that you can feel in the disconnect reset ring when the reset ring comes near the full travel limit.

If you start the engine after the test, you must do a GCU reset. To do this, release then push the related GEN pushbutton switch.

Close-up Subtask 24-21-00-410-064-A A.

Close Access (1)

Close the right fan-cowl door (Ref. TASK 71-13-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 438AR

(b)

FOR 1000EM2 (ENGINE-2) 448AR

Subtask 24-21-00-860-054-A B.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) INSPECTION/CHECK ** On A/C ALL Task 24-21-00-210-045-A Inspection of the Filter Element(s) WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY AR WARNING NOTICE(S)

DESIGNATION

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 438AR FOR FIN 1000EM2(ENGINE-2) 448AR C.

Referenced Information

REFERENCE 12-32-24-281-001-A

DESIGNATION Sampling of the IDG Oil for Analysis

24-21-00-612-044-A

Servicing of the IDG after Oil Chemical Contamination

24-21-00-612-044-A-01

Servicing of the IDG after Oil Chemical Contamination and Extension of the OilFilter Differential-Pressure Indicator (DPI)

24-21-42-000-010-B 24-21-42-400-010-B 24-21-49-000-041-A

Removal of the Fuel-Cooled IDG Oil-Cooler Installation of the Fuel-Cooled IDG Oil-Cooler Removal of the Tubings - IDG Cooling Oil

24-21-49-400-041-A

Installation of the Tubing - IDG Cooler Oil

24-21-51-000-010-A

Removal of the Integrated Drive Generator -IDG 1(2)

24-21-51-000-011-A

Removal of the IDG Oil Filter(s)

24-21-51-400-010-A

Installation of the Integrated Drive Generator -IDG 1(2)

24-21-51-400-011-A

Installation of the IDG Oil Filter(s)

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

AES

24-21-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-21-00-941-058-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-21-00-010-058-A B.

Get Access (1)

4.

Open the right fan-cowl door (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 438AR

(b)

FOR 1000EM2 (ENGINE-2) 448AR

Procedure Subtask 24-21-00-020-051-A A.

Remove the IDG Oil Filter(s) (Ref. TASK 24-21-51-000-011-A).

Subtask 24-21-00-210-065-A B.

Visual Inspection of the Filter Element (1)

If you smell a fuel odour from the filter element or filter cover, do the servicing of the IDG after oil chemical contamination (Ref. TASK 24-21-00-612-044-A) or (Ref. TASK 24-21-00-612-044-A-01).

(2)

If you think that the condition of the oil in the filter element or on the filter cover is not correct, do a sampling of the IDG oil for analysis (Ref. TASK 12-32-24-281-001-A).

(3)

If the filter element does not show signs of metal particles, do the steps that follow:

(4)

(5)

(a)

If the oil-filter Differential Pressure Indicator (DPI) is not extended: . install the IDG filter element (Ref. TASK 24-21-51-400-011-A).

(b)

If the DPI is extended: . do the alternate procedure: Refer to TSM/24.

- If the filter element shows bright metal deposits that are chuncks or pieces which are the result of a breakage, (not non magnetic flakes or slivers from normal wear), or - if there are large quantities of bright metal deposits on the filter element, in the filter cavity or in the oil drained from the IDG, (a)

Remove the IDG (Ref. TASK 24-21-51-000-010-A) and send it back to the overhaul facility.

(b)

Install a new IDG (Ref. TASK 24-21-51-400-010-A).

If the filter element or/and the O-rings is(are) damaged or show signs of bypass, remove the tubings, the cooler and the IDG and return them to the overhaul facility. (a)

AES

Remove the tubings for cleaning (Ref. TASK 24-21-49-000-041-A).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

5.

(b)

Remove the cooler (Ref. TASK 24-21-42-000-010-B) and send it back to the overhaul facility.

(c)

Remove the IDG (Ref. TASK 24-21-51-000-010-A) and send it back to the overhaul facility.

(d)

Install a new IDG (Ref. TASK 24-21-51-400-010-A).

(e)

Install a new cooler (Ref. TASK 24-21-42-400-010-B).

(f)

Install the tubings (Ref. TASK 24-21-49-400-041-A) that you cleaned.

Close-up Subtask 24-21-00-410-058-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the right fan cowl door (Ref. TASK 71-13-00-410-010-A):

(3)

AES

(a)

FOR 1000EM1 (ENGINE-1) 438AR

(b)

FOR 1000EM2 (ENGINE-2) 448AR.

Remove the warning notice(s).

24-21-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-00-210-048-A Visual Inspection of the IDG for Oil Leaks and Check of the Electrical Circuits 1.

Reason for the Job To make sure that the IDG oil system is serviceable and to do a check for leakage, staining or wetting. To make sure that the wiring harnesses are in the correct condition. NOTE :

2.

If you cannot find the source of the oil leakage easily, refer to SIL 24-073.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY AR WARNING NOTICE(S)

DESIGNATION

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 438AR FOR FIN 1000EM2(ENGINE-2) 448AR C.

Referenced Information

REFERENCE 12-13-24-612-011-A 24-21-42-000-010-B 24-21-42-400-010-B 24-21-49-200-010-A

DESIGNATION IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check Removal of the Fuel-Cooled IDG Oil-Cooler Installation of the Fuel-Cooled IDG Oil-Cooler General Check of the IDG Oil Cooling Tubes

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

3.

Job Set-up Subtask 24-21-00-941-085-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

AES

Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

24-21-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-00-010-098-A B.

Get Access (1)

4.

Open the right fan-cowl door (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 438AR

(b)

FOR 1000EM2 (ENGINE-2) 448AR

Procedure Subtask 24-21-00-210-087-A A.

Visual Inspection (1)

Do a visual inspection of these components: NOTE :

(2)

There can be different signs of possible leakage: . Droplets of oil . Wet areas around connections, oil stripes on tubes . Stains or discoloration which can occur when oil or grease is in contact with very hot surfaces.

(a)

IDG fittings for leakage: . Pressure fill port . Overflow drain port . Oil-in and oil-out ports (cooling circuit interface with the IDG) . Case drain. If you find an oil leak, replace the related fitting.

(b)

IDG oil cooling tubes for leakage and correct condition (Ref. TASK 24-21-49-200-010-A).

(c)

IDG oil cooler for leakage: . Oil-in and oil-out ports (cooling circuit interface with the cooler) . Drain plug . Body of the cooler. If you find a leak, replace the IDG oil cooler (Ref. TASK 24-21-42-000-010-B) and (Ref. TASK 24-21-42-400-010-B).

If you find components wet with oil, make sure that you find and correct all the causes. If necessary, fill the oil tank (Ref. TASK 12-13-24-612-011-A).

Subtask 24-21-00-210-088-A B.

5.

Check of the Electrical Circuits (1)

Make sure that the wiring harnesses are in the correct condition.

(2)

Make sure that the electrical connectors are correctly connected.

Close-up Subtask 24-21-00-410-097-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the right fancowl door (Ref. TASK 71-13-00-410-010-A): (a)

AES

FOR 1000EM1 (ENGINE-1) 438AR

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b) (3)

AES

FOR 1000EM2 (ENGINE-2) 448AR.

Remove the warning notice(s).

24-21-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-00-210-048-A-01 Visual Inspection of the IDG for Oil Leakage Engine Static and Check of the Electrical Circuits WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. WARNING : WEAR GOGGLES, INSULATED GLOVES AND OTHER PROTECTIVE CLOTHES. HOT OIL CAN BURN YOUR EYES AND SKIN. IF OIL TOUCHES YOUR EYES OR SKIN, GET MEDICAL AID. CAUTION :

DO NOT OPERATE THE IDG: IF IT CONTAINS TOO MUCH OIL IF IT DOES NOT CONTAIN ENOUGH OIL IF YOU DO, YOU CAN CAUSE DAMAGE TO THE IDG.

CAUTION :

DO NOT USE SOLVENTS THAT CONTAIN CHLORINE TO CLEAN THE EQUIPMENT (PUMP, HOSES, TANK AND FUNNEL) USED TO FILL THE IDG WITH OIL. CHLORINE CONTAMINATION OF THE OIL CAN CAUSE FAST DETERIORATION OF THE OIL AND WILL DECREASE THE LIFE OF THE IDG.

1.

Reason for the Job To make sure that the IDG oil system is serviceable and to do a check for leakage, staining or wetting. To make sure that the wiring harnesses are in correct condition.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 AIR SOURCE 2 BAR (30 PSI) - REGULATED, FILTERED, DRY

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

753970A

1

CSD IDG SYSTEM LEAK TESTER

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 438AR FOR FIN 1000EM2(ENGINE-2) 448AR C.

Referenced Information

REFERENCE 12-13-24-612-011-A 24-21-42-000-010-B 24-21-42-400-010-B 24-21-49-200-010-A

DESIGNATION IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check Removal of the Fuel-Cooled IDG Oil-Cooler Installation of the Fuel-Cooled IDG Oil-Cooler General Check of the IDG Oil Cooling Tubes

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

AES

24-21-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 71-13-00-410-010-A

DESIGNATION Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-00-991-20000-B - Connection of the Test Tool on the IDG) 3.

Job Set-up Subtask 24-21-00-941-088-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-21-00-865-072-A B.

Open, safety and tag this(these) circuit breaker(s):

PANEL DESIGNATION FOR FIN 4000XU1000EM1 122VU ELEC/GCU/1 122VU

ELEC/IDG1/DISC

FOR FIN 4000XU1000EM2 122VU ELEC/GCU/2 122VU

ELEC/IDG2/DISC

FIN

LOCATION

2XU1

T26

1XT

T24

2XU2

T27

2XT

T25

Subtask 24-21-00-010-101-A C.

Get Access (1)

4.

Open the right fan-cowl door (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 438AR

(b)

FOR 1000EM2 (ENGINE-2) 448AR

Procedure (Ref. Fig. 24-21-00-991-20000-B - Connection of the Test Tool on the IDG) Subtask 24-21-00-210-092-A A.

AES

Oil Leak Test (1)

On the tool CSD IDG SYSTEM LEAK TESTER (753970A), turn the drain valve to the off position.

(2)

Set the shut-off valve to OFF and close the regulator valve to prevent pressure release to the IDG fitting.

(3)

Remove the dust cap from the pressure fill half-coupling.

(4)

Connect one end of the pressure fill hose of the tool to the pressure fill half-coupling (pressure fill port) of the IDG.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (5)

Connect the other end of the tool CSD IDG SYSTEM LEAK TESTER (753970A) to an AIR SOURCE 2 BAR (30 PSI) - REGULATED, FILTERED, DRY.

(6)

Turn the shut-off valve to ON and adjust the regulator valve to a pressure of 1.72 bar (24.9465 psi) on the system pressure gauge.

(7)

Turn the supply valve to OFF to keep the air in the system. NOTE :

Pressure will become stable in the system, with no leak. When the IDG case is vented: . The pressure will decrease to a lightly lower value because of the vent valve setting. . The pressure will stay at this setting.

(8)

Monitor the system pressure for five minutes for confirmation of the leak.

(9)

Do a visual inspection of these components in case of confirmed leak(s): NOTE :

There can be different signs of possible leakage: . Droplets of oil . Wet areas around connections, oil stripes on tubes . Stains or discoloration which can occur when oil or grease is in contact with very hot surfaces.

(a)

IDG fittings for leakage: . Pressure fill port . Overflow drain port . Oil-in and oil-out ports (cooling circuit interface with the IDG) . Case drain. If you find an oil leak, replace the related fitting.

(b)

IDG oil cooling tubes for leakage and correct condition (Ref. TASK 24-21-49-200-010-A).

(c)

IDG oil cooler for leakage: . Oil-in and oil-out ports (cooling circuit interface with the cooler) . Drain plug . Body of the cooler. If you find a leak, replace the IDG oil cooler (Ref. TASK 24-21-42-000-010-B) and (Ref. TASK 24-21-42-400-010-B).

(10) If you find components wet with oil, make sure that you find and correct all the causes. If necessary, fill the oil tank (Ref. TASK 12-13-24-612-011-A). (11) If the visual check does not locate the leak source, do a check of the system for leaks. To do this, use soap suds or equivalent leak detector fluid: . Put an appropriate container below the drain valve and open the valve to release the pressure. . Make the necessary corrections and restore the system to an operational configuration. . Do the check again to make sure that the leak was corrected. NOTE :

If oil collects in the coalescing filter, use the drain valve a the bottom of the filter housing to drain the oil.

NOTE :

If you use an AIR SOURCE 2 BAR (30 PSI) - REGULATED, FILTERED, DRY, it is necessary to install a plug on the port for the compressed air source.

Subtask 24-21-00-210-094-A B.

AES

Check of the Electrical Circuits (1)

Make sure that the wiring harnesses are in the correct condition.

(2)

Make sure that the electrical connectors are correctly connected.

24-21-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-21-00-410-100-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the right fancowl door (Ref. TASK 71-13-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 438AR

(b)

FOR 1000EM2 (ENGINE-2) 448AR.

Subtask 24-21-00-865-073-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL DESIGNATION FOR FIN 4000XU1000EM1 122VU ELEC/GCU/1 122VU

ELEC/IDG1/DISC

FOR FIN 4000XU1000EM2 122VU ELEC/GCU/2 122VU

ELEC/IDG2/DISC

FIN

LOCATION

2XU1

T26

1XT

T24

2XU2

T27

2XT

T25

Subtask 24-21-00-942-055-A C.

AES

Remove the warning notice(s).

24-21-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL ELECTRICAL P IND BUTTON CONNECTOR (SILVER END, RED 4000XUC CYLINDRICAL SIDE) ELECTRICAL CONNECTOR PUSH TO VENT VALVE 4000XUA

OIL FILTER

PRESSURE FILL PORT DISCONNECT RESET RING ELECTRICAL CONNECTOR 4000XUB TERMINAL BLOCK OIL OUT PORT OVERFLOW DRAIN PORT OIL IN PORT SIGHT GLASS

SHUT−OFF VALVE

CASE DRAIN PLUG

REGULATOR VALVE COALESCING FILTER CHECK VALVE

SYSTEM PRESSURE GAUGE

FROM DRY AIR SOURCE

DRAIN VALVE RELIEF−VALVE (PRE−SET AT 100 PSI) REGULATOR PRESSURE GAUGE RELIEF−VALVE (PRE−SET AT 50 PSI) N_MM_242100_6_ACM0_01_00

AES

FIGURE 24-21-00-991-20000-B SHEET 1 Connection of the Test Tool on the IDG

24-21-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

THERMOCOUPLE - IDG OIL TEMPERATURE REMOVAL/INSTALLATION ** On A/C ALL Task 24-21-15-000-010-A Removal of the IDG Oil Temperature Thermocouple WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. WARNING : DO NOT GET ENGINE OIL ON YOUR SKIN FOR A LONG TIME. FLUSH THE OIL FROM YOUR SKIN WITH WATER. THE OIL IS POISONOUS AND CAN GO THROUGH YOUR SKIN AND IN TO YOUR BODY. CAUTION :

DO NOT LET ENGINE FUEL OR OIL FALL ON THE ENGINE. UNWANTED FUEL OR OIL MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT FREE CLOTH. THE FUEL OR OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS.

FIN 4015KS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY AR COVER - BLANKING

No specific

AR

B.

WARNING NOTICE(S)

Consumable Materials

REFERENCE Material No: 19-003 C.

DESIGNATION

DESIGNATION LINT-FREE COTTON CLOTH

Work Zones and Access Panels ZONE/ACCESS

453 463 FOR FIN 1000EM1(ENGINE-1)

ZONE DESCRIPTION HOT SECTION HOT SECTION

437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR D.

Referenced Information

REFERENCE 71-13-00-010-010-A

DESIGNATION Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-15-991-15000-A - IDG Oil Temperature thermocouple)

AES

24-21-15 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-21-15-941-050-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

Put a WARNING NOTICE(S) to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Subtask 24-21-15-010-050-A B.

4.

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (1)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(2)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Procedure (Ref. Fig. 24-21-15-991-15000-A - IDG Oil Temperature thermocouple) Subtask 24-21-15-020-050-A A.

AES

Removal of the IDG Oil-Temperature Thermocouple (1)

Disconnect the electrical connector (3) from the IDG oil-temperature thermocouple (4).

(2)

Remove the bolts (2) that attach the thermocouple (4) to the fuel-cooled IDG oil-cooler.

(3)

Remove the thermocouple (4).

(4)

Remove and discard the packing (1).

(5)

Use the clean LINT-FREE COTTON CLOTH (Material No: 19-003) to remove oil leakage.

(6)

Put the applicable COVER - BLANKING on all of the openings, the electrical connector and the electrical receptacle.

24-21-15 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

I.D.G. OIL COOLER

1 PACKING 4 THERMOCOUPLE

3 ELECTRICAL CONNECTOR

2 BOLT

12476

N_MM_242115_4_XAM0_01_00

AES

FIGURE 24-21-15-991-15000-A SHEET 1 IDG Oil Temperature thermocouple

24-21-15 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-15-400-010-A Installation of the IDG Oil Temperature Thermocouple WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. WARNING : DO NOT GET ENGINE OIL ON YOUR SKIN FOR A LONG TIME. FLUSH THE OIL FROM YOUR SKIN WITH WATER. THE OIL IS POISONOUS AND CAN GO THROUGH YOUR SKIN AND IN TO YOUR BODY. CAUTION :

DO NOT LET ENGINE FUEL OR OIL FALL ON THE ENGINE. UNWANTED FUEL OR OIL MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT FREE CLOTH. THE FUEL OR OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS.

FIN 4015KS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M(3 FT)

No specific

AR

No specific

B.

WARNING NOTICE(S) Torque wrench: range to between 62.00 and 900.00 LBF.IN (0.70 and 10.00 M.DAN)

Consumable Materials

REFERENCE Material No: V01-002 Material No: V10-039

cleaning fluid engine oil

Material No: 19-003

LINT-FREE COTTON CLOTH

C.

DESIGNATION

Work Zones and Access Panels ZONE/ACCESS

453 463 FOR FIN 1000EM1(ENGINE-1)

ZONE DESCRIPTION HOT SECTION HOT SECTION

437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR D.

Expendable Parts

FIG.ITEM 1

AES

DESIGNATION packing

IPC-CSN 24-21-15-80-040

24-21-15 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL E.

Referenced Information

REFERENCE 24-21-51-200-010-A

DESIGNATION Check of the Oil Level and Filter Differential Pressure Indicator (DPI)

70-23-11-911-013-A

General Torque Tightening Techniques

70-23-13-911-010-A

Procedures for the Installation of Preformed Packings

70-23-15-912-010-A 71-00-00-710-017-B

Connection of Electrical Connectors Ground Test Requirements after Power Plant Module/Component Repair or Replacement Procedures

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-15-991-15000-A - IDG Oil Temperature thermocouple) 3.

Job Set-up Subtask 24-21-15-860-050-A A.

Aircraft Maintenance Configuration (1)

On the center pedestal panel 115VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the engine.

(2)

On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a WARNING NOTICE(S) is in position to tell persons not to energize the FADEC 1(2).

(3)

Make sure that the ACCESS PLATFORM 1M(3 FT) is in position.

Subtask 24-21-15-010-051-A B.

Get Access (1)

4.

Make sure that the fan cowl doors are open (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Procedure (Ref. Fig. 24-21-15-991-15000-A - IDG Oil Temperature thermocouple) Subtask 24-21-15-110-050-A A.

Cleaning of the Components before Installation (Ref. Fig. 24-21-15-991-15000-A - IDG Oil Temperature thermocouple) WARNING : DO NOT GET CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES. PUT ON PROTECTIVE CLOTHING, GOGGLES AND A FACE MASK. USE THE FLUID IN A WELL VENTILATED AREA. DO NOT BREATHE THE VAPOR. IF YOU GET THE CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES FLUSH IT AWAY WITH WATER. GET MEDICAL AID IF YOUR SKIN OR EYES BECOME IRRITATED.

AES

24-21-15 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (1)

Remove all the covers/caps/plugs from the openings the electrical connector and the electrical receptacle.

(2)

Use a LINT-FREE COTTON CLOTH (Material No: 19-003) made moist with cleaning fluid (Material No: V01-002) to clean these parts: (a)

The IDG oil cooler.

(b)

The IDG oil-temperature thermocouple (4).

(3)

Use a clean LINT-FREE COTTON CLOTH (Material No: 19-003) to dry the IDG oil-cooler and the IDG oil-temperature thermocouple (4).

(4)

Make sure that these items have no damage: (a)

The IDG oil cooler.

(b)

The IDG oil-temperature thermocouple (4).

(c)

The electrical connector.

Subtask 24-21-15-420-050-A B.

Installation of the IDG Oil-Temperature Thermocouple on the IDG Oil Cooler WARNING : DO NOT GET ENGINE OIL ON YOUR SKIN FOR A LONG TIME. FLUSH THE OIL FROM YOUR SKIN WITH WATER. THE OIL IS POISONOUS AND CAN GO THROUGH YOUR SKIN AND IN TO YOUR BODY. CAUTION :

MAKE SURE THAT YOU DO NOT CAUSE DAMAGE TO THE NEW PACKING WHEN

(1)

Lubricate the new (IPC-CSN 24-21-15-80) packing (1) with clean engine oil (Material No: V10-039) , then install it on the IDG oil-temperature thermocouple (4) (Ref. TASK 70-23-13-911-010-A).

(2)

Install the IDG oil-temperature thermocouple (4) in the IDG oil cooler and attach with the two bolts (2).

(3)

TORQUE the bolts (2) (Ref. TASK 70-23-11-911-013-A) to 100 LBF.IN (1.13 M.DAN).

(4)

Connect the electrical connector (3) (Ref. TASK 70-23-15-912-010-A) to the IDG oil-temperature thermocouple (4).

Subtask 24-21-15-710-050-A C.

Operational Test of the IDG Oil-Temperature Thermocouple-System (1)

Do an operational test of the IDG oil-temperature thermocouple-system (Ref. TASK 71-00-00-710-017B).

Subtask 24-21-15-790-050-A D.

Test for Leaks (1)

Do an oil-system leak test of the IDG oil-temperature thermocouple. Leaks are not permitted (Ref. TASK 71-00-00-710-017-B).

Subtask 24-21-15-210-050-A E.

Check of the IDG Oil Level (1)

AES

Do a check of the IDG oil level (Ref. TASK 24-21-51-200-010-A).

24-21-15 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-21-15-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowls (Ref. TASK 71-13-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

(3)

Remove the warning notice(s).

(4)

Remove the access platform(s).

24-21-15 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

COUPLING - QAD, IDG - REMOVAL/INSTALLATION ** On A/C ALL Task 24-21-41-000-010-A Removal of the Quick Attach/Detach (QAD) Adapter of the IDG FIN 4000XU 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY AR COVER - PROTECTION

No specific

AR

B.

DESIGNATION

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR C.

Referenced Information

REFERENCE 24-21-51-000-010-A

DESIGNATION Removal of the Integrated Drive Generator -IDG 1(2)

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-41-991-15000-A - Quick Attach/Detach (QAD) Adapter (Coupling)) (Ref. Fig. 24-21-41-991-15200-A - Removal of the QAD Adapter (Coupling)) 3.

Job Set-up Subtask 24-21-41-941-050-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

(2)

Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

On the overhead maintenance panel 50VU: (a)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-21-41-010-050-A B.

Get Access (1)

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (a)

AES

FOR 1000EM1 (ENGINE-1) 437AL 438AR

24-21-41 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b) 4.

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Procedure (Ref. Fig. 24-21-41-991-15000-A - Quick Attach/Detach (QAD) Adapter (Coupling)) (Ref. Fig. 24-21-41-991-15200-A - Removal of the QAD Adapter (Coupling)) Subtask 24-21-41-020-051-A A.

Remove the Integrated Drive Generator (IDG) (Ref. TASK 24-21-51-000-010-A).

Subtask 24-21-41-020-050-A B.

Removal of the QAD Adapter (1)

To remove the QAD adapter (1) from the accessory-gearbox mounting-pad: . hit the head of each flat head screw (3) with a flat head punch. NOTE :

CAUTION :

YOU CAN DAMAGE THE SCREWS IF YOU USE TOO MUCH FORCE TO HIT THE PUNCH.

(2)

If you cannot loosen the flat head screws: . get a pointed punch. . put the pointed punch on the screw (3) with an angular position which will make the screw turn counterclockwise. . hit the screw.

(3)

Remove the screws (3) that attach the QAD adapter (1) to the accessory-gearbox mounting-pad.

(4)

Pull the QAD adapter (1) away from the accessory-gearbox mounting-pad. NOTE :

AES

Flat head srews (3) rub or get caught in mating parts. Strong contact is required to loosen the flat head screws.

If you cannot easily release the QAD adapter (1) from the mounting-pad, lightly hit the QAD adapter with a soft-faced mallet.

(5)

Discard the gasket (2) only if it is damaged or shows signs of excessive wear.

(6)

Install the COVER - PROTECTION on the accessory-gearbox mounting-pad.

24-21-41 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

1 COUPLING 2 GASKET

TOP V2500

FWD TOP CFM

3 SCREW

ALIGNMENT MARK INDEX PIN HOLE

GEARBOX

A 12351 A

N_MM_242141_4_XAM0_01_00

AES

FIGURE 24-21-41-991-15000-A SHEET 1 Quick Attach/Detach (QAD) Adapter (Coupling)

24-21-41 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL GEARBOX

Q.A.D. COUPLING

A

FLAT HEAD PUNCH

SCREW

A FLAT HEAD PUNCH SCREW

COUNTERCLOCKWISE DIRECTION

POINTED PUNCH

A POINTED PUNCH 14270

N_MM_242141_4_XBM0_01_00

AES

FIGURE 24-21-41-991-15200-A SHEET 1 Removal of the QAD Adapter (Coupling)

24-21-41 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-41-400-010-A Installation of the Quick Attach/Detach (QAD) Adapter of the IDG FIN 4000XU 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY AR COTTON SWAB

No specific

AR

No specific

B.

WARNING NOTICE(S) Torque wrench: range to between 62.00 and 900.00 LBF.IN (0.70 and 10.00 M.DAN)

Consumable Materials

REFERENCE Material No: V01-002 Material No: 03-002 Material No: 05-063 Material No: 19-003 C.

DESIGNATION

DESIGNATION cleaning fluid OILS LUBRICATING OIL TURBINE ENGINE SYNT BASE SPECIAL MATERIALS NEVERSEEZ NICKEL SPECIAL GRADE LINT-FREE COTTON CLOTH

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR D.

Expendable Parts

FIG.ITEM 6

DESIGNATION

IPC-CSN 24-21-41-80-030

gasket E.

Referenced Information

REFERENCE 24-21-51-400-010-A

DESIGNATION Installation of the Integrated Drive Generator -IDG 1(2)

70-23-11-911-013-A

General Torque Tightening Techniques

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-41-991-15000-A - Quick Attach/Detach (QAD) Adapter (Coupling))

AES

24-21-41 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-21-41-860-050-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

(2)

Make sure that the WARNING NOTICE(S) is in position to tell persons not to start the engine.

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Make sure that the warning notice to tell persons not to energize the FADEC 1(2), is in position.

Subtask 24-21-41-010-052-A B.

Get Access (1)

4.

Make sure that the fan cowls are open (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Procedure (Ref. Fig. 24-21-41-991-15000-A - Quick Attach/Detach (QAD) Adapter (Coupling)) Subtask 24-21-41-110-050-A A.

Visual Check of the Connecting Surfaces (1)

Remove the protective cover from the accessory-gearbox mounting-pad.

(2)

Do a visual check of the QAD adapter (1) for damage from incorrect shipping or handling.

(3)

Do a visual check of the connecting surfaces of the QAD adapter (1) and the accessory-gearbox mounting-pad. They must be smooth and clean.

Subtask 24-21-41-640-050-A B.

Lubrication of the QAD Adapter Tension Bolt CAUTION :

(1)

LUBRICATE THE QAD ADAPTER TENSION-BOLT BEFORE YOU INSTALL THE ADAPTER ON THE GEARBOX MOUNTING PAD. NO LUBRICANT ON THE TENSION BOLT CAN CAUSE INCREASED WEAR TO THE TENSION BOLT AND THE BRACKET.

Apply OILS (Material No: 03-002) to the QAD tension bolt.

Subtask 24-21-41-420-050-A C.

Installation of the QAD adapter (Ref. Fig. 24-21-41-991-15000-A - Quick Attach/Detach (QAD) Adapter (Coupling)) WARNING : DO NOT GET CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES. PUT ON PROTECTIVE CLOTHING, GOGGLES AND A FACE MASK. USE THE FLUID IN A WELL VENTILATED AREA. DO NOT BREATHE THE VAPOR. IF YOU GET THE CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES FLUSH IT AWAY WITH WATER. GET MEDICAL AID IF YOUR SKIN OR EYES BECOME IRRITATED.

AES

24-21-41 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL CAUTION :

(1)

DO NOT LET THE LUBRICANT STAY IN THE DOWEL PIN HOLES AND SCREW HOLES OF THE QAD ADAPTER. LUBRICANT BUILDUP CAN CAUSE THE PRESSURE TO INCREASE. INCREASED PRESSURE CAN CAUSE DAMAGE TO THE GEARBOX WHEN YOU INSTALL AND TORQUE THE SCREWS.

Clean the gearbox mounting surface, index pin hole and screw holes. (a)

Use a clean LINT-FREE COTTON CLOTH (Material No: 19-003) and COTTON SWAB made moist with cleaning fluid (Material No: V01-002) to remove the lubricant from the screw holes and index pin holes.

(b)

Use a clean LINT-FREE COTTON CLOTH (Material No: 19-003) made moist with cleaning fluid (Material No: V01-002) to clean the gearbox mounting surface and QAD adapter. Wipe dry before cleaning fluid evaporates. NOTE :

Make sure that the stripe on the QAD ring is aligned with the stripe on the adapter plate.

(2)

Install the (IPC-CSN 24-21-41-80) gasket (6) on the face of the QAD adapter (1). Make sure that the index pin hole of the QAD adapter is aligned with the index pin hole of the QAD gasket.

(3)

Install the QAD adapter (1) on the accessory-gearbox mounting-pad with the screws (3). NOTE :

Make sure that the words ”TOP-V2500” on the QAD adapter are in the top position (12 o’clock).

(4)

Use a brush to apply a thin layer of SPECIAL MATERIALS (Material No: 05-063) to the conical surface of the heads of the screws (3) and to the threads of the screws.

(5)

TORQUE the screws (3) to between 348 and 384 LBF.IN (3.93 and 4.34 M.DAN) to QAD adapter (Ref. TASK 70-23-11-911-013-A).

Subtask 24-21-41-420-051-A D. 5.

Install the IDG (Ref. TASK 24-21-51-400-010-A).

Close-up Subtask 24-21-41-410-050-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowls (Ref. TASK 71-13-00-410-010-A):

(3)

AES

(a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Remove the warning notice(s).

24-21-41 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

COUPLING - QAD, IDG - INSPECTION/CHECK ** On A/C ALL Task 24-21-41-200-010-A Torque Check of the Quick Attach-Detach (QAD) Adapter Tension-Bolt WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. 1.

Reason for the Job (Ref. MPD 24-21-00-06-) CHECK TORQUE OF QUICK-ATTACH-DETACH (QAD) TENSION BOLT To do a torque check of the IDG QAD adapter tension bolt without component removal.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific

B.

DESIGNATION

Torque wrench: range to between 62.00 and 900.00 LBF.IN (0.70 and 10.00 M.DAN)

Consumable Materials

REFERENCE Material No: V02-147 C.

QTY AR WARNING NOTICE(S)

DESIGNATION lockwire

Work Zones and Access Panels ZONE/ACCESS

438 448 FOR FIN 1000EM1(ENGINE-1)

ZONE DESCRIPTION FAN COWL FAN COWL

437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR D.

Referenced Information

REFERENCE 24-21-41-000-010-A

DESIGNATION Removal of the Quick Attach/Detach (QAD) Adapter of the IDG

24-21-51-000-010-A

Removal of the Integrated Drive Generator -IDG 1(2)

70-23-11-911-013-A

General Torque Tightening Techniques

70-40-11-911-012-A 71-13-00-010-010-A

General Instructions for the Uses of Lockwire Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-41-991-15100-A - IDG QAD Coupling)

AES

24-21-41 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-21-41-941-051-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-21-41-010-051-A B.

Get Access (1)

4.

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR.

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Procedure (Ref. Fig. 24-21-41-991-15100-A - IDG QAD Coupling) Subtask 24-21-41-220-050-A A.

Torque Check of the QAD Adapter Tension-Bolt WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU. (1)

Cut and remove the lockwire (1) from the tension bolt (2).

(2)

Do a check of the torque value of the QAD coupling bolt (2): (a)

TORQUE the QAD coupling bolt to between 264 and 313 LBF.IN (2.98 and 3.54 M.DAN), (Ref. TASK 70-23-11-911-013-A).

(b)

Lightly hit the external circumference of the QAD coupling (3) to enter it and prevent incorrect torque values.

(c)

TORQUE the QAD coupling bolt to between 264 and 313 LBF.IN (2.98 and 3.54 M.DAN), (Ref. TASK 70-23-11-911-013-A).

(d)

Continue to do this sequence until the torque value does not decrease by more than 24 lbf.in (0.27 m.daN).

(e)

Do a check of the distance between the ring lug and the bracket of the QAD ring. If the the distance is less than 0.56 in.(14,3mm): 1

Replace the IDG (Ref. TASK 24-21-51-000-010-A).

2

After you install the new IDG and torque the QAD, measure the QAD gap again before you attach the hoses, the wires, and the other components. a

AES

If gap is correct, the old IDG is worn and you must replace its input flange.

24-21-41 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL b (3) 5.

If the gap is not correct, remove the new IDG and replace the QAD adapter (Ref. TASK 24-21-41-000-010-A).

Safety the tension bolt (2) with lockwire (Material No: V02-147) , (Ref. TASK 70-40-11-911-012-A) (1).

Close-up Subtask 24-21-41-410-051-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowls (Ref. TASK 71-13-00-410-010-A):

(3)

AES

(a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR.

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Remove the warning notice(s).

24-21-41 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

QAD COUPLING

GEARBOX

FWD LOCKWIRE

QAD COUPLING BOLT

A TAP HERE

A QAD RING

QAD RING

3

1

BRACKET

1

BRACKET

2

2

TAP ALONG THIS AREA RING LUG BRACKET 0.56in. RING LUG

0.56in. MINI.

QAD RING

2 3

BRACKET N_MM_242141_6_XAM0_01_00

AES

FIGURE 24-21-41-991-15100-A SHEET 1 IDG QAD Coupling

24-21-41 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

IDG OIL COOLER - FUEL COOLED - REMOVAL/INSTALLATION ** On A/C ALL Task 24-21-42-000-010-B Removal of the Fuel-Cooled IDG Oil-Cooler WARNING : DO NOT LET THE ENGINE FUEL OR OIL STAY ON YOUR SKIN FOR A LONG TIME. FLUSH FUEL AND OIL FROM YOUR SKIN WITH WATER. THE FUEL AND OIL ARE POISONOUS AND CAN GO THROUGH YOUR SKIN AND INTO YOUR BODY. WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. CAUTION :

1.

DO NOT LET ENGINE FUEL OR OIL FALL ON THE ENGINE. UNWANTED FUEL OR OIL MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT FREE CLOTH. THE FUEL OR OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR CONTAINER - CLEAN, APPLICABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR C.

Referenced Information

REFERENCE 24-21-15-000-010-A

DESIGNATION Removal of the IDG Oil Temperature Thermocouple

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-42-991-15000-A - Fuel-Cooled IDG Oil-Cooler) (Ref. Fig. 24-21-42-991-15300-A - Fuel-Cooled IDG Oil-Cooler) (Ref. Fig. 24-21-42-991-15100-A - Fuel-Cooled IDG Oil-Cooler) (Ref. Fig. 24-21-42-991-15200-B - Fuel-Cooled IDG Oil-Cooler)

AES

24-21-42 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-21-42-941-051-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

Put a WARNING NOTICE(S) to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Subtask 24-21-42-010-052-A B.

4.

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (1)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(2)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Procedure Subtask 24-21-42-680-052-A A.

Draining of the Oil from the Fuel-Cooled IDG Oil-Cooler (Ref. Fig. 24-21-42-991-15000-A - Fuel-Cooled IDG Oil-Cooler) CAUTION :

DO NOT PUT THE OIL THAT HAS BEEN DRAINED FROM THE ENGINE BACK IN TO THE OIL SYSTEM.

(1)

Cut and discard the wire which safeties the oil drain plug (4) to the fuel-cooled IDG oil-cooler.

(2)

Remove the oil drain plug from the fuel-cooled IDG oil-cooler and drain the oil into the CONTAINER CLEAN, APPLICABLE.

(3)

Remove and discard the sealing ring (1).

Subtask 24-21-42-680-053-A B.

Draining of the Fuel from the Fuel-Cooled IDG Oil-Cooler (Ref. Fig. 24-21-42-991-15000-A - Fuel-Cooled IDG Oil-Cooler) CAUTION :

DO NOT PUT FUEL THAT HAS BEEN DRAINED FROM THE ENGINE BACK IN TO THE FUEL SYSTEM.

(1)

Cut and discard the wire which safeties the fuel drain plug (3) to the fuel-cooled IDG oil-cooler.

(2)

Remove the fuel drain plug from the fuel-cooled IDG oil-cooler and drain the fuel into the CONTAINER - CLEAN, APPLICABLE.

(3)

Remove and discard the sealing ring (2).

Subtask 24-21-42-020-058-A C.

Removal of the Fuel-Cooled IDG Oil Cooler Temperature Thermocouple (1)

AES

Remove the fuel-cooled IDG oil-cooler temperature thermocouple (Ref. TASK 24-21-15-000-010-A).

24-21-42 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-42-020-059-A D.

Disconnection of the Clips of the EEC Harness at Positions B, C, D and E (Ref. Fig. 24-21-42-991-15300-A - Fuel-Cooled IDG Oil-Cooler) (1)

Remove the bolt (12), nut (16) and washer (13) at position B.

(2)

Remove the bolt (21), nut (24) and washer (22) at position C.

(3)

Remove the bolt (41), nut (43) and washer (46) at position D.

(4)

Remove the bolt (31), nut (34) and washer (32) at position E.

Subtask 24-21-42-020-060-A E.

Disconnection of the Oil Tubes from the Fuel-Cooled IDG Oil-Cooler (Ref. Fig. 24-21-42-991-15100-A - Fuel-Cooled IDG Oil-Cooler) (1)

Remove the bolts (67) and disconnect the bracket (65) and the oil tube (64) from the fuel-cooled IDG oil-cooler.

(2)

Remove and discard the sealing ring (66).

(3)

Remove the bolts (62) and disconnect the bracket (61) and the oil tube (63) from the fuel-cooled IDG oil-cooler.

(4)

Remove and discard the sealing ring (60).

Subtask 24-21-42-020-061-A F.

Disconnection of the Fuel Tubes from the Fuel-Cooled IDG Oil-Cooler (Ref. Fig. 24-21-42-991-15100-A - Fuel-Cooled IDG Oil-Cooler) (1)

Remove the bolts (53) and disconnect the bracket (52) and the fuel tube (51) from the fuel-cooled IDG oil-cooler.

(2)

Remove the bolts (56).

(3)

Disconnect the fuel tube (55) and the seal housing (58) from the fuel-cooled IDG oil-cooler.

Subtask 24-21-42-020-062-A G.

Removal of the Fuel-Cooled IDG Oil-Cooler (Ref. Fig. 24-21-42-991-15200-B - Fuel-Cooled IDG Oil-Cooler) (1)

Remove the pin (76).

(2)

Remove the pin (75). NOTE :

Hold the weight of the fuel-cooled IDG oil-cooler before the pin (75) is removed.

(3)

Remove the fuel-cooled IDG oil-cooler from the fan case.

(4)

Remove the bushes (71) and (77) from the fuel-cooled IDG oil-cooler.

Subtask 24-21-42-020-063-A H.

AES

Removal of the Sealing Rings (Ref. Fig. 24-21-42-991-15100-A - Fuel-Cooled IDG Oil-Cooler) (1)

Remove the sealing ring (54) from the fuel tube (51) and discard it.

(2)

Remove the seal housing (58) from the fuel tube (55).

(3)

Remove the sealing ring (59) from the seal housing and discard it.

(4)

Remove the two sealing rings (57) from the fuel tube (55) and discard them.

24-21-42 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

B IDG FCOC OIL TEMPERATURE THERMOCOUPLE

C BOLT (2 off)

D

FUEL COOLED IDG OIL COOLER (IDG FCOC)

E

1 SEALING RING

2 SEALING RING 3 FUEL DRAIN PLUG

LP COMPRESSOR / INTERMEDIATE CASE MODULE

4 OIL DRAIN PLUG

A 10938B N_MM_242142_4_XAM0_01_00

AES

FIGURE 24-21-42-991-15000-A SHEET 1 Fuel-Cooled IDG Oil-Cooler

24-21-42 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

21 BOLT

11 CLIP

26 CLIP

12 BOLT

22 WASHER

13 WASHER 14 HARNESS

23 HARNESS

25 TUBE

15 BRACKET

24 NUT

16 NUT

C B

CLIP POINT 0756

CLIP POINT 0754

31 BOLT 41 BOLT

46 WASHER

32 WASHER

42 HARNESS

33 HARNESS

45 CLIP

36 CLIP

43 NUT 44 TUBE

D

34 NUT

35 TUBE

CLIP POINT 0291

E

CLIP POINT 0290

E1977 N_MM_242142_4_XGM0_01_00

AES

FIGURE 24-21-42-991-15300-A SHEET 1 Fuel-Cooled IDG Oil-Cooler

24-21-42 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

52 BRACKET

53 BOLT (3 off) 56 BOLT (3 off)

PRESSURE OIL TUBE 51 IDG FCOC TO DIVERTER VALVE FUEL TUBE FUEL TUBE

67 BOLT (3 off)

55 LP PUMP TO IDG FCOC FUEL TUBE 54 SEALING RING

66 SEALING RING 57 SEALING RING (2 off) 58 SEAL HOUSING

65 BRACKET

64 OUTLET OIL TUBE

SCAVENGE OIL. TUBE

59 SEALING RING 60 SEALING RING

61 BRACKET

PRESSURE OIL TUBE 63 INLET OIL TUBE

62 BOLT (3 off) PRESSURE OIL TUBE

FUEL COOLED IDG OIL COOLER (IDG FCOC)

LP COMPRESSOR/INTERMEDIATE CASE MODULE

10939B

N_MM_242142_4_XCM0_01_00

AES

FIGURE 24-21-42-991-15100-A SHEET 1 Fuel-Cooled IDG Oil-Cooler

24-21-42 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FUEL COOLED IDG OIL COOLER (IDG FCOC)

A

B

71 BUSH A

77 BUSH B

75 PIN

A

LP COMPRESSOR / INTERMEDIATE CASE MODULE

76 PIN

B E1980 N_MM_242142_4_XEN0_01_00

AES

FIGURE 24-21-42-991-15200-B SHEET 1 Fuel-Cooled IDG Oil-Cooler

24-21-42 PB401

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-42-400-010-B Installation of the Fuel-Cooled IDG Oil-Cooler WARNING : DO NOT LET THE ENGINE OIL STAY ON YOUR SKIN FOR A LONG TIME. FLUSH OIL FROM YOUR SKIN WITH WATER. THE OIL IS POISONOUS AND CAN GO THROUGH YOUR SKIN AND INTO YOUR BODY. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific

B.

QTY AR WARNING NOTICE(S)

DESIGNATION

Torque wrench: range to between 30.00 and 220.00 LBF.IN (0.34 and 2.60 M.DAN)

Consumable Materials

REFERENCE Material No: V01-124 Material No: V02-147 Material No: V10-039

isopropyl alcohol lockwire engine oil

Material No: 19-003

LINT-FREE COTTON CLOTH

C.

DESIGNATION

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR D.

Expendable Parts

FIG.ITEM 66 60 54 59 57 1 2

DESIGNATION

E.

Referenced Information

REFERENCE 24-21-15-400-010-A 70-23-11-911-013-A

AES

IPC-CSN 24-21-42-80-060 24-21-42-80-070 24-21-42-80-100 24-21-42-80-100 24-21-42-80-130 24-21-42-80-180 24-21-42-80-180

sealing ring sealing ring sealing ring sealing ring sealing rings sealing ring packing

DESIGNATION Installation of the IDG Oil Temperature Thermocouple General Torque Tightening Techniques

24-21-42 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 70-23-13-911-010-A

DESIGNATION Procedures for the Installation of Preformed Packings

71-00-00-710-017-B

Ground Test Requirements after Power Plant Module/Component Repair or Replacement Procedures

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-42-991-15000-A - Fuel-Cooled IDG Oil-Cooler) (Ref. Fig. 24-21-42-991-15100-A - Fuel-Cooled IDG Oil-Cooler) (Ref. Fig. 24-21-42-991-15200-B - Fuel-Cooled IDG Oil-Cooler) (Ref. Fig. 24-21-42-991-15300-A - Fuel-Cooled IDG Oil-Cooler) 3.

Job Set-up Subtask 24-21-42-860-051-A A.

Aircraft Maintenance Configuration (1)

Make sure that the WARNING NOTICE(S) is (are) on the panel 115VU to tell persons not to start the engine 1(2).

(2)

Make sure that the WARNING NOTICE(S) is (are) on the panel 50VU to tell persons not to power supply the FADEC system.

Subtask 24-21-42-010-053-A B.

4.

Make sure that the fan cowls are open (Ref. TASK 71-13-00-010-010-A): (1)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(2)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Procedure Subtask 24-21-42-110-052-A A.

Cleaning of the Mounting Surfaces WARNING : DO NOT GET CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES. PUT ON PROTECTIVE CLOTHING, GOGGLES AND A FACE MASK. USE THE FLUID IN A WELL VENTILATED AREA. DO NOT BREATHE THE VAPOR. IF YOU GET THE CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES FLUSH IT AWAY WITH WATER. GET MEDICAL AID IF YOUR SKIN OR EYES BECOME IRRITATED. (1)

Use a LINT-FREE COTTON CLOTH (Material No: 19-003) , made moist with isopropyl alcohol (Material No: V01-124) to clean the mounting surfaces on the fan case.

Subtask 24-21-42-420-062-A B.

AES

Installation of the Fuel Drain Plug (Ref. Fig. 24-21-42-991-15000-A - Fuel-Cooled IDG Oil-Cooler) (1)

Lubricate the new (IPC-CSN 24-21-42-80) packing (2) with engine oil (Material No: V10-039) and install it on the fuel drain plug (3), (Ref. TASK 70-23-13-911-010-A).

(2)

Install the fuel drain plug on the fuel-cooled IDG oil-cooler.

24-21-42 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

TORQUE the fuel drain plug to between 40 and 65 LBF.IN (0.45 and 0.73 M.DAN), (Ref. TASK 70-23-11-911-013-A).

(4)

Safety the fuel drain plug to the fuel-cooled IDG oil-cooler with lockwire (Material No: V02-147) .

Subtask 24-21-42-420-063-A C.

Installation of the Oil Drain Plug (Ref. Fig. 24-21-42-991-15000-A - Fuel-Cooled IDG Oil-Cooler) (1)

Lubricate the new (IPC-CSN 24-21-42-80) sealing ring (1) with clean engine oil V10-039 and install it on the oil drain plug (4), (Ref. TASK 70-23-13-911-010-A).

(2)

Install the oil drain plug on the fuel-cooled IDG oil-cooler.

(3)

TORQUE the oil drain plug to between 40 and 65 LBF.IN (0.45 and 0.73 M.DAN), (Ref. TASK 70-23-11-911-013-A).

(4)

Safety the oil drain plug to the fuel-cooled IDG oil-cooler with the V02-147 lockwire.

Subtask 24-21-42-420-065-A D.

Installation of the Sealing Rings and the Seal Housing on the Fuel Tube (Ref. Fig. 24-21-42-991-15100-A - Fuel-Cooled IDG Oil-Cooler) (1)

Lubricate two new (IPC-CSN 24-21-42-80) sealing rings (57) with clean engine oil (Material No: V10-039) and install them on the fuel tube (55), (Ref. TASK 70-23-13-911-010-A).

(2)

Install the seal housing (58) on the fuel tube (55).

Subtask 24-21-42-420-066-A E.

Installation of the Fuel-Cooled IDG Oil-Cooler (Ref. Fig. 24-21-42-991-15200-B - Fuel-Cooled IDG Oil-Cooler) (1)

Put the bushes (71) and (77) into the mounting holes in the flanges of the fuel-cooled IDG oil-cooler.

(2)

Put the fuel-cooled IDG oil-cooler on the fan case flange.

(3)

Install the pin (75) through the fan case flange and into the bush (71).

(4)

Tighten the pin lightly.

(5)

Install the pin (76) through the fan case flange and into the bush (77).

(6)

Tighten the pin lightly.

(7)

TORQUE the pins (75) and (76) to between 85 and 105 LBF.IN (0.96 and 1.19 M.DAN), (Ref. TASK 70-23-11-911-013-A).

Subtask 24-21-42-420-067-A F.

Connection of the Seal Housing and the Fuel Tube to the Fuel-Cooled IDG Oil-Cooler (Ref. Fig. 24-21-42-991-15100-A - Fuel-Cooled IDG Oil-Cooler) (1)

Lubricate the new (IPC-CSN 24-21-42-80) sealing ring (59) with clean engine oil (Material No: V10-039) and install it in the seal housing (58), (Ref. TASK 70-23-13-911-010-A).

(2)

Attach the seal housing and the fuel tube to the fuel-cooled IDG oil-cooler with the bolts (56).

(3)

TORQUE the bolts to between 85 and 105 LBF.IN (0.96 and 1.19 M.DAN), (Ref. TASK 70-23-11-911-013-A).

Subtask 24-21-42-420-068-A G.

AES

Connection of the Fuel Tube to the Fuel-Cooled IDG Oil-Cooler (Ref. Fig. 24-21-42-991-15100-A - Fuel-Cooled IDG Oil-Cooler)

24-21-42 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (1)

Lubricate the new (IPC-CSN 24-21-42-80) sealing ring (54) with clean engine oil (Material No: V10-039) and install it on the fuel tube (51), (Ref. TASK 70-23-13-911-010-A).

(2)

Attach the fuel tube and the bracket (52) to the fuel-cooled IDG oil-cooler with the bolts (53).

(3)

TORQUE the bolts to between 85 and 105 LBF.IN (0.96 and 1.19 M.DAN), (Ref. TASK 70-23-11-911-013-A).

Subtask 24-21-42-420-069-A H.

Connection of the Oil Tube to the Fuel-Cooled IDG Oil-Cooler (Ref. Fig. 24-21-42-991-15100-A - Fuel-Cooled IDG Oil-Cooler) (1)

Lubricate the new (IPC-CSN 24-21-42-80) sealing ring (60) with clean engine oil (Material No: V10-039) and install it on the oil tube (63), (Ref. TASK 70-23-13-911-010-A).

(2)

Attach the oil tube and the bracket (61) to the fuel-cooled IDG oil-cooler with the bolts (62).

(3)

TORQUE the bolts to between 85 and 105 LBF.IN (0.96 and 1.19 M.DAN), (Ref. TASK 70-23-11-911-013-A).

Subtask 24-21-42-420-070-A J.

Connection of the Oil Tube to the Fuel-Cooled IDG Oil-Cooler (Ref. Fig. 24-21-42-991-15100-A - Fuel-Cooled IDG Oil-Cooler) (1)

Lubricate the new (IPC-CSN 24-21-42-80) sealing ring (66) with clean engine oil (Material No: V10-039) and install it on the oil tube (64), (Ref. TASK 70-23-13-911-010-A).

(2)

Attach the oil tube and the bracket (65) to the fuel-cooled IDG oil-cooler with the bolts (67).

(3)

TORQUE the bolts to between 85 and 105 LBF.IN (0.96 and 1.19 M.DAN), (Ref. TASK 70-23-11-911-013-A).

Subtask 24-21-42-420-071-A K.

Attachment of the Clips of the EEC Harness at Positions B, C, D and E (Ref. Fig. 24-21-42-991-15300-A - Fuel-Cooled IDG Oil-Cooler) (1)

Attach the harness (33) to the tube (35) with the clip (36), bolt (31), washer (32) and nut (34) at position E.

(2)

Attach the harness (42) to the tube (44) with the clip (45), bolt (41), washer (46) and nut (43) at position D.

(3)

Attach the harness (23) to the tube (25) with the clip (26), bolt (21), washer (22) and nut (24) at position C.

(4)

Attach the harness (14) to the tube (15) with the clip (11), bolt (12), washer (13) and nut (16) at position B.

(5)

TORQUE the bolts (31), (41), (21) and (12) and the nuts (34), (43), (24), and (16) to between 85 and 105 LBF.IN (0.96 and 1.19 M.DAN), (Ref. TASK 70-23-11-911-013-A).

Subtask 24-21-42-420-072-A L.

Installation of the Fuel-Cooled IDG Oil-Cooler Temperature Thermocouple (1)

Install the fuel-cooled IDG oil-cooler temperature thermocouple (Ref. TASK 24-21-15-400-010-A).

Subtask 24-21-42-790-051-A M.

Test for Fuel and Oil Leaks (1)

AES

Do a fuel and oil leak test (Ref. TASK 71-00-00-710-017-B).

24-21-42 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-21-42-410-051-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowls (Ref. TASK 71-13-00-410-010-A):

(3)

AES

(a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Remove the warning notice(s).

24-21-42 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

IDG OIL COOLER - FUEL COOLED - CLEANING/PAINTING ** On A/C ALL Task 24-21-42-100-040-A Cleaning of the Fuel Cooled IDG Oil Cooler 1.

Reason for the Job (Ref. MPD 24-21-00-10-) CLEAN INTEGRATED DRIVE GENERATOR (IDG) OIL COOLER.

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

437 447

FAN COWL FAN COWL B.

Referenced Information

REFERENCE 24-21-42-000-010-B 24-21-42-400-010-B CMM 24-21-42 3.

ZONE DESCRIPTION

DESIGNATION Removal of the Fuel-Cooled IDG Oil-Cooler Installation of the Fuel-Cooled IDG Oil-Cooler

Job Set-up Subtask 24-21-42-020-056-A A.

Removal of the Fuel-Cooled IDG Oil-Cooler (1)

4.

Remove the fuel-cooled IDG oil-cooler (Ref. TASK 24-21-42-000-010-B).

Procedure Subtask 24-21-42-110-051-A A.

Cleaning of the Fuel-Cooled IDG Oil-Cooler (1)

5.

Clean the fuel-cooled IDG oil-cooler (Ref. CMM 24-21-42).

Close-up Subtask 24-21-42-420-060-A A.

Installation of the Fuel-Cooled IDG Oil-Cooler (1)

AES

Install the fuel-cooled IDG oil-cooler (Ref. TASK 24-21-42-400-010-B).

24-21-42 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

IDG - CABLES - REMOVAL/INSTALLATION ** On A/C ALL Task 24-21-43-000-010-A Removal of the IDG Cables WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. 1.

Reason for the Job The removal/installation procedures for the IDG cable assembly are identical for both engines.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT)

No specific

AR

CAP - BLANKING

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR C.

Referenced Information

REFERENCE 24-92-00-000-001-A

DESIGNATION Removal of the IDG Feeders from the Pylon

24-92-00-400-001-A

Installation of the IDG Feeders on the Pylon

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-43-991-15000-A - IDG Cables) 3.

Job Set-up Subtask 24-21-43-860-050-A A.

Aircraft Maintenance Configuration (1)

On the center pedestal, on the ENG panel 115VU: (a)

AES

Put a WARNING NOTICE(S) to tell persons not to start the engine 1(2).

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

24-21-43 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-43-010-050-A B.

Get Access (1)

(2) 4.

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Put the ACCESS PLATFORM 2M (6 FT) into position on the right side of the engine.

Procedure (Ref. Fig. 24-21-43-991-15000-A - IDG Cables) Subtask 24-21-43-020-050-A A.

Removal of the IDG Cable Assembly from the Engine (1)

(2)

Remove the IDG terminal cover: (a)

Remove the screws (12) and the washers (11) from the terminal cover.

(b)

Remove the terminal cover.

Disconnect the IDG cables from the IDG: (a)

Remove the nuts (13) and the washers (14) from the four terminal posts. NOTE :

(b) (3)

Disconnect the four IDG cables.

Disconnect the electrical connector from the aircraft pylon receptacle. NOTE :

(4)

(5)

AES

Alternate configuration, remove the four terminal nuts with captive washer (15) from the four terminal posts.

If you find signs of arcing in the electrical connector, remove the harness in the pylon (Ref. TASK 24-92-00-000-001-A) and (Ref. TASK 24-92-00-400-001-A).

Remove the IDG cable clips and the cable clamp: (a)

Remove the six bolts (9) and the six nuts (8) from the clips (10).

(b)

Remove the six clips (10).

(c)

Remove the bolts (3) and (5) and the nuts (6) and (7) from the clamp (4).

(d)

Remove the clamp (4) and the support bushes from the IDG cable assembly (2).

Remove the IDG cable assembly from the engine: (a)

Remove the nut (1) from the terminal post.

(b)

Remove the IDG cable assembly (2).

(c)

Put blanking caps on the disconnected electrical connector(s).

24-21-43 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

DIMENSION X (Minimum) CABLE T1 AND T2 12.25 in (311 mm) CABLE T3 AND N 11.80 in (300 mm) DIMENSION X (Maximum) CABLE T1 AND T2 12.52 in (318 mm) CABLE T3 AND N 12.07 in (306 mm)

X

A

ELECTRICAL CONNECTOR

H

B

B

C

4 CLAMP

16 BOLT

5 BOLT

3 BOLT

C

15 BRACKET SUPPORT BRACKET

17 NUT

D

1 NUT 6 NUT

2 IDG CABLE ASSEMBLY

SUPPORT BUSHES

7 NUT

D

E

DETAIL AT 4 POSITIONS

D

DETAIL AT 2 POSITIONS

8 NUT (4 off)

10 CLIP 10 CLIP

8 NUT (2 off)

D 9 BOLT (2 off)

SUPPORT BRACKET

SUPPORT BRACKET 9 BOLT (4 off)

D

F TERMINAL COVER

E 15 CAPTIVE WASHER NUT

sh00012493d

IDG CABLE ASSEMBLY

AES

F 12 SCREW (2 off)

E

11 WASHER (2 off)

IDG

G

FIGURE 24-21-43-991-15000-A SHEET 1 IDG Cables

N_MM_242143_4_XAM0_01_01

24-21-43 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

G PHASE LEAD INSTALLATION

13

TERMINAL LUG

TERMINAL BLOCK STUD

TERMINAL BLOCK

GENERATOR TERMINAL LEAD ASSEMBLY

shv2500772

SQUARE WASHER

AES

N_MM_242143_4_XAM0_02_01

FIGURE 24-21-43-991-15000-A SHEET 2 IDG Cables

24-21-43 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

H INCORRECT ROUTING OF IDG HARNESS

1

H CORRECT ROUTING OF IDG HARNESS PYLON INTERFACE IDG CONNECTOR

X

DIMENSION X (Minimum) CABLE T1 AND T2 12.25 in (311 mm) CABLE T3 AND N 11.80 in (300 mm) DIMENSION X (Maximum) CABLE T1 AND T2 12.52 in (318 mm) CABLE T3 AND N 12.07 in (306 mm)

FLANGE FE

CLIP POSITION 0882

sh000b4793C

IDG HARNESS

AES

NOTE:

1

TOO MUCH BEND IN HARNESS MAY CAUSE FORCE ON THE CONNECTOR CONTACTS. N_MM_242143_4_XAM0_03_00

FIGURE 24-21-43-991-15000-A SHEET 3 IDG Cables

24-21-43 PB401

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-43-400-010-A Installation of the IDG Cables 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

WARNING NOTICE(S)

No specific

Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

No specific

Torque wrench: range to between 62.00 and 900.00 LBF.IN (0.70 and 10.00 M.DAN)

B.

Consumable Materials

REFERENCE Material No: V01-002 Material No: V02-147 Material No: 19-003 C.

DESIGNATION cleaning fluid lockwire LINT-FREE COTTON CLOTH

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR D.

Referenced Information

REFERENCE 31-60-00-860-001-A 70-23-11-911-013-A

DESIGNATION EIS Start Procedure General Torque Tightening Techniques

70-23-15-912-010-A 71-00-00-710-012-B 71-13-00-010-010-A

Connection of Electrical Connectors Test No.3 : Idle Leak Check Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

ESPM 20-48-23-0 (Ref. Fig. 24-21-43-991-15000-A - IDG Cables)

AES

24-21-43 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-21-43-860-051-A A.

Aircraft Maintenance Configuration (1)

On the center pedestal, on the panel 115VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the engine.

(2)

On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a WARNING NOTICE(S) is in position to tell persons not to energize the FADEC 1(2).

(3)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position.

Subtask 24-21-43-010-051-A B.

Get Access (1)

4.

Make sure that the fan cowl doors are open (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Procedure (Ref. Fig. 24-21-43-991-15000-A - IDG Cables) Subtask 24-21-43-110-050-A A.

Cleaning of the IDG Cable Assembly WARNING : DO NOT GET CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES. PUT ON PROTECTIVE CLOTHING, GOGGLES AND A FACE MASK. USE THE FLUID IN A WELL VENTILATED AREA. DO NOT BREATHE THE VAPOR. IF YOU GET THE CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES FLUSH IT AWAY WITH WATER. GET MEDICAL AID IF YOUR SKIN OR EYES BECOME IRRITATED. (1)

Use a LINT-FREE COTTON CLOTH (Material No: 19-003) made moist with cleaning fluid (Material No: V01-002) to clean the cable assembly (2).

(2)

Use a clean lint-free cloth to dry the cable assembly (2).

Subtask 24-21-43-220-051-A B.

Check of the Sockets (1)

Remove the blanking caps from the electrical connector(s).

(2)

Check the retention pin of each socket (Ref. ESPM 20-48-23-0).

(3)

Do not clean contacts with abrasive material.

(4)

Connect the electrical connector to the aircraft pylon receptacle (Ref. TASK 70-23-15-912-010-A)

(5)

Tighten the connector by hand until the orange color is shown in the coupling nut window. NOTE :

(6)

AES

When you tighten the connector, the torque value increases. This causes the connector to make clicks until it is fully engaged.

Safety the connector with lockwire (Material No: V02-147) .

24-21-43 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-43-420-050-A C.

Installation of the IDG Cable Assembly (1)

Attach the cable assembly (2) to the engine with the six clips (10), the six bolts (9) and the six nuts (8). NOTE :

(2)

Do not tighten the nuts at this step.

Attach the two cable ends to the terminal post on the bracket (15) with the nut (1). NOTE :

Do not tighten the nut at this step.

Subtask 24-21-43-420-051-A D.

Installation of the Clamp on the Support Bushes (1)

Put the support bushes on the IDG cable assembly (2).

(2)

Measure dimension X from the electrical connector to the support bushes.

(3)

Make sure dimension X is 12.25 in. (311 mm) minimum and 12.52 in. (318 mm) maximum for the T1 and T2 cables.

(4)

Make sure dimension X is 11.8 in. (300 mm) minimum and 12.25 in. (311 mm) maximum for the T3 and N cables. NOTE :

The cables are identified at their ends.

(5)

If dimension X is not the correct minimum distance, move the support bushes to get the correct distance.

(6)

Install the clamp (4) on the support bushes.

(7)

Attach the clamp (4) to the support bracket with the two bolts (3) and (5) and the two nuts (6) and (7).

** On A/C ALL EMB SB 71-1034 FOR A/C 003-008 Subtask 24-21-43-220-050-B E.

Check the bend on the IDG cable assembly. (1)

Make sure that there is not too much bend on the cable assembly (2) that will cause too much force on the connector contacts.

(2)

If there is too much bend on the cable assembly (2), adjust the cable routing and the bracket (15) as follows. (a)

Loosen the nuts (17) from the bolts (16).

(b)

Move the bracket (15) along the slots to remove the bend on the cable assembly.

(c)

TORQUE the nuts (17) to between 85 and 105 LBF.IN (0.96 and 1.19 M.DAN) ** On A/C ALL (Ref. TASK 70-23-11-911-013-A).

** On A/C ALL Subtask 24-21-43-420-052-A F.

Safety the fasteners. (1)

AES

TORQUE the nuts (8) to 40 LBF.IN (0.45 M.DAN) (Ref. TASK 70-23-11-911-013-A).

24-21-43 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

TORQUE the nuts (6) and (7) to 100 LBF.IN (1.13 M.DAN) (Ref. TASK 70-23-11-911-013-A).

(3)

TORQUE the nuts (1) to 110 LBF.IN (1.24 M.DAN) (Ref. TASK 70-23-11-911-013-A).

Subtask 24-21-43-420-053-A G.

Installation of the Phase Leads on the IDG (1)

Connect the IDG cables to the IDG. (a)

Attach the cable ends to the IDG terminal posts with the washers (14) and the nuts (13). NOTE :

(b)

TORQUE the nuts to between 144 and 168 LBF.IN (1.63 and 1.90 M.DAN) (Ref. TASK 70-23-11-911-013-A) NOTE :

(2)

The cable ends and the IDG terminals are identified as T1 (red) , T2 (yellow), T3 (blue) and N (white).

Alternate configuration, attach the cable ends to the terminal posts with the terminal nuts with captive washer (15). TORQUE the terminal nuts with captive washer (15) to between 144 and 168 LBF.IN (1.63 and 1.90 M.DAN).

Install the terminal cover. (a)

Attach the terminal cover to the IDG with the washers (11) and the screws (12).

(b)

TORQUE the screws to between 20 and 22 LBF.IN (0.23 and 0.25 M.DAN) (Ref. TASK 70-23-11-911-013-A).

Subtask 24-21-43-410-051-A H.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowl doors (Ref. TASK 71-13-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Subtask 24-21-43-710-050-A J.

Do an Idle Power Test (Ref. TASK 71-00-00-710-012-B) (1)

5.

Make sure that the IDG 1(2) operates correctly. (a)

Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(b)

On the ECAM control panel, push the ELEC key to get the ELEC page: . make sure that the voltage of the IDG is 115VAC . make sure that the frequency of the IDG is 400Hz + or - 5Hz.

Close-up Subtask 24-21-43-942-050-A A.

Put the aircraft back to its initial configuration (1)

AES

Remove the warning notice(s).

24-21-43 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

TUBING - IDG COOLER OIL - REMOVAL/INSTALLATION ** On A/C ALL Task 24-21-49-000-041-A Removal of the Tubings - IDG Cooling Oil WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. WARNING : DO NOT GET ENGINE OIL ON YOUR SKIN FOR A LONG TIME. FLUSH THE OIL FROM YOUR SKIN WITH WATER. THE OIL IS POISONOUS AND CAN GO THROUGH YOUR SKIN AND IN TO YOUR BODY. WARNING : WEAR GOGGLES, INSULATED GLOVES AND OTHER PROTECTIVE CLOTHES. HOT OIL CAN BURN YOUR EYES AND SKIN. IF OIL TOUCHES YOUR EYES OR SKIN, GET MEDICAL AID. CAUTION :

DO NOT LET ENGINE FUEL OR OIL FALL ON THE ENGINE. UNWANTED FUEL OR OIL MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT FREE CLOTH. THE FUEL OR OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS.

FIN 4000XU 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR CONTAINER 10 L(2 1/2 USGAL)

No specific

AR

FILLING EQUIPMENT - TANK OIL, DH13PM TYP

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR C.

Referenced Information

REFERENCE 71-13-00-010-010-A

DESIGNATION Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-49-991-90100-A - Tubings - IDG Cooling Oil)

AES

24-21-49 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-21-49-941-054-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

Put a WARNING NOTICE(S) to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off

(b)

Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Subtask 24-21-49-865-056-A B.

Open, safety and tag this(these) circuit breaker(s):

PANEL DESIGNATION FOR FIN 4000XU1000EM1 122VU ELEC/GCU/1 122VU

FIN

ELEC/IDG1/DISC

FOR FIN 4000XU1000EM2 122VU ELEC/GCU/2 122VU

ELEC/IDG2/DISC

LOCATION

2XU1

T26

1XT

T24

2XU2

T27

2XT

T25

Subtask 24-21-49-010-056-A C.

Get Access (1)

4.

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Procedure (Ref. Fig. 24-21-49-991-90100-A - Tubings - IDG Cooling Oil) Subtask 24-21-49-864-053-A A.

Depressurization of the IDG case. WARNING : YOU MUST PUT THE DRAIN HOSE INTO A CONTAINER BEFORE YOU CONNECT THE DRAIN HOSE TO THE OVERFLOW DRAIN HALF-COUPLING. MAKE SURE THAT THE DRAIN HOSE HANGS DOWN VERTICALLY AND THE END OF THE HOSE IS ABOVE THE OIL LEVEL IN THE CONTAINER. WHEN YOU CONNECT THE DRAIN HOSE TO THE IDG, YOU RELEASE THE OIL PRESSURE AND OIL WILL SPRAY FROM THE DRAIN HOSE.

AES

(1)

Put a CONTAINER 10 L(2 1/2 USGAL) in position under the IDG.

(2)

Remove the dust cap from the overflow drain half-coupling.

24-21-49 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Connect the overflow drain hose of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP to the overflow drain half-coupling. Oil can come out of the overflow drain hose of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP from the overflow drain half-coupling.

(4)

Disconnect the overflow drain hose of the FILLING EQUIPMENT - TANK OIL, DH13PM TYP from the overflow drain half-coupling.

(5)

Install the dust cap on the overflow drain half-coupling.

Subtask 24-21-49-020-059-A B.

Removal of the two Harness/Tubes WARNING : YOU MUST PUT THE DRAIN HOSE INTO A CONTAINER BEFORE YOU CONNECT THE DRAIN HOSE TO THE OVERFLOW DRAIN HALF-COUPLING. MAKE SURE THAT THE DRAIN HOSE HANGS DOWN VERTICALLY AND THE END OF THE HOSE IS ABOVE THE OIL LEVEL IN THE CONTAINER. WHEN YOU CONNECT THE DRAIN HOSE TO THE IDG, YOU RELEASE THE OIL PRESSURE AND OIL WILL SPRAY FROM THE DRAIN HOSE. (1)

Put the CONTAINER 10 L(2 1/2 USGAL) below the oil tubes (1) and (2).

(2)

Remove the five nuts (5) and the bolts (6).

(3)

Use temporary ties to hold the two harness/tubes (7) clear of the two oil tubes.

Subtask 24-21-49-020-057-A C.

Removal of the Oil Tubes from the IDG CAUTION :

MAKE SURE THAT THE COUPLINGS DO NOT TWIST. DAMAGE TO THE IDG BOSSES CAN OCCUR IF YOU DO NOT HOLD THE COUPLINGS.

CAUTION :

MAKE SURE THAT THE TUBES CANNOT TWIST. DAMAGE TO THE TUBES CAN OCCUR IF THEY DO TWIST.

(1)

At the gearbox bracket (8), remove the bolts (9) and (10) and the spacers (11) and (12).

(2)

Hold the coupling (3) and disconnect the oil inlet tube (1).

(3)

Hold the coupling (4) and disconnect the oil outlet tube (2).

(4)

Hold the tube (24), disconnect and remove the oil inlet tube (1).

(5)

Hold the tube (25), disconnect and remove the oil outlet tube (2).

(6)

Hold the tube (13), disconnect and remove the oil tube (24).

(7)

Hold the tube (14), disconnect and remove the oil tube (25).

Subtask 24-21-49-020-058-A D.

AES

Removal of the Oil Tubes from the IDG Oil Cooler (1)

Remove the bolts (15) and disconnect the oil tube (13) from the fuel cooled IDG oil cooler.

(2)

Remove and discard the sealing ring (16).

(3)

Remove the bolts (17) and disconnect the oil tube (14) from the fuel cooled IDG oil cooler.

(4)

Remove and discard the sealing ring (18).

24-21-49 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

15

A

16

A

IDG OIL COOLER

IDG

C

18

17

13

14 25

B

4 2 3

B C

B

B B

24 1

B

5

8 11 18

12

9

19

10

7 20

21

6

N_MM_242149_4_XAM0_01_00

AES

FIGURE 24-21-49-991-90100-A SHEET 1 Tubings - IDG Cooling Oil

24-21-49 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-49-400-041-A Installation of the Tubing - IDG Cooler Oil WARNING : DO NOT GET ENGINE OIL ON YOUR SKIN FOR A LONG TIME. FLUSH THE OIL FROM YOUR SKIN WITH WATER. THE OIL IS POISONOUS AND CAN GO THROUGH YOUR SKIN AND IN TO YOUR BODY. WARNING : WEAR GOGGLES, INSULATED GLOVES AND OTHER PROTECTIVE CLOTHES. HOT OIL CAN BURN YOUR EYES AND SKIN. IF OIL TOUCHES YOUR EYES OR SKIN, GET MEDICAL AID. CAUTION :

DO NOT LET ENGINE FUEL OR OIL FALL ON THE ENGINE. UNWANTED FUEL OR OIL MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT FREE CLOTH. THE FUEL OR OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS.

FIN 4000XU 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY AR WARNING NOTICE(S)

DESIGNATION

No specific

Torque wrench: range to between 62.00 and 900.00 LBF.IN (0.70 and 10.00 M.DAN)

No specific

Torque wrench: range to between 180.00 and 1800.00 LBF.IN (2.00 and 20.00 M.DAN)

B.

Consumable Materials

REFERENCE Material No: V10-039 C.

DESIGNATION engine oil

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR D.

Expendable Parts

FIG.ITEM 18 16

AES

DESIGNATION ring packing

IPC-CSN 24-21-42-80-060 24-21-42-80-070

24-21-49 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL E.

Referenced Information

REFERENCE 12-13-24-612-011-A 70-23-11-911-013-A

DESIGNATION IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check General Torque Tightening Techniques

70-23-13-911-010-A

Procedures for the Installation of Preformed Packings

70-30-00-918-010-A 71-00-00-710-017-B

Consumable Materials Index Ground Test Requirements after Power Plant Module/Component Repair or Replacement Procedures

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-49-991-90100-A - Tubings - IDG Cooling Oil) 3.

Job Set-up Subtask 24-21-49-860-052-A A.

Aircraft Maintenance Configuration (1)

Make sure that the WARNING NOTICE(S) is (are) on the panel 115VU to tell persons not to start the engine 1(2).

(2)

Make sure that the WARNING NOTICE(S) is (are) on the panel 50VU to tell persons not to power supply the FADEC system.

Subtask 24-21-49-865-057-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL DESIGNATION FOR FIN 4000XU1000EM1 122VU ELEC/GCU/1 122VU

ELEC/IDG1/DISC

FOR FIN 4000XU1000EM2 122VU ELEC/GCU/2 122VU

ELEC/IDG2/DISC

FIN

LOCATION

2XU1

T26

1XT

T24

2XU2

T27

2XT

T25

Subtask 24-21-49-010-057-A C.

Get Access (1)

4.

Make sure that the fan cowls are open (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Procedure (Ref. Fig. 24-21-49-991-90100-A - Tubings - IDG Cooling Oil)

AES

24-21-49 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-49-420-057-A A.

Installation of the IDG Oil Tubes on the IDG Oil Cooler (1)

Lubricate the new (IPC-CSN 24-21-42-80) ring (18) with clean engine oil (Material No: V10-039) and install it to the oil tube (14) (Ref. TASK 70-23-13-911-010-A).

(2)

Attach the oil tube to the fuel cooled IDG oil cooler with the bolts (17).

(3)

TORQUE the bolts to between 85 and 105 LBF.IN (0.96 and 1.19 M.DAN) (Ref. TASK 70-23-11-911-013-A).

(4)

Lubricate the new (IPC-CSN 24-21-42-80) packing (16) with clean engine oil (Material No: V10-039) and install it to the oil tube (13) (Ref. TASK 70-23-13-911-010-A).

(5)

Attach the oil tube to the fuel cooled IDG oil cooler with the bolts (15).

(6)

TORQUE the bolts to between 85 and 105 LBF.IN (0.96 and 1.19 M.DAN) (Ref. TASK 70-23-11-911-013-A).

Subtask 24-21-49-420-058-A B.

Installation of the Oil Tubes on the IDG CAUTION :

MAKE SURE THAT THE TUBES CANNOT TWIST. DAMAGE TO THE TUBES CAN OCCUR IF THEY DO TWIST.

CAUTION :

MAKE SURE THAT THE COUPLINGS DO NOT TWIST. DAMAGE TO THE IDG BOSSES CAN OCCUR IF YOU DO NOT HOLD THE COUPLINGS.

(1)

Lighly lubricate the end fittings on the oil tubes and the couplings with engine oil (Material No: V10-039) (Ref. TASK 70-30-00-918-010-A).

(2)

Connect the oil inlet tube (1) to the coupling (3).

(3)

Connect the oil inlet tube (2) to the coupling (4).

(4)

Put the oil tube (24) in to the correct position for installation between the tube (13) and the tube (1).

(5)

Put the oil tube (25) in to the correct position for installation between the tube (14) and the tube (2).

(6)

Hand tighten the three tubes on the connectors.

(7)

At the gearbox bracket (8) align the spacer (11) and the clip (18) and install the bolt (9).

(8)

At the gearbox bracket (8) align the spacer (12) and the clip (19) and install the bolt (10).

(9)

Hold the tube (24) and TORQUE the oil inlet tube (1) to between 844 and 945 LBF.IN (9.54 and 10.68 M.DAN) (Ref. TASK 70-23-11-911-013-A).

(10) Hold the tube (25) and TORQUE the oil outlet tube (2) to between 620 and 680 LBF.IN (7.01 and 7.68 M.DAN) (Ref. TASK 70-23-11-911-013-A). (11) Hold the tube (13) and TORQUE the oil tube (24) to between 844 and 945 LBF.IN (9.54 and 10.68 M.DAN) (Ref. TASK 70-23-11-911-013-A). (12) Hold the tube (14) and TORQUE the oil tube (25) to between 620 and 680 LBF.IN (7.01 and 7.68 M.DAN) (Ref. TASK 70-23-11-911-013-A). (13) Hold the oil outlet coupling (4) with a wrench and TORQUE the tube (2) to between 620 and 680 LBF.IN (7.01 and 7.68 M.DAN) (Ref. TASK 70-23-11-911-013-A). (14) Hold the oil inlet coupling (3) with a wrench and TORQUE the tube (1) to between 855 and 945 LBF.IN (9.66 and 10.68 M.DAN) (Ref. TASK 70-23-11-911-013-A).

AES

24-21-49 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-49-420-059-A C.

Installation of the two Harness/Tubes (1)

Remove the temporary ties from the two harness/tube assemblies.

(2)

Align the five clips (21) with the five support clips (20).

(3)

Make sure that the two harness/tube (7) assemblies are loose, have no tension and are clear or adjacent components and the structure.

(4)

Install the five bolts (6) and the nuts (5).

Subtask 24-21-49-612-053-A D.

Filling of the IDG with Oil (1)

Fill the IDG with oil (Ref. TASK 12-13-24-612-011-A).

Subtask 24-21-49-210-055-A E.

Visual Inspection for Oil Leaks (1)

Do a visual inspection for oil leaks at the IDG and the oil tubes. Leaks are not permitted.

Subtask 24-21-49-865-058-A F.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL DESIGNATION FOR FIN 4000XU1000EM1 122VU ELEC/GCU/1 122VU

FIN

ELEC/IDG1/DISC

FOR FIN 4000XU1000EM2 122VU ELEC/GCU/2 122VU

ELEC/IDG2/DISC

LOCATION

2XU1

T26

1XT

T24

2XU2

T27

2XT

T25

Subtask 24-21-49-790-050-A G.

Oil Leak Test (1)

5.

Do an oil leak test at the IDG and the oil tubes (Ref. TASK 71-00-00-710-017-B). Leaks are not permitted.

Close-up Subtask 24-21-49-410-054-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowls (Ref. TASK 71-13-00-410-010-A):

(3)

AES

(a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Remove the warning notice(s).

24-21-49 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

TUBING - IDG COOLER OIL - INSPECTION/CHECK ** On A/C ALL Task 24-21-49-200-010-A General Check of the IDG Oil Cooling Tubes WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY AR WARNING NOTICE(S)

DESIGNATION

Consumable Materials

REFERENCE Material No: V01-002

cleaning fluid

Material No: 19-003

LINT-FREE COTTON CLOTH

C.

DESIGNATION

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR D.

Referenced Information

REFERENCE 71-13-00-010-010-A

DESIGNATION Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-49-991-15000-A - IDG Oil-Cooling Tubes) 3.

Job Set-up Subtask 24-21-49-941-052-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

(2)

AES

Put a WARNING NOTICE(S) to tell persons not to start the engine.

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

24-21-49 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Subtask 24-21-49-010-054-A B.

Get Access (1)

4.

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR.

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Procedure Subtask 24-21-49-110-050-A A.

Cleaning of the IDG oil-cooling tubes (Ref. Fig. 24-21-49-991-15000-A - IDG Oil-Cooling Tubes) WARNING : DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: FLUSH IT AWAY WITH CLEAN WATER GET MEDICAL AID. (1)

Use a clean LINT-FREE COTTON CLOTH (Material No: 19-003) , made moist with cleaning fluid (Material No: V01-002) to clean the tubes.

(2)

Dry the tubes with a clean LINT-FREE COTTON CLOTH (Material No: 19-003) .

Subtask 24-21-49-210-052-A B.

Visual Inspection of the Oil Cooling Tubes for Security (Ref. Fig. 24-21-49-991-15000-A - IDG Oil-Cooling Tubes) (1)

Examine the IDG oil-cooling tubes for security. Use the inspection lamp and the inspection mirror.

(2)

If the IDG oil-cooling tubes are loose, examine the items below for damage, wear and loosening: (a)

The attachment nuts and bolts.

(b)

The clips.

(c)

The tube connection nuts. 1

If above items show signs of damage or wear, replace them.

Subtask 24-21-49-210-053-A C.

Visual Inspection of the Oil Cooling Tubes for Leaks (Ref. Fig. 24-21-49-991-15000-A - IDG Oil-Cooling Tubes) (1)

Examine the oil cooling tubes for leaks. Use the inspection lamp and the inspection mirror.

(2)

If leaks are found: (a)

Examine the attachment bolts and the tube connection nuts for loosening. 1

AES

If the bolts or nuts are loose, examine them for damage and wear. If the above items show signs of damage or wear, replace them.

24-21-49 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-49-210-054-A D.

Visual Inspection of the Oil Cooling Tubes for General Condition (Ref. Fig. 24-21-49-991-15000-A - IDG Oil-Cooling Tubes) (1)

Examine the general condition of the oil cooling tubes. Use the inspection lamp and the inspection mirror.

(2)

Examine the oil cooling tubes for cracks. (a)

(3)

Examine the tubes for nicks or scratches. (a)

(4)

If a tube is cracked, replace it.

If a tube has nicks or scratches, replace it.

Examine the tubes for dents (a)

If the straight area of a tube has dents, replace the tube.

(b)

If on the bend area : 1

Tube 1 has a dent, replace it.

2

Tube 2 or 3 :

3

4

(5)

has more than one dent, with less than 1.00 in. (25.4000 mm) between the edges of the dents, replace it.

b

has one or more dents with more than 1.00 in. (25.4000 mm) between the edges of the dents, with a depth up to 0.075 in. (1.9050 mm) and the radius of the dent not less than 0.056 in. (1.4224 mm), the tube is serviciable. . If the tube is out of the tolerances above, replace it.

Tube 4 or 5 : a

has more than one dent, with less than 1.00 in. (25.4000 mm) between the edges of the dents, replace it.

b

one or more dents with more than 1.00 in. (25.4000 mm) between the edges of the dents, with a deep Up to 0.063 in. (1.6002 mm) and the radius of the dent not less than 0.056 in. (1.4224 mm),the tube is serviciable. . If the tube is out of the tolerances above, replace it.

Tube 6 : a

has more than one dent, with less than 1.00 in. (25.4000 mm) between the edges of the dents, replace it.

b

one or more dents with more than 1.00 in. (25.4000 mm) between the edges of the dents, with a depth up to 0.070 in. (1.7780 mm) and the radius of the dent not less than 0.056 in. (1.4224 mm), the tube is serviciable. . If the tube is out of the tolerances above, replace it.

Examine the tubes for distortion (a)

AES

a

If on the bend area : 1

Tube 1 has distortion, replace it.

2

Tube 2 has a distortion more than 0.038 in. (0.9652 mm), replace it.

3

Tube 3 has a distortion of more than 0.050 in. (1.2700 mm) , replace it.

4

Tube 4 or 5 has a distortion of more than 0.025 in. (0.6350 mm), replace it.

5

Tube 6 has a distortion of more than 0.035 in. (0.8890 mm), replace it.

24-21-49 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (6)

5.

Examine the tubes for rubs (a)

If the straight area of a tube has rubs, replace the tube.

(b)

If on the bend area: 1

Tube 1, 2, 4, 5, or 6 has rubs, replace it.

2

Tube 3 has rubs of more than 0.010 in. (0.2540 mm), replace it.

Close-up Subtask 24-21-49-410-052-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowls (Ref. TASK 71-13-00-410-010-A):

(3)

AES

(a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR.

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Remove the warning notice(s).

24-21-49 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

TUBE 1

TUBE 3 TUBE 6

TUBE 2

TUBE 4

TUBE 5

N_MM_242149_6_XAM0_01_00

AES

FIGURE 24-21-49-991-15000-A SHEET 1 IDG Oil-Cooling Tubes

24-21-49 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

GENERATOR - INTEGRATED DRIVE (IDG) REMOVAL/INSTALLATION ** On A/C ALL Task 24-21-51-000-010-A Removal of the Integrated Drive Generator -IDG 1(2) WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. WARNING : DO NOT GET ENGINE OIL ON YOUR SKIN FOR A LONG TIME. FLUSH THE OIL FROM YOUR SKIN WITH WATER. THE OIL IS POISONOUS AND CAN GO THROUGH YOUR SKIN AND IN TO YOUR BODY. WARNING : BE CAREFUL DURING THE REMOVAL/INSTALLATION OF THE IDG. IT WEIGHS 124lb (60kg). DRY WEIGHT. CAUTION :

DO NOT LET ENGINE FUEL OR OIL FALL ON THE ENGINE. UNWANTED FUEL OR OIL MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT FREE CLOTH. THE FUEL OR OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS.

CAUTION :

DO NOT USE THE IDG CABLES FOR A HAND HOLD. IF THE IDG CABLES ARE PULLED LOOSE IT CAN CAUSE DAMAGE TO THE CABLES OR TO THE ENGINE.

1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY AR BAG - PLASTIC

No specific

AR

CAP - BLANKING

No specific

1

CONTAINER 10 L(2 1/2 USGAL)

No specific

AR

COVER - PROTECTION

No specific No specific

AR AR

PLUG - BLANKING SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

S888IDG

1

HOIST-ACCESSORY, IDG R/I FOR IAEV2500

TMHSD09-10-00

1

HOIST-ACCESSORY,IDG R/I FOR IAEV2500

B.

Work Zones and Access Panels ZONE/ACCESS

436 453 463

AES

DESIGNATION

ZONE DESCRIPTION FAN AND ACCESSORY GEARBOX HOT SECTION HOT SECTION

24-21-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR, 451AL, 452AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR, 461AL, 462AR C.

Referenced Information

REFERENCE 12-13-24-680-010-A

DESIGNATION Draining of the Oil from the IDG

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

78-32-00-010-010-A

Opening of the Thrust Reverser Halves

(Ref. Fig. 24-21-51-991-15200-A - Integrated Drive Generator (IDG)) (Ref. Fig. 24-21-51-991-15100-A - Integrated Drive Generator (IDG)) (Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG)) 3.

Job Set-up Subtask 24-21-51-941-050-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

Put a WARNING NOTICE(S) to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Subtask 24-21-51-865-050-A B.

Open, safety and tag this(these) circuit breaker(s):

PANEL DESIGNATION FOR FIN 4000XU1000EM1 122VU ELEC/GCU/1 122VU

FIN

ELEC/IDG1/DISC

FOR FIN 4000XU1000EM2 122VU ELEC/GCU/2 122VU

ELEC/IDG2/DISC

LOCATION

2XU1

T26

1XT

T24

2XU2

T27

2XT

T25

Subtask 24-21-51-010-050-A C.

Get Access (1)

AES

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

24-21-51 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

4.

Open the reverser cowls (Ref. TASK 78-32-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 451AL 452AR

(b)

FOR 1000EM2 (ENGINE-2) 461AL 462AR

Procedure Subtask 24-21-51-680-050-A A.

Draining of the Oil from the IDG System before you remove the Integrated Drive Generator (1)

Drain the IDG oil (Ref. TASK 12-13-24-680-010-A).

Subtask 24-21-51-020-051-A B.

Removal of the Electrical Harnesses (Ref. Fig. 24-21-51-991-15200-A - Integrated Drive Generator (IDG)) (1)

Disconnect the three electrical connectors (38)

(2)

Put blanking caps on the disconnected electrical connector(s).

Subtask 24-21-51-020-052-A C.

Removal of the Phase Leads (Ref. Fig. 24-21-51-991-15200-A - Integrated Drive Generator (IDG)) (1)

For IDG Serial No. 021 thru 051: (a)

(2)

For IDG Serial No. 052 and up: (a)

(3)

Remove the two bolts (27), the washers (28) and the cover (29) from the terminal block (30). Remove the two bolts (33), the washers (32) and the cover (31) from the terminal block (37).

Remove the four nuts (34) and the washers (35). NOTE :

Alternate configuration, remove the four terminal nuts with captive washer (40) from the four terminal studs.

(4)

Disconnect the four phase cables (39) from the IDG (1).

(5)

Use temporary ties and safety the four phase cables (39) and the three electrical connectors (38) away from the IDG (1).

Subtask 24-21-51-020-053-A D.

AES

Removal of the Oil-in and Oil-out Lines (Ref. Fig. 24-21-51-991-15100-A - Integrated Drive Generator (IDG)) (Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG))

CAUTION :

MAKE SURE THAT THE COUPLINGS DO NOT TWIST. DAMAGE TO THE IDG BOSSES CAN OCCUR IF YOU DO NOT HOLD THE COUPLINGS.

CAUTION :

MAKE SURE THAT THE TUBES CANNOT TWIST. DAMAGE TO THE TUBES CAN OCCUR IF THEY DO TWIST.

(1)

Put the CONTAINER 10 L(2 1/2 USGAL) below the oil tubes (52) and (53)

(2)

Remove the nut (54), the washer(s) (55) and the bolt (58).

24-21-51 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the nut (67), the washer(s) (68) and the bolt (71).

(4)

Remove the nut (72), the washer(s) (73) and the bolt (76).

(5)

Remove the nut (77), the washer(s) (78) and the bolt (80).

(6)

Use temporary ties to hold the harness away from the two oil tubes.

(7)

At the gearbox bracket (60), remove the bolts (63) and (64) and the spacers (61) and (66). NOTE :

Hold the two couplings (14) and (15) when you disconnect the oil tubes.

(8)

Hold the coupling (15) and disconnect the oil inlet tube (52).

(9)

Hold the coupling (14) and disconnect the oil outlet tube (53). NOTE :

Hold the tubes (51) and (50) when you loosen the connections.

(10) Hold the tube (50), disconnect and remove the oil inlet tube (52). (11) Hold the tube (51), disconnect and remove the oil outlet tube (53). Subtask 24-21-51-020-054-A E.

Removal of the transferable parts (Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG)) (1)

Make a note of the positions of the banjo couplings (14) and (15), they must be put in the same positions on installation.

(2)

Remove the banjo couplings (14) and (15).

(3)

Discard the seals (13) and (16).

(4)

Remove the overflow drain half-coupling (10) and the pressure fill half-coupling (11).

(5)

Discard the packings (9) and (12).

Subtask 24-21-51-480-050-A F.

Installation of the IDG Removal/Installation Tool (1)

Put the IDG removal/installation tool HOIST-ACCESSORY,IDG R/I FOR IAEV2500 (TMHSD09-10-00) or HOIST-ACCESSORY, IDG R/I FOR IAEV2500 (S888IDG). in position below the IDG.

(2)

Lift the attachment cradle to the IDG with the hydraulic pump on the IDG Removal/Installation Tool.

(3)

Attach the tool to the IDG.

Subtask 24-21-51-020-050-A G.

Removal of the IDG from the Engine Gearbox (Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG))

WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU. CAUTION :

AES

PULL THE IDG OUT IN A STRAIGHT LINE: SO THAT THE INPUT SHAFT DOES NOT RUB TO PREVENT DAMAGE TO THE IDG INPUT SEAL.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL CAUTION :

DO NOT USE EXTERNAL PARTS TO PULL OR LIFT THE IDG. IF YOU DO SO YOU CAN CAUSE DAMAGE TO THE IDG.

(1)

Cut and remove the lockwire from the QAD coupling (4).

(2)

Loosen the QAD tension bolt (4) until: . The screw head touches the lug on the QAD ring, or . The stripe marks on the QAD ring align with the housing of the IDG. NOTE :

The QAD kit is in the ”open position” and the clamping lugs are disengaged when the stripe marks are aligned.

(3)

If the tension bolt (4) does not turn the QAD ring to the aligned/open position: . Turn the QAD ring by hand, or . Lightly hit the ring up to the aligned position.

(4)

Remove the IDG. CAUTION :

(a)

BE VERY CAREFUL WHEN YOU REMOVE THE IDG FROM THE ACCESSORY GEARBOX. THIS WILL HELP TO PREVENT DAMAGE TO THE ADJACENT ENGINE PARTS.

Carefully pull the IDG (1) rearwards from the gearbox and remove it.

(5)

Remove and discard the packings (2) and (7).

(6)

Remove the container and discard all drained oil.

(7)

Put blanking plugs on the disconnected line ends.

(8)

Put blanking caps on the disconnected electrical connector(s).

(9)

Install the COVER - PROTECTION on the IDG interface side of the gearbox (6).

(10) Protect the IDG (1) with a BAG - PLASTIC.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A A 27 BOLT 28 WASHER

ALTERNATIVE (SERIAL N° 021 TO 051)

29 COVER 30 TERMINAL BLOCK 32 WASHER

31 COVER 33 BOLT

T1 39 PHASE CABLES

34 NUT 35 WASHER

T2 T3

36 SQUARE WASHER

N 37 TERMINAL BLOCK 38 ELECTRICAL CONNECTORS QAD COUPLING LIFTING BOSS

FWD

14110A N_MM_242151_4_XEM0_01_00

AES

FIGURE 24-21-51-991-15200-A SHEET 1 Integrated Drive Generator (IDG)

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

PHASE LEAD INSTALLATION

34 40 35 ALTERNATE CONFIGURATION

TERMINAL LUG

TERMINAL BLOCK STUD SQUARE WASHER TERMINAL BLOCK

GENERATOR TERMINAL LEAD ASSEMBLY

N_MM_242151_4_XEM0_02_00

AES

FIGURE 24-21-51-991-15200-A SHEET 2 Integrated Drive Generator (IDG)

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

N_MM_242151_4_XCM0_01_00

AES

FIGURE 24-21-51-991-15100-A SHEET 1 Integrated Drive Generator (IDG)

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

54 NUT

67 NUT

55 WASHER

68 WASHER EEC HARNESS

56 CLIP

EEC HARNESS

69 CLIP

57 CLIP

70 CLIP TUBE 100 F W D

55 WASHER

TUBE 100

68 WASHER

58 BOLT

71 BOLT

C

D

CLIP POINT 1123 PRE SBE 71−0288

CLIP POINT 1124 PRE SBE 71−0288

72 NUT 73 WASHER

77 BOLT EEC HARNESS 78 WASHER 74 CLIP

TUBE 100

75 CLIP 73 WASHER

EEC HARNESS 79 CLIP TUBE 100

76 BOLT 80 NUT

E CLIP POINT 1125 PRE SBE 71−0288

F CLIP POINT 1043 PRE SBE 71−0288 N_MM_242151_4_XCM0_02_00

AES

FIGURE 24-21-51-991-15100-A SHEET 2 Integrated Drive Generator (IDG)

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 54 NUT

67 NUT EEC FAN CASE AND IGNITION SUPPLY HARNESS

56 CLIP

57 CLIP

EEC FAN CASE AND IGNITION SUPPLY HARNESS

69 CLIP

70 CLIP TUBE 100

55 WASHER

TUBE 100

F W D

58 BOLT

68 WASHER 71 BOLT

D

C CLIP POINT 1123 POST SBE 71−0288

CLIP POINT 1124 POST SBE 71−0288

74 CLIP

72 NUT 77 BOLT EEC FAN CASE AND IGNITION SUPPLY HARNESS

TUBE 100

75 CLIP

EEC FAN CASE AND IGNITION SUPPLY HARNESS

79 CLIP

TUBE 100

73 WASHER 80 NUT

76 BOLT

F E

CLIP POINT 1043 POST SBE 71−0288

CLIP POINT 1125 POST SBE 71−0288 N_MM_242151_4_XCM0_03_00

AES

FIGURE 24-21-51-991-15100-A SHEET 3 Integrated Drive Generator (IDG)

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

LOCKWIRE

A A 3 TOP V2500 1 IDG 2 PACKING

4 QAD COUPLING

16 SEAL 15 COUPLING (INLET)

5 OPEN MARK

14 COUPLING (OUTLET)

8 OPEN MARK

13 SEAL

7 PACKING 6 GEARBOX

9 PACKING 12 PACKING 10 OVERFLOW DRAIN HALF−COUPLING 11 PRESSURE−FILL HALF−COUPLING

N_MM_242151_4_XAM0_01_00

AES

FIGURE 24-21-51-991-15000-A SHEET 1 Integrated Drive Generator (IDG)

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-51-400-010-A Installation of the Integrated Drive Generator -IDG 1(2) WARNING : DO NOT GET ENGINE OIL ON YOUR SKIN FOR A LONG TIME. FLUSH THE OIL FROM YOUR SKIN WITH WATER. THE OIL IS POISONOUS AND CAN GO THROUGH YOUR SKIN AND IN TO YOUR BODY. WARNING : BE CAREFUL DURING THE REMOVAL/INSTALLATION OF THE IDG. IT WEIGHS 124lb (60kg). DRY WEIGHT. CAUTION :

DO NOT LET ENGINE FUEL OR OIL FALL ON THE ENGINE. UNWANTED FUEL OR OIL MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT FREE CLOTH. THE FUEL OR OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS.

CAUTION :

DO NOT USE THE IDG CABLES FOR A HAND HOLD. IF THE IDG CABLES ARE PULLED LOOSE IT CAN CAUSE DAMAGE TO THE CABLES OR TO THE ENGINE.

1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY AR CAP - DUST

No specific

AR

DESIGNATION

WARNING NOTICE(S)

No specific

Torque wrench: range to between 2.00 and 26.00 LBF.FT (0.20 and 3.60 M.DAN)

No specific

Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

No specific

Torque wrench: range to between 30.00 and 220.00 LBF.IN (0.34 and 2.60 M.DAN)

No specific

Torque wrench: range to between 180.00 and 1800.00 LBF.IN (2.00 and 20.00 M.DAN)

S888IDG

1

HOIST-ACCESSORY, IDG R/I FOR IAEV2500

TMHSD09-10-00

1

HOIST-ACCESSORY,IDG R/I FOR IAEV2500

B.

Consumable Materials

REFERENCE Material No: V01-002 Material No: V02-147 Material No: V10-039

cleaning fluid lockwire engine oil

Material No: 19-003

LINT-FREE COTTON CLOTH

C.

Work Zones and Access Panels ZONE/ACCESS

436

AES

DESIGNATION

ZONE DESCRIPTION FAN AND ACCESSORY GEARBOX

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ZONE/ACCESS 453 463 FOR FIN 1000EM1(ENGINE-1)

ZONE DESCRIPTION HOT SECTION HOT SECTION

437AL, 438AR, 451AL, 452AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR, 461AL, 462AR D.

Expendable Parts

FIG.ITEM 7 2 9 12 16 13

DESIGNATION

IPC-CSN 24-21-51-82-010 24-21-51-82-020 24-21-51-85-050 24-21-51-85-080 24-21-51-85-100 24-21-51-85-120

packing packing packing packing seal seal E.

Referenced Information

REFERENCE 12-13-24-612-011-A 24-21-00-720-042-A

DESIGNATION IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check Operational Test of the IDG Disconnect and Reconnect (Reset) Function Engine in Operation

24-21-00-730-041-A

System Test of the IDG Frequency (P/N 766219)

70-23-11-911-013-A

General Torque Tightening Techniques

70-23-13-911-010-A

Procedures for the Installation of Preformed Packings

70-23-15-912-010-A 70-30-00-918-010-A 71-00-00-710-043-A

Connection of Electrical Connectors Consumable Materials Index Normal Engine Automatic Start Procedure

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

78-32-00-010-010-A

Opening of the Thrust Reverser Halves

78-32-00-410-010-A

Closing of the Thrust Reverser Halves

(Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG)) (Ref. Fig. 24-21-51-991-15100-A - Integrated Drive Generator (IDG)) (Ref. Fig. 24-21-51-991-15200-A - Integrated Drive Generator (IDG)) 3.

Job Set-up Subtask 24-21-51-860-050-A A.

Aircraft Maintenance Configuration (1)

AES

On the center pedestal, on the ENG panel 115VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the engine.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a WARNING NOTICE(S) is in position to tell persons not to energize the FADEC 1(2).

Subtask 24-21-51-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL DESIGNATION FOR FIN 4000XU1000EM1 122VU ELEC/GCU/1 122VU

ELEC/IDG1/DISC

FOR FIN 4000XU1000EM2 122VU ELEC/GCU/2 122VU

ELEC/IDG2/DISC

FIN

LOCATION

2XU1

T26

1XT

T24

2XU2

T27

2XT

T25

Subtask 24-21-51-010-053-A C.

Make sure that the fan cowls are open (Ref. TASK 71-13-00-010-010-A): (1)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(2)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Subtask 24-21-51-010-067-A D.

4.

Make sure the reverser cowls are open (Ref. TASK 78-32-00-010-010-A): (1)

FOR 1000EM1 (ENGINE-1) 451AL 452AR

(2)

FOR 1000EM2 (ENGINE-2) 461AL 462AR

Procedure Subtask 24-21-51-110-050-A A.

Preparation of the Replacement IDG (Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG)) (1)

Remove the protective cover from the IDG interface side of the gearbox (6).

(2)

Remove the IDG (1) from the plastic bag.

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Remove the blanking plugs from the disconnected line ends.

(5)

Make sure that the two couplings (14) and (15) have been removed

(6)

Clean the component WARNING : DO NOT GET CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES. PUT ON PROTECTIVE CLOTHING, GOGGLES AND A FACE MASK. USE THE FLUID IN A WELL VENTILATED AREA. DO NOT BREATHE THE VAPOR. IF YOU GET THE CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES FLUSH IT AWAY WITH WATER. GET MEDICAL AID IF YOUR SKIN OR EYES BECOME IRRITATED.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (a)

Use a clean LINT-FREE COTTON CLOTH (Material No: 19-003) , made moist with cleaning fluid (Material No: V01-002) to clean these components: . the IDG flange on the gearbox (6) . the IDG (1) mounting flange . the QAD coupling (4).

(b)

Dry the components with a clean LINT-FREE COTTON CLOTH (Material No: 19-003) .

Subtask 24-21-51-420-054-A B.

Installation of the IDG Removal/Installation Tool (1)

Attach the IDG to the IDG removal/installation tool, HOIST-ACCESSORY,IDG R/I FOR IAEV2500 (TMHSD09-10-00) or HOIST-ACCESSORY, IDG R/I FOR IAEV2500 (S888IDG).

Subtask 24-21-51-420-055-A C.

Preparation for Installation of the IDG (1)

Install new (IPC-CSN 24-21-51-82) packing (2) and (IPC-CSN 24-21-51-82) packing (7) on the IDG (1) (Ref. TASK 70-23-13-911-010-A)

(2)

Put the QAD coupling (4) in position on the gearbox (6).

(3)

Make sure that the coupling is fully open.

(4)

Turn the QAD coupling (4) until the arrow ’TOP V2500’ (3) is at the top center and the OPEN mark (5) is aligned with the adjacent gearbox mark.

Subtask 24-21-51-640-050-A D.

Lubricate these components with engine oil (Material No: V10-039) (Ref. TASK 70-30-00-918-010-A) (Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG)) . the packings (2) and (7), . the IDG (1) drive shaft, . the QAD coupling (4).

Subtask 24-21-51-210-050-A E.

Visual Inspection of the Mounting Pad (1)

Make sure that the mounting pad has no damage.

Subtask 24-21-51-420-050-A F.

Installation of the IDG to Engine Gearbox (Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG)) WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU.

AES

CAUTION :

DO NOT USE EXTERNAL PARTS TO PULL OR LIFT THE IDG. IF YOU DO SO YOU CAN CAUSE DAMAGE TO THE IDG.

CAUTION :

BE CAREFUL TO SUPPORT THE IDG CORRECTLY. YOU CAN CAUSE DAMAGE TO THE INPUT SEAL IF: YOU LIFT THE IDG TOO MUCH YOU DO NOT SUPPORT THE IDG SUFFICIENTLY.

CAUTION :

MAKE SURE YOU INSTALL THE IDG CORRECTLY. IF NOT YOU CAN CAUSE DAMAGE TO MATING PARTS.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL CAUTION :

BE VERY CAREFUL WHEN YOU INSTALL THE IDG ON THE ACCESSORY GEARBOX. THIS WILL HELP TO PREVENT DAMAGE TO THE ADJACENT ENGINE PARTS.

(1)

Put the IDG (1) in position on the gearbox (6).

(2)

Carefully align the IDG drive shaft and the gearbox output shaft.

(3)

Push the IDG (1) forward onto the gearbox (6).

(4)

Make sure that the mounting flanges are correctly aligned.

(5)

Make sure that the two OPEN marks (5) and (8) are aligned.

(6)

Make sure that the IDG (1) is correctly engaged in the QAD coupling (4).

(7)

Tighten the QAD coupling (4) until the IDG flange lugs are fully engaged in the QAD coupling lugs.

(8)

Make sure that the QAD coupling turns easily and does not catch.

(9)

TORQUE the QAD coupling (4) to between 264 and 313 LBF.IN (2.98 and 3.54 M.DAN) (Ref. TASK 70-23-11-911-013-A).

(10) Lightly hit the QAD coupling circumference to center it and make sure that the torque values are correct. (11) Do a check of the torque value on the QAD coupling (4). (12) Make sure that the torque has not decreased by more than 24 lbf.in (0.27 m.daN) from the torque given in step (9). (13) If necessary, do steps (9) thru (12) again. (14) Make sure that the torque value of the QAD coupling is between the limits given in step (9). (15) Safety the QAD coupling with lockwire (Material No: V02-147) . (16) Remove the IDG removal/installation tool. Subtask 24-21-51-110-051-A G.

Cleaning of the transferable parts (Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG)) WARNING : DO NOT GET CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES. PUT ON PROTECTIVE CLOTHING, GOGGLES AND A FACE MASK. USE THE FLUID IN A WELL VENTILATED AREA. DO NOT BREATHE THE VAPOR. IF YOU GET THE CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES FLUSH IT AWAY WITH WATER. GET MEDICAL AID IF YOUR SKIN OR EYES BECOME IRRITATED. (1)

Use a clean LINT-FREE COTTON CLOTH (Material No: 19-003) made moist with cleaning fluid (Material No: V01-002) to clean the components: . the overflow drain half-coupling (10) . the pressure fill half-coupling (11) . the couplings (14) and (15) . the applicable parts on the IDG (1).

(2)

Dry the components with a clean LINT-FREE COTTON CLOTH (Material No: 19-003) .

Subtask 24-21-51-640-051-A H.

Lubrication of the Packings and Seals (Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG)) (1)

AES

Lubricate these components with engine oil (Material No: V10-039) (Ref. TASK 70-30-00-918-010-A) . the packings (9) and (12),

24-21-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL .

the seals (13) and (16).

Subtask 24-21-51-420-056-A J.

Installation of the Transferable Parts (Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG)) (1)

(2)

Installation of the overflow drain half-coupling (10) (a)

Put a new (IPC-CSN 24-21-51-85) packing (9) on the overflow drain half-coupling (10) (Ref. TASK 70-23-13-911-010-A).

(b)

Install the overflow drain half-coupling (10) on the IDG (1).

(c)

TORQUE the overflow drain half-coupling (10) to between 20 and 25 LBF.FT (2.71 and 3.39 M.DAN) (Ref. TASK 70-23-11-911-013-A).

(d)

Put the CAP - DUST on the overflow drain half-coupling (10).

Installation of the pressure fill half-coupling (11) (a)

Put a new (IPC-CSN 24-21-51-85) packing (12) on the pressure fill half-coupling (11) (Ref. TASK 70-23-13-911-010-A).

(b)

Install the pressure fill half-coupling (11) on the IDG (1).

(c)

TORQUE the pressure fill half-coupling (11) to between 10 and 15 LBF.FT (1.36 and 2.03 M.DAN) (Ref. TASK 70-23-11-911-013-A).

(d)

Put the CAP - DUST on the pressure fill half-coupling (11).

Subtask 24-21-51-420-051-A K.

Installation of the Oil-in and Oil-out lines (Ref. Fig. 24-21-51-991-15100-A - Integrated Drive Generator (IDG)) (Ref. Fig. 24-21-51-991-15000-A - Integrated Drive Generator (IDG)) (1)

Lightly lubricate the end fittings on the oil tubes and the couplings with engine oil (Material No: V10-039) (Ref. TASK 70-30-00-918-010-A).

(2)

Put a new (IPC-CSN 24-21-51-85) seal (13) on the coupling (14) (Ref. TASK 70-23-13-911-010-A).

(3)

Loosely install the coupling (14) on the IDG (1) and align the temporary marks.

(4)

Put a new (IPC-CSN 24-21-51-85) seal (16) on the coupling (15) (Ref. TASK 70-23-13-911-010-A).

(5)

Loosely install the coupling (15) on the IDG (1) and align the temporary marks.

(6)

Put the oil inlet tube (52) in the correct position for installation between the tube (50) and the coupling (15).

(7)

Put the oil outlet tube (53) in the correct position for installation between the tube (51) and the coupling (14).

(8)

Hand tighten the two tubes on the connectors.

(9)

At the gearbox bracket (60), align the spacer (61) and the clip (62) and install the bolt (63).

(10) At the gearbox bracket (60), align the spacer (66) and the clip (65) and install the bolt (64). (11) TORQUE the tubes CAUTION :

AES

MAKE SURE THAT THE TUBES CANNOT TWIST. DAMAGE TO THE TUBES CAN OCCUR IF THEY DO TWIST.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (a)

Hold the tube (51) and TORQUE the oil outlet tube (53) to between 620 and 680 LBF.IN (7.01 and 7.68 M.DAN) (Ref. TASK 70-23-11-911-013-A). NOTE :

(b)

Hold the tubes (51) and (50) when you tighten the connections.

Hold the tube (50) and TORQUE the oil inlet tube (52) to between 844 and 945 LBF.IN (9.54 and 10.68 M.DAN) (Ref. TASK 70-23-11-911-013-A).

(12) Hold the outlet coupling (14) with a wrench and TORQUE the collar to between 300 and 350 LBF.IN (3.39 and 3.96 M.DAN) (Ref. TASK 70-23-11-911-013-A). (13) Hold the inlet coupling (15) with a wrench and TORQUE the collar to between 320 and 370 LBF.IN (3.62 and 4.18 M.DAN) (Ref. TASK 70-23-11-911-013-A). (14) TORQUE the tubes CAUTION :

(a)

MAKE SURE THAT THE COUPLINGS DO NOT TWIST. DAMAGE TO THE IDG BOSSES CAN OCCUR IF YOU DO NOT HOLD THE COUPLINGS.

Hold the oil outlet coupling (14) with a wrench and TORQUE the tube (51) to between 620 and 680 LBF.IN (7.01 and 7.68 M.DAN) (Ref. TASK 70-23-11-911-013-A). NOTE :

(b)

Hold the coupling (14) and (15) when you tighten the oil tubes.

Hold the oil inlet coupling (15) with a wrench and TORQUE the tube (50) to between 855 and 945 LBF.IN (9.66 and 10.68 M.DAN) (Ref. TASK 70-23-11-911-013-A).

Subtask 24-21-51-420-052-A L.

Installation of the two Harness/Tubes (Ref. Fig. 24-21-51-991-15100-A - Integrated Drive Generator (IDG)) CAUTION :

(1)

Remove the temporary ties from the two harness/tube assemblies.

(2)

Install the harness and tube at position C.

(3)

(4)

AES

MAKE SURE CLIP POINT 1125 AND CLIP POINT 1124 HOLD THE HARNESS INBOARD OF THE OIL TUBE. DAMAGE CAN OCCUR TO THE HARNESS IF HELD OUTBOARD.

(a)

Align the clip (56) with the support clip (57).

(b)

Make sure that two harness/tube assemblies are loose, have no tension and are away from or adjacent components and the structure.

(c)

Install the bolt (58), washer(s) (55) and the nut (54).

Install the harness and the tube at position D. (a)

Align the clip (69) with the support clip (70).

(b)

Make sure that two harness/tube assemblies are loose, have no tension and are away from or adjacent components and the structure.

(c)

Install the bolt (71), washer(s) (68) and the nut (67).

Install the harness and the tube at position E. (a)

Align the clip (74) with the support clip (75)

(b)

Make sure that two harness/tube assemblies are loose, have no tension and are away from or adjacent components and the structure.

(c)

Install the bolt (76), washer(s) (73) and the nut (72).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (5)

Install the harness and tube at position F (a)

Align the clip (79) with the lug.

(b)

Make sure that two harness/tube assemblies are loose, have no tension and are away from or adjacent components and the structure.

(c)

Install the bolt (77), washer (78) (if applicable) and the nut (80).

Subtask 24-21-51-420-053-A CAUTION :

M.

IF THE WASHERS ARE NOT INSTALLED CORRECTLY THE TERMINAL BLOCK CAN BECOME HOT AND BURN.

Installation of the Phase Leads and Electrical Connectors (Ref. TASK 70-23-15-912-010-A) to the IDG (Ref. Fig. 24-21-51-991-15200-A - Integrated Drive Generator (IDG)) NOTE :

The square washers (36) must be installed between the IDG output cables and the terminal block. The round washers (35) must be installed between the phase cables (39) and the nuts (34).

(1)

Remove the temporary ties from the four phase cables (39) and the three electrical connectors (38).

(2)

Make sure that the IDG ouptut cables and the square washers (36) are in the correct position on the terminal block.

(3)

Put the four phase cables (39) in the correct position for installation on the terminal block.

(4)

Install the four round washers and the four nuts (34). TORQUE the nuts (34) to between 144 and 168 LBF.IN (1.63 and 1.90 M.DAN) (Ref. TASK 70-23-11-911-013-A). NOTE :

(5)

(6)

Alternate configuration, install the four terminal nuts with captive washer (40) on the four terminal studs. TORQUE the terminal nuts with captive washer (40) to between 144 and 168 LBF.IN (1.63 and 1.90 M.DAN).

Install the terminal block cover for IDG Serial No. 021 thru 051 (a)

Put the cover (29) in the correct position for installation on the terminal block (30).

(b)

Install the washers (28) and the bolts (27).

(c)

TORQUE the bolts (27) to between 20 and 22 LBF.IN (0.23 and 0.25 M.DAN) (Ref. TASK 70-23-11-911-013-A).

Install the terminal block cover for IDG Serial No. 052 and up (a)

Put the cover (31) in the correct position for installation on the terminal block (37).

(b)

Install the washers (32) and the bolts (33).

(c)

TORQUE the bolts (33) to between 20 and 22 LBF.IN (0.23 and 0.25 M.DAN) (Ref. TASK 70-23-11-911-013-A).

(7)

Make sure that the three electrical connectors (38) are clean.

(8)

Connect the three electrical connectors (38) to the IDG and tighten them manually. NOTE :

On connector 4000XU-C, play is permitted. Damage can occur if you try to tighten the connector too much to remove this play.

Subtask 24-21-51-612-050-A N.

Filling of the IDG (1)

AES

Fill the IDG with oil (Ref. TASK 12-13-24-612-011-A).

24-21-51 PB401

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-51-410-063-A P.

Close the reverser cowls (Ref. TASK 78-32-00-410-010-A): (1)

FOR 1000EM1 (ENGINE-1) 451AL 452AR

(2)

FOR 1000EM2 (ENGINE-2) 461AL 462AR

Subtask 24-21-51-865-052-A Q.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL DESIGNATION FOR FIN 4000XU1000EM1 122VU ELEC/GCU/1 122VU

ELEC/IDG1/DISC

FOR FIN 4000XU1000EM2 122VU ELEC/GCU/2 122VU

ELEC/IDG2/DISC

FIN

LOCATION

2XU1

T26

1XT

T24

2XU2

T27

2XT

T25

Subtask 24-21-51-710-050-A R.

Operational Test of the IDG (1)

Do an operational test (Ref. TASK 24-21-00-720-042-A). Check the IDG output values.

Subtask 24-21-51-720-051-A S.

Check of the Oil Leaks and the Electrical Characteristics (1)

At the first engine start-up: (a)

Make sure that the IDG operates correctly: . on the lower ECAM DU, get the ELEC page, . do a check of the voltage (115 VAC), . do a check of the frequency (400 Hz, + or - 5 Hz). If the frequency is out, adjust the IDG frequency (Ref. TASK 24-21-00-730-041-A). NOTE :

(b)

Make sure that there are no oil leaks. NOTE :

(c) 5.

If the IDG has been removed after an IDG disconnection, do a GCU reset at first engine start-up at idle. To do this, push (ON) then release (OFF) the related GEN pushbutton switch.

We recommend that you do a visual inspection to make sure there are no oil leaks at the cover of the IDG oil filter. Do this inspection at the subsequent engine start, at minimum idle (Ref. TASK 71-00-00-710-043-A) . At this time, the oil pressure in the lubrification system and the cooling system of the IDG is higher and the oil circulation time is longer.

Do a check of the oil level. (Ref. TASK 12-13-24-612-011-A)

Close-up Subtask 24-21-51-410-050-A A.

Close Access (1)

AES

Make sure that the work area is clean and clear of tool(s) and other items.

24-21-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

(3)

AES

Close the fan cowls (Ref. TASK 71-13-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Remove the warning notice(s).

24-21-51 PB401

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-51-000-011-A Removal of the IDG Oil Filter(s) WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. WARNING : WEAR GOGGLES, INSULATED GLOVES AND OTHER PROTECTIVE CLOTHES. HOT OIL CAN BURN YOUR EYES AND SKIN. IF OIL TOUCHES YOUR EYES OR SKIN, GET MEDICAL AID. CAUTION :

1.

DO NOT LET ENGINE OIL FALL ON THE ENGINE. UNWANTED OIL MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT FREE CLOTH THE OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY AR CAP - BLANKING

No specific

AR

CONTAINER 10 L(2 1/2 USGAL)

No specific

AR

WARNING NOTICE(S)

B.

DESIGNATION

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR C.

Referenced Information

REFERENCE 12-13-24-680-010-A

DESIGNATION Draining of the Oil from the IDG

24-21-00-210-045-A

Inspection of the Filter Element(s)

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-51-991-15400-B - IDG Oil Filter) 3.

Job Set-up Subtask 24-21-51-941-052-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

(2)

AES

Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

24-21-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-21-51-010-052-A B.

Get Access (1)

4.

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR.

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Procedure (Ref. Fig. 24-21-51-991-15400-B - IDG Oil Filter) Subtask 24-21-51-680-051-A A.

Draining of the IDG oil (1)

Drain the oil from the IDG (Ref. TASK 12-13-24-680-010-A).

Subtask 24-21-51-020-055-A B.

Removal of the IDG Oil Filter WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU. (1)

Cut and remove the lockwire from the filter cover (4). NOTE :

You can put a CONTAINER 10 L(2 1/2 USGAL) below the filter cavity.

(2)

Remove the filter cover (4).

(3)

Remove and discard the packing (3) from the filter cover (4).

(4)

Remove the filter element (1).

(5)

Remove and discard the packing (2) from the filter element (1).

(6)

Install a CAP - BLANKING on the filter cavity port.

Subtask 24-21-51-210-055-A C.

Inspection of the Filter Element (1)

AES

Do the inspection of the filter element (Ref. TASK 24-21-00-210-045-A), and if necessary, replace it by a new filter element (1).

24-21-51 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

2

1

3

4

N_MM_242151_4_XGN0_01_00

AES

FIGURE 24-21-51-991-15400-B SHEET 1 IDG Oil Filter

24-21-51 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-51-400-011-A Installation of the IDG Oil Filter(s) WARNING : WEAR GOGGLES, INSULATED GLOVES AND OTHER PROTECTIVE CLOTHES. HOT OIL CAN BURN YOUR EYES AND SKIN. IF OIL TOUCHES YOUR EYES OR SKIN, GET MEDICAL AID. CAUTION :

1.

DO NOT LET ENGINE OIL FALL ON THE ENGINE. UNWANTED OIL MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT FREE CLOTH THE OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific

B.

DESIGNATION

Torque wrench: range to between 2.50 and 18.50 LBF.FT (0.34 and 2.60 M.DAN)

Consumable Materials

REFERENCE Material No: 03-002 Material No: 19-010 C.

QTY AR WARNING NOTICE(S)

DESIGNATION OILS LUBRICATING OIL TURBINE ENGINE SYNT BASE LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR D.

Expendable Parts

3

FIG.ITEM packing

IPC-CSN 24-21-51-81-160

1 2

filter element packing

24-21-51-81-170 24-21-51-81-180

E.

DESIGNATION

Referenced Information

REFERENCE 12-13-24-612-011-A 70-23-13-911-010-A

DESIGNATION IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check Procedures for the Installation of Preformed Packings

71-00-00-710-043-A

Normal Engine Automatic Start Procedure

AES

24-21-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 71-00-00-710-045-A

DESIGNATION Test No.1 : Dry Motor Leak Check

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-51-991-15400-B - IDG Oil Filter) 3.

Job Set-up Subtask 24-21-51-860-051-A A.

4.

Aircraft Maintenance Configuration (1)

On the center pedestal, on the ENG panel 115VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the engine.

(2)

On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a WARNING NOTICE(S) is in position to tell persons not to energize the FADEC 1(2).

(3)

Make sure that the fan cowls are open (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR

Procedure (Ref. Fig. 24-21-51-991-15400-B - IDG Oil Filter) Subtask 24-21-51-640-055-A A.

Lubrication of the Expendable parts (1)

Lubricate the new inner packing (2) with the OILS (Material No: 03-002) .

(2)

Lubricate the new outer packing (3) with the OILS (Material No: 03-002) .

Subtask 24-21-51-420-057-A B.

Installation of the Filter Element WARNING : WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THE LOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLIND YOU.

AES

CAUTION :

MAKE SURE THE COMPONENTS ARE SEATED IN THE IDG SCAVENGE FILTER CAVITY BEFORE YOU INSTALL THE FILTER COVER. DO NOT TIGHTEN THE FILTER COVER SCREWS TO FORCE THE FILTER COMPONENTS INTO THE HOUSING.

CAUTION :

DO NOT CLEAN AND USE AGAIN A FILTER ELEMENT THAT YOU REMOVED.

(1)

Remove the blanking cap from the filter cavity port.

(2)

Install the new (IPC-CSN 24-21-51-81) packing (2) on the filter element (1), and make sure that it is in the correct position (Ref. TASK 70-23-13-911-010-A).

(3)

Install the new (IPC-CSN 24-21-51-81) packing (3) on the filter cover (4), and make sure that it is in the correct position (Ref. TASK 70-23-13-911-010-A).

(4)

Put the (IPC-CSN 24-21-51-81) filter element (1) in the filter cavity.

24-21-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (5)

Install the filter cover (4).

(6)

TORQUE the filter cover to between 13 and 15 LBF.FT (1.76 and 2.03 M.DAN).

(7)

Safety the filter cover with LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA (Material No: 19-010) .

Subtask 24-21-51-612-051-A C.

Fill the IDG oil system (Ref. TASK 12-13-24-612-011-A).

Subtask 24-21-51-210-051-A D.

Visual Inspection for Oil Leaks (1)

Do dry motoring (Ref. TASK 71-00-00-710-045-A) and make sure that there are no oil leaks at the covers of the IDG oil filter. NOTE :

5.

We recommend that you do a visual inspection to make sure there are no oil leaks at the cover of the IDG oil filter.Do this inspection at the subsequent engine start, at minimum idle (Ref. TASK 71-00-00-710-043-A). At this time, the oil pressure in the lubrification system and the cooling system of the IDG is higher and the oil circulation time is longer.

Close-up Subtask 24-21-51-410-052-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowls (Ref. TASK 71-13-00-410-010-A):

(3)

AES

(a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR.

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Remove the warning notice(s).

24-21-51 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

GENERATOR - INTEGRATED DRIVE (IDG) INSPECTION/CHECK ** On A/C ALL Task 24-21-51-200-010-A Check of the Oil Level and Filter Differential Pressure Indicator (DPI) WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. 1.

Reason for the Job (Ref. MPD 24-21-00-07-) -CHECK OIL LEVEL OF INTEGRATED DRIVE GENERATOR (GREEN RANGE) AND REPLENISH IF NECESSARY -CHECK FILTER DIFFERENTIAL PRESSURE INDICATOR ( POP OUT NOT PROTRUDING ) . check oil level of integrated drive generator (green range) and replenish if necessary, . check differential pressure indicator (pop out not protruging).

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

438 448 B.

Referenced Information

REFERENCE 12-13-24-612-011-A 24-21-51-200-011-A 3.

ZONE DESCRIPTION FAN COWL FAN COWL

DESIGNATION IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check Check IDG Oil Filter Differential Pressure Indicator (DPI)

Job Set-up Subtask 24-21-51-869-052-A A.

4.

Not Applicable

Procedure Subtask 24-21-51-210-053-A A.

Visual Inspection of the Differential Pressure Indicator (DPI) (1)

Do a check of the IDG-filter differential-pressure indicator (Ref. TASK 24-21-51-200-011-A).

Subtask 24-21-51-210-054-A B.

Visual Inspection of the IDG Oil Level (1)

AES

Inspection of the Oil Level (a)

Let the oil in the IDG become stable for 5 minutes after engine 1(2) shutdown.

(b)

(b) Look at the oil level sight-glass of the IDG: . if the oil level is in the green band, oil servicing is not necessary.

24-21-51 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL .

if the oil level is below the green band or above the green band, an IDG oil servicing is necessary (Ref. TASK 12-13-24-612-011-A).

NOTE :

AES

An internal oil consumption of 1 cc is permitted for each flight hour or when the engines operate.

24-21-51 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-21-51-200-011-A Check IDG Oil Filter Differential Pressure Indicator (DPI) WARNING : BE CAREFUL WHEN YOU WORK ON THE ENGINE COMPONENTS IMMEDIATELY AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS CAN STAY HOT FOR UP TO ONE HOUR. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific

QTY DESIGNATION AR LIGHT SOURCE - INSPECTION AR MIRROR - INSPECTION

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR C.

Referenced Information

REFERENCE 71-13-00-010-010-A

DESIGNATION Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-21-51-991-15300-A - Differential Pressure Indicator (DPI) of the Oil Filter) 3.

Job Set-up Subtask 24-21-51-941-051-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: (a)

AES

Put a WARNING NOTICE(S) to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

24-21-51 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-21-51-010-051-A B.

Get Access (1)

4.

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Procedure (Ref. Fig. 24-21-51-991-15300-A - Differential Pressure Indicator (DPI) of the Oil Filter) Subtask 24-21-51-210-060-A A.

Visual Inspection of the DPI of the Oil Filter (1)

Make sure that the red button of the DPI is not extended. Use an LIGHT SOURCE - INSPECTION and an MIRROR - INSPECTION, if necessary. (a)

5.

If the red button is extended from the end of the indicator. . do the alternate procedure: Refer to TSM/24.

Close-up Subtask 24-21-51-410-051-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the fan cowls (Ref. TASK 71-13-00-410-010-A):

(3)

AES

(a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR,

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Remove the warning notice(s).

24-21-51 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

RED BUTTON

INDICATOR

EXTENDED

A INDICATOR

NORMAL OR RESET 14188

N_MM_242151_6_XAM0_01_00

AES

FIGURE 24-21-51-991-15300-A SHEET 1 Differential Pressure Indicator (DPI) of the Oil Filter

24-21-51 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC MAIN GENERATION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The two engine generators provide the AC main generation. The AC main generation supplies the whole aircraft in normal flight configuration. The transfer circuit supplies either one or the two distribution networks from any generation source: . main, . auxiliary, . or ground.

AES

24-22-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location

** On A/C 003-004 (Ref. Fig. 24-22-00-12400-A - AC Main Generation - Component Location) ** On A/C 005-099 (Ref. Fig. 24-22-00-12400-B - AC Main Generation - Component Location) ** On A/C ALL (Ref. Fig. 24-22-00-12500-B - AC Main Generation - Component Location) FIN 1XU1 1XU2 3XU1

GCU-1 GCU-2 P/BSW-ELEC/GEN 1

91VU 91VU 35VU

ZONE ACCESS DOOR 121 121 210

3XU2

P/BSW-ELEC/GEN 2

35VU

210

24-21-00

9XU1 9XU2 10XU

GLC-1 GLC-2 P/BSW-ELEC/BUS TIE

120VU 120VU 35VU

212 212 210

24-22-55 24-22-55 24-21-00

11XU1 11XU2 13XU

BTC-1 BTC-2 P/BSW-EMER ELEC PWR/GEN1 LINE

120VU 120VU 21VU

212 212 211

24-22-55 24-22-55 24-21-00

41XU1 CT-AC, 1 41XU2 CT-AC, 2 ** On A/C 005-099

131 132

24-22-17 24-22-17

51XU1 51XU2 ** On A/C ALL

CT CT

212 212

24-22-17 24-22-17

4000XU 22XU1 22XU2 42XU1 42XU2 42XU3 42XU4 50XU1 50XU2

IDG EGIU-1 EGIU-2 CT-AC, 1 CT-AC, 2 CT-AC, 1 CT-AC, 2 SENSOR-TDC AC, 1 SENSOR-TDC AC, 2

445 121 122 212 212 212 212 126 126

24-21-51 24-22-33 24-22-33 24-22-17 24-22-17 24-22-17 24-22-17 24-22-18 24-22-18

AES

FUNCTIONAL DESIGNATION

PANEL

95VU 96VU 120VU 120VU 120VU 120VU 103VU 103VU

24-22-00 PB001

ATA REF. 24-22-34 24-22-34 24-21-00

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description

** On A/C 003-004 (Ref. Fig. 24-22-00-13700-C - AC Main Generation (Normal Configuration) - General Schematic) ** On A/C 005-099 (Ref. Fig. 24-22-00-13700-H - AC Main Generation (Normal Configuration) - General Schematic) When the two engines run in normal conditions, generator 1 and generator 2 supply their own network. Generator 1 supplies network 1, including: . AC BUS 1, . AC ESSENTIAL BUS, . AC SHEDDABLE ESSENTIAL BUS. Generator 2 supplies network 2, corresponding to AC BUS 2. Networks 1 and 2 are supplied in priority order: . by their generator, . by the electrical ground power unit, . by the auxiliary generator, . or by the other generator. GEN1 and GEN2 pushbutton switches, on the panel 35VU on the overhead panel, control the generators 1 and 2 respectively via the GCU. The EGIU transmit the main parameters from the GCU and generators to the ECAM system.

AES

24-22-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Component Description A.

Generator Control Unit 1XU1 1XU2 The 3 GCUs are identical and interchangeable. The GCU functions (GCU1, GCU2, APU GCU) are selected by Pin Programming. The GCU has four different functions: . voltage regulation, . control and protection of the network and the generator, . control of the various indications, . system test and self-monitoring. Voltage regulation is performed in the analog form, whereas the other functions are digital. The GCUs are supplied: . directly from the PMG, for generator excitation and 28VDC internal and external supply, . from the aircraft normal network (28 VDC) for the internal and external supply. This dual supply constitutes a back up supply. (1) Voltage regulation The voltage regulation is performed by regulating the generator excitation current: the voltage is kept at the nominal Point Of Regulation (POR). The POR is located in the electrical power center at the end of the generator feeder, upstream of the line contactor. Analog circuits achieve the regulation. The PMG provides directly the excitation supply via the Generator Control Relay (GCR). The excitation supply is rectified. Then a chopper amplifier (pulse width modulation), protected by a freewheeling diode, controls the excitation supply. The regulation is achieved using a signal proportional to the average of the three line to neutral voltages at the input. NOTE : . During an operation in unbalanced rating, the voltage level of the higher phase is limited. This limit has a priority on the regulation of the three phase mean voltage. . A stabilization circuit enables the dynamic response of the regulation to be improved. . A current limiter circuit limits the current supplied by the generator. As the excitation current is limited, the mechanical power that the drive part supplies is also limited. . If the protection circuits detect a fault, the generator excitation is cut off: . electronically by shorting to ground the Voltage Regulation Shut Down: (VR S/D Down), . by cutting off its supply by the GCR. . With a generator selected by the GEN pushbutton switch, the excitation command signal (VR S/D Line) is used to command: . the initial generator excitation at engine start, . its de-energization at engine shutdown. (325 Hz line frequency). (2) Generator control and protection functions These functions are mainly the generator excitation and line contactor control. The excitation is controlled via the GCR. The line contactor is controlled via the Power Ready Relay (PR) which is energized when: . the speed is more than 4730 rpm and, . the GCR is closed. Signals received or generated by the GCU control these two relays. The following control or fault signals cause generator shutdown or de-energization: (Ref. Fig. 24-22-00-15500-A - Zone of Protection) . IDG disconnection, . GLC failure (BTC is only locked out), . engine shutdown with the ENG FIRE pushbutton switches (IDG position),

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . . . . . .

PMG short circuit, over/under voltage, over/under frequency, open cable (IDG position), APU ready (APU position), differential protection: . Zone 1 : monitoring of the generator 1 or 2 and feeders, . Zone 2 : monitoring between the line contactor and the primary circuit breakers related to the channel. Monitoring between the BTC of the applicable channel and the primary circuit breakers, . GEN pushbutton switch, . short circuit of the rotating diodes, . phase sequence (in this case, the GCU opens the PR relay only). Except in some particular cases, the system may be reset by setting the GEN pushbutton switch to OFF. The PR is also controlled by the IDG drive underspeed. This prevents the generator from being energized. NOTE :

Each time the generator is de-energized because of a fault signal, do a GCU reset. To do this, push (ON) then release (OFF) the related GEN pushbutton switch.

NOTE :

After: . activation of a differential pressure, or . activation of a GLC fault. The system can be reset only two times via the GEN pushbutton switch.

A table listing all these functions is shown below. GCU DETECTION: -----------------------------------------------------------------------------! FUNCTION !SENSING ! THRESHOLD !TIME DELAY !TRIPS! REMARKS !INHIBITION! !-----------!--------!-----------!-----------!-----!---------------!----------! !Overvoltage!Highest ! 130 VAC, ! Inverse ! GLC ! Turns off ! ! !(OV) !phase at! + or !(compatible! GCR ! voltage ! ! ! !POR ! 1.5 V ! with the ! ! regulator ! ! !(IDG and ! ! ! guaranteed! ! ! ! ! APU GEN) ! ! ! transient ! ! ! ! ! ! ! ! voltage ! ! ! ! ! ! ! ! to the ! ! ! ! ! ! ! ! network) ! ! ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Undervol- ! Lowest ! 100 VAC, !4 s to 5 s ! GLC ! Turns off ! ! ! tage (UV) ! phase ! + or ! ! GCR ! voltage ! ! ! ! at POR ! 4 V ! ! ! regulator ! ! ! ! voltage! ! ! ! ! ! ! (IDG and ! ! ! ! ! !Locked out! ! APU GEN) ! ! ! ! ! !by US TRIP! ! ! ! ! ! ! !APU TRIP ! ! ! ! ! ! ! !or UP TRIP! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Overfre- ! PMG ! PMG fre- !3 s to 5 s ! GLC ! Turns off ! ! ! quency(OF)! fre! quency ! ! GCR ! voltage ! ! ! (IDG and ! quency ! correspon-! ! ! regulator ! ! ! APU GEN) ! ! ding to ! ! ! ! ! ! ! ! (433 Hz ! ! ! ! ! ! ! ! + or ! ! ! ! !

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ! ! ! 3 Hz) ! ! ! ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Underfre- ! PMG ! PMG fre- !3 s to 5 s ! GLC ! Turns off !Locked out! ! quency(UF)! fre! quency ! ! GCR ! voltage !by US TRIP! ! (IDG and ! quency ! correspon-! ! ! regulator ! or ! ! APU GEN) ! ! ding to ! ! ! !APU TRIP ! ! ! ! (363 Hz ! ! ! ! ! ! ! ! + or ! ! ! ! ! ! ! ! 3 Hz) ! ! ! ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Underspeed! IDG !4730 RPM !100 ms max.! GLC ! Generator ! ! ! (US) ! input ! + or ! ! ! excitation ! ! ! (IDG) ! speed ! 30 RPM ! ! ! is cut off ! ! ! !magnetic! ! ! ! through an UF ! ! ! ! pick-up! ! ! ! signal at ! ! ! ! ! ! ! ! frequency ! ! ! ! ! ! ! ! below 325 Hz ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Overload ! Average! 277 A ! 13 s ! ! Signal for ! ! ! (OL) ! of the ! + or ! + or ! ! warning and ! ! ! (IDG and ! three ! 13 A ! 3 s ! ! automatic gal-! ! ! APU GEN) ! genera-! ! ! ! ley shedding ! ! ! ! tor ! ! ! ! of APU GEN on ! ! ! ! current! ! ! ! ground ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Phase se- !2 phases! A.B.C.N. ! None ! GLC ! Prevents GLC ! ! ! quence(PS)!at POR ! phase ! ! ! closure if ! ! ! ! ! sequence ! ! ! phase sequence! ! ! (IDG and ! ! ! ! ! is not ABCN ! ! ! APU GEN) ! ! ! ! ! ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Disconnect! Discon-! Manual ! None ! GLC ! Turns off vol-! ! ! (D) (IDG) ! nect ! action ! ! GCR ! tage regula- ! ! ! ! signal ! ! ! ! tor, turns on ! ! ! ! from ! ! ! ! warning light ! ! ! ! cockpit! ! ! ! ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Fire (F) ! Fire ! Manual ! None ! GLC ! Turns off vol-! ! ! (IDG) ! signal ! action ! ! GCR ! tage regulator! ! ! ! cockpit! ! ! ! ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Differen- ! Diffe- ! 45 A ! 37.5 ms ! GLC ! Open BTC, GLC.! ! ! tial Pro- ! rential! + or ! + or ! GCR ! If DP is in ! ! ! tection ! current! 5 A ! 2.5 ms ! BTC ! zone 1, then ! ! ! (DP) ! of each! ! ! ! remove inter- ! ! ! ! phase ! ! ! ! lock from BTC ! ! ! ! from ! ! ! ! in 120+10 ms. ! ! ! (IDG and !the CT’s! ! ! ! If DP zone 2, ! ! ! APU GEN) ! sensing! ! ! ! lockout GLC ! ! ! ! ! ! ! ! and BTC ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Shorted ! Three ! Ripple ! 2 s ! GLC ! Turns off vol-! ! ! Permanent ! phases ! of PMG -! + or ! GCR ! tage regulator! !

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ! Magnet ! voltage! rectified ! 0.5 s ! ! ! ! ! Generator ! PMG ! output ! ! ! ! ! ! (S PMG) ! ! ! ! ! ! ! ! (IDG and ! ! ! ! ! ! ! ! APU GEN) ! ! ! ! ! ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Open Cable! Diffe- ! I > 80 A ! 3 ms ! GLC ! Turns off ! ! ! (OC) ! rential! + or ! + or ! GCR ! voltage ! ! ! (IDG) ! current! 0.8 A ! 0.3 ms ! ! regulator. ! ! ! ! from ! ! ! ! 28 VDC is pro-! ! ! ! 6 hole ! ! ! ! vided by TDC ! ! ! ! CTA ! ! ! ! AC SENSOR to ! ! ! ! ! ! ! ! fire trip GCU ! ! ! ! ! ! ! ! input ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! GLC fai- ! Indivi-! GLC status! 250 ms !LOCKS! ! ! ! -lure (IDG! -dual ! ON and I ! + or ! OUT ! ! ! ! and APU ! CTA ! I > or = ! 50 ms ! BTC ! ! ! ! GEN) ! current! 25 A ! ! ! ! ! ! ! GLC ! + or - 5 A! ! ! ! ! ! ! status ! with PRR ! ! ! ! ! ! ! ! OFF ! ! ! ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! APU ready ! Signal ! Absence of! None ! GLC ! Generator ! ! ! (APU GEN) ! from ! signal ! ! ! excitation ! ! ! ! elec- ! ! ! ! is cut off ! ! ! ! tronic ! ! ! ! through signal! ! ! ! control! ! ! ! at frequency ! ! ! ! unit of! ! ! ! below 325 Hz. ! ! ! ! APU ! ! ! !.Oil over temp ! ! ! ! ! ! ! ! 185 deg. C ! ! ! ! ! ! ! ! + or - 5 deg.C! ! ! ! ! ! ! !.Speed 95 per- ! ! ! ! ! ! ! ! cent Nn signal! ! ! ! ! ! ! ! from ECB ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Oil Over ! Oil out! 185 plus ! None ! ! IDG fault ! ! !Temperature! tempe- ! or minus ! ! ! indication ! ! ! (OOT) ! rature ! 5 deg.C ! ! ! ! ! ! (IDG) ! bulb ! ! ! ! ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Open Cir- !4 cables! >9 A ! 37.5 ms ! GCR ! If either CT, ! ! ! cuit (OCT)!from ge-! average ! + or ! GLC ! except 6 h CT,! ! ! !nerator ! current ! 5 ms ! BTC ! opens while ! ! ! !CT and 4! ! ! ! loaded reclose! ! ! !cables ! ! ! ! BTC and if ! ! ! !from ! ! ! ! line CT opens ! ! ! !line CT ! ! ! ! before closing! ! ! (IDG and ! ! ! ! ! into load, ! ! ! APU GEN) ! ! ! ! ! lockout BTC ! ! ! ! ! ! ! ! open ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! Rotor dio-! Current! Function ! 3 s ! GCR ! Turns off vol-! !

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ! de short ! and ! of DC ex- ! + or ! and ! tage regulator! ! ! circuit ! voltage! citer vol-! 0.5 s ! PR ! ! ! ! sensing ! exciter! tage Vs ! ! ! ! ! ! ! field ! Generator ! ! ! ! ! ! (IDG and ! ! load ! ! ! ! ! ! APU GEN) ! ! current ! ! ! ! ! !-----------!--------!-----------!-----------!-----!---------------!----------! ! ! ! ! ! ! ! ! ! Generator !.Closed ! ! !.GCR !.GLC will close! ! ! control ! ! ! !close! when voltage ! ! ! switch ! ! ! ! ! frequency and ! ! ! ! ! ! ! ! phase sequence! ! ! ! ! ! ! ! are within ! ! ! ! ! ! ! ! limits ! ! ! !.Open ! ! !.GCR !.Turns off vol-! ! ! ! ! ! ! trip! tage regulator! ! ! ! ! ! ! GLC ! ! ! ! ! ! ! ! open! ! ! ------------------------------------------------------------------------------(3) Control of the various indications (warnings and annunciators) The GCU controls the warnings and annunciators related to the IDG channel. . Generator FAULT comes on when the protections come into operation (PR opening) . Generator FAULT also comes on: for the main generators whenever the GLC is open, for the APU generator whenever the GLC is open or the EPC opens with the APU ready. . Galley FAULT when an overload is detected . IDG FAULT for a low pressure or high temperature of the cooling and lubrication oil system. (4) System self-monitoring and test function (BITE) This function can be divided into three different parts: . test and analysis after generator tripping, . passive fault detection, . maintenance test. (a) Test and analysis after generator tripping When a generator has tripped (active failure), the GCU . identifies the protection which has caused the tripping (over-frequency, differential protection, etc...), . analyses the conditions in which the tripping has occurred, . then, determines the origin of the fault (GCU wiring or peripherals). (b) Passive fault detection Certain passive fault can affect the system operation, but the generator continues to work. The GCU permanently monitors the majority of the circuits concerned. When detecting a fault, the GCU determines the origin. (c) Maintenance test It can only be performed on the ground, with IDGs shut down. It completes to a certain extent, the above described monitorings. The test consists in exciting (stimuli) the circuits concerned and analysing the response. It is controlled: . either automatically at each GPCU Power Up, . or manually by means of a discrete signal provided by the CFDIU to the GPCU.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL All the data relating to these tests are stored in a coded form in the non volatile memory of the GCU (62 failures capacity). Only the faults of the last 7 flights are kept in the non volatile memory. The architecture of data transmissions is described more in detail in the GPCU functions (Ref. 24-41-00-00). (d) Electrical Generation Interface Unit (EGIU) The main function of this unit is to provide main electrical parameters to the SDACS via ARINC 429 data links. Two identical EGIU’s are used per aircraft. One consists of 2 isolated channels: (Ref. Fig. 24-22-00-15700-B - Electrical Generation Interface Unit - Schematic Diagram) . Channel 1 is allocated to IDG1 or IDG2, . Channel 2 is allocated to APU Generator or External Power (EXT PWR). The information provided to the SDACs is as follows: . POR voltage (phase A), . Load (phase A), . Line Frequency (phase A), . Oil Inlet/Outlet Temperature, . Overload, . Generator Fault, . IDG Disconnect Status, . IDG Low Oil Pressure, . External Power available, . External Power ON. Analog and discrete input parameters are listed below: Channel 1: Analog and Discrete Input Parameters ------------------------------------------------------------------------------! PARAMETER DEFINITION !IDG1!IDG2! STATE ! COMMENTS ! !-----------------------------!----!----!-------------!-----------------------! ! POR VOLTAGE 115 VAC, 400 Hz ! X ! X ! ! Parameter for defini- ! ! (PHASE A) ! ! ! ! tion of AC voltage ! ! ! ! ! ! and frequency ! !-----------------------------!----!----!-------------!-----------------------! ! AC LOAD ! X ! X ! ! ! ! ! ! ! ! ! !-----------------------------!----!----!-------------!-----------------------! ! IDG OIL INLET TEMPERATURE ! X ! X ! ! ! ! ! ! ! ! ! !-----------------------------!----!----!-------------!-----------------------! ! IDG OIL OUTLET TEMPERATURE ! X ! X ! ! ! ! ! ! ! ! ! !-----------------------------!----!----!-------------!-----------------------! ! OVERLOAD WARNING ! X ! X ! Ground when ! ! ! ! ! ! overload ! ! !-----------------------------!----!----!-------------!-----------------------! ! GENERATOR FAULT ! X ! X ! 28 VDC when ! ! ! ! ! ! FAULT ! ! !-----------------------------!----!----!-------------!-----------------------! ! IDG DISC. STATUS ! X ! X ! Ground when ! ! ! ! ! ! DISC ! ! !-----------------------------!----!----!-------------!-----------------------! ! IDG DISC P/BSW POS ! X ! X ! Ground when ! From P/BSW contact ! ! ! ! ! ON ! relay ! !-----------------------------!----!----!-------------!-----------------------!

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ! IDG OIL LOW PRESSURE ! X ! X ! Ground when ! From IDG low pressure ! ! ! ! ! low pressure! switch ! ! ! ! ! ! ! ! ! ! ! ! ! !-----------------------------!----!----!-------------!-----------------------! ! GEN P/BSW POSITION ! X ! X ! 28 VDC when ! From GCU TR source ! ! ! ! ! ON ! (through PR) ! ------------------------------------------------------------------------------Channel 2: Analog and Discrete Input Parameters ------------------------------------------------------------------------------! PARAMETER DEFINITION ! EXT! APU! STATE ! COMMENTS ! ! ! PWR! ! ! ! !-----------------------------!----!----!-------------!-----------------------! ! POR VOLTAGE 115VAC 400 Hz ! X ! X ! ! Parameter for defini- ! ! (PHASE A) ! ! ! ! tion of AC voltage ! ! ! ! ! ! and frequency ! !-----------------------------!----!----!-------------!-----------------------! ! AC LOAD ! ! X ! ! ! ! ! ! ! ! ! !-----------------------------!----!----!-------------!-----------------------! ! OVERLOAD WARNING ! ! X ! Ground when ! ! ! ! ! ! overload ! ! !-----------------------------!----!----!-------------!-----------------------! ! GENERATOR FAULT ! ! X ! 28 VDC when ! From aircraft 28 VDC ! ! ! ! ! FAULT ! (through power ready) ! !-----------------------------!----!----!-------------!-----------------------! ! GEN P/BSW POSITIOM ! ! X ! 28 VDC when ! From GCU TR source ! ! ! ! ! ON ! (through PR) ! !-----------------------------!----!----!-------------!-----------------------! ! EXT PWR AVAILABLE ! X ! ! 28 VDC when ! ! ! ! ! ! available ! ! !-----------------------------!----!----!-------------!-----------------------! ! Class II FAILURE ! X ! ! Ground when ! ! ! ! ! ! message ! ! !-----------------------------!----!----!-------------!-----------------------! ! EXT PWR ON ! X ! ! Ground when ! ! ! ! ! ! ON ! ! ------------------------------------------------------------------------------Channel 2: Flip-Flop Circuit ------------------------------------------------------------------------------! INPUT ! STATE ! COMMENTS ! !---------------------------------------!-------------!-----------------------! ! 28 VDC VIA EXT PWR P/BSW ! 28 VDC when ! ! ! ! P/BSW ON ! ! ------------------------------------------------------------------------------Each EGIU includes a one shot circuit controlled by EXT PWR pushbutton switch allowing to latch the EPC auxiliary relay. This device is located on channel 2 of EGIU. (Ref. Fig. 24-22-00-15800-A - Flip-Flop Circuit - Block Diagram) The supply of each channel of the unit is provided: . either by 28 V back-up (from busbar 3PP), . or by 28 VDC delivered by the associated control unit (GCU or GPCU). A 5 VDC supply is provided to the FAULT legend of the GEN pushbutton switches.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL B.

System Data Acquisition Concentrator (SDAC) Communications (Ref. Fig. 24-22-00-16000-A - SDAC Communication - Block Diagram) Each EGIU channel interfaces with each SDAC via a single ARINC 429 data bus. The parameters are displayed on the ECAM system.

(1) Table of main digital signals received and sent out by the SDAC 1(2) ------------------------------------------------------------------------------! CHANNEL 1 ! !-----------------------------------------------------------------------------! ! OUT ! SDI ! !FORMAT!REFRESH! No.OF!CODING! ! ! SOURCE ! !LABEL!GEN1!GEN2! PARAMETER !(BNR ! RATE !SIGNI-!RANGE !RESOL!UNIT! ORIGIN ! ! ! ! ! DEFINITION ! or ! (MS) !FICANT! MIN/ ! ! ! ! ! ! ! ! ! BCD) !MIN/MAX! BITS ! MAX ! ! ! ! !-----!----!----!------------!------!-------!------!------!-----!----!--------! ! 070 ! 01 ! 10 ! AC FREQUEN-! BNR !250/500! 9 ! 0/512! 1 Hz! Hz ! From ! ! ! ! ! CY Ph A ! ! ! ! ! ! ! 115 VAC! ! ! ! ! ! ! ! ! ! ! ! 400 Hz ! ! ! ! ! ! ! ! ! ! ! ! INPUT ! ! ! ! ! ! ! ! ! ! ! ! GCU 1 ! ! ! ! ! ! ! ! ! ! ! ! GCU 2 ! !-----!----!----!------------!------!-------!------!------!-----!----!--------! ! 072 ! 01 ! 10 ! AC VOLTAGE ! BNR !250/500! 8 ! 0/256! 1 V ! V ! From ! ! ! ! ! Ph A ! ! ! ! ! ! ! 115 VAC! ! ! ! ! ! ! ! ! ! ! ! 400 Hz ! ! ! ! ! ! ! ! ! ! ! ! INPUT ! ! ! ! ! ! ! ! ! ! ! ! GCU 1 ! ! ! ! ! ! ! ! ! ! ! ! GCU 2 ! !-----!----!----!------------!------!-------!------!------!-----!----!--------! ! 077 ! 01 ! 10 ! AC LOAD ! BNR !250/500! 8 ! 0/256! 1per! per! GCU 1 ! ! ! ! ! ! ! ! ! ! cent!cent! GCU 2 ! !-----!----!----!------------!------!-------!------!------!-----!----!--------! ! 105 ! 01 ! 10 ! IDG OIL ! BNR !250/500! 8 ! -256 ! 1 !deg.! GCU 1 ! ! ! ! ! INLET TEMP ! ! ! ! / !deg.C! C ! GCU 2 ! ! ! ! ! ! ! ! ! +256 ! ! ! ! !-----!----!----!------------!------!-------!------!------!-----!----!--------! ! 106 ! 01 ! 10 ! IDG OIL ! BNR !250/500! 8 ! -256 ! 1 !deg.! GCU 1 ! ! ! ! ! OUTLET TEMP! ! ! ! / !deg.C! C ! GCU 2 ! ! ! ! ! ! ! ! ! +256 ! ! ! ! ------------------------------------------------------------------------------! CHANNEL 2 ! !-----------------------------------------------------------------------------! ! OUT ! SDI ! !FORMAT!REFRESH! No.OF!CODING! ! ! SOURCE ! !LABEL!APU !EXT ! PARAMETER !(BNR ! RATE !SIGNI-!RANGE !RESOL!UNIT! ORIGIN ! ! !GEN !PWR ! DEFINITION ! or ! (MS) !FICANT! MIN/ ! ! ! ! ! ! ! ! ! BCD) !MIN/MAX! BITS ! MAX ! ! ! ! !-----!----!----!------------!------!-------!------!------!-----!----!--------! ! 071 ! 01 ! !APU GEN FREQ! BNR !250/500! 9 ! 0/512! 1 Hz! Hz !APU GCU ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! 10 !EXT PWR FREQ! ! ! ! ! ! !GPCU ! !-----!----!----!------------!------!-------!------!------!-----!----!--------! ! 075 ! 01 ! !APU GEN ! BNR !250/500! 8 ! 0/256! 1 V ! V !APU GCU ! ! ! ! !VOLTAGE ! ! ! ! ! ! ! !

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! 10 !EXT PWR ! ! ! ! ! ! !GPCU ! ! ! ! !VOLTAGE ! ! ! ! ! ! ! ! !-----!----!----!------------!------!-------!------!------!-----!----!--------! ! 100 ! 00 ! ! AC LOAD ! BNR !250/500! 8 ! 0/256! 1per! per!APU GCU ! ! ! ! ! ! ! ! ! cent!cent! ! ------------------------------------------------------------------------------! CHANNEL 1 ! !-----------------------------------------------------------------------------! ! OUT ! ! SDI ! !REFRESH! ! ! SOURCE ! !LABEL! BIT!GEN1!GEN2! PARAMETER ! RATE ! STATE 0 ! STATE 1 ! ORIGIN ! ! ! No.! ! ! DEFINITION! (MS) ! ! ! ! ! ! ! ! ! !MIN/MAX! ! ! ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 050 ! 11 ! 01 ! 10 ! OVERLOAD !250/500!no warning! warning ! ! ! ! ! ! ! WARNING ! ! ! ! ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 050 ! 12 ! 01 ! 10 ! GENERATOR !250/500! no fault ! fault ! ! ! ! ! ! ! FAULT ! ! ! ! ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 050 ! 13 ! 01 ! 10 ! IDG DIS- !250/500! not disc ! disc ! ! ! ! ! ! ! CONNECT ! ! ! ! ! ! ! ! ! ! STATUS ! ! ! ! ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 050 ! 14 ! 01 ! 10 ! IDG DIS- !250/500! P/BSW OFF! P/BSW ON ! ! ! ! ! ! ! CONNECT ! ! ! ! ! ! ! ! ! ! P/B POS ! ! ! ! ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 050 ! 17 ! 01 ! 10 ! IDG OIL !250/500! no over- ! overheat ! From IDG ! ! ! ! ! ! OUTLET ! ! heat ! ! OUTLET TEMP ! ! ! ! ! ! OVERHEAT ! ! ! ! Input parame-! ! ! ! ! ! ! ! ! ! ter with ! ! ! ! ! ! ! ! ! ! threshold ! ! ! ! ! ! ! ! ! !185 deg.C plus! ! ! ! ! ! ! ! ! ! or minus ! ! ! ! ! ! ! ! ! ! 5 deg.C ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 050 ! 18 ! 01 ! 10 ! IDG OIL !250/500! low pres-! normal ! ! ! ! ! ! ! LOW PRES- ! ! sure ! pressure ! ! ! ! ! ! ! SURE ! ! ! ! ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 050 ! 19 ! 01 ! 10 ! GEN P/BSW !250/500! P/BSW OFF! P/BSW ON ! ! ! ! ! ! ! POSITION ! ! ! ! ! ------------------------------------------------------------------------------! CHANNEL 2 ! !-----------------------------------------------------------------------------! ! OUT ! ! SDI ! !REFRESH! ! ! SOURCE ! !LABEL! BIT!GEN3! EXT! PARAMETER ! RATE ! STATE 0 ! STATE 1 ! ORIGIN ! ! ! No.! ! PWR! DEFINITION! (MS) ! ! ! ! ! ! ! ! ! !MIN/MAX! ! ! ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 052 ! 11 ! 01 ! ! OVERLOAD !250/500!no warning! warning ! ! ! ! ! ! ! WARNING ! ! ! ! !

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 052 ! 12 ! 01 ! ! GENERATOR !250/500! no fault ! fault ! ! ! ! ! ! ! FAULT ! ! ! ! ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 052 ! 14 ! 01 ! ! GEN P/BSW !250/500! P/BSW OFF! P/BSW ON ! ! ! ! ! ! ! POSITION ! ! ! ! ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 052 ! 12 ! ! 10 ! EXT PWR !250/500! not avai-! available! ! ! ! ! ! ! AVAILABLE ! ! lable ! ! ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 052 ! 13 ! ! 10 ! EXT PWR ON!250/500! OFF ! ON ! ! !-----!----!----!----!-----------!-------!----------!----------!--------------! ! 052 ! 15 ! ! 10 ! CLASS II !250/500!no failure! failure ! Actuated by ! ! ! ! ! ! FAILURE ! ! ! ! GPCU BITE ! ! ! ! ! ! ! ! ! ! Message ! ! ! ! ! ! ! ! ! ! Discrete ! NOTE :

For some more information: see ATA Ref. 31-54-00.

(2) Table of main discrete signals received and sent out by the SDAC1(2) ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------! 002 00! BUS TIE ! ! ! ! 21 ! ! ! ! 10XU ! ! ! P/B OFF ! ! ! ! ! ! ! ! ! ! 002 00! BUS TIE ! ! ! ! 21 ! ! ! ! 10XU ! ! ! P/B ON ! ! ! ! ! ! ! ! ! ! 002 01!GEN1 LINE ! ! ! ! 14 ! ! ! ! 9XU1 ! ! !CNTOR ON ! ! ! ! ! ! ! ! ! ! 002 01!GEN1 LINE ! ! ! ! 14 ! ! ! ! 9XU1 ! ! !CNTOR OFF ! ! ! ! ! ! ! ! ! ! 002 01! TRANSFER ! ! ! ! 15 ! ! ! ! 11XU1 ! ! !CNTOR1 ON ! ! ! ! ! ! ! ! ! ! 002 01! TRANSFER ! ! ! ! 15 ! ! ! ! 11XU1 ! ! !CNTOR1 OFF! ! ! ! ! ! ! ! ! ! 002 10!GEN2 LINE ! ! ! ! 14 ! ! ! ! 9XU2 ! ! !CNTOR ON ! ! ! ! ! ! ! ! ! ! 002 10!GEN2 LINE ! ! ! ! 14 ! ! ! ! 9XU2 ! ! !CNTOR OFF ! ! ! ! ! ! ! ! ! ! 002 10! TRANSFER ! ! ! ! 15 ! ! ! ! 11XU2 ! ! !CNTOR2 ON ! ! ! ! ! ! ! ! ! ! 002 10! TRANSFER ! ! ! ! 15 ! ! ! ! 11XU2 ! ! !CNTOR2 OFF! ! ! ! ! ! ! ! ! NOTE :

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For some more information: see ATA Ref. 31-54-00.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Power Contactor ** On A/C 003-004 (1) Technology The contactors are made up of a base with the power circuit connector terminals and a removable assembly mainly consisting of the motor, power contacts, auxiliary contacts and connector. It is possible to remove a contactor without removing the base to which power circuits are connected. ** On A/C 005-099 (2) Technology The contactors are made up of a removable assembly which mainly consists of the motor, power contacts, auxiliary contacts and connector. The contactors are installed on a module or a base to which the power circuits are connected. It is possible to remove a contactor without removing the module or the base. ** On A/C ALL (3) Characteristics of main contacts (a) Three pole contactors: 2 types (260 A or 60 A) Nominal current . 260 A, . 60 A. Overload at nominal voltage . 1.5 x In for 5 minutes . 2 x In for 1 minute (b) Single pole contactors: 3 types (100 A-200 A-300 A) Nominal current . 100 A, . 200 A, . 300 A. Overload . 100 A, 200 A: 1.5XIn for 5 minutes 2XIn for 1 minute 5XIn for 1 second (only for 200 A contactors). . 300 A: in normal operation one cycle has an inrush current of 650 A to 950 A and cut off current of 150 A to 300 A (APU start contactor).

D. TDC AC Sensor If an open cable condition occurs with a current of more than 80A, after a 3 seconds delay, the TDC AC sensor 50XU1 (50XU2) supplies a 28 VDC signal to the GPCU and to the fire trip GCU1 (GCU2) input. The GCU1 (GCU2) does not energize its related GLC1 (GLC2) contactor. E.

Lightning Protection Module The lightning protection modules (19XU1, 19XU2) protect the equipment supplied by the feeders of the IDGs (115V/400Hz, three-phase) against the lightning strikes.

F.

Current Transformer (CT)

** On A/C 003-004 (Ref. Fig. 24-22-00-12400-A - AC Main Generation - Component Location) ** On A/C 005-099 (Ref. Fig. 24-22-00-12400-B - AC Main Generation - Component Location)

AES

24-22-00 PB001

Page 14 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL (Ref. Fig. 24-22-00-12500-B - AC Main Generation - Component Location) (Ref. Fig. 24-22-00-17900-A - Current Transformers - Block Diagram) There are two CTs per AC main generation channel: . one CT is built into the IDG generator, . one six-hole CT is installed upstream of the generator line contactor. (1) Functions (a) Generator CT The generator CT is used for differential and overcurrent protections (Ref. Para. 4.A.(2) Generator control and protection functions). (b) Six-hole CT The six-hole CT contains six toroidal transformers, one for each of the parallel power feeder cables. The six-hole CT is connected in electrical opposition to the CT of the IDG generator. This CT is used for differential and open cable protections (Ref. Para. 4.A.(2) Generator control and protection functions). (c) Three-hole CT The three-hole CT contains three toroidal transformers, one for each of the power feeder cables.

AES

24-22-00 PB001

Page 15 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 5.

Operation/Control and Indicating A.

Generator Control Controls and indications for each generator are located on the overhead panel in the cockpit. The signals to and from the indicators and controls transit by the GCU. A general view of AC main generation channel 1 is shown on (Ref. Fig. 24-22-00-19500-E - AC Main Generation Channel 1 - Schematic Diagram) Each GCU controls the opening and closing of the associated GLC. (Ref. Fig. 24-22-00-19600-B - GLC/BTC Logic - Schematic Diagram) (Ref. Fig. 24-22-00-19700-A - GLC-1 Supply - Schematic Diagram) The operation of each generator is controlled by the GEN1 (2) pushbutton switch. This pushbutton switch has two stable positions: . OFF selected, the pushbutton switch is released and the white OFF legend is on. The generator is shut down (de-energized) and the line contactor (GLC) is open, . when the pushbutton switch is pressed in, the generator is energized, its rotational speed being high enough. If the electrical parameters are correct, the line contactor closes. Then, the generator supplies its network. When a fault is detected: . the GCU protections are activated (PR opening), . FAULT legend comes on on GEN pushbutton switch (accompanied by the single chime and MASTER CAUT light). (Ref. Fig. 24-22-00-19900-A - GEN 1 FAULT - Upper and Lower ECAM Display Unit) At the same time: . on the upper display unit of the ECAM system, an amber message is displayed, . on the lower display unit, the ELEC page is automatically displayed. Simultaneously, the automatic transfer becomes effective: . the lost network is supplied by another power source available. The crew has to release-out GEN pushbutton switch (white OFF legend comes on on GEN pushbutton switch). NOTE :

B.

FAULT legend comes on on GEN pushbutton switch also when GLC is open. When starting engine 1, GEN 1 OFF warning is displayed on the ECAM display unit if generator 1 is not on line: (Ref. Fig. 24-22-00-20000-A - GEN 1 OFF - Upper and Lower ECAM Display Unit) Similarly, when starting engine 2, GEN 2 OFF warning is displayed on the ECAM display unit if generator 2 is not in line: (Ref. Fig. 24-22-00-20100-A - GEN 2 OFF _ Upper and Lower ECAM Display Unit)

Transfer Circuit The transfer circuit enables supply of both or either AC electrical network(s) from one of the four power sources (GEN 1, GEN 2, APU GEN, EXT PWR). This is via the transfer contactors (BTC). The BTC control is entirely automatic. It depends on the availability of these sources and the correct condition of each network. The BTC 1 closes if no interlock condition exists on GCU 1: (Ref. Fig. 24-22-00-20500-A - BTC-1 Supply - Schematic Diagram) . ** On A/C 003-004 when generator 1 is not available, in order to supply network 1 from another power source (generator 2, auxiliary generator or ground power unit), . to supply network 2 from generator 1 in case of non-availability of: generator 2, auxiliary generator, and electrical ground power unit.

AES

24-22-00 PB001

Page 16 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL .

** On A/C 005-099 when generator 1 is not available, in order to supply network 1 from another power source (generator 2, auxiliary generator or ground power unit), . to supply network 2 from generator 1 in case of non-availability of: generator 2, auxiliary generator, and electrical ground power unit. In case of single generator configuration, the sheddable busbars 218XP, 220XP, 210PP and 212PP are no longer available. BTC2 control is symmetrical to BTC1 ** On A/C ALL (Ref. Fig. 24-22-00-20800-C - BTC-2 Supply - Schematic Diagram) GCU1 or GCU2 enables closure of BTC1 or BTC2 if: . no DP zone 2 condition, . no GLC welded failure occurred. Networks 1 and 2 are supplied in priority order: . by the corresponding generator, . by the electrical ground power unit, . by the auxiliary generator, . or by the other generator. NOTE :

BTC’s 1 and 2 can be locked out by pressing BUS TIE pushbutton switch located on ELEC overhead panel (Ref. 24-00-00-00). This causes both channels to be isolated.

In case of transfer impossibility or inhibition, AC BUS 1 or AC BUS 2 are lost. The procedure to be applied in case of loss of these busbars is shown in figures. (Ref. Fig. 24-22-00-21000-A - AC BUS 1 Fault - Upper and Lower ECAM Display Unit) (Ref. Fig. 24-22-00-21100-A - AC BUS 2 Fault - Upper and Lower ECAM Display Unit) C.

Smoke Detection In case of smoke detection, amber SMOKE legend comes on on GEN 1 LINE pushbutton switch located on cockpit overhead panel (Ref. 24-00-00-00). It is accompanied by the single chime and the MASTER WARN. Then, the crew has to follow the procedure shown in figures (Ref. Fig. 24-22-00-21500-B - Smoke Detection - Upper and Lower ECAM Display Unit) NOTE :

AES

This smoke procedure is also described in Ref. 24-24-00 since the emergency generator is used in the smoke configuration.

24-22-00 PB001

Page 17 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU FR12 FR14

FR5

FR16 FR20

FR3

122VU

121VU

124VU

125VU

123VU

811 121AL 822 841

A 21VU

35VU

A

25VU

120VU

42XU4

B 4WT1

42XU3

11XU2

42XU1

9XU2

11XU1

4WT2

9XU1

C 42XU2

C B

N_MM_242200_0_AAM0_01_00

AES

FIGURE 24-22-00-12400-A SHEET 1 AC Main Generation - Component Location

24-22-00 PB001

Page 18 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

PANEL 35VU DC BUS 1

1

BAT 1

BAT

2

FAULT

FAULT

OFF

OFF

V

35VU

BAT 2

DC BUS 2 AC ESS FEED V

FAULT

GALLEY

E L E C

FAULT OFF

A U T O

AC BUS 1

AC BUS 2

BUS TIE

IDG 1

FAULT

ALTN

AC ESS BUS

A U T O

IDG 2 EXT PWR

GEN 2

FAULT

AVAIL

FAULT

OFF

ON

OFF

GEN 1

APU GEN

FAULT OFF

OFF

3XU1

10XU

E L E C

FAULT

3XU2

PANEL 21VU

EMER GEN TEST

EMER ELEC PWR GEN 1 LINE

RAT & EMER GEN

SMOKE

FAULT

OFF

MAN ON

A U T O

13XU

N_MM_242200_0_AAM0_02_00

AES

FIGURE 24-22-00-12400-A SHEET 2 AC Main Generation - Component Location

24-22-00 PB001

Page 19 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU FR12 FR14

FR5

FR16

FR3

FR20

122VU

121VU

124VU

125VU

123VU

811 121AL 822 841

A 21VU

35VU 30XN2 25VU

A 120VU

42XU4

B 4WT1

42XU3

11XU2

42XU1

9XU2

11XU1

4WT2

9XU1

C 42XU2 30XN1

C B

N_MM_242200_0_AAP0_01_00

AES

FIGURE 24-22-00-12400-B SHEET 1 AC Main Generation - Component Location

24-22-00 PB001

Page 20 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

PANEL 35VU 1

BAT 1

DC BUS 1

BAT

2

FAULT

FAULT

OFF

OFF

V

35VU

BAT 2

DC BUS 2 AC ESS FEED V

FAULT

GALLEY

E L E C

FAULT OFF

A U T O

AC BUS 1

AC BUS 2

BUS TIE

IDG 1

FAULT

ALTN

AC ESS BUS

A U T O

IDG 2 EXT PWR

GEN 2

FAULT

AVAIL

FAULT

OFF

ON

OFF

GEN 1

APU GEN

FAULT OFF

OFF

3XU1

10XU

E L E C

FAULT

3XU2

PANEL 21VU

EMER ELEC PWR EMER GEN TEST GEN 1 LINE

RAT & EMER GEN

SMOKE

FAULT

OFF

MAN ON

A U T O

13XU

N_MM_242200_0_AAP0_02_00

AES

FIGURE 24-22-00-12400-B SHEET 2 AC Main Generation - Component Location

24-22-00 PB001

Page 21 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

41XU2

B

41XU1

B A FR34

C

FR9

A 103VU

B

50XU2 50XU1

N_MM_242200_0_ACPA_01_00

AES

FIGURE 24-22-00-12500-B SHEET 1 AC Main Generation - Component Location

24-22-00 PB001

Page 22 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

C 90VU

D D 91VU

1XU1

22XU2

E 1XU2 22XU1

E

E

N_MM_242200_0_ACPA_02_00

AES

FIGURE 24-22-00-12500-B SHEET 2 AC Main Generation - Component Location

24-22-00 PB001

Page 23 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 801PP

APU START 49 − 42 − 00

CSM/G CONTROL UNIT 5KA

10KA

6KA

6XE

DC BUS 1

4PB1

1PP

8PR

703PP BAT1 2PB1

6PN 3PN2

28VDC

1PN2

204PP

601PP

202PP

602PP

3PB1 3PP

DC BUS 2

1PC2

2PP 28VDC

28VDC 3XB

7PN

DC SVCE BUS

8PN

2XB

115

6PP 28VDC

3PX

5XB

28

4PP

206PP

1PR SHUNT

DC ESS BUS

4PC

208PP

SHUNT 3PB2

701PP

12PB1

6PB1

28VDC

501PP 5PR

BAT2 2PB2

401PP

502PP

704PP

12PB2

BAT BUS

1PC1

2PR

702PP

5PB1

101PP

1PN1

8PH

20PC

5PB2

4PB2 6PB2 1PB1 BCL−1

103PP

8PP 28VDC

1PB2 BCL−2

3PN1

DC SHED ESS BUS

301PP

11PB

6PH

5PU1 STATIC INV

5PU2

901XP

12XB

801XP

8XH

110XP 26V

5XN1

15XN1

5XH 103XP

115VAC

5XN2

401XP

AC ESS BUS

26V

231XP−A

15XN2

115VAC

101XP

1XN1 1XP

431XP−A

26V

4XH

204XP

3XN2

4XP

2XC

AC BUS 2

2XP 115VAC

3XC 15XE

GLC−1 9XU1 GCU−1 1XU1

AES

BTC−1 11XU1

EPC 3XG

GLC−APU 3XS

4000XU

GCU−APU 1XS

FIGURE 24-22-00-13700-C SHEET 1 AC Main Generation (Normal Configuration) - General Schematic

APU GEN

8XS

GPCU 1XG

24-22-00 PB001

2PU2

14PU

10XN

12XN

3801GX 3805GX

BTC−2 11XU2

GLC−2 9XU2

FUEL PUMPS 28 − 21 − 00 GEN 1

4XX

202XP

1XN2

1XC

1XX

14XX

2XX

12XX

3802GX 3806GX EXTERNAL POWER RECEPTACLE

Page 24 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

1PE ESS TR

1PU2 TR2

210XP

7XN2

131XP−A

3XN1

AC BUS 1

24 − 50 − 00

115VAC

7XN1

2PU1

1PX

AC SHED ESS BUS 8XP

24 − 50 − 00

1PU1 TR1

3PE

4000XU

214XP

216XP 212XP

4PE

ELEC PUMP−Y 29 − 24 − 00 GLC−EMERG 2XE

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_242200_0_AGL0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 801PP

APU START 49 − 42 − 00

CSM/G CONTROL UNIT 5KA

10KA

6KA

6XE

DC BUS 1

4PB1

1PP

8PR

703PP BAT1 2PB1

6PN 3PN2

28VDC

1PN2

204PP

601PP

202PP

602PP

3PB1 3PP

DC BUS 2

1PC2

2PP 28VDC

28VDC 3XB 2XB

115

7PN

DC SVCE BUS

8PN

11PN

6PH

10PN

6PP 28VDC

210PP 5XB

28

4PP

206PP

1PR SHUNT

DC ESS BUS

4PC

208PP

SHUNT 3PB2

701PP

12PB1

6PB1

28VDC

501PP 5PR

BAT2 2PB2

401PP

502PP

704PP

12PB2

BAT BUS

1PC1

2PR

702PP

5PB1

101PP

1PN1

8PH

20PC

5PB2

4PB2 6PB2 1PB1 BCL−1

103PP

8PP 28VDC

1PB2 BCL−2

3PN1

DC SHED ESS BUS

301PP

11PB

3PX

212PP

5PU1 STATIC INV

24 − 50 − 00

901XP

12XB

5PU2 220XP

801XP 24 − 50 − 00

1PU1 TR1

21XN1 26V

5XN1

15XN1

110XP

7XN2

131XP−A

4XH

5XH 103XP

1XN1 1XP 115VAC

5XN2

401XP

AC ESS BUS

231XP−A

26V 15XN2

115VAC

101XP

21XN2

204XP

3XN2

4XP

2XC

AC BUS 2

2XP 115VAC

3XC 15XE

GLC−1 9XU1 GCU−1 1XU1

AES

BTC−1 11XU1

EPC 3XG

GLC−APU 3XS

4000XU

GCU−APU 1XS

FIGURE 24-22-00-13700-H SHEET 1 AC Main Generation (Normal Configuration) - General Schematic

APU GEN

8XS

GPCU 1XG

24-22-00 PB001

2PU2

14PU

10XN

12XN

3801GX 3805GX

BTC−2 11XU2

GLC−2 9XU2

FUEL PUMPS 28 − 21 − 00 GEN 1

4XX

202XP

1XN2

1XC

1XX

14XX

2XX

12XX

3802GX 3806GX EXTERNAL POWER RECEPTACLE

Page 25 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

1PE ESS TR

1PU2 TR2

210XP

431XP−A

26V

1PX

218XP

8XH

3XN1

AC BUS 1

27XN

115VAC

7XN1

2PU1

28XN

AC SHED ESS BUS 8XP

3PE

4000XU

16XX

214XP

216XP 212XP

4PE

ELEC PUMP−Y 29 − 24 − 00 GLC−EMERG 2XE

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_242200_0_AGV0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

BUS2 GEN 2

CL2

ZONE 1 BTC2

BUS1 GEN 1

CL1

ZONE 1 BTC1

BUS2 GEN 2

CL2

ZONE 2 BTC2

BUS1 GEN 1

CL1

ZONE 2 BTC1

N_MM_242200_0_BWQE_01_00

AES

FIGURE 24-22-00-15500-A SHEET 1 Zone of Protection

24-22-00 PB001

Page 26 May 01/12 Revision n˚: 40

AES FIGURE 24-22-00-15700-B SHEET 1 Electrical Generation Interface Unit - Schematic Diagram GLC

24-22-00 PB001 Page 27 May 01/12 Revision n˚: 40

TO GCU

FROM GCU

FROM GPCU

LIGHT RELAY (40mA)

FROM GPCU

FROM GCU

TO GCU

EXT PWR SW

FROM GCU

28VDC

B RECEPTACLE

GEN SW

GLC LIGHT RELAY (40mA)

GEN FAULT 28VDC

EPLC

FROM GCU : OVERLOAD

28VDC

DC GROUND

FROM GCPU

LIGHT RELAY (40mA)

INPUTS

TO GCU

AC GROUND

DISTRIBUTION CT

GEN SW

RELAY (40mA)

FROM GCU AC LOAD

28VDC

115VAC OA(POR)

FROM GCU

TO GCU

28VDC

FROM GCU

FROM IDG : LOW PRESSURE SW−89

3XT IDG DISC.CTL

FROM GCU : IDG DISC. <> LIGHT RELAY (40mA)

LIGHT RELAY (40mA)

GEN FAULT 28VDC

LIGHT RELAY (40mA)

GEN P/B SW POSITION

FLIP FLAP CIRCUIT

EXT PWR ON

EXT PWR AVAILABLE

GENERATOR FAULT

R=100

10W

10W

CHANNEL 2−EXT PWR OR APU GEN

−

ARINC CPU BOARD +

SUPPLY

OVERLOAD WARNING

CLASS 2 FAILURE

AC LOAD PARAMETER VALABLE

BACK UP SUPPLY

VOLTAGE AND FREQUENCY PARAMETERS

R=100

CHASSIS GROUND

−

CHANNEL 1−GEN 1 OR GEN 2

GEN P/B SW POSITION

FROM GCU

ARINC CPU BOARD +

SUPPLY

IDG OIL LOW PRESSURE

IDG DISC P/B POS

IDG DISC STATUS

GENERATOR FAULT

OVERLOAD WARNING

FROM GCU : OVERLOAD

AC LOAD PARAMETER VALABLE

BACK UP SUPPLY

OIL IN AND PARAMETERS OIL OUT

28VDC

DC GROUND

AC GROUND

VOLTAGE AND FREQUENCY PARAMETERS

OIL IN FROM GCU : COMMON OIL OUT

AC LOAD −

FROM GCU +

28VDC

115VAC OA(POR)

DISTRIBUTION CT

INPUTS

C RECEPTACLE

FROM CPCU

EXT PWR AUX RELAY (110mA)

TO SDAC 2

TO SDAC 1

SVDC FAULT LIGHT (230mA)

FROM GCU−APU OR GPCU

OUTPUTS

GLC AUX RELAY (110mA)

GEN SW

GCU

A RECEPTACLE

PR

PR

RECEPTACLE CANNON BK REY−125−300(OZ)

TO SDAC 2

TO SDAC 1

LIGHT RELAY (see GEN FAULT)

GCU

GCU

GCU

SVDC FAULT LIGHT (230mA)

OUTPUTS

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242200_0_AJN0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

PIN 2C OF GPCU (P. R)

EGIU CHANNEL 2

EST. PWR ON

EXT.PWR AUX LINE RELAY (110 mA)

SUPPLY J

PIN 2C OF GPCU (P. R)

CLOCK EXT. PWR P/B (SPRING LOADED P/B)

Q

K

FLIP − FLOP (MASTER − SLAVE)

IF 28VDC AT PIN 2C OF GPCU: Qn + 1 = Qn (CHANGE OF STATE AT EACH EXT. PWR P/B IMPULSE) IF OVDC AT PIN 2C OF GPCU: Q = 0

N_MM_242200_0_ALM0_01_00

AES

FIGURE 24-22-00-15800-A SHEET 1 Flip-Flop Circuit - Block Diagram

24-22-00 PB001

Page 28 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

EXT. PWR PARAMETERS

GEN 1 PARAMETERS

GPCU

GEN APU PARAMETERS

GCU − 1

GEN 2 PARAMETERS

GCU − APU

GCU − 2

CLASS 2 FAILURE

CHANNEL 2

CHANNEL 1

CHANNEL 2

EGIU 1

CHANNEL 1

EGIU 2

SDAC 1 (SYSTEM + ECAM)

SDAC 2 (SYSTEM + ECAM)

ARINC 429 ANALOG AND DISCRETE SIGNALS

N_MM_242200_0_ANM0_01_00

AES

FIGURE 24-22-00-16000-A SHEET 1 SDAC Communication - Block Diagram

24-22-00 PB001

Page 29 May 01/12 Revision n˚: 40

AES

FIGURE 24-22-00-17900-A SHEET 1 Current Transformers - Block Diagram

41XU1

1XU1

GCU−1

GEN 1

AC BUS 1

115VAC

42XU3

15XN1

4000XU

DIFFERENTIAL MEASURE AND PROTECTION

1XS

GCU−APU

FUEL PUMPS 53(54)QA 28−21−00

42XU1

DIFFERENTIAL MEASURE AND PROTECTION

42XU3

11XU1 BTC−1

11(12)QA

1XP

1XN1 4XP

101XP

103XP

131XP−A

110XP

APU GEN

DIFFERENTIAL MEASURE AND PROTECTION

26V

5XN1

1XC

21XN1

7XN1

3XN1

4MC

1MC

AC BUS 2

2XP

8XS

1XG

GPCU

42XU2

115VAC

2PU2

42XU4

DIFFERENTIAL MEASURE AND PROTECTION

10XN

EXTERNAL POWER RECEPTACLE

11XU2 BTC−2

1XN2

3XN2

5XN2

7XN2

15XN2

GCU−2

41XU2

1XU2

212XP

216XP

202XP

204XP

231XP−A

210XP

GALLEYS 24−56−00

WHC−2 30−42−00

FAN−EXTRACT 21−26−00

4XP

GEN 2

4000XU

DIFFERENTIAL MEASURE AND PROTECTION

DIFFERENTIAL MEASURE AND PROTECTION

26V

21XN2

5MC

2MC

13MC

12MC GALLEYS 24−56−00

6MC

3MC

WHC−1 30−42−00

1DG1

1DG2

FAN−BLOWER 21−26−00

8HQ

1HQ

7HQ

2HQ

ELEC PUMP−B 29−12−00

2705GJ

2XC

DC SUPPLY

2701GJ

2PU1

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242200_0_AKM0_01_00

24-22-00 PB001

Page 30 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL A B C . T6 T3 L3 . . T5 T2 L2 . ROTOR

. T4 T1 L1 .

L6 D L5

E

L4

41XU1

J RETURN EXCITER FIELD

PMG

DIFFERENTIAL MEASURE AND PROTECTION

GCR

S N

COM SENSE TEMP

OIL OUT TEMP OIL TEM COM OIL IN TEMP

SPEED SENSE

MAGNETIC PICK−UP

SENSE

LOW OIL PRESSURE

IDG DISC

IDG FAULT

1XU1 GCU1

DISC.SOL. 4000XU IDG1 301PP 28VDC

G L.O.P INFO IDG DISC P/BSW POS

1XT 5VAC ESS

SDAC 1

FAULT

SDAC 2

10LP

ENGINE LO PR

AES

5XT IDG DISC

3XT 7XT

FIGURE 24-22-00-19500-E SHEET 1 AC Main Generation Channel 1 - Schematic Diagram

ARINC CPU BOARD

22XU1 EGIU1 N_MM_242200_0_AQRA_01_00

24-22-00 PB001

Page 31 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL A B

M N

C

P

D

Q

E

R

RS422 1XG GPCU

DC1

IDG GCU POS.

RS422

OVER CURRENT

OIL OUT

OIL IN

A320 GCU POS.

AC LOAD

1XU1 GCU1

G

S COM OVER CURRENT

OIL OUT

OIL IN

AC LOAD

22XU1 EGIU1 N_MM_242200_0_AQRA_02_00

AES

FIGURE 24-22-00-19500-E SHEET 2 AC Main Generation Channel 1 - Schematic Diagram

24-22-00 PB001

Page 32 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL M N 1XP OC

P

42XU3 CT T3

L3

T2

L2

T1

L1

OA

T3

L3

OB

T2

L2

OC

T1

L1

OB

Q

LOAD

OA R 9XU1−GLC1

TO BTC2

11XU1−BTC1 42XU1 CT P.O.R LOCK OUT BTC

J

SUPPLY PROTECTION MODULE

DIFFERENTIAL MEASURE AND PROTECTION

3XU1−GEN1

5VAC ESS

5VAC ESS FAULT OFF

GLC1 PR

AUX−RLY

COMP. RESET

BTC1

SMOKE RLY

GEN COM.

FIRE FUNCTION

GPCU TEST

1XU1 GCU1

SMOKE RLY FIRE PANEL

S

LEVEL DETECT

GLC1 7XT

301PP 28VDC

TIMER 3*

GEN FAULT R

SUPPLY

22XU1 EGIU1

5VDC

50XU1 SENSOR TDC AC,1

GEN P/BSW POS. VOLTAGE AND FREQUENCY PARAMETERS BACK−UP SUPPLY

AC DC

24XU1

301PP 28VDC

EGIU1−CHANNEL 1 N_MM_242200_0_AQRA_03_00

AES

FIGURE 24-22-00-19500-E SHEET 3 AC Main Generation Channel 1 - Schematic Diagram

24-22-00 PB001

Page 33 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL P/BSW FAULT GEN2 OFF GCU−2 4XU2

3XU2

PRR

11XU2

SUPPLY

22XU2 GLC−2 9XU2

PMG2

9XU2

BTC−1 11XU1

A

9XU1

30XU1

2XU2

4XU1

9XU2

4XS

P/BSW BUSTIE

5XG

3XG

3XS

3PP 28VDC BAT BUS

15XU

OFF GCU−1

10XU 8XU

9XU2

BTC−2 11XU2 30XU2

B

11XU1

9XU1

4XU2

4XS

5XG

3XG

3XS

14XU

GCU−2 GCU−1

PMG1

9XU1 GLC−1 9XU1

SUPPLY 11XU1 4XU1 SMOKE

20XU

13XU

22XU1 P/BSW GEN1 OFF

PRR

FAULT

3XU1 N_MM_242200_0_ASN0_01_00

AES

FIGURE 24-22-00-19600-B SHEET 1 GLC/BTC Logic - Schematic Diagram

24-22-00 PB001

Page 34 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL GPCU PRR

EXT PWR

11XG SUPPLY

A EXT PWR CTL 3PP 28VDC BAT BUS

7XG 22XU1

5XU

9XU1

9XU2

11XU1

11XU2

5XG 6XS

B

GCU−3

PMG3 SUPPLY

PRR EPC 3XG

GLC APU 3XS

FAULT

P/BSW APU GEN

OFF

3XG

4XS

2XS

N_MM_242200_0_ASN0_02_00

AES

FIGURE 24-22-00-19600-B SHEET 2 GLC/BTC Logic - Schematic Diagram

24-22-00 PB001

Page 35 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

GLC−1 301PP BAT BUS

2XU1

BTC−1

GEN 1 FAULT OFF

PMG PR

LOCK−OUT BTC

AUX LINE 1 RLY

BTC−2

GCU−1 301PP BAT BUS

2XU2

GLC−2

GEN 2 FAULT OFF

PMG PR

LOCK−OUT BTC AUX LINE 2 RLY GCU−2

301PP BAT BUS

APU GEN

GLC−APU

6XS

EPC

FAULT OFF PMG

PR 301PP BAT BUS

GCU−APU

14XU

APU AUX LINE RLY

G.P PR GPCU 11XG EXT PWR CTL EXT PWR AUX RLY EGIU 1 − CHANNEL B N_MM_242200_0_AUM0_01_00

AES

FIGURE 24-22-00-19700-A SHEET 1 GLC-1 Supply - Schematic Diagram

24-22-00 PB001

Page 36 May 01/12 Revision n˚: 40

AES

FIGURE 24-22-00-19900-A SHEET 1 GEN 1 FAULT - Upper and Lower ECAM Display Unit

ACTION ON CLEAR P/BSW ON ECAM CP

RELEASED − OUT GEN 1 P/BSW

MANUAL CREW ACTION

AUTOMATIC TRANSFERT OF APU NETWORK 1 ON ANOTHER POWER SOURCE (GEN 2)

CONFIG. SYSTEM

24-22-00 PB001 WHITE "OFF"

OFF

FAULT

GEN 1

WHITE "OFF"

OFF

FAULT

GEN 1

AMBER "FAULT"

OFF

FAULT

GEN 1

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

GEN 1 FAULT (CLASS 1 − LEVEL 2)

NORMAL CONFIG.

NORMAL CONFIG.

ELEC GEN 1 FAULT

ELEC GEN 1 FAULT GEN 1...OFF THEN ON IF UNSUCCESSFUL GEN 1.....................OFF

ECAM UPPER DISPLAY

GEN 1

INOP SYS:

APU START UP MAIN GALLEY TO FL 310

TO FL 350

APU GEN UP

STATUS

NORMAL CONFIG.

SEE TWO PAGES FARTHER

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242200_0_AWM0_01_00

Page 37 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

DC BAT

DC 1

BAT 2 28V 0A

DC 2 DC ESS

TR 1 28V 110A

AC 1

GEN 1 00% 11 6 V 400 HZ IDG 1

ESS TR

EMER GEN

AC ESS

APU GEN

°C110

TR 2 28V 82A

AC 2

GEN 2 96% 11 6 V 400 HZ 110°C IDG 2

4WT2 DU − ECAM, LOWER

N_MM_242200_0_AWM0_02_00

AES

FIGURE 24-22-00-19900-A SHEET 2 GEN 1 FAULT - Upper and Lower ECAM Display Unit

24-22-00 PB001

Page 38 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

BAT 1 28V 0A

ELEC

BAT 2 28V 0A

DC BAT

DC 1

DC 2 DC ESS

TR 1 28V 110A

AC 1

ESS TR

EMER GEN

AC ESS

GEN 1 OFF

TR 2 28V 82A

AC 2

GEN 2 96% 116V 400HZ

APU GEN IDG 1

°C110

110°C

IDG 2

4WT2 DU − ECAM, LOWER

N_MM_242200_0_AWM0_03_00

AES

FIGURE 24-22-00-19900-A SHEET 3 GEN 1 FAULT - Upper and Lower ECAM Display Unit

24-22-00 PB001

Page 39 May 01/12 Revision n˚: 40

AES

FIGURE 24-22-00-20000-A SHEET 1 GEN 1 OFF - Upper and Lower ECAM Display Unit

PRESS − IN P/BSW

MANUAL CREW ACTION

− ENGINE 1 STARTING

NETWORK SUPPLIED BY APU GEN

CONFIG. SYSTEM

OFF

FAULT

GEN 1

WHITE "OFF"

OFF

FAULT

GEN 1

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

GEN 1 OFF (CLASS 1− LEVEL 2)

NORMAL CONFIG.

ELEC GEN 1 OFF

ECAM UPPER DISPLAY

NORMAL CONFIG.

PAGE

PRESELECTED

RETURN TO

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242200_0_BWM0_01_00

24-22-00 PB001

Page 40 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

BAT 2 28V 0A

DC BAT

DC 1

DC 2 DC ESS

TR 1 28V 110A

AC 1

GEN 1 OFF

ESS TR

EMER GEN

AC ESS

APU GEN 80% 116V 400HZ

IDG 1 °C110

TR 2 28V 82A

AC 2

GEN 2 00% 00V 00HZ 110°C IDG 2

4WT2 DU − ECAM, LOWER

N_MM_242200_0_BWM0_02_00

AES

FIGURE 24-22-00-20000-A SHEET 2 GEN 1 OFF - Upper and Lower ECAM Display Unit

24-22-00 PB001

Page 41 May 01/12 Revision n˚: 40

AES

FIGURE 24-22-00-20100-A SHEET 1 GEN 2 OFF _ Upper and Lower ECAM Display Unit

PRESS − IN P/BSW

MANUAL CREW ACTION

− ENGINE 2 STARTING

NETWORK SUPPLIED BY GEN 1 AND APU GEN

CONFIG. SYSTEM

OFF

FAULT

GEN 2

WHITE "OFF"

OFF

FAULT

GEN 2

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

GEN 2 OFF (CLASS 1− LEVEL 2)

NORMAL CONFIG.

ELEC GEN 2 OFF

ECAM UPPER DISPLAY

NORMAL CONFIG.

PAGE

PRESELECTED

RETURN TO

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242200_0_CAM0_01_00

24-22-00 PB001

Page 42 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

BAT 2 28V 0A

DC BAT

DC 1

DC 2 DC ESS

TR 1 28V 110A

AC 1

GEN 1 62% 116V 400HZ IDG 1 °C110

ESS TR

EMER GEN

AC ESS

TR 2 28V 82A

AC 2

GEN 2 APU GEN 60% 116V 400HZ

OFF

110°C IDG 2

4WT2 DU − ECAM, LOWER

N_MM_242200_0_CAM0_02_00

AES

FIGURE 24-22-00-20100-A SHEET 2 GEN 2 OFF _ Upper and Lower ECAM Display Unit

24-22-00 PB001

Page 43 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

GLC−1 301PP BAT BUS

2XU1

BTC−1

GEN 1 FAULT OFF

PMG PR

LOCK−OUT BTC

AUX LINE 1 RLY BTC−2

GCU−1

301PP BAT BUS

2XU2

GEN 2

GLC−2

FAULT OFF

PMG PR

BUS TIE RLY

LOCK−OUT BTC GCU−2

AUX LINE 2 RLY

301PP BAT BUS

APU GEN

GLC−APU

6XS

EPC

FAULT OFF PMG

PR 301PP BAT BUS

GCU−APU 5XU

301PP BAT BUS

APU AUX LINE RLY

14XU

G.P PR GPCU 11XG EXT PWR CTL

EGIU 1−CHANNEL B

EXT PWR AUX RLV1 N_MM_242200_0_BAM0_01_00

AES

FIGURE 24-22-00-20500-A SHEET 1 BTC-1 Supply - Schematic Diagram

24-22-00 PB001

Page 44 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 301PP BAT BUS

8XU GLC−1

301PP BAT BUS

2XU1

BTC−1

GEN 1 FAULT OFF

PMG PR

3XU1 P/B SW

LOCK−OUT BTC

4XU1 GLC−2 9XU1

GCU−1 301PP BAT BUS

2XU2

BTC−2 11XU1

11XU2

GEN 2 FAULT OFF

PMG PR

30XU2 BUS TIE RLY

3XU2 P/B SW

LOCK−OUT BTC

4XU2

9XU2

GCU−2 301PP BAT BUS

GLC−APU EPC

APU GEN 6XS

3XG FAULT OFF

PMG

PR

301PP BAT BUS 2XS

GCU−APU

5XU

301PP BAT BUS

14XU

4XS

3XS G.P

PR

GPCU

EXT PWR CTL

11XG

5XG RELAY EGIU 1 − CHANNEL B N_MM_242200_0_BCP0_01_00

AES

FIGURE 24-22-00-20800-C SHEET 1 BTC-2 Supply - Schematic Diagram

24-22-00 PB001

Page 45 May 01/12 Revision n˚: 40

AES

FIGURE 24-22-00-21000-A SHEET 1 AC BUS 1 Fault - Upper and Lower ECAM Display Unit

− CLEAR P/BSW (ON ECAM CP)

− BLOWER OVRD

− RELEASED − OUT AC ESS FEED P/BSW

MANUAL CREW ACTION

WHITE "FAULT"

− DC ESS BUS AND DC SHEDDABLE ESS BUS SUPPLIED BY TR ESS

WHITE "FAULT"

ALTN

FAULT

AC ESS FEED

ALTN

FAULT

AC ESS FEED

AMBER "FAULT"

ALTN

FAULT

AC ESS FEED

OVHD SYST PANEL IND.

− AC ESS BUS AND AC SHEDDABLE ESS BUS SUPPLIED BY AC2

− AC1 OFF

− COUPLING OF DC1, DC2 AND DC3

− TR1 INOP

− LOSS OF: AC1, AC ESS BUS, AC SHEDDABLE ESS BUS

CONFIG. SYSTEM

MASTER CAUTION

+

SINGLE CHIME

WARNING

ELEC

NORMAL CONFIG.

AC1 BUS FAULT

ECAM UPPER DISPLAY

AC BUS 1 FAULT (CLASS 1 − LEVEL 2)

CAT 3 SINGLE ONLY

CAB ZONE AT FIXED TEMP

1 NOP SYS TR1

STATUS

SEE FOLLOWING PAGE

ELEC AC ESS BUS FAULT AC ESS FEED............ALTN AC1 BUS FAULT BLOWER ................OVRD DC ESS BUS FAULT

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242200_0_BEM0_01_00

24-22-00 PB001

Page 46 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28 V 0A

DC BAT

BAT 2 28 V 0A

DC 1

DC 2 DC ESS

TR 1 0 V 0 A

AC 1

GEN 1 62 % 116 V 400 HZ IDG 1

ESS TR 28 V 62 A

EMER GEN

AC ESS

APU GEN

°C110

TR 2 28 V 130 A

AC 2

GEN 2 60 % 116 V 400 HZ 110°C

IDG 2

4WT2 DU − ECAM, LOWER

N_MM_242200_0_BEM0_02_00

AES

FIGURE 24-22-00-21000-A SHEET 2 AC BUS 1 Fault - Upper and Lower ECAM Display Unit

24-22-00 PB001

Page 47 May 01/12 Revision n˚: 40

AES

FIGURE 24-22-00-21100-A SHEET 1 AC BUS 2 Fault - Upper and Lower ECAM Display Unit

− MAINTAINS PRESSED − IN ELEC" P/BSW ON ECAM CP

− DC ESS BUS AND DC SHEDDABLE ESS BUS SUPPLIED BY TR ESS

− COUPLING OF DC1 DC2 AND DC3

− TR2 INOP.

− LOSS OF AC2

CONFIG. SYSTEM

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

SEE FOLLOWING PAGE

ELEC AC BUS 2 FAULT EXTRACT....................OVRD

ECAM UPPER DISPLAY

NOTA : CAPT CAN ALL ECAM ELEC IMAGE ON HIS ND IF REQUIRED BY MEANS OF THE EIS DMC3 AND ECAM /ND TRANSFERT CONTROLS.

− EXTRACT OVRD

MANUAL CREW ACTION

AC BUS 2 FAULT (CLASS 1 − LEVEL 2)

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242200_0_BJM0_01_00

24-22-00 PB001

Page 48 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

DC BAT

BAT 2 28V 0A

DC 1

DC 2 DC ESS

TR 1 28V 130A

AC 1

GEN 1 62% 11 6 V 400 HZ IDG 1

ESS TR

EMER GEN

TR 2 0V 0A

28V 62A AC ESS

APU GEN

° C110

AC 2 GEN 2 60% 11 6 V 400 HZ 110C °

IDG 2

4WT1 DU−ECAM, UPPER

N_MM_242200_0_BJM0_02_00

AES

FIGURE 24-22-00-21100-A SHEET 2 AC BUS 2 Fault - Upper and Lower ECAM Display Unit

24-22-00 PB001

Page 49 May 01/12 Revision n˚: 40

AES

FIGURE 24-22-00-21500-B SHEET 1 Smoke Detection - Upper and Lower ECAM Display Unit

− MAINTAINS PRESSED IN "ELEC" P/BSW ON ECAM CP

− REALIZES THE PROCEDURE − AC ESS BUS AND DC ESS BUS SUPPLIED BY CSM/G

− TWO FUEL PUMPS SUPPLIED BY GEN 1 (OVRD)

AFTER PROCEDURE:

− SMOKE DETECTION

CONFIG. SYSTEM

WHITE "OFF"

OFF

SMOKE

GEN 1 LINE

WHITE "OFF"

OFF

SMOKE

GEN 1 LINE

AMBER "SMOKE"

OFF

SMOKE

GEN 1 LINE

OVHD SYST PANEL IND.

SINGLE CHIME

WARNING

MASTER WARNING

+

IF SMOKE PERSISTS:

MANUEL CREW ACTION

EMER CONFIG

SEE TWO PAGES FARTHER

MIN RAT SPEED . . . 140KT I − APU MASTER SW . . . OFF I − BEFORE L/G EXTENSION: − GEN 2 . . . . . . . . . . . . ON − EMER ELEC GEN1 LINE. ON

ELEC

.WHEN EMER GEN AVAIL: − APU GEN . . . . . . . . OFF − GEN 2 . . . . . . . . . . . OFF I

− IF PERPECTIBLE SMOKE I IF SMOKE AFTER 5 MN00S: − EMER ELEC GEN1 LIN OFF − EMER ELEC PWR . MAN ON

AVIONICS SMOKE

ECAM UPPER DISPLAY

SMOKE DETECTION (CLASS 1 − LEVEL 3)

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242200_0_BNL0_01_00

24-22-00 PB001

Page 50 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

BAT 2 28V 0A

DC BAT

DC 2

DC 1 DC ESS TR 1 28V 110A

ESS TR

AC 1

GEN 1 62% 116V 400HZ IDG 1

°C110

EMER GEN

AC ESS

APU GEN 00% 116V 400HZ

TR 2 28V 82A

AC 2

GEN 2 60% 116V 400HZ 110°C IDG 2

4WT2 DU − ECAM, LOWER

N_MM_242200_0_BNL0_02_00

AES

FIGURE 24-22-00-21500-B SHEET 2 Smoke Detection - Upper and Lower ECAM Display Unit

24-22-00 PB001

Page 51 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28 V 0A

BAT 2 28 V 0A

DC BAT

DC 1

DC 2 DC ESS

TR 1 0V 0A

ESS TR 28 V 62 A

AC 1

GEN 1 06% 116 V 400 HZ IDG 1

EMER GEN 116 V 400 HZ AC ESS

TR 2 0V 0A

AC 2

GEN 2 APU GEN

°C110

OFF 110 C ° IDG 2

4WT1 DU−ECAM, UPPER

N_MM_242200_0_BNL0_03_00

AES

FIGURE 24-22-00-21500-B SHEET 3 Smoke Detection - Upper and Lower ECAM Display Unit

24-22-00 PB001

Page 52 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC MAIN GENERATION - ADJUSTMENT/TEST ** On A/C ALL Task 24-22-00-710-001-A Operational Test of the Generator Line Contactor (GLC-1) Opening in the Smoke Procedure 1.

Reason for the Job (Ref. MPD 24-51-00-01-) OPERATIONAL CHECK OF GENERATOR LINE CONTACTOR OPENING Test to make sure that the generator line contactor 1 opens and test of the power supply of the two fuel pumps in smoke procedure.

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

210

CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD B.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A 71-00-00-710-018-A 71-00-00-710-043-A

EIS Start Procedure EIS Stop Procedure Discontinued Start, Restart and Shutdown Procedures Normal Engine Automatic Start Procedure

3.

Job Set-up Subtask 24-22-00-860-050-B A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

Start the engine (Ref. TASK 71-00-00-710-043-A). NOTE :

AES

You can do this test: start engine No. 1 only. Energize the electrical circuit No. 2 with an electrical ground power unit or with the APU (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

24-22-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

On the HYD/FUEL panel 40VU, make sure that the L TK PUMPS/1 AND 2 and R TK PUMPS/1 AND 2 pushbutton switches are pushed.

(5)

On the ECAM control panel, push the FUEL key. On the lower ECAM display unit, make sure that the L wing tank pumps 1 and 2 and R wing tank pumps 1 and 2 operate correctly.

Subtask 24-22-00-865-050-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

49VU

DESIGNATION FUEL/SMOKE/CONFIG/PUMP CTL

55QA

A14

121VU

FUEL/L WING TK/PUMP1 SPLY

1QA

N23

121VU

FUEL/R WING TK/PUMP1 SPLY

2QA

Q23

121VU

FUEL/PUMPS/1/R CTL AND L IND

4QA

R28

121VU

FUEL/PUMPS/1/L CTL AND R IND

3QA

R23

123VU

L WING TK/PUMP 1/STBY SPLY

11QA

AD12

123VU

R WING TK/PUMP 1/STBY SPLY

12QA

AE12

123VU

R WING TK/PUMP 1/STBY SPLY

12QA

AE12

4.

FIN

LOCATION

Procedure Subtask 24-22-00-710-050-B A.

Operational test of the GLC-1 ACTION

1.On the panel 121VU: . open the circuit breaker 1QA.

RESULT On the panel 40VU: . the FAULT legend of the L TK PUMPS/1 pushbutton switch comes on, On the lower ECAM display unit: . on the FUEL page, the pump No. 1 of the left tank no longer operates.

2.On the EMER ELEC PWR panel 21VU: . release the GEN 1 LINE pushbutton switch.

On the panel 21VU: . the OFF legend of the GEN 1 LINE pushbutton switch comes on. On the panel 40VU: . the FAULT legend of the L TK PUMPS/1 pushbutton switch goes off.

3.On the ECAM control panel: . push the ELEC key.

On the lower ECAM display unit: . the generator No. 1 no longer supplies the AC 1 busbar. This busbar is supplied from the other generator with the transfer circuit. On the lower ECAM display unit: . pump No. 1 of the left tank operates, . pump No. 1 of the right tank operates.

4.On the ECAM control panel: . push the FUEL key. 5.On the panel 121VU: . close the circuit breaker 1QA, . open the circuit breaker 2QA. 6.On the EMER ELEC PWR panel 21VU: . push the GEN 1 LINE pushbutton switch.

AES

There is no change.

On the panel 21VU: . the OFF legend of the GEN 1 LINE pushbutton switch goes off.

24-22-00 PB501

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION

RESULT On the panel 40VU: . the FAULT legend of the R TK PUMPS/1 pushbutton switch comes on. On the lower ECAM display unit: . on the FUEL page, the pump No. 1 of the right tank no longer operates.

7.On the ECAM control panel: . push the ELEC key.

On the lower ECAM display unit: . the generator No. 1 supplies the circuit No. 1. The other generator supplies the circuit No. 2.

8.On the panel 121VU: . close the circuit breaker 2QA.

On the panel 40VU: . the FAULT legend of the R TK PUMPS/1 pushbutton switch goes off.

9.On the ECAM control panel: . push the FUEL key.

On the lower ECAM display unit: . the pump No. 1 of the right tank operates.

5.

Close-up Subtask 24-22-00-860-051-B A.

AES

Put the aircraft back to its initial configuration. (1)

Stop the engines (Ref. TASK 71-00-00-710-018-A).

(2)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(3)

De-energize the aircraft electrical circuits or de-energize the APU (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-22-00 PB501

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-22-00-710-002-A Operational Test of the Transfer Inhibition 1.

Reason for the Job (Ref. MPD 24-22-00-01-) OPERATIONAL CHECK OF TRANSFER INHIBITION Make sure that the transfer function is off when you release the BUS TIE pushbutton switch.

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

210

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

B.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

3.

Job Set-up Subtask 24-22-00-860-052-A A.

4.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

On the ELEC panel 35VU, make sure that the BAT1 and BAT2 pushbutton switches are pushed.

Procedure Subtask 24-22-00-710-051-A A.

Operational test of the transfer inhibition ACTION

1.On the panel 35VU: . release the BUS TIE pushbutton switch.

RESULT In the cockpit, on the panel 35VU: . loss of the power supply from the electrical ground power unit: .the OFF legend of the BUS TIE pushbutton switch comes on. NOTE :

AES

This shows that the transfer contactors are open. The batteries are the only available power supply.

24-22-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 2.On the panel 35VU: . push the BUS TIE pushbutton switch.

5.

RESULT In the cockpit, on the panel 35VU: . the OFF legend of the BUS TIE pushbutton switch goes off. All the aircraft electrical circuits are supplied.

Close-up Subtask 24-22-00-862-051-A A.

Put the aircraft back to its initial configuration. (1)

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02)

24-22-00 PB501

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CURRENT TRANSFORMER - AC - REMOVAL/INSTALLATION ** On A/C ALL Task 24-22-17-000-001-A Removal of the AC Current Transformers WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 42XU1, 42XU2, 42XU3, 42XU4 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY AR WARNING NOTICE(S)

DESIGNATION

FOR FIN 42XU1(CT-AC, 1) FOR FIN 42XU2(CT-AC, 2) No specific

AR

CAP - BLANKING

AR

WARNING NOTICE(S)

No specific

AR

CAP - BLANKING

No specific

AR

TIE WRAP

FOR FIN 42XU1(CT-AC, 1) FOR FIN 42XU2(CT-AC, 2) FOR FIN 42XU3(CT-AC, 1) FOR FIN 42XU4(CT-AC, 2) No specific FOR FIN 42XU3(CT-AC, 1) FOR FIN 42XU4(CT-AC, 2)

B.

Work Zones and Access Panels ZONE/ACCESS

131 133 212 FOR FIN 42XU1(CT-AC, 1)

ZONE DESCRIPTION FORWARD CARGO COMPARTMENT BAY UNDER FWD CAR COMPT FLOOR COCKPIT

FOR FIN 42XU2(CT-AC, 2) FOR FIN 42XU3(CT-AC, 1) FOR FIN 42XU4(CT-AC, 2) 121AL

AES

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Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Referenced Information

REFERENCE DESIGNATION (Ref. Fig. 24-22-17-991-00300-A - AC Current Transformer (42XU3, 42XU4)) (Ref. Fig. 24-22-17-991-00400-A - AC Current Transformer (42XU1, 42XU2)) (Ref. Fig. 24-22-17-991-00300-B - AC Current Transformer (42XU3, 42XU4)) (Ref. Fig. 24-22-17-991-00400-B - AC Current Transformer (42XU1, 42XU2)) FOR FIN 42XU1(CT-AC, 1) 24-22-55-000-001-A FOR FIN 42XU1(CT-AC, 1)

Removal of the Contactors

FOR FIN 42XU2(CT-AC, 2) 24-23-55-000-001-A FOR FIN 42XU1(CT-AC, 1)

Removal of the APU GLC

FOR FIN 42XU2(CT-AC, 2) FOR FIN 42XU3(CT-AC, 1) FOR FIN 42XU4(CT-AC, 2) 25-11-41-000-001-A

Removal of the Third Occupant Seat

FOR FIN 42XU2(CT-AC, 2) 24-22-55-000-001-A 3.

Removal of the Contactors

Job Set-up Subtask 24-22-17-010-051-A A.

Get Access (1)

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2), 42XU3 (CT-AC, 1), 42XU4 (CT-AC, 2) Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

On the rear panel 120VU, open the panel which gives access to the AC power center 123VU.

(3)

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2) Remove the APU GLC (3XS) (Ref. TASK 24-23-55-000-001-A).

(4)

FOR 42XU1 (CT-AC, 1) Remove the BTC-1 (11XU1) (Ref. TASK 24-22-55-000-001-A).

(5)

FOR 42XU2 (CT-AC, 2) Remove the BTC-2 (11XU2) (Ref. TASK 24-22-55-000-001-A).

Subtask 24-22-17-941-050-A B.

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2), 42XU3 (CT-AC, 1), 42XU4 (CT-AC, 2) (a)

(3)

AES

In . . . .

Put WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT1, BAT2, APU GEN, GEN1, GEN2, EXT PWR.

24-22-17 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

4.

In the cockpit, put WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

Procedure

** On A/C 003-004 (Ref. Fig. 24-22-17-991-00300-A - AC Current Transformer (42XU3, 42XU4)) (Ref. Fig. 24-22-17-991-00400-A - AC Current Transformer (42XU1, 42XU2)) ** On A/C 005-099 (Ref. Fig. 24-22-17-991-00300-B - AC Current Transformer (42XU3, 42XU4)) (Ref. Fig. 24-22-17-991-00400-B - AC Current Transformer (42XU1, 42XU2)) ** On A/C 003-004 Subtask 24-22-17-020-051-A A.

Removal of the AC Current Transformer (1)

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2) (a)

Remove the nuts (8) and the washers (7) from the studs of the contactor (5).

(b)

Disconnect the bars (6) from the studs of the contactor (5).

(c)

Disconnect the electrical connector (4) from the current transformer (1).

(d)

Put CAP - BLANKING on the disconnected electrical connector (4) and electrical receptacle.

(e)

Remove the screws (3) and the washers (2) from the current transformer (1).

(f)

Remove the current transformer (1).

Subtask 24-22-17-020-052-A B.

Removal of the AC Current Transformer (1)

FOR 42XU3 (CT-AC, 1), 42XU4 (CT-AC, 2) CAUTION :

AES

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(a)

FOR 42XU3 (CT-AC, 1) In the rear panel 120VU, disconnect all the cables from the pin 2 of the circuit breakers connected to the AC BUS 1 busbar 1XP.

(b)

FOR 42XU4 (CT-AC, 2) In the rear panel 120VU, disconnect all the cables from the pin 2 of the circuit breakers connected to the AC BUS 2 busbar 2XP.

(c)

In the AC power center 123VU, disconnect all the cables from the pin 2 of the circuit breakers 11QA and 12QA.

(d)

Record the location and the color of the cables of each bundle which goes through the current transformer (1).

(e)

Remove the screws (12) and the washers (11) from the studs of the contactor (5).

24-22-17 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (f)

Disconnect the cables (10) from the studs of the contactor (5). NOTE :

You must identify (also with the indications on the current transformer) and disconnect only the cables which go through the current transformer.

(g)

Remove the nuts (9) and the washers (8) from the studs of the contactor (5).

(h)

Disconnect the cables (6) and (7) from the studs of the contactor (5).

(i)

Disconnect the electrical connector (4) from the current transformer (1).

(j)

Put CAP - BLANKING on the disconnected electrical connector (4) and electrical receptacle.

(k)

Remove the screws (3) and the washers (2) from the current transformer (1).

(l)

Remove the necessary TIE WRAP to move the current transformer (1) along the cable bundles.

(m) Remove the current transformer (1). ** On A/C 005-099 Subtask 24-22-17-020-051-B A.

Removal of the AC Current Transformer (1)

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2) (a)

Remove the screws (9) and the washers (8) from the studs of the module 29XN and 30XN1 (30XN2).

(b)

Disconnect the bars (7) from the studs of the modules 29XN and 30XN1 (30XN2).

(c)

Disconnect the electrical connector (4) from the current transformer (1).

(d)

Put CAP - BLANKING on the disconnected electrical connector (4) and electrical receptacle.

(e)

Remove the screws (3), the washers (2), the nuts (5) and the washers (6) from the current transformer (1).

(f)

Remove the current transformer (1).

Subtask 24-22-17-020-052-B B.

Removal of the AC Current Transformer (1)

FOR 42XU3 (CT-AC, 1), 42XU4 (CT-AC, 2) CAUTION :

AES

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(a)

FOR 42XU3 (CT-AC, 1) In the rear panel 120VU, disconnect all the cables from the pin 2 of the circuit breakers connected to the AC BUS 1 busbar 1XP.

(b)

FOR 42XU4 (CT-AC, 2) In the rear panel 120VU, disconnect all the cables from the pin 2 of the circuit breakers connected to the AC BUS 2 busbar 2XP.

(c)

In the AC power center 123VU, disconnect all the cables from the pin 2 of the circuit breakers 11QA and 12QA.

(d)

Record the location and the color of the cables each bundle which goes through the current transformer (1).

(e)

Remove the screws (12) and the washers (11) from the studs of the module 30XN1 (30XN2).

24-22-17 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (f)

Disconnect the cables (10) from the studs of the module 30XN1 (30XN2). NOTE :

You must identify (also with the indications on the current transformer) and disconnect only the cables which go through the current transformer.

(g)

Remove the nuts (9) and the washers (8) from the studs of the module 30XN1 (30XN2).

(h)

Disconnect the cables (6) and (7) from the studs of the module 30XN1 (30XN2).

(i)

Disconnect the electrical connector (4) from the current transformer (1).

(j)

Put CAP - BLANKING on the disconnected electrical connector (4) and electrical receptacle.

(k)

Remove the screws (3) and the washers (2) from the current transformer (1).

(l)

Remove and discard the necessary TIE WRAP to move the current transformer (1) along the cable bundles.

(m) Remove the current transformer (1).

AES

24-22-17 PB401

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

A 120VU

B

122VU 42XU4

121VU

B 42XU3

124VU 123VU 9XU2

C

9XU1

C

A C 6 7 8 9 10

11

12

B

1

5

4 2 3 N_MM_242217_4_ACM0_01_00

AES

FIGURE 24-22-17-991-00300-A SHEET 1 AC Current Transformer (42XU3, 42XU4)

24-22-17 PB401

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

A 120VU

122VU

B

121VU 124VU

11XU2

123VU

C

42XU1 11XU1

42XU2

B C

A B 4

C

1 6

6

5

2 3

6

7

8 N_MM_242217_4_ADM0_01_00

AES

FIGURE 24-22-17-991-00400-A SHEET 1 AC Current Transformer (42XU1, 42XU2)

24-22-17 PB401

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A B

120VU

B

122VU

121VU

42XU4 42XU3

124VU 123VU

30XN2 9XU2

30XN1 9XU1

C C

A B

1

MODULE

C 6

4 2

7 3

8 9 10

11

12

5 N_MM_242217_4_ACP0_01_00

AES

FIGURE 24-22-17-991-00300-B SHEET 1 AC Current Transformer (42XU3, 42XU4)

24-22-17 PB401

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A 120VU

122VU

B

121VU 11XU2

124VU 123VU

C

42XU1

30XN2

11XU1 30XN1

42XU2

A

B C

4

1

B

C

MODULE

5 6 7

2 3

7

8

9 N_MM_242217_4_ADP0_01_00

AES

FIGURE 24-22-17-991-00400-B SHEET 1 AC Current Transformer (42XU1, 42XU2)

24-22-17 PB401

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-22-17-400-001-A Installation of the AC Current Transformers WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 42XU1, 42XU2, 42XU3, 42XU4 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY AR WARNING NOTICE(S)

DESIGNATION

** On A/C 005-099 FOR FIN 42XU1(CT-AC, 1) FOR FIN 42XU2(CT-AC, 2) No specific

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

FOR FIN 42XU1(CT-AC, 1) FOR FIN 42XU2(CT-AC, 2) FOR FIN 42XU3(CT-AC, 1) FOR FIN 42XU4(CT-AC, 2) No specific

AR

WARNING NOTICE(S)

AR

TIE WRAP

FOR FIN 42XU3(CT-AC, 1) FOR FIN 42XU4(CT-AC, 2) No specific No specific

Torque wrench: range to between 0.00 and 1.20 M.DAN (0.00 and 9.00 LBF.FT)

No specific

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

B.

Work Zones and Access Panels ZONE/ACCESS

131 133 212 FOR FIN 42XU1(CT-AC, 1)

ZONE DESCRIPTION FORWARD CARGO COMPARTMENT BAY UNDER FWD CAR COMPT FLOOR COCKPIT

FOR FIN 42XU2(CT-AC, 2) FOR FIN 42XU3(CT-AC, 1) FOR FIN 42XU4(CT-AC, 2) 121AL

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Referenced Information

REFERENCE 24-41-00-740-004-A

DESIGNATION Operational Check of the GPCU via the CFDS

24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

(Ref. Fig. 24-22-17-991-00300-A - AC Current Transformer (42XU3, 42XU4)) (Ref. Fig. 24-22-17-991-00400-A - AC Current Transformer (42XU1, 42XU2)) (Ref. Fig. 24-22-17-991-00300-B - AC Current Transformer (42XU3, 42XU4)) (Ref. Fig. 24-22-17-991-00400-B - AC Current Transformer (42XU1, 42XU2)) FOR FIN 42XU1(CT-AC, 1) 24-22-55-000-001-A 24-22-55-400-002-A FOR FIN 42XU1(CT-AC, 1)

Removal of the Contactors Installation of the Contactors

FOR FIN 42XU2(CT-AC, 2) 24-23-55-000-001-A 24-23-55-400-001-A 24-41-00-861-002-A

Removal of the APU GLC Installation of the APU GLC Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

FOR FIN 42XU1(CT-AC, 1) FOR FIN 42XU2(CT-AC, 2) FOR FIN 42XU3(CT-AC, 1) FOR FIN 42XU4(CT-AC, 2) 24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-11-41-000-001-A

Removal of the Third Occupant Seat

25-11-41-400-001-A

Installation of the Third Occupant Seat

FOR FIN 42XU2(CT-AC, 2) 24-22-55-000-001-A 24-22-55-400-002-A FOR FIN 42XU3(CT-AC, 1)

Removal of the Contactors Installation of the Contactors

21-26-00-710-002-A

Operational Check of Override Function (BLOWER and EXTRACT)

24-24-00-710-001-A

Operational Test of the Emergency Generation System

** On A/C 003-004 24-26-00-710-001-A

Operational Test of the Manual and Automatic Shedding of the Galleys

** On A/C 005-099 24-26-00-710-002-A

Operational Test of the Manual and Automatic Galley and Bus Shedding

24-32-00-710-001-A

Operational Test of the DC Generation Switching

28-21-00-710-001-A

Operational Test of the Wing-Tank Fuel Control

AES

24-22-17 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 29-12-00-710-001-A 29-31-00-710-001-A

DESIGNATION Functional Check of Blue Electrical Pump Pressure by Reading ECAM Indication Functional Check of Reservoir Low Level Warning

30-31-00-710-001-A 30-42-00-710-001-A

Operational Test of the Probe Ice Protection Operational Test of the Windshield Anti-Icing and Defogging

33-25-00-710-001-A

Operational test of the Passenger Reading Light System

33-51-00-710-001-A

Operational Test of the Emergency Lights

FOR FIN 42XU4(CT-AC, 2) 21-26-00-710-002-A

Operational Check of Override Function (BLOWER and EXTRACT)

24-24-00-710-001-A

Operational Test of the Emergency Generation System

** On A/C 003-004 24-26-00-710-001-A

Operational Test of the Manual and Automatic Shedding of the Galleys

** On A/C 005-099 24-26-00-710-002-A

Operational Test of the Manual and Automatic Galley and Bus Shedding

24-32-00-710-001-A

Operational Test of the DC Generation Switching

24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

28-21-00-710-001-A

Operational Test of the Wing-Tank Fuel Control

30-31-00-710-001-A 30-42-00-710-001-A

Operational Test of the Probe Ice Protection Operational Test of the Windshield Anti-Icing and Defogging

33-21-00-710-001-A 33-25-00-710-001-A

Operational Test of the General Illumination Operational test of the Passenger Reading Light System

34-11-00-710-001-A

Test of the Monitoring of the ADR/AOA 26VAC Power Supply

3.

Job Set-up ** On A/C ALL Subtask 24-22-17-010-053-A A.

AES

Get Access (1)

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2), 42XU3 (CT-AC, 1), 42XU4 (CT-AC, 2) Make sure that the Third Occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(2)

On the rear panel 120VU, make sure that the panel which gives access to the AC power center 123VU is open.

(3)

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2) Make sure that the APU GLC (3XS) is removed (Ref. TASK 24-23-55-000-001-A).

(4)

FOR 42XU1 (CT-AC, 1) Make sure that the BTC-1 (11XU1) is removed (Ref. TASK 24-22-55-000-001-A).

(5)

FOR 42XU2 (CT-AC, 2) Make sure that the BTC-2 (11XU2) is removed (Ref. TASK 24-22-55-000-001-A).

24-22-17 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-22-17-860-050-A B.

Aircraft Maintenance Configuration (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2), 42XU3 (CT-AC, 1), 42XU4 (CT-AC, 2) (a)

4.

Make sure that the WARNING NOTICE(S) is (are) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT1, BAT2, APU GEN, GEN1, GEN2, EXT PWR.

(4)

In the cockpit, make sure that the WARNING NOTICE(S) is (are) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

Procedure

** On A/C 003-004 (Ref. Fig. 24-22-17-991-00300-A - AC Current Transformer (42XU3, 42XU4)) (Ref. Fig. 24-22-17-991-00400-A - AC Current Transformer (42XU1, 42XU2)) ** On A/C 005-099 (Ref. Fig. 24-22-17-991-00300-B - AC Current Transformer (42XU3, 42XU4)) (Ref. Fig. 24-22-17-991-00400-B - AC Current Transformer (42XU1, 42XU2)) ** On A/C 003-004 Subtask 24-22-17-420-051-A A.

Installation of the AC Current Transformer (1)

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2) (a)

Install the washers (2) and the screws (3) on the current transformer (1) and tighten them.

(b)

Remove the blanking caps from the electrical connectors.

(c)

Make sure that the electrical connectors are clean and in the correct condition.

(d)

Connect the electrical connector (4) to the current transformer (1).

(e)

Connect the bars (6) to the studs of the contactor (5).

(f)

Install the washers (7) and the nuts (8) on the studs of the contactors (5) and tighten them.

Subtask 24-22-17-420-052-A B.

Installation of the AC Current Transformer (1)

FOR 42XU3 (CT-AC, 1), 42XU4 (CT-AC, 2) (a)

Put the disconnected cables through the current transformer (1). NOTE :

AES

Make sure that the location and the color of the cables of each bundle agree with those you recorded at the removal.

24-22-17 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b)

Move the current transformer (1) along the cable bundles.

(c)

Install the washers (2) and the screws (3) on the current transformer (1) and tighten them.

(d)

Remove the blanking caps from the electrical connectors.

(e)

Make sure that the electrical connectors are clean and in the correct condition.

(f)

Connect the electrical connector (4) to the current transformer (1).

(g)

Install new TIE WRAP.

(h)

Connect the cables (6) and (7) to the studs of the contactors (5).

(i)

Install the washers (8) and the nuts (9) on the studs of the contactor (5) and tighten them.

(j)

Connect the cables (10) to the studs of the contactor (5).

(k)

Install the washers (11) and the screws (12) on the studs of the contactor (5) and tighten them.

(l)

FOR 42XU3 (CT-AC, 1) In the rear panel 120VU, connect the related cables to the pin 2 of the circuit breakers connected to the AC BUS 1 busbar 1XP.

(m) FOR 42XU4 (CT-AC, 2) In the rear panel 120VU, connect the related cables to the pin 2 of the circuit breakers connected to the AC BUS 2 busbar 2XP. (n)

In the AC power center 123VU, connect the related cables to the pin 2 of the circuit breakers 11QA and 12QA. NOTE :

Make sure that the location and the color of the cables agree with those you recorded at the removal.

** On A/C 005-099 Subtask 24-22-17-420-051-B A.

Installation of the AC Current Transformer (1)

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2) (a)

Install the washers (2), the screws (3), the washers (6) and the nuts (5) on the current transformer (1) and tighten them.

(b)

Remove the blanking caps from the electrical connector (4) and the electrical receptacle.

(c)

Make sure that the electrical connectors are clean and in the correct condition.

(d)

Connect the electrical connector (4) to the current transformer (1).

(e)

Connect the bars (7) to the studs of the modules 29XN and 30XN1 (30XN2).

(f)

Install the washers (8) and the screws (9) on the studs of the modules 29XN and 30XN1 (30XN2).

(g)

TORQUE the screws (9) to between 0.73 and 0.81 M.DAN (64.60 and 71.68 LBF.IN).

Subtask 24-22-17-420-052-B B.

Installation of the AC Current Transformer (1)

FOR 42XU3 (CT-AC, 1), 42XU4 (CT-AC, 2) (a)

Put the disconnected cables through the current transformer (1). NOTE :

AES

Make sure that the location and the color of the cables of each bundle agree with those you recorded at the removal.

24-22-17 PB401

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b)

Move the current transformer (1) along the cable bundles.

(c)

Install the washers (2) and the screws (3) on the current transformer (1) and tighten them.

(d)

Remove the blanking caps from the electrical connector (4) and electrical receptacle.

(e)

Make sure that the electrical connectors are clean and in the correct condition.

(f)

Connect the electrical connector (4) to the current transformer (1).

(g)

Install new TIE WRAP.

(h)

Connect the cables (6) and (7) to the studs of the module 30XN1 (30XN2).

(i)

Install the washers (8) and the nuts (9) on the studs of the module 30XN1 (30XN2).

(j)

TORQUE the nuts (9) to between 1.25 and 1.35 M.DAN (110.62 and 119.47 LBF.IN).

(k)

Connect the cables (10) to the studs of the module 30XN1 (30XN2).

(l)

Install the washers (11) and the screws (12) on the studs of the module 30XN1 (30XN2).

(m) TORQUE the screws (12) to between 0.17 and 0.19 M.DAN (15.04 and 16.81 LBF.IN). (n)

FOR 42XU3 (CT-AC, 1) In the rear panel 120VU, connect the related wires to pin 2 of the circuit breakers connected to the AC BUS 1 busbar 1XP.

(o)

FOR 42XU4 (CT-AC, 2) In the rear panel 120VU, connect the related wires to pin 2 of the circuit breakers connected to the AC BUS 2 busbar 2XP.

(p)

In the AC power center 123VU, connect the related wires to pin 2 of the circuit breakers 11QA and 12QA. NOTE :

Make sure that the location and the color of the cables agree with those you recorded at the removal.

** On A/C ALL Subtask 24-22-17-410-054-A C.

Close Access (1)

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2) (a)

Make sure that the work area is clean and clear of tool(s) and other items.

(b)

Install the APU GLC (3XS) (Ref. TASK 24-23-55-400-001-A).

(c)

FOR 42XU1 (CT-AC, 1) Install the BTC-1 (11XU1) (Ref. TASK 24-22-55-400-002-A).

(d)

FOR 42XU2 (CT-AC, 2) Install the BTC-2 (11XU2) (Ref. TASK 24-22-55-400-002-A).

Subtask 24-22-17-860-054-A D.

Aircraft Maintenance Configuration (1)

AES

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2) Energize the aircraft electrical circuits from the external power (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

24-22-17 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 Subtask 24-22-17-860-057-A E.

Aircraft Maintenance Configuration (1)

FOR 42XU3 (CT-AC, 1) Do these tests: . (Ref. TASK 24-26-00-710-001-A), . (Ref. TASK 29-12-00-710-001-A), . (Ref. TASK 21-26-00-710-002-A), . (Ref. TASK 30-42-00-710-001-A), . (Ref. TASK 28-21-00-710-001-A), . (Ref. TASK 33-51-00-710-001-A), . (Ref. TASK 29-31-00-710-001-A), . (Ref. TASK 33-25-00-710-001-A), . (Ref. TASK 24-24-00-710-001-A), . (Ref. TASK 30-31-00-710-001-A), . (Ref. TASK 24-32-00-710-001-A).

(2)

Energize the aircraft electrical circuits from the external power (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

Subtask 24-22-17-860-058-A F.

Aircraft Maintenance Configuration (1)

FOR 42XU4 (CT-AC, 2) (a)

(b)

Do . . . . . . . . . .

these tests: (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK

24-26-00-710-001-A), 21-26-00-710-002-A), 30-42-00-710-001-A), 33-25-00-710-001-A), 28-21-00-710-001-A), 30-31-00-710-001-A), 34-11-00-710-001-A), 33-21-00-710-001-A), 24-24-00-710-001-A), 24-32-00-710-001-A).

Energize the aircraft electrical circuits from the external power (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

** On A/C 005-099 Subtask 24-22-17-860-057-B E.

Aircraft Maintenance Configuration (1)

AES

FOR 42XU3 (CT-AC, 1) Do these tests: . (Ref. TASK 24-26-00-710-002-A), . (Ref. TASK 29-12-00-710-001-A), . (Ref. TASK 21-26-00-710-002-A), . (Ref. TASK 30-42-00-710-001-A), . (Ref. TASK 28-21-00-710-001-A), . (Ref. TASK 33-51-00-710-001-A), . (Ref. TASK 29-31-00-710-001-A), . (Ref. TASK 33-25-00-710-001-A),

24-22-17 PB401

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . . . (2)

(Ref. TASK 24-24-00-710-001-A), (Ref. TASK 30-31-00-710-001-A), (Ref. TASK 24-32-00-710-001-A).

Energize the aircraft electrical circuits from the external power (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

Subtask 24-22-17-860-058-B F.

Aircraft Maintenance Configuration (1)

FOR 42XU4 (CT-AC, 2) (a)

(b)

Do . . . . . . . . . .

these tests: (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK (Ref. TASK

24-26-00-710-002-A), 21-26-00-710-002-A), 30-42-00-710-001-A), 33-25-00-710-001-A), 28-21-00-710-001-A), 30-31-00-710-001-A), 34-11-00-710-001-A), 33-21-00-710-001-A), 24-24-00-710-001-A), 24-32-00-710-001-A).

Energize the aircraft electrical circuits from the external power (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

** On A/C ALL Subtask 24-22-17-865-050-A G.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

FWD GALLEY/FEEDER F

16MC

AC10

FWD GALLEY/FEEDER C

1MC

AE10

122VU

FIN

LOCATION

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

** On A/C 005-099 123VU

AES

24-22-17 PB401

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 Subtask 24-22-17-710-050-A H.

Operational Test (1)

Do this test:

ACTION 1.On the ECAM control panel: . Push the ELEC key to get the ELEC page.

RESULT On the lower ECAM display unit: . The ELEC page comes into view.

2.On the ELEC panel 35VU: . Push the GALLEY pushbutton switch.

On the panel 35VU: . The OFF legend of the GALLEY pushbutton switch goes off.

3.In the FWD and/or AFT galleys: . Energize all the items of equipment.

On the lower ECAM display unit: . Make sure that the electrical parameters (load, voltage and frequency) of the APU GEN are correct.

4.On the MCDU: On the MCDU, on the AC GEN page: . Do the operational check of the GPCU with the CFDS . The TEST OK message comes into view (after some (Ref. TASK 24-41-00-740-004-A). seconds). ** On A/C 005-099 Subtask 24-22-17-710-050-B H.

Operational Test (1)

Do this test:

ACTION 1.On the ECAM control panel: . Push the ELEC key to get the ELEC page.

RESULT On the lower ECAM display unit: . The ELEC page comes into view.

2.On the ELEC panel 35VU: . Push the GALY & CAB pushbutton switch.

On the panel 35VU: . The OFF legend of the GALY & CAB pushbutton switch goes off.

3.In the FWD and/or AFT galleys: . Energize all the items of equipment.

On the lower ECAM display unit: . Make sure that the electrical parameters (load, voltage and frequency) of the APU GEN are correct.

4.On the MCDU: On the MCDU, on the AC GEN page: . Do the operational check of the GPCU with the CFDS . The TEST OK message comes into view (after some (Ref. TASK 24-41-00-740-004-A). seconds). ** On A/C ALL Subtask 24-22-17-860-056-A J.

Aircraft Maintenance Configuration (1)

AES

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2), 42XU3 (CT-AC, 1), 42XU4 (CT-AC, 2) De-energize the aircraft electrical circuits supplied from the external power (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-22-17 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-22-17-410-051-A A.

Close Access (1)

AES

FOR 42XU1 (CT-AC, 1), 42XU2 (CT-AC, 2), 42XU3 (CT-AC, 1), 42XU4 (CT-AC, 2) (a)

Make sure that the work area is clean and clear of tool(s) and other items.

(b)

On the rear panel 120VU, close the panel which gives access to the AC power center 123VU.

(c)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(d)

Remove the warning notice(s).

24-22-17 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-22-17-000-002-A Removal of the AC Current Transformers WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 41XU1, 41XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL, 131AC, 131BC, 131CC, 825AR C.

Referenced Information

REFERENCE 25-54-12-000-002-A

DESIGNATION Removal of the Ceiling Panels in the Forward Cargo-Compartment

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

(Ref. Fig. 24-22-17-991-00200-A - AC Current Transformer (41XU1, 41XU2)) 3.

Job Set-up Subtask 24-22-17-010-058-A A.

Get Access (1)

Open the cargo-compartment door 825AR (Ref. TASK 52-30-00-860-001-A).

(2)

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 825AR.

(3)

In the zone 131, remove the ceiling panels 131AC 131BC 131CC (Ref. TASK 25-54-12-000-002-A).

Subtask 24-22-17-941-053-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Put a WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT1, BAT2, APU GEN, GEN1, GEN2,

24-22-17 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . (4)

4.

EXT PWR.

In the cockpit, put a WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

Procedure (Ref. Fig. 24-22-17-991-00200-A - AC Current Transformer (41XU1, 41XU2)) Subtask 24-22-17-020-055-A A.

Removal of the AC Current Transformer (1)

Remove the screws (6).

(2)

Remove the cover (7) to get access to the terminal block (5). NOTE :

AES

You must identify (also with the indications on the current transformer) and disconnect only the cables which go through the current transformer.

(3)

Remove the nuts (1), the washers (2) and the cables (3) and (4) from the studs of the terminal block (5).

(4)

Disconnect the electrical connector (11) from the current transformer (10).

(5)

Put CAP - BLANKING on the disconnected electrical connector (11) and electrical receptacle (12).

(6)

Remove the screws (8) and the washers (9) from the current transformer (10).

(7)

Move the current transformer (10) along the cables to remove it.

24-22-17 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR34

A FR33 41XU1

C

Z131− Z132

C

A

41XU2

C

9 1 8 2 3 10 4 12

B

B

5 11

7

6

N_MM_242217_4_ABM0_01_00

AES

FIGURE 24-22-17-991-00200-A SHEET 1 AC Current Transformer (41XU1, 41XU2)

24-22-17 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-22-17-400-002-A Installation of the AC Current Transformers WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 41XU1, 41XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL, 131AC, 131BC, 131CC, 825AR C.

Referenced Information

REFERENCE 24-41-00-740-004-A 24-41-00-861-002-A

DESIGNATION Operational Check of the GPCU via the CFDS Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-54-12-000-002-A

Removal of the Ceiling Panels in the Forward Cargo-Compartment

25-54-12-400-002-A

Installation of the Ceiling Panels in the Forward Cargo-Compartment

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

52-30-00-860-002-A

(Ref. Fig. 24-22-17-991-00200-A - AC Current Transformer (41XU1, 41XU2)) 3.

Job Set-up Subtask 24-22-17-010-060-A A.

AES

Get Access (1)

Make sure that the cargo-compartment door 825AR is open (Ref. TASK 52-30-00-860-001-A).

(2)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the cargocompartment door 825AR.

24-22-17 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

In the zone 131, make sure that the ceiling panels 131AC 131BC 131CC are removed (Ref. TASK 25-54-12-000-002-A).

Subtask 24-22-17-860-064-A B.

4.

Aircraft Maintenance Configuration (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Make sure that a WARNING NOTICE(S) is (are) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In . . . .

(4)

In the cockpit, make sure that the WARNING NOTICE(S) is (are) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT1, BAT2, APU GEN, GEN1, GEN2, EXT PWR.

Procedure (Ref. Fig. 24-22-17-991-00200-A - AC Current Transformer (41XU1, 41XU2)) Subtask 24-22-17-420-055-A A.

Installation of the AC Current Transformer (1)

Put the disconnected cables (3) and (4) through the current transformer (10). NOTE :

Make sure that the location of the cables agrees with that you recorded at the removal.

(2)

Move the current transformer (10) along the cables.

(3)

Install the washers (9) and the screws (8) on the current transformer (10) and tighten them.

(4)

Remove the blanking caps from the electrical connectors.

(5)

Make sure that the electrical connectors are clean and in the correct condition.

(6)

Connect the electrical connector (11) to the current transformer (10).

(7)

Install the cables (3) and (4), the washers (2) and the nuts (1) on the studs of the terminal block (5) and tighten them. NOTE :

Make sure that the location of the cables agrees with that you recorded at the removal.

(8)

Install the cover (7) and the screws (6) on the terminal block (5).

(9)

Tighten the screws (6).

Subtask 24-22-17-860-065-A B.

Aircraft Maintenance Configuration (1)

AES

Energize the aircraft electrical circuits from the engine 1(2) (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

24-22-17 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-22-17-865-052-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

FWD GALLEY/FEEDER F

16MC

AC10

FWD GALLEY/FEEDER C

1MC

AE10

122VU

FIN

LOCATION

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

** On A/C 005-099 123VU

** On A/C 003-004 Subtask 24-22-17-710-054-A D.

Operational Test (1)

Do this test:

ACTION 1.On the ECAM control panel: . Push the ELEC key to get the ELEC page.

RESULT On the lower ECAM display unit: . The ELEC page comes into view.

2.On the ELEC panel 35VU: . Push the GALLEY pushbutton switch.

On the ELEC panel 35VU: . The OFF legend of the GALLEY pushbutton switch goes off.

3.In the FWD and/or AFT galleys: . Energize all the items of equipment.

On the lower ECAM display unit: . Make sure that the electrical parameters (load, voltage and frequency) of the APU GEN are correct.

4.On the MCDU: On the MCDU, on the AC GEN page: . Do the operational check of the GPCU with the CFDS . The TEST OK message comes into view (after some (Ref. TASK 24-41-00-740-004-A). seconds). ** On A/C 005-099 Subtask 24-22-17-710-054-B D.

Operational Test (1)

Do this test:

ACTION 1.On the ECAM control panel: . Push the ELEC key to get the ELEC page.

AES

RESULT On the lower ECAM display unit: . The ELEC page comes into view.

24-22-17 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 2.On the ELEC panel 35VU: . Push the GALY & CAB pushbutton switch.

RESULT On the ELEC panel 35VU: . The OFF legend of the GALY & CAB pushbutton switch goes off.

3.In the FWD and/or AFT galleys: . Energize all the items of equipment.

On the lower ECAM display unit: . Make sure that the electrical parameters (load, voltage and frequency) of the APU GEN are correct.

4.On the MCDU: On the MCDU, on the AC GEN page: . Do the operational check of the GPCU with the CFDS . The TEST OK message comes into view (after some (Ref. TASK 24-41-00-740-004-A). seconds). ** On A/C ALL Subtask 24-22-17-860-066-A E.

Aircraft Maintenance Configuration (1)

5.

De-energize the aircraft electrical circuits supplied from the engine 1(2) (Ref. TASK 24-41-00-862-002A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Close-up Subtask 24-22-17-410-055-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

In the zone 131, install the ceiling panels 131AC 131BC 131CC (Ref. TASK 25-54-12-400-002-A).

(3)

Remove the access platform(s).

(4)

Remove the warning notice(s).

(5)

Close the access door 825AR (Ref. TASK 52-30-00-860-002-A).

24-22-17 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-22-17-000-003-A Removal of the AC Current Transformers WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 51XU1, 51XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

TIE WRAP

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL, 822 C.

Referenced Information

REFERENCE DESIGNATION (Ref. Fig. 24-22-17-991-00500-B - AC Current Transformer (51XU1, 51XU2)) 3.

Job Set-up Subtask 24-22-17-010-059-A A.

Get Access (1)

Put an ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 822.

(2)

Open the access door 822.

Subtask 24-22-17-941-054-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft external power receptacle.

(2)

Put a WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft external power receptacle.

(3)

In . . . .

(4)

In the cockpit, put WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section),

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT1, BAT2, APU GEN, GEN1, GEN2, EXT PWR.

24-22-17 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . . 4.

25VU (APU section), 35VU (ELEC).

Procedure (Ref. Fig. 24-22-17-991-00500-B - AC Current Transformer (51XU1, 51XU2)) Subtask 24-22-17-020-056-A A.

Removal of the AC Current Transformer (1)

Record the location and the color of the cables of each bundle which goes through the current transformer (1).

(2)

Remove the screws (7) and the washers (8) from the studs of the module 30XN1 (30XN2).

(3)

Disconnect the cables (9) from the studs of the module 30XN1 (30XN2). NOTE :

You must identify (also with the indications on the current transformer) and disconnect only the cables which go through the current transformer.

(4)

Remove the nuts (10) and the washers (11) from the studs of the module 30XN1 (30XN2).

(5)

Disconnect the cables (12) from the studs of the module 30XN1 (30XN2).

(6)

Disconnect the electrical connector (3) from the current transformer (1).

(7)

Put CAP - BLANKING on the disconnected electrical connector (3) and electrical receptacle.

(8)

Remove the screws (4) and (2) and the nuts (6) and (5) from the current transformer (1).

(9)

Remove and discard the necessary TIE WRAP to move the current transformer (1) along the cable bundles.

(10) Remove the current transformer (1).

AES

24-22-17 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 FR12

A

FR14

B A

51XU2 822 51XU1 822

B

FR14

9XU2

C

FR12

9XU1

9

C C

7

5

8

B 10 11 12

6 30XN1 (30XN2)

1

2

3 4 N_MM_242217_4_AAR0_01_00

AES

FIGURE 24-22-17-991-00500-B SHEET 1 AC Current Transformer (51XU1, 51XU2)

24-22-17 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-22-17-400-003-A Installation of the AC Current Transformers WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 51XU1, 51XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

TIE WRAP

No specific

AR

WARNING NOTICE(S)

No specific

Torque wrench: range to between 0.00 and 1.20 M.DAN (0.00 and 9.00 LBF.FT)

No specific

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL, 822 C.

Referenced Information

REFERENCE 24-41-00-740-004-A

DESIGNATION Operational Check of the GPCU via the CFDS

24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

(Ref. Fig. 24-22-17-991-00500-B - AC Current Transformer (51XU1, 51XU2)) 3.

Job Set-up Subtask 24-22-17-010-061-A A.

AES

Get Access (1)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 822.

(2)

Make sure that the access door 822 is open.

24-22-17 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-22-17-860-067-A B.

4.

Aircraft Maintenance Configuration (1)

Make sure that the external power connector is not connected to the aircraft external power receptacle.

(2)

Make sure that a WARNING NOTICE(S) is (are) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft external power receptacle.

(3)

In . . . .

(4)

In the cockpit, make sure that the WARNING NOTICE(S) is (are) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT1, BAT2, APU GEN, GEN1, GEN2, EXT PWR.

Procedure (Ref. Fig. 24-22-17-991-00500-B - AC Current Transformer (51XU1, 51XU2)) Subtask 24-22-17-420-056-A A.

Installation of the AC Current Transformer (1)

Put the disconnect cables through the current transformer (1). NOTE :

Make sure that the location and the color of the cables of each bundle agree with those you recorded at the removal.

(2)

Move the current transformer (1) along the cable bundles.

(3)

Install the screws (2) and (4) and the nuts (5) and (6) on the current transformer (1) and tighten them.

(4)

Remove the blanking caps from the electrical connectors.

(5)

Make sure that the electrical connectors are clean and in the correct condition.

(6)

Connect the electrical connector (3) to the current transformer (1).

(7)

Install new TIE WRAP.

(8)

Connect the cables (12) to the studs of the module 30XN1 (30XN2).

(9)

Install the washers (11) and the nuts (10) on the studs of the module 30XN1 (30XN2).

(10) TORQUE the nut to between 1.25 and 1.35 M.DAN (110.62 and 119.47 LBF.IN). (11) Connect the cables (9) to the studs of the module 30XN1 (30XN2). (12) Install the washers (8) and the screws (7) on the studs of the module 30XN1 (30XN2). (13) TORQUE the screws (7) to between 0.17 and 0.19 M.DAN (15.04 and 16.81 LBF.IN). Subtask 24-22-17-860-068-A B.

Aircraft Maintenance Configuration (1)

AES

Energize the aircraft electrical circuits from the external power (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

24-22-17 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-22-17-865-053-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

122VU

DESIGNATION ELEC/GALLEY/CNTOR

FIN

LOCATION

7MC

S28

122VU

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER C

1MC

AE10

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

FWD GALLEY/FEEDER F

16MC

AC10

Subtask 24-22-17-710-055-A D.

Operational test (1)

Do this test:

ACTION 1.On the ECAM control panel: . Push the ELEC key to get the ELEC page.

RESULT On the lower ECAM display unit: . The ELEC page comes into view.

2.On the ELEC panel 35VU: . Push the GALY & CAB pushbutton switch.

On the ELEC panel 35VU: . The OFF legend of the GALY & CAB pushbutton switch goes off.

3.In the FWD and/or AFT galleys: . Energize all the items of equipment.

On the lower ECAM display unit: . Make sure that the electrical parameters (load, voltage and frequency) of the APU GEN are correct.

4.On the MCDU: . Do the operational test of the GPCU via the CFDS (Ref. TASK 24-41-00-740-004-A).

On the MCDU, on the AC GEN page: . The TEST OK indication comes into view (after some seconds).

Subtask 24-22-17-860-069-A E.

Aircraft Maintenance Configuration (1)

5.

De-energize the aircraft electrical circuits supplied from the external power (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Close-up Subtask 24-22-17-410-056-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the warning notice(s).

(3)

Close the access door 822.

(4)

Remove the access platform(s).

24-22-17 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

SENSOR - TDC AC - REMOVAL/INSTALLATION ** On A/C ALL Task 24-22-18-000-001-A Removal of the TDC AC Sensor 1(2) FIN 50XU1, 50XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS

126 822

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE DESIGNATION (Ref. Fig. 24-22-18-991-00100-A - Time Delay Closing (TDC) AC Sensor) 3.

Job Set-up Subtask 24-22-18-865-050-A A.

Open, safety and tag this(these) circuit breaker(s):

PANEL FOR FIN 50XU1 122VU

DESIGNATION

122VU FOR FIN 50XU2 122VU 122VU

FIN

LOCATION

ELEC/GCU/1

2XU1

T26

ELEC/IDG1/DISC

1XT

T24

ELEC/GCU/2

2XU2

T27

ELEC/IDG2/DISC

2XT

T25

Subtask 24-22-18-010-050-A B.

AES

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 822 of the electronics compartment.

(2)

Open the access door 822.

(3)

Open the access door of the relay box 103VU (5).

24-22-18 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-22-18-991-00100-A - Time Delay Closing (TDC) AC Sensor) Subtask 24-22-18-020-050-A A.

AES

Removal of the TDC AC Sensor (1)

Hold the sensor (3).

(2)

Loosen the screws (4).

(3)

Remove the sensor (3).

24-22-18 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

822

A A

103VU 5 FR16 FR9

50XU2 50XU1

B

B

4 1 2 3

N_MM_242218_4_AAM0_01_00

AES

FIGURE 24-22-18-991-00100-A SHEET 1 Time Delay Closing (TDC) AC Sensor

24-22-18 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-22-18-400-001-A Installation of the TDC AC Sensor 1(2) FIN 50XU1, 50XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

126 822

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-740-004-A

DESIGNATION Operational Check of the GPCU via the CFDS

(Ref. Fig. 24-22-18-991-00100-A - Time Delay Closing (TDC) AC Sensor) 3.

Job Set-up Subtask 24-22-18-860-050-A A.

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 822 of the electronics compartment.

(2)

Make sure that the access door 822 is open.

(3)

Make sure that the access door 103VU (5) is open.

Subtask 24-22-18-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL FOR FIN 50XU1 122VU 122VU FOR FIN 50XU2 122VU 122VU 4.

DESIGNATION

FIN

LOCATION

ELEC/GCU/1

2XU1

T26

ELEC/IDG1/DISC

1XT

T24

ELEC/GCU/2

2XU2

T27

ELEC/IDG2/DISC

2XT

T25

Procedure (Ref. Fig. 24-22-18-991-00100-A - Time Delay Closing (TDC) AC Sensor)

AES

24-22-18 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-22-18-420-050-A A.

Installation of the TDC AC Sensor (1)

Put the sensor (3) in position on the barrels (2) of the base (1).

(2)

Tighten the screws (4).

Subtask 24-22-18-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

DESIGNATION

FIN

LOCATION

122VU

ELEC/GCU/2

2XU2

T27

122VU

ELEC/GCU/1

2XU1

T26

122VU

ELEC/IDG2/DISC

2XT

T25

122VU

ELEC/IDG1/DISC

1XT

T24

Subtask 24-22-18-710-050-A C. 5.

Do the operational check of the GPCU with the CFDS (Ref. TASK 24-41-00-740-004-A).

Close-up Subtask 24-22-18-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access door 103VU (5).

(3)

Close the access door 822.

(4)

Remove the access platform(s).

24-22-18 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

ELECTRICAL GENERATION INTERFACE UNIT (EGIU) REMOVAL/INSTALLATION ** On A/C ALL Task 24-22-33-000-001-A Removal of the EGIU-1(2) FIN 22XU1, 22XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

121 122 811

ZONE DESCRIPTION AVIONICS COMPARTMENT AVIONICS COMPARTMENT

C.

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

(Ref. Fig. 24-22-33-991-00100-A - Electrical Generation Interface Unit 1(2)) 3.

Job Set-up Subtask 24-22-33-860-052-A A.

Aircraft Maintenance Configuration (1)

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

(2)

On the center pedestal, on the ENG panel 115VU: . put a WARNING NOTICE(S) to tell persons not to start the engine.

Subtask 24-22-33-865-050-A B.

Open, safety and tag this(these) circuit breaker(s):

PANEL FOR FIN 22XU1 122VU

AES

DESIGNATION ELEC/GCU/1

FIN 2XU1

LOCATION T26

24-22-33 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

122VU

PANEL

DESIGNATION ELEC/IDG1/DISC

1XT

T24

122VU

ELEC/EXT PWR/LT CLT/AVAIL

4XG

X31

122VU

ELEC/EXT PWR/CTL

11XG

X29

122VU

ELEC/EXT PWR/COCKPIT/AVAIL/LT

12XG

X28

122VU

ELEC/EXT PWR/EGIU1/28VDC

26XU1

Z31

122VU

ELEC/GEN1/EGIU1/28VDC

24XU1

Z30

123VU

GEN1/EGIU1/115VAC

23XU1

AF12

123VU

EXT PWR/EGIU1/115VAC

23XG

AA07

ELEC/GEN1/OFF/BTC2 SPLY

14XU

T30

122VU

ELEC/GCU/2

2XU2

T27

122VU

ELEC/IDG2/DISC

2XT

T25

122VU

APU GEN/EGIU2/28VDC

26XU2

Y31

122VU

GEN2/EGIU2/28VDC

24XU2

Y30

123VU

APU GEN/EGIU2/115VAC

23XS

AA08

123VU

GEN2/EGIU2/115VAC

23XU2

AF01

FOR FIN 22XU2 122VU

FIN

LOCATION

Subtask 24-22-33-010-050-A C.

4.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access door 811 of the avionics compartment.

(2)

Open the access door 811.

Procedure (Ref. Fig. 24-22-33-991-00100-A - Electrical Generation Interface Unit 1(2)) Subtask 24-22-33-020-050-A A.

AES

Removal of the EGIU (1)

Loosen the knurled nut (1).

(2)

Lower the knurled nut (1) to disengage the stud (2).

(3)

Carefully pull the handle (3) until the EGIU (4) is disconnected from the rack receptacle (5).

(4)

Remove the EGIU from the rack (6).

(5)

Put CAP - BLANKING on the rack receptacle (5) and on the EGIU connector.

24-22-33 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR1

A

811

FR9

A

B

B

22XU2

B 22XU1 FWD ELECTRONICS RACK 90VU 4

3

2

5 6

1

N_MM_242233_4_AAM0_01_00

AES

FIGURE 24-22-33-991-00100-A SHEET 1 Electrical Generation Interface Unit 1(2)

24-22-33 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-22-33-400-002-A Installation of the EGIU-1(2) FIN 22XU1, 22XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121 122 811

AVIONICS COMPARTMENT AVIONICS COMPARTMENT C.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

24-42-00-861-001-A

Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

(Ref. Fig. 24-22-33-991-00100-A - Electrical Generation Interface Unit 1(2)) 3.

Job Set-up Subtask 24-22-33-860-050-A A.

Aircraft Maintenance Configuration (1)

Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001-A). NOTE :

(2)

AES

When the circuit breakers 4XG and 12XG are open, the EXT PWR/AVAIL caution light and the AVAIL legend of the EXT PWR pusbutton switch are off.

On the ENG panel 115VU: . make sure that the WARNING NOTICE(S) to tell persons not to start the engine, is in position.

24-22-33 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-22-33-865-053-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL FOR FIN 22XU1 122VU

DESIGNATION

FIN

LOCATION

ELEC/GCU/1

2XU1

T26

122VU

ELEC/IDG1/DISC

1XT

T24

122VU

ELEC/EXT PWR/LT CLT/AVAIL

4XG

X31

122VU

ELEC/EXT PWR/CTL

11XG

X29

122VU

ELEC/EXT PWR/COCKPIT/AVAIL/LT

12XG

X28

122VU

ELEC/EXT PWR/EGIU1/28VDC

26XU1

Z31

123VU

GEN1/EGIU1/115VAC

23XU1

AF12

123VU

EXT PWR/EGIU1/115VAC

23XG

AA07

ELEC/GEN1/OFF/BTC2 SPLY

14XU

T30

122VU

ELEC/GCU/2

2XU2

T27

122VU

ELEC/IDG2/DISC

2XT

T25

122VU

APU GEN/EGIU2/28VDC

26XU2

Y31

122VU

GEN2/EGIU2/28VDC

24XU2

Y30

123VU

APU GEN/EGIU2/115VAC

23XS

AA08

123VU

GEN2/EGIU2/115VAC

23XU2

AF01

FOR FIN 22XU2 122VU

Subtask 24-22-33-010-051-A C.

4.

Get Access (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 811.

(2)

Make sure that the access door 811 is open.

Procedure (Ref. Fig. 24-22-33-991-00100-A - Electrical Generation Interface Unit 1(2)) Subtask 24-22-33-420-051-A A.

AES

Installation of the EGIU (1)

Remove the blanking caps from the electrical connector(s).

(2)

Make sure that the electrical connectors are clean and in the correct condition.

(3)

Clean the component interface and/or the adjacent area.

(4)

Do an inspection of the component interface and/or the adjacent area.

(5)

Put the EGIU in position in the rack (6).

(6)

Carefully push the EGIU until it engages the rack receptacle (5).

(7)

Put the knurled nut (1) on the stud (2) and tighten the knurled nut (1).

24-22-33 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-22-33-865-054-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL FOR FIN 22XU1 122VU

DESIGNATION

FIN

LOCATION

ELEC/GCU/1

2XU1

T26

122VU

ELEC/IDG1/DISC

1XT

T24

122VU

ELEC/EXT PWR/LT CLT/AVAIL

4XG

X31

122VU

ELEC/EXT PWR/CTL

11XG

X29

122VU

ELEC/EXT PWR/COCKPIT/AVAIL/LT

12XG

X28

122VU

ELEC/EXT PWR/EGIU1/28VDC

26XU1

Z31

122VU

ELEC/GEN1/EGIU1/28VDC

24XU1

Z30

123VU

GEN1/EGIU1/115VAC

23XU1

AF12

123VU

EXT PWR/EGIU1/115VAC

23XG

AA07

ELEC/GEN1/OFF/BTC2 SPLY

14XU

T30

122VU

ELEC/GCU/2

2XU2

T27

122VU

ELEC/IDG2/DISC

2XT

T25

122VU

APU GEN/EGIU2/28VDC

26XU2

Y31

122VU

GEN2/EGIU2/28VDC

24XU2

Y30

123VU

APU GEN/EGIU2/115VAC

23XS

AA08

123VU

GEN2/EGIU2/115VAC

23XU2

AF01

FOR FIN 22XU2 122VU

Subtask 24-22-33-860-051-A C.

Aircraft Maintenance Configuration (1)

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

(2)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

Subtask 24-22-33-710-050-A D.

Operational Test of the EGIU (1)

AES

For 22XU1 (a)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A)

(b)

On the ECAM control panel, push the ELEC key (on the lower ECAM DU, the ELEC page comes into view).

(c)

On the ELEC page, make sure that the following EXT PWR parameters are correct: . AC V = 115 + or - 5V, . FRQ HZ = 400 + or - 10HZ.

(d)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

24-22-33 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

5.

For 22XU2 (a)

Energize the aircraft electrical circuits from the APU (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(b)

On . . .

(c)

Stop the APU (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

the ELEC page, make sure that the following APU GEN parameters are correct: AC LOAD Percent shown in green, AC V = 115 + or - 5V, FRQ HZ = 400 + or - 10HZ.

Close-up Subtask 24-22-33-862-051-A A.

Put the aircraft back to its initial configuration. (1)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Subtask 24-22-33-410-051-A B.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access door 811.

(3)

Remove the warning notice(s).

(4)

Remove the access platform(s).

24-22-33 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTROL UNIT - GENERATOR (GCU) REMOVAL/INSTALLATION ** On A/C ALL Task 24-22-34-000-001-A Removal of the GCU-1(2) CAUTION :

USE ONLY THE GROUND SERVICE NETWORK TO SUPPLY THE AIRCRAFT WITH AC AND DC POWER. YOU CAN CAUSE DAMAGE TO THE EQUIPMENT DURING ITS REMOVAL/ INSTALLATION IF THE RELATED NETWORK IS NOT ISOLATED.

FIN 1XU1, 1XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

121 811

ZONE DESCRIPTION AVIONICS COMPARTMENT

C.

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

(Ref. Fig. 24-22-34-991-00100-A - Generator Control Unit 1(2) GCU-1(2)) 3.

Job Set-up Subtask 24-22-34-860-050-A A.

AES

Aircraft Maintenance Configuration (1)

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

(2)

In the cockpit, put a WARNING NOTICE(S) to tell persons not to operate the pushbutton switches (ENG MASTER 1(2)) on the pylon panel 115VU (ENG panel)

24-22-34 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-22-34-865-052-A B.

Open, safety and tag this(these) circuit breaker(s):

PANEL FOR FIN 1XU1 122VU

DESIGNATION

FIN

LOCATION

ELEC/GCU/1

2XU1

T26

FOR FIN 1XU2 122VU

ELEC/GCU/2

2XU2

T27

Subtask 24-22-34-010-052-A C.

4.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access door 811 of the avionics compartment.

(2)

Open the access door 811.

Procedure (Ref. Fig. 24-22-34-991-00100-A - Generator Control Unit 1(2) GCU-1(2)) Subtask 24-22-34-020-052-A A.

AES

Removal of the GCU (1)

Loosen the 2 knurled nuts (1).

(2)

Lower the 2 knurled nuts (1) to disengage the 2 studs (2).

(3)

Carefully pull the handle (3) of the GCU (4) until the GCU is disconnected from the rack receptacle (5).

(4)

Remove the GCU from the rack (6).

(5)

Put CAP - BLANKING on the rack receptacle (5) and on the GCU connector.

24-22-34 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A FR1 1XU2 1XU1

FR9 811

B

A

B B FWD ELECTRONICS RACK 90VU 4

3

2

5 6

1 N_MM_242234_4_AAM0_01_00

AES

FIGURE 24-22-34-991-00100-A SHEET 1 Generator Control Unit 1(2) GCU-1(2)

24-22-34 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-22-34-400-001-A Installation of the GCU-1(2) CAUTION :

USE ONLY THE GROUND SERVICE NETWORK TO SUPPLY THE AIRCRAFT WITH AC AND DC POWER. YOU CAN CAUSE DAMAGE TO THE EQUIPMENT DURING ITS REMOVAL/ INSTALLATION IF THE RELATED NETWORK IS NOT ISOLATED.

FIN 1XU1, 1XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

121 811

ZONE DESCRIPTION AVIONICS COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-740-004-A 24-42-00-861-001-A

DESIGNATION Operational Check of the GPCU via the CFDS Energize the Ground Service Network from the External Power

31-60-00-860-001-A 31-60-00-860-002-A 71-00-00-710-018-A 71-00-00-710-043-A

EIS Start Procedure EIS Stop Procedure Discontinued Start, Restart and Shutdown Procedures Normal Engine Automatic Start Procedure

(Ref. Fig. 24-22-34-991-00100-A - Generator Control Unit 1(2) GCU-1(2)) 3.

Job Set-up Subtask 24-22-34-860-051-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001-A).

(2)

Make sure that the WARNING NOTICE(S) is in the cockpit to tell persons not to operate the pushbutton switches (ENG MASTER 1(2)) on the pylon panel 115VU (ENG panel).

24-22-34 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-22-34-865-054-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL FOR FIN 1XU1 122VU

DESIGNATION

FIN

LOCATION

ELEC/GCU/1

2XU1

T26

FOR FIN 1XU2 122VU

ELEC/GCU/2

2XU2

T27

Subtask 24-22-34-010-053-A C.

4.

Get Access (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 811.

(2)

Make sure that the access door 811 is open.

Procedure (Ref. Fig. 24-22-34-991-00100-A - Generator Control Unit 1(2) GCU-1(2)) Subtask 24-22-34-420-050-A A.

Installation of the GCU (1)

Remove the blanking caps from the electrical connector(s).

(2)

Make sure that the electrical connectors are clean and in the correct condition.

(3)

Clean the component interface and/or the adjacent area.

(4)

Do an inspection of the component interface and/or the adjacent area.

(5)

Put the GCU in position in the rack (6).

(6)

Carefully push the GCU until it is connected to the rack receptacle (5).

(7)

Lift the 2 knurled nuts (1) on the 2 studs (2).

(8)

Tighten the 2 knurled nuts (1).

Subtask 24-22-34-865-057-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL FOR FIN 1XU1 122VU

DESIGNATION

FIN

LOCATION

ELEC/GCU/1

2XU1

T26

FOR FIN 1XU2 122VU

ELEC/GCU/2

2XU2

T27

Subtask 24-22-34-710-050-A C.

Do the operational check of the GPCU with the CFDS (Ref. TASK 24-41-00-740-004-A). NOTE :

As an alternative procedure, do this operational test without the CFDS.

Subtask 24-22-34-710-051-B D.

Operational test of the GPCU without the CFDS. (1)

AES

Start the engine 1(2) automatically (Ref. TASK 71-00-00-710-043-A).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

5.

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

On the ECAM control panel: . push the ELEC key to get the ELEC system page.

(4)

On the lower ECAM display unit, make sure that there is the green line between GEN1(2) and AC1(2).

(5)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A)

(6)

Stop the engine 1(2) (Ref. TASK 71-00-00-710-018-A).

Close-up Subtask 24-22-34-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access door 811.

(3)

Remove the warning notice(s).

(4)

Remove the access platform(s).

24-22-34 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

MODULE - LIGHTNING PROTECTION REMOVAL/INSTALLATION ** On A/C ALL Task 24-22-51-000-001-A Removal of the Lightning Protection Modules FIN 19XU1, 19XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE ** On A/C 005-099

QTY

No specific

1

ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

WARNING NOTICE(S)

B.

DESIGNATION

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 25-11-41-000-001-A

DESIGNATION Removal of the Third Occupant Seat

(Ref. Fig. 24-22-51-991-00100-A - Lightning Protection Module) (Ref. Fig. 24-22-51-991-00100-B - Lightning Protection Module) ** On A/C 003-004 FOR FIN 19XU1(MODULE-LIGHTNING PROT, 1) 24-22-55-000-001-A Removal of the Contactors FOR FIN 19XU2(MODULE-LIGHTNING PROT, 2) 24-22-55-000-001-A 3.

Removal of the Contactors

Job Set-up Subtask 24-22-51-010-050-A A.

AES

Get Access (1)

FOR 19XU1 (MODULE-LIGHTNING PROT, 1) Remove the contactor 9XU1. (Ref. TASK 24-22-55-000-001-A)

(2)

FOR 19XU2 (MODULE-LIGHTNING PROT, 2) Remove the contactor 9XU2. (Ref. TASK 24-22-55-000-001-A)

24-22-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Subtask 24-22-51-010-050-B A.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

On the L lower side of the panel 120VU, remove the access door.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-22-51-860-053-A B.

4.

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Put warning notice(s) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In . . . .

(4)

In the cockpit, put WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

Procedure

** On A/C 003-004 (Ref. Fig. 24-22-51-991-00100-A - Lightning Protection Module) ** On A/C 005-099 (Ref. Fig. 24-22-51-991-00100-B - Lightning Protection Module) ** On A/C 003-004 Subtask 24-22-51-020-050-A A.

Removal of the Lightning Protection Module (1)

Loosen and remove the screw (1).

(2)

Remove the lightning protection module (3).

** On A/C 005-099 Subtask 24-22-51-020-050-B A.

AES

Removal of the Lightning Protection Module (1)

Loosen and remove the screw (1).

(2)

Remove the bonding lead (2).

(3)

On the module 30XN1 (30XN2), loosen and remove the screws (4) and the washers (5).

24-22-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

AES

Remove the lightning protection module (3).

24-22-51 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

120VU

122VU

A

121VU

120VU 124VU

126VU

123VU 9XU2 19XU2 9XU1

B

19XU1

A B

4

3

2 5

1

CONTACTOR N_MM_242251_4_AAM0_01_00

AES

FIGURE 24-22-51-991-00100-A SHEET 1 Lightning Protection Module

24-22-51 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

120VU

A 120VU

122VU

121VU 11XU2 19XU2

126VU

124VU

9XU2

123VU

11XU1 19XU1 9XU1

30XN2

A

30XN1 4

2

5

1

3

CONTACTOR (11XU1, 11XU2)

MODULE 30XN1, 30XN2 N_MM_242251_4_AAP0_01_00

AES

FIGURE 24-22-51-991-00100-B SHEET 1 Lightning Protection Module

24-22-51 PB401

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-22-51-400-001-A Installation of the Lightning Protection Modules FIN 19XU1, 19XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE ** On A/C 005-099

QTY

No specific

1

ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

WARNING NOTICE(S)

No specific

B.

DESIGNATION

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 20-28-00-912-043-A

DESIGNATION Electrical Bonding by Direct Contact

25-11-41-000-001-A 25-11-41-400-001-A

Removal of the Third Occupant Seat Installation of the Third Occupant Seat

** On A/C 003-004 FOR FIN 19XU1(MODULE-LIGHTNING PROT, 1) 24-22-55-000-001-A Removal of the Contactors 24-22-55-400-002-A Installation of the Contactors FOR FIN 19XU2(MODULE-LIGHTNING PROT, 2) 24-22-55-000-001-A 24-22-55-400-002-A 3.

Removal of the Contactors Installation of the Contactors

Job Set-up Subtask 24-22-51-010-051-A A.

AES

Get Access (1)

FOR 19XU1 (MODULE-LIGHTNING PROT, 1) Make sure that the contactor 9XU1 is removed. (Ref. TASK 24-22-55-000-001-A)

(2)

FOR 19XU2 (MODULE-LIGHTNING PROT, 2) Make sure that the contactor 9XU2 is removed. (Ref. TASK 24-22-55-000-001-A)

24-22-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Subtask 24-22-51-010-051-B A.

Get Access (1)

Make sure that the Third Occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(2)

On the L lower side of the panel 120VU, make sure that the access door is removed.

(3)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

Subtask 24-22-51-860-054-A B.

4.

Aircraft Maintenance Configuration (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptable.

(2)

Make sure that the WARNING NOTICE(S) are in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In . . . .

(4)

In the cockpit, make sure that the WARNING NOTICE(S) are in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

Procedure ** On A/C 003-004 Subtask 24-22-51-420-050-A A.

Installation of the Lightning Protection Module (1)

Install the lightning protection module (3) on the three barrels (4) of the contactor base (5).

(2)

Install the bonding lead (2) of the lightning protection module (3) with the screw (1) and then tighten.

(3)

Do the electrical bonding (Ref. TASK 20-28-00-912-043-A).

** On A/C 005-099 Subtask 24-22-51-420-050-B A.

AES

Installation of the Lightning Protection Module (1)

Install the lightning protection module (3) on the module 30XN1 (30XN2).

(2)

Install the screws (4) and the washers (5).

(3)

TORQUE the screws (4) to between 0.73 and 0.81 M.DAN (64.60 and 71.68 LBF.IN).

(4)

Install the bonding lead (2) of the lightning protection module (3) with the screw (1) then tighten.

(5)

Do the electrical bonding (Ref. TASK 20-28-00-912-043-A).

24-22-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up ** On A/C 003-004 Subtask 24-22-51-410-050-A A.

Close Access (1)

FOR 19XU1 (MODULE-LIGHTNING PROT, 1) Install the contactor 9XU1. (Ref. TASK 24-22-55-400-002-A).

(2)

FOR 19XU2 (MODULE-LIGHTNING PROT, 2) Install the contactor 9XU2 (Ref. TASK 24-22-55-400-002-A).

** On A/C 005-099 Subtask 24-22-51-410-050-B A.

AES

Close Access (1)

Close the access door 121AL.

(2)

Remove the access platform(s).

(3)

On the L lower side of the panel 120VU, install the access door.

(4)

Install the third occupant seat (Ref. TASK 25-11-41-400-001-A).

24-22-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

MODULE - LIGHTNING PROTECTION - INSPECTION/CHECK ** On A/C ALL Task 24-22-51-200-001-A Check of the Lightning Protection Modules WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 19XU1, 19XU2 1.

Reason for the Job The crew has made an entry in the log book for a lightning.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

LIGHT SOURCE - INSPECTION

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL C.

Referenced Information

REFERENCE 24-22-51-000-001-A

DESIGNATION Removal of the Lightning Protection Modules

24-22-51-400-001-A

Installation of the Lightning Protection Modules

25-11-41-000-001-A 25-11-41-400-001-A

Removal of the Third Occupant Seat Installation of the Third Occupant Seat

3.

Job Set-up Subtask 24-22-51-010-052-A A.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

In the cockpit, on the rear panel 120VU, open the panel which gives access to the AC power center 123VU.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-22-51-860-052-A B.

Safety Precautions (1)

AES

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

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4.

(2)

Put a warning notice on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In . . . .

(4)

In the cockpit, put WARNING NOTICE(S) to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 25VU (APU), . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: APU GEN, BAT 1, BAT 2, GEN 1, GEN 2, EXT PWR.

Procedure Subtask 24-22-51-210-050-A A.

5.

Inspection (1)

With an LIGHT SOURCE - INSPECTION, do a visual check of the external condition of the lightning protection modules and of the adjacent area to find: . on each lightning protection module: . cracks, . blisters. . in the adjacent area: . projections of black or/and white spots.

(2)

Replace the lightning protection module if at least one of these damages is found (Ref. TASK 24-22-51-000-001-A) and (Ref. TASK 24-22-51-400-001-A).

Close-up Subtask 24-22-51-410-051-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

In the cockpit, on the rear panel 120VU, close the panel which gives access to the AC power center 123VU.

(3)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

24-22-51 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-22-55-000-001-A Removal of the Contactors WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 9XU1, 9XU2, 11XU1, 11XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 25-11-41-000-001-A

DESIGNATION Removal of the Third Occupant Seat

(Ref. Fig. 24-22-55-991-00100-A - Contactors) (Ref. Fig. 24-22-55-991-00100-B - Contactors) 3.

Job Set-up Subtask 24-22-55-010-050-A A.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

On the L lower side of the panel 120VU, remove the access door (8).

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-22-55-860-051-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Put warning notice(s) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

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4.

(3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

(4)

In the cockpit, put WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

Procedure

** On A/C 003-004 (Ref. Fig. 24-22-55-991-00100-A - Contactors) ** On A/C 005-099 (Ref. Fig. 24-22-55-991-00100-B - Contactors) ** On A/C ALL Subtask 24-22-55-020-050-A A.

Removal of the Contactor CAUTION :

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

(1)

Disconnect the electrical connector (1).

(2)

Put CAP - BLANKING on the disconnected electrical connector (1) and the electrical receptacle (7).

(3)

Loosen the captive screws (2). NOTE :

(4)

Do not remove the captive screws (2) and the spring washers from contactor (3).

Remove the contactor (3).

** On A/C 003-004 Subtask 24-22-55-020-051-A CAUTION :

B.

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Removal of the Contactor Base NOTE : (1)

AES

The removal of the base is necessary only if the base is damaged.

If the base has the components that follow: (a)

Remove the screws (9) and the washers (10).

(b)

Disconnect the electrical wires (11).

(2)

Remove the nuts (12) and the washers (13).

(3)

Disconnect the cables (14) from the base (6).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

Remove the nuts (15) and the washers (16).

(5)

Remove the jumpers (17) from the base (6) and from the adjacent bases.

(6)

Remove the four screws (19) and the four washers (18).

(7)

Remove the base (6).

** On A/C 005-099 Subtask 24-22-55-020-051-B CAUTION :

B.

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Removal of the Contactor Module NOTE : (1)

AES

The removal of the module is necessary only if the module is damaged.

If the module has the components that follow: (a)

Remove the screws (9) and the washers (10).

(b)

Disconnect the electrical wires (11).

(2)

Remove the nuts (12) and the washers (13).

(3)

Disconnect the cables (14) from the module (5).

(4)

Remove the nuts (19) and the washers (18).

(5)

Remove the jumpers (17) from the module (5) and from the adjacent modules.

(6)

Remove the eight screws (16) and the eight washers (15).

(7)

Remove the module (5).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

A 120VU

122VU 11XU2

B

121VU 9XU2

11XU1

126VU

124VU

B

123VU

9XU1

8

A

16

17

15

B 14 5

13

11 12

6

10 3

9

2 CONTACTOR BASE

CONTACTOR 18 19

7 1 N_MM_242255_4_AAM0_01_00

AES

FIGURE 24-22-55-991-00100-A SHEET 1 Contactors

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A 11XU2 122VU

120VU

B 9XU2

11XU1

B

121VU

9XU1 126VU

124VU 123VU

30XN2 30XN1

8

B

14 13

A

11

12

10 9 3

2 17

CONTACTOR 18 7 19 5 1

MODULE

CONTACTOR

1

7

15 16 N_MM_242255_4_AAP0_01_00

AES

FIGURE 24-22-55-991-00100-B SHEET 1 Contactors

24-22-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-22-55-400-002-A Installation of the Contactors WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 9XU1, 9XU2, 11XU1, 11XU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

No specific

B.

WARNING NOTICE(S) Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 20-21-15-912-001-A

DESIGNATION Tightening Torques for Electrical Component Fasteners

25-11-41-000-001-A 25-11-41-400-001-A

Removal of the Third Occupant Seat Installation of the Third Occupant Seat

(Ref. Fig. 24-22-55-991-00100-A - Contactors) (Ref. Fig. 24-22-55-991-00100-B - Contactors) FOR FIN 11XU1(BTC-1) FOR FIN 11XU2(BTC-2) 24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

FOR FIN 9XU1(GLC-1) FOR FIN 9XU2(GLC-2) 31-60-00-860-001-A

AES

EIS Start Procedure

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 31-60-00-860-002-A

EIS Stop Procedure

71-00-00-710-018-A 71-00-00-710-043-A

Discontinued Start, Restart and Shutdown Procedures Normal Engine Automatic Start Procedure

3.

DESIGNATION

Job Set-up Subtask 24-22-55-010-051-A A.

Get Access (1)

Make sure that the Third Occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(2)

On the L lower side of the panel 120VU, make sure that the access door (8) is removed.

(3)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

Subtask 24-22-55-860-050-A B.

4.

Aircraft Maintenance Configuration (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptable.

(2)

Make sure that the WARNING NOTICE(S) are in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In . . . .

(4)

In the cockpit, make sure that the WARNING NOTICE(S) are in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMERG ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN GEN 1, GEN 2, EXT PWR.

Procedure

** On A/C 003-004 (Ref. Fig. 24-22-55-991-00100-A - Contactors) ** On A/C 005-099 (Ref. Fig. 24-22-55-991-00100-B - Contactors) ** On A/C 003-004 Subtask 24-22-55-420-052-A A.

Installation of the Contactor Base CAUTION :

AES

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (1)

Install the contactor base (6) in correct position.

(2)

Install the four screws (19) and washers (18) and tighten them.

(3)

Make sure that the electrical cables (6) are clean and in correct condition.

(4)

Install the cables (14).

(5)

Install the nuts (12) and the washers (13) and tighten them.

(6)

If the base has the components that follow: (a)

Install the electrical wires (11).

(b)

Install the screws (10) and the washers (9) and tighten them.

(7)

Install the jumpers (17) between the base (6) and the adjacent bases.

(8)

Install the washers (15) and the nuts (16) and tighten them (Ref. TASK 20-21-15-912-001-A).

Subtask 24-22-55-420-051-A B.

Installation of the Contactor (1)

Install the contactor (3) on the 6 tapped barrels (5) of the contactor base (6).

(2)

TORQUE the captive screws (2) to between 0.50 and 0.60 M.DAN (44.25 and 53.10 LBF.IN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (1).

** On A/C 005-099 Subtask 24-22-55-420-052-B A.

Installation of the Contactor Module CAUTION :

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Install the contactor module (5) in correct position.

(2)

Install the eight screws (16) and washers (15) and tighten them.

(3)

Make sure that the electrical cables (14) are clean and in correct condition.

(4)

Install the cables (14).

(5)

Install the nuts (12) and the washers (13) and tighten them.

(6)

TORQUE the nuts (12) to between 1.25 and 1.35 M.DAN (110.62 and 119.47 LBF.IN).

(7)

If the base has the components that follow: (a)

Install the electrical wires (11).

(b)

Install the screws (9) and the washers (10) and tighten them.

(8)

Install the jumpers (17) between the module (5) and the adjacent modules.

(9)

Install the washers (18) and the nuts (19) and tighten them (Ref. TASK 20-21-15-912-001-A).

(10) TORQUE the nuts (19) to between 0.73 and 0.81 M.DAN (64.60 and 71.68 LBF.IN).

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-22-55-420-051-B B.

Installation of the Contactor (1)

Install the contactor (3) on the module 30XN1 (30XN2) (5).

(2)

TORQUE the captive screws (2) to between 0.50 and 0.60 M.DAN (44.25 and 53.10 LBF.IN).

(3)

Remove the blanking caps from the electrical connectors (1) and the electrical receptacle (7).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (1) to the contactor (3)..

** On A/C ALL Subtask 24-22-55-710-053-A C.

Test of the Bus Transfer Contactor (BTC) (1)

FOR 11XU1 (BTC-1), 11XU2 (BTC-2) NOTE :

This test is for BTC 1. For the BTC 2, use the indications between the parentheses.

(a)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(b)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(c)

On the ECAM control panel: . Push the ELEC key to get the ELEC system page.

(d)

On the lower ECAM display unit, make sure that the green lines between the EXT PWR and AC 1(2) are present.

(e)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A)

(f)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Subtask 24-22-55-710-054-B D.

Test of the Generator Line Contactor (GLC) (1)

FOR 9XU1 (GLC-1), 9XU2 (GLC-2) NOTE :

AES

This test is for GLC 1. For the GLC 2, use the indications between the parentheses.

(a)

Start the engine 1(2) automatically (Ref. TASK 71-00-00-710-043-A).

(b)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(c)

On the ECAM control panel: . Push the ELEC key to get the ELEC system page.

(d)

On the lower ECAM display unit, make sure that green line between GEN 1(2) and AC 1(2) is present.

(e)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A)

(f)

Stop the engine 1(2) (Ref. TASK 71-00-00-710-018-A).

24-22-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-22-55-410-051-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the access door (8) on L lower side of the panel 120VU.

(3)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC AUXILIARY GENERATION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The AC auxiliary generation comes from the APU generator. This generator can: . in flight, replace either or both engine generator(s) in case of failure, . on the ground, supply the aircraft electrical network when the electrical ground power unit is not available.

AES

24-23-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location

** On A/C 003-004 (Ref. Fig. 24-23-00-12300-A - AC Auxiliary Generation (APU Generator GCU) Component Location) ** On A/C 005-099 (Ref. Fig. 24-23-00-12300-B - AC Auxiliary Generation (APU Generator GCU) Component Location) ** On A/C ALL (Ref. Fig. 24-23-00-12400-A - AC Auxiliary Generation (APU Generator GCU) Component Location) FIN

91VU 35VU

ZONE ACCESS ATA REF. DOOR 121 24-23-34 210 24-23-00

120VU

212

24-23-55

8XS GEN-APU ** On A/C 008-099

310

24-23-51

8XS ** On A/C ALL

GEN-APU

316

24-23-51

42XS

CT-AC, APU GEN

212

24-23-17

1XS 2XS

FUNCTIONAL DESIGNATION GCU-APU P/BSW-ELEC/APU GEN

3XS GLC-APU ** On A/C 003-007

PANEL

120VU

The APU generator is installed in the APU compartment. It is attached to the APU gearbox by a button hole flange.

AES

24-23-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description

** On A/C 003-004 (Ref. Fig. 24-23-00-13800-C - APU Generator Configuration - Block Diagram) ** On A/C 005-099 (Ref. Fig. 24-23-00-13800-G - APU Generator Configuration - Block Diagram)

AES

24-23-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Component Description A.

APU Generator 8XS The APU directly drives the APU generator at a nominal 24000 rpm constant speed. The APU gearbox supplies the oil for cooling and lubrication of the generator. The cooling circuit is common to the APU and the generator. The APU supplies, scavenges, drains the oil. The generator is a brushless oil-cooled generator with a nominal 115/200 volt, 90 KVA, 3 phase 400 Hz output. The generator includes three stages which are: . the pilot exciter, . the main exciter, . the main alternator. The operation principle is the same as that of the IDG generator (Ref. 24-21, generator section). NOTE :

The PMG frequency for the APU generator is 1600 Hz.

A temperature bulb is included in the auxiliary generator. It senses the generator-oil outlet temperature. This sensor is connected to the Electronic Control Box (ECB) of the APU. Any high oil temperature causes the automatic shutdown of the APU (by the ECB). This in turn causes the APU speed to decrease to zero. B.

Generator Control Unit (GCU) The overall function of the APU GCU is selected by pin programming. The 3 GCUs are identical and interchangeable. For details concerning the description and functions of the APU GCU, refer to 24-22-00.

C.

Electrical Generation Interface Unit (EGIU) EGIU2 channel 2 is for the APU generator. Its main function is to give the main electrical parameters of the APU generator channel to the SDACS. This is via the ARINC 429 data links. For more details on the EGIU description and functions, refer to 24-22-00 .

D. Power Contactor Refer to Chapter 24-22-00. E.

Current Transformer (CT)

** On A/C 003-004 (Ref. Fig. 24-23-00-12300-A - AC Auxiliary Generation (APU Generator GCU) Component Location) ** On A/C 005-099 (Ref. Fig. 24-23-00-12300-B - AC Auxiliary Generation (APU Generator GCU) Component Location) ** On A/C ALL (Ref. Fig. 24-23-00-16800-A - Current Transformers - Block Diagram) There are two CTs for AC auxiliary generation channel: . one CT is built into the APU generator, . one three-hole CT is installed upstream of the generator line contactor. (1) Functions (a) Generator CT The generator CT is used for differential and overcurrent protections.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b) Three-hole CT The three-hole CT contains three toroidal transformers, one for each of the power feeder cables. The three-hole CT is connected in electrical opposition to the CT of the APU generator. This CT is used for differential and open cable protections.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 5.

Operation/Control and Indicating A.

APU Generator Control (Ref. Fig. 24-23-00-18300-E - Auxiliary Generation Operation - Schematic Diagram) The operation of the APU generator is through the APU GEN pushbutton switch, which has two stable positions: . when in OFF position, the pushbutton switch is released, and the white OFF legend is on. The generator is shut down (de-energized) and the line contactor is open, . when the pushbutton switch is pushed, the generator is energized, because its rotational speed is high enough. If the electrical parameters are correct, the GCU controls the line contactor closing: this causes the supply of the transfer circuit. The APU GLC supplies the aircraft electrical network if the other power sources are not available. (Ref. Fig. 24-23-00-18500-A - GLC - APU Supply - Schematic Diagram) NOTE :

AES

On the ground, the generator line contactor closes only if the ground power unit does not already supply the transfer network. For the power supply of the aircraft, the ground power unit is more important than the APU generator. (Ref. Fig. 24-23-00-18700-A - APU GEN FAULT - Upper and Lower ECAM Display Unit) When the FAULT legend comes on, there is a failure of the channel. At the same time: . the single chime operates, . the MASTER CAUT light comes on, . on the upper ECAM display unit, an amber message is shown, . on the lower ECAM display unit, the ELEC page is automatically shown.

24-23-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU FR16

FR5 FR3

FR20

122VU

121VU

125VU

124VU 123VU

811 121AL

841

A 21VU

35VU

A

25VU

4WT1

120VU

42XS

B

3XS

C

4WT2

C B

N_MM_242300_0_AAM0_01_00

AES

FIGURE 24-23-00-12300-A SHEET 1 AC Auxiliary Generation (APU Generator GCU) Component Location

24-23-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

DC BUS 1

1

BAT 1 V

BAT 2

35VU

BAT 2

FAULT FAULT OFF OFF

DC BUS 2 AC ESS FEED V

GALLEY

E L E C

FAULT UA OFF OT

AC BUS 1

AC BUS 2

BUS TIE

IDG 1

FAULT

FAULT ALTN

AC ESS BUS

GEN 1

APU GEN

FAULT

FAULT

OFF

OFF

OFF

A U T O

IDG 2 EXT PWR

GEN 2

AVAIL ON

FAULT OFF

E L E C

FAULT

2XS

8XS FR87 316AR 315AL

FR70

N_MM_242300_0_AAM0_02_00

AES

FIGURE 24-23-00-12300-A SHEET 2 AC Auxiliary Generation (APU Generator GCU) Component Location

24-23-00 PB001

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU FR16

FR5 FR3

FR20

122VU

121VU

124VU

125VU

123VU

811 121AL

841

A 21VU

35VU

A

25VU

120VU

4WT1

42XS

B

3XS 4WT2

C

C

29XN

B

N_MM_242300_0_AAP0_01_00

AES

FIGURE 24-23-00-12300-B SHEET 1 AC Auxiliary Generation (APU Generator GCU) Component Location

24-23-00 PB001

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

DC BUS 1

1

BAT 1 V

BAT 2

35VU

BAT 2

FAULT FAULT OFF OFF

DC BUS 2 AC ESS FEED V

GALLEY

E L E C

FAULT UA OFF OT

AC BUS 1

AC BUS 2

BUS TIE

IDG 1

FAULT

FAULT ALTN

AC ESS BUS

GEN 1

APU GEN

FAULT

FAULT

OFF

OFF

OFF

A U T O

IDG 2 EXT PWR

GEN 2

AVAIL ON

FAULT OFF

E L E C

FAULT

2XS

8XS FR87 316AR 315AL

FR70

N_MM_242300_0_AAP0_02_00

AES

FIGURE 24-23-00-12300-B SHEET 2 AC Auxiliary Generation (APU Generator GCU) Component Location

24-23-00 PB001

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FR24A

90VU

B B FR1

91VU

1XS

C

C

N_MM_242300_0_ACM0_01_00

AES

FIGURE 24-23-00-12400-A SHEET 1 AC Auxiliary Generation (APU Generator GCU) Component Location

24-23-00 PB001

Page 11 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

APU START 49 − 42 − 00

5KA

6KA

10KA

3PN1

BAT2 2PB2 701PP

12PB1

4PB1

28VDC

6PB1

BAT BUS

1PC1

BAT1 2PB1

8PR

SHUNT 3PB2

8PH

602PP

202PP

1PN2 DC BUS 2

1PC2

601PP

204PP

3PN2 SHUNT

4PP 28VDC

206PP

6PN

1PR

401PP

DC ESS BUS

4PC

208PP

3PB1

3PP

20PC

501PP 5PR

703PP

5PB1

1PP

502PP

704PP

12PB2

1PB1 BCL−1

101PP

1PN1 DC BUS 1

2PR

6PB2

4PB2

8PP 28VDC

702PP

5PB2

1PB2 BCL−2

DC SHED ESS BUS

CSM/G CONTROL UNIT

6XE

103PP

801PP

301PP

11PB

2PP

28VDC

DC SVCE BUS

28VDC

7PN

6PP

8PN 28VDC

3PX 5XB 5PU1

3XB 28

2XB

6PH

115

STATIC INV

901XP

12XB

1PU1 TR1

5PU2

801XP AC SHED ESS BUS 8XP

24 − 50 − 00 110XP

7XN1 26V

5XN1

2PU1

15XN1 3XN1

1XP

7XN2 26V

4XH

431XP−A

5XH

103XP 101XP

AC ESS BUS

202XP

1XN2 2XC

1XC

204XP

3XN2

4XP

AC BUS 2

2XP 115VAC

3XC

115VAC

15XE

GLC−1 9XU1

BTC−1 11XU1

BTC−2 11XU2

GLC−2 9XU2

FUEL PUMPS 28 − 21 − 00 GCU−1 1XU1

AES

GEN 1

4000XU

GCU−APU 1XS

4XX

214XP 216XP

2PU2

14PU

10XN

12XN

212XP

3801GX 3805GX

EPC 3XG

GLC−APU 3XS

1PE ESS TR

231XP−A

26V 15XN2

401XP

1PU2 TR2

210XP

21XN2

5XN2

115VAC

1XN1 AC BUS 1

131XP−A

1PX

24 − 50 − 00

115VAC

8XH

3PE

1XX

14XX

2XX

12XX

4PE

ELEC PUMP − Y 29 − 24 − 00 GLC−EMERG 2XE

3802GX 3806GX APU GEN

FIGURE 24-23-00-13800-C SHEET 1 APU Generator Configuration - Block Diagram

8XS

GPCU 1XG

EXTERNAL POWER RECEPTACLE

24-23-00 PB001

Page 12 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G 8XE CONTROL UNIT CSM/G 1XE N_MM_242300_0_AGL0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

APU START 49 − 42 − 00

5KA

6KA

10KA

3PN1

BAT2 2PB2 701PP

12PB1

4PB1

28VDC

6PB1

BAT BUS

1PC1

BAT1 2PB1

8PR

SHUNT 3PB2

8PH

1PR

601PP

204PP

3PN2

602PP

202PP

1PN2 DC BUS 2

1PC2

4PP 28VDC

206PP

6PN

SHUNT

401PP

DC ESS BUS

4PC

208PP

3PB1

3PP

20PC

501PP 5PR

703PP

5PB1

1PP

502PP

704PP

12PB2

1PB1 BCL−1

101PP

1PN1 DC BUS 1

2PR

6PB2

4PB2

8PP 28VDC

702PP

5PB2

1PB2 BCL−2

DC SHED ESS BUS

CSM/G CONTROL UNIT

6XE

103PP

801PP

301PP

11PB

2PP

28VDC

DC SVCE BUS

28VDC

7PN

6PP

8PN 28VDC

3PX 5XB 5PU1

3XB 28

2XB

6PH

115

STATIC INV

901XP

12XB

1PU1 TR1

5PU2

801XP AC SHED ESS BUS 8XP

24 − 50 − 00

7XN1

21XN1 26V

5XN1

2PU1

15XN1 3XN1

1XP

115VAC

8XH

131XP−A

7XN2 26V

4XH

431XP−A

5XH

103XP 101XP

AC ESS BUS

204XP

3XN2

4XP

202XP

1XN2 AC BUS 2

2XP 115VAC

3XC

115VAC

15XE

GLC−1 9XU1

BTC−1 11XU1

BTC−2 11XU2

GLC−2 9XU2

FUEL PUMPS 28 − 21 − 00 GCU−1 1XU1

AES

GEN 1

4000XU

GCU−APU 1XS

4XX 2PU2

14PU

10XN

12XN

3801GX 3805GX

EPC 3XG

GLC−APU 3XS

1PE ESS TR

231XP−A

26V 15XN2

401XP

1PU2 TR2

210XP

21XN2

5XN2

2XC

1XC

1PX

24 − 50 − 00

115VAC

1XN1 AC BUS 1

110XP

3PE

1XX

14XX

2XX

12XX

16XX

214XP

216XP 4PE

212XP ELEC PUMP − Y 29 − 24 − 00

GLC−EMERG 2XE

3802GX 3806GX APU GEN

FIGURE 24-23-00-13800-G SHEET 1 APU Generator Configuration - Block Diagram

8XS

GPCU 1XG

EXTERNAL POWER RECEPTACLE

24-23-00 PB001

Page 13 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G 8XE CONTROL UNIT CSM/G 1XE N_MM_242300_0_AGG0_01_00

AES

FIGURE 24-23-00-16800-A SHEET 1 Current Transformers - Block Diagram GCU−1 1XU1

GEN 1

AC BUS 1 115VAC

11XU1 BTC−1

4000XU

11(12)QA

1XP

1XS

GCU−APU

42XS

FUEL PUMPS 53(54)QA 28−21−00

APU GEN

AC BUS 2

8XS

DIFFERENTIAL MEASURE AND PROTECTION

1XG

GPCU

115VAC

EXTERNAL POWER RECEPTACLE

11XU2 BTC−2

2XP

GCU−2 1XU2

GEN 2

4000XU

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242300_0_AHM0_01_00

24-23-00 PB001

Page 14 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

B

ROTOR C

J

EXCITER FIELD RETURN

S N

PMG

DIFFERENTIAL MEASURE AND PROTECTION

A B C GCR

OVER CURRENT

OUTLET OIL TEMPERATURE BULB

8XS GEN−APU

1XS GCU−APU

SENSE TEMP

59KD E.C.B

OVER CURRENT SDAC1

SDAC2

ARINC CPU BOARD

22XU2 EGIU−2 N_MM_242300_0_AJPA_01_00

AES

FIGURE 24-23-00-18300-E SHEET 1 Auxiliary Generation Operation - Schematic Diagram

24-23-00 PB001

Page 15 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL T3

A

L3 .

T2

B

TO BTC1 BTC2 EPC

L2 .

T1

C

L1 .

3XS EPC

42XS CT 23XS

49−61 TO ECB VIA TR1 5VAC ESS

2XS P/BSW

DC1

P.O.R

A320 GCU POSITION

J

5VAC ESS

FAULT OFF

DIFFERENTIAL MEASURE AND PROTECTION AUX.RLY PR SUPPLY PROTECTION MODULE AC LOAD

BTC2

COMP. RESET GEN. COM.

APU READY

1XS GCU−APU

GLC2

GLC1 EXT PWR CTL BTC1 RLY

301PP 6XS 28VDC

EPC

GLC APU

APU CTL RLY AC LOAD PARAMETERS

SUPPLY

GEN FAULT GEN P/BSW POS.

5VDC R VOLTAGE AND FREQUENCY PARAMETERS BACK−UP SUPPLY

AC DC

26XU2

301PP 28VDC

22XU2 EGIU−2 N_MM_242300_0_AJPA_02_00

AES

FIGURE 24-23-00-18300-E SHEET 2 Auxiliary Generation Operation - Schematic Diagram

24-23-00 PB001

Page 16 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

GLC−1 301PP BAT BUS

2XU1

BTC−1

GEN 1 FAULT OFF

PMG PR

LOCK−OUT BTC

AUX LINE 1 RLY

GCU−1 301PP BAT BUS

BTC−2 2XU2

GLC−2

GEN 2 FAULT OFF

PMG PR

LOCK−OUT BTC

AUX LINE 2 RLY

GCU−2 301PP BAT BUS

APU GEN 6XS FAULT OFF

PMG

GLC−APU

PR

EPC

GCU−APU 5XU

301PP BAT BUS

APU AUX LINE RLY

G.P PR

GPCU 11XG EXT PWR CTL

EGIU 1 − CHANNEL B

AES

FIGURE 24-23-00-18500-A SHEET 1 GLC - APU Supply - Schematic Diagram

EXT PWR AUX RLY N_MM_242300_0_ALM0_01_00

24-23-00 PB001

Page 17 May 01/12 Revision n˚: 40

AES

FIGURE 24-23-00-18700-A SHEET 1 APU GEN FAULT - Upper and Lower ECAM Display Unit

ACTION ON CLEAR P/BSW ON ECAM CP

RELEASED − OUT GEN APU P/BSW

MANUAL CREW ACTION

AUTOMATIC TRANSFERT OF APU NETWORK ON ANOTHER POWER SOURCE (GEN 1)

CONFIG. SYSTEM

24-23-00 PB001 WHITE OFF"

OFF

FAULT

APU GEN

WHITE OFF"

OFF

FAULT

APU GEN

AMBER FAULT"

OFF

FAULT

APU GEN

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

APU GEN FAULT

ELEC

NORMAL CONFIG.

NORMAL CONFIG.

APU GEN FAULT

APU GEN . . . . OFF THEN ON IF UNSUCCESSFUL APU GEN . . . . . . . . . . OFF

ELEC

ECAM UPPER DISPLAY

APU GEN FAULT (CLASS 1 − LEVEL 2)

STATUS SYS:

MAIN GALLEY

APU − GEN

INOP

SEE TWO PAGES FARTHER

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242300_0_ANM0_01_00

Page 18 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0 A

BAT 2 28V 0 A

DC BAT

DC 2

DC 1

DC ESS TR 1 28V 110A

AC 1

GEN

EMER

AC ESS

°C 1 1 0

GEN

TR 2 28V 82A

AC 2

GEN 2

1

96% 116V 4 0 0 HZ IDG 1

ESS TR

APU GEN 00% 116V 4 0 0 HZ

OFF 1 1 0 °C

IDG 2

4WT2 DU−ECAM, LOWER

N_MM_242300_0_ANM0_02_00

AES

FIGURE 24-23-00-18700-A SHEET 2 APU GEN FAULT - Upper and Lower ECAM Display Unit

24-23-00 PB001

Page 19 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 2 28 V 0A

BAT 1

DC BAT

28 V 0A

DC 2

DC 1 DC ESS

28V

EMER

ESS TR

AC 1

GEN

AC ESS

28V

AC 2

GEN 2

1

96% 116V

GEN

82A

110A

APU GEN

OFF

400HZ

OFF IDG 1

°C 1 1 0

1 1 0°C

IDG 2

4WT2 DU−ECAM, LOWER

N_MM_242300_0_ANM0_03_00

AES

FIGURE 24-23-00-18700-A SHEET 3 APU GEN FAULT - Upper and Lower ECAM Display Unit

24-23-00 PB001

Page 20 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC AUXILIARY GENERATION - DEACTIVATION/REACTIVATION ** On A/C ALL Task 24-23-00-040-001-A Deactivation of the APU Generator by Installation of the Substitution Kit WARNING : DO NOT TOUCH THE APU UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S). WARNING : USE THE CORRECT PERSONAL PROTECTION. OIL CAN HAVE ADDITIVE CALLED TRICRESYL PHOSPHATE IN IT. THIS CHEMICAL IS AN ASPHYXIANT, IT IS POISONOUS AND CAN BE ABSORBED THROUGH THE SKIN. USE CARE WHEN ENGINE OIL IS DRAINED. HOT OIL CAN POSSIBLY CAUSE BAD BURNS. 1.

Reason for the Job MMEL 24-23-01H AC Auxiliary Generation (APU Generator, GCU, Line Contactor) MMEL 24-23-01C AC Auxiliary Generation (APU Generator, GCU, Line Contactor) (Old MMEL ref: 24-20-02)

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)

No specific

AR

COVER - PLASTIC

No specific

1

PLACARD

No specific

AR

WARNING NOTICE(S)

No specific

Torque wrench: range to between 0.67 and 13.50 M.DAN (4.94 and 99.57 LBF.FT)

3862619-1 B.

1 Consumable Materials

REFERENCE Material No: 03-002 Material No: 03-003 Material No: 19-003 Material No: 19-010 C.

COVER-ASSEMBLY

DESIGNATION OILS LUBRICATING OIL TURBINE ENGINE SYNT BASE OILS LUBRICATING OIL TURBINE SYNTHETIC BASE LINT-FREE COTTON CLOTH LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

315AL, 316AR

AES

24-23-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL D.

Expendable Parts

FIG.ITEM 9

DESIGNATION

IPC-CSN 49-11-04-05-110

seal E.

Referenced Information

REFERENCE 24-23-51-000-001-A 24-23-51-000-001-A-01 24-42-00-861-001-A

DESIGNATION Removal of the APU Generator Removal of the APU Generator with the Minilift Hoist Energize the Ground Service Network from the External Power

29-00-00-864-001-A

Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Pressurization of the Hydraulic Reservoirs through the Ground Connector

29-14-00-614-002-A ** On A/C 006-099 49-00-00-860-005-A

APU Start by External Power

49-00-00-860-005-A-01

APU Start by Batteries

49-00-00-860-006-A

APU Shutdown by External Power

49-00-00-860-006-A-01

APU Shutdown by Batteries

** On A/C 003-005 49-00-00-860-008-A

APU Start by External Power

49-00-00-860-008-A-01

APU Start by Batteries

49-00-00-860-009-A

APU Shutdown by External Power (131-9(A))

49-00-00-860-009-A-01

APU Shutdown by Batteries (131-9(A))

** On A/C 006-099 49-90-00-600-004-A

Check Oil Level and Replenish (APS 3200)

** On A/C 003-005 49-90-00-600-007-A

Check Oil Level and Replenish (131-9(A))

52-41-00-010-001-A

Open the APU Doors for Access

52-41-00-410-001-A Close the APU Doors after Access (Ref. Fig. 24-23-00-991-00100-A - Components for Flight without an APU Generator Installed) 3.

Job Set-up ** On A/C ALL Subtask 24-23-00-860-050-A A.

Obey the MMEL requirements related to Weight Impact and Effect on Balance for Flights without APU Generator (1)

Weight Impact: -21.95 kg (-48.3915 lb).

(2)

Effect on Balance: -871.35 m.daN (-77110.62 lbf.in).

Subtask 24-23-00-860-051-A B.

Aircraft Maintenance Configuration (1)

AES

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

24-23-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

On the APU section of the overhead panel 25VU, make sure that the APU MASTER SW pushbutton switch is released (the ON legend is off).

(3)

Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to start the APU.

(4)

Make sure that the ground fire-extinguishing equipment is available.

(5)

Make sure that hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001-A).

Subtask 24-23-00-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

121VU

PANEL

DESIGNATION APU/APU/CTL

2KD

FIN L42

LOCATION

121VU

APU/ECB/SPLY

1KD

L41

Subtask 24-23-00-010-050-A D.

4.

Get Access (1)

Put the ACCESS PLATFORM 4M (13 FT) in position below the APU compartment.

(2)

Open the APU access doors 315AL and 316AR (Ref. TASK 52-41-00-010-001-A).

(3)

Set the control switch 11LJ to the ON position.

(4)

Remove the APU generator (Ref. TASK 24-23-51-000-001-A) or (Ref. TASK 24-23-51-000-001-A-01).

Procedure (Ref. Fig. 24-23-00-991-00100-A - Components for Flight without an APU Generator Installed) Subtask 24-23-00-420-050-A A.

Installation of the Substitution Kit for Flight without an APU Generator Installed (1)

(2)

Do an inspection of the component interface and/or the adjacent area. (a)

Remove the COVER - PLASTIC from the generator pad on the accessory drive gearbox.

(b)

Clean the component interface and/or the adjacent area.

(c)

Remove and keep the nuts (1) from the studs. Make sure that the nuts (1) are serviceable.

(d)

Make sure that the face of the generator pad (10) and the studs are in the correct condition.

Do a visual inspection of the cable support assembly (5). (a)

(3)

(4)

AES

Make sure that the cable support assembly (5) is in the correct condition. 1

Make sure that the components of the terminal block are in the correct condition.

2

Do an inspection of the component interface and/or the adjacent area.

Do a visual inspection of the seal plate (4095KM) (7). (a)

Clean the seal plate (7) with OILS (Material No: 03-002) or OILS (Material No: 03-003) and a lint-free cotton cloth LINT-FREE COTTON CLOTH (Material No: 19-003) .

(b)

Make sure that the faces of the seal plate (7) are in the correct condition.

Do a visual inspection of the COVER-ASSEMBLY (3862619-1) (11). (a)

Make sure that the COVER-ASSEMBLY (3862619-1) (11) is clean and in the correct condition.

(b)

Make sure that the oil transfer channel and its inlet and outlet openings are clean and not clogged.

24-23-00 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (c) (5)

Make sure that the drain plug (6) is installed correctly, fully tightened and safetied with LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA (Material No: 19-010) .

Install the seal plate (4095KM) (7) on the COVER-ASSEMBLY (3862619-1) (11). (a)

Lubricate the new (IPC-CSN 49-11-04-05) seal (9) and the screws (8) with OILS (Material No: 03-002) or OILS (Material No: 03-003) .

(b)

Put the seal plate (7) in position on the COVER-ASSEMBLY (3862619-1) (11). NOTE :

(6)

(c)

Install the screws (8).

(d)

Install the seal (9) on the COVER-ASSEMBLY (3862619-1) (11).

Install the COVER-ASSEMBLY (3862619-1) (11). (a)

Put the COVER-ASSEMBLY (3862619-1) (11) in position on the generator pad (10). NOTE :

(7)

Make sure that the dowel pin on the COVER-ASSEMBLY (3862619-1) (11) engages correctly into the pilot hole on the seal plate (7).

(b)

Put the cable support assembly (5) in position.

(c)

Install the nuts (1).

(d)

TORQUE the nuts (1) to between 3.9 and 4.4 M.DAN (28.76 and 32.45 LBF.FT).

Install the generator supply cables (3) on the terminal block on the cable support assembly (5). (a)

Remove the nuts (2).

(b)

Remove the tie-wraps that temporarily hold the generator supply cables (3).

(c)

Remove the COVER - PLASTIC from the ring terminals of the generator supply cables (3).

(d)

Attach the generator supply cables (3) to the applicable studs on the terminal block with the nuts (2). NOTE :

(8)

Make sure that the dowel pin on the COVER-ASSEMBLY (3862619-1) (11) engages correctly into the pilot hole on the seal plate (7).

Refer to the marks on the terminal block and the generator supply cables (3).

Connect the generator control cable to the connector on the cable support assembly (5). (a)

Remove the tie-wrap that temporarily holds the electrical connector (4).

(b)

Remove the blanking caps from the electrical connector(s).

(c)

Make sure that the electrical connectors are clean and in the correct condition.

(d)

Connect the electrical connector (4) to the cable support assembly (5).

Subtask 24-23-00-865-051-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

121VU

PANEL

DESIGNATION APU/APU/CTL

2KD

L42

121VU

APU/ECB/SPLY

1KD

L41

AES

FIN

LOCATION

24-23-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-23-00-790-050-A C.

Leak test WARNING : DO NOT TOUCH THE APU UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S). (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Start the APU: . GTCP 36-300 (Ref. AMM 49-00-00-860-003) or . APS 3200 ** On A/C 006-099 (Ref. TASK 49-00-00-860-005-A) or (Ref. TASK 49-00-00-860-005-A-01) or . 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-00-00-860-008-A)(Ref. TASK 49-00-00-860-008-A-01).

(3)

Do a check for oil leaks. (a)

Examine the joint between the COVER-ASSEMBLY (3862619-1) (11) and the generator pad (10) on the accessory drive gearbox for oil leaks.

(b)

Examine the drain plug (6) on the COVER-ASSEMBLY (3862619-1) (11) for oil leaks. NOTE :

AES

Leaks are not permitted.

(4)

Stop the APU: . GTCP 36-300 (Ref. AMM 49-00-00-860-004) or . APS 3200 ** On A/C 006-099 (Ref. TASK 49-00-00-860-006-A) or (Ref. TASK 49-00-00-860-006-A-01) or . 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-00-00-860-009-A)(Ref. TASK 49-00-00-860-009-A-01).

(5)

Do a check of the oil quantity on the APU oil sight-glass. Add oil if the oil level is on or below the ADD mark on the oil sight glass: . GTCP 36-300 (Ref. AMM 49-90-00-600-001) or . APS 3200 ** On A/C 006-099 (Ref. TASK 49-90-00-600-004-A) or . 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-90-00-600-007-A).

24-23-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up ** On A/C ALL Subtask 24-23-00-410-050-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Set the control switch 11JL to the OFF position.

(3)

Close the APU access doors 315AL and 316AR (Ref. TASK 52-41-00-410-001-A).

(4)

Remove the access platform(s).

Subtask 24-23-00-860-052-A B.

AES

Put the aircraft back to its initial configuration. (1)

Put a PLACARD in the cockpit to tell persons that the APU generator is deactivated.

(2)

De-energize the ground service network (Ref. TASK 29-14-00-614-002-A).

(3)

Remove the warning notice(s).

(4)

Make an entry in the log book.

24-23-00 PB401

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR80

FR84

8XS

A

A

4

3 316AR

315AL

2

1 11

5

10

9

6 7 4095KM 8 N_MM_242300_4_AAM0_01_00

AES

FIGURE 24-23-00-991-00100-A SHEET 1 Components for Flight without an APU Generator Installed

24-23-00 PB401

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-23-00-440-001-A Reactivation of the APU Generator after Removal of the Substitution Kit WARNING : DO NOT TOUCH THE APU UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S). WARNING : USE THE CORRECT PERSONAL PROTECTION. OIL CAN HAVE ADDITIVE CALLED TRICRESYL PHOSPHATE IN IT. THIS CHEMICAL IS AN ASPHYXIANT, IT IS POISONOUS AND CAN BE ABSORBED THROUGH THE SKIN. USE CARE WHEN ENGINE OIL IS DRAINED. HOT OIL CAN POSSIBLY CAUSE BAD BURNS. 1.

Reason for the Job MMEL 24-23-01H AC Auxiliary Generation (APU Generator, GCU, Line Contactor) MMEL 24-23-01C AC Auxiliary Generation (APU Generator, GCU, Line Contactor) (Old MMEL ref: 24-20-02)

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)

No specific

AR

CAP - BLANKING

No specific

AR

CAP - BLANKING, PLASTIC

No specific

AR

CONTAINER 1 L (1/4 USGAL)

No specific

1

INSTALLATION TOOL - TIE WRAP

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

3862619-1

1

COVER-ASSEMBLY

B.

Consumable Materials

REFERENCE Material No: 19-010 C.

DESIGNATION LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

315AL, 316AR D.

Referenced Information

REFERENCE 24-23-51-400-001-A 24-23-51-400-001-A-01 24-42-00-861-001-A

DESIGNATION Installation of the APU Generator Installation of the APU Generator with the Minilift Hoist Energize the Ground Service Network from the External Power

29-00-00-864-001-A

Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Pressurization of the Hydraulic Reservoirs through the Ground Connector

29-14-00-614-002-A

AES

24-23-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 52-41-00-010-001-A

DESIGNATION Open the APU Doors for Access

52-41-00-410-001-A Close the APU Doors after Access (Ref. Fig. 24-23-00-991-00100-A - Components for Flight without an APU Generator Installed) 3.

Job Set-up Subtask 24-23-00-860-053-A A.

Aircraft Maintenance Configuration (1)

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

(2)

On the APU section of the overhead panel 25VU, make sure that the APU MASTER SW pushbutton switch is released (the ON legend is off).

(3)

Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to start the APU.

(4)

Make sure that the ground fire-extinguishing equipment is available.

(5)

Make sure that hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001-A).

Subtask 24-23-00-865-052-A B.

Open, safety and tag this(these) circuit breaker(s):

121VU

PANEL

DESIGNATION APU/APU/CTL

2KD

FIN L42

LOCATION

121VU

APU/ECB/SPLY

1KD

L41

Subtask 24-23-00-010-051-A C.

4.

Get Access (1)

Put the ACCESS PLATFORM 4M (13 FT) in position below the APU compartment.

(2)

Open the APU access doors 315AL and 316AR (Ref. TASK 52-41-00-010-001-A).

(3)

Set the control switch 11LJ to the ON position.

Procedure (Ref. Fig. 24-23-00-991-00100-A - Components for Flight without an APU Generator Installed) Subtask 24-23-00-020-050-A A.

Removal of the Substitution Kit for Fight without an APU Generator Installed (1)

(2)

AES

Disconnect the generator control cable from the connector on the cable support assembly (5). (a)

Remove the electrical connector (4).

(b)

Put blanking caps on the disconnected electrical connector(s).

(c)

Temporarily attach the electrical connector (4) to the APU generator with a INSTALLATION TOOL - TIE WRAP.

Disconnect the generator supply cables (3) from the terminal block on the cable support assembly (5). (a)

Remove the nuts (2) and disconnect the generator supply cables (3).

(b)

Temporarily install the nuts (2) on the studs of the terminal block on the cable support assembly (5).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

(3)

(4)

(5)

5.

(c)

Put CAP - BLANKING, PLASTIC on the ring terminals of the disconnected generator supply cables (3).

(d)

Temporarily attach the generator supply cables (3) with a tie-wrap to put it in stowage position in the APU compartment.

Drain the remaining oil from the COVER-ASSEMBLY (3862619-1) (11). (a)

Put the CONTAINER 1 L (1/4 USGAL) in position below the generator pad (10).

(b)

Remove and discard the lockwire from the drain plug (6).

(c)

Remove the drain plug (6) and let the residual oil drain fully.

(d)

Tighten the drain plug (6) and safety it with LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA (Material No: 19-010) .

Remove the cable support assembly (5) and the COVER-ASSEMBLY (3862619-1) (11). (a)

Hold the cable support assembly (5) and the COVER-ASSEMBLY (3862619-1) (11) in the correct position.

(b)

Remove and keep the nuts (1).

(c)

Remove the cable support assembly (5) and the COVER-ASSEMBLY (3862619-1) (11).

Remove the seal plate (4095KM) (7). (a)

Remove the seal (9).

(b)

Remove the screws (8) and the seal plate (4095KM) (7).

(c)

Remove the container.

(6)

Clean the component interface and/or the adjacent area.

(7)

Do an inspection of the component interface and/or the adjacent area.

(8)

Make sure that the parts retained from the removed component are clean and in the correct condition.

(9)

Install the APU generator (Ref. TASK 24-23-51-400-001-A) or (Ref. TASK 24-23-51-400-001-A-01).

Close-up Subtask 24-23-00-865-053-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

121VU

PANEL

DESIGNATION APU/APU/CTL

2KD

FIN L42

LOCATION

121VU

APU/ECB/SPLY

1KD

L41

Subtask 24-23-00-410-051-A B.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Set the control switch 11JL to the OFF position.

(3)

Close the APU access doors 315AL and 316AR (Ref. TASK 52-41-00-410-001-A).

(4)

Remove the access platform(s).

24-23-00 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-23-00-860-054-A C.

AES

Put the aircraft back to its initial configuration. (1)

De-energize the ground service network (Ref. TASK 29-14-00-614-002-A).

(2)

Remove the warning notice(s).

24-23-00 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-23-00-040-002-A Deactivation of the APU Generator by Removal of the Quill Shaft WARNING : DO NOT TOUCH THE APU UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S). WARNING : USE THE CORRECT PERSONAL PROTECTION. OIL CAN HAVE ADDITIVE CALLED TRICRESYL PHOSPHATE IN IT. THIS CHEMICAL IS AN ASPHYXIANT, IT IS POISONOUS AND CAN BE ABSORBED THROUGH THE SKIN. USE CARE WHEN ENGINE OIL IS DRAINED. HOT OIL CAN POSSIBLY CAUSE BAD BURNS. 1.

Reason for the Job MMEL 24-23-01I AC Auxiliary Generation (APU Generator, GCU, Line Contactor) MMEL 24-23-01C AC Auxiliary Generation (APU Generator, GCU, Line Contactor) (Old MMEL ref: 24-20-02)

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)

No specific

1

PLACARD

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

315AL, 316AR C.

Referenced Information

REFERENCE 24-23-51-000-001-A 24-23-51-000-001-A-01 24-23-51-400-001-A 24-23-51-400-001-A-01 24-42-00-861-001-A

DESIGNATION Removal of the APU Generator Removal of the APU Generator with the Minilift Hoist Installation of the APU Generator Installation of the APU Generator with the Minilift Hoist Energize the Ground Service Network from the External Power

29-00-00-864-001-A

Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Pressurization of the Hydraulic Reservoirs through the Ground Connector

29-14-00-614-002-A

52-41-00-010-001-A Open the APU Doors for Access 52-41-00-410-001-A Close the APU Doors after Access (Ref. Fig. 24-23-00-991-00200-A - APU Generator without Quill Shaft)

AES

24-23-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-23-00-860-055-A A.

Aircraft Maintenance Configuration (1)

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

(2)

On the APU section of the overhead panel 25VU, make sure that the APU MASTER SW pushbutton is released (the ON legend is off).

(3)

Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to start the APU.

(4)

Make sure that the ground fire extinguishing equipment is available.

(5)

Make sure that hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001-A).

Subtask 24-23-00-865-054-A B.

Open, safety and tag this(these) circuit breaker(s):

121VU

PANEL

DESIGNATION APU/APU/CTL

2KD

FIN L42

LOCATION

121VU

APU/ECB/SPLY

1KD

L41

Subtask 24-23-00-010-053-A C.

4.

Get Access (1)

Put the ACCESS PLATFORM 4M (13 FT) in position below the APU compartment.

(2)

Open the APU access doors 315AL and 316AR (Ref. TASK 52-41-00-010-001-A).

(3)

Set the control switch 11LJ to the ON position.

Procedure (Ref. Fig. 24-23-00-991-00200-A - APU Generator without Quill Shaft) Subtask 24-23-00-020-051-A A.

Remove the APU Generator (Ref. TASK 24-23-51-000-001-A) or (Ref. TASK 24-23-51-000-001-A-01).

Subtask 24-23-00-020-052-A B.

Remove the Quill Shaft (1)

Carefully remove the bolt (1) from the groove in the drive end of the finished rotor assembly.

(2)

Remove the quill shaft assembly (3) from the drive end of the finished rotor assembly.

(3)

Remove the seals (2) and (4) from the quill shaft assembly (3).

(4)

Discard the seals.

Subtask 24-23-00-420-051-A C.

AES

Install the APU generator (Ref. TASK 24-23-51-400-001-A) or (Ref. TASK 24-23-51-400-001-A-01) without the quill shaft.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-23-00-865-055-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

121VU

PANEL

DESIGNATION APU/APU/CTL

2KD

FIN L42

LOCATION

121VU

APU/ECB/SPLY

1KD

L41

Subtask 24-23-00-410-052-A B.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Set the control switch 11JL to the OFF position.

(3)

Close the APU access doors 315AL and 316AR (Ref. TASK 52-41-00-410-001-A).

(4)

Remove the access platform(s).

Subtask 24-23-00-860-056-A C.

AES

Put the aircraft back to its initial configuration. (1)

Put a PLACARD in the cockpit to tell persons that the APU generator is deactivated.

(2)

De-energize the ground service network (Ref. TASK 29-14-00-614-002-A).

(3)

Remove the warning notice(s).

(4)

Make an entry in the log book.

24-23-00 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR80

FR84

8XS

A 316AR

315AL

A

4 3 1

2

N_MM_242300_4_AAN0_01_00

AES

FIGURE 24-23-00-991-00200-A SHEET 1 APU Generator without Quill Shaft

24-23-00 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-23-00-440-002-A Reactivation of the APU Generator after Quill Shaft Removal WARNING : DO NOT TOUCH THE APU UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S). WARNING : USE THE CORRECT PERSONAL PROTECTION. OIL CAN HAVE ADDITIVE CALLED TRICRESYL PHOSPHATE IN IT. THIS CHEMICAL IS AN ASPHYXIANT, IT IS POISONOUS AND CAN BE ABSORBED THROUGH THE SKIN. USE CARE WHEN ENGINE OIL IS DRAINED. HOT OIL CAN POSSIBLY CAUSE BAD BURNS. 1.

Reason for the Job MMEL 24-23-01I AC Auxiliary Generation (APU Generator, GCU, Line Contactor) MMEL 24-23-01C AC Auxiliary Generation (APU Generator, GCU, Line Contactor) (Old MMEL ref: 24-20-02)

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels

ZONE/ACCESS 315AL, 316AR C.

ZONE DESCRIPTION

Referenced Information

REFERENCE 24-23-51-000-001-A 24-23-51-000-001-A-01 24-23-51-400-001-A 24-23-51-400-001-A-01 24-42-00-861-001-A 29-00-00-864-001-A

DESIGNATION Removal of the APU Generator Removal of the APU Generator with the Minilift Hoist Installation of the APU Generator Installation of the APU Generator with the Minilift Hoist Energize the Ground Service Network from the External Power

29-14-00-614-002-A

Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Pressurization of the Hydraulic Reservoirs through the Ground Connector

52-41-00-010-001-A 52-41-00-410-001-A

Open the APU Doors for Access Close the APU Doors after Access

AES

24-23-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-23-00-860-057-A A.

Aircraft Maintenance Configuration (1)

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

(2)

On the APU section of the overhead panel 25VU, make sure that the APU MASTER SW pushbutton is released (the ON legend is off).

(3)

Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to start the APU.

(4)

Make sure that the ground fire-extinguishing equipment is available.

(5)

Make sure that hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001-A).

Subtask 24-23-00-865-056-A B.

Open, safety and tag this(these) circuit breaker(s):

121VU

PANEL

DESIGNATION APU/APU/CTL

2KD

FIN L42

LOCATION

121VU

APU/ECB/SPLY

1KD

L41

Subtask 24-23-00-010-054-A C.

4.

Get Access (1)

Put the ACCESS PLATFORM 4M (13 FT) in position below the APU compartment.

(2)

Open the APU access doors 315AL and 316AR (Ref. TASK 52-41-00-010-001-A).

(3)

Set the control switch 11LJ to the ON position.

Procedure Subtask 24-23-00-020-053-A A.

Remove the APU Generator (Ref. TASK 24-23-51-000-001-A) or (Ref. TASK 24-23-51-000-001-A-01) without the quill shaft.

Subtask 24-23-00-420-052-A B. 5.

Install the new APU Generator (Ref. TASK 24-23-51-400-001-A) or (Ref. TASK 24-23-51-400-001-A-01).

Close-up Subtask 24-23-00-865-057-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

121VU

DESIGNATION APU/APU/CTL

FIN

LOCATION

2KD

L42

121VU

APU/ECB/SPLY

1KD

L41

Subtask 24-23-00-410-053-A B.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Set the control switch 11JL to the OFF position.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Close the APU access doors 315AL and 316AR (Ref. TASK 52-41-00-410-001-A).

(4)

Remove the access platform(s).

Subtask 24-23-00-860-058-A C.

AES

Put the aircraft back to its initial configuration. (1)

De-energize the ground service network (Ref. TASK 29-14-00-614-002-A).

(2)

Remove the warning notice(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CURRENT TRANSFORMER - AC - REMOVAL/INSTALLATION ** On A/C ALL Task 24-23-17-000-001-A Removal of the AC Current Transformer WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 42XS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific No specific

AR AR

CAP - BLANKING TIE WRAP

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL C.

Referenced Information

REFERENCE 25-11-41-000-001-A

DESIGNATION Removal of the Third Occupant Seat

(Ref. Fig. 24-23-17-991-00300-A - AC Current Transformer - Block Diagram) (Ref. Fig. 24-23-17-991-00400-A - AC Current Transformer) (Ref. Fig. 24-23-17-991-00400-B - AC Current Transformer) 3.

Job Set-up Subtask 24-23-17-010-050-A A.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

On the rear panel 120VU, open the panel which gives access to the AC power center 123VU.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-23-17-941-050-A B.

Safety Precautions (1)

AES

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

24-23-17 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4.

(2)

Put WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In . . . .

(4)

In the cockpit, put WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pusbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

Procedure ** On A/C 003-004 Subtask 24-23-17-020-051-A A.

Removal of the AC Current Transformer (Ref. Fig. 24-23-17-991-00300-A - AC Current Transformer - Block Diagram) (Ref. Fig. 24-23-17-991-00400-A - AC Current Transformer) (1)

Remove the screws (12) and the washers (11) from the studs of the contactor (5).

(2)

Disconnect the cables (10) from the studs of the contactor (5). NOTE :

You must identify (also with the indications on the current transformer) and disconnect only the cables which go through the current transformer.

(3)

Remove the nuts (9) and the washers (8) from the studs of the contactor (5).

(4)

Disconnect the cables (6) and (7) from the studs of the contactor (5).

(5)

Disconnect the electrical connector (4) from the current transformer (1).

(6)

Put CAP - BLANKING on the disconnected electrical connector (4) and electrical receptacle.

(7)

Remove the screws (3) and the washers (2) from the current transformer (1).

(8)

Remove the necessary TIE WRAP to move the current transformer (1) along the cables.

(9)

Remove the current transformer (1).

** On A/C 005-099 Subtask 24-23-17-020-051-B A.

Removal of the AC Current Transformer (Ref. Fig. 24-23-17-991-00300-A - AC Current Transformer - Block Diagram) (Ref. Fig. 24-23-17-991-00400-B - AC Current Transformer) (1)

Remove the screws (12) and the washers (11) from the studs of the module 29XN.

(2)

Disconnect the cables (10) from the studs of the module 29XN. NOTE :

(3)

AES

You must identify (also with the indications on the current transformer) and disconnect only the cables which go through the current transformer.

Remove the nuts (9) and the washers (8) from the studs of the module 29XN.

24-23-17 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AES

(4)

Disconnect the cables (6) and (7) from the studs of the module 29XN.

(5)

Disconnect the electrical connector (4) from the current transformer (1).

(6)

Put CAP - BLANKING on the disconnected electrical connector (4) and electrical receptacle.

(7)

Remove the screws (3) and the washers (2) from the current transformer (1).

(8)

Remove and discard the necessary TIE WRAP to move the current transformer (1) along the cables.

(9)

Remove the current transformer (1).

24-23-17 PB401

Page 3 May 01/12 Revision n˚: 40

AES

FIGURE 24-23-17-991-00300-A SHEET 1 AC Current Transformer - Block Diagram GCU−1 1XU1

GEN 1

AC BUS 1 115VAC

11XU1 BTC−1

4000XU

11(12)QA

1XP

1XS

GCU−APU

42XS

FUEL PUMPS 53(54)QA 28−21−00

APU GEN

GPCU

8XS

DIFFERENTIAL MEASURE AND PROTECTION

1XG

AC BUS 2

2XP

EXTERNAL POWER RECEPTACLE

11XU2 BTC−2

115VAC

GCU−2 1XU2

GEN 2

4000XU

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242317_4_AAM0_01_00

24-23-17 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

A 120VU

122VU

B

121VU 124VU

42XS

123VU

C 3XS

A C 6 7 8 9 10

11

12

B

1

5

4 2 3 N_MM_242317_4_ABM0_01_00

AES

FIGURE 24-23-17-991-00400-A SHEET 1 AC Current Transformer

24-23-17 PB401

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A 120VU

122VU

B

121VU 124VU

42XS

123VU

3XS

C

29XN

A B 1

MODULE 29XN

C 6

4 2

7 3

8 9 10

11

12

5 N_MM_242317_4_ABP0_01_00

AES

FIGURE 24-23-17-991-00400-B SHEET 1 AC Current Transformer

24-23-17 PB401

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-23-17-400-001-A Installation of the AC Current Transformer WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 42XS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 18M (59 FT) - ADJUSTABLE

No specific

AR

TIE WRAP

No specific

AR

WARNING NOTICE(S)

** On A/C 005-099 No specific

Torque wrench: range to between 0.00 and 1.20 M.DAN (0.00 and 9.00 LBF.FT)

No specific

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL C.

Referenced Information

REFERENCE 24-41-00-740-004-A

DESIGNATION Operational Check of the GPCU via the CFDS

24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-11-41-000-001-A 25-11-41-400-001-A

Removal of the Third Occupant Seat Installation of the Third Occupant Seat

(Ref. Fig. 24-23-17-991-00300-A - AC Current Transformer - Block Diagram) (Ref. Fig. 24-23-17-991-00400-A - AC Current Transformer) (Ref. Fig. 24-23-17-991-00400-B - AC Current Transformer)

AES

24-23-17 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up ** On A/C ALL Subtask 24-23-17-010-051-A A.

Get access (1)

Make sure that the Third Occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(2)

On the rear panel 120VU, make sure that the panel which gives access to the AC power center 123VU is open.

(3)

Make sure that the ACCESS PLATFORM 18M (59 FT) - ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

Subtask 24-23-17-860-050-A B.

4.

Aircraft Maintenance Configuration (1)

Make sure that the external power connector is not connected to the aircraft external power receptacle.

(2)

Make sure that the WARNING NOTICE(S) is (are) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft external power receptacle.

(3)

In . . . .

(4)

In the cockpit, make sure that the WARNING NOTICE(S) is (are) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

Procedure ** On A/C 003-004 Subtask 24-23-17-420-050-A A.

Installation of the AC Current Transformer (Ref. Fig. 24-23-17-991-00300-A - AC Current Transformer - Block Diagram) (Ref. Fig. 24-23-17-991-00400-A - AC Current Transformer) (1)

Put the cables (6), (7) and (10) through the current transformer (1). NOTE :

AES

Make sure that the location of the cables agrees with that you recorded at the removal.

(2)

Move the current transformer (1) along the cables.

(3)

Install the washers (2) and the screws (3) on the current transformer (1) and tighten them.

(4)

Remove the blanking caps from the electrical connector(s).

(5)

Make sure that the electrical connectors are clean and in the correct condition.

(6)

Connect the electrical connector (4) to the current transformer (1).

(7)

Install new TIE WRAP.

24-23-17 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (8)

Install the cables (6) and (7), the washers (8) and the nuts (9) on the studs of the contactor (5) and tighten them.

(9)

Install the cables (10), the washers (11) and the screws (12) on the studs of the contactor (5) and tighten them.

** On A/C 005-099 Subtask 24-23-17-420-050-B A.

Installation of the AC Current Transformer (Ref. Fig. 24-23-17-991-00300-A - AC Current Transformer - Block Diagram) (Ref. Fig. 24-23-17-991-00400-B - AC Current Transformer) (1)

Put the disconnected cables (6), (7) and (10) through the current transformer (1). NOTE :

Make sure that the location of the cables agrees with that you recorded at the removal.

(2)

Move the current transformer (1) along the cables.

(3)

Install the washers (2) and the screws (3) on the current transformer (1) and tighten them.

(4)

Remove the blanking caps from the electrical connector (4) and the electrical receptacle.

(5)

Make sure that the electrical connectors are clean and in the correct condition.

(6)

Connect the electrical connector (4) to the current transformer (1).

(7)

Install new TIE WRAP.

(8)

Connect the cables (6) and (7), to the studs of the module 29XN.

(9)

Install the washers (8) and the nuts (9) on the studs of the module 29XN.

(10) TORQUE the nuts (9) to between 1.25 and 1.35 M.DAN (110.62 and 119.47 LBF.IN). (11) Connect the cables (10) to the studs of the module 29XN. (12) Install the washers (11) and the screws (12) on the studs of the module 29XN. (13) TORQUE the screws (12) to between 0.17 and 0.19 M.DAN (15.04 and 16.81 LBF.IN). ** On A/C ALL Subtask 24-23-17-860-051-A B.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits from the APU (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

Subtask 24-23-17-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

122VU

DESIGNATION ELEC/GALLEY/CNTOR

7MC

FIN S28

LOCATION

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

FWD GALLEY/FEEDER D

2MC

AD04

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL 123VU

AES

24-23-17 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

123VU

PANEL

DESIGNATION AFT GALLEY/FEEDER A

3MC

FIN AF04

LOCATION

123VU

AFT GALLEY/FEEDER B

12MC

AD09

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

FWD GALLEY/FEEDER F

16MC

AC10

FWD GALLEY/FEEDER C

1MC

AE10

** On A/C 005-099 123VU

** On A/C 003-004 Subtask 24-23-17-710-050-A D.

Operational test (1)

Do this test:

ACTION 1.On the ECAM control panel: . Push the ELEC key to get the ELEC page

RESULT On the lower ECAM display unit: . The ELEC page comes into view.

2.On the ELEC panel 35VU: . Push the GALLEY pushbutton switch.

On the panel 35VU: . The OFF legend of the GALLEY pushbutton switch goes off.

3.In the FWD and/or AFT galleys: . Energize all the items of equipment.

On the lower ECAM display unit: . Make sure that the electrical parameters (load, voltage and frequency) of the APU GEN are correct.

4.On the MCDU: On the MCDU, on the AC GEN page: . Do the operational check of the GPCU with the CFDS . The TEST OK message comes into view (after some (Ref. TASK 24-41-00-740-004-A). seconds). ** On A/C 005-099 Subtask 24-23-17-710-050-B D.

Operational test (1)

Do this test:

ACTION 1.On the ECAM control panel: . Push the ELEC key to get the ELEC page

RESULT On the lower ECAM display unit: . The ELEC page comes into view.

2.On the ELEC panel 35VU: . Push the GALY & CAB pushbutton switch.

On the panel 35VU: . The OFF legend of the GALY & CAB pushbutton switch goes off.

3.In the FWD and/or AFT galleys: . Energize all the items of equipment.

On the lower ECAM display unit: . Make sure that the electrical parameters (load, voltage and frequency) of the APU GEN are correct.

4.On the MCDU: On the MCDU, on the AC GEN page: . Do the operational check of the GPCU with the CFDS . The TEST OK message comes into view (after some (Ref. TASK 24-41-00-740-004-A). seconds).

AES

24-23-17 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Subtask 24-23-17-860-052-A E.

Aircraft Maintenance Configuration (1)

De-energize the aircraft electrical circuits supplied from the APU (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Subtask 24-23-17-410-050-A F.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

On the rear panel 120VU, close the panel which gives access to the AC power center 123VU.

(3)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

24-23-17 PB401

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTROL UNIT - GENERATOR (GCU) REMOVAL/INSTALLATION ** On A/C ALL Task 24-23-34-000-001-A Removal of the GCU-APU CAUTION :

MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF DAMAGE TO EQUIPMENT DURING ITS REMOVAL/ INSTALLATION IF THE AC OR DC POWER STAYS CONNECTED.

FIN 1XS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 18M (59 FT) - ADJUSTABLE

No specific No specific

AR AR

CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

121 811

ZONE DESCRIPTION AVIONICS COMPARTMENT

C.

Referenced Information

REFERENCE DESIGNATION (Ref. Fig. 24-23-34-991-00100-A - APU Generator Control Unit (GCU)) 3.

Job Set-up Subtask 24-23-34-860-051-A A.

AES

Safety Precautions (1)

In the cockpit, on the overhead panel 25VU and 35VU, make sure these pushbutton switches are released: . START, . APU GEN.

(2)

In the cockpit, put WARNING NOTICE(S) to tell persons not to operate the pushbutton switches on these overhead panels: . 25VU (APU), . 35VU (ELEC).

24-23-34 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-23-34-865-050-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL

122VU

DESIGNATION ELEC/GEN1/OFF/BTC1 SPLY

FIN

LOCATION

5XU

T28

122VU

ELEC/APU/GCU

6XS

Y25

Subtask 24-23-34-010-050-A C.

4.

Get Access (1)

Put an ACCESS PLATFORM 18M (59 FT) - ADJUSTABLE at the access door 811 of the avionics compartment.

(2)

Open the access door 811.

Procedure (Ref. Fig. 24-23-34-991-00100-A - APU Generator Control Unit (GCU)) Subtask 24-23-34-020-050-A A.

AES

Removal of the GCU (1)

Loosen the 2 knurled nuts (1).

(2)

Lower the 2 knurled nuts (1) to disengage the 2 studs (2).

(3)

Carefully pull the handle (3) of the GCU (4) until the GCU is disconnected from the rack receptacle (5).

(4)

Remove the GCU from the rack (6).

(5)

Put CAP - BLANKING on the rack receptacle (5) and the GCU connector.

24-23-34 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR9

A 1XS

FR1

B

A

811

B FWD ELECTRONICS RACK 90VU 4

3

2

5 6

1 N_MM_242334_4_AAM0_01_00

AES

FIGURE 24-23-34-991-00100-A SHEET 1 APU Generator Control Unit (GCU)

24-23-34 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-23-34-400-001-A Installation of the GCU-APU CAUTION :

MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF DAMAGE TO EQUIPMENT DURING ITS REMOVAL/ INSTALLATION IF THE AC OR DC POWER STAYS CONNECTED.

FIN 1XS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

121 811

ZONE DESCRIPTION AVIONICS COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-740-004-A 24-41-00-861-002-A

DESIGNATION Operational Check of the GPCU via the CFDS Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

(Ref. Fig. 24-23-34-991-00100-A - APU Generator Control Unit (GCU)) 3.

Job Set-up Subtask 24-23-34-860-052-A A.

Aircraft Maintenance Configuration (1)

AES

In the cockpit, on the overhead panel 25VU and 35VU, make sure that these pushbutton switches are released: . START, . APU GEN.

24-23-34 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

In the cockpit, make sure that WARNING NOTICE(S) are in position to tell persons not to operate the pushbutton switches on these overhead panels: . 25VU (APU), . 35VU (ELEC).

Subtask 24-23-34-865-052-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

122VU

PANEL

DESIGNATION ELEC/GEN1/OFF/BTC1 SPLY

5XU

FIN T28

LOCATION

122VU

ELEC/APU/GCU

6XS

Y25

Subtask 24-23-34-010-051-A C.

4.

Get Access (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 811 of the avionics compartment.

(2)

Make sure that the access door 811 is open.

Procedure (Ref. Fig. 24-23-34-991-00100-A - APU Generator Control Unit (GCU)) Subtask 24-23-34-420-050-A A.

Installation of the GCU (1)

Remove the blanking caps from the electrical connector(s).

(2)

Make sure that the electrical connectors are clean and in the correct condition.

(3)

Clean the component interface and/or the adjacent area.

(4)

Do an inspection of the component interface and/or the adjacent area.

(5)

Put the GCU in position in the rack (6).

(6)

Carefully push the GCU until it is connected to the rack receptacle (5).

(7)

Lift the 2 knurled nuts (1) on the 2 studs (2).

(8)

Tighten the 2 knurled nuts (1).

Subtask 24-23-34-865-055-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

122VU

DESIGNATION ELEC/GEN1/OFF/BTC1 SPLY

FIN

LOCATION

5XU

T28

122VU

ELEC/APU/GCU

6XS

Y25

Subtask 24-23-34-710-050-A C.

Operational Test of the GCU (1)

Do the operational check of the GPCU with the CFDS (Ref. TASK 24-41-00-740-004-A). NOTE :

AES

As an alternative procedure, do this operational test without the CFDS:

24-23-34 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

5.

Do an operational test of the GCU without the CFDS: (a)

Do the procedure to energize the electrical circuits with the APU (Ref. TASK 24-41-00-861-002A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(b)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(c)

On the ECAM control panel: . push the ELEC key to get the ELEC system page.

(d)

On the lower ECAM display unit, make sure that the A/C electrical configuration is correct.

(e)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A)

(f)

De-energize the electrical circuits supplied from the APU (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Close-up Subtask 24-23-34-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access door 811.

(3)

Remove the access platform(s).

(4)

Remove the warning notice(s).

24-23-34 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

GENERATOR - APU - REMOVAL/INSTALLATION ** On A/C ALL Task 24-23-51-000-001-A Removal of the APU Generator WARNING : ISOLATE THE ELECTRICAL CIRCUITS FROM THE RELATED EQUIPMENT AND THE ENVIRONMENT. WARNING : LOCK THE MECHANISM OF THE ACCESS DOOR 316AR WITH THE PIP PIN WHEN YOU OPEN THE ACCESS DOOR. THIS WILL PREVENT INJURY. WARNING : DO NOT TOUCH THE APU UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S). WARNING : DO NOT LET OIL STAY ON YOUR SKIN FOR A LONG TIME AS IT CAN CAUSE INJURY. WARNING : DO NOT CAUSE DAMAGE TO THE THREADS OF THE SET SCREWS WHEN YOU REMOVE OR INSTALL THE GENERATOR. THE GENERATOR WEIGHS APPROXIMATELY 23kg (50.7lb). FIN 8XS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

CONTAINER 3 L(3/4 USGAL)

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

98D49207537001

1

CABLE-SAFETY, APU GENERATOR

B.

Work Zones and Access Panels

ZONE/ACCESS 315AL, 316AR C.

ZONE DESCRIPTION

Referenced Information

REFERENCE 29-00-00-864-001-A

DESIGNATION Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action

** On A/C 006-099 49-90-00-600-004-A

Check Oil Level and Replenish (APS 3200)

49-90-00-600-005-A

Oil Change (Drain Procedure) (APS 3200)

AES

24-23-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 49-90-00-600-005-A-01

DESIGNATION Oil Change (Top-Off Procedure) (APS 3200)

49-90-00-600-005-A-02

Brand/Type Oil Change (Flush Procedure) (APS 3200)

** On A/C 003-005 49-90-00-600-007-A

Check Oil Level and Replenish (131-9(A))

49-90-00-600-008-A

Oil Change (Drain Procedure) (131-9(A))

49-90-00-600-008-A-01

Oil Change (Top-Off Procedure) (131-9(A))

49-90-00-600-008-A-02

Brand/Type Oil Change (Flush Procedure) (131-(A))

49-91-41-200-002-A

Remove and Discard Oil Filter Elements (131-9(A))

** On A/C 006-099 49-91-41-920-001-A

Discard Pressure Oil Filter Element (APS 3200)

49-91-41-920-002-A

Replace AC-Generator Scavenge Filter-Element (APS 3200)

52-41-00-010-001-A

Open the APU Doors for Access

(Ref. Fig. 24-23-51-991-00100-B - APU Generator 8XS) (Ref. Fig. 24-23-51-991-00300-B - APU Generator Safety Cable) 3.

Job Set-up ** On A/C ALL Subtask 24-23-51-860-050-A A.

Aircraft Maintenance Configuration (1)

On the panel 25VU, make sure that the APU MASTER SW pushbutton switch is off.

(2)

Put a WARNING NOTICE(S) in the cockpit to tell persons not to start the APU.

(3)

Make sure that ground fire extinguishing equipment is available.

(4)

Make sure that hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001-A).

Subtask 24-23-51-865-050-A B.

Open, safety and tag this(these) circuit breaker(s):

121VU

PANEL

DESIGNATION APU/APU/CTL

2KD

FIN L42

LOCATION

121VU

APU/ECB/SPLY

1KD

L41

Subtask 24-23-51-010-050-A C.

4.

Get Access (1)

Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the APU access doors 315AL and 316AR.

(2)

Open the APU access doors 315AL and 316AR (Ref. TASK 52-41-00-010-001-A).

Procedure (Ref. Fig. 24-23-51-991-00100-B - APU Generator 8XS) (Ref. Fig. 24-23-51-991-00300-B - APU Generator Safety Cable)

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24-23-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-23-51-020-050-A A.

Removal of the APU Generator WARNING : DO NOT CAUSE DAMAGE TO THE THREADS OF THE SET SCREWS WHEN YOU REMOVE OR INSTALL THE GENERATOR. THE GENERATOR WEIGHS APPROXIMATELY 23kg (50.7lb). (1)

Put the CABLE-SAFETY, APU GENERATOR (98D49207537001) on the generator to get a safe condition when you remove the generator.

(2)

Disconnect the electrical connector (12) from the APU generator (4).

(3)

Put blanking caps on the disconnected electrical connector(s).

(4)

Remove the screws (17),the washers (16) and the cover plate (18).

(5)

Remove the nuts (19), the four electrical cables (20) and the washers (21). NOTE :

Remember that washers (21) are not installed on a model of APU Generator.

(6)

Put a CONTAINER 3 L(3/4 USGAL) below the generator (4) to collect the oil which will flow when you remove the drain plug (14).

(7)

Remove the drain plug (14). Take care to collect the drained oil in the container.

(8)

Remove and discard the sealwasher (13) from the drain plug (14).

(9)

Loosen the bolts CAUTION :

(a)

BE CAREFUL WHEN YOU REMOVE THE NUTS. A SPANNER CAN EASILY CAUSE DAMAGE TO THE ADJACENT WEBS OF THE GENERATOR HOUSING.

Support the generator (4), loosen the bolts (15) until the generator can be rotated.

(10) Turn the Generator CAUTION :

(a)

BE CAREFUL WHEN YOU TURN THE GENERATOR. TOOLS THAT YOU USE TO HELP YOU MOVE THE APU GENERATOR CAN EASILY CAUSE DAMAGE TO THE HOUSING. DO NOT APPLY FORCE TO THE WEBS AT THE MAIN FLANGE.

Turn the generator (4) counterclockwise and withdraw it from the gear-box splined drive.

(11) Remove and discard the O-rings (9) and (10). (12) Remove the countersunk screws (1) and the seal plate (7), if a new generator must be installed. Subtask 24-23-51-210-059-A B.

Replacement and check of the APU Oil Filters . for APU GTCP 36-300 (Ref. AMM 49-91-45-200-003) . . for APU APS3200

.

** On A/C 006-099 (Ref. TASK 49-91-41-920-001-A) and (Ref. TASK 49-91-41-920-002-A). for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-91-41-200-002-A).

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Subtask 24-23-51-612-050-A C.

Draining and check of the oil (1)

Drain the oil: . for APU GTCP 36-300 (Ref. AMM 49-90-00-600-002) . . for APU APS3200

.

** On A/C 006-099 (Ref. TASK 49-90-00-600-005-A) or (Ref. TASK 49-90-00-600-005-A-01) or (Ref. TASK 49-90-00-600-005-A-02). for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-90-00-600-008-A)(Ref. TASK 49-90-00-600-008-A-01)(Ref. TASK 49-90-00-600-008-A-02).

(2)

Fill the APU reservoir: . for APU GTCP 36-300 (Ref. AMM 49-90-00-600-001) . . for APU APS3200

.

** On A/C 006-099 (Ref. TASK 49-90-00-600-004-A). for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-90-00-600-007-A).

AES

24-23-51 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR80

FR84

A

3

8XS 1

B

2

11

8 316AR 4

5

315AL

6

C

19 21

7 4095KM

10 1

12

20 9

B C 18

A 17 16

4

13

15

14

N_MM_242351_4_LAM0_01_00

AES

FIGURE 24-23-51-991-00100-B SHEET 1 APU Generator 8XS

24-23-51 PB401

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR80

A

FR84

A

B 40 8XS

41

42 316AR

315AL

42

B 43

44

10

N_MM_242351_4_LCM0_01_00

AES

FIGURE 24-23-51-991-00300-B SHEET 1 APU Generator Safety Cable

24-23-51 PB401

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-23-51-000-001-A-01 Removal of the APU Generator with the Minilift Hoist WARNING : ISOLATE THE ELECTRICAL CIRCUITS FROM THE RELATED EQUIPMENT AND THE ENVIRONMENT. WARNING : LOCK THE MECHANISM OF THE ACCESS DOOR 316AR WITH THE PIP PIN WHEN YOU OPEN THE ACCESS DOOR. THIS WILL PREVENT INJURY. WARNING : DO NOT TOUCH THE APU UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S). WARNING : DO NOT LET OIL STAY ON YOUR SKIN FOR A LONG TIME AS IT CAN CAUSE INJURY. WARNING : DO NOT CAUSE DAMAGE TO THE THREADS OF THE SET SCREWS WHEN YOU REMOVE OR INSTALL THE GENERATOR. THE GENERATOR WEIGHS APPROXIMATELY 23kg (50.7lb). FIN 8XS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

CONTAINER 3 L(3/4 USGAL)

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

A1-91-265

1

HOIST-MINILIFT

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

315AL, 316AR C.

Referenced Information

REFERENCE 29-00-00-864-001-A

DESIGNATION Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action

** On A/C 006-099 49-90-00-600-004-A

Check Oil Level and Replenish (APS 3200)

49-90-00-600-005-A

Oil Change (Drain Procedure) (APS 3200)

49-90-00-600-005-A-01

Oil Change (Top-Off Procedure) (APS 3200)

49-90-00-600-005-A-02

Brand/Type Oil Change (Flush Procedure) (APS 3200)

AES

24-23-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE ** On A/C 003-005

DESIGNATION

49-90-00-600-007-A

Check Oil Level and Replenish (131-9(A))

49-90-00-600-008-A

Oil Change (Drain Procedure) (131-9(A))

49-90-00-600-008-A-01

Oil Change (Top-Off Procedure) (131-9(A))

49-90-00-600-008-A-02

Brand/Type Oil Change (Flush Procedure) (131-(A))

49-91-41-200-002-A

Remove and Discard Oil Filter Elements (131-9(A))

** On A/C 006-099 49-91-41-920-001-A

Discard Pressure Oil Filter Element (APS 3200)

49-91-41-920-002-A

Replace AC-Generator Scavenge Filter-Element (APS 3200)

52-41-00-010-001-A

Open the APU Doors for Access

(Ref. Fig. 24-23-51-991-00500-B - APU Generator 8XS) (Ref. Fig. 24-23-51-991-00600-B - APU Generator Hoist) 3.

Job Set-up ** On A/C ALL Subtask 24-23-51-860-052-A A.

Aircraft Maintenance Configuration (1)

On the panel 25VU, make sure that the APU MASTER SW pushbutton switch is off.

(2)

Put a WARNING NOTICE(S) in the cockpit to tell persons not to start the APU.

(3)

Make sure that ground fire extinguishing equipment is available.

(4)

Make sure that hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001-A).

Subtask 24-23-51-865-058-A B.

Open, safety and tag this(these) circuit breaker(s):

121VU

PANEL

DESIGNATION APU/APU/CTL

2KD

FIN L42

LOCATION

121VU

APU/ECB/SPLY

1KD

L41

Subtask 24-23-51-010-053-A C.

4.

Get Access (1)

Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the APU access doors 315AL and 316AR.

(2)

Open the APU access doors 315AL and 316AR (Ref. TASK 52-41-00-010-001-A).

Procedure (Ref. Fig. 24-23-51-991-00500-B - APU Generator 8XS) (Ref. Fig. 24-23-51-991-00600-B - APU Generator Hoist) Subtask 24-23-51-020-052-A A.

Removal of the APU Generator WARNING : OBEY THE HOISTING SAFETY PROCEDURES.

AES

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Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL MAKE SURE THAT THE HOIST IS ASSEMBLED AND ATTACHED CORRECTLY BEFORE YOU PUT A LOAD ON IT. OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THE HOIST. IF THE HOIST IS IN AN INCORRECT CONDITION THE LOAD CAN MOVE ACCIDENTALLY AND KILL PERSONS OR CAUSE INJURY. WARNING : DO NOT CAUSE DAMAGE TO THE THREADS OF THE SET SCREWS WHEN YOU REMOVE OR INSTALL THE GENERATOR. THE GENERATOR WEIGHS APPROXIMATELY 23kg (50.7lb). (1)

Disconnect the electrical connector (12) from the APU generator (4).

(2)

Put blanking caps on the disconnected electrical connector(s).

(3)

Remove the screws (17), the washers (16) and the cover plate (18).

(4)

Remove the nuts (19), the four electrical cables (20) and the washers (21). NOTE :

Remember that washers (21) are not installed on a model of APU Generator.

(5)

Put a CONTAINER 3 L(3/4 USGAL) below the generator (4) to collect the oil which will flow when you remove the drain plug (14).

(6)

Remove the drain plug (14). Take care to collect the drained oil in the container.

(7)

Remove and discard the sealwasher (13) from the drain plug (14).

(8)

Install the lifting eye (23) to the lifting boss of the generator (4). NOTE :

(9)

Make sure that the threads of the lifting eye (23) and the generator-lifting boss are in correct condition. Use the drained oil to lubricate the thread of the lifting eye (23).

Install the HOIST-MINILIFT (A1-91-265) to the APU generator hoist-bracket (21) with the quickrelease pin (22).

(10) Install the shackle with the quick-release pin (25) to the generator lifting-eye (23). (11) Operate the HOIST-MINILIFT (A1-91-265) until its cable (24) has a sufficient tension. (12) Loosen the bolts CAUTION :

(a)

BE CAREFUL WHEN YOU REMOVE THE NUTS. A SPANNER CAN EASILY CAUSE DAMAGE TO THE ADJACENT WEBS OF THE GENERATOR HOUSING.

Make sure that the HOIST-MINILIFT (A1-91-265) holds the weight of the generator (4) and loosen the bolts (15) until the generator can be rotated.

(13) Turn the generator CAUTION :

(a)

BE CAREFUL WHEN YOU TURN THE GENERATOR. TOOLS THAT YOU USE TO HELP YOU MOVE THE APU GENERATOR CAN EASILY CAUSE DAMAGE TO THE HOUSING. DO NOT APPLY FORCE TO THE WEBS AT THE MAIN FLANGE.

Turn the generator (4) counterclockwise and withdraw it from the gear-box splined drive.

(14) Lower the generator from the APU compartment and disconnect the shackle from the lifting eye (23). (15) Remove the lifting eye (23). (16) Remove and discard the O-rings (9) and (10). (17) Remove the countersunk screws (1) and the seal plate (7), if a new generator must be installed.

AES

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Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-23-51-210-060-A B.

Replacement and check of the APU Oil Filters . for APU GTCP 36-300 (Ref. AMM 49-91-45-200-003) . . for APU APS3200

.

** On A/C 006-099 (Ref. TASK 49-91-41-920-001-A) and (Ref. TASK 49-91-41-920-002-A). for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-91-41-200-002-A).

** On A/C ALL Subtask 24-23-51-612-051-A C.

Draining and check of the oil: (1)

Drain the oil: . for APU GTCP 36-300 (Ref. AMM 49-90-00-600-002) . for APU APS3200

.

** On A/C 006-099 (Ref. TASK 49-90-00-600-005-A) or (Ref. TASK 49-90-00-600-005-A-01) or (Ref. TASK 49-90-00-600-005-A-02) for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-90-00-600-008-A)(Ref. TASK 49-90-00-600-008-A-01)(Ref. TASK 49-90-00-600-008-A-02)

(2)

Fill the APU reservoir: . for APU GTCP 36-300 (Ref. AMM 49-90-00-600-001) . . for APU APS3200

.

** On A/C 006-099 (Ref. TASK 49-90-00-600-004-A). for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-90-00-600-007-A).

AES

24-23-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR80 FR84

12

A 8XS

C A B 316AR 315AL

4

13

C

14 15

17

B

18 16

3 19 21

1

20

5

4

6 7 4095KM

10 9

1 N_MM_242351_4_LEM0_01_00

AES

FIGURE 24-23-51-991-00500-B SHEET 1 APU Generator 8XS

24-23-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR80

A

FR84

A 22 8XS 21

316AR

23

315AL

24

25

23

4

N_MM_242351_4_LGM0_01_00

AES

FIGURE 24-23-51-991-00600-B SHEET 1 APU Generator Hoist

24-23-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-23-51-400-001-A Installation of the APU Generator WARNING : BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS AND YOUR LOCAL REGULATIONS. FIN 8XS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY

DESIGNATION Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

98D49207537001 FRDH141

1 1

CABLE-SAFETY, APU GENERATOR ADAPTER-TORQUE

B.

Consumable Materials

REFERENCE Material No: 03-002 Material No: 07-020 Material No: 11-026 C.

DESIGNATION OILS LUBRICATING OIL TURBINE ENGINE SYNT BASE LACQUERS IDENTIFICATION PAINT CLEANING AGENTS SOLVENT GENERAL PURPOSE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

315AL, 316AR D.

Expendable Parts

FIG.ITEM 7 9 10 13

DESIGNATION

IPC-CSN 24-23-04-01-040 24-23-51-01-010 24-23-51-01-020 24-23-51-01-040

seal plate seal packing sealwasher E.

Referenced Information

REFERENCE 20-21-11-911-001-A

DESIGNATION Tightening Torques for Standard Threaded Fasteners

29-00-00-864-001-A

Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action

** On A/C 006-099 49-00-00-860-005-A

APU Start by External Power

49-00-00-860-005-A-01

APU Start by Batteries

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 49-00-00-860-006-A

DESIGNATION APU Shutdown by External Power

49-00-00-860-006-A-01

APU Shutdown by Batteries

** On A/C 003-005 49-00-00-860-008-A

APU Start by External Power

49-00-00-860-008-A-01

APU Start by Batteries

49-00-00-860-009-A

APU Shutdown by External Power (131-9(A))

49-00-00-860-009-A-01

APU Shutdown by Batteries (131-9(A))

** On A/C 006-099 49-90-00-600-004-A

Check Oil Level and Replenish (APS 3200)

** On A/C 003-005 49-90-00-600-007-A

Check Oil Level and Replenish (131-9(A))

52-41-00-010-001-A Open the APU Doors for Access 52-41-00-410-001-A Close the APU Doors after Access (Ref. Fig. 24-23-51-991-00100-B - APU Generator 8XS) 3.

Job Set-up ** On A/C ALL Subtask 24-23-51-860-051-A A.

4.

Aircraft Maintenance Configuration (1)

On the panel 25VU make sure that the APU MASTER SW pushbutton switch is off.

(2)

Make sure that there is a warning notice in the cockpit to tell persons not to start the APU.

(3)

Make sure that hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001-A).

(4)

Make sure that ground fire extinguishing equipment is available.

(5)

Make sure that the access platform is in position below the APU compartment.

(6)

Make sure that the APU access doors are open (Ref. TASK 52-41-00-010-001-A).

(7)

Put an CABLE-SAFETY, APU GENERATOR (98D49207537001) on the generator to get a safe condition when you install the generator.

Procedure (Ref. Fig. 24-23-51-991-00100-B - APU Generator 8XS) Subtask 24-23-51-420-050-A A.

Installation of the APU Generator (1)

Examine the (IPC-CSN 24-23-04-01) seal plate (7) and the seal (8) and (11), which are part of the seal plate (7).

(2)

Replace the seal plate (7) if you find: . breaks and/or scratches on the seal plate (7), . cuts on the seals (8) and/or (11), . the height of the seals (8) and/or (11) above the seal plate (7) is less then 0.25 mm (0.0098 in.). (a)

AES

Remove the countersunk screws (1) and the seal plate (7).

24-23-51 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b)

Lubricate the seals (8) and (11) of the new seal plate (7) with a thin layer of OILS (Material No: 03-002) .

(c)

Position the seal plate (7) with the seal (8) for the oil scavenge port in the 6 o’clock position on the flange of the APU generator (4). NOTE :

Make sure that the dowel pin (3) engages correctly with the pilot hole (2).

(d)

Lubricate the countersunk screws (1) with OILS (Material No: 03-002) .

(e)

Install the countersunk screws (1) and TORQUE to between 0.43 and 0.47 M.DAN (38.05 and 41.59 LBF.IN).

(3)

Lubricate the new (IPC-CSN 24-23-51-01) packing (10) and the new (IPC-CSN 24-23-51-01) seal (9) with a thin layer of OILS (Material No: 03-002)

(4)

Install the new seal (10) on the generator splined drive shaft.

(5)

Install the new preformed packing (9) on the generator mount flange.

(6)

Install the generator (4) over the nuts (15) and turn it clockwise to engage the slots.

(7)

Make sure that the dowel pin (3) fully engages in the mounting flange of the accessory drive gearbox.

(8)

TORQUE the nuts (15) to between 2.6 and 3.0 M.DAN (19.17 and 22.12 LBF.FT).

(9)

TORQUE the nuts (15) behind the generator terminal with an ADAPTER-TORQUE (FRDH141) (Ref. TASK 20-21-11-911-001-A).

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. (10) Clean the nuts of the APU generator with CLEANING AGENTS (Material No: 11-026) . (11) Mark the tightened generator nuts with LACQUERS (Material No: 07-020) . (12) Remove the blanking caps from the electrical connectors. (13) Connect the electrical connector (12) to the APU generator (4). NOTE :

CAUTION :

Make sure that you connect the electrical cable connections correctly to the APU generator terminal. MAKE SURE THAT THE WASHER IS INSTALLED BETWEEN THE PHASE LEADS AND THE TERMINAL NUT. IF NOT, THE TERMINAL BLOCK WILL BURN LOCALLY BECAUSE OF RESISTANCE HEATING.

(14) Connect the electrical cables (20) with the washers (21) and the nuts (19) to the APU generator (4) as follows: . cable 8XS-T1 to generator terminal T1, . cable 8XS-T2 to generator terminal T2, . cable 8XS-T3 to generator terminal T3, . cable 8XS- N to generator terminal N.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL NOTE :

Remember that washers (21) are not installed on a model of APU Generator.

(15) TORQUE the nuts (19) to between 2.3 and 2.49 M.DAN (16.96 and 18.36 LBF.FT). (16) Install the cover plate (18) with the washers (16) and the screws (17). (17) TORQUE the screws (17) to between 0.43 and 0.47 M.DAN (38.05 and 41.59 LBF.IN). (18) Install the drain plug (14) with a new (IPC-CSN 24-23-51-01) sealwasher (13) . (19) TORQUE the drain plug (14) to between 2.95 and 3.25 M.DAN (21.76 and 23.97 LBF.FT). Subtask 24-23-51-210-051-A B.

Visual Check CAUTION :

(1)

USE ONLY APPROVED TYPES/BRANDS OF LUBRICANTS. DO NOT MIX TYPES//BRANDS OF LUBRICANTS.

Do a visual check of the oil quantity on the APU oil level. Add oil if the oil level is on or less than the ADD mark on the sight glass . for APU GTCP 36-300 (Ref. AMM 49-90-00-600-001) . for APU APS 3200

.

** On A/C 006-099 (Ref. TASK 49-90-00-600-004-A) for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-90-00-600-007-A)

** On A/C ALL Subtask 24-23-51-865-053-A C.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

121VU

DESIGNATION APU/APU/CTL

FIN

LOCATION

2KD

L42

121VU

APU/ECB/SPLY

1KD

L41

Subtask 24-23-51-710-050-A D.

Start and Operate the APU (1)

Start the APU . for APU GTCP 36-300 (Ref. AMM 49-00-00-860-003) . for APU APS 3200

.

** On A/C 006-099 (Ref. TASK 49-00-00-860-005-A) or (Ref. TASK 49-00-00-860-005-A-01) for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-00-00-860-008-A)(Ref. TASK 49-00-00-860-008-A-01)

AES

24-23-51 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Allows the APU to run 15 minutes.

(3)

Check at 95 % speed of the APU that the generator energizes and begins to indicate voltage and frequency (without the selection of electrical loads).

(4)

An ’AVAIL’ message on top of the APU page shows that you can select an electric/pneumatic load.

(5)

Shutdown the APU . for APU GTCP 36-300 (Ref. AMM 49-00-00-860-004) . for APU APS 3200

.

** On A/C 006-099 (Ref. TASK 49-00-00-860-006-A) or (Ref. TASK 49-00-00-860-006-A-01) for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-00-00-860-009-A)(Ref. TASK 49-00-00-860-009-A-01)

(6)

Open the APU access doors ** On A/C ALL (Ref. TASK 52-41-00-010-001-A).

(7)

Do a leak check of the APU Oil System. NOTE :

5.

No leaks are permitted.

Close-up Subtask 24-23-51-410-051-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the APU access doors 315AL 316AR (Ref. TASK 52-41-00-410-001-A).

(3)

Remove the access platform(s).

(4)

Remove the warning notice(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-23-51-400-001-A-01 Installation of the APU Generator with the Minilift Hoist WARNING : BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS AND YOUR LOCAL REGULATIONS. FIN 8XS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY

DESIGNATION Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

A1-91-265 FRDH141

1 1

HOIST-MINILIFT ADAPTER-TORQUE

B.

Consumable Materials

REFERENCE Material No: 03-002 Material No: 07-016 Material No: 11-026 C.

DESIGNATION OILS LUBRICATING OIL TURBINE ENGINE SYNT BASE LACQUERS PROTECTING LACQUER CLEANING AGENTS SOLVENT GENERAL PURPOSE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

315AL, 316AR D.

Expendable Parts

FIG.ITEM 7 13

DESIGNATION

IPC-CSN 24-23-04-01-040 24-23-51-01-040

seal plate sealwasher E.

Referenced Information

REFERENCE 20-21-11-911-001-A

DESIGNATION Tightening Torques for Standard Threaded Fasteners

29-00-00-864-001-A

Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action

** On A/C 006-099 49-00-00-860-005-A

APU Start by External Power

49-00-00-860-005-A-01

APU Start by Batteries

49-00-00-860-006-A

APU Shutdown by External Power

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 49-00-00-860-006-A-01

DESIGNATION APU Shutdown by Batteries

** On A/C 003-005 49-00-00-860-008-A

APU Start by External Power

49-00-00-860-008-A-01

APU Start by Batteries

49-00-00-860-009-A

APU Shutdown by External Power (131-9(A))

49-00-00-860-009-A-01

APU Shutdown by Batteries (131-9(A))

** On A/C 006-099 49-90-00-600-004-A

Check Oil Level and Replenish (APS 3200)

** On A/C 003-005 49-90-00-600-007-A

Check Oil Level and Replenish (131-9(A))

52-41-00-010-001-A

Open the APU Doors for Access

52-41-00-410-001-A Close the APU Doors after Access (Ref. Fig. 24-23-51-991-00500-B - APU Generator 8XS) (Ref. Fig. 24-23-51-991-00600-B - APU Generator Hoist) 3.

Job Set-up ** On A/C ALL Subtask 24-23-51-860-053-A A.

4.

Aircraft Maintenance Configuration (1)

On the panel 25VU make sure that the APU MASTER SW pushbutton switch is off.

(2)

Make sure that there is a warning notice in the cockpit to tell persons not to start the APU.

(3)

Make sure that hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001-A).

(4)

Make sure that ground fire extinguishing equipment is available.

(5)

Make sure that the access platform is in position below the APU compartment.

(6)

Make sure that the APU access doors are open (Ref. TASK 52-41-00-010-001-A).

(7)

Make sure that the HOIST-MINILIFT (A1-91-265) is installed correctly in the APU generator hoist bracket.

Procedure (Ref. Fig. 24-23-51-991-00500-B - APU Generator 8XS) (Ref. Fig. 24-23-51-991-00600-B - APU Generator Hoist) Subtask 24-23-51-420-053-A A.

Installation of the APU Generator WARNING : OBEY THE HOISTING SAFETY PROCEDURES. MAKE SURE THAT THE HOIST IS ASSEMBLED AND ATTACHED CORRECTLY BEFORE YOU PUT A LOAD ON IT. OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THE HOIST. IF THE HOIST IS IN AN INCORRECT CONDITION THE LOAD CAN MOVE ACCIDENTALLY AND KILL PERSONS OR CAUSE INJURY.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL WARNING : DO NOT CAUSE DAMAGE TO THE THREADS OF THE SET SCREWS WHEN YOU REMOVE OR INSTALL THE GENERATOR. THE GENERATOR WEIGHS APPROXIMATELY 23kg (50.7lb). (1)

Replace the (IPC-CSN 24-23-04-01) seal plate (7) if it is necessary. The seal plate (7) is attached with two countersunk screws (1) to the generator flange.

(2)

Replace the seal plate (7) if you find: . breaks and/or scratches on the seal plate (7), . cuts on the seals (8) and/or (11), . the height of the seals (8) and/or (11) above the seal plate (7) is less than 0.25 mm (0.0098 in.). (a)

Remove the countersunk screws (1) and the seal plate (7).

(b)

Lubricate the seals (8) and (11) of the new seal plate (7) with a thin layer of OILS (Material No: 03-002) .

(c)

Position the seal plate (7) with the seal (8) for the oil scavenge port in the 6 o’clock position on the flange of the APU generator (4). NOTE :

Make sure that the dowel pin (3) engages correctly with the pilot hole (2).

(d)

Lubricate the countersunk screws (1) with OILS (Material No: 03-002) .

(e)

Install the countersunk screws (1) and TORQUE to between 0.43 and 0.47 M.DAN (38.05 and 41.59 LBF.IN).

(3)

Install the new seal (10) on the generator splined-drive-shaft (6).

(4)

Install the new preformed packing (9) on the generator mount-flange (5).

(5)

Install the lifting eye (23) to the lifting boss of the generator (4). NOTE :

Make sure that the threads of the lifting eye (23) and the generator lifting boss are in good condition. Lubricate the thread of the lifting eye (23) with OILS (Material No: 03-002) .

(6)

Install the shackel with the quick-release pin (25) to the lifting eye (23).

(7)

Operate the HOIST-MINILIFT (A1-91-265) and lift the generator (4) in position to the generator mounting flange.

(8)

Lubricate the generator splined-drive-shaft (6) with OILS (Material No: 03-002) .

(9)

Install the generator (4) over the nuts (15) and turn it clockwise to engage the slots.

(10) Make sure that the dowel pin (3) fully engages in the mounting flange of the accessory drive gearbox. (11) TORQUE the nuts (15) to between 2.69 and 3.22 M.DAN (19.84 and 23.75 LBF.FT). (12) TORQUE the nuts (15) behind the generator terminal with an ADAPTER-TORQUE (FRDH141) (Ref. TASK 20-21-11-911-001-A). WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (13) Clean the nuts of the APU generator with CLEANING AGENTS (Material No: 11-026) . (14) Mark the tightened generator nuts with LACQUERS (Material No: 07-016) . (15) Remove the blanking caps from the electrical connectors. (16) Connect the electrical connector (12) to the APU generator (4). NOTE :

CAUTION :

Make sure that you connect the electrical cable connections correctly to the APU generator terminal. MAKE SURE THAT THE WASHER IS INSTALLED BETWEEN THE PHASE LEADS AND THE TERMINAL NUT. IF NOT, THE TERMINAL BLOCK WILL BURN LOCALLY BECAUSE OF RESISTANCE HEATING.

(17) Connect the electrical cables (20) with the washers (21) and the nuts (19) to the APU generator (4) as follows: . cable 8XS-T1 to generator terminal T1, . cable 8XS-T2 to generator terminal T2, . cable 8XS-T3 to generator terminal T3, . cable 8XS- N to generator terminal N. NOTE :

Remember that washers (21) are not installed on a model of APU Generator.

(18) TORQUE the nuts (19) to between 2.3 and 2.49 M.DAN (16.96 and 18.36 LBF.FT). (19) Install the cover plate (18) with the washers (16) and the screws (17). (20) TORQUE the screws (17) to between 0.43 and 0.47 M.DAN (38.05 and 41.59 LBF.IN). (21) Install the drain plug (14) with a new (IPC-CSN 24-23-51-01) sealwasher (13) . (22) TORQUE the drain plug (14) to between 2.95 and 3.25 M.DAN (21.76 and 23.97 LBF.FT). Subtask 24-23-51-210-058-A B.

Visual Check CAUTION :

(1)

USE ONLY APPROVED TYPES/BRANDS OF LUBRICANTS. DO NOT MIX TYPES//BRANDS OF LUBRICANTS.

Do a visual check of the oil quantity on the APU oil level. Add oil if the oil level is on or less than the ADD mark on the sight glass . for APU GTCP 36-300 (Ref. AMM 49-90-00-600-001) . for APU APS 3200

.

** On A/C 006-099 (Ref. TASK 49-90-00-600-004-A) for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-90-00-600-007-A)

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Subtask 24-23-51-865-059-A C.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

121VU

PANEL

DESIGNATION APU/APU/CTL

2KD

FIN L42

LOCATION

121VU

APU/ECB/SPLY

1KD

L41

Subtask 24-23-51-710-054-A D.

Start and Operate the APU (1)

Start the APU . for APU GTCP 36-300 (Ref. AMM 49-00-00-860-003) . for APU APS 3200

.

** On A/C 006-099 (Ref. TASK 49-00-00-860-005-A) or (Ref. TASK 49-00-00-860-005-A-01) for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-00-00-860-008-A)(Ref. TASK 49-00-00-860-008-A-01)

(2)

Allows the APU to run 15 minutes.

(3)

Check at 95 % speed of the APU that the generator energizes and begins to indicate voltage and frequency (without the selection of electrical loads).

(4)

An ’AVAIL’ message on top of the APU page shows that you can select an electric/pneumatic load.

(5)

Shutdown the APU . for APU GTCP 36-300 (Ref. AMM 49-00-00-860-004) . for APU APS 3200

.

** On A/C 006-099 (Ref. TASK 49-00-00-860-006-A) or (Ref. TASK 49-00-00-860-006-A-01) for APU 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-00-00-860-009-A)(Ref. TASK 49-00-00-860-009-A-01)

(6)

Open the APU access doors ** On A/C ALL (Ref. TASK 52-41-00-010-001-A).

(7)

Do a leak check of the APU Oil System. NOTE :

AES

No leaks are permitted.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-23-51-410-056-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the APU access doors 315AL 316AR (Ref. TASK 52-41-00-410-001-A).

(3)

Remove the access platform(s).

(4)

Remove the warning notice(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-23-55-000-001-A Removal of the APU GLC WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 3XS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 25-11-41-000-001-A

DESIGNATION Removal of the Third Occupant Seat

(Ref. Fig. 24-23-55-991-00100-A - Contactor) (Ref. Fig. 24-23-55-991-00100-B - Contactor) 3.

Job Set-up Subtask 24-23-55-860-050-A A.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Put warning notice(s) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

In the cockpit, put WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

Subtask 24-23-55-010-050-A B.

4.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

On the L lower side of the panel 120VU, remove the access door (8).

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Procedure

** On A/C 003-004 (Ref. Fig. 24-23-55-991-00100-A - Contactor) ** On A/C 005-099 (Ref. Fig. 24-23-55-991-00100-B - Contactor) ** On A/C ALL Subtask 24-23-55-020-050-A A.

Removal of the Contactor CAUTION :

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

(1)

Disconnect the electrical connector (1).

(2)

Put CAP - BLANKING on the disconnected electrical connector (1) and the electrical receptacle (7).

(3)

Loosen the captive screws (2). NOTE :

(4)

Do not remove the captive screws (2) and the spring washers (4) from the contactor (3).

Remove the contactor (3).

** On A/C 003-004 Subtask 24-23-55-020-051-A CAUTION :

B.

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Removal of the Contactor Base NOTE : (1)

AES

The removal of the base is necessary only if the base is damaged.

If the base has the components that follow: (a)

Remove the screws (9) and the washers (10).

(b)

Disconnect the electrical wires (11).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Remove the nuts (12) and the washers (13).

(3)

Disconnect the cables (14) from the base (6).

(4)

Remove the nuts (15) and the washers (16).

(5)

Remove the jumpers (17) from the base (6) and from the adjacent bases.

(6)

Remove the four screws (19) and the four washers (18).

(7)

Remove the base (6).

** On A/C 005-099 Subtask 24-23-55-020-051-B CAUTION :

B.

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Removal of the Contactor Module NOTE : (1)

AES

The removal of the module is necessary only if the module is damaged.

If the module has the components that follow: (a)

Remove the screws (9) and the washers (10).

(b)

Disconnect the electrical wires (11).

(2)

Remove the nuts (12) and the washers (13).

(3)

Disconnect the cables (14) from the module (5).

(4)

Remove the nuts (19) and the washers (18).

(5)

Remove the jumpers (17) from the module (5) and from the adjacent modules.

(6)

Remove the eight screws (16) and the eight washers (15).

(7)

Remove the module (5).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

A B

122VU

120VU

3XS

121VU

125VU

124VU 123VU

8

A

16

17

15

B 14 5

13

11 12

6

10 3

9

2 CONTACTOR BASE

CONTACTOR 18 19

7 1 N_MM_242355_4_AAM0_01_00

AES

FIGURE 24-23-55-991-00100-A SHEET 1 Contactor

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

B

A 120VU

122VU 3XS 121VU 29XN

125VU

124VU 123VU

8

B

14 13

A

11

12

10 9 3

2 17

CONTACTOR 18 7 19 5 1

MODULE

CONTACTOR

1

7

15 16 N_MM_242355_4_AAP0_01_00

AES

FIGURE 24-23-55-991-00100-B SHEET 1 Contactor

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-23-55-400-001-A Installation of the APU GLC WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 3XS 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific

B.

QTY AR WARNING NOTICE(S)

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

DESIGNATION

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 20-21-15-912-001-A

DESIGNATION Tightening Torques for Electrical Component Fasteners

24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-11-41-000-001-A

Removal of the Third Occupant Seat

25-11-41-400-001-A 31-60-00-860-001-A 31-60-00-860-002-A

Installation of the Third Occupant Seat EIS Start Procedure EIS Stop Procedure

(Ref. Fig. 24-23-55-991-00100-A - Contactor) (Ref. Fig. 24-23-55-991-00100-B - Contactor) 3.

Job Set-up Subtask 24-23-55-860-051-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Make sure that the warning notice(s) are in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

(4)

In the cockpit, make sure that the WARNING NOTICE(S) are in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

Subtask 24-23-55-010-051-A B.

4.

Get Access (1)

Make sure that the Third Occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(2)

On the L lower side of the panel 120VU, make sure that the access door (8) is removed.

(3)

Make sure that the access platform is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

Procedure

** On A/C 003-004 (Ref. Fig. 24-23-55-991-00100-A - Contactor) ** On A/C 005-099 (Ref. Fig. 24-23-55-991-00100-B - Contactor) ** On A/C 003-004 Subtask 24-23-55-420-051-A A.

Installation of the Contactor Base CAUTION :

AES

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Install the contactor base (6) in correct position.

(2)

Install the four screws (19) and washers (18) and tighten them.

(3)

Make sure that the electrical cables (14) are clean and in correct condition.

(4)

Install the cables (14).

(5)

Install the nuts (12) and the washers (13) and tighten them.

(6)

If the base has the components that follow: (a)

Install the three electrical wires (11).

(b)

Install the screws (10) and the washers (9) and tighten them.

(7)

Install the jumpers (17) between the base (6) and the adjacent bases.

(8)

Install the washers (15) and the nuts (16) and tighten them (Ref. TASK 20-21-15-912-001-A).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-23-55-420-050-A B.

Installation of the Contactor (1)

Install the contactor (3) on the 6 tapped barrels (5) of the contactor base (6).

(2)

TORQUE the captive screws (2) to between 0.50 and 0.60 M.DAN (44.25 and 53.10 LBF.IN).

(3)

Remove the blanking caps from the electrical connector (1) and the electrical receptacle (7).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (1).

** On A/C 005-099 Subtask 24-23-55-420-051-B A.

Installation of the Contactor Module CAUTION :

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Install the contactor module (5) in correct position.

(2)

Install the eight screws (16) and washers (15) and tighten them.

(3)

Make sure that the electrical cables (14) are clean and in correct condition.

(4)

Install the cables (14).

(5)

Install the nuts (13) and the washers (12) and tighten them.

(6)

If the base has the components that follow: (a)

Install the electrical wires (11).

(b)

Install the screws (10) and the washers (9) and tighten them.

(7)

Install the jumpers (17) between the module (5) and the adjacent modules.

(8)

Install the washers (19) and the nuts (18) and tighten them (Ref. TASK 20-21-15-912-001-A).

Subtask 24-23-55-420-050-B B.

Installation of the Contactor (1)

Install the contactor (3) on the module 29XN (5).

(2)

TORQUE the captive screws (2) to between 0.50 and 0.60 M.DAN (44.25 and 53.10 LBF.IN).

(3)

Remove the blanking caps from the electrical connector (1) and the electrical receptacle (7).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (1) to the contactor (3).

** On A/C ALL Subtask 24-23-55-710-050-A C.

AES

Test of the Contactor (1)

Energize the aircraft electrical circuits from the APU (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

On the ECAM control panel, push the ELEC key to get the ELEC system page.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

5.

(4)

On the lower ECAM display unit, make sure that the A/C electrical configuration is correct.

(5)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A)

(6)

De-energize the aircraft electrical circuits supplied from the APU (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Close-up Subtask 24-23-55-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the access door (8) on the L lower side of the panel 120VU.

(3)

Install the Tthird Ooccupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC EMERGENCY GENERATION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The AC emergency generation enables part of the distribution network to be recovered in case of: . loss of the two main generation sources and, . unavailability of the auxiliary generation.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-24-00-12300-B - AC Emergency Generation - Component Location) (Ref. Fig. 24-24-00-12400-A - AC Emergency Generation - Component Location) (Ref. Fig. 24-24-00-12500-A - AC Emergency Generation - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS ATA REF. DOOR 125 24-24-34

1XE

CONTROL UNIT-CSM/G

2XE 8XE

GLC-EMER CSM/G

106VU

125 148

24-24-55 24-24-51

14XE

ANN-EMER ELEC PWR/RAT/&/EMER GEN

21VU

211

24-24-00

15XE 23XE

106VU 21VU

125 211

24-24-55 24-24-00

24XE

CNTOR-AC ESS BUS SWITCHING P/BSW-EMER ELEC PWR/EMER GEN TEST P/BSW-EMER ELEC PWR/MAN ON

21VU

211

24-24-00

33XE

TIMER

106VU

125

24-24-00

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description

** On A/C 003-004 (Ref. Fig. 24-24-00-13900-C - Electrical Emergency Generating System - Schematic) ** On A/C 005-099 (Ref. Fig. 24-24-00-13900-D - Electrical Emergency Generating System - Schematic)

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Component Description The emergency generation system is mainly composed of: . a Constant Speed Motor/Generator (CSM/G) including a hydraulic motor and an AC generator, . a Generator Control Unit (GCU). A hydraulic motor drives the emergency generator. A servo valve speed regulator controls the speed: it transforms the oil flow of the Blue hydraulic system into constant speed for the generator. When emergency conditions are met, this Blue system is supplied by a Ram Air Turbine (RAT). NOTE : A.

The Blue hydraulic system is supplied by an electric pump in normal configuration.

Constant Speed Motor/Generator 8XE (1) Hydraulic motor: . Powered by the Blue hydraulic circuit (RAT in emergency configuration; electrical hydraulic pump in test), . speed regulation by servovalve, . integrated solenoid control valve. (2) AC . . .

generator: Three phase 115V/200V - 400 Hz (12000 rpm), output power: 5 KVA continuously, oil cooled.

B.

Generator Control Unit The GCU main functions are: . to control the servo-valve excitation for speed regulation, . to regulate the generator voltage by the field current, . to protect the network and the generator by controlling the associated line contactor and generator field current. ------------------------------------------------------------------------------CONTROLS/PROTECTIONS OF GCU ! TIME DELAY ! EFFECTS ------------------------------------------------------------------------------- Over/Under Voltage (OV/UV) ! 3-5 s ! Line contactor opens, generator - Over Frequency (OF) ! 3-5 s ! de-energization and control - Under Frequency (UF) ! 300 ms ! valve close (FAULT warning on, - Shorted PMG ! 3-5 s ! RAT & EMER GEN warning light). - Fast overspeed shutdown ! 150 ms !

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 5.

Operation A.

Control and Indicating Circuits (1) Emergency generator switching (Ref. Fig. 24-24-00-17000-D - Electrical Emergency Switching - Schematic) (Ref. Fig. 24-24-00-17100-C - EMER & AC ESS BUS Contactors Control - Logic Diagram) The emergency generator is switched through: . contactor 2XE (emergency generator line contactor or EMER GLC), and . contactor 15XE (AC ESS BUS contactor). . timer 33XE, it avoids the closure of the contactor 15XE in case of an electric transfer and close this contactor 15XE only in emergency configuration. The emergency generator has priority over its network and supplies the essential busbars (4XP, 8XP, 4PP, 8PP). Supply to the line contactor (EMER GLC) only depends on the availability of the emergency generator. Supply of section 1 of contactor 15XE depends on several conditions: . the availability of the emergency generator, . the failure of one of the 2 normal TR’s (TR 1 or TR 2), . the failure of the DC ESS BUS SUPPLY and/or DC NORM BUS 1 switching contactors (4PC/1PC1). ** On A/C 003-004 (2) RAT extension logic and CSM/G control logic (Ref. Fig. 24-24-00-17200-D - RAT Extension Logic & CSM/G Control Logic - Schematic) (a) RAT extension logic 3 different logics control RAT extension: . the automatic electrical logic: this energizes solenoid N˚.1 when there is loss of voltage at busbars 1XP and 2XP and speed V > 100 kts, . the manual electrical logic: this energizes solenoid No. 2 directly, via OVRD ELEC pushbutton switch, . the manual hydraulic logic: this energizes solenoid No. 1 directly, via OVRD HYD pushbutton switch. (b) CSM/G control logic 3 different logics control energization of the emergency generation: . the automatic electrical logic: this is identical to that of the RAT extension, in the landing gear retracted configuration, . the manual electrical logic: this is identical to that of the RAT extension, in the landing gear retracted configuration, . the electrical test logic: this simulates the automatic electrical logic because it allows the emergency generator to be coupled to the Blue hydraulic system (supplied by the hydraulic electric pump) while inhibiting RAT extension. ** On A/C 005-099 (3) RAT extension logic and CSM/G control logic (Ref. Fig. 24-24-00-17200-E - RAT Extension Logic and CSM/G Control Logic - Schematic) (a) RAT extension logic 3 different logics control RAT extension: . the automatic electrical logic: this energizes solenoid N˚.1 when there is loss of voltage at busbars 1XP and 2XP and speed V > 100 kts, . the manual electrical logic: this energizes solenoid No. 2 directly, via OVRD ELEC pushbutton switch,

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL .

the manual hydraulic logic: this energizes solenoid No. 1 directly, via OVRD HYD pushbutton switch.

(b) CSM/G control logic 3 different logics control energization of the emergency generation: . the automatic electrical logic: this is identical to that of the RAT extension, . the manual electrical logic: this is identical to that of the RAT extension, . the electrical test logic: this simulates the automatic electrical logic because it allows the emergency generator to be coupled to the Blue hydraulic system (supplied by the hydraulic electric pump) while inhibiting RAT extension. ** On A/C ALL (4) Controls and indications in the cockpit

** On A/C 003-004 (Ref. Fig. 24-24-00-17400-G - Electrical Emergency Generation System - Control System) ** On A/C 005-099 (Ref. Fig. 24-24-00-17400-F - Electrical Emergency Generation System - Control System) (a) The RAT and CSM/G are: . automatically controlled by AC BUS 1 and AC BUS 2 loss and V > 100 kts, . or manually by means of the EMER ELEC PWR/MAN ON guarded pushbutton switch on the EMER ELEC PWR section of the overhead panel 21VU. When a failure of the AC BUS 1 and 2 occurs, simultaneously: . the RAT is automatically extended, . the emergency generator is automatically coupled to AC and DC ESS busbars, . the red FAULT legend comes on on RAT & EMER GEN annunciator until the emergency generator is available. In all cases, the pilot has to press EMER ELEC PWR/MAN ON pushbutton switch in order to confirm the automatic logic. Red FAULT legend disappears if coupling is obtained. (b) A test of the emergency generator can be initiated on the ground. The procedure is controlled by the EMER GEN TEST pushbutton switch located on the EMER ELEC PWR section of overhead panel 21VU. When EMER GEN TEST pushbutton switch is pressed and held: . ELEC page is automatically displayed on the ECAM system (on ground only), . the emergency generator is coupled to its network, . DC ESS BUS SPLY and AC ESS BUS switching line contactors (4PC/3XC) open, isolating AC and DC essential busses, . on the ECAM system: green lines between normal busbars and essential busbar disappear. The white EMER GEN, ESS TR and the green indications of the corresponding parameters appear, green lines between EMER GEN and AC ESS and DC ESS appear. NOTE :

The ELEC page must disappear when the EMER GEN TEST pushbutton switch is released.

(c) A test of the emergency GCU can be initiated on the ground from the CFDS. The emergency GCU is a type 3 system: i.e. it has neither an input bus nor an output bus, it is connected to CFDIU by 2 discrete links. The test procedure is described in ** On A/C ALL (Ref. Fig. 24-24-00-17600-B - Test Procedure for GCU EMER by MCDU)

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL B.

Electrical Emergency Configuration NOTE :

For more data, REF.31-67-24.

** On A/C 003-004 (Ref. Fig. 24-24-00-18000-B - Electrical Emergency Configuration - Upper and Lower ECAM Display Unit) ** On A/C 005-099 (Ref. Fig. 24-24-00-18000-C - Electrical Emergency Configuration - Upper and Lower ECAM Display Unit) ** On A/C 003-004 (1) Electrical emergency configuration during RAT extension (<10 sec) and in landing gear extended configuration (Ref. Fig. 24-24-00-18200-B - ELectrical Emergency Configuration During RAT Deployment and in Landing Gear Extented Configuration) This configuration is the result either of the RAT extension phase or of the activation of the CSM/G interlock logic when the landing gear is extended during an emergency configuration. In this case the CSM/G is switched off through a logic controlled by LGCIU-1. No power source (GEN 1, GEN 2, APU GEN, EXT PWR, EMER GEN) being available, static inverter, busbars 4XP and 901XP are supplied by battery 1 and busbar 4PP by battery 2 via static inverter through contactor 2XB. NOTE :

1 In landing gear extended configuration, at go around, the emergency generator can be restored to the on-line status by opening the circuit breaker associated with LGCIU 1 and pressing MAN ON pushbutton switch located on the EMER ELEC PWR section of overhead panel 21VU.

NOTE :

2 If in landing gear extented configuration, the crew must retract the landing gear, it is necessary to press MAN ON pushbutton switch on the EMER ELEC PWR section of panel 21VU to restore the emergency generator to the on line status.

(Ref. Fig. 24-24-00-18300-A - ESS BUSES ON BAT - Upper and Lower ECAM Display Unit) ** On A/C 005-099 (2) Electrical emergency configuration during RAT extension (<10 sec) and after landing configuration (Ref. Fig. 24-24-00-18200-B - ELectrical Emergency Configuration During RAT Deployment and in Landing Gear Extented Configuration) This configuration is the result either of the RAT extension phase or of the CSM/G shutdown after landing in emergency configuration. The CSM/G can be switched off by the priority valve closure due to a blue hydraulic pressure drop. Nevertheless, the CSM/G is switched off through a logic controlled by both ADIRU1 (A/C speed < 100 Knots) and LGCIU1 5GA1 (main landing gear compressed). No power source (GEN 1, GEN 2, APU GEN, EXT PWR, EMER GEN) being available, (static inverter) busbars 4XP and 901XP are supplied by battery 1 and busbar 4PP by battery 2 via static inverter through contactor 2XB. (Ref. Fig. 24-24-00-18300-A - ESS BUSES ON BAT - Upper and Lower ECAM Display Unit) NOTE :

AES

At go around, the emergency generator can be restored to the on-line status by pressing MAN ON pushbutton switch located on the EMER ELEC PWR section of overhead panel 21VU.

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Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL (3) Electrical emergency configuration with CSM/G running (Ref. Fig. 24-24-00-18500-B - Electrical Emergency Configuration with CSM/G Running) (4) Electrical Emergency Configuration on the ground, with speed < 50 kts. (Ref. Fig. 24-24-00-18700-B - Electrical Emergency Configuration on the Ground with speed < 50kts) In this configuration, busbar 4XP is shed. Battery 1 supplies busbar 901XP via the static inverter. Battery 2 supplies busbar 4PP. NOTE :

At A/C speed approximately equal to 100 Knots, the BCL’s control the closure of battery contactors 6PB1 and 6PB2. So that the supply of static inverter contactor 2XB depends on the position of battery contactors.

NOTE :

A list of available functions in emergency configuration is shown in the following figures:

** On A/C 003-004 (Ref. Fig. 24-24-00-18800-A - Available Functions in Emergency Configuration) ** On A/C 005-099 (Ref. Fig. 24-24-00-18800-B - Available Functions in Emergency Configuration) ** On A/C 003-004 (Ref. Fig. 24-24-00-18900-A - Available Functions in Emergency Configuration) ** On A/C 005-099 (Ref. Fig. 24-24-00-18900-B - Available Functions in Emergency Configuration) ** On A/C 003-004 (Ref. Fig. 24-24-00-19000-A - Available Functions in Emergency Configuration) ** On A/C 005-099 (Ref. Fig. 24-24-00-19000-B - Available Functions in Emergency Configuration) ** On A/C 003-004 (Ref. Fig. 24-24-00-19100-A - Available Functions in Emergency Configuration) ** On A/C 005-099 (Ref. Fig. 24-24-00-19100-B - Available Functions in Emergency Configuration) ** On A/C 003-004 (Ref. Fig. 24-24-00-19200-A - Available Functions in Emergency Configuration) ** On A/C 005-099 (Ref. Fig. 24-24-00-19200-B - Available Functions IN Emergency Configuration) ** On A/C 003-004 (Ref. Fig. 24-24-00-19300-C - Available Functions in Emergency Configuration) ** On A/C 005-099 (Ref. Fig. 24-24-00-19300-D - Available Functions in Emergency Configuration) ** On A/C ALL C.

Electrical Smoke Configuration (Ref. Fig. 24-24-00-19700-B - Smoke Detection - Upper and Lower ECAM Display Unit) (Ref. Fig. 24-24-00-19800-B - Electrical Smoke Configuration) This configuration is the same as the electrical emergency configuration.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL In addition, one fuel pump per wing is directly supplied by generator 1 upstream the generator line contactor 1 (GLC1). Description of smoke procedure: Smoke evacuation: . OXYGEN/MASK MAN ON pushbutton switch to ON, . VENTILATION/BLOWER and EXTRACT pushbutton switches to OVRD (open fully the conditioned air inlet valve and partially the skin air outlet valve), . VENTILATION/CAB FANS pushbutton switch to OFF (stops recirculation). If the smoke persists after 5mn: Smoke isolation: . EMER ELEC PWR/GEN 1 LINE pushbutton switch to OFF (opens GLC1), . EMER ELEC PWR/MAN ON pushbutton switch (RAT extension), . ELEC/APU GEN pushbutton switch to OFF, . ELEC/GEN 2 pushbutton switch to OFF (2 fuel pumps supplied by Gen 1 upstream GLC1). Before landing gear extension: . GEN 2 pushbutton switch to ON . GEN 1 LINE pushbutton switch to ON. NOTE :

If, in normal configuration, GEN 1 LINE pushbutton switch is released, the EMER GEN 1 LINE OFF message is displayed on the upper ECAM display unit.

D. Electrical Configuration in case of Failure of Both Engines ** On A/C 003-004 If both AC BUS 1 and AC BUS 2 buses are lost and the aircraft speed is above 100 knots, the Ram Air Turbine (RAT) extends automatically. This powers the Blue hydraulic system, which drives the CSM/G by means of a hydraulic motor. This CSM/G supplies the AC ESS BUS and the DC ESS BUS, via the essential transformer rectifier (ESS TR). When the landing gear is down, there is no sufficient power to operate the CSM/G and the emergency generation network is automatically transferred to the batteries and the static inverter. The system automatically sheds the AC SHED ESS buses and DC SHED ESS buses. When the aircraft is on the ground: . below 100 knots, the DC BAT BUS is automatically connected to the batteries . below 50 knots, the AC ESS BUS is automatically shed, which causes the loss of all CRTs. NOTE :

During RAT extension and CSM/G coupling (about 8 seconds), the batteries power the emergency generation network.

NOTE :

If only the batteries power the emergency generation network, APU start is only available on ground (speed below 100 knots).

** On A/C 005-099 If both AC BUS 1 and AC BUS 2 buses are lost and the aircraft speed is above 100 knots, the Ram Air Turbine (RAT) extends automatically. This powers the Blue hydraulic system, which drives the CSM/G by means of a hydraulic motor. This CSM/G supplies the AC ESS BUS and the DC ESS BUS, via the essential transformer rectifier (ESS TR). If the RAT stalls or if the aircraft is on the ground with the speed below 100 knots, there is no sufficient power to operate the CSM/G. The emergency generation network is automatically transferred to the batteries and the static inverter, and the system automatically sheds the AC SHED ESS buses and DC SHED ESS buses. When the aircraft is on the ground:

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . .

below 100 knots, the DC BAT BUS is automatically connected to the batteries below 50 knots, the AC ESS BUS is automatically shed, which causes the loss of all CRTs.

NOTE :

AES

During RAT extension and CSM/G coupling (about 8 seconds), the batteries power the emergency generation network.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A C

A

106VU

2XE 33XE 15XE

812 FR12

D

FR16

B

B

D

C

N_MM_242400_0_AAL0_01_00

AES

FIGURE 24-24-00-12300-B SHEET 1 AC Emergency Generation - Component Location

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

FR13

Z125 FR12

A B

1XE

B PANEL 21VU EMER GEN TEST BL

EMER ELEC PWR RAT & GEN 1 LINE EMER GEN

MAN ON R

23XE

24XE FAULT OFF

A U T O

14XE N_MM_242400_0_AAP0_01_00

AES

FIGURE 24-24-00-12400-A SHEET 1 AC Emergency Generation - Component Location

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

8XE

FR45

N_MM_242400_0_AAR0_01_00

AES

FIGURE 24-24-00-12500-A SHEET 1 AC Emergency Generation - Component Location

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

GROUND POINT

2XE CNTOR GLC EMER

CHASSIS GROUND

27WV SDAC−1

28 VDC WHEN ABOVE UV AND UF THRESHOLD

SDAC−2

EXCITER

VOLTAGE AND FREQUENCY

CLOSE K2 GLC CONTROL

OPEN VOLTAGE REGULATION

15XE CNTOR (COIL : 15XE1) AC ESS BUS

TEST TURN OFF PROTECTION MODULE GROUND SIGNAL WHEN TEST OK

SUPPLY PMG

NOSE L/G NOT LOKED UP

N a

1TW−CFDIU

28VDC

S

NOSE L/G LOKED UP

TIME DELAY 400 ms

MOTOR

5GA1−LGCIU1 SERVO VALVE

SPEED REGULATION

SWITCH OFF AFTER 10s

23XE P/BSW EMER ELEC PWR/ EMER GEN TEST

28 VDC SOLENOID CONTROL VALVE

3s

2PB2 BAT2

K1 8XE CSM/G

CLOSE

K3 24XE P/BSW EMER ELEC PWR/MAN ON

OPEN 1XE CONTROL UNIT CSM/G

3PH

CSM/G CONTROL LOGIC

N_MM_242400_0_ACP0_01_00

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FIGURE 24-24-00-13900-C SHEET 1 Electrical Emergency Generating System - Schematic

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

GROUND POINT

CHASSIS GROUND

2XE CNTOR GLC EMER

15XE CNTOR (COIL : 15XE1) AC ESS BUS

27WV SDAC−1

SDAC−2

28 VDC WHEN ABOVE UV AND UF THRESHOLD

CLOSE K2 GLC CONTROL

OPEN

EXCITER

VOLTAGE REGULATION

VOLTAGE AND FREQUENCY

TEST TURN OFF SUPPLY

PROTECTION MODULE GROUND SIGNAL WHEN TEST OK

PMG N a

SPEED

1TW−CFDIU

100 KNTS

S TIME DELAY 400 ms

1FP1 16XE RLY ADIRU1 EMER GEN TEST CONDITION

MOTOR SERVO VALVE

SPEED REGULATION

SWITCH OFF AFTER 10s

MAIN L/G COMPRESSED

2PB2 BAT2

3s

K1

8XE CSM/G

703PP 28VDC HOT BUS

5AGA1−LGCIU1

28 VDC

SOLENOID CONTROL VALVE

7XE

CLOSE

K3 24XE P/BSW EMER ELEC PWR/MAN ON

OPEN 1XE CONTROL UNIT CSM/G

3PH

CSM/G CONTROL LOGIC

N_MM_242400_0_ACQ0_01_00

AES

FIGURE 24-24-00-13900-D SHEET 1 Electrical Emergency Generating System - Schematic

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

1PE TR ESS

4XP 115VAC ESS BUS

4PE

115VAC

EMER GEN

28VAC 5XE

3XB STATIC INVERTER

8XE 1XP 115VAC BUS 1 33XE 2XE GLC EMER

TIMER 100ms

1XC

2XC 15XC

2XP 115VAC BUS 2

16XC 15XE (1) CNTOR AC ESS BUS

15XE (2) 17XN1 5XC

17XN2

4XC 14XC 13XC

3XC−CNTOR AC ESS BUS SWITCHING

12XE

PC LOGIC (4XP)

CSM/G PMG SUPPLY FAULT ALTN

GLC EMER CONTROL

11XC AC ESS FEED

NORM 1XE CSM/G CTL UNIT

N_MM_242400_0_AEP0_01_00

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FIGURE 24-24-00-17000-D SHEET 1 Electrical Emergency Switching - Schematic

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33XE 4XP

5PU1 5PU2 4PC

3XC2

3XC1

115VAC CSM/G 3XC1 3XC2

EMER GEN 3XC1 3XC2

FAULT CSM/G 28V PMG

8XE CSM/G

2XE

TIMER 100ms

15XE1

1PE ESS TR

4XP 115VAC ESS BUS

** On A/C ALL

N_MM_242400_0_AGN0_01_00

AES

FIGURE 24-24-00-17100-C SHEET 1 EMER & AC ESS BUS Contactors Control - Logic Diagram

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AES 1XP

V 100 Knts

2XP

FIGURE 24-24-00-17200-D SHEET 1 RAT Extension Logic & CSM/G Control Logic - Schematic

L/G LOCKED UP 1XP 2XP ESS TR

BAT 2

BLC1

4PP

16XE

103VU

106VU

1PH

6XE RES

DITTO BCL2

31XE

16XC

20XE

CONF 1s

BAT CHG LIM 1/2 (NOSE GEAR BAY) (SUPPLIED FROM 701PP/702PP)

ADIRS 1 (ZONE 127) (SUPPLIED FROM 704PP)

120VU

703PP HOT BUS 1

105VU

15XC

24-24-00 PB001

28VDC

701PP

NO FAULT

PULSE

5GA1 LGCIU − 1

NOSE L/G LOCKED UP

3PH

120VU

2805 GE

HYD/BLUE/ RAT MAN ON

40VU

1XE CSM/G CTL UNIT (ZONE 125)

FAULT

24XE

OVRD ELEC

14XE

ELECT. VALVE CSM/G

23XE

EMER ELEC PWR EMER GEN TEST

21VU

20VU

2

1

RAT SOLENOIDS (HYDRAULIC BAY)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 003-004

N_MM_242400_0_AJR0_01_00

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AES 1XP 2XP

FIGURE 24-24-00-17200-E SHEET 1 RAT Extension Logic and CSM/G Control Logic Schematic

1PB1 BCL1

MAIN LANDING GEAR COMPRESSED 1XP 2XP ESS TR

2PB2 BAT2

24-24-00 PB001

4PP 28VDC

16XE

103VU

RES

31XE

16XC

DITTO BCL1

1PB2 BCL2

106VU

1PH

6XE

20XE

CONF 1s

BAT CHG LIM 1/2 (NOSE GEAR BAY) (SUPPLIED FROM 701PP/702PP)

ADIRS 1 (ZONE 127) (SUPPLIED FROM 704PP)

SPD 100 Knots

120VU

703PP HOT BUS 1

105VU

15XC

701PP

NO FAULT

PULSE

120VU

2805 GE

HYD/BLUE/ RAT MAN ON

40VU

1XE CSM/G CTL UNIT (ZONE 125)

FAULT

24XE

OVRD ELEC

14XE

ELECT. VALVE CSM/G

23XE

EMER ELEC PWR EMER GEN TEST

21VU

20VU

2

1

RAT SOLENOIDS (HYDRAULIC BAY)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 005-099

N_MM_242400_0_AJT0_01_00

Page 19 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

703PP 28VDC HOT BUS

CSM/G CONTROL UNIT 7XE CSM/G STOP

106VU

CSM/G CONTROL

VALVE SUPPLY ON BAT

FAULT RAT/ CSM. G CTL

BAT.2

1PB1 BCL − 1

GLC CONTROL 2PB2

1XP 115VAC BUS1

11XE

2XP 115VAC BUS2

9XE

FAULT RAT/ CSM. G CTL

1XE

1PB2 BCL − 2

17XE EMER AUTO LOG CONDITION 6XE MAIN L/G COMPRESSED

4PP 28VDC

5GA1 LGCIU1

120VU 18XE EMER AUTO LOG CONDITION

BCL 1 (2)

N 704PP 28VDC HOT BUS

100KNTS

1PH

32XE

14XE ANN EMER ELEC PWR/ RAT/&/ EMER GEN

TEST

1S FAULT

6FP1

31XE

20XE RAT EXTN INHIB CONDITION 1FP1 ADIRU − 1

3PH 23XE EMER ELEC PWR/ EMER GEN TEST

XH XH

SDAC 1XP

30XE

16XE 22XE EMER GEN TEST CONDITION CSM/G EV SPLY MONG

X2

4XP 2XP

XC

XC

XC

XB

XB

12XE

EMER ELEC PWR/ MAN ON

X1

XC

5XE PC LOGIC

TD0

C1 EMER GEN TEST

3XC

4XP

STAT INV

15XE 24XE

16XC

15XC

21VU PH

106VU

XC

ESS TR

2

21XE B HYD PUMP CTL 103VU

XC

EMER GEN

PH

2XE GLC EMER

RAT DEPLOY SOLENOIDS

701PP

100ms

1

33XE − TIMER RAT ACTUATOR

2805GE

106VU

N_MM_242400_0_ALR0_01_00

AES

FIGURE 24-24-00-17400-F SHEET 1 Electrical Emergency Generation System - Control System

24-24-00 PB001

Page 20 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

703PP 28VDC HOT BUS

FAULT RAT/ CSM.G CTL

CSM/G CONTROL UNIT 7XE

CSM/G STOP

CSM/G CONTROL

VALVE SUPPLY ON BAT

BAT 2

1PB1 BCL − 1

GLC CONTROL

105VU 2PB2

FAULT RAT/ CSM.G CTL

1XE 1XP 115VAC BUS 1

2XP 115VAC BUS 2

1PB2 BCL − 2 28VDC

17XE EMER AUTO LOG CONDITION

11XE

NOSE L/G LOCKED UP

6XE

5GA1 LGCIU1

9XE

1PH

32XE 14XE ANN EMER ELEC PWR/ RAT/&/ EMER GEN

120VU 18XE EMER AUTO LOG CONDITION

BCL (1,2)

4PP

TEST

FAULT 3PH 704PP 28VDC HOT BUS

N

31XE

100KNTS

6FP1

1FP1 ADIRU − 1

23XE EMER ELEC PWR/ EMER GEN TEST

20XE RAT EXTN INHIB CONDITION

XH

SDAC

4XP

1XP

XH

2XP

30XE

X2 15XC

16XC

16XE EMER GEN TEST CONDITION

X1

3XC

24XE PH

106VU

RAT DEPLOY SOLENOIDS 1

21XE B HYD PUMP CTL 103VU

XB

XB

4XP

RAT ACTUATOR

STAT INV

XC XC

21VU 2

22XE CSM/G EV SPLY MONG

XC

PC LOGIC

3S C1 EMER GEN TEST

PH

XC

5XE

15XE

6S

XC

12XE

EMER ELEC PWR/ MAN ON

TDO

XC

2805GE

ESS TR

EMER GEN 2XE GLC EMER

100ms

701PP

33XE − TIMER 106VU N_MM_242400_0_ALS0_01_00

AES

FIGURE 24-24-00-17400-G SHEET 1 Electrical Emergency Generation System - Control System

24-24-00 PB001

Page 21 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

<

<

SELECT CFDS

<

<

<

<

<

< <

*

SELECT SYSTEM REPORT/TEST

>

< <

>

<

>

SELECT ELEC

<

<

<

>

<

>

<

>

<

>

<

>

<

>

NEGATIVE TEST

SELECT GCU EMER

<

<

<

*

NOTE : IF TEST POSITIVE "TEST OK" IS DISPLAYED N_MM_242400_0_ANP0_01_00

AES

FIGURE 24-24-00-17600-B SHEET 1 Test Procedure for GCU EMER by MCDU

24-24-00 PB001

Page 22 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

ELEC

BAT 1

BAT 2

28V 0A

DC BAT

28V 0A

DC 1

DC 2 DC ESS

TR 1

0v 0A

AC 1 GEN 1 0% 116V 400HZ IDG 1

TR 2

0v

EMER GEN

ESS TR

28V 62A

0A

116V 400HZ

AC ESS

AC 2 GEN

APU GEN

°C110

2

0% 116V 400HZ 110°C

IDG 2

4WT1 DU−ECAM, UPPER

N_MM_242400_0_AQKL_01_00

AES

FIGURE 24-24-00-18000-B SHEET 1 Electrical Emergency Configuration - Upper and Lower ECAM Display Unit

24-24-00 PB001

Page 23 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

ELEC

BAT 1

BAT

28V

DC

BAT

0A

DC

0A

1

DC DC

TR

ESS

V

0 A

AC

GEN

1

TR

EMER

GEN

28V

116V

62A

400HZ

AC

ESS

1

TR 2 0 V 0 A

AC

IDG 1

2

GEN

0% 116V 400HZ

2

ESS

1 0

2

28V

2

0%

APU

GEN

°C 1 1 0

116V 400HZ 1 1 0°C

IDG 2

NM5 24 32 00 0 AFLM 02

4WT1 DU−ECAM, UPPER

N_MM_242400_0_AQLL_01_00

AES

FIGURE 24-24-00-18000-C SHEET 1 Electrical Emergency Configuration - Upper and Lower ECAM Display Unit

24-24-00 PB001

Page 24 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 801PP

APU START 49 − 42 − 00

CSM/G CONTROL UNIT 5KA

10KA

6KA

6XE

4PB1

704PP

12PB2

BAT2 2PB2 701PP

12PB1

703PP BAT1 2PB1

6PB1 3PP

28VDC

DC ESS BUS

4PC

28VDC

SHUNT 3PB2 24 − 67 − 00 24 − 60 − 00

24 − 61 − 00 SHUNT DC BUS 2

1PC2

3XB

2PP 7PN

28VDC

28VDC

DC SVCE BUS

8PN

2XB

115

6PP 28VDC

3PX

5XB

28

4PP

3PB1

BAT BUS

1PC1

401PP

702PP

5PB1 1PP

8PH

20PC

5PB2

4PB2 6PB2 1PB1 BCL−1

24 − 61 − 00

8PP 28VDC

1PB2 BCL−2

DC BUS 1

DC SHED ESS BUS

301PP

11PB

6PH

5PU1 STATIC INV

5PU2

901XP

12XB

801XP

3PE

1PX

AC SHED ESS BUS 8XP 1PU1 TR1

115VAC

8XH

5XH

401XP 115VAC

24 − 50 − 00

2PU1

AC ESS BUS

AC BUS 1

1XP 115VAC

1PE ESS TR

431XP−A

26V

4XH

1PU2 TR2

24 − 50 − 00

4XP

AC BUS 2

2XC

1XC

2XP 115VAC

3XC

2PU2

14PU

24 − 42 − 00 4PE

24 − 50 − 00 15XE 15xe2

GLC−1 9XU1

BTC−1 11XU1

15xe1 EPC 3XG

GLC−APU 3XS

1XX

BTC−2 11XU2

GLC−2 9XU2

FUEL PUMPS 28 − 21 − 00 GCU−1 1XU1

AES

GEN 1

4000XU

14XX

GLC−EMERG 2XE

24 − 42 − 00 24 − 50 − 00

GCU−APU 1XS

APU GEN

8XS

FIGURE 24-24-00-18200-B SHEET 1 ELectrical Emergency Configuration During RAT Deployment and in Landing Gear Extented Configuration

GPCU 1XG

24-24-00 PB001

EXTERNAL POWER RECEPTACLE

Page 25 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_242400_0_AUL0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1

BAT 2 24 V 50 A

DC BAT

24 V 75 A

DC 1

DC 2 DC ESS SHED

TR 1 0V 0A

ESS TR

AC 1

EMER GEN

AC ESS

TR 2 0V 0A

AC 2

SHED

GEN 1 0% 0V 0HZ IDG1

APU GEN

°C 20

STAT INV 115V 4 0 0 HZ

GEN 2 0% 0V 0HZ 20 °C

IDG2

4WT1 DU − ECAM, UPPER

N_MM_242400_0_BNME_01_00

AES

FIGURE 24-24-00-18300-A SHEET 1 ESS BUSES ON BAT - Upper and Lower ECAM Display Unit

24-24-00 PB001

Page 26 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 801PP

APU START 49 − 42 − 00

CSM/G CONTROL UNIT 5KA

10KA

6KA

6XE

4PB1

704PP

12PB2

BAT2 2PB2 701PP

12PB1

703PP BAT1 2PB1

6PB1 3PP

28VDC

DC ESS BUS

4PC

28VDC

SHUNT 3PB2 24 − 67 − 00 24 − 61 − 00

24 − 60 − 00

SHUNT DC BUS 2

1PC2

3XB

2PP 7PN

28VDC

28VDC

DC SVCE BUS

8PN

2XB

115

6PP 28VDC

3PX

5XB

28

4PP

3PB1

BAT BUS

1PC1

401PP

702PP

5PB1 1PP

8PH

20PC

5PB2

4PB2 6PB2 1PB1 BCL−1

24 − 61 − 00

8PP 28VDC

1PB2 BCL−2

DC BUS 1

DC SHED ESS BUS

301PP

11PB

6PH

5PU1 STATIC INV

5PU2

901XP

12XB

801XP

3PE

1PX

AC SHED ESS BUS 8XP 1PU1 TR1

115VAC

8XH

5XH AC ESS BUS

AC BUS 1

1XP 115VAC

401XP 115VAC

24 − 50 − 00

2PU1

1PE ESS TR

431XP−A

26V

4XH

1PU2 TR2

24 − 50 − 00

4XP

AC BUS 2

2XC

1XC

2XP 115VAC

3XC

2PU2

14PU

24 − 42 − 00 4PE

24 − 50 − 00 15XE 15xe2

GLC−1 9XU1

BTC−1 11XU1

15xe1 EPC 3XG

GLC−APU 3XS

1XX

BTC−2 11XU2

GLC−2 9XU2

FUEL PUMPS 28 − 21 − 00 GCU−1 1XU1

AES

GEN 1

4000XU

14XX

GLC−EMERG 2XE

24 − 42 − 00 24 − 50 − 00

GCU−APU 1XS

APU GEN

8XS

FIGURE 24-24-00-18500-B SHEET 1 Electrical Emergency Configuration with CSM/G Running

GPCU 1XG

24-24-00 PB001

EXTERNAL POWER RECEPTACLE

Page 27 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_242400_0_AWL0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 801PP

APU START 49 − 42 − 00

CSM/G CONTROL UNIT 5KA

10KA

6KA

6XE

4PB1

704PP

12PB2

BAT2 2PB2 701PP

12PB1

703PP BAT1 2PB1

6PB1 3PP

28VDC

DC ESS BUS

4PC

4PP 28VDC

SHUNT 3PB2 24 − 67 − 00 24 − 61 − 00

24 − 60 − 00

SHUNT 3PB1

BAT BUS

1PC1

401PP

702PP

5PB1 1PP

8PH

20PC

5PB2

4PB2 6PB2 1PB1 BCL−1

24 − 61 − 00

8PP 28VDC

1PB2 BCL−2

DC BUS 1

DC SHED ESS BUS

301PP

11PB

DC BUS 2

1PC2

2PP 7PN

28VDC

28VDC

DC SVCE BUS

8PN

6PP 28VDC

3PX 5XB

3XB 28 5PU1

2XB

6PH

115

STATIC INV

5PU2

901XP

12XB

801XP

3PE

1PX

AC SHED ESS BUS 8XP 1PU1 TR1

115VAC

8XH

5XH AC ESS BUS

AC BUS 1

1XP 115VAC

401XP 115VAC

24 − 50 − 00

2PU1

24 − 50 − 00

4XP

AC BUS 2

2XC

1XC

1PE ESS TR

431XP−A

26V

4XH

1PU2 TR2

2XP 115VAC

3XC

2PU2

14PU 4PE

24 − 50 − 00 15XE 15xe2 GLC−1 9XU1

BTC−1 11XU1

15xe1 EPC 3XG

GLC−APU 3XS

1XX

BTC−2 11XU2

GLC−2 9XU2

FUEL PUMPS 28 − 21 − 00 GCU−1 1XU1

AES

GEN 1

4000XU

14XX 24 − 42 − 00

GLC−EMERG 2XE

24 − 50 − 00 GCU−APU

1XS

APU GEN

8XS

FIGURE 24-24-00-18700-B SHEET 1 Electrical Emergency Configuration on the Ground with speed < 50kts

GPCU 1XG

24-24-00 PB001

EXTERNAL POWER RECEPTACLE

Page 28 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_242400_0_BAL0_01_00

AES

FIGURE 24-24-00-18800-A SHEET 1 Available Functions in Emergency Configuration X X X X X

X

ATA 22 : AUTO FLIGHT FGC 1 MCDU 1 FAC 1 FCU 1

ATA 23 : COMMUNICATION * HF1 VHF 1 AUDIO MANAGER UNIT (CAPT−F/O) RADIO MANAGER UNIT 1 (RMP1) FLIGHT INTERPHONE CIDS CVR

X X X X

DURING RAT DEPLOYMENT

ATA 21 : AIR CONDITIONING * FLOW CONTROL PACK1 (SOLENOID) * CARGO VENT. ISOL. VALVE (AFT−FWD) AUTO PRESSURIZATION SYSTEM 1 EXTRACTION BY P (ONLY FLIGHT) BLOWING BY AIR CONDITIONING RAM AIR INLET

(*) REQUIRED FOR ETOPS

LIST OF AVAILABLE FUNCTIONS

SUPPLY ONLY BY BATTERIES (FLIGHT)

SUPPLY ONLY BY BATTERIES (FLT/GND)

X X X X X X X

X X X X

X X X X X X

CSM/G RUNNING

X X X X X

X

X X X X

CSM/G NOT RUNNING L/G NOT LOCKED UP

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

V

X X X X X

X

X

X

50Knts

SUPPLY ONLY BY BATTERIES (GROUND)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 003-004

N_MM_242400_0_BQM0_01_00

24-24-00 PB001

Page 29 May 01/12 Revision n˚: 40

AES

FIGURE 24-24-00-18800-B SHEET 1 Available Functions in Emergency Configuration X X X X X

X

ATA 22 : AUTO FLIGHT FMGC 1 MCDU 1 FAC 1 FCU 1

ATA 23 : COMMUNICATION * HF1 VHF 1 AUDIO MANAGER UNIT (CAPT−F/O) RADIO MANAGER UNIT 1 (RMP1) FLIGHT INTERPHONE CIDS CVR

X X X X

DURING RAT DEPLOYMENT

ATA 21 : AIR CONDITIONING FLOW CONTROL PACK1 (SOLENOID) * CARGO VENT. ISOL. VALVE (AFT−FWD) AUTO PRESSURIZATION SYSTEM 1 EXTRACTION BY P (ONLY FLIGHT) BLOWING BY AIR CONDITIONING RAM AIR INLET

(*) REQUIRED FOR ETOPS

LIST OF AVAILABLE FUNCTIONS

SUPPLY ONLY BY BATTERIES (FLIGHT)

SUPPLY ONLY BY BATTERIES (GROUND)

X X X X X X X

X X X X

X X X X X X

CSM/G RUNNING

X X X X X

X

X X X X

CSM/G NOT RUNNING V 100KTs

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

V

X X X X X

X

X

X

50KTs

SUPPLY ONLY BY BATTERIES (GROUND)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 005-099

N_MM_242400_0_BQN0_01_00

24-24-00 PB001

Page 30 May 01/12 Revision n˚: 40

AES

FIGURE 24-24-00-18900-A SHEET 1 Available Functions in Emergency Configuration

ATA 26 : FIRE PROTECTION ENG 1 FIRE DET LOOP A ENG 2 FIRE DET LOOP B ENG 1 & 2 FIRE EXTINGH BTL 1 ** APU FIRE AND OVHT DET LOOP A & B APU FIRE EXTINGH SQUIB A * CARGO SMOKE DET CHAN 1 * CARGO FIRE EXTINGH

ATA 24 : ELECTRICAL BAT CHG LIM 1 & 2 SUPPLY VOLT REF BAT 1 & 2 CSM/G ELECTROVALVE AUTO SUPPLY GEN 1 & 2 WARNING LIGHT RAT DEPLOYMENT AUTO (SOLENOID 1) RAT DEPLOYMENT MANUALLY (SOLENOID 2)

(*) REQUIRED FOR ETOPS

LIST OF AVAILABLE FUNCTIONS

X

X X X

X X X

X X

DURING RAT DEPLOYMENT

SUPPLY ONLY BY BATTERIES (FLIGHT)

SUPPLY ONLY BY BATTERIES (FLT/GND)

X X X X X

X X X X X X

CSM/G RUNNING

X

X X X

X X X X X X X

X

X

X X

50Knts

X

V

SUPPLY ONLY BY BATTERIES (GROUND)

X

X X

CSM/G NOT RUNNING L/G NOT LOCKED UP

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 003-004

N_MM_242400_0_BSM0_01_00

24-24-00 PB001

Page 31 May 01/12 Revision n˚: 40

AES

FIGURE 24-24-00-18900-B SHEET 1 Available Functions in Emergency Configuration

ATA 26 : FIRE PROTECTION ENG 1 FIRE DET LOOP A ENG 2 FIRE DET LOOP B ENG 1 & 2 FIRE EXTINGH BTL 1 ** APU FIRE AND OVHT DET LOOP A & B APU FIRE EXTINGH SQUIB A CARGO SMOKE DET CHAN 1 * CARGO FIRE EXTINGH

ATA 24 : ELECTRICAL BAT CHG LIM 1 & 2 SUPPLY VOLT REF BAT 1 & 2 CSM/G ELECTROVALVE AUTO SUPPLY GEN 1 & 2 WARNING LIGHT RAT DEPLOYMENT AUTO (SOLENOID 1) RAT DEPLOYMENT MANUALLY (SOLENOID 2)

(*) REQUIRED FOR ETOPS

LIST OF AVAILABLE FUNCTIONS

X

X X X

X X X

X X

DURING RAT DEPLOYMENT

SUPPLY ONLY BY BATTERIES (FLIGHT)

SUPPLY ONLY BY BATTERIES (GROUND)

X X X X X

X X X X X X

CSM/G RUNNING

X

X X X

X X X X X X X

X

X

X X

50KTs

X

V

SUPPLY ONLY BY BATTERIES (GROUND)

X

X X

CSM/G NOT RUNNING V 100KTs

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 005-099

N_MM_242400_0_BSN0_01_00

24-24-00 PB001

Page 32 May 01/12 Revision n˚: 40

AES

FIGURE 24-24-00-19000-A SHEET 1 Available Functions in Emergency Configuration

ATA 28 : FUEL (*SEE NOTA) FUEL QUANTITY IND 1 FUEL CROSS FEED VALVE LP FUEL FIRE SHUT OFF CTL INTERCELL TRANSFERT VALVE

ATA 27 : FLIGHT CONTROL ELAC 1 ELAC 2 SEC 1 ASSOCIATED ELECTROVALVES TRIM (THS) (MOT 1) TRIM (THS) (MOT 2) FCDC 1 SFCC 1 FLAPS/SLATS POSITION IND.

LIST OF AVAILABLE FUNCTIONS

X

X X

X X (305) X X X

DURING RAT DEPLOYMENT

SUPPLY ONLY BY BATTERIES (FLIGHT)

SUPPLY ONLY BY BATTERIES (FLT/GND)

X X X X

X X X X

X X

X

CSM/G RUNNING

X

X X

X X X X

CSM/G NOT RUNNING L/G NOT LOCKED UP

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

V

X

X

X X X X

50Knts

SUPPLY ONLY BY BATTERIES (GROUND)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 003-004

N_MM_242400_0_BUM0_01_00

24-24-00 PB001

Page 33 May 01/12 Revision n˚: 40

AES

FIGURE 24-24-00-19000-B SHEET 1 Available Functions in Emergency Configuration

ATA 28 : FUEL (*SEE NOTA) FUEL QUANTITY IND 1 LP FUEL FIRE SHUT OFF CTL INTERCELL TRANSFERT VALVE

ATA 27 : FLIGHT CONTROL ELAC 1 ELAC 2 SEC 1 ASSOCIATED ELECTROVALVES TRIM (THS) (MOT 1) TRIM (THS) (MOT 2) FCDC 1 SFCC 1 FLAPS/SLATS POSITION IND.

LIST OF AVAILABLE FUNCTIONS

X

X X

X X (305) X X X

DURING RAT DEPLOYMENT

SUPPLY ONLY BY BATTERIES (FLIGHT)

SUPPLY ONLY BY BATTERIES (GROUND)

X X X

X X X X

X X

X

CSM/G RUNNING

X

X X

X X X X

CSM/G NOT RUNNING V 100KTs

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

V

X

X

X X X X

50KTs

SUPPLY ONLY BY BATTERIES (GROUND)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 005-099

N_MM_242400_0_BUN0_01_00

24-24-00 PB001

Page 34 May 01/12 Revision n˚: 40

AES

FIGURE 24-24-00-19100-A SHEET 1 Available Functions in Emergency Configuration X X X X X X

X X

X X X X

ATA 30 : ICE AND RAIN PROTECTION * WING DE−ICING AOA PROBES 1 DE−ICING NACELLE ANTI−ICE (PNEUMATIC OPENING) CAPTAIN S PITOT ANTI−ICE PROBE ICE PROTECTION (CTL & MONG) RAIN REPELLENT

ATA 31 : INDICATING/RECORDING SYSTEM DMC 1 OR 3 PFD CAPT * ND CAPT ECAM DU UPPER SDAC 1 FWC 1 COCKPIT LOUD SPEAKER 1 ELECTRICAL CLOCK ECAM CTL PANEL

X X

DURING RAT DEPLOYMENT

ATA 29 : HYDRAULIC POWER HYDRAULIC FIRE VALVE ENG 1 AND 2 RAT DEPLOYMENT (SOLENOID 1)

(*) REQUIRED FOR ETOPS

LIST OF AVAILABLE FUNCTIONS

SUPPLY ONLY BY BATTERIES (FLIGHT)

SUPPLY ONLY BY BATTERIES (FLT/GND)

X X X X X X X X X

X X X X X X

X X

CSM/G RUNNING

X X X X X X

X X

X X X X

X X

CSM/G NOT RUNNING L/G NOT LOCKED UP

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

V

X X X

X X

X

X X

50Knts

SUPPLY ONLY BY BATTERIES (GROUND)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 003-004

N_MM_242400_0_BWM0_01_00

24-24-00 PB001

Page 35 May 01/12 Revision n˚: 40

AES

FIGURE 24-24-00-19100-B SHEET 1 Available Functions in Emergency Configuration X X X X X X

X X

X X X X

ATA 30 : ICE AND RAIN PROTECTION NACELLE ANTI−ICE (PNEUMATIC OPENING) CAPTAIN S PITOT ANTI−ICE PROBE ICE PROTECTION (CTL & MONG) RAIN REPELLENT

ATA 31 : INDICATING/RECORDING SYSTEM DMC 1 OR 3 PFD CAPT ND CAPT ECAM DU UPPER SDAC 1 FWC 1 COCKPIT LOUD SPEAKER 1 ELECTRICAL CLOCK ECAM CTL PANEL

X X

DURING RAT DEPLOYMENT

ATA 29 : HYDRAULIC POWER HYDRAULIC FIRE VALVE ENG 1 AND 2 RAT DEPLOYMENT (SOLENOID 1)

LIST OF AVAILABLE FUNCTIONS

SUPPLY ONLY BY BATTERIES (FLIGHT)

SUPPLY ONLY BY BATTERIES (GROUND)

X X X X X X X X X

X X X X

X X

CSM/G RUNNING

X X X X X X

X X

X X X X

X X

CSM/G NOT RUNNING V 100KTs

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

V

X X X

X X

X

X X

50KTs

SUPPLY ONLY BY BATTERIES (GROUND)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

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24-24-00 PB001

Page 36 May 01/12 Revision n˚: 40

AES

FIGURE 24-24-00-19200-A SHEET 1 Available Functions in Emergency Configuration X

X X

X X

X X X

ATA 33 : LIGHTS STANDBY COMPASS LIGHTING EMERGENCY COCKPIT LIGHTING (CAPT) EMERGENCY CABIN LIGHTING

ATA 34 : NAVIGATION * ADF 1 VOR 1 ILS 1 DME 1 STANDBY HORIZON ADIRS 1 VIBRATOR FOR STANDBY ALTIMETER ATC 1 & CTL BOX STBY VOR DME RMI

X X X X

DURING RAT DEPLOYMENT

ATA 32 : LANDING GEAR LGCIU 1 (L/G EXTENSION AND RETRACTION FUNCTION) EMERGENCY BRAKE PARKING BRAKE TRIPLE BRAKE PRESS INDICATOR

(*) REQUIRED FOR ETOPS

LIST OF AVAILABLE FUNCTIONS

SUPPLY ONLY BY BATTERIES (FLIGHT)

SUPPLY ONLY BY BATTERIES (FLT/GND)

X X X X X X X X X

X X X

X X X X

CSM/G RUNNING

X

X X

X X

X X X

X X X X

CSM/G NOT RUNNING L/G NOT LOCKED UP

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

V

X X

X X X

X X X X

50Knts

SUPPLY ONLY BY BATTERIES (GROUND)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

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24-24-00 PB001

Page 37 May 01/12 Revision n˚: 40

AES

FIGURE 24-24-00-19200-B SHEET 1 Available Functions IN Emergency Configuration X

X X

X X

X X X

ATA 33 : LIGHTS STANDBY COMPASS LIGHTING EMERGENCY COCKPIT LIGHTING (CAPT) EMERGENCY CABIN LIGHTING

ATA 34 : NAVIGATION ADF 1 VOR 1 ILS 1 DME 1 STANDBY HORIZON ADIRS 1 VIBRATOR FOR STANDBY ALTIMETER ATC 1 & CTL BOX STBY VOR DME RMI

X X X X

DURING RAT DEPLOYMENT

ATA 32 : LANDING GEAR LGCIU 1 (L/G EXTENSION AND RETRACTION FUNCTION) EMERGENCY BRAKE PARKING BRAKE TRIPLE BRAKE PRESS INDICATOR

LIST OF AVAILABLE FUNCTIONS

SUPPLY ONLY BY BATTERIES (FLIGHT)

SUPPLY ONLY BY BATTERIES (GROUND)

X X X X X X X X X

X X X

X X X X

CSM/G RUNNING

X

X X

X X

X X X

X X X X

CSM/G NOT RUNNING V 100KTs

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

V

X X

X X X

X X X X

50KTs

SUPPLY ONLY BY BATTERIES (GROUND)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 005-099

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24-24-00 PB001

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AES

FIGURE 24-24-00-19300-C SHEET 1 Available Functions in Emergency Configuration DURING RAT DEPLOYMENT

SUPPLY ONLY BY BATTERIES (FLT/GND)

CSM/G RUNNING

CSM/G NOT RUNNING L/G NOT LOCKED UP

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

V

50Knts

SUPPLY ONLY BY BATTERIES (GROUND)

NOTA: −FOR ONLY SMOKE CONFIGURATION, ONE FUEL PUMP BY WING IS DIRECTLY SUPPLIED BY GENERATOR 1 UP− STREAM THE GENERATOR 1 LINE CONTACTOR −**THESE FUNCTIONS ARE AVAILABLE IF ONLY "MASTER SWITCH" IS SELECTED "ON" −BAT BUS IS SUPPLIED BY BATTERIES. ONLY TWO APU START ATTEMPS ARE ALLOWED

FADEC 1 AND EIU 1 FADEC 2 AND EIU 2 CONTINUOUS RELIGHT SYS A HP FUEL SOLENOID ENG 1 & 2

ATA 72−78 : ENGINE CONTROL

ATA 49 : APU ** ECB ** APU FUEL PUMP ** APU FUEL LP VALVE

ATA 36 : PNEUMATIC AIR BLEED ENG 1 MONG & CTL * X FEED VALVE (MANUAL)

ATA 35 : OXYGEN CREW OXYGEN CTL PASSENGER OXYGEN CTL & IND

(*) REQUIRED FOR ETOPS

LIST OF AVAILABLE FUNCTIONS

SUPPLY ONLY BY BATTERIES (FLIGHT)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 003-004

N_MM_242400_0_CBA0_01_00

24-24-00 PB001

Page 39 May 01/12 Revision n˚: 40

AES

FIGURE 24-24-00-19300-D SHEET 1 Available Functions in Emergency Configuration DURING RAT DEPLOYMENT

SUPPLY ONLY BY BATTERIES (GROUND)

CSM/G RUNNING

CSM/G NOT RUNNING V 100KTs

LOSS OF MAIN ELECTRICAL GENERATION

SUPPLY BY EMERGENCY GEN (FLIGHT)

V

50KTs

SUPPLY ONLY BY BATTERIES (GROUND)

NOTA: −FOR ONLY SMOKE CONFIGURATION, ONE FUEL PUMP BY WING IS DIRECTLY SUPPLIED BY GENERATOR 1 UP− STREAM THE GENERATOR 1 LINE CONTACTOR −**THESE FUNCTIONS ARE AVAILABLE IF ONLY "MASTER SWITCH" IS SELECTED "ON" −BAT BUS IS SUPPLIED BY BATTERIES. ONLY TWO APU START ATTEMPS ARE ALLOWED

FADEC 1 AND EIU 1 FADEC 2 AND EIU 2 CONTINUOUS RELIGHT SYS A HP FUEL SOLENOID ENG 1 & 2

ATA 72−78 : ENGINE CONTROL

ATA 49 : APU ** ECB ** APU FUEL PUMP ** APU FUEL LP VALVE

ATA 36 : PNEUMATIC AIR BLEED ENG 1 MONG & CTL X FEED VALVE (MANUAL)

ATA 35 : OXYGEN CREW OXYGEN CTL PASSENGER OXYGEN CTL & IND

LIST OF AVAILABLE FUNCTIONS

SUPPLY ONLY BY BATTERIES (FLIGHT)

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

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24-24-00 PB001

Page 40 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1

28V

DC

BAT 2 28 V 0A

BAT

DC 1

DC DC

28V

ESS

ESS EMER

TR

GEN

28V

110A

AC 1

GEN

2

82A

AC

ESS

1

AC

2

GEN

2

62% 116V

APU

116V

400HZ

00%

400HZ

IDG 1

°C 1 1 0

60% 116V 400HZ

1 1 0°C

IDG 2

4WT2 DU − ECAM, LOWER

N_MM_242400_0_BCLE_01_00

AES

FIGURE 24-24-00-19700-B SHEET 1 Smoke Detection - Upper and Lower ECAM Display Unit

24-24-00 PB001

Page 41 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1

BAT 2

DC BAT

28 V 0A

28 V 0A

DC 2

DC 1 DC ESS

TR 2

TR 1

0v 0A

GEN

AC ESS

AC 2 GEN 2

1

06% 116V

0A

116V 4 0 0 HZ

28V 62A

AC 1

0v

EMER GEN

ESS TR

OFF

APU GEN

4 0 0 HZ OFF IDG 1

°C 1 1 0

1 1 0°C

IDG 2

4WT1 DU−ECAM, UPPER

N_MM_242400_0_BCLE_02_00

AES

FIGURE 24-24-00-19700-B SHEET 2 Smoke Detection - Upper and Lower ECAM Display Unit

24-24-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 801PP

APU START 49 − 42 − 00

CSM/G CONTROL UNIT 5KA

10KA

6KA

6XE

4PB1

704PP

12PB2

BAT2 2PB2 701PP

12PB1

703PP BAT1 2PB1

6PB1 3PP

28VDC

DC ESS BUS

4PC

4PP 28VDC

SHUNT 3PB2 26 − 67 − 00 24 − 61 − 00

24 − 60 − 00

SHUNT 3PB1

BAT BUS

1PC1

401PP

702PP

5PB1 1PP

8PH

20PC

5PB2

4PB2 6PB2 1PB1 BCL−1

24 − 61 − 00

8PP 28VDC

1PB2 BCL−2

DC BUS 1

DC SHED ESS BUS

301PP

11PB

DC BUS 2

1PC2

2PP 7PN

28VDC

28VDC

DC SVCE BUS

8PN

6PP 28VDC

3PX 5XB

3XB 28 5PU1

2XB

6PH

115

STATIC INV

5PU2

901XP

12XB

801XP

3PE

1PX

AC SHED ESS BUS 8XP 1PU1 TR1

115VAC

8XH

5XH AC ESS BUS

AC BUS 1

1XP 115VAC

401XP 115VAC

24 − 50 − 00

2PU1

1PE ESS TR

431XP−A

26V

4XH

1PU2 TR2

24 − 50 − 00

4XP

AC BUS 2

2XC

1XC

2XP 115VAC

3XC

2PU2

14PU

24 − 42 − 00 4PE

24 − 50 − 00 15XE 15xe2

GLC−1 9XU1

BTC−1 11XU1

15xe1 EPC 3XG

GLC−APU 3XS

1XX

BTC−2 11XU2

GLC−2 9XU2

FUEL PUMPS 28 − 21 GCU−1 1XU1

AES

GEN 1

4000XU

14XX

GLC−EMERG 2XE

24 − 42 − 00 24 − 50 − 00

GCU−APU 1XS

FIGURE 24-24-00-19800-B SHEET 1 Electrical Smoke Configuration

APU GEN

8XS

GPCU 1XG

24-24-00 PB001

EXTERNAL POWER RECEPTACLE

Page 43 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_242400_0_BJL0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC EMERGENCY GENERATION - ADJUSTMENT/TEST ** On A/C ALL Task 24-24-00-710-001-A Operational Test of the Emergency Generation System 1.

Reason for the Job (Ref. MPD 24-24-00-01-) OPERATIONAL CHECK OF EMERGENCY GENERATING SYSTEM Make sure that the essential busbars are supplied through the CSM/G. NOTE :

2.

You can do this test with the Blue electric pump or with a ground hydraulic cart.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

WARNING NOTICE(S)

98D27803500001

1

TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER

B.

Work Zones and Access Panels ZONE/ACCESS

210 812, 822 C.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

29-10-00-863-003-A

Pressurize the Blue Hydraulic System with a Ground Power Supply

29-10-00-863-003-A-01

Pressurize the Blue Hydraulic System with the Blue Electric Pump

29-10-00-864-003-A

Depressurize the Blue Hydraulic System

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

TSM 24-24-00-810-806

Result of the EMER GEN Test Incorrect (Failure of the Switching)

AES

24-24-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-24-00-860-050-A A.

Aircraft Maintenance Configuration WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE. (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

Pressurize the Blue hydraulic system with the Blue electric pump (Ref. TASK 29-10-00-863-003-A) or (Ref. TASK 29-10-00-863-003-A-01) or with a ground power supply (Ref. TASK 29-10-00-863-003-A) or (Ref. TASK 29-10-00-863-003-A-01).

(4)

On the FLAPS control panel 114VU: . Make sure that the slat/flap control lever is on the 0 position. . Make sure that the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) is in position on the flap/slat control lever. . Put a WARNING NOTICE(S) in position to tell persons not to operate the flap/slat control lever.

(5)

On the HYD section of the panel 50VU, release the LEAK MEASUREMENT VALVES/B pushbutton switch (the OFF legend comes on).

Subtask 24-24-00-010-051-A B.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access doors 812 and 822 of the avionics compartment.

(2)

Open the access doors 812 and 822.

Subtask 24-24-00-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) closed:

49VU

PANEL

DESIGNATION FWS/FWC1/SPLY

3WW

F01

105VU

ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/CNTOR/CTL

5PE

C02

106VU

ESS TR/SPLY

4PE

C01

121VU

EIS/FWC2/SPLY

2WW

Q07

122VU

ELEC/EMER GEN AUTO/2

9XE

Z26

122VU

ELEC/EMER GEN AUTO/1

11XE

Z25

AES

FIN

LOCATION

24-24-00 PB501

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure Subtask 24-24-00-710-050-B A.

Operational Test of the Emergency Generation System

ACTION 1.On the panel 21VU, on the EMER ELEC PWR section: . Lift the safety guard. . Push and hold the EMER GEN TEST pushbutton switch.

RESULT On the lower ECAM display unit: . The ELEC page comes into view automatically. . The green lines between the AC1 and the AC ESS busbar and the DC1 and the DC ESS busbar go out of view. . The EMER GEN and ESS TR indications are shown in white. The related parameters are shown in green. . The green lines between the EMER GEN and the AC ESS busbar, the EMER GEN and the ESS TR, the ESS TR and the DC ESS busbar come into view. . The SHED indication comes into view below the AC ESS and DC ESS busbar indications. NOTE :

2.On the panel 21VU: . Release the EMER GEN TEST pushbutton switch.

- During the CSM/G test (when the CSM/G is running), push the TR RESET pushbutton switch (15PU) on the panel 103VU to reset the essential TR. On the panel 21VU: . Check that the safety guard is back in its place. NOTE :

3.On the ECAM control panel: . Push the ELEC key to get the ELEC page.

(1) The Blue electric pump stops automatically (if you do the test with the Blue electric pump). (2) If not, on the HYD section of the panel 50VU, push and release the BLUE PUMP/OVRD pushbutton switch. Make sure that the ON legend goes off. The Blue electric pump must stop. Do the trouble shooting of the emergency generation system (Ref. TSM 24-24-00-810-806).

On the lower ECAM display unit: . The normal configuration comes into view: the emergency AC generator stops and the AC1 supplies the AC ESS busbars. NOTE :

AES

- If the essential TR is not in line: . its related parameters are shown in amber and . the green line between the essential TR and the DC essential busbar is not shown.

It is possible that the ESS TR continues to supply the DC ESS busbar. If this occurs, on the AC power center 123VU, open and close the circuit breaker 1XC and make sure that the ESS TR no longer supplies the DC ESS busbar.

24-24-00 PB501

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 4.On the ECAM control panel: . Push the STS key to get the STATUS page.

RESULT On the STATUS page of the lower ECAM display unit: . If the AIR BLEED status maintenance comes into view below the MAINTENANCE item, it is necessary to reset the two FWCs. Thus the FWCs will not keep a record of the indication in the POST FLIGHT REPORT at the next flight. Do the step that follows.

5.On the panel 49VU: . Open and close the circuit breaker 3WW. On the panel 121VU: . Open and close the circuit breaker 2WW.

On the STATUS page: . The AIR BLEED indication goes out of view.

5.

Close-up Subtask 24-24-00-860-051-A A.

Put the aircraft back to its initial configuration. (1)

If the test continues for more than 30 seconds, on the panel 22VU, the FAULT legend of the EXTRACT pushbutton switch comes on. In this case, release then push the EXTRACT pushbutton switch (the FAULT legend goes off).

(2)

On the HYD section of the panel 50VU, push the LEAK MEASUREMENT VALVES/B pushbutton switch (the OFF legend goes off).

(3)

Depressurize the Blue hydraulic system (Ref. TASK 29-10-00-864-003-A).

(4)

Remove the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) of the flap/slat control lever.

(5)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(6)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Subtask 24-24-00-410-051-A B.

AES

Close Access (1)

Close the access doors 812 and 822.

(2)

Remove the warning notice(s).

(3)

Remove the access platform(s).

24-24-00 PB501

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-24-00-710-002-A Operational Test of the Emergency Generator Control Unit (GCU) from Centralized Fault Display System (CFDS) 1.

Reason for the Job (Ref. MPD 24-24-00-02-) OPERATIONAL CHECK OF EMERGENCY GCU VIA CFDS Make sure that the protection modules (overvoltage, undervoltage, overfrequency, underfrequency) of the emergency GCU operate correctly, with the CFDS.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

210 812, 822 C.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-32-00-860-004-A

Procedure to Get Access to the SYSTEM REPORT/TEST/ELEC Page

3.

Job Set-up Subtask 24-24-00-010-052-A A.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access doors 812 and 822 of the avionics compartments.

(2)

Open the access doors 812 and 822.

Subtask 24-24-00-865-056-A B.

Make sure that this(these) circuit breaker(s) is(are) closed:

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

AES

FIN

LOCATION

24-24-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-24-00-860-052-A C.

4.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the procedure to get the SYSTEM REPORT/TEST ELEC page. (Ref. TASK 31-32-00-860-004-A).

Procedure Subtask 24-24-00-710-051-A A.

Operational Test of the GCU EMER from the CFDS

ACTION 1.On the MCDU, on the SYSTEM REPORT/TEST ELEC page: . push the line key adjacent to the GCU EMER indication. 2.On the MCDU, on the GCU EMER page: . push the line key adjacent to the TEST indication.

RESULT On the MCDU: . the GCU EMER page comes into view.

On the MCDU, on the GCU EMER page: . the TEST OK message comes into view. On the CSM/G GCU: . the red LED goes off after 10 seconds.

5.

Close-up Subtask 24-24-00-860-053-A A.

Put the aircraft back to its initial configuration. (1)

On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view.

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Subtask 24-24-00-410-052-A B.

AES

Close Access (1)

Close the access doors 812 and 822.

(2)

Remove the access platform(s).

24-24-00 PB501

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTROL UNIT - CSM/G - REMOVAL/INSTALLATION ** On A/C ALL Task 24-24-34-000-001-A Removal of the CSM/G Control Unit FIN 1XE 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

(Ref. Fig. 24-24-34-991-00100-A - CSM/G Control Unit) 3.

Job Set-up Subtask 24-24-34-860-050-A A.

Aircraft Maintenance Configuration (1)

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

(2)

In the cockpit, on the EMER ELEC PWR section of the overhead panel 21VU, put a WARNING NOTICE(S) to tell persons not to operate the pushbutton switches.

Subtask 24-24-34-010-050-A B.

AES

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access doors 812 and 822 of the avionics compartment.

(2)

Open the access doors 812 and 822.

24-24-34 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-24-34-865-050-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

105VU

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-24-34-991-00100-A - CSM/G Control Unit) Subtask 24-24-34-020-050-A A.

AES

Removal of the GCU (1)

Disconnect the electrical connector (4).

(2)

Loosen the 4 screws (3).

(3)

Hold the CSM/G control unit (1).

(4)

Remove the screws (3) and the washers (2).

(5)

Remove the CSM/G control unit (1).

(6)

Put CAP - BLANKING on the electrical connector (4) and the electrical receptacle (5).

24-24-34 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

1XE

B Z125

A

FR13 FR12

B

4

5

1

2 3

N_MM_242434_4_AAM0_01_00

AES

FIGURE 24-24-34-991-00100-A SHEET 1 CSM/G Control Unit

24-24-34 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-24-34-400-001-A Installation of the CSM/G Control Unit FIN 1XE 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-24-00-710-001-A

DESIGNATION Operational Test of the Emergency Generation System

24-24-00-710-002-A

Operational Test of the Emergency Generator Control Unit (GCU) from Centralized Fault Display System (CFDS)

24-42-00-861-001-A

Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

(Ref. Fig. 24-24-34-991-00100-A - CSM/G Control Unit) 3.

Job Set-up Subtask 24-24-34-860-052-A A.

Aircraft Maintenance Configuration (1)

Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001-A).

(2)

Make sure that the WARNING NOTICE(S) is in the cockpit, on the EMER ELEC PWR section of the overhead panel 21VU, to tell persons not to operate the pushbutton switches.

(3)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access doors 812 and 822 of the avionics compartment.

(4)

Make sure that the access doors 812 and 822 are open.

Subtask 24-24-34-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

AES

FIN

LOCATION

24-24-34 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-24-34-991-00100-A - CSM/G Control Unit) Subtask 24-24-34-420-050-A A.

Installation of the GCU (1)

Clean the component interface and/or the adjacent area.

(2)

Do an inspection of the component interface and/or the adjacent area.

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Put the CSM/G control unit (1) in position.

(6)

Install the washers (2) and the screws (3) and then tighten the screws.

(7)

Connect the electrical connector (4).

Subtask 24-24-34-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

FIN C01

LOCATION

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

Subtask 24-24-34-710-050-A C.

Operational test (1)

Do an operational test of the emergency GCU, with the CFDS (Ref. TASK 24-24-00-710-002-A). NOTE :

(2) 5.

As an alternative procedure, do this operational test without the CFDS.

Do an operational test of the emergency GCU without the CFDS (Ref. TASK 24-24-00-710-001-A).

Close-up Subtask 24-24-34-410-050-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access doors 812 and 822.

(3)

Remove the warning notice(s).

(4)

Remove the access platform(s).

Subtask 24-24-34-860-051-A B.

Put the aircraft back to its initial configuration. (1)

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

24-24-34 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

GENERATOR - CONSTANT SPEED MOTOR (CSM/G) REMOVAL/INSTALLATION ** On A/C ALL Task 24-24-51-000-001-A Removal of the Constant Speed Motor/Generator (CSM/G) WARNING : OBEY THE HYDRAULIC SAFETY PROCEDURES. WARNING : DO NOT WALK ON A CLOSED LANDING GEAR DOOR. CAUTION :

USE HIGH-PRESSURE SPRAYING EQUIPMENT FOR SPECIFIED AREAS ONLY. DO NOT USE HIGH-PRESSURE SPRAYING EQUIPMENT TO CLEAN THE AREAS AROUND SENSORS, PROBES, ANTENNAS, ETC. YOU MUST CLEAN THESE AREAS BY HAND. MAKE SURE THAT YOU ADJUST THE HIGH-PRESSURE SPRAYING EQUIPMENT TO, AND USE IT AT, THE SPECIFIED VALUES. IF YOU DO NOT OBEY THESE PRECAUTIONS, YOU CAN CAUSE DAMAGE TO THE SURFACE OR TO PARTS. HIGH-PRESSURE SPRAYING EQUIPMENT CAN PUSH LIQUIDS INTO BEARINGS, JOINTS, PROBES, BRAKES, ELECTRICAL CONNECTORS AND OTHER SEALED COMPONENTS. LIQUIDS THAT GO INTO THESE AREAS CAN FREEZE DURING AIRCRAFT FLIGHT, REMOVE LUBRICANTS, CAUSE CORROSION AND ELECTRICAL FAULTS.

FIN 8XE 1.

Reason for the Job Self Explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific No specific

QTY DESIGNATION AR CAP - BLANKING 1 CONTAINER - HYDRAULIC FLUID RESISTANT AR PLUG - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

1

STEPLADDER 2.0 M (6.6 FT)

No specific

1

WARNING NOTICE(S)

B.

Referenced Information

REFERENCE 29-00-00-864-001-A 29-14-00-614-001-A

DESIGNATION Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Depressurization of the Hydraulic Reservoirs

32-12-00-010-001-A

Open the Main Gear Doors for Access

(Ref. Fig. 24-24-51-991-00100-A - Constant Speed Motor/Generator - CSM/G 8XE.)

AES

24-24-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-24-51-860-050-A A.

Aircraft Maintenance Configuration (1)

On . . .

the overhead panel 21VU, make sure that: the guarded pushbutton-switch EMER GEN TEST is released (the guard is closed), the guarded pushbutton-switch MAN ON/AUTO is released (the guard is closed), the guarded pushbutton-switch RAT MAN ON 2805GE is released (the guard is closed).

(2)

Put a WARNING NOTICE(S) in position to tell persons not to pressurize the Blue hydraulic system: . in the cockpit on the overhead panel 40VU, . on the ground service panel of the Blue hydraulic system.

(3)

Depressurization of the Hydraulic System (a)

Depressurize the Blue hydraulic system (Ref. TASK 29-00-00-864-001-A).

(b)

Depressurize the reservoir of the Blue hydraulic system (Ref. TASK 29-14-00-614-001-A).

Subtask 24-24-51-865-050-A B.

Open, safety and tag this(these) circuit breaker(s):

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

FIN C01

LOCATION

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/EMER GEN AUTO/2

9XE

Z26

122VU

ELEC/EMER GEN AUTO/1

11XE

Z25

Subtask 24-24-51-010-050-A C.

4.

Get Access (1)

Open the LH or RH Main Landing-Gear (MLG) door (Ref. TASK 32-12-00-010-001-A).

(2)

Put the STEPLADDER 2.0 M (6.6 FT) in position at the MLG bay.

Procedure (Ref. Fig. 24-24-51-991-00100-A - Constant Speed Motor/Generator - CSM/G 8XE.) Subtask 24-24-51-020-050-A A.

AES

Removal of the Constant Speed Motor/Generator (8XE) (1)

Disconnect the electrical connectors (2),(3),(13) and (14) from the CSM/G (1).

(2)

Put blanking caps on the disconnected electrical connector(s).

(3)

Put a CONTAINER - HYDRAULIC FLUID RESISTANT in position to collect hydraulic fluid leakage.

(4)

Disconnect the flexible hydraulic pipes (11), (12) and (15) from the CSM/G (1).

(5)

Disconnect the flexible drain hoses (4) and (10) from the CSM/G (1).

(6)

Put blanking plugs on the disconnected line ends.

(7)

Loosen the lockwashers (8), remove the screws (5), the washer (6) and discard the lockwashers (8).

(8)

Loosen the bonding strap (7) from its position.

(9)

Remove the CSM/G (1) from the support mounts (9).

24-24-51 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z197

A

Z147

2 8XE2

A

3 8XE1 1 8XE

5 6 Z734

7

15

14 8XE4 12

11

8 5

4

8

13 8XE3 10

9

N_MM_242451_4_AAM0_01_00

AES

FIGURE 24-24-51-991-00100-A SHEET 1 Constant Speed Motor/Generator - CSM/G 8XE.

24-24-51 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-24-51-400-001-A Installation of the Constant Speed Motor/Generator (CSM/G) WARNING : OBEY THE HYDRAULIC SAFETY PROCEDURES. WARNING : DO NOT WALK ON A CLOSED LANDING GEAR DOOR. CAUTION :

USE HIGH-PRESSURE SPRAYING EQUIPMENT FOR SPECIFIED AREAS ONLY. DO NOT USE HIGH-PRESSURE SPRAYING EQUIPMENT TO CLEAN THE AREAS AROUND SENSORS, PROBES, ANTENNAS, ETC. YOU MUST CLEAN THESE AREAS BY HAND. MAKE SURE THAT YOU ADJUST THE HIGH-PRESSURE SPRAYING EQUIPMENT TO, AND USE IT AT, THE SPECIFIED VALUES. IF YOU DO NOT OBEY THESE PRECAUTIONS, YOU CAN CAUSE DAMAGE TO THE SURFACE OR TO PARTS. HIGH-PRESSURE SPRAYING EQUIPMENT CAN PUSH LIQUIDS INTO BEARINGS, JOINTS, PROBES, BRAKES, ELECTRICAL CONNECTORS AND OTHER SEALED COMPONENTS. LIQUIDS THAT GO INTO THESE AREAS CAN FREEZE DURING AIRCRAFT FLIGHT, REMOVE LUBRICANTS, CAUSE CORROSION AND ELECTRICAL FAULTS.

FIN 8XE 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

Expendable Parts

FIG.ITEM 8

QTY DESIGNATION 1 STEPLADDER 2.0 M (6.6 FT)

DESIGNATION

IPC-CSN 24-24-03-01-110

lockwashers C.

Referenced Information

REFERENCE 20-28-00-912-004-A

DESIGNATION Electrical Bonding of Components With Conductive Bolts and Screws and Bonding Straps in the Fuselage and in the Wings (this does not include the tanks)-

24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

29-00-00-864-001-A

Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Pressurize the Blue Hydraulic System with a Ground Power Supply

29-10-00-863-003-A

AES

24-24-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 29-10-00-863-003-A-01

DESIGNATION Pressurize the Blue Hydraulic System with the Blue Electric Pump

29-10-00-864-003-A

Depressurize the Blue Hydraulic System

29-14-00-614-001-A

Depressurization of the Hydraulic Reservoirs

29-14-00-614-002-A

Pressurization of the Hydraulic Reservoirs through the Ground Connector

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

32-12-00-010-001-A Open the Main Gear Doors for Access 32-12-00-410-001-A Close the Main Gear Doors after Access (Ref. Fig. 24-24-51-991-00100-A - Constant Speed Motor/Generator - CSM/G 8XE.) 3.

Job Set-up Subtask 24-24-51-860-052-A A.

Aircraft Maintenance Configuration (1)

Make sure that the blue hydraulic system is depressurized (Ref. TASK 29-00-00-864-001-A).

(2)

Make sure that the reservoir of the blue hydraulic system is depressurized (Ref. TASK 29-14-00-614-001-A).

(3)

Make sure that the LH and RH Main Landing Gear (MLG) is opened (Ref. TASK 32-12-00-010-001-A).

(4)

Make sure that the STEPLADDER 2.0 M (6.6 FT) is in position at the MLG bay.

Subtask 24-24-51-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/EMER GEN AUTO/2

9XE

Z26

122VU

ELEC/EMER GEN AUTO/1

11XE

Z25

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-24-51-991-00100-A - Constant Speed Motor/Generator - CSM/G 8XE.) Subtask 24-24-51-420-051-A A.

AES

Installation of the CSM/G (1)

Put the CSM/G (1) in position on the support mounts (9) on top of the keel beam.

(2)

Attach the CSM/G (1) with new (IPC-CSN 24-24-03-01) lockwashers (8) , the screws (5), the washer (6) and the bonding strap (7) on the support mounts (9) (Ref. TASK 20-28-00-912-004-A).

(3)

Tighten the screws (5).

(4)

Safety the screws (5) with the lockwashers (8).

(5)

Make sure that the hydraulic line end-fittings are serviceable.

(6)

Remove the blanking plugs and connect the hydraulic pipes (11),(12) and (15) to the CSM/G (1).

(7)

Remove the blanking plugs and connect the flexible drain hoses (4) and (10) to the CSM/G (1).

(8)

Remove the blanking caps and connect the electrical connectors (2), (3), (13) and (14) to the CSM/G (1).

24-24-51 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-24-51-865-055-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

105VU

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

FIN

LOCATION

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/EMER GEN AUTO/2

9XE

Z26

122VU

ELEC/EMER GEN AUTO/1

11XE

Z25

Subtask 24-24-51-860-051-A C.

Preparation for Test (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

Pressurize the Blue Hydraulic System (a)

Pressurize the reservoir of the Blue hydraulic system (Ref. TASK 29-14-00-614-002-A).

(b)

Pressurize the Blue hydraulic system either with the electric pump or a ground hydraulic cart (Ref. TASK 29-10-00-863-003-A) or (Ref. TASK 29-10-00-863-003-A-01).

Subtask 24-24-51-710-051-A D.

Test

ACTION RESULT 1.On the overhead panel 21VU, on the EMER ELEC PWR On the lower ECAM display unit: section: . The ELEC page comes into view automatically. . Lift the safety guard, push and hold the EMER GEN . The green lines between the AC1 and the AC ESS TEST pushbutton switch 23XE. busbar and the DC1 and the DC ESS busbar go out of view. . The EMER GEN and ESS TR indications are white. The parameters are green. . Green lines come into view between: EMER GEN and AC ESS EMER GEN and ESS TR ESS TR and DC ESS indications. . The SHED indication comes into view below the AC ESS and DC ESS indications. NOTE :

AES

It is necessary to do a reset of the essential TR when: . Its related parameters are amber and/or . The green line between the ESS TR and the DC ESS indications is not shown.

24-24-51 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION RESULT 2.On the panel 103VU: On the lower ECAM display unit: . Push the TR RESET pushbutton switch 15PU to do a . The parameters of the essential TR are green and reset of the essential TR. . The green line between the ESS TR and the DC ESS indications comes into view. NOTE : This reset is only necessary when: . The parameters of the essential TR are amber and/or . The green line between the ESS TR and the DC ESS indications is not shown. The CSM/G must be in operation when you push the TR RESET pushbutton switch 15PU. 3.On the overhead panel 21VU, on the EMER ELEC PWR On the overhead panel 21VU, on the EMER ELEC PWR section: section: . Release the EMER GEN TEST pushbutton switch . The safety guard is back in the released position. 23XE. On the lower ECAM display unit: . The Blue electrical hydraulic pump stops and the generator is automatically disconnected from its network. . All indications are cancelled. . The ELEC page goes out of view. 5.

Close-up Subtask 24-24-51-410-052-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the stepladder.

(3)

Close the LH and RH MLG door (Ref. TASK 32-12-00-410-001-A).

(4)

Put the system back to a serviceable condition

(5)

Remove the warning notices from the cockpit and from the ground service panel of the Blue hydraulic system.

(6)

Remove the ground support and maintenance equipment, the special and standard tools and all other items.

Subtask 24-24-51-860-053-A B.

AES

Put the aircraft back to its initial configuration. (1)

De-pressurize the Blue hydraulic system (Ref. TASK 29-10-00-864-003-A).

(2)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(3)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-24-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-24-55-000-001-A Removal of the Emergency Generator Line Contactor (EMER GLC) WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 2XE 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE (Ref. Fig. 24-24-55-991-00100-A - Contactor) 3.

DESIGNATION

Job Set-up Subtask 24-24-55-941-051-A A.

AES

Safety Precautions (1)

In . . .

the cockpit, on the overhead panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, GEN 1(2), APU GEN, EXT PWR.

(2)

In the cockpit, put a WARNING NOTICE(S) to tell persons not to operate the pushbutton switches on the overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(3)

Make sure that the external power connector is not connected to the aircraft receptable EXT PWR.

(4)

Put a WARNING NOTICE(S) on the access door 121AL to tell persons not to connect the external power connector.

24-24-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-24-55-010-050-A B.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the avionics compartment doors 812 and 822.

(2)

Open the access doors 812 and 822.

Subtask 24-24-55-865-050-A C.

Open, safety and tag this(these) circuit breaker(s):

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

FIN C01

LOCATION

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

Subtask 24-24-55-010-052-A D.

Get Access (1)

4.

In the avionics compartment, remove the access panel (1) from the AC/DC emergency power center 106VU.

Procedure (Ref. Fig. 24-24-55-991-00100-A - Contactor) CAUTION :

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Subtask 24-24-55-020-050-A A.

AES

Removal of the Contactor (1)

Disconnect the wires (6) from the contactor (7).

(2)

Remove the 6 screws (5) and washers (4).

(3)

Remove the power supply wires (3).

(4)

Loosen the 4 nuts (2).

(5)

Hold the contactor (7).

(6)

Remove the 4 nuts (2).

(7)

Remove the contactor (7).

24-24-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR12

822

A A 106VU

FR16

812

2XE

B

B

1

106VU

2 3

4 5 7

6 N_MM_242455_4_AAM0_01_00

AES

FIGURE 24-24-55-991-00100-A SHEET 1 Contactor

24-24-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-24-55-400-001-A Installation of the Emergency Generator Line Contactor (EMER GLC) WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 2XE 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-24-00-710-001-A

DESIGNATION Operational Test of the Emergency Generation System

(Ref. Fig. 24-24-55-991-00100-A - Contactor) 3.

Job Set-up Subtask 24-24-55-860-052-A A.

AES

Aircraft Maintenance Configuration (1)

In . . .

the cockpit, on the overhead panel 35VU, make sure that these pushbutton switches are realeased: BAT 1, BAT 2, GEN 1(2), APU GEN, EXT PWR.

(2)

Make sure that there is a WARNING NOTICE(S) in the cockpit to tell persons not to operate the pushbutton switches on the overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(3)

Make sure that the external power connector is not connected to the aircraft receptable EXT PWR.

(4)

Make sure that there is a WARNING NOTICE(S) on the access door 121AL to tell persons not to connect the external power connector.

(5)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE are in position at the access doors 812 and 822.

(6)

Make sure that the access doors 812 and 822 are open.

24-24-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (7)

In the avionics compartment, make sure that the access panel (1) from the AC/DC emergency power center 106VU is open.

Subtask 24-24-55-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-24-55-991-00100-A - Contactor) Subtask 24-24-55-420-050-A A.

Installation of the Contactor CAUTION :

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Put the contactor (7) in position.

(2)

Install the nuts (2) and tighten them.

(3)

Install the power supply wires (3).

(4)

Install the 6 washers (4) and screws (5). Tighten the screws (5).

(5)

Connect the wires (6) to the contactor (7).

Subtask 24-24-55-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

105VU

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

FIN

LOCATION

7XE

C01

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

Subtask 24-24-55-710-050-A C. 5.

Do an operational test of the emergency AC generation system (Ref. TASK 24-24-00-710-001-A).

Close-up Subtask 24-24-55-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the access panel (1) on the AC/DC emergency power center 106VU.

24-24-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AES

(3)

Close the access doors 812 and 822.

(4)

Remove the warning notice(s).

(5)

Remove the access platform(s).

24-24-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-24-55-000-002-A Removal of the AC ESS BUS Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 15XE 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE (Ref. Fig. 24-24-55-991-00300-A - Contactor) 3.

DESIGNATION

Job Set-up Subtask 24-24-55-941-052-A A.

Safety Precautions (1)

In . . .

the cockpit, on the overhead panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, GEN 1(2), APU GEN, EXT PWR.

(2)

In the cockpit, put a WARNING NOTICE(S) to tell persons not to operate the pushbutton switches on the overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(3)

Make sure that the external power connector is not connected to the aircraft receptable EXT PWR.

(4)

Put a WARNING NOTICE(S) on the access door 121AL to tell persons not to connect the external power connector.

Subtask 24-24-55-010-051-A B.

Get access to the Avionics Compartment (1)

AES

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access doors 812 and 822.

24-24-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Open the access doors 812 and 822.

Subtask 24-24-55-865-053-A C.

Open, safety and tag this(these) circuit breaker(s):

106VU

PANEL

DESIGNATION AC ESS/BUS/EMER/CNTOR/SPLY

15PC

FIN C08

LOCATION

106VU

AC ESS BUS/EMER/STBY/CNTOR/SPLY

10XE

C06

Subtask 24-24-55-010-053-A D.

Get Access (1)

4.

In the avionics compartment, remove the access panel (13) from the AC/DC emergency power center 106VU.

Procedure (Ref. Fig. 24-24-55-991-00300-A - Contactor) CAUTION :

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Subtask 24-24-55-020-051-A A.

Removal of the Contactor (1)

Disconnect the two electrical connectors (5).

(2)

Put CAP - BLANKING on the electrical connectors (5) and the electrical receptacles (4).

(3)

Loosen the nuts (6).

(4)

Remove the nuts (6) and the washers (7).

(5)

Remove the power supply wires (8) and the retaining washers (9).

(6)

Remove the crimped lugs (10) with the shunts (11) and but do not discard them.

(7)

Loosen the 4 nuts (12).

(8)

Hold the contactor (2).

(9)

Remove the 4 nuts (12) and washers (1).

(10) Remove the contactor (2).

AES

24-24-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

FR12

106VU

822

A FR16

812

B 13

B

6

15XE

7 8 9

10 11 12 2

1

5 3 106VU 4 N_MM_242455_4_AAL0_01_00

AES

FIGURE 24-24-55-991-00300-A SHEET 1 Contactor

24-24-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-24-55-400-002-A Installation of the AC ESS BUS Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 15XE 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-24-00-710-001-A

DESIGNATION Operational Test of the Emergency Generation System

24-28-00-710-001-A

Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the External Power

24-28-00-710-001-A-01

Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the APU

(Ref. Fig. 24-24-55-991-00300-A - Contactor) 3.

Job Set-up Subtask 24-24-55-860-053-A A.

AES

Aircraft Maintenance Configuration (1)

In . . .

the cockpit, on the overhead panel 35VU, make sure that these pushbutton switches are realeased: BAT 1, BAT 2, GEN 1(2), APU GEN, EXT PWR.

(2)

Make sure that there is a WARNING NOTICE(S) in the cockpit to tell persons not to operate the pushbutton switches on the overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(3)

Make sure that the external power connector is not connected to the aircraft receptable EXT PWR.

(4)

Make sure that there is a WARNING NOTICE(S) on the access door 121AL to tell persons not to connect the external power connector.

24-24-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (5)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE are in position at the access doors 812 and 822.

(6)

Make sure that the access doors 812 and 822 are open.

(7)

In the avionics compartment, make sure that the access panel (13) of the AC/DC emergency power center 106VU is open.

Subtask 24-24-55-865-054-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

106VU

PANEL

DESIGNATION AC ESS/BUS/EMER/CNTOR/SPLY

15PC

C08

106VU

AC ESS BUS/EMER/STBY/CNTOR/SPLY

10XE

C06

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-24-55-991-00300-A - Contactor) Subtask 24-24-55-420-051-A A.

Installation of the Contactor CAUTION :

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Put the contactor (2) in position on the studs (3).

(2)

Install the washers (1) and the nuts (12). Tighten the nuts.

(3)

Install the crimped lugs (10) with the shunts (11).

(4)

Install the retaining washers (9).

(5)

Install the power supply wires (8).

(6)

Install the washers (7) and the nuts (6). Tighten the nuts (6).

(7)

Remove the blanking caps from the electrical connector(s).

(8)

Make sure that the electrical connectors are clean and in the correct condition.

(9)

Connect the 2 electrical connectors (5).

Subtask 24-24-55-865-055-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

106VU

PANEL

DESIGNATION AC ESS/BUS/EMER/CNTOR/SPLY

15PC

FIN C08

LOCATION

106VU

AC ESS BUS/EMER/STBY/CNTOR/SPLY

10XE

C06

Subtask 24-24-55-710-051-A C.

AES

Operational Tests (1)

Do the operational test of the emergency generation system (Ref. TASK 24-24-00-710-001-A).

(2)

Do the operational test of the static inverter (Ref. TASK 24-28-00-710-001-A) or (Ref. TASK 24-28-00-710-001-A-01).

24-24-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-24-55-410-051-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the access panel (13) on the AC/DC emergency power center 106VU.

(3)

Close the access doors 812 and 822.

(4)

Remove the warning notice(s).

(5)

Remove the access platform(s).

24-24-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC ESSENTIAL GENERATION SWITCHING - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General These circuits control the supply of the AC essential distribution network. They enable: . its normal supply in normal flight configuration, . transfer of the supply in case of AC BUS 1 loss, ** On A/C 004-099 EMB SB 24-1120 FOR A/C 004-008 POST SB 24-1120 FOR A/C 003-003 - automatic transfer to the AC BUS 2 after 3 seconds.

AES

24-25-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-25-00-12400-A - AC Essential Generation Switching - Component Location) (Ref. Fig. 24-25-00-12500-A - AC Essential Generation Switching - Component Location) FIN

3XC 11XC

AES

FUNCTIONAL DESIGNATION CNTOR-AC ESS BUS SWITCHING P/BSW-ELEC/AC ESS FEED

PANEL 106VU 35VU

ZONE ACCESS ATA REF. DOOR 125 24-25-55 210 24-25-00

24-25-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

Operation

** On A/C 003-004 (Ref. Fig. 24-25-00-13800-C - Loss of AC Normal BUS 1XP - Block Diagram Control and Indicating Circuits) ** On A/C 005-099 (Ref. Fig. 24-25-00-13800-F - Loss of AC Normal BUS 1XP - Block Diagram Control and Indicating Circuits) AC Essential Busbar (AC ESS BUS) and AC Sheddable Essential Busbar (AC SHED ESS BUS) are normally supplied in series from AC BUS 1 through respectively AC ESS BUS TIE CONTACTOR (3XC1) and AC SHED ESS BUS CONTACTOR (8XH). In the event of AC BUS 1 loss, AC ESS BUS is no longer supplied, which causes amber MASTER CAUT light to come on. ** On A/C 003-003 PRE SB 24-1120 FOR A/C 003-003 Amber ”FAULT” legend illuminates on AC ESS FEED pushbutton switch located on the ELEC panel 35VU. On the lower ECAM DU, ELEC page is displayed, ”AC ESS” becomes amber, synoptic is modified. NOTE :

MASTER CAUT light + single chime + amber message on the upper ECAM DU confirm this failure.

To recover AC ESS busses, the crew has to push AC ESS FEED pushbutton switch. AC ESS busses are then supplied by AC BUS 2. White ALTN legend illuminates on AC ESS FEED pushbutton switch, (FAULT legend remains on if AC ESS bus is still not supplied). On the lower ECAM DU, AC ESS becomes green again and synoptic is modified. ** On A/C 004-099 EMB SB 24-1120 FOR A/C 004-008 POST SB 24-1120 FOR A/C 003-003 Amber ”FAULT” legend illuminates on AC ESS FEED pushbutton switch located on the ELEC panel 35VU. On the lower ECAM DU, ELEC page is displayed, ”AC ESS” becomes amber, synoptic is modified. NOTE :

MASTER CAUT light + single chime + amber message on the upper ECAM DU confirm this failure.

To recover AC ESS busses, supplied by the AC BUS 2, the crew must release the AC ESS FEED pushbutton switch. If, after 3 seconds, the creaw did not release the AC ESS pushbutton switch, the auto switching system is set on. When the crew releases the AC ESS FEED pushbutton switch, the white ALTN legend comes on (the FAULT legend stays on if the AC ESS bus stays not supplied). On the lower ECAM DU, the AC ESS becomes green again and the synoptic is modified.

AES

24-25-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR13 FR15

812

A 106VU 3XC

A B FR16 FR9

B

N_MM_242500_0_AAM0_01_00

AES

FIGURE 24-25-00-12400-A SHEET 1 AC Essential Generation Switching - Component Location

24-25-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A 11XC

PANEL 35VU DC BUS 1

1

BAT 1

BAT

2

FAULT

FAULT

OFF

OFF

V

35VU

BAT 2

DC BUS 2 AC ESS FEED V

FAULT

GALLEY

E L E C

FAULT OFF

A U T O

AC BUS 1

AC BUS 2

BUS TIE

IDG 1

FAULT

ALTN

AC ESS BUS

A U T O

IDG 2 EXT PWR

GEN 2

FAULT

AVAIL

FAULT

OFF

ON

OFF

GEN 1

APU GEN

FAULT OFF

OFF

E L E C

FAULT

N_MM_242500_0_ACM0_01_00

AES

FIGURE 24-25-00-12500-A SHEET 1 AC Essential Generation Switching - Component Location

24-25-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 801PP

APU START 49 − 42 − 00

5KA

10KA

28VDC 6XE

6KA

4PB2

5PB2

DC BUS 1

1PP

4PB1 BAT BUS

1PC1

28VDC

401PP

704PP BAT2 2PB2

6PB2

701PP

SHUNT 3PB2 24 − 67 − 00

703PP BAT1 2PB1

6PB1 3PP

206PP

6PN 3PN2

SHUNT

1PN2

3PB1

DC BUS 2

1PC2

DC ESS BUS

4PC

208PP

12PB1 5PB1

101PP

8PH

20PC 702PP

12PB2

1PB1 BCL−1

103PP

1PN1

8PP

CSM/G CONTROL UNIT

1PB2 BCL−2

3PN1

DC SHED ESS BUS

301PP

11PB

24 − 28 − 00

204PP

601PP

202PP

602PP

2PP 7PN

28VDC

28VDC

4PP 28VDC 24 − 67 − 00

DC SVCE BUS

8PN

6PP 28VDC

3PX

24 − 62 − 00 24 − 28 − 00

5PU1

5PU2

801XP AC SHED ESS BUS 8XP

1PX 24 − 50 − 00

115VAC 8XH

1PU1 TR1

5XH

5XN2

401XP

AC ESS BUS

24 − 50 − 00

AC BUS 1

1XP 115VAC

231XP−A

26V 15XN2

204XP

3XN2

115VAC 4XP

202XP

1XN2

2XC

1XC

1PE ESS TR

1PU2 TR2

210XP

7XN2

431XP−A

26V

4XH

2PU1

3PE

AC BUS 2

4XX

214XP

2XP 14PU

115VAC 3xc1 3XC 3xc2

4PE

24 − 50 − 00 15XE

24 − 28 − 00

GLC−1 9XU1

BTC−1 11XU1

EPC 3XG

GLC−APU 3XS

1XX

BTC−2 11XU2

GLC−2 9XU2

AES

GEN 1

4000XU

GCU−APU 1XS

FIGURE 24-25-00-13800-C SHEET 1 Loss of AC Normal BUS 1XP - Block Diagram Control and Indicating Circuits

GLC−EMERG 2XE

24 − 42 − 00 24 − 50 − 00

FUEL PUMPS 28 − 21 − 00 GCU−1 1XU1

14XX

APU GEN

8XS

GPCU 1XG

24-25-00 PB001

EXTERNAL POWER RECEPTACLE

Page 6 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_242500_0_AEL0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 801PP

APU START 49 − 42 − 00

CSM/G CONTROL UNIT 5KA

10KA

6KA

6XE

DC BUS 1

4PB1

1PP

BAT BUS

1PC1

28VDC

8PH 401PP

702PP 704PP

12PB2

208PP BAT2 2PB2 701PP

12PB1

703PP

5PB1

101PP

1PN1

20PC

5PB2

4PB2 6PB2 1PB1 BCL−1

103PP

8PP 28VDC

1PB2 BCL−2

3PN1

DC SHED ESS BUS

301PP

11PB

6PB1 3PP

SHUNT 3PB2 24 − 67 − 00

206PP

6PN 3PN2

BAT1 2PB1

SHUNT

1PN2

3PB1

DC BUS 2

1PC2

4PC

DC ESS BUS

24 − 28 − 00

204PP

601PP

202PP

602PP

2PP 7PN

28VDC

28VDC

4PP 28VDC 24 − 67 − 00

DC SVCE BUS

8PN

6PP 28VDC

3PX

24 − 62 − 00 24 − 28 − 00

5PU1

5PU2

801XP

1PX

AC SHED ESS BUS 8XP 8XH

1PU1 TR1

4XH

24 − 50 − 00

115VAC

7XN2

431XP−A

26V 5XH

5XN2

401XP

AC ESS BUS

24 − 50 − 00

AC BUS 1

1XP 115VAC

231XP−A

26V 15XN2

4XP

204XP 202XP

1XN2

2XC

1XC

1PE ESS TR

1PU2 TR2

210XP

21XN2

3XN2

115VAC 2PU1

3PE

AC BUS 2

4XX

16XX

214XP

2XP 14PU

115VAC 3xc1 3XC 3xc2

4PE

24 − 50 − 00 15XE

24 − 28 − 00

GLC−1 9XU1

BTC−1 11XU1

GLC−APU 3XS

AES

GEN 1

4000XU

GCU−APU 1XS

GLC−2 9XU2

14XX

GLC−EMERG 2XE

24 − 42 − 00 24 − 50 − 00

FUEL PUMPS 28 − 21 − 00 GCU−1 1XU1

1XX

BTC−2 11XU2

EPC 3XG

APU GEN

FIGURE 24-25-00-13800-F SHEET 1 Loss of AC Normal BUS 1XP - Block Diagram Control and Indicating Circuits

8XS

GPCU 1XG

EXTERNAL POWER RECEPTACLE

24-25-00 PB001

Page 7 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_242500_0_AER0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC ESSENTIAL GENERATION SWITCHING ADJUSTMENT/TEST ** On A/C ALL Task 24-25-00-710-001-A Operational Test of the AC Essential-Generation Switching 1.

Reason for the Job (Ref. MPD 24-25-00-01-) OPERATIONAL CHECK OF AC ESS GENERATION SWITCHING Make sure that the AC ESS and AC SHED ESS busbars can be energized with the AC2 normal busbar when the AC1 busbar is no longer energized.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS

210

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

3.

Job Set-up Subtask 24-25-00-860-050-A A.

AES

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

24-25-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-25-00-865-050-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

106VU

DESIGNATION AC ESS BUS/STBY/CNTOR/CTL

FIN

LOCATION

5XC

B08

106VU

AC ESS/BUS NORM/CNTOR/CTL

4XC

B03

122VU

ELEC/AC/BUS1/CTL

17XN1

V25

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

Subtask 24-25-00-865-051-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

122VU

DESIGNATION ANTI ICE/PROBES/2/PITOT

3DA2

Y14

122VU

ANTI ICE/PROBES/3/PITOT

3DA3

Z16

122VU

ANTI ICE/PROBES/1/TAT

1DA1

Z12

4.

FIN

LOCATION

Procedure ** On A/C 003-003 PRE SB 24-1120 FOR A/C 003-003 Subtask 24-25-00-710-050-A A.

Operational Test of the AC Essential-Generation Switching

ACTION 1.On the ECAM control panel: . Push the ELEC key.

2.On the AC power center 123VU: . Open the circuit breaker 1XC.

RESULT On the ECAM DU, on the ELEC page: . A green bar comes into view between the AC1 and AC ESS busbars. This shows that the AC1 busbar energizes the AC ESS busbar. On the F/O glareshield panel 130VU: . The MASTER legend light of the F/O master caution pushbutton switch comes on. You can hear the single chime.

3.On the ELEC panel 35VU: . Release the AC ESS FEED pushbutton switch.

AES

The indications: ELEC AC ESS BUS FAULT then AC ESS FEED... ALTN is shown on the ECAM DU. On the ELEC panel 35VU: . The FAULT legend of the AC ESS FEED pushbutton switch comes on. On the ELEC panel 35VU: . The FAULT legend of the AC ESS FEED pushbutton switch goes off. . The ALTN legend of the AC ESS FEED pushbutton switch comes on.

24-25-00 PB501

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 4.On the ECAM control panel: . Push the ELEC key.

5.On the AC power center 123VU: . Close the circuit breaker 1XC. 6.On the ELEC panel 35VU: . Push the AC ESS FEED pushbutton switch.

RESULT On the ECAM DU, on the ELEC page: . A green bar comes into view between the AC2 and AC ESS busbars. This shows that the AC2 busbar energizes the AC ESS busbar. . The green bar between the AC1 and AC ESS busbars goes out of view.

On the ELEC panel 35VU: . The ALTN legend of the AC ESS FEED pushbutton switch goes off. On the ELEC page: . The green bar between the AC2 and AC ESS busbars goes out of view. . The green bar between the AC1 and AC ESS busbars comes into view.

** On A/C 004-099 EMB SB 24-1120 FOR A/C 004-008 POST SB 24-1120 FOR A/C 003-003 Subtask 24-25-00-710-050-B A.

Operational Test of the AC Essential-Generation Switching

ACTION 1.On the ECAM control panel: . Push the ELEC key.

2.On the AC power center 123VU: . Open the circuit breaker 1XC.

RESULT On the ECAM DU, on the ELEC page: . A green line comes into view between the AC1 and AC ESS busbars. This shows that the AC1 busbar energizes the AC ESS busbar. On the F/O glareshield panel 130VU: . The MASTER legend light of the F/O master-caution pushbutton switch comes on. You can hear the single chime.

3.On the rear circuit-breaker panel 122VU: . Open the circuit breaker 17XN1. . Wait 3 seconds to let the auto switching system set on. 4.On the ECAM control panel: . Push the ELEC key.

AES

The indications ELEC AC ESS BUS FAULT then AC ESS FEED... ALTN are shown on the ECAM DU. On the ELEC panel 35VU: . The FAULT legend of the AC ESS FEED pushbutton switch comes on. On the ELEC panel 35VU: . The FAULT legend of the AC ESS FEED pushbutton switch goes off. . The ALTN legend of the AC ESS FEED pushbutton switch stays off. On the ECAM DU, on the ELEC page: . A green line comes into view between the AC2 and AC ESS busbars. This shows that the AC2 busbar energizes the AC ESS busbar. . The green line between the AC1 and AC ESS busbars goes out of view.

24-25-00 PB501

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 5.On the EMER ELEC PWR section of the panel 21VU : . Lift the safety guard. . Push and hold the EMER GEN TEST pushbutton switch. 6.On the AC power-center 123VU: . Close the circuit breaker 1XC. 7.On the rear circuit-breaker panel 122VU: . Close the circuit breaker 17XN1. 8.On the EMER ELEC PWR section of the panel 21VU: . Release the EMER GEN TEST pushbutton switch.

RESULT On the ECAM DU, on the ELEC page: . The AC2 busbar energizes the AC ESS busbar.

On the ECAM DU, on the ELEC page: . The AC2 busbar continues to supply the AC ESS busbar. On the EMER ELEC PWR section of the panel 21VU: . Make sure that the safety guard is back in position. On the ECAM DU, on the ELEC page: . The green line between the AC2 and the AC ESS busbars goes out of view. . The green line between the AC1 and the AC ESS busbars comes into view. This shows that the AC1 busbar energizes the AC ESS busbar.

9.On the AC power-center 123VU: . Open the circuit breaker 1XC.

On the F/O glareshield panel 130VU: . The MASTER legend light of the F/O master caution pushbutton switch comes on. You can hear the single chime.

10.On the ELEC panel 35VU: . Release the AC ESS FEED pushbutton switch.

11.On the ECAM control panel: . Push the ELEC key.

12.On the AC power center 123VU. . Close the circuit breaker 1XC. 13.On the ELEC panel 35VU: . Push the AC ESS FEED pushbutton switch.

The indications ELEC AC ESS BUS FAULT then AC ESS FEED... ALTN is shown on the ECAM DU. On the ELEC panel 35VU: . The FAULT legend of the AC ESS FEED pushbutton switch comes on. On the ELEC panel 35VU: . The FAULT legend of the AC ESS FEED pushbutton switch goes off. . The ALTN legend of the AC ESS FEED pushbutton switch comes on. On the ECAM DU, on the ELEC page: . A green line comes into view between the AC2 and AC ESS busbars. This shows that the AC2 busbar energizes the AC ESS busbar. . The green line between the AC1 and AC ESS busbars goes out of view.

On the ELEC panel 35VU: . The ALTN legend of the AC ESS FEED pushbutton switch goes off. On the ELEC page: . The green line between the AC2 and AC ESS busbars goes out of view. . The green line between the AC1 and AC ESS busbars comes into view.

AES

24-25-00 PB501

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up ** On A/C ALL Subtask 24-25-00-865-052-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

122VU

DESIGNATION ANTI ICE/PROBES/2/PITOT

FIN

LOCATION

3DA2

Y14

122VU

ANTI ICE/PROBES/3/PITOT

3DA3

Z16

122VU

ANTI ICE/PROBES/1/TAT

1DA1

Z12

Subtask 24-25-00-860-051-A B.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-25-00 PB501

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-25-55-000-001-A Removal of the AC Essential Bus Switching Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 3XC 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

B.

CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS

125 812

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE (Ref. Fig. 24-25-55-991-00100-A - Contactor) 3.

DESIGNATION

Job Set-up Subtask 24-25-55-941-051-A A.

AES

Safety Precautions (1)

In . . .

the cockpit, on the overhead panel 35VU, make sure these pushbutton switches are released: BAT 1, BAT 2, GEN 1, GEN 2, EXT A.

(2)

In the cockpit, put a warning notice to tell persons not to operate the pushbutton switches on these panels of the overhead panels: . 35VU (ELEC), . 21VU (EMER ELEC PWR).

(3)

Make sure that the external power connector is not connected to the aircraft receptable EXT PWR A.

(4)

Put a warning notice on the access door 121AL to tell persons not to connect the external power connector.

24-25-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-25-55-010-050-A B.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 812.

(2)

Open the access door 812.

(3)

Remove the access door (14) from the panel 106VU.

Subtask 24-25-55-865-052-A C.

Open, safety and tag this(these) circuit breaker(s):

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-25-55-991-00100-A - Contactor) Subtask 24-25-55-020-050-A A.

Removal of the Contactor (1)

Disconnect the two electrical connectors (1, 2).

(2)

Put CAP - BLANKING on the electrical connectors (1, 2) and the electrical receptacles (12, 13)

(3)

Loosen the 9 nuts (3).

(4)

Remove the 9 nuts (3), the spring washers (4) and the plates (5) and (10).

(5)

Remove the electrical wires: CAUTION :

(a)

AES

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Remove the electrical power supply wires (6).

(6)

Loosen the 4 nuts (7).

(7)

Hold the contactor (8).

(8)

Remove the 4 nuts (7) and the washers (9).

(9)

Remove the contactor (8).

24-25-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 106VU 3XC

A

14 FR16

FR12 812

B

13 12 106VU 11 (1.2)

9

6

10

4

3

8 7 6 5 4 3 N_MM_242555_4_AAM0_01_00

AES

FIGURE 24-25-55-991-00100-A SHEET 1 Contactor

24-25-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-25-55-400-001-A Installation of the AC Essential Bus Switching Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 3XC 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

No specific

B.

WARNING NOTICE(S) Torque wrench: range to between 0.00 and 1.20 M.DAN (0.00 and 9.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

125 812

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-25-00-710-001-A

DESIGNATION Operational Test of the AC Essential-Generation Switching

(Ref. Fig. 24-25-55-991-00100-A - Contactor) 3.

Job Set-up Subtask 24-25-55-860-050-A A.

AES

Aircraft Maintenance Configuration (1)

In . . .

the cockpit, on the overhead panel 35VU, make sure that these puhbutton switches are released: BAT 1, BAT 2, GEN 1, GEN 2, EXT A.

(2)

In the cockpit, make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the pushbutton switches on these panels of the overhead panels: . 35VU (ELEC), . 21VU (EMER ELEC PWR).

(3)

Make sure that the external power connector is not connected to the aircraft receptable EXT PWR A.

(4)

On the access door 121AL, make sure that the WARNING NOTICE(S) is in position to tell persons not to connect the external power connector.

(5)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 812.

(6)

Make sure that the access door 812 is open.

24-25-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (7)

In the avionics compartment, make sure that the access door (14) is removed from the panel 106VU.

Subtask 24-25-55-865-050-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-25-55-991-00100-A - Contactor) Subtask 24-25-55-420-050-A A.

Installation of the Contactor (1)

Clean the component interface and/or the adjacent area.

(2)

Do an inspection of the component interface and/or the adjacent area.

(3)

Put the contactor (8) in position on the studs (11).

(4)

Install the washers (9) and the nuts (7), then tighten the nuts.

(5)

Install the electrical wires: CAUTION :

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(a)

Install the electrical power-supply wires (6).

(b)

Install the plates (5) and (10), the spring washers (4) and the nuts (3),

(c)

TORQUE the nuts (3) to between 0.147 and 0.176 M.DAN (13.01 and 15.58 LBF.IN).

(6)

Remove the blanking caps from the electrical connector(s).

(7)

Make sure that the electrical connectors are clean and in the correct condition.

(8)

Connect the 2 electrical connectors (1, 2).

Subtask 24-25-55-865-051-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

AES

FIN

LOCATION

24-25-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-25-55-710-050-A C. 5.

Do an operational test of the AC essential generation switching (Ref. TASK 24-25-00-710-001-A).

Close-up Subtask 24-25-55-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the access door (14) on the panel 106VU.

(3)

Remove the warning notice(s).

(4)

Close the access door 812.

(5)

Remove the access platform(s).

24-25-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

GALLEY SUPPLY CONTROL - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The galley assembly is divided into several parts: . Aft galley, . Forward galley. NOTE :

For some more information (Ref. 24-56-00-00).

** On A/C 005-099 Furthermore, the galley supply control powers two AC and DC sheddable busbars.

AES

24-26-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location

** On A/C 003-004 (Ref. Fig. 24-26-00-12500-A - Galley Supply Control - Component Location) ** On A/C 005-099 (Ref. Fig. 24-26-00-12500-B - Galley Supply Control - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS ATA REF. DOOR

** On A/C ALL 2XA

AES

P/BSW-ELEC/GALLEY

35VU

210

24-26-00 PB001

24-26-00

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description

** On A/C 003-004 (Ref. Fig. 24-26-00-13800-E - Galley Supply Control - Block Diagram) ** On A/C 005-099 (Ref. Fig. 24-26-00-13800-N - Galley Supply Control - Block Diagram) ** On A/C 003-004 The galley general supply is controlled from flight compartment overhead panel 35VU by means of GALLEY pushbutton switch (normal operation when the pushbutton is pressed in). ** On A/C 005-099 If the OFF legend of COMMERCIAL pushbutton switch (commercial load shed) is off (pushbutton switch pressed in), galley general supply can be controlled from flight compartment overhead panel 35VU by means of GALLEY pushbutton switch (normal operation when the pushbutton is pressed in).

AES

24-26-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Operation/Control and Indicating A.

Galley Automatic Shedding ** On A/C 003-004 (Ref. Fig. 24-26-00-13800-E - Galley Supply Control - Block Diagram) If only one generator is available, galley(s) (primary feeders controlled by the relay 6XA) is(are) automatically shedded. White GALLEY SHED indication appears on the ELEC page of the lower ECAM display unit (no light on GALLEY pushbutton switch). ** On A/C 005-099 (Ref. Fig. 24-26-00-13800-N - Galley Supply Control - Block Diagram) If only one generator is available, galley(s) (primary feeders controlled by the relay 6XA) and sheddable busbars (controlled by the relay 10XA) are automatically shedded. White GALLEY SHED indication appears on the ELEC page of the lower ECAM display unit (no light on GALY & CAB pushbutton switch).

** On A/C ALL B.

Overload detected by a GCU ** On A/C 003-004 (Ref. Fig. 24-26-00-15600-A - Overload - Upper and Lower ECAM Display Unit) If an overload is detected: . amber FAULT legend illuminates on GALLEY pushbutton switch, . auto display of the ELEC page on the lower ECAM display unit, . MASTER CAUT light + single chime + amber message on the upper ECAM display unit confirm the overload. The crew has to release GALLEY pushbutton switch on the UPPER ECAM DU (white OFF legend illuminates). This action results in shedding of all galleys. GALLEY indication is displayed on the lower ECAM DU, STATUS page. NOTE :

On ground, it is possible to supply all galleys: . either with the APU GEN: If I > 277 A, galleys automatic shedding, . or with the EXT PWR: without galleys automatic shedding.

** On A/C 005-099 (Ref. Fig. 24-26-00-15600-A - Overload - Upper and Lower ECAM Display Unit) If an overload is detected: . amber FAULT legend illuminates on GALY & CAB pushbutton switch, . auto display of the ELEC page on the lower ECAM display unit, . MASTER CAUT light + single chime + amber message on the upper ECAM display unit confirm the overload. The crew has to release GALY & CAB pushbutton switch on the panel 35VU (white OFF legend illuminates). This action results in shedding of all the galleys and the sheddable busbars 218XP, 220XP, 210PP and 212PP. GALLEY indication is displayed on the lower ECAM DU, STATUS page. NOTE :

AES

On ground, it is possible to supply all galleys: . either with the APU GEN: If I > 277 A, galleys automatic shedding, . or with the EXT PWR: without galleys automatic shedding.

24-26-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

A

A PANEL 35VU DC BUS 1

1

BAT 1

BAT 2

FAULT

FAULT

OFF

OFF

V

35VU

BAT 2

DC BUS 2 AC ESS FEED V

FAULT

GALLEY

2XA

E L E C

FAULT OFF

A U T O

AC BUS 1

AC BUS 2

BUS TIE

IDG 1 FAULT

ALTN

AC ESS BUS

A U T O

IDG 2 EXT PWR

GEN 2

FAULT

AVAIL

FAULT

OFF

ON

OFF

GEN 1

APU GEN

FAULT OFF

OFF

E L E C

FAULT

N_MM_242600_0_AAM0_01_00

AES

FIGURE 24-26-00-12500-A SHEET 1 Galley Supply Control - Component Location

24-26-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

A

A PANEL 35VU DC BUS 1

1

BAT 1

2XA

E L E C

2

FAULT

FAULT

OFF

OFF

V GALY & CAB A FAULT U T O OFF

BAT

AC BUS 1

DC BUS 2 AC ESS FEED V

FAULT ALTN

AC ESS BUS

AC BUS 2

BUS TIE

IDG 1

FAULT

35VU

BAT 2

A U T O

IDG 2 EXT PWR

GEN 2

FAULT

AVAIL

FAULT

OFF

ON

OFF

GEN 1

APU GEN

FAULT OFF

OFF

E L E C

FAULT

N_MM_242600_0_AAP0_01_00

AES

FIGURE 24-26-00-12500-B SHEET 1 Galley Supply Control - Component Location

24-26-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

FAULT OFF

601PP 28VDC SVCE BUS

TO CNTOR 15MC

+28VDC FROM 601PP

TO CNTOR 17MC

1XA 2XA P/BSW ELEC/PWR/GALLEY

9XA GALLEY SPLY CTL TO CNTOR 5MC

+28VDC FROM 601PP

TO CNTOR 13MC TO CNTOR 6MC TO CNTOR 4MC

4XA GND FAIL MONG

5XA GALLEY SPLY CTL

6XA MAIN GALLEY SPLY CTL

BTC−1

BTC−2

EPC

3XA GND/FLT CONDITION

GLC−APU

N_MM_242600_0_ABSE_01_00

AES

FIGURE 24-26-00-13800-E SHEET 1 Galley Supply Control - Block Diagram

24-26-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

OFF 601PP 28VDC SVCE BUS

TO CNTOR 27XN

+28VDC FROM 202PP

TO CNTOR 10PN

1PC2

1XA 22XN P/BSW ELEC/COMMERCIAL

FAULT OFF

10XA SHED BUS SPLY CTL TO CNTOR 15MC

+28VDC FROM 601PP

2XA P/BSW ELEC/GALY & CAB

TO CNTOR 17MC

9XA GALY & CAB SPLY CTL TO CNTOR 5MC

+28VDC FROM 601PP

TO CNTOR 13MC TO CNTOR 6MC TO CNTOR 4MC

4XA GND FAIL MONG

5XA GALLEY SPLY CTL

6XA MAIN GALLEY SPLY CTL

BTC−1

BTC−2

EPC

3XA GND/FLT CONDITION

GLC−APU N_MM_242600_0_ACE0_01_00

AES

FIGURE 24-26-00-13800-N SHEET 1 Galley Supply Control - Block Diagram

24-26-00 PB001

Page 8 May 01/12 Revision n˚: 40

AES

FIGURE 24-26-00-15600-A SHEET 1 Overload - Upper and Lower ECAM Display Unit

ACTION ON CLEAR P/BSW (ON ECAM CP)

− RELEASED − OUT GALLEY P/BSW

MANUAL CREW ACTION

ALL THE GALLEY ARE SHEDDED

OVERLOAD ON GEN 1, GEN 2 OR APU GEN

CONFIG. SYSTEM

24-26-00 PB001 WHITE OFF"

OFF

FAULT

GALLEY

WHITE OFF"

OFF

FAULT

GALLEY

AMBER FAULT"

OFF

FAULT

GALLEY

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

GEN 1 OVERLOAD

STS

NORMAL CONFIG.

NORMAL CONFIG.

GALLEY.................OFF

ELEC

ECAM UPPER DISPLAY

OVERLOAD (CLASS 1 − LEVEL 2)

STATUS SYS: GALLEY

INOP

SEE TWO PAGES FARTHER

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_242600_0_ACM0_01_00

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT

BAT 1

DC BAT

28V

2

28V

0A

0A

DC

DC 1 DC

28V

ESS

ESS

EMER

TR

GEN

28V 82A

110A

AC 1

GEN

AC

ESS

APU

GEN

400HZ IDG 1

AC

2

GEN

1

120% 116V

2

°C 1 1 0

2

00% 116V

400HZ 1 1 0°C

IDG 2

4WT2 DU − ECAM LOWER

N_MM_242600_0_ACM0_02_00

AES

FIGURE 24-26-00-15600-A SHEET 2 Overload - Upper and Lower ECAM Display Unit

24-26-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

BAT 1 28 V 0A

ELEC

BAT 2 28 V 0A

DC BAT

DC 2

DC 1 DC ESS

ESS TR

28V 110A

EMER

AC ESS

AC 1

GEN

1

62%

AC 2

2

00%

APU

400HZ

IDG 1

28V 82A

GEN

GALLEY SHED

116V

GEN

°C 1 1 0

GEN

116V 400HZ

1 1 0°C IDG 2

4WT2 DU − ECAM, LOWER

N_MM_242600_0_ACM0_03_00

AES

FIGURE 24-26-00-15600-A SHEET 3 Overload - Upper and Lower ECAM Display Unit

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

GALLEY SUPPLY CONTROL - ADJUSTMENT/TEST ** On A/C ALL ** On A/C 003-004 Task 24-26-00-710-001-A Operational Test of the Manual and Automatic Shedding of the Galleys 1.

Reason for the Job (Ref. MPD 24-26-00-01-) OPERATIONAL CHECK OF MANUAL AND AUTOMATIC GALLEY SHEDDING Make sure that the manual and automatic shedding of the galleys operates.

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

210

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

B.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

ASM 24-56/01 3.

Job Set-up Subtask 24-26-00-860-050-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits from the external power or from the APU (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALLEY pushbutton switch is pushed (the OFF legend is off).

Subtask 24-26-00-865-050-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

122VU

AES

DESIGNATION ELEC/GALLEY/CTL

FIN 1XA

LOCATION S26

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122VU

PANEL

DESIGNATION ELEC/GALLEY/FAULT/LT CTL

8XA

S25

122VU

ELEC/GALLEY/GND/FLT/LOGIC

7XA

S24

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

4.

FIN

LOCATION

Procedure Subtask 24-26-00-710-050-A A.

Operational Test of the Manual and Automatic Shedding of the Galleys

ACTION 1.On the ECAM control panel: . push the ELEC key to get the ELEC system page.

RESULT On the lower ECAM display unit: . the ELEC page comes into view.

2.On the panel 35VU: . release the GALLEY pushbutton switch.

On the panel 35VU: . the OFF legend of the GALLEY pushbutton switch comes on. On the lower ECAM display unit: . the white GALLEY SHED indication comes into view. In the forward and aft galleys: . make sure that no equipment operates.

3.On the panel 35VU: . push the GALLEY pushbutton switch.

On the panel 35VU: . the OFF legend of the GALLEY pushbutton switch goes off. On the lower ECAM display unit: . the white GALLEY SHED indication goes out of view. In the forward and aft galleys: . make sure that all the galley equipment operate.

4.On the panel 122VU: . open the circuit breaker 7XA.

On the lower ECAM display unit, on the ELEC page: . the white GALLEY SHED indication comes into view. In the forward and aft galleys: . when items of equipment are installed in the galleys (Ref. ASM 24-56/01), make sure that only the galleys supplied by the contactor 5MC operate.

5.On the ECAM control panel: . push the STS key to get the STATUS page, INOP SYS section. 6.On the panel 122VU: . close the circuit breaker 7XA. 7.On the ECAM control panel: . push the ELEC key to get the ELEC system page.

On the lower ECAM display unit: . the MAIN GALLEY indication comes into view.

On the lower ECAM display unit: . the GALLEY SHED indication goes out of view. In the forward and aft galleys: . make sure that all the galley equipment operate.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-26-00-860-051-A A.

AES

Put the aircraft back to its initial configuration. (1)

De-energize the aircraft electrical circuits supplied from the external power or from the APU (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

(2)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-26-00-710-002-A Operational Test of the Manual and Automatic Galley and Bus Shedding 1.

Reason for the Job (Ref. MPD 24-26-00-02-) OPERATIONAL CHECK OF MANUAL AND AUTOMATIC GALLEY AND BUS SHEDDING

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

210

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

B.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

ASM 24-56/01 3.

Job Set-up Subtask 24-26-00-860-054-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits from the external power or from the APU (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALY & CAB pushbutton switch is pushed (the OFF legend is off).

Subtask 24-26-00-865-052-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

122VU

DESIGNATION ELEC/GALY & CAB/CTL

1XA

S26

122VU

ELEC/GALY & CAB/FAULT/LT CTL

8XA

S25

122VU

ELEC/GALY & CAB/GND/FLT/LOGIC

7XA

S24

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

AES

FIN

LOCATION

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure Subtask 24-26-00-710-052-B A.

Operational Test of the Manual and Automatic Galley and Bus Shedding

ACTION 1.On the ECAM control panel: . push the ELEC key to get the ELEC page.

RESULT On the lower ECAM display unit: . the ELEC page comes into view.

2.On the panel 35VU: . release the GALY & CAB pushbutton switch.

On the panel 35VU: . the OFF legend of the GALY & CAB pushbutton switch comes on. On the lower ECAM display unit: . the white GALLEY SHED indication comes into view. In the forward and aft galleys: . make sure that no galley equipment operates.

3.On the panel 35VU: . push the GALY & CAB pushbutton switch.

On the panel 35VU: . the OFF legend of the GALY & CAB pushbutton switch goes off. On the lower ECAM display unit: . the white GALLEY SHED indication goes out of view. In the forward and aft galleys: . make sure that all the galley equipment operates.

4.On the panel 122VU: . open the circuit breaker 7XA.

On the lower ECAM display unit, on the ELEC page: . the white GALLEY SHED indication comes into view. In the forward galleys: . When items of equipment are installed in the galleys (Ref. ASM 24-56/01), make sure that only the galleys supplied by the contactor 5MC operate. In the aft galleys: . When items of equipment are installed in the galleys (Ref. ASM 24-56/01), make sure that only the galleys supplied by the contactor 13MC operate.

5.On the ECAM control panel: . push the STS key to get the STATUS page. 6.On the panel 122VU: . close the circuit breaker 7XA. 7.On the ECAM control panel: . push the ELEC key to get the ELEC page.

On the lower ECAM display unit: . the MAIN GALLEY indication comes into view in the INOP SYS item.

On the lower ECAM display unit: . the GALLEY SHED indication goes out of view. In the forward and aft galleys: . make sure that all the galley equipment operates.

5.

Close-up Subtask 24-26-00-860-055-A A.

Put the aircraft back to its initial configuration. (1)

AES

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

AES

De-energize the aircraft electrical circuits supplied from the external power or from the APU (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-26-00 PB501

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC GENERATION MONITORING AND INDICATING DESCRIPTION AND OPERATION ** On A/C ALL 1.

General Monitoring and indicating of the Alternating Current (AC) generation and distribution is done with the Electronic Centralized Aircraft Monitoring (ECAM) system which displays the electrical parameters related to: . the two Integrated Drive Generators (IDG)s, . the Auxiliary Power Unit (APU) generator, . the Constant Speed Motor/Generator (CSM/G), (emergency generator), . the static inverter, . the electrical ground power unit.

AES

24-27-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

System Description (Ref. Fig. 24-27-00-12300-A - AC Generation Monitoring and Indicating - ECAM) The following AC electrical parameters are shown on the ELEC page of the lower ECAM Display Unit: . the oil outlet temperatures, the low oil pressure indication and the disconnection status of each IDG, . the voltage, frequency and nominal load in percentage of each main generator and APU generator, . the status of the AC normal and essential busbars, . the status of the galleys and the commercial loads; the ECAM also gives a synoptic of the AC generation system which tells the flight crew what is the electrical configuration, . the voltage and frequency of the ground power unit, the emergency generator and the static inverter.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

Operation/Control and Indicating A.

Operation The ELEC page on the lower ECAM Display Unit is shown: . either automatically after a class 1 failure on the AC network (if requested by the Flight Warning System (FWS)), . or manually if the ELEC page is selected on the ECAM control panel (Ref. 31-56-00).

B.

Description (Ref. Fig. 24-27-00-12300-A - AC Generation Monitoring and Indicating - ECAM) For more information, refer to 31-67-24.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

ELEC

BAT 1 28 V 20 A

DC BAT

BAT 2 28 V 0A

DC 1

DC 2 DC ESS

TR 1 28 V 75 A

ESS TR

AC 1 GEN 1 26 % 1 16 V 4 0 0 HZ

TR 2 28 V 60 A

EMERG GEN

AC 2

AC ESS APU GEN

90 °C IDG 1 TAT +19 °C SAT +18 °C

GEN 2 26 % 116 V 4 0 0 HZ IDG 2

80 °C

G.W. 60 3 T C.G. 28 1 %

4WT2 DU−ECAM,LOWER

N_MM_242700_0_AAM0_01_00

AES

FIGURE 24-27-00-12300-A SHEET 1 AC Generation Monitoring and Indicating - ECAM

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC GENERATION MONITORING AND INDICATING ADJUSTMENT/TEST ** On A/C ALL Task 24-27-00-710-001-A Operational Test of the GEN FAULT Warning 1.

Reason for the Job Make sure that the GEN FAULT warning is operative when there are no more indications on the ECAM ELEC page.

2.

Job Set-up Information A.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

3.

Job Set-up Subtask 24-27-00-860-050-A A.

4.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

In the cockpit, on the overhead panel 35VU, make sure that the GEN1 (2) pushbutton switch is released.

Procedure Subtask 24-27-00-710-050-A A.

Operational Test of the GEN FAULT Warning: ACTION

1.On the panel 35VU: . push the GEN1(2) pushbutton switch. 2.On the panel 35VU: . release the GEN1(2) pushbutton switch.

AES

RESULT On the panel 35VU: . the FAULT legend of the GEN1(2) pushbutton switch comes on. On the panel 35VU: . the FAULT legend of the GEN1(2) pushbutton switch goes off, . the OFF legend of the GEN1(2) pushbutton switch comes on.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-27-00-862-050-A A.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-27-00 PB501

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-27-00-710-002-A Operational Test of the Automatic Galley Shedding 1.

Reason for the Job Make sure that the automatic galley shedding is operative when there are no more indications on the ECAM ELEC page.

2.

Job Set-up Information A.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

3.

Job Set-up Subtask 24-27-00-860-051-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits from the APU (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

In the cockpit, on the overhead panel 35VU, make sure that the GALLEY pushbutton switch is pushed (the OFF legend is off).

(3)

In the forward and aft galleys, make sure that all the units operate.

Subtask 24-27-00-865-050-A B.

Make sure that this(these) circuit breaker(s) is(are) closed:

PANEL ** On A/C 003-004

DESIGNATION

FIN

LOCATION

122VU

ELEC/GALLEY/CTL

1XA

S26

122VU

ELEC/GALLEY/FAULT/LT CTL

8XA

S25

122VU

ELEC/GALLEY/GND/FLT/LOGIC

7XA

S24

122VU

ELEC/GALY & CAB/CTL

1XA

S26

122VU

ELEC/GALY & CAB/FAULT/LT CTL

8XA

S25

122VU

ELEC/GALY & CAB/GND/FLT/LOGIC

7XA

S24

** On A/C 005-099

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure ** On A/C ALL Subtask 24-27-00-710-051-A A.

Operational Test of the Automatic Galley Sheeding:

ACTION 1.On the panel 122VU: . open the circuit breaker 7XA. 5.

RESULT In the forward and aft galleys: . make sure that only the secondary units operate.

Close-up Subtask 24-27-00-862-051-A A.

AES

De-energize the aircraft electrical circuits supplied from the APU. (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

STATIC INVERTER - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The 1000 VA nominal-power static inverter transforms the direct current voltage from battery 1 into a single-phase 115 VAC/400 Hz alternating current.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-28-00-12300-B - Contactor and Fuse - Component Location) (Ref. Fig. 24-28-00-12400-A - Static Inverter - Component Location) FIN

ZONE ACCESS ATA REF. DOOR 2XB CNTOR-STAT INV 105VU 126 24-28-55 3XB STAT INV 126 24-28-51 ------------------------------------------------------------------------------FIN ! FUNCTIONAL DESIGNATION ! PANEL!ZONE!ACCESS ! ATA ! ! ! ! DOOR ! REF. _______________________________________________________________________________ 5XB HOLDER-FUSE 105VU 126 822 24-28-00 5XB1 FUSE-AC STAT INV BUS SPLY 105VU 126 822 24-28-00

AES

FUNCTIONAL DESIGNATION

PANEL

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description

** On A/C 003-004 The static inverter starts to operate automatically in the conditions that follow: . APU start (supply of fuel pump) . Battery supplies the engine ignition system (in emergency configuration) . Ram Air Turbine (RAT) deployment (< 10s) (supply of ECAM display units) . On ground, on batteries only (pushbutton switch supply) . In emergency configuration with landing gear extended (the 115 VAC ESS BUS 4XP is supplied, the CSM/G is not supplied). ** On A/C 005-099 The static inverter starts to operate automatically in the conditions that follow: . APU start (supply of fuel pump) . Battery supplies the engine ignition system (in emergency configuration) . Ram Air Turbine (RAT) deployment (< 10s) (supply of ECAM display units), . On ground, on batteries only (pushbutton switch supply) . In emergency configuration after landing, when the CSM/G is switched off (the 115 VAC ESS BUS 4XP is supplied, the CSM/G is not supplied).

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Operation/Control and Indicating (Ref. Fig. 24-28-00-14900-A - Static Inverter - Schematic Diagram) The static inverter starts automatically if: . the AC BUS 1 and 2 are lost, . the CSM/G is not available, and . speed is more than 50 Kts. When the static inverter is faulty, it generates a permanent ground signal to the BCL1. The presence of the ground signal means: . overheat, . output overvoltage, . input undervoltage, . input overvoltage. The static inverter defect is sent to the battery charge limiter 1 which stores it in a memory as a class I failure. When the network is supplied, STATIC INV FAULT message appears on the upper ECAM display unit. The fault indication will be available during BCL BITE reading from the Centralized Fault Display System (CFDS).

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 5.

Test On the ground, the static inverter can be checked applying the following procedure (aircraft supplied by EXT POWER or APU GEN): . EMER GEN TEST: ON . BUS TIE: OFF . On the ECAM ELEC page, check voltage and frequency of static inverter.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

822

A 105VU

A FR16 FR16 FR9

5XB

B C 2XB

C

5XB1 5XB

B

CONTACTOR BASE

CONTACTOR N_MM_242800_0_AAL0_01_00

AES

FIGURE 24-28-00-12300-B SHEET 1 Contactor and Fuse - Component Location

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR15 FR14

A

B

Z126

A

B

3XB

N_MM_242800_0_ACM0_01_00

AES

FIGURE 24-28-00-12400-A SHEET 1 Static Inverter - Component Location

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

4PB21 FUSE

3PB2 2PB2 SHUNT BAT2

3PP 28VDC BAT BUS

901XP 115VAC STAT INV BUS

115VAC

12XB

115VAC 704PP 28VDC HOT BUS

AC RETURN

14XB

6PB2 DC RETURN

STAT INV ON 1WW2 FWC−2 STAT INV ON 1WW1 FWC−1 TO SDAC.1(2)

+28VDC

4PB11 FUSE

3PB1 2PB1 SHUNT BAT1

STAT INV FAULT 5XB1 FUSE

FAULT INDICATOR

1PB1 BCL−1

6PB1

3XB STAT INV

4PP 28VDC DC ESS BUS

6PH1 FUSE

2XB CNTOR

A

B

C 115VAC 4XP

LOSS OF 1XP

LOSS OF 2XP

TO ESS TR VIA C/B 4PE FROM EMER GLC 2XE

23XE P/B EMER ELEC PWR/ EMER GEN TEST

10XE TDC 80ms

15XC (1XP)

V0

50KTS

1FP1 ADIRU1

16XC (2XP)

12XE EMER CONDITION

6XB 15XE(2)

15XE(1) CNTOR

7XB RLY

13XC (3XC1)

14XC (3XC2)

N_MM_242800_0_AEN0_01_00

AES

FIGURE 24-28-00-14900-A SHEET 1 Static Inverter - Schematic Diagram

24-28-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

STATIC INVERTER - ADJUSTMENT/TEST ** On A/C ALL Task 24-28-00-710-001-A Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the External Power 1.

Reason for the Job (Ref. MPD 24-28-00-01-) OPERATIONAL CHECK OF STATIC INVERTER Test of the correct power supply of the DC ESS BUS, AC ESS BUS and AC STAT INV BUS in emergency configuration when the batteries are the only power supply source.

2.

NOTE :

If the external power is not available, there is an alternative method (with the APU) for this procedure. This task gives the first method. For the alternative method, refer to the other task in this page block.

NOTE :

If the external power is available and the APU is in operation, you must refer to the alternative method with the APU to do the operational test of the static inverter.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

210 812, 822 C.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

3.

Job Set-up Subtask 24-28-00-860-050-A A.

AES

Safety Precautions (1)

Do not energize the aircraft electrical circuits.

(2)

On the panel 35VU, make sure that: . the BAT1 and BAT2 pushbutton switches are released,

24-28-00 PB501

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL .

the BUS TIE and AC ESS FEED pushbutton switches are pushed.

NOTE :

On the panel 2000VU, put the MAINT BUS switch (5XX) in the OFF position during the test.

Subtask 24-28-00-010-050-A B.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access doors 812 and 822 of the avionics compartment.

(2)

Open the access doors 812 and 822.

Subtask 24-28-00-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) closed:

105VU

PANEL

DESIGNATION ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/701PP SPLY

5PB1

D01

105VU

ELEC/BAT REF/BCL2

9PB2

F02

105VU

ELEC/BAT REF/BCL1

9PB1

F01

105VU

ELEC/STAT INV/CNTOR/CTL

14XB

G02

105VU

ELEC/STAT INV/BUS 901XP/SPLY

12XB

H02

106VU

AC ESS BUS/EMER/STBY/CNTOR/SPLY

10XE

C06

4.

FIN

LOCATION

Procedure WARNING : TELL ALL THE PERSONS ON THE AIRCRAFT THAT: THE LIGHTS WILL GO OFF DURING THIS TEST THEY MUST NOT MOVE ON THE AIRCRAFT UNTIL THIS TEST IS COMPLETED. IF NOT INJURY AND/OR DAMAGE CAN OCCUR WHEN THE LIGHTS GO OFF SUDDENLY. Subtask 24-28-00-710-050-B A.

Operational Test of the Static Inverter

ACTION 1.On the panel 35VU: . make sure that the voltage of the batteries 1 and 2 is higher than 25.5V.

RESULT

2.Power supply the aircraft electrical circuits: . energize the aircraft electrical circuits from the external power (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02), 3.Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A). 4.On the ECAM control panel: . get the ELEC page.

AES

On the lower ECAM display unit: . make sure that the external power energizes correctly the aircraft electrical circuits.

24-28-00 PB501

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 5.On the panel 35VU: . release the BAT1 pushbutton switch. .

push the BAT1 pushbutton switch.

.

release the BAT2 pushbutton switch.

.

push the BAT2 pushbutton switch.

RESULT On the panel 35VU: . the OFF legend of the BAT1 pushbutton switch comes on. . the OFF legend of the BAT1 pushbutton switch goes off. . the OFF legend of the BAT2 pushbutton switch comes on. . the OFF legend of the BAT2 pushbutton switch goes off. On the lower ECAM display unit: . make sure that the battery charge current (for BAT1 and BAT2) is lower than 60A after approximately 10 seconds. NOTE :

6.On the panel 35VU: . release the BAT1 and BAT2 pushbutton switches. 7.On the panel 21VU, in the section EMER ELEC PWR: . open the guard, push and hold the EMERG GEN TEST pushbutton switch during all the test, .

after 5 seconds, on the panel 35VU, release the BUS TIE pushbutton switch. 8.On the ECAM control panel: . push and hold the ELEC key, the ELEC page comes into view and stays on during the test.

If the current does not decrease after 10 seconds, it is necessary to do a charging cycle of the batteries. When the charging cycle is completed (batteries no longer connected to the DC BAT BUS), do the check again.

On the panel 35VU: . the OFF legend of the BAT1 and BAT2 pushbutton switches comes on. On the panel 35VU:

.

the OFF legend of the BUS TIE pushbutton switch comes on. On the upper ECAM display unit: . the DC ESS and AC ESS indications come on green, . the amber SHED indication comes on under the DC ESS and AC ESS indications, . the STAT INV indication comes on white and the related parameters come on green. NOTE :

9.On the panel 35VU: . push the BUS TIE pushbutton switch. . push the BAT1 and BAT2 pushbutton switches.

10.On the panel 21VU: . release the EMER GEN TEST pushbutton switch. 11.On the ECAM control panel: . get the ELEC page.

AES

There is no green line between the STAT INV box and the AC ESS and DC ESS indications. On the panel 35VU: . the OFF legend of the BAT1 and BAT2 pushbutton switches is off. On the panel 35VU: . the OFF legend of the BUS TIE pushbutton switch goes off. . the OFF legend of the BAT1 and BAT2 pushbutton switches goes off.

On the lower ECAM display unit: . check that the external power energizes correctly the aircraft electrical circuits.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-28-00-860-051-A A.

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Subtask 24-28-00-410-050-A B.

AES

Close Access (1)

Close the access doors 812 and 822.

(2)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-28-00-710-001-A-01 Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the APU 1.

Reason for the Job (Ref. MPD 24-28-00-01-) OPERATIONAL CHECK OF STATIC INVERTER Test of the correct power supply of the DC ESS BUS, AC ESS BUS and AC STAT INV BUS in emergency configuration when the batteries are the only power supply source.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

210 812, 822 C.

CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

3.

Job Set-up Subtask 24-28-00-860-052-A A.

Safety Precautions (1)

Do not energize the aircraft electrical circuits.

(2)

On the panel 35VU, make sure that: . the BAT1 and BAT2 pushbutton switches are released, . the BUS TIE and AC ESS FEED pushbutton switches are pushed.

NOTE :

On the panel 2000VU, put the MAINT BUS switch (5XX) in the OFF position during the test.

Subtask 24-28-00-010-051-A B.

Get access to the Avionics Compartment (1)

AES

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access doors 812 and 822 of the avionics compartment.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Open the access doors 812 and 822.

Subtask 24-28-00-865-051-A C.

Make sure that this(these) circuit breaker(s) is(are) closed:

105VU

PANEL

DESIGNATION ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/701PP SPLY

5PB1

D01

105VU

ELEC/BAT REF/BCL2

9PB2

F02

105VU

ELEC/BAT REF/BCL1

9PB1

F01

105VU

ELEC/STAT INV/CNTOR/CTL

14XB

G02

105VU

ELEC/STAT INV/BUS 901XP/SPLY

12XB

H02

106VU

AC ESS BUS/EMER/STBY/CNTOR/SPLY

10XE

C06

4.

FIN

LOCATION

Procedure WARNING : TELL ALL THE PERSONS ON THE AIRCRAFT THAT: THE LIGHTS WILL GO OFF DURING THIS TEST THEY MUST NOT MOVE ON THE AIRCRAFT UNTIL THIS TEST IS COMPLETED. IF NOT INJURY AND/OR DAMAGE CAN OCCUR WHEN THE LIGHTS GO OFF SUDDENLY. Subtask 24-28-00-710-051-B A.

Operational Test of the Static Inverter

ACTION 1.On the panel 35VU: . make sure that the voltage of the batteries 1 and 2 is higher than 25.5V.

RESULT

2.Power supply the aircraft electrical circuits: . energize the aircraft electrical circuits from the Auxiliary Power Unit (APU) (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02). 3.Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A). 4.On the ECAM control panel: . get the ELEC page. 5.On the panel 35VU: . release the BAT1 pushbutton switch. .

push the BAT1 pushbutton switch.

.

release the BAT2 pushbutton switch.

.

push the BAT2 pushbutton switch.

AES

On the lower ECAM display unit: . make sure that the APU energizes correctly the aircraft electrical circuits. On the panel 35VU: . the OFF legend of the BAT1 pushbutton switch comes on. . the OFF legend of the BAT1 pushbutton switch goes off. . the OFF legend of the BAT2 pushbutton switch comes on. . the OFF legend of the BAT2 pushbutton switch goes off.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION

RESULT On the lower ECAM display unit: . make sure that the battery charge current (for BAT1 and BAT2) is lower than 60A after approximately 10 seconds. NOTE :

6.On the panel 35VU: . release only the BAT1 pushbutton switch. 7.On the panel 21VU, in the section EMER ELEC PWR: . open the guard, push and hold the EMERG GEN TEST pushbutton switch during all the test, .

after 5 seconds, on the panel 35VU, release the BUS TIE pushbutton switch. 8.On the ECAM control panel: . push and hold the ELEC key, the ELEC page comes into view and stays on during the test.

If the current does not decrease after 10 seconds, it is necessary to do a charging cycle of the batteries. When the charging cycle is completed (batteries no longer connected to the DC BAT BUS), do the check again.

On the panel 35VU: . the OFF legend of the BAT1 pushbutton switch comes on. On the panel 35VU:

.

the OFF legend of the BUS TIE pushbutton switch comes on. On the upper ECAM display unit: . the DC ESS and AC ESS indications come on green, . the amber SHED indication comes on under the DC ESS and AC ESS indications, . the STAT INV indication comes on white and the related parameters come on green. NOTE :

There is no green line between the STAT INV box and the AC ESS and DC ESS indications. On the panel 35VU: . the OFF legend of the BAT2 pushbutton switch is off while the OFF legend of the BAT1 remains on. 9.On the panel 35VU: . push the BUS TIE pushbutton switch. . push the BAT1 pushbutton switch.

10.On the panel 21VU: . release the EMER GEN TEST pushbutton switch. 11.On the ECAM control panel: . get the ELEC page. 5.

On the panel 35VU: . the OFF legend of the BUS TIE pushbutton switch goes off. . the OFF legend of the BAT1 pushbutton switch goes off.

On the lower ECAM display unit: . check that the APU energizes correctly the aircraft electrical circuits.

Close-up Subtask 24-28-00-860-053-A A.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits from the APU (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-28-00 PB501

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-28-00-410-051-A B.

AES

Close Access (1)

Close the access doors 812 and 822.

(2)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

STATIC INVERTER - REMOVAL/INSTALLATION ** On A/C ALL Task 24-28-51-000-001-A Removal of the Static Inverter FIN 3XB 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

B.

Work Zones and Access Panels ZONE/ACCESS

126 822

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

(Ref. Fig. 24-28-51-991-00100-A - Static Inverter) 3.

Job Set-up Subtask 24-28-51-861-050-A A.

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

Subtask 24-28-51-010-050-A B.

Get Access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access door 822.

(2)

Open the access door 822.

Subtask 24-28-51-865-050-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

105VU 4.

DESIGNATION ELEC/STAT INV/CNTOR/CTL

FIN 14XB

LOCATION G02

Procedure (Ref. Fig. 24-28-51-991-00100-A - Static Inverter)

AES

24-28-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-28-51-020-050-A A.

AES

Removal of the Static Inverter (1)

Disconnect the electrical connector (3) from the electrical receptable (2).

(2)

Put CAP - BLANKING on the electrical connector (3) and the electrical receptacle (2).

(3)

Loosen the 4 screws (6).

(4)

Remove the screws (6) and the washers (5).

(5)

Remove the static inverter (1).

24-28-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

822

FR15 FR14

A

A

FR16 FR12

B

3XB

B

1

2

3

6

5

4

N_MM_242851_4_AAM0_01_00

AES

FIGURE 24-28-51-991-00100-A SHEET 1 Static Inverter

24-28-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-28-51-400-001-A Installation of the Static Inverter FIN 3XB 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

126 822

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-28-00-710-001-A

DESIGNATION Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the External Power

24-28-00-710-001-A-01

Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the APU

24-42-00-861-001-A

Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

(Ref. Fig. 24-28-51-991-00100-A - Static Inverter) 3.

Job Set-up Subtask 24-28-51-860-050-A A.

Aircraft Maintenance Configuration (1)

Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001-A).

(2)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 822.

(3)

Make sure that the access door 822 is open.

Subtask 24-28-51-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

105VU 4.

DESIGNATION ELEC/STAT INV/CNTOR/CTL

FIN 14XB

LOCATION G02

Procedure (Ref. Fig. 24-28-51-991-00100-A - Static Inverter)

AES

24-28-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-28-51-420-050-A A.

Installation of the Static Inverter (1)

Put the static inverter (1) in position on its support (4).

(2)

Install the washers (5) and the screws (6) and then tighten the screws.

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (3).

Subtask 24-28-51-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

DESIGNATION ELEC/STAT INV/CNTOR/CTL

105VU

FIN 14XB

LOCATION G02

Subtask 24-28-51-710-050-A C. 5.

Do an operational test of the static inverter (Ref. TASK 24-28-00-710-001-A) or (Ref. TASK 24-28-00-710-001-A-01).

Close-up Subtask 24-28-51-410-050-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access door 822.

(3)

Remove the access platform(s).

Subtask 24-28-51-862-050-A B.

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-28-55-000-001-A Removal of the Static Inverter Contactor CAUTION :

MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF DAMAGE TO EQUIPMENT DURING ITS REMOVAL/ INSTALLATION IF THE AC OR DC POWER STAYS CONNECTED.

FIN 2XB 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

126 822

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE (Ref. Fig. 24-28-55-991-00100-B - Static Inverter Contactor) 3.

DESIGNATION

Job Set-up Subtask 24-28-55-941-050-A A.

AES

Safety Precautions (1)

In . . .

the cockpit, on the overhead panel 35VU, release these pushbutton switches: BAT 1, BAT 2, GEN 1, GEN 2, EXT A.

(2)

In the cockpit, put a WARNING NOTICE(S) to tell persons not to operate the pushbutton switches on these overhead panels: . 35VU (ELEC), . 21VU (EMER ELEC PWR).

(3)

Make sure that the external power connector is not connected to the aircraft receptacle EXT PWR A.

(4)

Put a WARNING NOTICE(S) on the access door 121AL to tell persons not to connect the external power connector.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (5)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the avionics compartment door 822.

Subtask 24-28-55-010-050-B B.

Get Access (1)

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 822.

(2)

Open the access door 822.

(3)

In the avionics compartment, open the access door of the panel 105VU.

Subtask 24-28-55-869-050-B C.

Disconnect the Batteries (1)

In the avionics compartment, on the batteries 1 and 2: (a)

Loosen the knurled nut by one quarter of a turn and disconnect the connector from the batteries 1 and 2.

(b)

Put CAP - BLANKING on the diconnected electrical connectors.

Subtask 24-28-55-865-050-A D.

Open, safety and tag this(these) circuit breaker(s):

105VU

PANEL

DESIGNATION ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/701PP SPLY

5PB1

D01

105VU

ELEC/STAT INV/CNTOR/CTL

14XB

G02

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/REFLNG/ON/BAT

1PR

U28

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-28-55-991-00100-B - Static Inverter Contactor) Subtask 24-28-55-020-050-B A.

Removal of the Contactor CAUTION :

(1)

Disconnect the electrical connector (3).

(2)

Put CAP - BLANKING on the connector (3) and the electrical receptacle (2).

(3)

Loosen the 6 captive screws (4). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (4) and the spring washers from the contactor (1).

Disengage the contactor (1) from the base (7) and remove the contactor (1).

24-28-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

822

A 105VU

A

FR16

FR9

C/B PANEL

7

B

2XB

CONTACTOR

B 6 1 2

3

CONTACTOR BASE

5 4 N_MM_242855_4_ACM0_01_00

AES

FIGURE 24-28-55-991-00100-B SHEET 1 Static Inverter Contactor

24-28-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-28-55-400-001-A Installation of the Static Inverter Contactor CAUTION :

MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF DAMAGE TO EQUIPMENT DURING ITS REMOVAL/ INSTALLATION IF THE AC OR DC POWER STAYS CONNECTED.

FIN 2XB 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

No specific

B.

WARNING NOTICE(S) Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

Work Zones and Access Panels ZONE/ACCESS

126 822

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-28-00-710-001-A

DESIGNATION Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the External Power

24-28-00-710-001-A-01

Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the APU

(Ref. Fig. 24-28-55-991-00100-B - Static Inverter Contactor) 3.

Job Set-up Subtask 24-28-55-860-050-B A.

AES

Aircraft Maintenance Configuration (1)

In . . .

the cockpit, on the overhead panel 35VU, make sure these pushbutton switches are released: BAT 1, BAT 2, GEN 1, GEN 2, EXT A.

(2)

In the cockpit, make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the pushbutton switches on these overhead panels: . 35VU (ELEC), . 21VU (EMER ELEC PWR).

(3)

Make sure that the external power connector is not connected to the aircraft receptable EXT PWR A.

24-28-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

On the access door 121AL, make sure that the WARNING NOTICE(S) is in position to tell persons not to connect the external power connector.

(5)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 822.

(6)

Make sure that access door 822 is open.

(7)

In the avionics compartment, make sure that the access door from the panel 105VU is open.

(8)

Make sure that the batteries are disconnected.

Subtask 24-28-55-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

105VU

PANEL

DESIGNATION ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/701PP SPLY

5PB1

D01

105VU

ELEC/STAT INV/CNTOR/CTL

14XB

G02

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/REFLNG/ON/BAT

1PR

U28

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-28-55-991-00100-B - Static Inverter Contactor) Subtask 24-28-55-420-050-B A.

Installation of the contactor (1)

Install the contactor (1) on the 6 tapped barrels (6) of the contactor base (7).

(2)

TORQUE the six captive screws (4) to between 13.0128 and 15.5808 LBF.IN (0.15 and 0.18 M.DAN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (3).

(6)

Connect the batteries: (a)

Put the connectors on the batteries.

(b)

Tighten the knurled nuts by one quarter of a turn.

Subtask 24-28-55-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

105VU

DESIGNATION ELEC/HOT BUS/702PP SPLY

FIN

LOCATION

5PB2

D02

105VU

ELEC/HOT BUS/701PP SPLY

5PB1

D01

105VU

ELEC/STAT INV/CNTOR/CTL

14XB

G02

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/REFLNG/ON/BAT

1PR

U28

Subtask 24-28-55-710-050-A C.

AES

Do an operational test of the static inverter (Ref. TASK 24-28-00-710-001-A) or (Ref. TASK 24-28-00-710-001-A-01).

24-28-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-28-55-410-050-B A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access door of panel 105VU.

(3)

Close the access door 822.

(4)

Remove the access platform(s).

(5)

Remove the warning notice(s).

24-28-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC GENERATION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The aircraft DC power generation is provided by three Transformers Rectifiers (TR). A.

In Normal Configuration ** On A/C 003-004 (Ref. Fig. 24-30-00-11200-B - DC Generation and Distribution - General) In normal configuration, direct current is provided by both normal transformers rectifiers (TR1 and TR2) and possibly by batteries. TR1 supplies, through TR1 contactor (5PU1) normal bus 1 (DC BUS1), battery bus (DC BAT BUS), essential bus (DC ESS BUS) and sheddable essential bus (DC SHED ESS BUS). The BAT BUS is supplied from BUS 1, through DC NORM BUS 1 SWITCHING contactor (1PC1), and provides power to ESS BUS and SHED ESS BUS through respectively DC ESS BUS SUPPLY contactor (4PC) and DC SHED ESS BUS contactor (8PH) in succession. Both batteries and their respective HOT BUS are connected or not to BAT BUS, in parallel, through both BATTERY LINE contactors (6PB1 & 6PB2). TR2 supplies, through TR2 contactor (5PU2), normal bus 2 (DC BUS 2). ** On A/C 005-099 (Ref. Fig. 24-30-00-11200-C - DC Generation and Distribution - General) In normal configuration, direct current is provided by both normal transformers rectifiers (TR1 and TR2) and possibly by batteries. TR1 supplies, through TR1 contactor (5PU1) normal bus 1 (DC BUS1), battery bus (DC BAT BUS), essential bus (DC ESS BUS) and sheddable essential bus (DC SHED ESS BUS). The BAT BUS is supplied from BUS 1, through DC NORM BUS 1 SWITCHING contactor (1PC1), and provides power to ESS BUS and SHED ESS BUS through respectively DC ESS BUS SUPPLY contactor (4PC) and DC SHED ESS BUS contactor (8PH) in succession. Both batteries and their respective HOT BUS are connected or not to BAT BUS, in parallel, through both BATTERY LINE contactors (6PB1 & 6PB2). TR2 supplies, through TR2 contactor (5PU2), normal bus 2 (DC BUS 2).

** On A/C ALL B.

Loss of the Transformer Rectifier 1 (TR1) ** On A/C 003-004 (Ref. Fig. 24-30-00-11900-B - Loss of Transformer Rectifier 1 - Block Diagram) In the event of TR1 loss, DC BUS 1 and DC BAT BUS are automatically restored from TR2 through DC NORM BUS 2 SWITCHING contactor (1PC2) and DC NORM BUS 1 SWITCHING contactor (1PC1). DC ESS and SHED ESS BUSSES are automatically transferred to ESS TR through ESS TR contactor (3PE). ESS TR supply is provided from AC BUS 1 through AC ESS BUS SWITCHING contactor (3XC) and AC ESS BUS contactor (15XE) in succession. ** On A/C 005-099 (Ref. Fig. 24-30-00-11900-B - Loss of Transformer Rectifier 1 - Block Diagram)

AES

24-30-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL In the event of TR1 loss, DC BUS 1 and DC BAT BUS are automatically restored from TR2 through DC NORM BUS 2 SWITCHING contactor (1PC2) and DC NORM BUS 1 SWITCHING contactor (1PC1). DC ESS and SHED ESS BUSSES are automatically transferred to ESS TR through ESS TR contactor (3PE). ESS TR supply is provided from AC BUS 1 through AC ESS BUS SWITCHING contactor (3XC) and AC ESS BUS contactor (15XE) in succession. The 28VDC SHED BUSSES 210PP and 212PP are automatically shedded. ** On A/C ALL C.

Loss of the Transformer Rectifier 2 (TR2) ** On A/C 003-004 (Ref. Fig. 24-30-00-12300-B - Loss of Transformer Rectifier 2 - Block Diagram) TR2 loss leads to symmetrical recovery of DC BUS 2 from TR1; DC ESS and SHED ESS BUSSES are transferred to ESS TR through ESS TR contactor. ** On A/C 005-099 (Ref. Fig. 24-30-00-12300-B - Loss of Transformer Rectifier 2 - Block Diagram) TR2 loss leads to symmetrical recovery of DC BUS 2 from TR1; DC ESS and SHED ESS BUSSES are transferred to ESS TR through ESS TR contactor. The 28VDC SHED BUSSES 210PP and 212PP are automatically shedded.

** On A/C ALL D. Loss of the TR1 and TR2 In the event of TR1 and TR2 loss (loss of DC BUS 1 & 2), DC ESS and SHED ESS BUSSES are automatically restored from ESS TR through ESS TR contactor (3PE), from AC normal generation.

AES

24-30-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-30-00-13800-B - DC Generation - Component Location) (Ref. Fig. 24-30-00-14400-A - Spare Fuses - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS DOOR 124 124 126 126

ATA REF. 24-38-34 24-38-34 24-38-51 24-38-51

1PB1 1PB2 2PB1 2PB2 ** On A/C 003-004

BCL-1 BCL-2 BAT-1 BAT-2

4PB1 4PB2 ** On A/C ALL

HOLDER-BAT 1 FUSE HOLDER-BAT 2 FUSE

120VU 120VU

212 212

24-38-00 24-38-00

6PB1 6PB2 7PB1

CNTOR-LINE, BAT 1 CNTOR-LINE, BAT 2 P/BSW-ELEC/BAT 1

105VU 120VU 35VU

126 212 210

24-38-55 24-38-55 24-38-00

7PB2

P/BSW-ELEC/BAT 2

35VU

210

24-38-00

1PC1 CNTOR-DC NORM BUS 1 SWITCHING 1PC2 CNTOR-DC NORM BUS 2 SWITCHING 4PC CNTOR-DC ESS BUS SUPPLY ** On A/C 003-004

120VU 120VU 106VU

212 212 125

24-35-55 24-35-55 24-35-55

20PC ** On A/C ALL

120VU

212

24-35-00

106VU

125 125 126

24-34-51 24-34-55 24-32-51

124

24-32-51

HOLDER-FUSE

1PE TR-ESS 3PE CNTOR-ESS TR 1PU1 TR-1 ** On A/C ALL EMB SB 24-1099 FOR A/C 003-005 1PU2 ** On A/C ALL

TR-2

5PU1 5PU2 14PU

CNTOR-TR 1 CNTOR-TR 2 CNTOR-TR 2/AC SVCE BUS NORM SPLY

120VU 120VU 120VU

212 212 212

24-32-55 24-32-55 24-32-55

15PU

P/BSW-TR RST

103VU

126

24-32-00

3PV1 VOLTMETER-BAT 1 35VU 210 24-37-21 3PV2 VOLTMETER-BAT 2 35VU 210 24-37-21 ------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA I I I I DOOR I REF. ------------------------------------------------------------------------------4PB11 FUSE-BAT1 120VU 212 24-38-00 4PB21 FUSE-BAT2 120VU 212 24-38-00 20PC1 FUSE 120VU 212 24-35-00

AES

24-30-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL A.

Spare Fuses (1) If fuses 4PB11 and 4PB21 blow, you can replace them by spare 350 A fuses located on the panel 120VU. (2) If fuse 20PC1 blows, you can replace it by a spare 80 A fuse located on the panel 120VU or by a spare 80 A fuse located on the left side panel, in the cockpit.

AES

24-30-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

BITE Test (Ref. Fig. 24-30-00-15600-A - CFDS Architecture (Liaison with TR’s and BCL’s)) The BITE and maintenance test of both BCL as well as maintenance test of the three TR’s are controlled through the Centralized Fault Display System (CFDS). The CFDS is composed of: . Centralized Fault Display Interface Unit (CFDIU), . two Multipurpose Control and Display Units (MCDU). BCL’s are type 2 systems, i.e. they are connected to the CFDIU with: . a discrete input used to initiate a test from CFDS, . an ARINC 429 output bus. TR’s are type 3 systems, i.e. they are connected to the CFDIU with 2 discrete links: . one of them used to send a ground signal to CFDIU in case of TR FAULT. . the other used for the reset from CFDIU.

AES

24-30-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

301PP

11PB APU START 49 − 42 − 00

801PP

CSM/G CONTROL UNIT 5KA

10KA

6KA

DC SHED ESS BUS

6XE

4PB2

28VDC

702PP

5PB2

1PB2 BCL−2

502PP

704PP

12PB2

BAT2 2PB2

6PB2

701PP

12BP1

BCL−1

5PR

SHUNT

DC BUS 1

1PP

BAT BUS

1PC1

BAT1 2PB1

6PB1 3PP

28VDC

28VDC

401PP

208PP 206PP

1PR

DC ESS BUS

4PC

28VDC

6PN 204PP

601PP

SHUNT

202PP

602PP

1PN2

3PB1

DC BUS 2

1PC2

2PP 28VDC

7PN

DC SVCE BUS

8PN

3XB

5PU1

28

6PP 28VDC

3PX

5XB 2XB

4PP

3PN2

24 − 61 − 00 4PB1

8PH

8PR

703PP

5PB1

20PC

501PP

3PB2 1PB1

8PP

2PR

6PH 5PU2

115

3PE

STATIC INV 1PX 1PU1 TR1

2PU1

1PE ESS TR

1PU2 TR2

24 − 50 − 00

24 − 50 − 00

AC BUS 1

1XP

24 − 25 − 00

24 − 25 − 00

AC BUS 2

24 − 42 − 00

2XP 115VAC

115VAC 24 − 22 − 00

24 − 22 − 00

2PU2

24 − 50 − 00

14PU

4PE

24 − 43 − 00 24 − 24 − 00

N_MM_243000_0_AAL0_01_00

AES

FIGURE 24-30-00-11200-B SHEET 1 DC Generation and Distribution - General

24-30-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

301PP

11PB APU START 49 − 42 − 00

801PP

CSM/G CONTROL UNIT 5KA

10KA

6KA

DC SHED ESS BUS

6XE

4PB2

28VDC

702PP

5PB2

1PB2 BCL−2

502PP

704PP

12PB2

BAT2 2PB2

6PB2

701PP

12BP1

BCL−1

5PR

SHUNT

DC BUS 1

1PP

BAT BUS

1PC1

BAT1 2PB1

6PB1 3PP

28VDC

28VDC

206PP

1PR

3XB

5PU1

28

DC ESS BUS

4PC

4PP 28VDC

6PN

SHUNT

204PP

601PP

202PP

602PP

1PN2

3PB1

DC BUS 2

1PC2

2PP 28VDC

7PN

DC SVCE BUS

8PN

6PP 28VDC

210PP 3PX

5XB 2XB

401PP

208PP

3PN2

24 − 61 − 00 4PB1

8PH

8PR

703PP

5PB1

20PC

501PP

3PB2 1PB1

8PP

2PR

11PN

10PN

6PH

212PP

115

5PU2

3PE

STATIC INV 1PX 1PU1 TR1

2PU1

1PE ESS TR

1PU2 TR2

24 − 50 − 00

24 − 50 − 00

AC BUS 1

1XP

24 − 25 − 00

24 − 25 − 00

AC BUS 2

24 − 42 − 00

2XP 115VAC

115VAC 24 − 22 − 00

24 − 22 − 00

2PU2

24 − 50 − 00

14PU

4PE

24 − 43 − 00 24 − 24 − 00

N_MM_243000_0_AAP0_01_00

AES

FIGURE 24-30-00-11200-C SHEET 1 DC Generation and Distribution - General

24-30-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

301PP

11PB APU START 49 − 42 − 00

801PP

CSM/G CONTROL UNIT 5KA

10KA

6KA

24 − 43 − 00

6XE

4PB2

28VDC 24 − 60 − 00

704PP

12PB2

BAT2 2PB2

6PB2

SHUNT

5PR

8PR

20PC

8PH

24 − 60 − 00

401PP

3PB2 701PP

12BP1

1PB1 BCL−1

DC BUS 1

1PP

1PC1

BAT BUS

28VDC

DC ESS BUS

4PC

1PR

5PB1

BAT1 2PB1

6PB1

28VDC

24 − 61 − 00

SHUNT 3PB1

3PP

DC BUS 2

1PC2

28VDC

4PP

24 − 28 − 00

703PP

24 − 61 − 00 4PB1

8PP

702PP

5PB2

1PB2 BCL−2

DC SHED ESS BUS

2PR

24 − 43 − 00

2PP 28VDC

7PN

DC SVCE BUS

8PN

6PP 28VDC

3PX

24 − 62 − 00

5PU1

5PU2

24 − 28 − 00

3PE

1PX 1PU1 TR1

1PE ESS TR

1PU2 TR2

24 − 52 − 00 115V AC 2PU1

AC ESS BUS

24 − 50 − 00

AC BUS 1

1XP 115VAC

1XC

4XP

24 − 50 − 00

2XC

AC BUS 2

2XP 115VAC

3XC

24 − 42 − 00 2PU2

14PU

4PE

24 − 22 − 00 24 − 28 − 00 15XE 24 − 22 − 00

24 − 43 − 00

24 − 24 − 00

N_MM_243000_0_ACL0_01_00

AES

FIGURE 24-30-00-11900-B SHEET 1 Loss of Transformer Rectifier 1 - Block Diagram

24-30-00 PB001

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

301PP

11PB APU START 49 − 42 − 00

801PP

CSM/G CONTROL UNIT 5KA

10KA

6KA

24 − 43 − 00

6XE

4PB2

28VDC 24 − 60 − 00

704PP

12PB2

BAT2 2PB2

6PB2

SHUNT

5PR

8PR

20PC

8PH

24 − 60 − 00

401PP

3PB2 701PP

12BP1

1PB1 BCL−1

DC BUS 1

1PP

1PC1

BAT BUS

28VDC

DC ESS BUS

4PC

1PR

5PB1

BAT1 2PB1

6PB1

28VDC

24 − 61 − 00

SHUNT 3PB1

3PP

DC BUS 2

1PC2

28VDC

4PP

24 − 28 − 00

703PP

24 − 61 − 00 4PB1

8PP

702PP

5PB2

1PB2 BCL−2

DC SHED ESS BUS

2PR

24 − 43 − 00

2PP 28VDC

7PN

DC SVCE BUS

8PN

6PP 28VDC

3PX

24 − 62 − 00

5PU1

5PU2

24 − 28 − 00

3PE

1PX 1PE ESS TR

1PU2 TR2

1PU1 TR1

24 − 52 − 00 115VAC 2PU1

AC ESS BUS

24 − 50 − 00

AC BUS 1

1XP 115VAC

1XC

4XP

24 − 50 − 00

2XC

AC BUS 2

2XP 115VAC

3XC

24 − 42 − 00 2PU2

14PU

4PE

24 − 22 − 00 24 − 28 − 00 15XE 24 − 22 − 00

24 − 43 − 00

24 − 24 − 00

N_MM_243000_0_AEL0_01_00

AES

FIGURE 24-30-00-12300-B SHEET 1 Loss of Transformer Rectifier 2 - Block Diagram

24-30-00 PB001

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

35VU

PANEL 120VU

122VU

121VU

123VU

RADOME

124VU

ACCESS DOOR

FR1

109VU FR5

811

FWD ELEKS RACK 90VU 108VU

FR9 105VU

FR11

1PU1 1PE

103VU

FR13

2PB1 1PU2

822

1PB1

812 FR15

2PB2

106VU

3XB 1PB2

NOSE LDG/GR WELL FR21 824 FR23

63VU

187VU

188VU

AFT ELEKS RACK 80VU N_MM_243000_0_AGL0_01_00

AES

FIGURE 24-30-00-13800-B SHEET 1 DC Generation - Component Location

24-30-00 PB001

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 120VU

A FR24

C

FR20

A

FR16 FR13

FR1

C SPARE FUSES

B

B

SPARE FUSE

N_MM_243000_0_AHL0_01_00

AES

FIGURE 24-30-00-14400-A SHEET 1 Spare Fuses - Component Location

24-30-00 PB001

Page 11 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL TYPE 3

TYPE 2

TR 1, 2 & 3

BCL 1&2

BITE

CFDIU

MCDU 1

MCDU 2

DISCRETE SIGNAL DATA BUS (ARINC 429)

N_MM_243000_0_AJM0_01_00

AES

FIGURE 24-30-00-15600-A SHEET 1 CFDS Architecture (Liaison with TR’s and BCL’s)

24-30-00 PB001

Page 12 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC GENERATION - DEACTIVATION/REACTIVATION ** On A/C ALL Task 24-30-00-040-001-A Perform a Charging Cycle on the Battery Associated With the Operative Battery Charge Limiter (BCL) 1.

Reason for the Job MMEL 24-38-02A Battery Charger Limiter (BCL) (Old MMEL ref: 24-30-03)

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

822 C.

Referenced Information

REFERENCE 24-38-51-000-001-A 24-38-51-400-001-A 24-41-00-861-002-A

Removal of the Batteries Installation of the Batteries Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

CMM 24-38-51 3.

DESIGNATION

(for corrective action)

Job Set-up Subtask 24-30-00-010-053-A A.

AES

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the avionics compartment door 822.

(2)

Open the access door 822.

(3)

Open the access panel of the BATTERY power center 105VU.

24-30-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-30-00-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

105VU

DESIGNATION ELEC/HOT BUS/702PP SPLY

FIN

LOCATION

5PB2

D02

105VU

ELEC/HOT BUS/701PP SPLY

5PB1

D01

105VU

ELEC/BAT REF/BCL2

9PB2

F02

105VU

ELEC/BAT REF/BCL1

9PB1

F01

105VU

ELEC/BAT BUS/REF/BCL1

8PB1

G01

105VU

ELEC/BAT BUS/REF/BCL2

8PB2

J02

125VU

BAT BUS/301PP/SPLY

11PB

CC01

Subtask 24-30-00-860-052-A C.

4.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

In the cockpit, on the ELEC panel 35VU: . make sure that the BAT 1 and BAT 2 pushbutton switches are released (the OFF legends are on).

(3)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

Procedure Subtask 24-30-00-040-050-B A.

Do a charging cycle of the battery 1 (2) related to the BCL 1 (2) in operation. (1)

If: . the failure of the BCL 1(2) occurred during the last flight and the time the aircraft was on ground was not more than 3 hours, or . the BCL 1(2) did not operate during the last flight and the time the aircraft was on ground was not more than 3 hours: (a)

on the ECAM control panel: . push the ELEC key to get the ELEC system page.

(b)

In the cockpit, on the ELEC panel 35VU: . push the related BAT 1 (2) pushbutton switch to start the charging cycle of the battery 1 (2).

(c)

On the lower ECAM display unit: . the green line between the BAT 1 (2) indication and the DC BAT busbar indication comes into view. The arrow points to the BAT 1 (2) indication, . the related parameter indications (voltage and current) come into view green.

(d)

On the ELEC system page, make sure that the ground power-unit voltage stays above 114VAC during the charge.

(e)

Wait until the battery contactor opens. 1

AES

After some 12 seconds, the green line between the BAT 1 (2) indication and the DC BAT busbar indication: . goes out of view if the battery charge is correct, . stays in view if a battery charge is necessary.

24-30-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL NOTE : (f)

The time for the battery to charge is approximately 20 minutes.

On the lower ECAM display unit, ELEC page, make sure that the battery voltage is above 25V and the battery discharge current is equal to or lower than 1A. NOTE :

The power consumption of the HOT bus is normally lower than 100mA.

(g)

Swap the BCL 1 and the BCL 2.

(h)

Start a charging cycle of the battery which was related to the failed BCL during the previous flight.

(i)

On the ELEC panel 35VU, push the related BAT 2 (1) pushbutton switch to start the charging cycle of the battery 2 (1).

(j)

Release the BAT 1 (2) pushbutton switch related to the defective BCL.

Subtask 24-30-00-040-051-A B.

Alternative Precodure to Charge the Battery 1(2) NOTE :

This procedure is applicable only if: . The failure of the BCL 1(2) occurred on ground at power up, or . The time the aircraft was on ground was more than three hours.

(1)

Remove the battery (Ref. TASK 24-38-51-000-001-A).

(2)

Send the battery 1(2) to the overhaul workshop to charge it (Ref. CMM 24-38-51).

(3)

Install the battery (Ref. TASK 24-38-51-400-001-A).

(4)

Release the BAT 1(2) pushbutton switch related to the defective BCL.

Subtask 24-30-00-040-053-A C.

Alternative Procedure: (1)

5.

If the procedure in step A. and B. are not applicable: (a)

Replace the battery related to the defective BCL with a fully-charged serviceable battery (Ref. TASK 24-38-51-000-001-A) and (Ref. TASK 24-38-51-400-001-A).

(b)

Release the BAT 1(2) pushbutton switch related to the defective BCL.

Close-up Subtask 24-30-00-410-051-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access panel of the BATTERY power center 105VU.

(3)

Close the access door 822.

(4)

Remove the access platform(s).

Subtask 24-30-00-860-053-A B.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

Put a warning notice in position in the cockpit to tell the crew that one BCL does not operate.

(3)

Make an entry in the logbook.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-30-00 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-30-00-440-001-A Reactivation of the Battery Charge Limiter 1(2) 1.

Reason for the Job MMEL 24-38-02A Battery Charger Limiter (BCL) (old MMEL ref: 243003)

2.

Job Set-up Information A.

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

3.

Job Set-up Subtask 24-30-00-861-051-A A.

4.

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

Procedure Subtask 24-30-00-810-050-A A.

5.

Do the trouble shooting of the inoperative Battery Charge Limiter 1(2). . do the alternate procedure: Refer to TSM/24.

Close-up Subtask 24-30-00-862-051-A A.

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

24-30-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-30-00-040-002-A Deactivation of the Transformer Rectifier TR2 1.

Reason for the Job MMEL 24-32-01B DC Main Generation (TR 1, TR 2) (Old MMEL ref: 24-30-01)

2.

Job Set-up Information A.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

3.

Job Set-up Subtask 24-30-00-860-054-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

On the ELEC panel 35VU, make sure that: . The AC ESS FEED pushbutton switch is pushed (the ALTN legend is off).

Subtask 24-30-00-865-052-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

106VU

DESIGNATION AC ESS BUS/STBY/CNTOR/CTL

5XC

B08

106VU

AC ESS/BUS NORM/CNTOR/CTL

4XC

B03

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

AES

FIN

LOCATION

24-30-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure Subtask 24-30-00-040-052-A A.

Deactivation of the TR2 if AC ESS FEED Control Is Serviceable (1)

Operational test of the AC essential-generation switching system.

ACTION 1.On the ECAM control panel: . Push the ELEC key.

2.On the panel 123VU: . Open the circuit breaker 1XC.

RESULT On the lower ECAM DU, on the ELEC page: . A green bar comes into view between the AC1 and AC ESS busbars. This shows that the AC1 busbar energizes the AC ESS busbar. On the F/O glareshield panel 130VU: . The MASTER CAUT light comes on. You can hear the single chime. The upper ECAM DU becomes black.

3.On the ELEC panel 35VU: . Release the AC ESS FEED pushbutton switch.

4.On the ECAM control panel: . Push the ELEC key.

5.On the panel 123VU: . Close the circuit breaker 1XC. 6.On the ELEC panel 35VU: . Push the AC ESS FEED pushbutton switch.

The indications shown on the upper ECAM DU: ELEC AC ESS BUS FAULT then AC ESS FEED ... ALTN move to the lower ECAM DU. On the ELEC panel 35VU: . The FAULT legend of the AC ESS FEED pushbutton switch comes on. On the ELEC panel 35VU: . The FAULT legend of the AC ESS FEED pushbutton switch goes off. . The ALTN legend of the AC ESS FEED pushbutton switch comes on. On the lower ECAM DU, on the ELEC page: . A green bar comes into view between the AC2 and AC ESS busbars. This shows that the AC2 busbar energizes the AC ESS busbar, . The green bar between the AC1 and AC ESS busbars goes out of view.

On the ELEC panel 35VU: . The ALTN legend of the AC ESS FEED pushbutton switch goes off. On the ELEC page: . The green bar between the AC2 and AC ESS busbars goes out of view. . The green bar between the AC1 and AC ESS busbars comes into view.

5.

Close-up Subtask 24-30-00-860-055-A A.

Put the aircraft back to its initial configuration. (1)

AES

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

24-30-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AES

(2)

Make an entry in the logbook.

(3)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-30-00 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-30-00-440-002-A Reactivation of the Transformer Rectifier TR2 1.

Reason for the Job MMEL 24-32-01B DC Main Generation (TR 1, TR 2) (old MMEL ref: inexistent)

2.

Job Set-up Information A.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

TSM 24-30-00-810-802

Failure of the TR2 or TR2 Contactor or Related Wiring

3.

Job Set-up Subtask 24-30-00-860-056-A A.

4.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

Procedure Subtask 24-30-00-440-050-A A.

5.

Do the trouble shooting of the TR2 (Ref. TSM 24-30-00-810-802).

Close-up Subtask 24-30-00-860-057-A A.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-30-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC GENERATION - ADJUSTMENT/TEST ** On A/C ALL Task 24-30-00-710-001-A Operational Test of the Emergency Generation System with One Normal Transformer Rectifier (TR) Failed WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE. 1.

Reason for the Job CSM/G Test with one normal TR Failed.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

812, 822 C.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A 71-00-00-710-018-A 71-00-00-710-043-A

EIS Start Procedure EIS Stop Procedure Discontinued Start, Restart and Shutdown Procedures Normal Engine Automatic Start Procedure

3.

Job Set-up Subtask 24-30-00-860-050-A A.

AES

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

On the HYD/FUEL panel 40VU, make sure that the OFF legend of the BLUE ELEC PUMP pushbutton switch is OFF.

24-30-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-30-00-010-052-A B.

Get access to the Avionics Compartment (1)

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access doors 812 and 822.

(2)

Open the access doors 812 and 822.

Subtask 24-30-00-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) closed:

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

FIN C01

LOCATION

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/CNTOR/CTL

5PE

C02

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/EMER GEN AUTO/2

9XE

Z26

122VU

ELEC/EMER GEN AUTO/1

11XE

Z25

Subtask 24-30-00-710-050-B D.

Start one engine (Ref. TASK 71-00-00-710-043-A).

Subtask 24-30-00-869-052-A E. 4.

On the Ecam Control Panel (ECP), get the HYD page and make sure on the System Display (SD) that the blue system pressure is 3000 psi.

Procedure Subtask 24-30-00-710-051-A A.

Do the CSM/G test with one normal TR failed:

ACTION 1.On the panel 21VU, on the EMER ELEC PWR section: . lift the safety cover, . push and hold the EMER GEN TEST pushbutton switch.

RESULT On the lower ECAM display unit: . the ELEC page comes into view automatically, . the green lines between the AC1 and the AC ESS busbars and the DC1 and the DC ESS busbars go out of view, . the EMER GEN and ESS TR indications are shown in white. The related parameters are shown in green, . the green lines between the EMER GEN indication and the AC ESS busbar, the EMER GEN and the ESS TR indications, the ESS TR indication and the DC ESS busbar come into view, . the SHED indication comes into view below the AC ESS and DC ESS busbars.

2.On the panel 21VU: . release the EMER GEN TEST pushbutton switch. 3.On the ECAM control panel: . get the ELEC page.

On the lower ECAM display unit: . the normal configuration comes into view (the emergency AC generator stops).

4.On the panel 21VU: . lower the safety cover.

AES

24-30-00 PB501

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-30-00-710-052-B A.

Stop the engine (Ref. TASK 71-00-00-710-018-A).

Subtask 24-30-00-860-051-A B.

Put the aircraft back to its initial configuration. (1)

If the test duration is more than 30 seconds, on the panel 22VU, the FAULT light of the EXTRACT pushbutton switch comes on. If this occurs, release then push the EXTRACT pushbutton switch (the FAULT light goes off).

(2)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(3)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02)

Subtask 24-30-00-410-050-A C.

AES

Close Access (1)

Close the access doors 812 and 822.

(2)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC MAIN GENERATION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The DC main generation is provided by the two Transformers Rectifiers 1 and 2 (TR1 and TR2). They are supplied with three phases 115 VAC/400 Hz voltage from the normal Alternating Current (AC) distribution network.

AES

24-32-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location

** On A/C 003-004 (Ref. Fig. 24-32-00-12400-A - DC Main Generation (TR) - Component Location) ** On A/C 005-099 (Ref. Fig. 24-32-00-12400-B - DC Main Generation (TR) - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS ATA REF. DOOR

** On A/C ALL 1PU1 TR-1 ** On A/C ALL EMB SB 24-1099 FOR A/C 003-005

126

24-32-51

1PU2 ** On A/C ALL

TR-2

124

24-32-51

5PU1 5PU2 14PU

CNTOR-TR 1 CNTOR-TR 2 CNTOR-TR 2/AC SVCE BUS NORM SPLY

120VU 120VU 120VU

212 212 212

24-32-55 24-32-55 24-32-55

15PU

P/BSW-TR RST

103VU

126

24-32-00

AES

24-32-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

Component Description A.

Transformer Rectifier 1PU1 1PU2 (1) Operation (Ref. Fig. 24-32-00-13800-B - Transformer Rectifier 1 (TR1) - Component Description) (Ref. Fig. 24-32-00-13900-A - Transformer Rectifier 2 (TR2) - Component Description) (Ref. Fig. 24-32-00-14000-A - Transformer Rectifier Contactor Control - Simplified Logic) Each TR controls its contactor via an internal TR logic. This logic, which is intended to protect the Direct Current (DC) network and the TR, controls contactor opening in case of: . no current flow to the DC BUS (minimum current detection), . TR overheat (171/Deg.C). To ensure these protections, each TR sends a fault signal to the Centralized Fault Display System (CFDS) for maintenace purpose. Main TR’s are ventilated by air extracted from the aircraft ventilation network.

B.

TR Characteristics . ** On A/C ALL EMB SB 24-1099 FOR A/C 003-005 supply: 115 VAC/400 Hz, three phase . DC output current: 200 A in continuous operation 300 A for 5 minutes 500 A for 30 seconds 1000 A for 1 second . DC output voltage: 30.2 V with no load 27.5 V at 200A. TR1 (1PU1) is fully interchangeable with essential TR (1PE) and has the same electrical properties. NOTE :

AES

TR2 (1PU2) has not the same electrical properties and is not interchangeable.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Operation/Control and Indicating A.

Normal Operation The transformers rectifiers start to operate as soon as they are supplied: . TR1 is supplied by 1XP busbar, . TR2 is normally supplied by 2XP busbar. NOTE :

TR2 can also supply part of the DC network from the ground power unit and in ground service configuration (Ref. 24-43-00-00).

The parameters such as voltage and current are available and displayed via the SDAC on the ELEC page on the lower ECAM DU. B.

Failure of the TR1(2) (Ref. Fig. 24-32-00-16800-A - TR1 Fault (Class 1 - Level 1) - ECAM) (Ref. Fig. 24-32-00-16900-A - Normal Operation - Lower ECAM Display unit) In case of failure of the TR1(2), the TR FAULT warning appears on the upper ECAM display unit and at the same time, the ELEC page is displayed on the ECAM lower display unit.

C.

Table of Main Signals

(1) Table of Main Digital Signals Sent Out by the Equipments to SDAC 1(2) ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------! 1 102 01 ! BAT1 ! 512 ! A ! ! 09 ! ! ! !BCL1 ! ! ! CURRENT ! ! ! ! ! ! ! ! ! ! 2 102 10 ! BAT2 ! 512 ! A ! ! 09 ! ! ! !BCL2 ! ! ! CURRENT ! ! ! ! ! ! ! ! ! ! 1 104 01 ! BAT1 ! 32 ! V ! ! 05 ! ! ! !BCL1 ! ! ! VOLTAGE ! ! ! ! ! ! ! ! ! ! 2 104 10 ! BAT2 ! 32 ! V ! ! 05 ! ! ! !BCL2 ! ! ! VOLTAGE ! ! ! ! ! ! ! ! ! (2) Table of Main Low Level Direct Current (LLDC) Analogic Signals sent out by the Equipments to SDAC 1(2) ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------! ! TRU1 ! ! V ! ! ! ! ! !1PU1 ! ! ! VOLTAGE ! ! ! ! ! ! ! ! ! ! ! TRU1 ! ! A ! ! ! ! ! !1PU1 !

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! !

CURRENT TRU2 VOLTAGE TRU2 CURRENT ESS TRU VOLTAGE ESS TRU CURRENT

! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! !

V A V A

! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! !

! !1PU2 ! !1PU2 ! !1PE ! !1PE !

! ! ! ! ! ! ! ! !

(3) Table of Main Discrete Signals Received by the SDAC 1(2) ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------! 002 00 ! ESS TRU ! ! ! ! 17 ! ! ! !3PE ! ! ! CNTOR ON ! ! ! ! ! ! ! ! ! ! 002 00 ! ESS TRU ! ! ! ! 17 ! ! ! !3PE ! ! ! CNTOR OFF! ! ! ! ! ! ! ! ! ! 002 00 !DC BAT/ DC! ! ! ! 19 ! ! ! !8PH ! ! ! ESS SHED ! ! ! ! ! ! ! ! ! ! ! CNTOR ON ! ! ! ! ! ! ! ! ! ! 002 00 !DC BAT/ DC! ! ! ! 19 ! ! ! !8PH ! ! ! ESS SHED ! ! ! ! ! ! ! ! ! ! ! CNTOR OFF! ! ! ! ! ! ! ! ! ! 1 002 01 !TRU1 CNTOR! ! ! ! 17 ! ! ! !5PU1 ! ! ! ON ! ! ! ! ! ! ! ! ! ! 1 002 01 !TRU1 CNTOR! ! ! ! 17 ! ! ! !5PU1 ! ! ! OFF ! ! ! ! ! ! ! ! ! ! 002 01 !DC1/DC ESS! ! ! ! 18 ! ! ! !1PC1 ! ! ! CNTOR ON ! ! ! ! ! ! ! ! ! ! 002 01 !DC1/DC ESS! ! ! ! 18 ! ! ! !1PC1 ! ! ! CNTOR OFF! ! ! ! ! ! ! ! ! ! 1 002 01 !BAT1 CNTOR! ! ! ! 19 ! ! ! !6PB1 ! ! ! ON ! ! ! ! ! ! ! ! ! ! 1 002 01 !BAT1 CNTOR! ! ! ! 19 ! ! ! !6PB1 ! ! ! OFF ! ! ! ! ! ! ! ! ! ! 002 01 !DC BAT/ DC! ! ! ! 21 ! ! ! !4PC ! ! !ESS CNTOR ! ! ! ! ! ! ! ! ! ! ! ON ! ! ! ! ! ! ! ! ! ! 002 01 !DC BAT/ DC! ! ! ! 21 ! ! ! !4PC ! ! !ESS CNTOR ! ! ! ! ! ! ! ! ! ! ! OFF ! ! ! ! ! ! ! ! ! ! 1 002 01 ! BAT1 P/B ! ! ! ! 24 ! ! ! !7PB1 ! ! ! OFF ! ! ! ! ! ! ! ! ! ! 1 002 01 ! BAT1 P/B ! ! ! ! 24 ! ! ! !7PB1 ! ! ! ON ! ! ! ! ! ! ! ! ! ! 2 002 10 !TRU2 CNTOR! ! ! ! 17 ! ! ! !5PU2 !

AES

24-32-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

2

002 002 002

2

002

2

002

2

002

2 2

002 002

2

002

1

004

1 2

004 004

2

004 004 004

! ON ! 10 !TRU2 CNTOR! ! OFF ! 10 !DC2 / DC1 ! !CNTOR ON ! 10 !DC2 / DC1 ! !CNTOR OFF ! 10 !BAT2 CNTOR! ! ON ! 10 !BAT2 CNTOR! ! OFF ! 10 ! AC2 BUS ! ! OFF ! 10 !AC2 BUS ON! 10 ! BAT2 P/B ! ! OFF ! 10 ! BAT2 P/B ! ! ON ! 01 ! DC1 BUS ! ! OFF ! 01 !DC1 BUS ON! 10 ! DC2 BUS ! ! OFF ! 10 !DC2 BUS ON! 11 !DC ESS BUS! ! OFF ! 11 !DC ESS BUS! ! ON !

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

! 17 ! ! 18 ! ! 18 ! ! 19 ! ! 19 ! ! 20 ! ! 20 ! 24 ! ! 24 ! ! 29 ! ! 29 ! 29 ! ! 29 ! 29 ! ! 29 ! !

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

! !5PU2 ! !1PC2 ! !1PC2 ! !6PB2 ! !6PB2 ! !16XC ! !16XC !7PB2 ! !7PB2 ! !14WV ! !14WV !44WV ! !44WV !12WV ! !12WV !

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

D. Reset of the Protection of the Transformer Rectifier (TR) Before you reset a TR, make sure that the related electrical network supplies its primary winding, in any RESET mode. (1) From the CFDS or on the panel 103VU Reset of the TR protection is possible from the CFDIU (CFDS interface). If the CFDIU is not available, it is possible to start the transformers manually. To do this, push the TR RST pushbutton switch 15PU located on panel 103VU. (2) Description of the reset procedure (Ref. Fig. 24-32-00-17000-B - TR Reset Procedure) The reset procedure must be performed by selecting the SYSTEM REPORT/TEST item on the CFDS menu, then by selecting the involved TR on ELEC menu. (a) If the reset is effective, NO FAULT appears on the MCDU. (b) If the reset is impossible: . TR 1(2) is displayed on the MCDU, . TR 1(2) FAULT stays on the upper ECAM display unit. NOTE :

AES

After the reset procedure is performed, on the panel 35VU, the AC ESS FEED pushbutton switch must be released, and then pushed. The ESS TR no longer supplies the DC ESS BUS (4PP). On the lower ECAM display unit, the normal configuration comes into view.

24-32-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

A PANEL 120VU

14PU

122VU 121VU 123VU 124VU

B

C

A

D B

C 5PU2 5PU1

D D

N_MM_243200_0_AAM0_01_00

AES

FIGURE 24-32-00-12400-A SHEET 1 DC Main Generation (TR) - Component Location

24-32-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

822

A 1PU2

FR16

FR9 1PU1

A 103VU

15PU

N_MM_243200_0_AAM0_02_00

AES

FIGURE 24-32-00-12400-A SHEET 2 DC Main Generation (TR) - Component Location

24-32-00 PB001

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

A PANEL 120VU

14PU

122VU 121VU 123VU 124VU

C

B

20XX

A

D B

14PN

C

13PN 5PU2

D

5PU1

D

N_MM_243200_0_AAP0_01_00

AES

FIGURE 24-32-00-12400-B SHEET 1 DC Main Generation (TR) - Component Location

24-32-00 PB001

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

822

A 1PU2

FR16

FR9 1PU1

A 103VU

15PU

N_MM_243200_0_AAP0_02_00

AES

FIGURE 24-32-00-12400-B SHEET 2 DC Main Generation (TR) - Component Location

24-32-00 PB001

Page 10 May 01/12 Revision n˚: 40

115 VAC 400 HZ

AES

FIGURE 24-32-00-13800-B SHEET 1 Transformer Rectifier 1 (TR1) - Component Description

24-32-00 PB001 +

SDAC (CURRENT)

−

OV INT

LLDC SIGNAL

CHASSIS GROUND

TIME DELAY=5s

MINIMUN CURRENT DETECTION I 1A

P/B SW

OVERHEAT DETECTION

15PU

−12V INT.

Q2

K1

SET

CFDIU GROUND = RESET

KLIXON

+

SDAC (VOLTAGE)

28 VDC EXT

5PU1 CNTOR

4PU1

TO PC LOGIC AND CFDIU (GROUND = T.R.FAULT)

K2

−

−

+

CURRENT MEASURE

CURRENT SENSOR

TC°2

KLIXON

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_243200_0_ACN0_01_00

Page 11 May 01/12 Revision n˚: 40

115 VAC 400 HZ

AES

FIGURE 24-32-00-13900-A SHEET 1 Transformer Rectifier 2 (TR2) - Component Description

24-32-00 PB001 +

SDAC (CURRENT)

−

OV INT

LLDC SIGNAL

CHASSIS GROUND

TIME DELAY=5s

MINIMUN CURRENT DETECTION I 1A

P/B SW

OVERHEAT DETECTION

15PU

−12V INT.

Q2

K1

SET

CFDIU GROUND = RESET

KLIXON

+

SDAC (VOLTAGE)

3PX

28 VDC EXT

5PU2 CNTOR

4PU2

TO PC LOGIC AND CFDIU (GROUND = T.R.FAULT)

INH.MINI CURRENT DET.

K2

−

−

+

CURRENT MEASURE

CURRENT SENSOR

TC°1

KLIXON

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_243200_0_ADM0_01_00

Page 12 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

28V TR2 FAULT TR2 14PU

NOTA : FOR TR1 & TR2. "FAULT TR" NOT OUTPUT CURRENT OR OVERHEAT

1PU2

5PU2

2PP 28VDC BUS 2 TR2 2XP 115VAC BUS 2

5PU1 28V TR1 FAULT TR1

1XP 115VAC BUS 1

1PU1

TR1

1PP 28VDC BUS 1

** On A/C ALL

N_MM_243200_0_AEM0_01_00

AES

FIGURE 24-32-00-14000-A SHEET 1 Transformer Rectifier Contactor Control - Simplified Logic

24-32-00 PB001

Page 13 May 01/12 Revision n˚: 40

AES

FIGURE 24-32-00-16800-A SHEET 1 TR1 Fault (Class 1 - Level 1) - ECAM

− CLEAR P/BSW (ON ECAM CP)

− CLEAR P/BSW (ON ECAM CP)

MANUAL CREW ACTION

− DC ESS BUS AND DC SHEDDABLE ESS BUS SUPPLIED BY TR ESS

− DC1, DC2 AND DC BAT BUS SUPPLIED BY TR2.

− TR1 FAULT (OR TR2)

CONFIG. SYSTEM

OVHD SYST PANEL IND. WARNING

ELEC

24-32-00 PB001

NORMAL CONFIG.

STS

NORMAL CONFIG.

TR 1 FAULT

ECAM UPPER DISPLAY

TR 1 FAULT (CLASS 1 − LEVEL 1)

TR 1

INOP

NORMAL CONFIG.

RETURN TO PRESELECTED PAGE

STATUS

SEE FOLLOWING PAGE

SYS:

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_243200_0_AFL0_01_00

Page 14 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1

BAT

28V

DC

BAT

2

28V

0A

0A

DC 1

DC DC

TR 1 0 V 0 A

2

ESS TR 2

ESS

TR

EMER

GEN

28V 130A

28V 62A

AC 1

AC

ESS

GEN 1 62% 116V 400HZ IDG 1

°C 1 1 0

AC

2

GEN

2

60%

APU

GEN

116V 400HZ 1 1 0°C

IDG 2

NM5 24 26 00 0 ACME 00

4WT2

N_MM_243200_0_AFL0_02_00

AES

FIGURE 24-32-00-16800-A SHEET 2 TR1 Fault (Class 1 - Level 1) - ECAM

24-32-00 PB001

Page 15 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 2

BAT 1 28 V 0A

DC

28 V

BAT

10 A

DC 1

DC DC

TR 1 28 V

ESS

TR

EMER

TR 2 28 V

GEN

110A

AC 1

GEN 1 62% 116V 4 0 0 HZ IDG 1

°C 1 1 0

2

ESS

82A

AC

ESS

APU

AC

2

GEN 2 60% 116V 4 0 0 HZ

OFF

1 1 0°C

IDG 2

4WT2

N_MM_243200_0_AFN0_01_00

AES

FIGURE 24-32-00-16900-A SHEET 1 Normal Operation - Lower ECAM Display unit

24-32-00 PB001

Page 16 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL SYSTEM REPORT / TEST

SYSTEM REPORT / TEST

1L

AIRCOND

F/CTL

1R

2L

AFS

FUEL

2R

3L

COM

ICE&RAIN

3R

4L

ELEC

INST

4R

5L

FIRE PROT

L/G

5R

5L

6L

RETURN

NAV

6R

6L

SELECT ELEC

1L

AC GEN

TR

1

1R

2L

GCU EMER

TR

2

2R

3L

BCL

1

TR

3

3R

4L

BCL

2

4R 5R

RETURN

6R

SELECT SYSTEM REPORT/TEST SELECT TR 1

CFDS MENU 1L

LAST LEG REPORT

1R

2L

LAST LEG ECAM REPORT

2R

3L

PREVIOUS LEGS REPORT

3R

4L

AVIONICS STATUS

4R

5L

SYSTEM REPORT/TEST

5R

6L

TR 1 1L

6R

POST FLIGHT REPORT

SELECT CFDS

RESET

1R

2L

2R

3L

3R

4L

4R

5L

5R

6L

RETURN

6R

MCDU MENU 1L

FMS

1R

2L

DATA LINK

2R

3L

CFDS

3R

4L

AIDS

4R

SELECT RESET RESET IMPOSSIBLE

RESET EFFECTIVE

5R

5L

6R

6L SELECT DESIRED SYSTEM

PRESS KEY MCDU MENU

TR 1 1L

TR 1

TR 1

NO FAULT

1R

1L

2L

2R

2L

2R

3L

3R

3L

3R

4L

4R

4L

4R

5L

5R

5L

6R

6L

6L

RETURN

PRINT

1R

5R RETURN

PRINT

6R

N_MM_243200_0_AGP0_01_00

AES

FIGURE 24-32-00-17000-B SHEET 1 TR Reset Procedure

24-32-00 PB001

Page 17 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC MAIN GENERATION - ADJUSTMENT/TEST ** On A/C ALL Task 24-32-00-710-001-A Operational Test of the DC Generation Switching 1.

Reason for the Job (Ref. MPD 24-32-00-01-) OPERATIONAL CHECK OF DC GENERATION SWITCHING Make sure that DC BUS1, DC BUS2 and DC ESS busbars are supplied if transformer TR1 or TR2 fails.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS

210 812, 822 C.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-32-00-860-004-A

Procedure to Get Access to the SYSTEM REPORT/TEST/ELEC Page

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

3.

Job Set-up Subtask 24-32-00-860-050-A A.

AES

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

In the cockpit, on the overhead panel 35VU, make sure that the BAT1 and BAT2 pushbutton switches are pushed. (On these pushbutton switches, the OFF legend is off).

(3)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

24-32-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

On the ECAM control panel, get the ELEC page.

(5)

On the MCDU, get the ELEC menu on the SYSTEM REPORT/TEST page. (Ref. TASK 31-32-00-860-004-A) NOTE :

If during the electrical transfers, the displays on the lower ECAM display unit or on the MCDU go out of view, do paragraph (4) or (5) again.

Subtask 24-32-00-010-050-A B.

Get access to the Avionics Compartment (1)

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access doors 812 and 822.

(2)

Open the access doors 812 and 822.

Subtask 24-32-00-865-054-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

49VU

DESIGNATION HYD/HYD PWR/B WARN/& CTL

FIN

LOCATION

2702GJ

C12

123VU

B HYD/ELEC PUMP

2701GJ

AB09

Subtask 24-32-00-865-050-A D.

Make sure that this(these) circuit breaker(s) is(are) closed:

49VU

PANEL

DESIGNATION AIR COND/AVNCS VENT/CTL

6HQ

D06

105VU

ELEC/HOT BUS/702PP SPLY

12PB2

E02

105VU

ELEC/HOT BUS/701PP SPLY

12PB1

E01

106VU

AC ESS/BUS NORM/CNTOR/CTL

4XC

B03

106VU

ESS TR/CNTOR/CTL

5PE

C02

106VU

ESS TR/SPLY

4PE

C01

121VU

APU/FIRE/EXTIG/SQUIB/A

1WF

L38

121VU

APU/FIRE/LP VALVE/NORM

4WF

M42

121VU

HYDRAULIC/BRAKING AND STEERING/SYS1/CTL

1GG

M34

122VU

ELEC/CNTOR/DC BUS/TIE 1/FAULT

14PC

U24

122VU

ELEC/AC/BUS1/CTL

17XN1

V25

122VU

AIR COND/ZONE TEMP CTL/28VDC/SYS1

3HK

V19

122VU

LIGHTING/WING/STROBE

10LV

V05

122VU

ELEC/TR2/FAULT/DC BUS TIE/CONFIG

7PC2

W30

122VU

ELEC/TR1/FAULT/DC BUS TIE/CONFIG

7PC1

W29

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

122VU

ELEC/CNTOR/DC/BUS/TIE1

9PC

W25

122VU

ELEC/TR2/MONG

3PU2

X26

122VU

ELEC/TR1/MONG

3PU1

X25

AES

FIN

LOCATION

24-32-00 PB501

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C 005-099 122VU

DESIGNATION

FIN

LOCATION

AIR COND/CARGO/FIRE/EXTIG

1WX

T19

123VU

AVNCS VENT/BLOWER/FAN

1HQ

AD10

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

TR1/SPLY

2PU1

AB10

123VU

TR2/214XP/SPLY

2PU2

AB04

124VU

TR2/CNTOR/SPLY

4PU2

BC01

125VU

TR1/CNTOR/SPLY

4PU1

CF01

WATER SYS

1MA

D06

** On A/C ALL

2000VU 4.

Procedure Subtask 24-32-00-710-050-A A.

Operational Test of the DC Generation Switching NOTE :

This test is for the system 1. For the other system(s), use the indications between the parentheses.

ACTION 1.On the ELEC panel 35VU: . release the BAT1 and BAT2 pushbutton switches. 2.On the panel 35VU: . push the BAT1 and BAT2 pushbutton switches.

RESULT On the panel 35VU: . the OFF legends of the BAT1 and BAT2 pushbutton switches come on. On the panel 35VU: . the OFF legends of the BAT1 and BAT2 pushbutton switches go off.

3.On the panel 122VU: . open the circuit breaker 3PU1(2).

On the lower ECAM display unit: . the TR1(2) supplies the DC1(2) busbar.

4.On the panel 125VU (124VU): . open the circuit breaker 4PU1(2).

On the upper ECAM display unit: . the TR1(2) FAULT indication comes into view. On the lower ECAM display unit: . the TR1(2) no longer supplies the DC1(2) busbar, . the DC2(1) busbar supplies the DC1(2) busbar, through the DC BAT busbar, . The AC ESS busbar supplies the DC ESS busbar through the ESS TR.

5.On the panels 122VU and 125VU (124VU): . close the circuit breakers 3PU1(2) and 4PU1(2).

There is no change.

6.On the MCDU, on the ELEC page: . push the line key adjacent to the TR1(2) indication.

On the MCDU: . the TR1(2) page comes into view.

7.On the MCDU: . push the line key adjacent to the RESET indication.

On the TR1(2) page: . the NO FAULT indication comes into view. On the upper ECAM display unit: . the TR1(2) FAULT indication goes out of view. On the lower ECAM display unit: . the TR1(2) supplies the DC1(2) busbar.

AES

24-32-00 PB501

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 8.On the MCDU: . push the line key adjacent to the RETURN indication until the ELEC page comes into view. 9.On the panel 35VU: . release the AC ESS FEED pushbutton switch. 10.On the panel 35VU: . push the AC ESS FEED pushbutton switch. 11.On the ECAM control panel: . push the ELEC key to get the ELEC page.

RESULT

On the panel 35VU: . the ALTN legend of the AC ESS FEED pushbutton switch comes on. On the panel 35VU: . the ALTN legend of the AC ESS FEED pushbutton switch goes off. On the lower ECAM display unit: . the ESS TR no longer supplies the DC ESS busbar (the normal configuration comes into view). NOTE :

12.On the panel 35VU: . release the BAT1 and BAT2 pushbutton switches. 13.On the panel 35VU: . push the BAT1 and BAT2 pushbutton switches. 14.On the panel 123VU: . open the circuit breaker 2PU1(2).

It is possible that the ESS TR continues to supply the DC ESS busbar. If this occurs, on the AC power center 123VU, open and close the circuit breaker 1XC and make sure that the ESS TR no longer supplies the DC ESS busbar. On the panel 35VU: . the OFF legends of the BAT1 and BAT2 pushbutton switches come on. On the panel 35VU: . the OFF legends of the BAT1 and BAT2 pushbutton switches go off. On the upper ECAM display unit: . the TR1(2) FAULT indication comes into view. On the lower ECAM display unit: . the TR1(2) no longer supplies the DC1(2) busbar, . the DC2(1) busbar supplies DC1(2) busbar through the DC BAT busbar, . the voltage from TR1(2) = 0 V, . the AC ESS busbar supplies the DC ESS busbar through the ESS TR.

15.On the panel 123VU: . close the circuit breaker 2PU1(2).

On the lower ECAM display unit: . the voltage from TR1(2) is approximately 28 V.

16.On the MCDU, on the ELEC page: . push the line key adjacent to the TR1(2) indication.

On the MCDU: . the TR1(2) page comes into view.

17.On the MCDU: . push the line key adjacent to the RESET indication

On the MCDU, on the TR1(2) page: . the NO FAULT indication comes into view. On the upper ECAM display unit: . the TR1(2) FAULT indication goes out of view. On the lower ECAM display unit: . the TR1(2) supplies the DC1(2) busbar.

18.On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view.

AES

24-32-00 PB501

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 19.On the panel 35VU: . release the AC ESS FEED pushbutton switch. 20.On the panel 35VU: . push the AC ESS FEED pushbutton switch. 21.On the ECAM control panel: . push the ELEC key to get ELEC page.

5.

RESULT On the panel 35VU: . the ALTN legend of the AC ESS FEED pushbutton switch comes on. On the panel 35VU: . the ALTN legend of the AC ESS FEED pushbutton switch goes off. On the lower ECAM display unit: . the ESS TR no longer supplies the DC ESS busbar (the normal configuration comes into view).

Close-up Subtask 24-32-00-865-055-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

49VU

PANEL

DESIGNATION HYD/HYD PWR/B WARN/& CTL

2702GJ

FIN C12

LOCATION

123VU

B HYD/ELEC PUMP

2701GJ

AB09

Subtask 24-32-00-860-051-A B.

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Subtask 24-32-00-410-050-A C.

AES

Close Access (1)

Close the access doors 812 and 822.

(2)

Remove the access platform(s).

24-32-00 PB501

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

TRANSFORMER RECTIFIER - REMOVAL/INSTALLATION ** On A/C ALL Task 24-32-51-000-001-A Removal of the Transformer Rectifier WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 1PU1, 1PU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

SLEEVE - INSULATING

B.

Work Zones and Access Panels ZONE/ACCESS

126 822

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE (Ref. Fig. 24-32-51-991-00100-A - Transformer Rectifier) 3.

DESIGNATION

Job Set-up Subtask 24-32-51-865-050-A A.

Open, safety and tag this(these) circuit breaker(s):

PANEL FOR FIN 1PU1 123VU

TR1/SPLY

2PU1

AB10

FOR FIN 1PU2 123VU

TR2/214XP/SPLY

2PU2

AB04

TR2/SVCE/BUS 2/SPLY

1XX

AB08

123VU

DESIGNATION

FIN

LOCATION

Subtask 24-32-51-010-050-A B.

Get access to the Avionics Compartment (1)

AES

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access door 822.

24-32-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2) 4.

Open the access door 822.

Procedure (Ref. Fig. 24-32-51-991-00100-A - Transformer Rectifier) Subtask 24-32-51-020-050-A A.

AES

Removal of the Transformer Rectifier (1)

Remove the protective caps (7) from the DC output terminals (2).

(2)

Remove the nuts (5), (8) and the washers (4), (9).

(3)

Disengage the lugs (3) from the output terminals.

(4)

Put SLEEVE - INSULATING on the lugs (3).

(5)

Disconnect the connectors (6).

(6)

Put CAP - BLANKING on the connectors.

(7)

Remove the screws (11) and the washers (10).

(8)

Pull the transformer rectifier (1) to remove it.

24-32-51 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

822

FR16

A

1PU2

A

FR9

1PU1

1

2 3 4 5 6

6

11 10 7

2 3 9 8 7

N_MM_243251_4_AAM0_01_00

AES

FIGURE 24-32-51-991-00100-A SHEET 1 Transformer Rectifier

24-32-51 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-32-51-400-001-A Installation of the Transformer Rectifier WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 1PU1, 1PU2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

B.

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

126 822

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-32-00-710-001-A

DESIGNATION Operational Test of the DC Generation Switching

(Ref. Fig. 24-32-51-991-00100-A - Transformer Rectifier) 3.

Job Set-up Subtask 24-32-51-865-051-A A.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL FOR FIN 1PU1 123VU

TR1/SPLY

2PU1

AB10

FOR FIN 1PU2 123VU

TR2/214XP/SPLY

2PU2

AB04

TR2/SVCE/BUS 2/SPLY

1XX

AB08

123VU

DESIGNATION

FIN

LOCATION

Subtask 24-32-51-010-051-A B.

AES

Get access to the Avionics Compartment (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in positon at the access door 822.

(2)

Make sure that the access door 822 is open.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-32-51-991-00100-A - Transformer Rectifier) Subtask 24-32-51-420-050-A A.

Installation of the Transformer Rectifier (1)

Clean the component interface and/or the adjacent area.

(2)

Do an inspection of the component interface and/or the adjacent area.

(3)

Engage the transformer rectifier (1) on the centering pins to put it in position.

(4)

Install the washers (10) and the screws (11) and then tighten the screws.

(5)

Remove the blanking caps from the electrical connector(s).

(6)

Make sure that the electrical connectors are clean and in the correct condition.

(7)

Connect the connectors (6) to the transformer rectifier.

(8)

Remove the insulating sleeves from the lugs (3).

(9)

Connect the lugs (3) to the output terminals (2) of the transformer rectifier.

(10) Install the washer (4) and the nut (5) and TORQUE it to between 1.5 and 1.6 M.DAN (11.06 and 11.80 LBF.FT). (11) Install the washer (9) and the nut (8) and TORQUE it to between 0.6 and 0.7 M.DAN (53.10 and 61.95 LBF.IN). (12) Install the protective caps (7) on the output terminals (2). Subtask 24-32-51-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL FOR FIN 1PU1 123VU

DESIGNATION TR1/SPLY

2PU1

AB10

FOR FIN 1PU2 123VU

TR2/214XP/SPLY

2PU2

AB04

TR2/SVCE/BUS 2/SPLY

1XX

AB08

123VU

FIN

LOCATION

Subtask 24-32-51-710-050-A C.

Do an operational test of DC Generation Switching (Ref. TASK 24-32-00-710-001-A) NOTE :

5.

Before you start the operational test, you must reset the transformer rectifier from the CFDS.

Close-up Subtask 24-32-51-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access door 822.

(3)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-32-55-000-001-A Removal of the TR 1 and TR 2 Contactors and the TR 2/AC Service Bus Normal Supply Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 5PU1, 5PU2, 14PU 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

** On A/C 003-004 No specific

AR

CAP - BLANKING

No specific

AR

WARNING NOTICE(S)

AR

CAP - BLANKING

** On A/C 005-099 FOR FIN 5PU1(CNTOR-TR 1) FOR FIN 5PU2(CNTOR-TR 2) No specific B.

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 25-11-41-000-001-A

DESIGNATION Removal of the Third Occupant Seat

(Ref. Fig. 24-32-55-991-00100-A - Transformer Rectifier Contactors - Location) (Ref. Fig. 24-32-55-991-00100-B - Transformer Rectifier Contactors - Location) (Ref. Fig. 24-32-55-991-00200-A - TR 2/AC Service Bus Normal Supply Contactor) (Ref. Fig. 24-32-55-991-00300-A - TR 1 and TR 2 Contactors) (Ref. Fig. 24-32-55-991-00200-B - TR 2/AC Service Bus Normal Supply Contactor) (Ref. Fig. 24-32-55-991-00300-B - TR 1 and TR 2 Contactors) FOR FIN 13PN(MODULE-DC BUS 1 CNTOR) 24-61-58-000-001-A Removal of the DC Bus 1 Contactor Module FOR FIN 14PN(MODULE-DC BUS 2 CNTOR) 24-61-58-000-002-A

AES

Removal of the DC Bus 2 Contactor Module

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE FOR FIN 20XX(MODULE- AC SVCE BUS CNTOR) 24-42-58-000-001-A FOR FIN 5PU1(CNTOR-TR 1)

DESIGNATION

Removal of the AC Service Bus Contactor Module

FOR FIN 5PU2(CNTOR-TR 2) (Ref. Fig. 24-32-55-991-00300-B - TR 1 and TR 2 Contactors) 3.

Job Set-up ** On A/C ALL Subtask 24-32-55-010-050-A A.

Get Access ** On A/C 003-004 (Ref. Fig. 24-32-55-991-00100-A - Transformer Rectifier Contactors - Location) ** On A/C 005-099 (Ref. Fig. 24-32-55-991-00100-B - Transformer Rectifier Contactors - Location) (1)

Remove the Third Occupant seat ** On A/C ALL (Ref. TASK 25-11-41-000-001-A)

(2)

In the cockpit: (a)

FOR 14PU (CNTOR-TR 2/AC SVCE BUS NORM SPLY) remove the front panel of the panel 123VU.

(b)

FOR 5PU1 (CNTOR-TR 1), 5PU2 (CNTOR-TR 2) on the left lower side of the panel 120VU, remove the access door.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position on the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-32-55-860-050-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Put warning notice(s) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In . . . .

(4)

In the cockpit, put WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure

** On A/C 003-004 (Ref. Fig. 24-32-55-991-00200-A - TR 2/AC Service Bus Normal Supply Contactor) (Ref. Fig. 24-32-55-991-00300-A - TR 1 and TR 2 Contactors) ** On A/C 005-099 (Ref. Fig. 24-32-55-991-00200-B - TR 2/AC Service Bus Normal Supply Contactor) (Ref. Fig. 24-32-55-991-00300-B - TR 1 and TR 2 Contactors) ** On A/C 003-004 Subtask 24-32-55-020-050-A A.

Removal of the Contactor CAUTION :

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

(1)

Disconnect the electrical connector (9).

(2)

Put CAP - BLANKING on the disconnected electrical connector (9) and the electrical receptacle (8).

(3)

Loosen the captive screws (7). NOTE :

(4)

Do not remove the captive screws (7) and the spring washers from the contactor (10).

Remove the contactor (10).

Subtask 24-32-55-020-053-A CAUTION :

B.

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Removal of the Contactor Base NOTE :

The removal of the contactor base is necessary only if it is damaged.

(1)

Remove the nuts (11) and the washers (12).

(2)

Disconnect the cables (13) from the contactor base (1).

(3)

Remove the nuts (6) and the washers (5).

(4)

Remove the jumper (4) from the contactor base (1) and from the adjacent contactor base.

(5)

Remove the screws (3) and the washers (2).

(6)

Remove the contactor base (1).

** On A/C 005-099 Subtask 24-32-55-020-050-B CAUTION :

A.

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Removal of the Contactors (Ref. Fig. 24-32-55-991-00200-B - TR 2/AC Service Bus Normal Supply Contactor)

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (1)

FOR 5PU1 (CNTOR-TR 1), 5PU2 (CNTOR-TR 2) (Ref. Fig. 24-32-55-991-00300-B - TR 1 and TR 2 Contactors) (a)

Disconnect the electrical connector (4).

(b)

Put CAP - BLANKING on the disconnected electrical connector (4) and the electrical receptacle (2).

(c)

Loosen the captive screws (3). NOTE :

(d)

Do not remove the captive screws (3) and the spring washers from the contactor (5).

Remove the contactor (5).

Subtask 24-32-55-020-053-B CAUTION :

B.

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Removal of the Modules 20XX, 13PN and 14PN NOTE :

AES

The removal of the modules is necessary only if they are damaged.

(1)

FOR 20XX (MODULE- AC SVCE BUS CNTOR) . Remove the module 20XX (Ref. TASK 24-42-58-000-001-A).

(2)

FOR 13PN (MODULE-DC BUS 1 CNTOR) . Remove the module 13PN (Ref. TASK 24-61-58-000-001-A).

(3)

FOR 14PN (MODULE-DC BUS 2 CNTOR) . Remove the module 14PN (Ref. TASK 24-61-58-000-002-A).

24-32-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

122VU

121VU

124VU

125VU

123VU

B

A

B

5PU2

A 14PU

5PU1

D D

C

N_MM_243255_4_AAM0_01_00

AES

FIGURE 24-32-55-991-00100-A SHEET 1 Transformer Rectifier Contactors - Location

24-32-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A 122VU

121VU

14PU

124VU

125VU

123VU 20XX

B

A

B

14PN 13PN 5PU2 5PU1

D D

N_MM_243255_4_AAP0_01_00

AES

FIGURE 24-32-55-991-00100-B SHEET 1 Transformer Rectifier Contactors - Location

24-32-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

122VU

14PU

A 123VU

121VU

125VU

124VU 123VU

B A

B

13 12

14

11

CONTACTOR BASE 1 10 CONTACTOR 2 3

9 8

7 5 6

4

N_MM_243255_4_ACM0_01_00

AES

FIGURE 24-32-55-991-00200-A SHEET 1 TR 2/AC Service Bus Normal Supply Contactor

24-32-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

A

122VU

121VU

125VU

124VU 123VU

A 5PU2 5PU1

B B B 13

12 14

11

CONTACTOR BASE 7

1

CONTACTOR 10

2 3 9

8

7

4 5 6 N_MM_243255_4_AEM0_01_00

AES

FIGURE 24-32-55-991-00300-A SHEET 1 TR 1 and TR 2 Contactors

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A

122VU 14PU 121VU

124VU

125VU

123VU 20XX

A

B 1

5 CONTACTOR MODULE 20XX

2 4 3

N_MM_243255_4_ACP0_01_00

AES

FIGURE 24-32-55-991-00200-B SHEET 1 TR 2/AC Service Bus Normal Supply Contactor

24-32-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

120VU

A 122VU

121VU

124VU

125VU

123VU 1

A 14PN 13PN 5PU2 5PU1

B B

B

1

3

MODULE

CONTACTOR 5

4

2 3 N_MM_243255_4_AEP0_01_00

AES

FIGURE 24-32-55-991-00300-B SHEET 1 TR 1 and TR 2 Contactors

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-32-55-400-001-A Installation of the TR 1 and TR 2 Contactors and the TR 2/AC Service Bus Normal Supply Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 5PU1, 5PU2, 14PU 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

WARNING NOTICE(S)

** On A/C 003-004 No specific

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

FOR FIN 14PU(CNTOR-TR 2/AC SVCE BUS NORM SPLY) No specific

Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

FOR FIN 5PU1(CNTOR-TR 1) FOR FIN 5PU2(CNTOR-TR 2) No specific

B.

Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 20-21-15-912-001-A

DESIGNATION Tightening Torques for Electrical Component Fasteners

24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-11-41-000-001-A

Removal of the Third Occupant Seat

25-11-41-400-001-A 31-60-00-860-001-A

Installation of the Third Occupant Seat EIS Start Procedure

AES

24-32-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 31-60-00-860-002-A

DESIGNATION EIS Stop Procedure

(Ref. Fig. 24-32-55-991-00100-A - Transformer Rectifier Contactors - Location) (Ref. Fig. 24-32-55-991-00100-B - Transformer Rectifier Contactors - Location) ** On A/C 005-099 FOR FIN 13PN(MODULE-DC BUS 1 CNTOR) 24-61-58-400-001-A Installation of the DC Bus 1 Contactor Module FOR FIN 14PN(MODULE-DC BUS 2 CNTOR) 24-61-58-400-002-A Installation of the DC Bus 2 Contactor Module FOR FIN 14PU(CNTOR-TR 2/AC SVCE BUS NORM SPLY) FOR FIN 5PU1(CNTOR-TR 1) (Ref. Fig. 24-32-55-991-00200-A - TR 2/AC Service Bus Normal Supply Contactor) (Ref. Fig. 24-32-55-991-00200-B - TR 2/AC Service Bus Normal Supply Contactor) FOR FIN 20XX(MODULE- AC SVCE BUS CNTOR) 24-42-58-400-001-A FOR FIN 5PU2(CNTOR-TR 2)

Installation of the AC Service Bus Contactor Module

(Ref. Fig. 24-32-55-991-00300-A - TR 1 and TR 2 Contactors) (Ref. Fig. 24-32-55-991-00300-B - TR 1 and TR 2 Contactors) 3.

Job Set-up ** On A/C ALL Subtask 24-32-55-010-051-A A.

Get Access (1)

Make sure that the Third Occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(2)

In the cockpit: (a)

FOR 14PU (CNTOR-TR 2/AC SVCE BUS NORM SPLY) make sure that front panel of the panel 123VU is removed.

(b)

FOR 5PU1 (CNTOR-TR 1), 5PU2 (CNTOR-TR 2) make sure that on the left lower side of the panel 120VU, the access door is removed.

(3)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

Subtask 24-32-55-860-051-A B.

AES

Aircraft Maintenance Configuration (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Make sure that the WARNING NOTICE(S) is in position at the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: . BAT 1, BAT 2, . APU GEN,

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . . (4)

4.

GEN 1, GEN 2, EXT PWR.

In the cockpit, make sure that the WARNING NOTICE(S) are in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

Procedure

** On A/C 003-004 (Ref. Fig. 24-32-55-991-00100-A - Transformer Rectifier Contactors - Location) ** On A/C 005-099 (Ref. Fig. 24-32-55-991-00100-B - Transformer Rectifier Contactors - Location) CAUTION :

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

** On A/C 003-004 Subtask 24-32-55-420-053-A CAUTION :

A.

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Installation of the Contactor Base NOTE :

The installation of a contactor base is necessary only if it was removed.

(1)

Install the contactor base (1) in correct position.

(2)

Install the washers (2) and screws (3) and tighten them.

(3)

Make sure that the electrical cables (13) are clean and in correct condition.

(4)

Installation of the electrical cables (13). (a)

Install the washers (12) and the nuts (11).

(b)

TORQUE the nuts (11) to between 0.27 and 0.3 M.DAN (23.89 and 26.55 LBF.IN).

(5)

Install the jumpers (4) between the contactor base (1) and the adjacent base.

(6)

Install the washers (5) and the nuts (6) and tighten them (Ref. TASK 20-21-15-912-001-A).

Subtask 24-32-55-420-050-A B.

Installation of the Contactor (1)

FOR 5PU1 (CNTOR-TR 1), 14PU (CNTOR-TR 2/AC SVCE BUS NORM SPLY) (Ref. Fig. 24-32-55-991-00200-A - TR 2/AC Service Bus Normal Supply Contactor)

(2)

FOR 5PU2 (CNTOR-TR 2) (Ref. Fig. 24-32-55-991-00300-A - TR 1 and TR 2 Contactors) (a)

AES

Install the contactor (10) on the tapped barrels (14) of the contactor base (1).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b)

TORQUE the captive screws (7): 1

FOR 5PU1 (CNTOR-TR 1), 5PU2 (CNTOR-TR 2) TORQUE the screws to between 33.63 and 41.6 LBF.IN (0.38 and 0.47 M.DAN).

2

FOR 14PU (CNTOR-TR 2/AC SVCE BUS NORM SPLY) TORQUE the screws to between 13.28 and 15.93 LBF.IN (0.15 and 0.18 M.DAN).

(c)

Remove the blanking caps from the electrical connector(s).

(d)

Make sure that the electrical connectors are clean and in the correct condition.

(e)

Connect the connector (9).

** On A/C 005-099 Subtask 24-32-55-420-053-B A.

Intallation of the Modules 20XX, 13PN, and 14PN NOTE :

The installation of the modules is necessary only if they were removed.

(1)

FOR 20XX (MODULE- AC SVCE BUS CNTOR) . Install the module 20XX (Ref. TASK 24-42-58-400-001-A).

(2)

FOR 13PN (MODULE-DC BUS 1 CNTOR) . Install the module 13PN (Ref. TASK 24-61-58-400-001-A).

(3)

FOR 14PN (MODULE-DC BUS 2 CNTOR) . Install the module 14PN (Ref. TASK 24-61-58-400-002-A).

Subtask 24-32-55-420-050-B B.

AES

Installation of the Contactors (1)

FOR 5PU1 (CNTOR-TR 1), 14PU (CNTOR-TR 2/AC SVCE BUS NORM SPLY) (Ref. Fig. 24-32-55-991-00200-B - TR 2/AC Service Bus Normal Supply Contactor)

(2)

FOR 5PU2 (CNTOR-TR 2) (Ref. Fig. 24-32-55-991-00300-B - TR 1 and TR 2 Contactors) (a)

Install the contactor (5) on the module.

(b)

TORQUE the captive screws (3): 1

FOR 5PU1 (CNTOR-TR 1), 5PU2 (CNTOR-TR 2) TORQUE the screws to between 33.63 and 41.6 LBF.IN (0.38 and 0.47 M.DAN).

2

FOR 14PU (CNTOR-TR 2/AC SVCE BUS NORM SPLY) TORQUE the screws to between 13.28 and 15.93 LBF.IN (0.15 and 0.18 M.DAN).

(c)

Remove the blanking caps from the electrical connector (4) and the electrical receptacle (2).

(d)

Make sure that the electrical connectors are clean and in the correct condition.

(e)

Connect the electrical connector (4) to the contactor (5).

24-32-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Subtask 24-32-55-861-051-A C.

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002A-02).

Subtask 24-32-55-860-052-A D.

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

Subtask 24-32-55-710-050-A E.

Test of the Contactor (1)

On the ECAM control panel: . push the ELEC key to get the ELEC system page.

(2)

On the lower ECAM DU, make sure that the aircraft electrical configuration is correct.

Subtask 24-32-55-860-053-A F.

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

Subtask 24-32-55-862-051-A G.

5.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Close-up Subtask 24-32-55-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

In the cockpit: (a)

FOR 14PU (CNTOR-TR 2/AC SVCE BUS NORM SPLY) install the front panel of the panel 123VU.

(b)

FOR 5PU1 (CNTOR-TR 1), 5PU2 (CNTOR-TR 2) in the left Lower side of the panel 120VU, install the access door.

(3)

Install the third occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

24-32-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC EMERGENCY GENERATION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The DC emergency generation consists in the essential Transformer Rectifier (TR) and its associated contactor. It is supplied with 115 VAC/400 Hz either by the emergency generator or by the AC normal busbars, in failure conditions.

AES

24-34-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-34-00-12400-B - DC Emergency Generation - Component Location) FIN

1PE 3PE

AES

FUNCTIONAL DESIGNATION TR-ESS CNTOR-ESS TR

PANEL

106VU

ZONE ACCESS ATA REF. DOOR 125 24-34-51 125 24-34-55

24-34-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

Component Desccription (Ref. Fig. 24-34-00-14300-B - Essential TR Contactor-Control - Simplified Logic) A.

Essential TR The essential TR directly controls its contactor (3PE). The essential TR is ventilated by natural convection.

B.

Characteristics of the Essential TR ** On A/C ALL EMB SB 24-1099 FOR A/C 003-005 (see ATA Ref : 24-32-00). The essential TR is fully interchangeable with normal TR1 (1PU1) and has the same electrical properties. NOTE :

AES

The normal TR2 (1PU2) has not the same electrical properties and is not interchangeable.

24-34-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Operation/Control and Indicating The essential TR starts to operate as soon as it is supplied. It is supplied in the following cases: . loss of TR1, . loss of TR2, . loss of both TRs, . loss of DC NORM BUS 1 switching contactor (1PC1) or DC ESS BUS supply contactor (4PC), . availability of emergency generator in operation (Ref. 24-24-00-00). The essential TR is linked to the ECAM system in the same manner as the main TRs (Ref. 24-32-00, P. Block 1). A.

Reset of the Protection of the TR Before you reset the TR, make sure that the related electrical network supplies its primary winding, in any RESET mode. (1) From the panel 103VU To reset the TR protection push TR RST pushbutton switch 15PU located on panel 103 VU. (2) Description of the reset procedure The reset procedure must be performed by selecting the SYSTEM REPORT/TEST item on the CFDS menu, then by selecting the TR 3 page from the ELEC page. (a) If the reset is effective, the NO FAULT message appears on the MCDU. (b) If the reset is impossible: . the TR 3 message is displayed on the MCDU.

AES

24-34-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR16

FR9

A

B

1PE

A

812

C

B 106VU

C

3PE

N_MM_243400_0_AAL0_01_00

AES

FIGURE 24-34-00-12400-B SHEET 1 DC Emergency Generation - Component Location

24-34-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

+

EMER 115VAC GEN 8XE

4PP 28VDC ESS BUS

28VDC

−

4PE

SUPPLY

RESET

FAULT DETECTION

− +

CNTOR CONTROL MEASURE

5PE

U − +

1PE 3PE

N_MM_243400_0_ACN0_01_00

AES

FIGURE 24-34-00-14300-B SHEET 1 Essential TR Contactor-Control - Simplified Logic

24-34-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC EMERGENCY GENERATION - ADJUSTMENT/TEST ** On A/C ALL Task 24-34-00-710-001-A Operational Test of the DC EMER CONFIG Caution 1.

Reason for the Job (Ref. MPD 24-34-00-01-) OPERATIONAL CHECK OF ”DC EMERG. CONFIG” CAUTION Make sure that the DC EMER CONFIG caution appears in case of loss of the DC network.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

210 812

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

3.

Job Set-up Subtask 24-34-00-860-050-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

Subtask 24-34-00-010-050-A B.

Get access to the Avionics Compartment (1)

AES

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the avionics compartment door 812.

24-34-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Open the access door 812.

(3)

Open the access panel on the AC/DC emergency power center 106VU.

Subtask 24-34-00-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

49VU

DESIGNATION SDAC/1 AND 2/28VDC/ESS BUS

12WV

F05

106VU

DC BUS/1 AND 2/MONG

68WV

C03

4.

FIN

LOCATION

Procedure Subtask 24-34-00-710-050-A A.

Operational Test of the DC EMER CONFIG Caution ACTION

RESULT

1.On the panel 106VU: . open the circuit breaker 68WV. 2.On the panel 49VU: . open the circuit breaker 12WV.

3.On the panel 49VU: . close the circuit breaker 12WV. 4.On the panel 106VU: . close the circuit breaker 68WV. 5.

On the upper ECAM DU: . DC EMER CONFIG indication comes into view, with these indications below: - EMER ELEC PWR..MAN ON, - C/B TRIPPED L ELEC BAY. On the lower ECAM DU: . the ELEC page comes into view with the amber DC ESS indication. On the upper ECAM DU: . DC EMER CONFIG and EMER ELEC PWR..MAN ON indications go out of view. On the upper ECAM DU: . C/B TRIPPED L ELEC BAY indication goes out of view.

Close-up Subtask 24-34-00-410-050-A A.

Close Access (1)

Close the access panel on the AC/DC emergency power center 106VU.

(2)

Close the access door 812.

(3)

Remove the access platform(s).

Subtask 24-34-00-860-051-A B.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-34-00 PB501

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

TRANSFORMER RECTIFIER - REMOVAL/INSTALLATION ** On A/C ALL Task 24-34-51-000-001-A Removal of the Essential Transformer Rectifier FIN 1PE 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific No specific

AR AR

SAFETY CLIP - CIRCUIT BREAKER SLEEVE - INSULATING

B.

Work Zones and Access Panels ZONE/ACCESS

125 812

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE (Ref. Fig. 24-34-51-991-00200-A - Essential Transformer Rectifier) 3.

DESIGNATION

Job Set-up Subtask 24-34-51-010-050-A A.

Aircraft Maintenance Configuration (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the avionics compartment door 812.

(2)

Open the access door 812.

(3)

Open the access panel of the AC/DC emergency power center 106VU.

Subtask 24-34-51-865-050-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL

106VU 4.

DESIGNATION

FIN

ESS TR/SPLY

4PE

LOCATION C01

Procedure (Ref. Fig. 24-34-51-991-00200-A - Essential Transformer Rectifier)

AES

24-34-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-34-51-020-050-A A.

AES

Removal of the Essential Transformer Rectifier (1)

Remove the protective caps from the output terminals (8).

(2)

Remove the nuts (5), (10) and the washers (6), (9).

(3)

Disengage the lugs (7) from the output terminals.

(4)

Put an SLEEVE - INSULATING on the lugs.

(5)

Disconnect the connectors (4).

(6)

Put CAP - BLANKING on the connectors.

(7)

Remove the screws (3) and the washers (2).

(8)

Remove the transformer rectifier (1).

24-34-51 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR16

FR9

106VU

A

812

A

1PE

1

2 3

4 7 9 10 8 7 6 5 N_MM_243451_4_ACM0_01_00

AES

FIGURE 24-34-51-991-00200-A SHEET 1 Essential Transformer Rectifier

24-34-51 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-34-51-400-001-A Installation of the Essential Transformer Rectifier FIN 1PE 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

B.

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

125 812

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-24-00-710-001-A

DESIGNATION Operational Test of the Emergency Generation System

(Ref. Fig. 24-34-51-991-00200-A - Essential Transformer Rectifier) 3.

Job Set-up Subtask 24-34-51-860-050-A A.

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 812.

(2)

Make sure that the access door 812 is open.

(3)

In the avionics compartment, make sure that the access panel of the AC/DC emergency power center 106VU is open.

Subtask 24-34-51-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

106VU 4.

DESIGNATION

FIN

ESS TR/SPLY

4PE

LOCATION C01

Procedure (Ref. Fig. 24-34-51-991-00200-A - Essential Transformer Rectifier) Subtask 24-34-51-420-050-A A.

Installation of the Essential Transformer Rectifier (1)

AES

Put the transformer rectifier (1) in position.

24-34-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Install the washers (2) and the screws (3) and then tighten the screws.

(3)

Remove the blanking caps from the connectors.

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the connectors (4) to the transformer rectifier.

(6)

Remove the insulating sleeves from the lugs.

(7)

Connect the lugs (7) to the output terminals (8).

(8)

Install the washer (6) and the nut (5) and TORQUE it to between 0.6 and 0.7 M.DAN (53.10 and 61.95 LBF.IN).

(9)

Install the washer (9) and the nut (10) and TORQUE it to between 1.5 and 1.6 M.DAN (11.06 and 11.80 LBF.FT).

(10) Install the protective caps on the terminals (8). Subtask 24-34-51-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

DESIGNATION

106VU

ESS TR/SPLY

FIN 4PE

LOCATION C01

Subtask 24-34-51-710-050-A C.

Operational Test of the Emergency Generation System (1)

5.

Do an operational test of the Emergency Generation System (Ref. TASK 24-24-00-710-001-A).

Close-up Subtask 24-34-51-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

In the avionics compartment, close the access panel of the AC/DC emergency power center 106VU.

(3)

Close the access door 812.

(4)

Remove the access platform(s).

24-34-51 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-34-55-000-001-A Removal of the Essential TR Contactor FIN 3PE 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

B.

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE (Ref. Fig. 24-34-55-991-00100-B - Essential TR Contactor) 3.

DESIGNATION

Job Set-up Subtask 24-34-55-010-050-A A.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the avionics compartment doors 812 and 822.

(2)

Open the access doors 812 and 822.

(3)

Open the access panels of the AC/DC emergency power center 106VU and the access panels of the BATTERY power center 105VU.

Subtask 24-34-55-865-050-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL

105VU

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

AES

FIN

LOCATION

24-34-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL

DESIGNATION AC ESS/BUS ON/BUS 2

123VU 4.

FIN 2XC

LOCATION AC01

Procedure (Ref. Fig. 24-34-55-991-00100-B - Essential TR Contactor) Subtask 24-34-55-020-050-A A.

Removal of the Contactor CAUTION :

(1)

Disconnect the connector (4).

(2)

Put blanking caps on the disconnected electrical connector(s).

(3)

Loosen the captive screws (3). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (3) and the spring washers from contactor(5).

Disengage the contactor (5) from the base (1) and remove the contactor.

24-34-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR16

FR9 106VU

A 822

A

812

105VU

B

3PE

B 6

1

3

CONTACTOR BASE

CONTACTOR 5

7 4

3

N_MM_243455_4_AAL0_01_00

AES

FIGURE 24-34-55-991-00100-B SHEET 1 Essential TR Contactor

24-34-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-34-55-400-001-A Installation of the Essential TR Contactor FIN 3PE 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

B.

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-24-00-710-001-A

DESIGNATION Operational Test of the Emergency Generation System

(Ref. Fig. 24-34-55-991-00100-B - Essential TR Contactor) 3.

Job Set-up Subtask 24-34-55-860-050-A A.

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access doors 812 and 822.

(2)

Make sure that the access doors 812 and 822 are open.

(3)

In the avionics compartment, make sure that the access panel of the AC/DC emergency power center 106VU and BATTERY power center 105VU are open.

Subtask 24-34-55-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

AES

FIN

LOCATION

24-34-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-34-55-991-00100-B - Essential TR Contactor) CAUTION :

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

Subtask 24-34-55-420-050-A A.

Installation of the Contactor (1)

Install the contactor (5) in position on the tapped barrels (6) of the connecting base (1).

(2)

TORQUE the captive screws (3) to between 0.27 and 0.30 M.DAN (23.89 and 26.55 LBF.IN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the connector (4) on the contactor (5).

Subtask 24-34-55-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

FIN C01

LOCATION

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

Subtask 24-34-55-710-050-A C.

Operational Test of the Emergency Generation System (1)

5.

Do an operational test of the Emergency Generation System (Ref. TASK 24-24-00-710-001-A).

Close-up Subtask 24-34-55-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

In the avionics compartment, close the access panels of the AC/DC emergency power center 106VU and the BATTERY power center 105VU.

(3)

Close the access doors 812 and 822.

(4)

Remove the access platform(s).

24-34-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC ESSENTIAL & NORMAL GENERATION SWITCHING DESCRIPTION AND OPERATION ** On A/C ALL 1.

General These circuits control the supply of DC normal busbars and DC essential busbars. They enable: . their normal supply in normal flight configuration, . automatic transfer in some failure conditions.

AES

24-35-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location

** On A/C 003-004 (Ref. Fig. 24-35-00-12500-C - DC Essential & Normal Generation Switching - Component Location) ** On A/C 005-099 (Ref. Fig. 24-35-00-12500-D - DC Essential & Normal Generation Switching - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS ATA REF. DOOR

** On A/C ALL 1PC1 CNTOR-DC NORM BUS 1 SWITCHING 1PC2 CNTOR-DC NORM BUS 2 SWITCHING 4PC CNTOR-DC ESS BUS SUPPLY ** On A/C 003-004

120VU 120VU 106VU

212 212 125

24-35-55 24-35-55 24-35-55

20PC HOLDER-FUSE 120VU 212 24-35-00 ------------------------------------------------------------------------------FIN ! FUNCTIONAL DESIGNATION ! PANEL ! ZONE ! ACCESS ! ATA ! ! ! ! DOOR ! REF. ------------------------------------------------------------------------------20PC1 FUSE 120VU 212 24-35-00

AES

24-35-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

Operation/Control and Indicating A.

DC NORM BUS SWITCHING Contactor Control (1PC1 and 1PC2) (Ref. Fig. 24-35-00-14200-B - DC NORM BUS SWITCHING Contactor Control - Simplified Logic) Contactor 1PC1 is supplied in normal configuration and when a TR is lost. Contactor 1PC2 is supplied when a TR is lost or in case of DC NORM BUS 1 SWITCHING contactor (1PC1) failure. NOTE :

B.

AES

There is an electric interlock between contactors 1PC2 and 4PC to inhibit coupling between busbar 2PP and essential busbar 4PP.

DC ESS BUS SPLY Contactor Control (4PC) (Ref. Fig. 24-35-00-14300-B - DC ESS BUS SPLY Contactor Control - Simplified Logic) Contactor 4PC supplies DC ESS BUS 4PP via BAT BUS 3PP if normal DC busbars 1PP and 2PP are not coupled (electrical interlock between contactors 1PC2 and 4PC). DC ESS BUS SPLY contactor (4PC) opens when a normal TR is lost (coupling of busbars 1PP and 2PP), in emergency conditions or when the DC NORM BUS 1 SWITCHING contactor (1PC1) is lost.

24-35-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 FR16

A FR9

106VU

A

822 120VU

122VU

D

C 121VU

20PC

125VU 123VU

124VU

4PC

B

B

20PC1

C

C 1PC2 1PC1

C

20PC

D

N_MM_243500_0_ABL0_01_00

AES

FIGURE 24-35-00-12500-C SHEET 1 DC Essential & Normal Generation Switching - Component Location

24-35-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 FR16

A

FR9

106VU

822

A 120VU

122VU

C

121VU 125VU

D

123VU

124VU

4PC

B

B

20PC1

C 14PN

C

13PN

1PC2 1PC1

C

20PC

D

N_MM_243500_0_ABM0_01_00

AES

FIGURE 24-35-00-12500-D SHEET 1 DC Essential & Normal Generation Switching - Component Location

24-35-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4PC 1PC1 2PP 5PU2

2PP 28VDC BUS2 1XP 2XP

4PC

28V 2PP FAULT TR1

FAULT TR2

1XP 5PU1 28V 1PP

1PP 28VDC BUS1

1PC1

1PC2

3PP 28VDC BAT BUS

** On A/C ALL

N_MM_243500_0_ACL0_01_00

AES

FIGURE 24-35-00-14200-B SHEET 1 DC NORM BUS SWITCHING Contactor Control Simplified Logic

24-35-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

1PC2 2PP 28VDC BUS2

28V 1PP 5PU1 1PC2 1PC1

3PE

1PP 28VDC BUS1

1PC1

3PP 28VDC BAT BUS

4PC

4PP 28VDC ESS BUS

** On A/C ALL

N_MM_243500_0_AEL0_01_00

AES

FIGURE 24-35-00-14300-B SHEET 1 DC ESS BUS SPLY Contactor Control - Simplified Logic

24-35-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-35-55-000-001-A Removal of the Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 1PC1, 1PC2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 25-11-41-000-001-A

DESIGNATION Removal of the Third Occupant Seat

(Ref. Fig. 24-35-55-991-00500-A - Contactors) (Ref. Fig. 24-35-55-991-00500-B - Contactors) 3.

Job Set-up Subtask 24-35-55-010-051-A A.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

Remove the front panel on the bottom right side of the panel 120VU.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-35-55-860-050-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Put WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

24-35-55 PB401

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4.

(3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

(4)

In the cockpit, put WARNING NOTICE(S) in position to tell the persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section) . 35VU (ELEC).

Procedure

** On A/C 003-004 (Ref. Fig. 24-35-55-991-00500-A - Contactors) ** On A/C 005-099 (Ref. Fig. 24-35-55-991-00500-B - Contactors) ** On A/C ALL Subtask 24-35-55-020-050-A A.

Removal of the Contactor CAUTION :

(1)

Disconnect the electrical connector (4).

(2)

Put a blanking caps on the disconnect electrical connector (4) and the electrical receptacle.

(3)

Loosen the captive screws (3). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (3) and the spring washers from the contactor (5).

Remove the contactor (5).

24-35-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

122VU

A 121VU

125VU

124VU 123VU

A

1PC2 1PC1

3

B

B

6

1

B

CONTACTOR BASE

CONTACTOR 5

4 7

3

N_MM_243555_4_AEL0_01_00

AES

FIGURE 24-35-55-991-00500-A SHEET 1 Contactors

24-35-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A 122VU

121VU

125VU

124VU 123VU

A 14PN 13PN

1PC2 1PC1

B B

3

1

B

MODULE

CONTACTOR 4

5

3

N_MM_243555_4_AEN0_01_00

AES

FIGURE 24-35-55-991-00500-B SHEET 1 Contactors

24-35-55 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-35-55-400-001-A Installation of the Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 1PC1, 1PC2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific

B.

QTY AR WARNING NOTICE(S)

Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

DESIGNATION

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 24-32-00-710-001-A

DESIGNATION Operational Test of the DC Generation Switching

25-11-41-000-001-A

Removal of the Third Occupant Seat

25-11-41-400-001-A

Installation of the Third Occupant Seat

(Ref. Fig. 24-35-55-991-00500-A - Contactors) (Ref. Fig. 24-35-55-991-00500-B - Contactors) 3.

Job Set-up Subtask 24-35-55-860-051-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the access platform is in position at the access door 121AL.

(2)

Make sure that the access door 121AL is open.

(3)

Make sure that the external power connector is not connected to the aircraft receptacle.

(4)

Make sure that, on the access door 121AL, there is a WARNING NOTICE(S) to tell persons not to connect the external power connector.

(5)

In . . . .

the cockpit, on the overhead panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

24-35-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4.

(6)

Make sure that there is a WARNING NOTICE(S) in the cockpit to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(7)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

(8)

In the cockpit, make sure that the third occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(9)

In the cockpit, make sure that the front panel on the bottom right side of the panel 120VU is removed.

Procedure

** On A/C 003-004 (Ref. Fig. 24-35-55-991-00500-A - Contactors) ** On A/C 005-099 (Ref. Fig. 24-35-55-991-00500-B - Contactors) ** On A/C 003-004 Subtask 24-35-55-420-050-A A.

Installation of the Contactor CAUTION :

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Install the contactor (5) on the tapped barrels (6) of the connecting base (1).

(2)

TORQUE the captive screws (3) to between 33.63 and 41.6 LBF.IN (0.38 and 0.47 M.DAN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (4) to the contactor (5).

** On A/C 005-099 Subtask 24-35-55-420-050-B A.

Installation of the Contactor CAUTION :

AES

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Install the contactor (5) on the module 13PN (14PN) (1).

(2)

TORQUE the captive screws (3) to between 33.63 and 41.6 LBF.IN (0.38 and 0.47 M.DAN).

(3)

Remove the blanking caps from the electrical connector (4) and the electrical receptacle.

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (4) to the contactor (5).

24-35-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Subtask 24-35-55-710-050-A B.

Operational Test of DC Generation Switching (1)

5.

Do the operational test of DC Generation Switching (Ref. TASK 24-32-00-710-001-A).

Close-up Subtask 24-35-55-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the front panel on the bottom right side of the panel 120VU.

(3)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

24-35-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-35-55-000-002-A Removal of the Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 4PC 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

B.

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE (Ref. Fig. 24-35-55-991-00600-A - Contactor) 3.

DESIGNATION

Job Set-up Subtask 24-35-55-010-052-A A.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the avionics compartment doors 812 and 822.

(2)

Open the access doors 812 and 822.

(3)

Open the access panels of the AC/DC emergency power center 106VU and BATTERY power center 105VU.

Subtask 24-35-55-865-050-A B.

Open, safety and tag this(these) circuit breaker(s):

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

AES

FIN

LOCATION

24-35-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL

DESIGNATION AC ESS/BUS ON/BUS 2

123VU 4.

FIN 2XC

LOCATION AC01

Procedure (Ref. Fig. 24-35-55-991-00600-A - Contactor) Subtask 24-35-55-020-051-A A.

Removal of the Contactor CAUTION :

(1)

Disconnect the electrical connector (4).

(2)

Put blanking caps on the disconnected electrical connector(s).

(3)

Loosen the captive screws (3). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (3) and the spring washers from the contactor (5).

Release the contactor (5) from its base (1) and remove it.

24-35-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR16 FR9

822

106VU

A

A

812

105PU

4PC

B B

6

1

3

CONTACTOR BASE

CONTACTOR 5

4 7

3

N_MM_243555_4_AGL0_01_00

AES

FIGURE 24-35-55-991-00600-A SHEET 1 Contactor

24-35-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-35-55-400-002-A Installation of the Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 4PC 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

B.

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-32-00-710-001-A

DESIGNATION Operational Test of the DC Generation Switching

(Ref. Fig. 24-35-55-991-00600-A - Contactor) 3.

Job Set-up Subtask 24-35-55-010-054-A A.

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access doors 812 and 822.

(2)

Make sure that the access doors 812 and 822 are open.

(3)

In the avionics compartment, make sure that the access panels of the AC/DC emergency power center 106VU and BATTERY power center 105VU are open.

Subtask 24-35-55-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

AES

FIN

LOCATION

24-35-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL

DESIGNATION AC ESS/BUS ON/BUS 2

123VU 4.

FIN 2XC

LOCATION AC01

Procedure (Ref. Fig. 24-35-55-991-00600-A - Contactor) Subtask 24-35-55-420-051-A A.

Installation of the Contactor (1)

Install the contactor (5) in position on the tapped barrels (6) of the contactor base (1).

(2)

TORQUE the captive screws (3) to between 0.27 and 0.30 M.DAN (23.89 and 26.55 LBF.IN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (4) to the contactor (5).

Subtask 24-35-55-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

105VU

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

FIN

LOCATION

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

Subtask 24-35-55-710-051-A C.

Operational Test of the DC Generation Control (1)

5.

Do an operational test of the DC Generation Switching (Ref. TASK 24-32-00-710-001-A).

Close-up Subtask 24-35-55-410-052-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

In the avionics compartment, close the access panels of the AC/DC emergency power center 106VU and the BATTERY power center 105VU.

(3)

Close the access doors 812 and 822.

(4)

Remove the access platform(s).

24-35-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC GENERATION MONITORING AND INDICATING DESCRIPTION AND OPERATION ** On A/C ALL 1.

General Monitoring and indicating of aircraft DC generation and distribution are performed by means of: . two voltmeters located on the overhead ELEC panel (35VU) in the cockpit. They indicate to the flight crew the voltage of the HOT busses 701PP and 702PP. NOTE :

.

AES

The HOT busses are directly connected to the batteries as follows: . 701PP is connected to Bat 1, . 702PP is connected to Bat 2.

the centralized warning system (ECAM) on which the following parameters are available: . TRs voltage and current, . batteries voltage and current. Furthermore the ECAM system gives a synoptic of the electrical generation enabling the flight crew to know the current electrical configuration (DC essential and normal switching).

24-37-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-37-00-12400-A - DC Generation Monitoring and Indicating - Component Location) FIN

3PV1 3PV2

AES

FUNCTIONAL DESIGNATION VOLTMETER-BAT 1 VOLTMETER-BAT 2

PANEL 35VU 35VU

ZONE ACCESS ATA REF. DOOR 210 24-37-21 210 24-37-21

24-37-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

3PV1

DC BUS 1

1

BAT 1

V AC BUS 1

E

3PV2

BAT

2

35VU

BAT 2

FAULT

FAULT

OFF

OFF

DC BUS 2 AC ESS FEED V

FAULT ALTN

AC ESS BUS

E

AC BUS 2

B A

ELEC

BAT 1 28 V 20 A

DC BAT

BAT 2 28 V 0A

DC 1

DC 2 DC ESS

TR 1 28 V 75 A

ESS TR

AC 1

AC 2

AC ESS

GEN 1 26 % 116 V 4 0 0 HZ

B

TR 2 28 V 60 A

EMERG GEN

APU GEN

90 °C IDG 1

GEN 2 26 % 1 16 V 4 0 0 HZ IDG 2

TAT +19 °C SAT +18 °C

80 °C

G.W. 60 3 T C G 28 1 %

4WT2

N_MM_243700_0_AAM0_01_00

AES

FIGURE 24-37-00-12400-A SHEET 1 DC Generation Monitoring and Indicating - Component Location

24-37-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

VOLTMETER - REMOVAL/INSTALLATION ** On A/C ALL Task 24-37-21-000-001-A Removal of the Voltmeters FIN 3PV1, 3PV2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

ELECTRICAL CONTACTS EXTRACTION TOOLSMS2749R20

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

B.

Work Zones and Access Panels ZONE/ACCESS

210 822

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C.

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

(Ref. Fig. 24-37-21-991-00100-A - Voltmeters of Batteries) 3.

Job Set-up Subtask 24-37-21-861-051-A A.

Energize the ground service network (Ref. TASK 24-42-00-861-001-A)

Subtask 24-37-21-010-050-A B.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the avionics compartment door 822.

(2)

Open the access door 822.

(3)

Open the access panel of the BATTERY power center 105VU.

Subtask 24-37-21-865-050-A C.

Open, safety and tag this(these) circuit breaker(s):

PANEL FOR FIN 3PV1 105VU

AES

DESIGNATION ELEC/BAT REF/BCL1

FIN 9PB1

LOCATION F01

24-37-21 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL FOR FIN 3PV2 105VU 4.

DESIGNATION ELEC/BAT REF/BCL2

FIN 9PB2

LOCATION F02

Procedure (Ref. Fig. 24-37-21-991-00100-A - Voltmeters of Batteries) Subtask 24-37-21-020-050-A A.

Removal of the Voltmeter CAUTION :

AES

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Remove the 5 screws (7).

(2)

Remove the integrally lighted identification plate 13LF (6).

(3)

Turn the four quick-release fasteners (3) by a quarter turn.

(4)

Remove the panel 35VU (2) from its housing; do not disconnect the electrical connectors from the rear plate.

(5)

Disconnect the electrical wires (5) from the voltmeter (1) with the ELECTRICAL CONTACTS EXTRACTION TOOLSMS2749R20.

(6)

Loosen the two screws (4) and remove them.

(7)

Remove the voltmeter (1).

24-37-21 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A 3PV1

3PV2

1

BAT 1

DC BUS 1

BAT 2

FAULT

FAULT

OFF

OFF

V AC BUS 1

BAT 2

DC BUS 2 AC ESS FEED V

ALTN

AC ESS BUS

B

FAULT AC BUS 2

B

B 1

C

4

3 2 ? 6

C

5 7 N_MM_243721_4_AAM0_01_00

AES

FIGURE 24-37-21-991-00100-A SHEET 1 Voltmeters of Batteries

24-37-21 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-37-21-400-001-A Installation of the Voltmeters FIN 3PV1, 3PV2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

ELECTRICAL CONTACTS INSERTION TOOL MS2749A20

Work Zones and Access Panels ZONE/ACCESS

210 822

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C.

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

(Ref. Fig. 24-37-21-991-00100-A - Voltmeters of Batteries) 3.

Job Set-up Subtask 24-37-21-860-050-A A.

Aircraft Maintenance Configuration (1)

Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001-A).

(2)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the avionics compartment door 822.

(3)

Make sure that the access door 822 is open.

(4)

Make sure that the access panel of the BATTERY power center 105VU is opened.

Subtask 24-37-21-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL FOR FIN 3PV1 105VU

ELEC/BAT REF/BCL1

9PB1

F01

FOR FIN 3PV2 105VU

ELEC/BAT REF/BCL2

9PB2

F02

4.

DESIGNATION

FIN

LOCATION

Procedure (Ref. Fig. 24-37-21-991-00100-A - Voltmeters of Batteries)

AES

24-37-21 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-37-21-420-050-A A.

Installation of the Voltmeter CAUTION :

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Put the voltmeter (1) in position.

(2)

Install the two screws (4) and tighten them.

(3)

Connect the electrical wires (5) to the voltmeter (1) with the ELECTRICAL CONTACTS INSERTION TOOL MS2749A20.

(4)

Install the panel 35VU (2) in its housing.

(5)

Turn the four quick-release fasteners (3) by a quarter turn.

(6)

Install the plate 13LF (6) on the panel 35VU.

(7)

Install the 5 screws (7) and tighten them.

Subtask 24-37-21-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL FOR FIN 3PV1 105VU

DESIGNATION

FIN

LOCATION

ELEC/BAT REF/BCL1

9PB1

F01

FOR FIN 3PV2 105VU

ELEC/BAT REF/BCL2

9PB2

F02

Subtask 24-37-21-710-050-A C.

Check of the Battery Voltage (1)

5.

Make sure that the battery voltage comes into view.

Close-up Subtask 24-37-21-862-050-A A.

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

Subtask 24-37-21-410-050-A B.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access panel of the BATTERY power center 105VU.

(3)

Close the access door 822.

(4)

Remove the access platform(s).

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Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC GENERATION - BATTERIES - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The DC generation is provided by two batteries. Each of them has a nominal capacity of 23 Ah. ** On A/C 003-004 They are mainly used to: . start the APU in flight and on ground, . supply AC/DC essential network in emergency configuration during RAT deployment and when the emergency generator is not available (landing gear extended configuration). Each battery is associated with a Battery Charge Limiter (BCL) and a battery shunt. It should be noted that, in normal configuration, the batteries are most of the time uncoupled from the network during the flight. ** On A/C 005-099 They are mainly used to: . start the APU in flight and on ground, . supply AC/DC essential network in emergency configuration during RAT deployment and when the emergency generator is not available (CSM/G switched off after landing). Each battery is associated with a Battery Charge Limiter (BCL) and a battery shunt. It should be noted that, in normal configuration, the batteries are most of the time uncoupled from the network during the flight.

AES

24-38-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-38-00-12600-B - DC Generation - Batteries - Component Location) (Ref. Fig. 24-38-00-12700-B - DC Generation - Batteries - Component Location) (Ref. Fig. 24-38-00-12800-A - DC Generation - Battery Shunt - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS DOOR 124 124 126 126 126 126

ATA REF. 24-38-34 24-38-34 24-38-51 24-38-51 24-38-54 24-38-54

1PB1 1PB2 2PB1 2PB2 3PB1 3PB2 ** On A/C 003-004

BCL-1 BCL-2 BAT-1 BAT-2 SHUNT-BAT 1 SHUNT-BAT 2

4PB1 4PB2 ** On A/C ALL

HOLDER-BAT 1 FUSE HOLDER-BAT 2 FUSE

120VU 120VU

212 212

24-38-00 24-38-00

6PB1 6PB2 7PB1

CNTOR-LINE, BAT 1 CNTOR-LINE, BAT 2 P/BSW-ELEC/BAT 1

105VU 120VU 35VU

126 212 210

24-38-55 24-38-55 24-38-00

7PB2

P/BSW-ELEC/BAT 2

35VU

210

24-38-00

------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA I I I I DOOR I REF. ------------------------------------------------------------------------------4PB11 FUSE BAT-1 120VU 212 24-38-00 4PB21 FUSE BAT-2 120VU 212 24-38-00

AES

24-38-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

Component Description A.

Batteries 2PB1 2PB2 Each battery of the nickel-cadmium type is composed of twenty elements housed in a stainless steel case. Characteristics: . nominal voltage: 24 V, . nominal capacity: 23 Ah, . high instantaneous power, . electrolyte reserve: 60 cubic centimeters, . two ventilation ducts.

B. Battery Charge Limiter (BCL) ------------------------------------------------------------------------------! FUNCTION ! THRESHOLD ! TIME DELAY ! ACTION ! No.! !-----------------------------------------------------------------------------! ! Control of ! - Battery charge ! ! !BAT.CNTOR! ! ! battery ! . Charging !VBAT < 26,5 V! 225 ms ! CLOSING ! 7 ! ! contactor ! cycle !& V3PP > 27 V! ! ! ! ! ! ! ! ! ! ! ! ! . end of ! ICH < 4 A ! 10 s ! OPENING ! 6 ! ! ! charging ! ! ! ! ! ! ! cycle on ! ! ! ! ! ! ! ground ! ! ! ! ! ! ! ! ! ! ! ! ! ! . end of ! ICH < 4 A ! 30 mn ! OPENING ! ! ! ! charging ! ! ! ! ! ! ! cycle if ! ! ! ! ! ! ! aircraft ! ! ! ! ! ! ! speed is ! ! ! ! ! ! ! greater than ! ! ! ! ! ! ! 100 Kts ! ! ! ! ! ! ! or after an ! ! ! ! ! ! ! APU start ! ! ! ! ! ! ! ! ! ! ! ! ! ! - Thermal runaway! ! ! ! ! ! ! (1) ! ! ! ! ! ! ! . -------------! ICH > 10 A ! 3 X 60 s ! OPENING ! 5 ! ! ! !& >0,375 A/mn! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! .--------------! ICH > 150 A ! 90 s ! OPENING ! 4 ! ! ! ! ! ! ! ! ! ! - Starting of APU! ! ! CLOSING ! 8 ! ! ! ! ! ! ! ! ! ! - Supply on ! ! 75 ms ! CLOSING ! 3 ! ! ! ground ! ! ! ! ! ! ! ! ! ! ! ! ! ! - Transient fault! V3PP < 5 V ! ! CLOSING ! 2 ! ! ! conditions ! ! ! ! ! ! ! ! ! ! ! ! ! ! - Integrity of ! IDECH >100 A! 300 ms ! OPENING ! 1 ! ! ! hot bus ! ! ! ! !

AES

24-38-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ! ! ! ! ! ! ! ! ! - Electrical ! ! ! OPENING ! 10 ! ! ! emer condition ! ! ! ! ! !-----------------------------------------------------------------------------! ! Control of BCL! - Complete ! VBAT < 23 V ! 15 s ! OPENING BCL ! ! supply ! discharge ! ! ! SUPPLY ! ! ! protection ! ! ! ! ------------------------------------------------------------------------------! FUNCTION ! THRESHOLD ! TIME DELAY ! ACTION ! No.! !-----------------------------------------------------------------------------! ! "RAT-CSM/G ! ! ! ! WARNING ! ! FAULT" ! ! ! ! ! ! warning ! ! ! 1 s ! LIGHT ! ! control ! ! ! ! ! !-----------------------------------------------------------------------------! ! Inhibition of ! ! When ELEC ! 45 s ! APU START ! ! APU start ! ! EMER ! ! CNTOR ! ! sequence ! !configuration! ! INHIBITED ! ! ! !initiated and! ! ! ! ! !CSM/G not ! ! ! ! ! !available ! ! ! !-----------------------------------------------------------------------------! ! "BAT FAULT" ! - Thermal runaway! ! ! WARNING ! ! warning ! (see 1) ! ! ! ! ! control ! ! ! ! LIGHT ! C.

AES

Battery Shunt A 400 A/75mV shunt is installed on a base. It is used to read the charging and the discharging currents of a 24 V, 23 Ah battery. Characteristics: . Rating: the shunt supplies a voltage of 75 mV when a 400 A current goes through it. . Accuracy: 1% at 20 deg.C in the 0 - 400A range. . Overload capacity: 600 A during 30 seconds, 1000 A during 5 seconds. . Max. weight: 300 g.

24-38-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Operation/Control and Indicating A.

Control and Indicating Circuits ** On A/C 003-004 (Ref. Fig. 24-38-00-16300-C - Battery Charge Limiter (BCL1) - Schematic Simplified Cockpit Compartment Controls and Indicating) ** On A/C 005-099 (Ref. Fig. 24-38-00-16300-D - Battery Charge Limiter (BCL1) - Shematic Simplified Cockpit Compartment Controls and Indicating) The operation of each battery charge limiter is controlled from the ELEC panel 35VU in the cockpit by means of BAT1(2) pushbutton switches. These pushbutton switches have two stable positions: ** On A/C ALL (1) The pushbutton switch is released The battery charge limiter is not operating and the battery is uncoupled from the network. The status of this control is indicated by illumination of the white OFF legend on the pushbutton switch. The same indication is displayed on the ELEC page of the lower ECAM Display Unit and generates a warning if one or both engines are running. (2) The pushbutton switch is pressed The battery charge limiter is operating and controls the coupling and uncoupling of the battery. No light comes on on the pushbutton switch in normal operation. However white BAT1 and BAT2 and green indication of voltage and current are displayed on the ELEC page of the lower ECAM DU, as well as the green symbol when battery is charging and the amber symbol when battery is discharging. FAULT amber legend comes on on the pushbutton switch if a thermal runaway or internal short-circuit is detected. Simultaneously, the ELEC page is displayed on the lower ECAM DU with corresponding warnings (MASTER CAUT light + single chime + amber message on the upper ECAM display unit). A BAT OVHT fault causes automatic lock out of the battery line contactor. NOTE :

B.

An OFF/ON (Released/Pressed) action on the pushbutton switch allows to reset the BCL.

General Operating Principle of the Battery Charge Limiter ** On A/C 003-004 The battery charge limiter has a main function which is to control the battery contactor and three auxiliary functions which are: . RAT & EMER GEN FAULT warning control, . in emergency configuration, inhibition of APU start sequence during RAT deployment or when the landing gear is extended, . BAT FAULT warning control. Furthermore, the BCL delivers battery-related parameters and warnings to the ECAM display units, through busses. ** On A/C 005-099 The battery charge limiter has a main function which is to control the battery contactor and three auxiliary functions which are: . RAT & EMER GEN FAULT warning control, . in emergency configuration, inhibition of APU start sequence during RAT deployment, . BAT FAULT warning control. Furthermore, the BCL delivers battery-related parameters and warnings to the ECAM display units, through busses.

AES

24-38-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL C.

Battery Charge Limiter Functions ** On A/C 003-004 The functions of battery charge limiter are as follows: ** On A/C 005-099 The functions of battery charge limiter are as follows: ** On A/C 003-004 (1) Control of the battery contactor: . to ensure battery charge, . to start or assist starting of the APU, . to protect the battery against thermal runaway or short circuit, . to control equipment DC supply on ground, when no normal power is available, . to prevent complete discharge of the battery, when the aircraft is parked, . to supply equipment with DC during transient fault configurations, . to ensure integrity of the HOT bus. (a) Battery charge When battery voltage is lower than 26.5 V, beginning of the charging cycle. When battery charge current is lower than 4 A, end of the charging cycle. NOTE :

In flight or following APU start, when the battery charge current is lower than 4 A, a 30 mn time delay in the BCL controls the end of the charging cycle.

(b) Thermal runaway and internal short circuit Battery isolation occurs in case of: . charge current increasing with a slope greater than 0.375 A/mn. . charge current greater than a threshold (150 A) during 1 minute and 30 seconds. (c) Starting of the APU When the APU start sequence is initiated, the two batteries are connected to 28 VDC BAT BUS (3PP) to supply the APU starter motor. (d) Supply on ground When IDG’s, APU generator or external power are not available on ground, the batteries supply: . the 28 VDC BAT BUS (3PP) through the contactors 6PB1 and 6PB2, . the 28 VDC ESS BUS (4PP) through the contactor 2XB, . The 115 VAC STAT INV BUS (901XP) through the static inverter 3XB. (The BAT1(2) pushbutton switches are pushed). (e) Protection against complete discharge On ground, the batteries are automatically disconnected from the DC network when battery voltage is lower than 23 V during 15 seconds. NOTE :

But the disconnected battery always supplies its related HOT bus.

(f) Transient fault conditions Battery contactors are closed during 7 seconds when DC network is lost. (g) Integrity of the HOT bus Battery isolation in case of failure on DC network through monitoring of the battery discharge current (either I discharge > 400 A for 5 ms or I discharge > 100 A for 300 ms).

AES

24-38-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (h) Electrical emergency event Battery isolation in case of AC normal busbars failure (loss of AC main generation) except when APU start sequence is initiated. (2) RAT & EMER GEN control In case of AC normal busbars failure (loss of AC main generation) the red FAULT legend of the RAT & EMER GEN pushbutton switch on the ELEC EMER PWR section of the overhead panel 21VU comes on until the emergency generator is available (operational). The FAULT legend is inhibited when the landing gear is extended. (3) Inhibition of the APU start sequence In flight, when the electrical emergency configuration is initiated, the APU start sequence is inhibited during 45 seconds. NOTE :

If the CSM/G comes on line before 45 seconds, the APU start sequence is available as soon as the CSM/G is coupled to the network.

The APU start sequence is also inhibited in emergency configuration when the landing gear is extended. (4) BAT - Fault warning control When a thermal runaway occurs the FAULT legend of the BAT1(2) pushbutton switch comes on on the overhead ELEC panel 35VU. The battery contactors are opened but no action is required from the crew. ** On A/C 005-099 (5) Control of the battery contactor: . to ensure battery charge, . to start or assist starting of the APU, . to protect the battery against thermal runaway or short circuit, . to control equipment DC supply on ground, when no normal power is available, . to prevent complete discharge of the battery, when the aircraft is parked, . to supply equipment with DC during transient fault configurations, . to ensure integrity of the HOT bus. (a) Battery charge When battery voltage is lower than 26.5 V, beginning of the charging cycle. When battery charge current is lower than 4 A, end of the charging cycle. NOTE :

In flight or following APU start, when the battery charge current is lower than 4 A, a 30 mn time delay in the BCL controls the end of the charging cycle.

(b) Thermal runaway and internal short circuit Battery isolation occurs in case of: . charge current increasing with a slope greater than 0.375 A/mn. . charge current greater than a threshold (150 A) during 1 minute and 30 seconds. (c) Starting of the APU When the APU start sequence is initiated, the two batteries are connected to 28 VDC BAT BUS (3PP) to supply the APU starter motor. (d) Supply on ground When IDG’s, APU generator or external power are not available on ground, the batteries supply: . the 28 VDC BAT BUS (3PP) through the contactors 6PB1 and 6PB2, . the 28 VDC ESS BUS (4PP) through the contactor 2XB, . the 115 VAC STAT INV BUS (901XP) through the static inverter 3XB. (the BAT1(2) pushbutton switches are pushed).

AES

24-38-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (e) Protection against complete discharge On ground, the batteries are automatically disconnected from the DC network when battery voltage is lower than 23 V during 15 seconds. NOTE :

But the disconnected battery always supplies its related HOT bus.

(f) Transient fault conditions Battery contactors are closed during 7 seconds when DC network is lost. (g) Integrity of the HOT bus Battery isolation in case of failure on DC network through monitoring of the battery discharge current (either I discharge > 400 A for 5 ms or I discharge > 100 A for 300 ms). (h) Electrical emergency event Battery isolation in case of AC normal busbars failure (loss of AC main generation) except when APU start sequence is initiated. (6) RAT & EMER GEN control In case of AC normal busbars failure (loss of AC main generation) the red FAULT legend of the RAT & EMER GEN pushbutton switch on the ELEC EMER PWR section of the overhead panel 21VU comes on until the emergency generator is available (operational). The FAULT legend is inhibited when the landing gear is compressed. (7) Inhibition of the APU start sequence In flight, when the electrical emergency configuration is initiated, the APU start sequence is inhibited during 45 seconds. NOTE :

If the CSM/G comes on line before 45 seconds, the APU start sequence is available as soon as the CSM/G is coupled to the network.

(8) BAT - Fault warning control When a thermal runaway occurs the FAULT legend of the BAT1(2) pushbutton switch comes on on the overhead ELEC panel 35VU. The battery contactors are opened but no action is required from the crew.

AES

24-38-00 PB001

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 5.

BITE Test Built-In Test Equipment (BITE) allows two types of test: . tests at each power up on ground, . tests on ground from the Centralized Fault Display System (CFDS). Furthermore, the BCL system is monitored when the BCL is in operation. A.

Power up Test On the ground, when the equipment is switched on, the following tests are performed: . EPROM test (checksum), . RAM test, . timer test, . discret inputs test, . acquisition current test, . test of the output stage of the battery contactor control, . test of the output stage of the BAT FAULT warning control, . test of the output stage of the RAT & CSM/G warning control, . test of the output stage of the APU start inhibition control, . test of specific external wiring of the BCL, . watchdog test.

B.

Test from the CFDS The same tests as those applicable to power up are performed, plus a test for correct operation of the FAULT legend of BAT1(2) pushbutton switches and of RAT & EMER GEN annunciator which lasts 6 seconds.

C.

Monitoring of the BCL System When the BCL is supplied, the peripheral circuits are monitored through validation of the inputs (for example the position of the auxiliary contact of the battery contactor shall be coherent with the order).

D. Communication with the CFDS and/or ECAM E.

Communication with the MCDU and/or ECAM When a class 1 failure occurs, a BITE message is transmitted to the MCDU via an ARINC 429 serial data link and a failure indication is transmitted to the ECAM. In case of BAT FAULT warning, the crew is informed by: . a local amber warning on the overhead panel, . the single chime, . an amber caution on the main instrument panel. The warning page is displayed on the upper ECAM display unit and, at the same time, the ELEC page is displayed on the lower ECAM display unit: (Ref. Fig. 24-38-00-20100-A - BAT 1 FAULT - Lower and Upper ECAM Display Unit) (Ref. Fig. 24-38-00-20200-A - BAT 2 FAULT - Lower and Upper ECAM Display Unit) NOTE :

For some more information, see ATA (Ref. 31-51-00-00).

In case of BCL FAULT warning, the crew is informed by the BCL FAULT message displayed on the upper ECAM display unit whereas the ELEC page is displayed on the lower ECAM display unit. Class 3 failures can be read using the CFDS. Maintenance personnel must localize the failures by means of CFDS readouts (Ref. Fig. 24-38-00-20400-B - Maintenance Test Procedure for BCL) NOTE :

AES

If a BAT pushbutton switch is released (OFF position), the BAT OFF warning is displayed on the upper ECAM display unit whereas the ELEC page is displayed on the lower ECAM display unit.

24-38-00 PB001

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL The BITE messages generated by the BCL’s are: ------------------------------------------------------------------------------! ATA REF. ! MESSAGE ! CLASS ! COMMENT ! !----------!----------------------!-------!-----------------------------------! ! 24-38-51 ! BATTERY 1 (or 2) ! I ! Battery thermal runaway or ! ! ! ! ! internal short circuit ! !----------!----------------------!-------!-----------------------------------! ! 24-28-51 ! STATIC INVERTER 3XB ! I ! Failure of static inverter ! !----------!----------------------!-------!-----------------------------------! ! 24-38-55 ! CHECK CONTACTOR ! I ! Failure of battery contactor ! ! ! 6PB1 (or 6PB2) ! ! control of status circuit ! ! ! BCL1 (or BCL2) ! ! ! ! ! CIRCUIT ! ! ! !----------!----------------------!-------!-----------------------------------! ! 24-38-00 ! PUSHBUTTON 7PB1 ! I ! Failure of control P/BSW circuit ! ! ! (or 7PB2) / BCL1 ! ! ! ! ! (or BCL2) CIRCUIT ! ! ! !--------- !----------------------!-------!-----------------------------------! ! 24-38-00 ! SHUNT 3PB1 (or 3PB2) ! I ! Failure of current acquisition ! ! ! /BCL1 (or BCL2) ! ! circuit ! ! ! CIRCUIT ! ! ! !--------- !----------------------!-------!-----------------------------------! ! 24-38-00 ! FUSE 4PB1 (or 4PB2) ! I ! Fuse blown ! !----------!----------------------!-------!-----------------------------------! ! 24-38-34 ! BCL1 (or BCL2) ! I ! Failure of: ! ! ! ! ! -analogic/numeric converter ! ! ! ! ! -battery contactor control ! !----------!----------------------!-------!-----------------------------------! ! 24-38-00 ! CHECK DC BAT BUS ! I ! Failure of BCL BAT BUS supply ! ! ! 3PP/BCL1 (or BCL2) ! ! ! !----------!----------------------!-------!-----------------------------------! ! 24-38-34 ! BCL1 (or BCL2) ! III ! Failure of: ! ! ! ! ! -WATCH DOG ! ! ! ! ! -BAT FAULT control ! ! ! ! ! -APU START VALID control ! ! ! ! ! -RAT/EMER GEN/FAULT control ! ! ! ! ! (internal to BCL) ! !----------!----------------------!-------!-----------------------------------! ! 33-14-00 ! BOARD 5LP/BCL1 ! III ! Failure of BAT FAULT indication ! ! ! (or BCL2) CIRCUIT ! ! circuit ! !----------!----------------------!-------!-----------------------------------! ! 24-24-00 ! RELAY 31XE/BCL1 ! III ! Failure of RAT/EMER GEN/FAULT ! ! ! (or BCL2) CIRCUIT ! ! indication circuit ! !----------!----------------------!------ !-----------------------------------! ! 32-62-00 ! CHECK LGCIU1/BCL1 ! III ! Failure of nose L/G locked up ! ! ! (or BCL2) CIRCUIT ! ! information ! !----------!----------------------!-------!-----------------------------------! ! 24-38-00 ! BCL1 (or BCL2) ! III ! Ground/flight ADIRU or LGCIU ! ! ! LGCIU/ADIRU1 ! ! information disagree ! ! ! SIGNAL DISAGREE ! ! ! !----------!----------------------!-------!-----------------------------------! ! 24-34-55 ! CHECK CONTACTOR ! III ! Failure of ESS TR contactor ! ! ! 3PE/BCL1 (or BCL2) ! ! status circuit !

AES

24-38-00 PB001

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ! ! CIRCUIT ! ! ! !----------!----------------------!-------!-----------------------------------! ! 24-38-00 ! CHECK HOT BUS 701PP ! III ! Failure of voltage from HOT bus ! ! ! (or 702PP)/ BCL1 ! ! ! ! ! (or BCL2) CIRCUIT ! ! ! !----------!----------------------!-------!-----------------------------------! ! 24-25-00 ! RELAYS 15XC or 16XC/ ! III ! Failure of emergency ! ! ! BCL1 (or BCL2) ! ! configuration information ! ! ! CIRCUIT ! ! ! !----------!----------------------!-------!-----------------------------------! ! 24-38-00 ! CHECK HOT BUS POWER ! III ! Abnormal consumption on HOT bus ! ! ! CONSUMPTION ! ! ! !-----------------------------------------------------------------------------!

AES

24-38-00 PB001

Page 11 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 120VU 822 122VU 121VU 125VU 123VU

B A

124VU

FR16

FR9

C

(4PB2) 4PB1

A 105VU

C

D

4PB11 (4PB21)

6PB2

D

D

6PB1

4PB2 4PB1

E E

B 35VU

7PB1

DC BUS 1

BAT 1

1

V

E L E C

7PB2

BAT 2

FAULT

FAULT

OFF

OFF

GALLEY FAULT OFF

A U T O

AC BUS 1

AC ESS BUS

35VU

BAT 2

DC BUS 2

AC ESS FEED V

FAULT ALTN

AC BUS 2

E L E C

N_MM_243800_0_AAL0_01_00

AES

FIGURE 24-38-00-12600-B SHEET 1 DC Generation - Batteries - Component Location

24-38-00 PB001

Page 12 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

822

822

105VU

B

A FR24A

FR24A

FR9 FR1

1PB2 1PB1

FR9 FR1 2PB2 2PB1

A

B

N_MM_243800_0_ACL0_01_00

AES

FIGURE 24-38-00-12700-B SHEET 1 DC Generation - Batteries - Component Location

24-38-00 PB001

Page 13 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

3PB1

822

A 812

A

FR16 FR9

3PB2

A

N_MM_243800_0_AAN0_01_00

AES

FIGURE 24-38-00-12800-A SHEET 1 DC Generation - Battery Shunt - Component Location

24-38-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

CNTOR 2XB 2PB1 BAT1

3PP 28VDC BAT BUS 9PB1

8PB1

12PB1

DC1

3PB1

6PB1

703PP

701PP 28VDC HOT BUS

5PB1

SHUNT BAT

LP TEST BAT1 P/BSW FAULT OFF

5VAC ESS

CNTOR CTL

SUPPLY MODULE

HOT BUS BAT2

B1

SHORT CIRCUIT PROT.

FAULT ON

LOCK−OUT APU START

TO BCL2 10KA

14KD APU MASTER SW

TO BCL2

31XE BAT FAULT 7PB1

SDAC2

3PE CNTOR STATUS ARINC

429 L/G NOT LOCKED UP

TO BCL2

L/G LOCKED UP

ACQUISITION A/C SPEED

MODULE STATIC INVERTER FAULT

BCL1

3XB STAT INV. BCL1 POSITION

FAULT

FIGURE 24-38-00-16300-C SHEET 1 Battery Charge Limiter (BCL1) - Schematic Simplified Cockpit Compartment Controls and Indicating

TO BCL2

ELEC EMERG.

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Page 15 May 01/12 Revision n˚: 40

17XN1

15XC

202XP

TO RAT EXT.RELAY

100KNTS

1FP1 ADIRU1

CFDIU

GROUND CONDITI.

TO BCL2 N

SDAC1

APU START

28VDC

ON GROUND 5GA1 LGCIU1

LP TEST

14XE

101XP

6KD

FAULT

TO 4PP

P

3PE TO BCL2

14KD

AES

FAULT RAT/CSM.G CTL

BAT CNTOR STATUS

TO BCL2

FAULT ON

AUTO/OFF P/BSW

401PP 28VDC ESS BUS

1PH

17XN2 16XC

N_MM_243800_0_AEP0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 CNTOR 2XB 2PB1 BAT1

3PP 28VDC BAT BUS

8PB1

9PB1

DC1 LP TEST

LP TEST

6PB1 17PB

5VAC ESS

OFF

HOT BUS BAT2

703PP

5PB1

SHUNT BAT

BAT1 P/BSW FAULT

701PP 28VDC HOT BUS

12PB1

15PB

3PB1

CNTOR CTL

SUPPLY MODULE

B1 SHORT CIRCUIT PROT.

FAULT TO BCL2

ON

LOOK−OUT APU START

10KA 14KD APU MASTER SW 31XE 1PH

TO BCL2

BAT FAULT

AUTO/OFF P/BSW FAULT RAT/CSM.G CTL

7PB1 BAT CNTOR STATUS

401PP 28VDC ESS BUS

FAULT TO 4PP

p TO BCL2

FAULT TO BCL2

LP TEST

SDAC2

APU START

3PE

ON

14XE

3PE CNTOR STATUS

ARINC SDAC1

14KD

6KD L/G NOT LOCKED UP

TO BCL2

429 CFDIU

28VDC GROUND CONDITI.

MAIN L/G COMPRESSED

ON GROUND 5GA1 LGCIU1

TO RAT EXT.RELAY

ACQUISITION

A/C SPEED

ELEC EMERG.

TO BCL2

MODULE STATIC INVERTER FAULT

FAULT

BCL1

BCL1 POSITION

17XN1 15XC

202XP

N 100KNTS 1FP1 ADIRU1

3XB STAT INV.

101XP

TO BCL2

17XN2 16XC N_MM_243800_0_AEQ0_01_00

AES

FIGURE 24-38-00-16300-D SHEET 1 Battery Charge Limiter (BCL1) - Shematic Simplified Cockpit Compartment Controls and Indicating

24-38-00 PB001

Page 16 May 01/12 Revision n˚: 40

AES

FIGURE 24-38-00-20100-A SHEET 1 BAT 1 FAULT - Lower and Upper ECAM Display Unit

ACTION ON CLEAR P/BSW (ON ECAM CP)

MANUAL CREW ACTION

LOSS OF BAT 1

CONFIG. SYSTEM

BAT

BAT

AMBER FAULT"

OFF

FAULT

1

AMBER FAULT"

OFF

FAULT

1

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

ELEC

NORMAL CONFIG.

BAT 1 FAULT

ECAM UPPER DISPLAY

BAT 1 FAULT (CLASS 1 − LEVEL 2)

APU BAT START NOT AVAIL

STATUS

BAT 1

INOP

SEE FOLLOWING PAGE

SYS:

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_243800_0_AFL0_01_00

24-38-00 PB001

Page 17 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1

BAT 2 28V 10A

DC BAT

28V 0A

DC 1

DC 2 DC ESS

TR 1 28V 110A

ESS TR

AC 1

GEN 1 62% 116V 400HZ IDG 1

EMER GEN

AC ESS

APU GEN

°C110

TR 2 28V 82A

AC 2

GEN 2 60% 116V 400HZ 110°C

IDG 2

4WT2 DU−ECAM, LOWER

N_MM_243800_0_AFL0_02_00

AES

FIGURE 24-38-00-20100-A SHEET 2 BAT 1 FAULT - Lower and Upper ECAM Display Unit

24-38-00 PB001

Page 18 May 01/12 Revision n˚: 40

AES

FIGURE 24-38-00-20200-A SHEET 1 BAT 2 FAULT - Lower and Upper ECAM Display Unit

ACTION ON CLEAR P/BSW (ON ECAM CP)

MANUAL CREW ACTION

LOSS OF BAT 2

CONFIG. SYSTEM

OFF

FAULT

2

OFF

FAULT

2

AMBER FAULT"

BAT

AMBER FAULT"

BAT

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

ELEC

NORMAL CONFIG.

BAT 2 FAULT

ECAM UPPER DISPLAY

BAT 2 FAULT (CLASS 1 − LEVEL 2)

APU BAT START NOT AVAIL

STATUS

BAT 2

INOP

SEE FOLLOWING PAGE

SYS:

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_243800_0_AJL0_01_00

24-38-00 PB001

Page 19 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 2 28 V

BAT 1

28 V

DC BAT

0A

0A

DC 1

DC

2

DC ESS

28V

ESS

TR

EMER

GEN

28V

110A

AC 1

GEN

82A

AC ESS

1

6 2% 116V

2

GEN APU

GEN

400HZ

IDG 1

AC

°C110

2

60% 116V 400HZ

110°C

IDG 2

4WT2 DU−ECAM, LOWER

N_MM_243800_0_AJL0_02_00

AES

FIGURE 24-38-00-20200-A SHEET 2 BAT 2 FAULT - Lower and Upper ECAM Display Unit

24-38-00 PB001

Page 20 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

<

>

<

>

<

>

<

>

<

>

<

>

SELECT ELEC

<

>

<

>

<

>

<

<

SELECT SYSTEM REPORT/TEST SELECT TR 1 < < < <

<

<

<

<

*

SELECT CFDS

<

< < < <

SELECT TEST "TEST WAIT" IS DISPLAYED

SELECT LAST LEG REPORT

PRESS KEY MCDU MENU

<

*

NEGATIVE TEST IF TEST IS POSITIVE "TEST OK" IS DISPLAYED

AES

FIGURE 24-38-00-20400-B SHEET 1 Maintenance Test Procedure for BCL

*

<

NEGATIVE TEST (IF NO FAILURE "NO REPONSE" IS DISPLAYED) N_MM_243800_0_ANN0_01_00

24-38-00 PB001

Page 21 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC GENERATION - BATTERIES - ADJUSTMENT/TEST ** On A/C ALL Task 24-38-00-710-001-A Operational Test of the Battery Charge Limiter (BCL), (with the CFDS) 1.

Reason for the Job (Ref. MPD 24-38-00-01-) OPERATIONAL CHECK OF BATTERY CHARGE LIMITER NO 1 AND NO 2 VIA CFDS Operational test of the BITE function of the BCL. Make sure that the FAULT legends of the BAT pushbutton switches and the RAT & EMER GEN annunciator come on. NOTE :

2.

If the CFDS is not available, there is an alternative method for this procedure. This task gives the first method. For the alternative method, refer to the other task in this page block.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

210 812, 822 C.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-32-00-860-004-A

Procedure to Get Access to the SYSTEM REPORT/TEST/ELEC Page

3.

Job Set-up Subtask 24-38-00-860-051-A A.

AES

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

In the cockpit, on the overhead panel 35VU, make sure that the BAT 1 and BAT 2 pushbutton switches are released. (On these pushbutton switches, the OFF legend is on).

24-38-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

On the MCDU, on the SYSTEM REPORT/TEST page, get the ELEC menu (Ref. TASK 31-32-00-860-004-A).

Subtask 24-38-00-010-051-A B.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the avionics compartment doors 812 and 822.

(2)

Open the access doors 812 and 822.

(3)

Open the access panels of the AC/DC emergency power center 106VU and BATTERY power center 105VU.

Subtask 24-38-00-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

105VU

DESIGNATION ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/701PP SPLY

5PB1

D01

105VU

ELEC/BAT REF/BCL2

9PB2

F02

105VU

ELEC/BAT REF/BCL1

9PB1

F01

105VU

ELEC/BAT BUS/REF/BCL1

8PB1

G01

105VU

ELEC/BAT BUS/REF/BCL2

8PB2

J02

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

125VU

BAT BUS/301PP/SPLY

11PB

CC01

4.

FIN

LOCATION

Procedure Subtask 24-38-00-710-050-A A.

Operational Test of the BCL (with the CFDS)

ACTION 1.On the panel 35VU: . push the BAT 1 pushbutton switch. 2.On the MCDU, on the ELEC page: . push the line key adjacent to the BCL 1 indication. 3.On the BCL page: . push the line key adjacent to the TEST indication.

RESULT On the panel 35VU: . the OFF legend of the BAT 1 pushbutton switch goes off. On the MCDU: . the BCL page comes into view. On the panel 35VU: . the FAULT legend of the BAT 1 pushbutton switch comes on for 6 seconds approximately. On the panel 21VU: . the FAULT legend of the RAT & EMER GEN annunciator comes on for 6 seconds approximately. On the BCL page: . the TEST OK message comes into view.

4.On the MCDU: . push the line key adjacent to the RETURN indication until the ELEC page comes into view.

AES

24-38-00 PB501

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION 5.On the panel 35VU: . release the BAT 1 pushbutton switch, . push the BAT 2 pushbutton switch.

6.On the MCDU, on the ELEC page: . push the line key adjacent to the BCL 2 indication. 7.On the BCL page: . push the line key adjacent to the TEST indication.

RESULT On the panel 35VU: . the OFF legend of the BAT 1 pushbutton switch comes on, . the OFF legend of the BAT 2 pushbutton switch goes off. On the MCDU: . the BCL page comes into view. On the panel 35VU: . the FAULT legend of the BAT 2 pushbutton switch comes on for 6 seconds approximately. On the panel 21VU: . the FAULT legend of the RAT & EMER GEN annunciator comes on for 6 seconds approximately. On the BCL page: . the TEST OK message comes into view.

8.On the panel 35VU: . release the BAT 2 pushbutton switch. 5.

On the panel 35VU: . the OFF legend of the BAT 2 pushbutton switch comes on.

Close-up Subtask 24-38-00-410-051-A A.

Close Access (1)

Close the access panels of the AC/DC emergency power center 106VU and BATTERY power center 105VU.

(2)

Close the access doors 812 and 822.

(3)

Remove the access platform(s).

Subtask 24-38-00-860-050-A B.

AES

Put the aircraft back to its initial configuration. (1)

On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view.

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-38-00 PB501

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-38-00-710-001-A-01 Operational Test of the Battery Charge Limiter (BCL), (without the CFDS) 1.

Reason for the Job (Ref. MPD 24-38-00-01-) OPERATIONAL CHECK OF BATTERY CHARGE LIMITER NO 1 AND NO 2 VIA CFDS Test of the BCL when the CFDS is not operational

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

210 822

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

3.

Job Set-up Subtask 24-38-00-860-052-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

In the cockpit, on the overhead panel 35VU, make sure that the BAT 1 and BAT 2 pushbutton switches are released (the OFF legends are on).

(3)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

Subtask 24-38-00-010-052-A B.

AES

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the avionics compartment door 822.

(2)

Open the access door 822.

24-38-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Open the access panel of the BATTERY power center 105VU.

Subtask 24-38-00-865-054-A C.

Make sure that this(these) circuit breaker(s) is(are) closed:

105VU

PANEL

DESIGNATION ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/701PP SPLY

5PB1

D01

105VU

ELEC/BAT REF/BCL2

9PB2

F02

105VU

ELEC/BAT REF/BCL1

9PB1

F01

105VU

ELEC/BAT BUS/REF/BCL1

8PB1

G01

105VU

ELEC/BAT BUS/REF/BCL2

8PB2

J02

125VU

BAT BUS/301PP/SPLY

11PB

CC01

4.

FIN

LOCATION

Procedure Subtask 24-38-00-710-052-A A.

Operational Test of the BCL (without the CFDS)

ACTION 1.On the ECAM control panel: . get the ELEC page.

2.On the panel 35VU: . push the BAT 1(2) pushbutton switch.

RESULT the lower ECAM display unit: the usual configuration comes into view, the BAT 1(2) indication is white, the white OFF indication is in view, the amber crosses are in view at the DC BAT busbar indication. On the panel 35VU: . the OFF legend of the BAT 1(2) pushbutton switch goes off. On . . . .

On the lower ECAM display unit: . the green DC BAT busbar indication comes into view, . the green line between the BAT 1(2) indication and the DC BAT busbar indication comes into view. The arrow points to the BAT 1(2) indication, . the related parameter indications (voltage and current) come into view in green. After approximately 12 seconds, the green line between the BAT 1(2) indication and the DC BAT busbar indication: . goes out of view if the battery charge is correct, . stays in view if a battery charge is necessary. 3.On the panel 35VU: . release the BAT 1(2) pushbutton switch.

AES

On the panel 35VU: . the OFF legend of the BAT 1(2) pushbutton switch comes on. On the lower ECAM display unit: . the green line between the BAT 1(2) indication and the DC BAT busbar indication goes out of view (if it was in view).

24-38-00 PB501

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ACTION

5.

RESULT NOTE: If the BAT 1 and BAT 2 pushbutton switches are released simultaneously: . the white OFF indication comes into view, . the amber crosses come into view at the DC BAT busbar indication.

Close-up Subtask 24-38-00-410-052-A A.

Close Access (1)

Close the access panel of the BATTERY power center 105VU.

(2)

Close the access door 822.

(3)

Remove the access platform(s).

Subtask 24-38-00-860-053-A B.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-38-00 PB501

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC GENERATION - BATTERIES - INSPECTION/CHECK ** On A/C ALL Task 24-38-00-210-001-A Visual Inspection of the Batteries 1.

Reason for the Job Examination of the batteries.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific No specific

AR AR

SAFETY CLIP - CIRCUIT BREAKER SPONGE

No specific

AR

WARNING NOTICE(S)

B.

Consumable Materials

REFERENCE Material No: 19-003 Material No: 19-010 No specific C.

DESIGNATION LINT-FREE COTTON CLOTH LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA acetic acid

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

822 D.

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

3.

Job Set-up Subtask 24-38-00-861-054-A A.

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

Subtask 24-38-00-941-051-A B.

AES

Safety Precautions (1)

In the cockpit, on the overhead panel 35VU, make sure that the BAT 1 and 2 pushbutton switches are released (out).

(2)

In the cockpit, on the overhead panel 35VU, put a WARNING NOTICE(S) in position to tell the persons not to use the batteries.

24-38-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-38-00-010-050-A C.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 822.

(2)

Open the access door 822.

(3)

Open the access panel of the BATTERY power center 105VU.

Subtask 24-38-00-865-051-A D.

Open, safety and tag this(these) circuit breaker(s):

105VU

PANEL

DESIGNATION ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/701PP SPLY

5PB1

D01

4.

FIN

LOCATION

Procedure Subtask 24-38-00-210-050-A A.

Inspect the Batteries (1)

To do this: WARNING : DO NOT GET ELECTROLYTE ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: FLUSH IT AWAY IMMEDIATELY WITH CLEAN COLD WATER. GET MEDICAL AID. (a)

Disconnect the battery connector and put a CAP - BLANKING on the connector.

(b)

Examine the battery externally and make sure that these are in good condition: . case and lid, . latches, . pins of the electrical connector.

(c)

Examine the battery internally; to do this:

(d)

1

Cut and remove the lockwire from the lid.

2

Remove the lid and do a check of the condition of: . cells (electrolytic spillage, overheating, deformation), . connections between cells (oxidation), . safety valves. If you find spilled electrolyte, overheat marks or deformation (such as a cell with a swollen case, damaged cell strap), replace the battery.

Install the lid and safety it with LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA (Material No: 19-010) .

Subtask 24-38-00-210-051-A B.

Examine the Ventilation Ducts (1)

AES

To do this: (a)

Do a check of the condition of the ventilation ducts (traces of electrolyte).

(b)

Remove the ducts to clean and wash them with water and, if necessary, remove the electrolyte.

(c)

Install the ducts.

24-38-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-38-00-160-050-A C.

Clean of the Batteries Area (1)

In areas which you can get access to easily: Use a clean wet cloth to remove any trace of electrolyte. Be careful not to apply electrolyte all around with the cloth. You must of ten clean the cloth not to have a larger area with contamination.

(2)

In areas which you cannot get access to easily (complex structure): (a)

First clean the area with a 5 percent acetic acid solution. NOTE :

(b) (3)

5.

Then wipe and dry the area as well as possible with a clean cloth.

Electrical cables on which there is electrolyte contamination: (a)

(4)

If acetic acid is not available, you can use pure household spirit vinegar as an alternative.

Clean the cables with a clean SPONGE or LINT-FREE COTTON CLOTH (Material No: 19-003) ; if the cable insulation is damaged, replace the cable.

If some electrolyte comes out of the battery, you must write a report to give details on: . the area where it occurred . the cleaning procedure used and . the cable repair you did. This is necessary to do another check after 2 weeks.

Close-up Subtask 24-38-00-865-052-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

105VU

DESIGNATION ELEC/HOT BUS/702PP SPLY

FIN

LOCATION

5PB2

D02

105VU

ELEC/HOT BUS/701PP SPLY

5PB1

D01

Subtask 24-38-00-410-050-A B.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access panel of the BATTERY power center 105VU.

(3)

Close the access door 822.

(4)

Remove the access platform(s).

(5)

Remove the warning notice(s).

Subtask 24-38-00-862-051-A C.

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

24-38-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CHARGE LIMITER - BATTERY (BCL) REMOVAL/INSTALLATION ** On A/C ALL Task 24-38-34-000-001-A Removal of the Battery Charge Limiter (BCL) FIN 1PB1, 1PB2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

126 822

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

(Ref. Fig. 24-38-34-991-00100-A - Battery Charge Limiter) 3.

Job Set-up Subtask 24-38-34-860-050-A A.

Aircraft Maintenance Configuration (1)

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

(2)

In the cockpit, on the overhead panel 35VU, release the BAT pushbutton switches.

(3)

In the cockpit, on the overhead panel 35VU, put a WARNING NOTICE(S) to tell the persons not to operate the batteries.

Subtask 24-38-34-010-050-A B.

AES

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the avionics compartment door 822.

(2)

Open the access door 822.

(3)

Open the access panel of the BATTERY power center 105VU.

24-38-34 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-38-34-865-050-A C.

Open, safety and tag this(these) circuit breaker(s):

PANEL FOR FIN 1PB1 105VU 105VU FOR FIN 1PB2 105VU 105VU 4.

DESIGNATION

FIN

LOCATION

ELEC/BAT REF/BCL1

9PB1

F01

ELEC/BAT BUS/REF/BCL1

8PB1

G01

ELEC/BAT REF/BCL2

9PB2

F02

ELEC/BAT BUS/REF/BCL2

8PB2

J02

Procedure (Ref. Fig. 24-38-34-991-00100-A - Battery Charge Limiter) Subtask 24-38-34-020-050-A A.

AES

Removal of the Battery Charge Limiter (1)

Disconnect the connector (2).

(2)

Put blanking caps on the disconnected electrical connector(s).

(3)

Loosen and remove the four screws (4) and the washers (3).

(4)

Remove the battery charge limiter (1).

24-38-34 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

822

A 105VU

FR16 FR9 1PB1

1PB2

A 1

2

4 3

4 3

N_MM_243834_4_AAM0_01_00

AES

FIGURE 24-38-34-991-00100-A SHEET 1 Battery Charge Limiter

24-38-34 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-38-34-400-001-A Installation of the Battery Charge Limiter (BCL) FIN 1PB1, 1PB2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

126 822

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-38-00-710-001-A

DESIGNATION Operational Test of the Battery Charge Limiter (BCL), (with the CFDS)

24-38-00-710-001-A-01

Operational Test of the Battery Charge Limiter (BCL), (without the CFDS)

24-42-00-861-001-A

Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

(Ref. Fig. 24-38-34-991-00100-A - Battery Charge Limiter) 3.

Job Set-up Subtask 24-38-34-860-051-A A.

Aircraft Maintenance Configuration (1)

Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001-A).

(2)

In the cockpit, on the overhead panel 35VU, make sure that the BAT pushbutton switches are released.

(3)

In the cockpit, on the overhead panel 35VU, make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the batteries.

(4)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 822.

(5)

Make sure that the access door 822 is open.

(6)

Make sure that the access panel of the BATTERY power center 105VU is open.

Subtask 24-38-34-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL FOR FIN 1PB1 105VU

AES

DESIGNATION ELEC/BAT REF/BCL1

FIN 9PB1

LOCATION F01

24-38-34 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL 105VU FOR FIN 1PB2 105VU 105VU 4.

DESIGNATION ELEC/BAT BUS/REF/BCL1

8PB1

FIN G01

LOCATION

ELEC/BAT REF/BCL2

9PB2

F02

ELEC/BAT BUS/REF/BCL2

8PB2

J02

Procedure (Ref. Fig. 24-38-34-991-00100-A - Battery Charge Limiter) Subtask 24-38-34-420-050-A A.

Installation of the Battery Charge Limiter (1)

Install the battery charge limiter (1) on its support.

(2)

Install the four screws (4) and the washers (3) and then tighten screws.

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the connector (2) to the battery charge limiter (1).

Subtask 24-38-34-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL FOR FIN 1PB1 105VU

DESIGNATION

105VU FOR FIN 1PB2 105VU 105VU

FIN

LOCATION

ELEC/BAT REF/BCL1

9PB1

F01

ELEC/BAT BUS/REF/BCL1

8PB1

G01

ELEC/BAT REF/BCL2

9PB2

F02

ELEC/BAT BUS/REF/BCL2

8PB2

J02

Subtask 24-38-34-710-050-A C.

Do an operational test of the BCL from the CFDS (Ref. TASK 24-38-00-710-001-A) or (Ref. TASK 24-38-00-710-001-A-01). NOTE :

5.

As an alternative procedure, you can do this operational test without the CFDS (Ref. TASK 24-38-00-710-001-A) or (Ref. TASK 24-38-00-710-001-A-01).

Close-up Subtask 24-38-34-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access panel of the BATTERY power center 105VU.

(3)

Close the access door 822.

(4)

Remove the warning notice(s).

(5)

Remove the access platform(s).

24-38-34 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-38-34-862-050-A B.

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

24-38-34 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

BATTERY - REMOVAL/INSTALLATION ** On A/C ALL Task 24-38-51-000-001-A Removal of the Batteries FIN 2PB1, 2PB2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

126 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

(Ref. Fig. 24-38-51-991-00100-A - Batteries) (Ref. Fig. 24-38-51-991-00100-B - Batteries) 3.

Job Set-up Subtask 24-38-51-860-051-A A.

Aircraft Maintenance Configuration (1)

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

(2)

In the cockpit, on the overhead panel 35VU, release these pushbutton switches: . BAT 1, . BAT 2.

(3)

In the cockpit, on the overhead panel 35VU, put a WARNING NOTICE(S) in position to tell the persons not to operate the batteries.

Subtask 24-38-51-010-050-A B.

Get access to the Avionics Compartment (1)

AES

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the avionics compartment doors 812 and 822.

24-38-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Open the access doors 812 and 822.

(3)

Open the access panels of the AC/DC emergency power center 106VU and the BATTERY power center 105VU.

Subtask 24-38-51-865-050-A C.

Open, safety and tag this(these) circuit breaker(s):

PANEL FOR FIN 2PB1 105VU

DESIGNATION

FIN

LOCATION

ELEC/HOT BUS/701PP SPLY

5PB1

D01

ELEC/HOT BUS/701PP SPLY

12PB1

E01

ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/702PP SPLY

12PB2

E02

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

105VU FOR FIN 2PB2 105VU

4.

Procedure

** On A/C 003-004 (Ref. Fig. 24-38-51-991-00100-A - Batteries) ** On A/C 005-099 (Ref. Fig. 24-38-51-991-00100-B - Batteries) ** On A/C 003-004 Subtask 24-38-51-020-050-A WARNING : BE CAREFUL WHEN YOU REMOVE OR INSTALL THE BATTERY. THE BATTERY IS HEAVY AND CAN CAUSE INJURY AND/OR DAMAGE. A.

Removal of the Batteries NOTE :

AES

The weight of the battery is approximately 26 kg (57 lb).

(1)

Turn the knurled nut (6) by a quarter turn.

(2)

Disconnect the connector (7).

(3)

Put blanking caps on the disconnected electrical connector(s).

(4)

Loosen the clamp (9).

(5)

Disconnect the ventilation duct (10) and put a CAP - BLANKING on the duct.

(6)

Cut and remove the lockwire from the two wing nuts (2).

(7)

Loosen the two wing nuts (2).

(8)

Release the two rods (3) that hold the battery.

(9)

Remove the battery (1).

24-38-51 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Subtask 24-38-51-020-050-B WARNING : BE CAREFUL WHEN YOU REMOVE OR INSTALL THE BATTERY. THE BATTERY IS HEAVY AND CAN CAUSE INJURY AND/OR DAMAGE. A.

Removal of the Batteries NOTE :

The weight of the battery is approximately 26 kg (57 lb).

(1)

Cut and remove the copper shear wire between the knurled nut (6) and the connector (7).

(2)

Turn the knurled nut (6) by a quarter turn.

(3)

Disconnect the connector (7).

(4)

Put blanking caps on the disconnected electrical connector(s).

(5)

Loosen the clamp (9).

(6)

Disconnect the ventilation duct (10) and put a CAP - BLANKING on the duct.

(7)

Cut and remove the lockwire from the two wing nuts (2).

(8)

Loosen the two wing nuts (2).

(9)

Release the two rods (3) that hold the battery.

(10) Remove the battery (1). ** On A/C ALL Subtask 24-38-51-869-051-A B.

Make sure that there is no electrolyte leakage in the ventilation duct. NOTE :

AES

If there is, remove the duct, clean it and rinse it with water.

24-38-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 FR16

FR9 822

A

812 106VU 105VU 2PB1

10

2PB2 9

A 1

B B

2

B 8 LOCKWIRE 3 3 7

6

4

5

AES

FIGURE 24-38-51-991-00100-A SHEET 1 Batteries

N_MM_243851_4_AAM0_01_01

24-38-51 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 10 9

A

FR16

1 FR9

B

822

A B

812 106VU 105VU 2PB2

2PB1

3

C 4

COPPER SHEAR WIRE

5

C

B

7

2

6

8 LOCKWIRE 3 N_MM_243851_4_AAN0_01_01

AES

FIGURE 24-38-51-991-00100-B SHEET 1 Batteries

24-38-51 PB401

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-38-51-400-001-A Installation of the Batteries FIN 2PB1, 2PB2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

Consumable Materials

REFERENCE Material No: 19-009 No specific No specific C.

WARNING NOTICE(S)

DESIGNATION LOCKWIRE STAINLSS STL OR NICKEL ALLOY COPPER SHEAR WIRE NFL23-321 LOCK WIRE MS 20995CY15

Work Zones and Access Panels ZONE/ACCESS

126 812, 822 D.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-38-00-710-001-A

DESIGNATION Operational Test of the Battery Charge Limiter (BCL), (with the CFDS)

24-38-00-710-001-A-01

Operational Test of the Battery Charge Limiter (BCL), (without the CFDS)

24-42-00-861-001-A

Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

(Ref. Fig. 24-38-51-991-00100-A - Batteries) (Ref. Fig. 24-38-51-991-00100-B - Batteries) FOR FIN 2PB1(BAT-1) 31-21-00-750-002-A 3.

Procedure to set the Clock

Job Set-up Subtask 24-38-51-860-052-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001-A).

(2)

In the cockpit, on the overhead panel 35VU, make sure that these pushbutton switches are released: . BAT 1, . BAT 2.

24-38-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

In the cockpit, on the overhead panel 35VU, make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the batteries.

(4)

Make sure that an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the avionics compartment doors 812 and 822.

(5)

Make sure that the access doors 812 and 822 are open.

(6)

Make sure that the access panels of the AC/DC emergency power center 106VU and BATTERY power center 105VU are open.

Subtask 24-38-51-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL FOR FIN 2PB1 105VU

DESIGNATION

FIN

LOCATION

ELEC/HOT BUS/701PP SPLY

5PB1

D01

ELEC/HOT BUS/701PP SPLY

12PB1

E01

ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/702PP SPLY

12PB2

E02

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

105VU FOR FIN 2PB2 105VU

4.

Procedure

** On A/C 003-004 (Ref. Fig. 24-38-51-991-00100-A - Batteries) ** On A/C 005-099 (Ref. Fig. 24-38-51-991-00100-B - Batteries) ** On A/C 003-004 Subtask 24-38-51-420-050-A WARNING : BE CAREFUL WHEN YOU REMOVE OR INSTALL THE BATTERY. THE BATTERY IS HEAVY AND CAN CAUSE INJURY AND/OR DAMAGE. A.

Installation of the Batteries NOTE :

The weight of the battery is approximately 26 kg (57 lb).

(1)

Put the battery (1) in position between the four stops (4) on the plate assembly (5).

(2)

Put the rods (3) in position to the battery. NOTE :

AES

Make sure that the rods are engaged in the cover assembly slots of the battery (1) and the spacers (8) are in position.

(3)

Tighten the wing nuts (2) with your hand until they touch the battery, then tighten a 1/4 turn more.

(4)

Safety the wing nuts (2) with LOCKWIRE STAINLSS STL OR NICKEL ALLOY (Material No: 19-009) .

(5)

Remove all the blanking caps and connect the duct (10) on the battery.

(6)

Install the clamp (9) and tighten it.

24-38-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (7)

Remove the blanking caps from the electrical connector(s).

(8)

Make sure that the electrical connectors are clean and in the correct condition.

(9)

Connect the connector (7) on the battery (1).

(10) Turn the knurled nut (6) by a quarter turn. (11) If possible, install the COPPER SHEAR WIRE NFL23-321 between the knurled nut (6) and the connector (7). NOTE :

You can use the LOCK WIRE MS 20995CY15 as an alternative to the COPPER SHEAR WIRE NFL23-321.

** On A/C 005-099 Subtask 24-38-51-420-050-B WARNING : BE CAREFUL WHEN YOU REMOVE OR INSTALL THE BATTERY. THE BATTERY IS HEAVY AND CAN CAUSE INJURY AND/OR DAMAGE. A.

Installation of the Batteries NOTE :

The weight of the battery is approximately 26 kg (57 lb).

(1)

Put the battery (1) in position between the fours stops (4) on the plate assembly (5).

(2)

Put the rods (3) in position to the battery. NOTE :

Make sure that the rods are engaged in the cover assembly slots of the battery (1) and the spacers (8) are in position.

(3)

Tighten the wing nuts (2) with your hand until they touch the battery, then tighten a 1/4 turn more.

(4)

Safety the wing nuts (2) with LOCKWIRE STAINLSS STL OR NICKEL ALLOY (Material No: 19-009) .

(5)

Remove all the blanking caps and connect the duct (10) on the battery.

(6)

Install the clamp (9) and tighten it.

(7)

Remove the blanking caps from the electrical connector(s).

(8)

Make sure that the electrical connectors are clean and in the correct condition.

(9)

Connect the connector (7) on the battery (1).

(10) Turn the knurled nut (6) by a quarter turn. (11) Install the COPPER SHEAR WIRE NFL23-321 between the knurled nut (6) and the connector (7). NOTE :

You can use the LOCK WIRE MS 20995CY15 as an alternative to the COPPER SHEAR WIRE NFL23-321.

** On A/C ALL Subtask 24-38-51-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL FOR FIN 2PB1 105VU 105VU

AES

DESIGNATION

FIN

LOCATION

ELEC/HOT BUS/701PP SPLY

5PB1

D01

ELEC/HOT BUS/701PP SPLY

12PB1

E01

24-38-51 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL FOR FIN 2PB2 105VU

DESIGNATION

FIN

LOCATION

ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/702PP SPLY

12PB2

E02

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

Subtask 24-38-51-710-050-A C.

Do an operational test of the BCL from the CFDS (Ref. TASK 24-38-00-710-001-A) or (Ref. TASK 24-38-00-710-001-A-01). NOTE :

As an alternative procedure, you can do this operational test without the CFDS (Ref. TASK 24-38-00-710-001-A) or (Ref. TASK 24-38-00-710-001-A-01).

Subtask 24-38-51-750-050-B D.

Adjustment of the Clock (1)

5.

FOR 2PB1 (BAT-1) Adjust the clock (Ref. TASK 31-21-00-750-002-A).

Close-up Subtask 24-38-51-410-050-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access panels of the AC/DC emergency power center 106VU and BATTERY power center 105VU.

(3)

Close the access doors 812 and 822.

(4)

Remove the warning notice(s).

(5)

Remove the access platform(s).

Subtask 24-38-51-862-051-A B.

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

24-38-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

BATTERY - INSPECTION/CHECK ** On A/C ALL Task 24-38-51-280-001-A Removal of the Batteries 1 and 2 for Restoration FIN 2PB1, 2PB2 1.

Reason for the Job (Ref. MPD 24-38-51-01-) RESTORATION OF BATTERY

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

126 822

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-38-51-000-001-A 24-38-51-400-001-A 24-42-00-861-001-A

DESIGNATION Removal of the Batteries Installation of the Batteries Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

CMM 24-38-51 3.

Job Set-up Subtask 24-38-51-861-050-A A.

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

Subtask 24-38-51-010-051-A B.

4.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the avionics compartment door 822.

(2)

Open the access door 822.

Procedure Subtask 24-38-51-020-051-A A.

Removal of the Batteries (1)

AES

Remove the batteries (Ref. TASK 24-38-51-000-001-A).

24-38-51 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-38-51-280-050-A B.

Check of the Batteries (1)

Send the batteries to the workshop for the restoration procedure (Ref. CMM 24-38-51).

Subtask 24-38-51-420-051-A C.

Installation of the Batteries (1)

5.

Install the batteries (Ref. TASK 24-38-51-400-001-A).

Close-up Subtask 24-38-51-410-051-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access door 822.

(3)

Remove the access platform(s).

Subtask 24-38-51-862-050-A B.

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

24-38-51 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

SHUNT - BATTERY - REMOVAL/INSTALLATION ** On A/C ALL Task 24-38-54-000-001-A Removal of the Battery Shunt FIN 3PB1, 3PB2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

126 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

(Ref. Fig. 24-38-54-991-00100-A - Battery Shunt (3PB1, 3PB2)) 3.

Job Set-up Subtask 24-38-54-861-050-A A.

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

Subtask 24-38-54-941-050-A B.

Safety Precautions (1)

In the cockpit, on the ELEC panel 35VU, release these pushbutton switches: . BAT 1, . BAT 2.

(2)

In the cockpit, on the ELEC panel 35VU, put a WARNING NOTICE(S) in position to tell persons not to operate the batteries.

Subtask 24-38-54-010-050-A C.

AES

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the avionics compartment doors 812 and 822.

(2)

Open the access doors 812 and 822.

24-38-54 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Open the access panels of the AC/DC emergency power center 106VU and the battery power center 105VU.

Subtask 24-38-54-865-050-A D.

Open, safety and tag this(these) circuit breaker(s):

PANEL FOR FIN 3PB1 105VU

DESIGNATION

FIN

LOCATION

ELEC/HOT BUS/701PP SPLY

5PB1

D01

105VU

ELEC/HOT BUS/701PP SPLY

12PB1

E01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/REFLNG/ON/BAT

1PR

U28

ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/702PP SPLY

12PB2

E02

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/REFLNG/ON/BAT

1PR

U28

FOR FIN 3PB2 105VU

4.

Procedure (Ref. Fig. 24-38-54-991-00100-A - Battery Shunt (3PB1, 3PB2)) Subtask 24-38-54-020-050-A A.

AES

Removal of the Battery Shunt (1)

Remove the bolts (8), remove and discard the lockwashers (9), remove the washers (10) and the ground cable (11).

(2)

Remove the bolt (12), remove and discard the lockwasher (13), remove the electrical wire (14).

(3)

Remove the bolt (4), remove and discard the lockwasher (3), remove the electrical wire (2).

(4)

Remove the bolts (7), the washers (6) and the nuts (1).

(5)

Remove the battery shunt (5).

24-38-54 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

822

A 812

A

FR16 FR9

A 12 13

14

1

9

10 11

2 9

10 11

3 4

8

8

7

6

5

N_MM_243854_4_AAM0_01_00

AES

FIGURE 24-38-54-991-00100-A SHEET 1 Battery Shunt (3PB1, 3PB2)

24-38-54 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-38-54-400-001-A Installation of the Battery Shunt FIN 3PB1, 3PB2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

WARNING NOTICE(S)

No specific

Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

No specific

Torque wrench: range to between 30.00 and 220.00 LBF.IN (0.34 and 2.60 M.DAN)

B.

Work Zones and Access Panels ZONE/ACCESS

126 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Expendable Parts

FIG.ITEM 9 13 3

DESIGNATION lockwasher lockwasher lockwasher

D.

IPC-CSN 24-38-01-02-042 24-38-01-02-047 24-38-01-02-047

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

(Ref. Fig. 24-38-54-991-00100-A - Battery Shunt (3PB1, 3PB2)) 3.

Job Set-up Subtask 24-38-54-860-050-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001-A).

(2)

In the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: . BAT 1, . BAT 2.

(3)

In the cockpit, on the ELEC panel 35VU, make sure that the WARNING NOTICE(S) to tell persons not to operate the batteries, is in position.

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Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the avionics compartment doors 812 and 822.

(5)

Make sure that the access doors 812 and 822 are open.

(6)

Make sure that the access panels of the AC/DC emergency power center 106VU and the battery power center 105VU are open.

Subtask 24-38-54-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL FOR FIN 2PB1 105VU

DESIGNATION

FIN

LOCATION

ELEC/HOT BUS/701PP SPLY

5PB1

D01

105VU

ELEC/HOT BUS/701PP SPLY

12PB1

E01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/REFLNG/ON/BAT

1PR

U28

ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/702PP SPLY

12PB2

E02

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/REFLNG/ON/BAT

1PR

U28

FOR FIN 2PB2 105VU

4.

Procedure (Ref. Fig. 24-38-54-991-00100-A - Battery Shunt (3PB1, 3PB2)) Subtask 24-38-54-420-050-A A.

5.

Installation of the Battery Shunt (1)

Clean the component interface and/or the adjacent area.

(2)

Install the battery shunt (5).

(3)

Install the bolts (7), the washers (6) and the nuts (1).

(4)

TORQUE the nuts (1) to between 40 and 44.51 LBF.IN (0.45 and 0.50 M.DAN).

(5)

Install the ground cables (11), the washers (10), new (IPC-CSN 24-38-01-02) lockwasher (9) and the bolts (8).

(6)

TORQUE the bolts (8) to between 53.10 and 79.65 LBF.IN (0.60 and 0.90 M.DAN).

(7)

Install the electrical wire (2), a new (IPC-CSN 24-38-01-02) lockwasher (3) and the bolt (4).

(8)

Install the electrical wire (14), a new (IPC-CSN 24-38-01-02) lockwasher (13) and the bolt (12).

(9)

TORQUE the bolts (4) and (12) to between 22.12 and 33.63 LBF.IN (0.25 and 0.38 M.DAN).

Close-up Subtask 24-38-54-865-052-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL FOR FIN 2PB1 105VU

AES

DESIGNATION ELEC/HOT BUS/701PP SPLY

FIN 5PB1

LOCATION D01

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105VU

PANEL

DESIGNATION ELEC/HOT BUS/701PP SPLY

12PB1

E01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/REFLNG/ON/BAT

1PR

U28

ELEC/HOT BUS/702PP SPLY

5PB2

D02

105VU

ELEC/HOT BUS/702PP SPLY

12PB2

E02

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/REFLNG/ON/BAT

1PR

U28

FOR FIN 2PB2 105VU

FIN

LOCATION

Subtask 24-38-54-410-050-A B.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access panels of the AC/DC emergency power center 106VU and the battery power center 105VU.

(3)

Close the access doors 812 and 822.

(4)

Remove the warning notice(s).

(5)

Remove the access platform(s).

Subtask 24-38-54-862-050-A C.

AES

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

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CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-38-55-000-001-A Removal of the Battery Line Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 6PB1, 6PB2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

126 121AL, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE (Ref. Fig. 24-38-55-991-00100-B - Contactors) 3.

DESIGNATION

Job Set-up Subtask 24-38-55-010-050-B A.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access door 822.

(2)

Open the access door 822.

(3)

Put an ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-38-55-941-050-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft receptacle.

(2)

Put WARNING NOTICE(S) on the access door 121AL to tell the persons not to use the external power receptacle.

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4.

(3)

In . . . .

the cockpit, on the overhead ELEC panel 35VU, release these pushbutton switches: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

(4)

In the cockpit, put WARNING NOTICE(S) to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(5)

In the cockpit, on the APU section of the overhead panel 25VU, put WARNING NOTICE(S) to tell persons not to start the APU.

Procedure (Ref. Fig. 24-38-55-991-00100-B - Contactors) CAUTION :

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Subtask 24-38-55-020-051-A A.

Removal of the Contactor (1)

Disconnect the connector (4).

(2)

Put blanking caps on the disconnected electrical connector(s).

(3)

Loosen the two captive screws (2). NOTE :

(4)

AES

Do not remove the captive screws (2) and the spring washers from the contactor (3).

Disengage the contactor (3) from the base (5) and remove the contactor.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

822

A 105VU

A FR16 FR9

6PB2

B

6PB1

B

2

B CONTACTOR BASE

5

CONTACTOR

6 4

7

3

2

N_MM_243855_4_AAL0_01_00

AES

FIGURE 24-38-55-991-00100-B SHEET 1 Contactors

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-38-55-400-001-A Installation of the Battery Line Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 6PB1, 6PB2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

1

ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

WARNING NOTICE(S)

No specific

B.

Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

Work Zones and Access Panels ZONE/ACCESS

126 121AL, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-38-00-710-001-A

DESIGNATION Operational Test of the Battery Charge Limiter (BCL), (with the CFDS)

24-38-00-710-001-A-01

Operational Test of the Battery Charge Limiter (BCL), (without the CFDS)

(Ref. Fig. 24-38-55-991-00100-B - Contactors) 3.

Job Set-up Subtask 24-38-55-860-050-B A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 822.

(2)

Make sure that the access door 822 is open.

(3)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

(5)

Make sure that the external power connector is not connected to the aircraft receptacle.

(6)

Make sure that a WARNING NOTICE(S) is in position on the access door 121AL to tell persons not to use the external power receptacle.

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4.

(7)

In the cockpit, on the overhead ELEC panel 35VU, make sure that these pushbutton switches are released: . BAT 1, BAT 2, . APU GEN, . GEN 1, GEN 2, . EXT PWR.

(8)

In the cockpit, make sure that a WARNING NOTICE(S) is in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(9)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

Procedure (Ref. Fig. 24-38-55-991-00100-B - Contactors) Subtask 24-38-55-420-050-A A.

Installation of the Contactor CAUTION :

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Put the contactor (3) on the tapped barrels (6) of the contactor base (5).

(2)

TORQUE the captive screws (2) to between 33.63 and 41.6 LBF.IN (0.38 and 0.47 M.DAN).

(3)

Remove the blanking caps from the electrical connectors.

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the connector (4) to the contactor (3).

Subtask 24-38-55-710-050-A B.

Operational Test of the Battery Charge Limiter (BCL) (1)

5.

Do an operational test of the BCL from the CFDS (Ref. TASK 24-38-00-710-001-A) or (Ref. TASK 24-38-00-710-001-A-01).

Close-up Subtask 24-38-55-410-050-B A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the warning notice(s).

(3)

Close the access door 822.

(4)

Close the access door 121AL.

(5)

Remove the access platform(s).

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EXTERNAL POWER - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The aircraft network can be supplied by a ground power unit. For this, an external power receptacle is provided forward of the nose landing gear well. This receptacle enables to supply: . either the whole network via the transfer circuit (Ref. 24-41-00-00), . or only part of it, the ground service network which comprises: . the AC ground service bus control (Ref. 24-42-00-00), . the DC ground service bus control (Ref. 24-43-00-00).

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-40-00-12300-A - Main Components - Component Location) FIN

FUNCTIONAL DESIGNATION

1XG 3XG 8XG

GPCU EPC IND LT-EXT PWR/NOT IN USE

92VU 120VU 108VU

ZONE ACCESS DOOR 122 212 120

9XG

CAUT LT-EXT PWR/AVAIL

108VU

120

24-41-00

10XG

P/BSW-ELEC/EXT PWR

35VU

210

24-41-00

120VU 120VU

120 212 212

20XG RCPT-EXT PWR 12XX CNTOR-AC GND SVCE SPLY 14XX CNTOR-AC & DC GND SVCE SPLY ** On A/C 005-099

PANEL

121AL

ATA REF. 24-41-34 24-41-55 24-41-00

24-41-51 24-42-55 24-42-55

16XX CNTOR-SVCE BUS 2 120VU 212 24-42-00 ------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA I I I I DOOR I REF. ------------------------------------------------------------------------------5XX SW-MAINT BUS 2000VU 220 841 24-42-00

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR12 FR14

FR5 FR3

FR16 FR20

811 108VU 20XG 822 120VU

121AL

841 49VU

122VU 35VU 21VU 121VU

25VU

124VU

125VU

123VU

LOWER ECAM DISPLAY UNIT

UPPER ECAM DISPLAY UNIT

FR16

FR9

92VU

2000VU

106VU 90VU N_MM_244000_0_AAM0_01_00

AES

FIGURE 24-40-00-12300-A SHEET 1 Main Components - Component Location

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AC EXTERNAL POWER CONTROL - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The power supply control of the whole aircraft network from a ground power unit is performed from the cockpit overhead panel (Ref. 24-00-00-00). This control is associated with a ground power control unit (GPCU).

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location

** On A/C 003-004 (Ref. Fig. 24-41-00-12300-A - AC External Power Control (GPCU) - Component Location) ** On A/C 005-099 (Ref. Fig. 24-41-00-12300-B - AC External Power Control (GPCU) - Component Location) ** On A/C ALL (Ref. Fig. 24-41-00-12400-A - AC External Power Control (GPCU) - Component Location) FIN 1XG 3XG 8XG

GPCU EPC IND LT-EXT PWR/NOT IN USE

92VU 120VU 108VU

ZONE ACCESS DOOR 122 212 120

9XG

CAUT LT-EXT PWR/AVAIL

108VU

120

24-41-00

10XG

P/BSW-ELEC/EXT PWR

35VU

210

24-41-00

20XG

RCPT-EXT PWR

AES

FUNCTIONAL DESIGNATION

PANEL

120

121AL

24-41-00 PB001

ATA REF. 24-41-34 24-41-55 24-41-00

24-41-51

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description

** On A/C 003-004 (Ref. Fig. 24-41-00-14300-C - External Power Configuration - Block Diagram) ** On A/C 005-099 (Ref. Fig. 24-41-00-14300-G - External Power Configuration - Block Diagram) ** On A/C ALL (Ref. Fig. 24-41-00-14400-B - Ground Power Control Unit (GPCU) - Schematic Diagram) A.

External Power Receptable One external power receptable (20XG) located foward of the nose gear well enables power supply of the aircraft network up to 90 KVA. This is perfomed by means of a single three-phase, 400 Hz, 115/200 VAC Ground Power Unit (GPU).

B.

Ground Power Supply The GPU supplies the transfer circuit through the EPC (3XG). The effective supply of the aircraft network by means of the Bus Transfer Contactors (BTC), (Ref. 24-22-00-00), depends on the availability of the other generation sources and the defined priority order.

In ground configuration, these two power sources can supply all of the aircraft network: . The APU generator, to a maximum power of 115 KVA, or . The GPU, to a maximum power of 90 KVA (approximately 60KVA for the technical loads).

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Component Description A.

Ground Power Control Unit (GPCU) Control and Protection Functions 1XG The GPCU has three different functions: . aircraft power supply control and network protection, . system test and self-monitoring relating to these functions . provide BITE and messages for the AC generation (GCU’s and GPCU). NOTE :

B.

The GPCU transmits command and data to and receives data from up to the GCUs. The communication is made via RS422 serial data links.

Ground and Auxiliary Power Control Unit (GAPCU) Control and Protection Functions (1) Control Unit Supply The control unit is supplied: . with 115 VAC/400 Hz, directly from the external power receptacle, by the voltage it has to analyse. The GPCU generates 28VDC from this voltage. It is used: for its own needs (internal plus or minus 15 V, plus or minus 5 V and + 28 V supply), to supply the aircraft power supply control and indicating circuits (EPC, EXT PWR pushbutton switch, EXT PWR NOT IN USE indicator light and EXT PWR AVAIL caution light, flight/ground network contactors), . with 28 VDC from the normal aircraft electrical network and on the ground only. This dual supply constitutes the 28 V internal supply, peculiar to the control unit. (2) Controls The GPCU (in association with the EXT PWR pushbutton switch) controls the connection/disconnection of the external power to/from the aircraft electrical system. The necessary controls are achieved by means of relays. . The Pin Monitoring Relay (PMR) This relay when energized, connects a holding supply to the GPU line contactor. It is energized when the DC input voltage (Pin E and F) is within acceptable limits (less than 42 VDC). . The External Power Available Relay (PR) The PR when excited enables the connection of the ground power unit to the aircraft network provided none of the following protections is actived: . over/undervoltage, . over/underfrequency, . incorrect phase order, . GPCU internal fault. Any fault detection: . prevents the ground power unit from being connected to the aircraft network, . or causes it to trip if already in line. NOTE :

When a fault is detected, the PR is no longer excited and/or inhibits illumination of the ON legend of the EXT PWR pushbutton switch.

NOTE :

The PR also controls the illumination of the AVAIL legend of the EXT PWR pushbutton switch in the cockpit and the EXT PWR AVAIL caution light in the external power receptacle housing.

(3) Protections . Over/underfrequency (OF, UF) The control unit permanently monitors the frequency of phase A voltage of the external power receptacle. The over/underfrequencies protection are triggered when the frequency becomes higher/lower than a certain threshold. . Over/undervoltage (OV, UV)

AES

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.

The control unit permanently monitors the voltage of the three phases of the external power receptacle. The undervoltage protection is triggered when the voltage of the lower phase becomes lower than a certain threshold. Incorrect phase order (IPS) This detection is performed from voltage information of phases A and B of the external power receptacle. After excitation of the ground power unit generator, the control unit analyzes the phase order of the voltage supply. When the voltage is incorrect, the GPCU prevents the closure of the PR relay (protection of the three phase consumers).

NOTE :

This protection is effective in case of: cross connection between any two phases, and also if a phase and the neutral are crossed. A table listing these functions is shown below: GPCU PROTECTIONS ------------------------------------------------------------------------------I I FUNCTION ISENSING I THRESHOLD ITIME DELAY ITRIPSI REMARKS I INHIBITION I ------------------------------------------------------------------------------I IEP Overvol-IHighest I 124-132 I Inverse IEPC, I I I Itage (OV) Iphase EPI Volts I IGSR’sI I I I Ivoltage I I I I I I I-----------I--------I-----------I-----------I-----I-------------I------------I IEP Under- IIndivi- I 100 plus I 3 - 5 s IEPC IThis functionI I Ivoltage Idual I or minus I IGSR’sIcovers open I I I(UV) Iphase I 4 V I I Iphase. I I I Iunder- I I I I I I I Ivoltage I I I I I I I-----------I--------I-----------I-----------I-----I-------------I------------I IEP Overfre-IEP fre- I 433 plus I 3 - 5 s IEPC I I I Iquency (OF)Iquency I or minus I IGSR’sI I I I I I 3 Hz I I I I I I-----------I--------I-----------I-----------I-----I-------------I------------I IEP Under- IEP fre- I 363 plus I 3 - 5 s IEPC I I I Ifrequency Iquency I or minus I IGSR’sI I I I(UF) I I 3 Hz I I I I I I-----------I--------I-----------I-----------I-----I-------------I------------I IEP Phase I2 phasesI A-B-C-N I None IEPC IPrevents EPC I I ISequence I Iphase I IGSR’sIclosure if I I I(PS) I Isequence I I Iphase sequen-I I I I I I I Ice is not ABCI I I I I I I Ior if neutralI I I I I I I Iand phase I I I I I I I Ilead are I I I I I I I Icrossed. I I ------------------------------------------------------------------------------(4) BITE Functions (a) System self monitoring and function The same test philosophy applies for the GCU and as well as for the GPCU (Ref. 24-22-00). (b) Interface with CFDIU The GPCU permanently sends to the CFDIU all Fault messages detected in flight or on ground by the GPCU and GCU’s.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL All the information transmitted from the GPCU to the CFDIU is in ”Clear English Message” form. There are two transmission modes: . the normal mode . the menu mode.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 5.

Operation/Control and Indicating A.

Control and Indicating Circuits - Controls and Indicating in the Cockpit (Ref. Fig. 24-41-00-17800-A - External Power Contactor (EPC) Supply - Schematic Diagram) As soon as the ground power unit is connected and selected on, the GPCU analyzes the voltage delivered at the external power receptacle. If the analyzed parameters are correct: . the GPCU controls the illumination of the green AVAIL legend of EXT PWR pushbutton switch located on the overhead ELEC panel 35VU. This pushbutton switch controls the energization of the transfer network by means of the external power contactor (EPC). EPC supply is shown in this figure, . when the AVAIL legend of this pushbutton switch is illuminated, the EPC remains open. NOTE :

Nevertheless, the ground power unit can supply ground/flight networks in ground service configuration (Ref. 24-42-00-00).

.

when the pushbutton switch is pressed and released, the EPC closes and supplies the transfer circuit. Blue ON legend comes on to indicate the closure of EPC (AVAIL legend goes off). The effective supply of the aircraft network by means of the BTCs depends on the availability of the onboard main generation sources. In the case of APU generator already supplying the transfer circuit, the supply command by means of the external power receptacle causes the opening of the APU generator line contactor. For reference only, each channel is supplied according to the following priority order: . its generator, . the ground power unit, . the APU generator, . the second generator. NOTE : B.

Control and Indicating Circuits - Indicating in the External Power Receptacle Housing Two lights located in the external power receptacle housing enable easier utilization or removal of the ground power unit by the ground personnel. . Amber EXT PWR/AVAIL caution light controlled by the GPCU, comes on to indicate that the ground power unit is operating and the voltage correct. . White EXT/PWR NOT IN USE indicator light comes on to indicate that the ground power unit does not supply the aircraft and can be disconnected. NOTE :

C.

The EXT PWR pushbutton switch is springloaded. At each impulse on the EXT PWR pushbutton switch, the EGIU controls the change of position of the external power auxiliary relay, (Ref. 24-22-00-00).

A lamp test of these two lights can be performed by means of the LIGHT TEST pushbutton switch located in the external power receptacle housing.

Communications (Ref. Fig. 24-41-00-18600-A - Communication - Block Diagram) A general schematic is shown in this figure and describes all the communications between the different systems. They are of 2 types: . communications toward the SDAC, . BITE communications. (1) SDAC communications

(a) Table of Main Digital Signals Sent out by the Equipment to SDAC1(2) -------------------------------------------------------------------------------

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL | PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------! 1 070 01!GEN1 FREQ ! 512 ! HZ ! ! 09 ! ! ! ! GCU1 ! ! 2 070 10!GEN2 FREQ ! 512 ! HZ ! ! 09 ! ! ! ! GCU2 ! ! 071 01! APU GEN ! 512 ! HZ ! ! 09 ! ! ! !GCU-APU! ! ! FREQ ! ! ! ! ! ! ! ! ! ! 071 10! EXT PWR ! 512 ! HZ ! ! 09 ! ! ! ! GPCU ! ! ! FREQ ! ! ! ! ! ! ! ! ! ! 1 072 01! GEN1 ! 256 ! V ! ! 08 ! ! ! ! GCU1 ! ! ! VOLTAGE ! ! ! ! ! ! ! ! ! ! 2 072 10! GEN2 ! 256 ! V ! ! 08 ! ! ! ! GCU2 ! ! ! VOLTAGE ! ! ! ! ! ! ! ! ! ! 075 01! APU GEN ! 256 ! V ! ! 08 ! ! ! !GCU-APU! ! ! VOLTAGE ! ! ! ! ! ! ! ! ! ! 075 10! EXT PWR ! 256 ! V ! ! 08 ! ! ! ! GPCU ! ! ! VOLTAGE ! ! ! ! ! ! ! ! ! ! 1 077 01! GEN1 LOAD! 256 !PCT ! ! 08 ! ! ! ! GCU1 ! ! 2 077 10! GEN2 LOAD! 256 !PCT ! ! 08 ! ! ! ! GCU2 ! ! 100 00! APU GEN ! 256 !PCT ! ! 08 ! ! ! !GCU-APU! ! ! LOAD ! ! ! ! ! ! ! ! ! ! 1 105 01!IDG1 INLET! 256 !deg.! ! 08 ! ! ! ! GCU1 ! ! ! TEMP ! ! C ! ! ! ! ! ! ! ! 2 105 10!IDG2 INLET! 256 !deg.! ! 08 ! ! ! ! GCU2 ! ! ! TEMP ! ! C ! ! ! ! ! ! ! ! 1 106 01!IDG1OUTLET! 256 !deg.! ! 08 ! ! ! ! GCU1 ! ! ! TEMP ! ! C ! ! ! ! ! ! ! ! 2 106 10!IDG2OUTLET! 256 !deg.! ! 08 ! ! ! ! GCU2 ! ! ! TEMP ! ! C ! ! ! ! ! ! ! ! 071 11! EMER GEN ! 512 ! HZ ! ! 09 ! ! ! ! 27WV ! ! ! FREQ ! ! ! ! ! ! ! ! ! ! 075 11! EMER GEN ! 256 ! V ! ! 08 ! ! ! ! 27WV ! ! ! VOLTAGE ! ! ! ! ! ! ! ! ! ------------------------------------------------------------------------------(b) Table of Main Discrete Signals Received by the SDAC1(2) ------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | ------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | ------------------------------------------------------------------------------! 002 00!AC/ESS TRU! ! ! ! 15 ! ! ! ! 15XE ! ! ! CNTOR ON ! ! ! ! ! ! ! ! ! ! 002 00!AC/ESS TRU! ! ! ! 15 ! ! ! ! 15XE !

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Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

AES

002

002

002 002 002

002

002 002 002 002 002 002 002 002 002 002 002 002 002 002 002

002

002

! CNTOR OFF! 00! AC ESS ! ! SHED BUS ! ! ON ! 00! AC ESS ! ! SHED BUS ! ! OFF ! 00!AC ESS BUS! ! OFF ! 00!AC ESS BUS! ! ON ! 00! AC ESS ! ! FEED P/B ! ! ALTN ! 00! AC ESS ! ! FEED P/B ! ! NOT ALTN ! 00! BUS TIE ! ! P/B OFF ! 00! BUS TIE ! ! P/B ON ! 01!GEN1 LINE ! !CNTOR ON ! 01!GEN1 LINE ! !CNTOR OFF ! 01! TRANSFER ! !CNTOR1 ON ! 01! TRANSFER ! !CNTOR1 OFF! 01!AC1/AC ESS! ! CNTOR ON ! 01!AC1/AC ESS! ! CNTOR OFF! 10!GEN2 LINE ! !CNTOR ON ! 10!GEN2 LINE ! !CNTOR OFF ! 10! TRANSFER ! !CNTOR2 ON ! 10! TRANSFER ! !CNTOR2 OFF! 10!AC2/AC ESS! !CNTOR ON ! 10!AC2/AC ESS! !CNTOR OFF ! 11! APU GEN ! !LINE CNTOR! ! ON ! 11! APU GEN ! !LINE CNTOR! ! OFF ! 11! EXT PWR ! !LINE CNTOR!

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

! 16 ! ! ! 16 ! ! ! 18 ! ! 18 ! ! 20 ! ! ! 20 ! ! ! 21 ! ! 21 ! ! 14 ! ! 14 ! ! 15 ! ! 15 ! ! 16 ! ! 16 ! ! 14 ! ! 14 ! ! 15 ! ! 15 ! ! 16 ! ! 16 ! ! 14 ! ! ! 14 ! ! ! 15 ! !

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

3XH

3XH

3XH 3XH 11XC

11XC

10XU 10XU 9XU1 9XU1 11XU1 11XU1 13XC 13XC 9XU2 9XU2 11XU2 11XU2 14XC 14XC 3XS

3XS

3XG

24-41-00 PB001

! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! ! !

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ! ! ON ! ! ! ! ! ! ! ! ! ! 002 11! EXT PWR ! ! ! ! 15 ! ! ! ! 3XG ! ! !LINE CNTOR! ! ! ! ! ! ! ! ! ! ! OFF ! ! ! ! ! ! ! ! ! ! 002 11! GALLEY ! ! ! ! 17 ! ! ! ! 2XA ! ! ! SHED P/B ! ! ! ! ! ! ! ! ! ! ! OFF ! ! ! ! ! ! ! ! ! ! 002 11! GALLEY ! ! ! ! 17 ! ! ! ! 2XA ! ! ! SHED P/B ! ! ! ! ! ! ! ! ! ! ! NOT OFF ! ! ! ! ! ! ! ! ! ! 002 11!EMERGENCY ! ! ! ! 22 ! ! ! ! 23XE ! ! !GEN TEST ! ! ! ! ! ! ! ! ! ! 002 11! NO ! ! ! ! 22 ! ! ! ! 23XE ! ! !EMERGENCY ! ! ! ! ! ! ! ! ! ! !GEN TEST ! ! ! ! ! ! ! ! ! ! 004 11! MAIN ! ! ! ! 27 ! ! ! ! 6XA ! ! ! GALLEY ! ! ! ! ! ! ! ! ! ! ! SHED ! ! ! ! ! ! ! ! ! ! 004 11! NO MAIN ! ! ! ! 27 ! ! ! ! 6XA ! ! ! GALLEY ! ! ! ! ! ! ! ! ! ! ! SHED ! ! ! ! ! ! ! ! ! ------------------------------------------------------------------------------(2) BITE communications (a) Fault detection at system level As an assistance for maintenance tasks, the control units (GCU-1, GCU-2, GCU-APU) have to: . collect and analyse the failures, and store the corresponding fault code (hexadecimal) in their own Non Volatile Memory (NVM) . run out requested test (ex maintenance test). Each system is fitted with a RS 422 Serial link interface in order: . to transmit the contents of current flight from the NVM and receive test requests and give the results. (b) GPCU The GPCU transmits the fault messages in clear English to the CFDIU (the CFDIU is connected to the GPCU by a discrete input and an ARINC 429 output bus). It is also the interface between the CFDIU and the various control units (GCU1, GCU2, APU GCU). The control units are connected to the GPCU by RS422 serial data links. 1

Operation in normal mode The GPCU receives the fault information recorded by the GCU’s, compiles them with its own failures and transmits for the whole system a list of the failures in clear language and starting from the most recent. When a failure is identified, the information is permanently transmitted with the ATA reference of the LRU or of the faulty circuit up to the beginning of the next flight. The CFDIU records all the failures - Class I or II and internal to the system - transmitted by the GPCU in flight to inscribe them in the aircraft LAST LEG REPORT. The most recent failure is the first to be displayed on the MCDU.

2

Operation in menu mode In menu mode, 3 selections are possible: LAST LEG REPORT, TEST and CLASS 3 FAULTS. a

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LAST LEG REPORT When pressing the corresponding key (in the SYSTEM REPORT/TEST page) (Ref. Fig. 24-41-00-19200-B - Reading of Class 3 Faults on MCDU)

24-41-00 PB001

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL All the class I and II flight and ground failures of the current flight are displayed. The MCDU display order is as follows: . the flight messages (the most recent flight failure first), . then GND and the ground messages (the most recent ground failure first). At GPCU power up on the ground, the contents of the various NVM’s (GCU’s and GPCU) for the current flight is recovered in the order GPCU, GCU1, GCU2 and APU GCU. All the messages (flight and ground) become then ground messages. b

TEST When pressing the corresponding key (Ref. Fig. 24-41-00-19200-B - Reading of Class 3 Faults on MCDU) a test is generated and taken into account by the GPCU. The test request is transmitted by the discrete input signal from the CFDIU. Test logic: . ground signal for 500 ms + or - 10 percent = request for test, . open circuit = no test. NOTE :

The test mode is only available on the ground. The GPCU transmits the request for test to the GCU’s and the test results of all the control units (GCU1, GCU2, APU GCU and GPCU) to the CFDIU. When the test takes more than 3 seconds the system transmits the TEST WAIT message to inform the users that his request is being processed. The TEST WAIT message remains until the test result is available. The test result is transmitted three times and then the GPCU returns automatically in normal mode.

NOTE :

The results remain displayed on the MCDU display unit until the key adjacent to the RETURN line is pressed. The test cannot be initiated in the phases 2 to 8 (see ATA Ref. 31-32-00). In the phase 9, if the test is initiated when one engine or the APU is running, one of the following messages is displayed at the end of the test of the channel concerned: -------------------------------------------------------GENERATOR CHANNEL MESSAGE RUNNING --------------------------------------------------------IDG 1 MAIN 1 GCU1 TEST NOT RUN IDG 2 MAIN 2 GCU2 TEST NOT RUN APU APU GCU APU TEST NOT RUN c

Class 3 faults When pressing the corresponding key (Ref. Fig. 24-41-00-19200-B - Reading of Class 3 Faults on MCDU) the class III faults occured during the current flight are displayed (see TSM manual).

D. Automatic Periodic Test As soon as the GPCU is supplied (Aircraft on ground and engines shut down) it will automatically perform the test (GPCU and GCUs) and will store the failure (if any) in the corresponding NVM for transmission through the GPCU to the CFDIU. Moreover, the GPCU will activate the BITE Message discrete. This information is provided to the SDACs via the EGIU1 to be written on the ECAM status page.

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24-41-00 PB001

Page 11 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

122VU

21VU

35VU 121VU

25VU

B

125VU

124VU 123VU

LOWER ECAM DISPLAY UNIT

UPPER ECAM DISPLAY UNIT

A A

C

120VU

3XG

C

B

PANEL 35VU DC BUS 1

1

BAT 1

BAT 2

FAULT

FAULT

OFF

OFF

V

35VU

BAT 2

DC BUS 2 AC ESS FEED V

FAULT

GALLEY

E L E C

FAULT OFF

A U T O

AC BUS 1

ALTN

AC ESS BUS

AC BUS 2

BUS TIE

IDG 1 GEN 1

APU GEN

FAULT

FAULT

FAULT

OFF

OFF

A SMOKE U T O OFF

OFF

IDG 2 EXT PWR

GEN 2

AVAIL

FAULT

FAULT

ON

OFF

OFF

E L E C

10XG N_MM_244100_0_AAM0_01_00

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FIGURE 24-41-00-12300-A SHEET 1 AC External Power Control (GPCU) - Component Location

24-41-00 PB001

Page 12 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 FR12 FR5

FR14

FR3

FR16 FR20

811

D 108VU 121AL 822

20XG

841

D PANEL 108VU

EXT PWR

FLT INT 108VU

8XG 9XG NOT IN USE

AVAIL

LIGHT TEST

COCKPIT CALL ADIRU & APU FIRE AVNCS VENT

COCKPIT CALL

ASSET APU SHUT OFF

N_MM_244100_0_AAM0_02_00

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FIGURE 24-41-00-12300-A SHEET 2 AC External Power Control (GPCU) - Component Location

24-41-00 PB001

Page 13 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

122VU

21VU

35VU 121VU

25VU

B

125VU

124VU 123VU

LOWER ECAM DISPLAY UNIT

UPPER ECAM DISPLAY UNIT

A

C

A 120VU

29XN

3XG

C

B

PANEL 35VU DC BUS 1

BAT 1

1

FAULT

OFF

OFF

V

BAT 2

BAT 2

FAULT

DC BUS 2 AC ESS FEED V

FAULT

GALLEY

E L E C

FAULT OFF

A U T O

AC BUS 1

AC BUS 2

BUS TIE

IDG 1 FAULT

ALTN

AC ESS BUS

A U T O

IDG 2 EXT PWR

GEN 2

FAULT

AVAIL

FAULT

OFF

ON

OFF

GEN 1

APU GEN

FAULT OFF

OFF

E L E C

FAULT

10XG

N_MM_244100_0_AAP0_01_00

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FIGURE 24-41-00-12300-B SHEET 1 AC External Power Control (GPCU) - Component Location

24-41-00 PB001

Page 14 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 FR12 FR5

FR14

FR3

FR16 FR20

811

D 108VU 121AL 822

20XG

841

D PANEL 108VU

EXT PWR

FLT INT 108VU

8XG 9XG NOT IN USE

AVAIL

LIGHT TEST

COCKPIT CALL ADIRU & APU FIRE AVNCS VENT

COCKPIT CALL

ASSET APU SHUT OFF

N_MM_244100_0_AAP0_02_00

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FIGURE 24-41-00-12300-B SHEET 2 AC External Power Control (GPCU) - Component Location

24-41-00 PB001

Page 15 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 90VU

A B FR16

B

FR9

92VU

C 1XG

C

RACK

N_MM_244100_0_ACM0_01_00

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FIGURE 24-41-00-12400-A SHEET 1 AC External Power Control (GPCU) - Component Location

24-41-00 PB001

Page 16 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 801PP

APU START 49 − 42 − 00

CSM/G CONTROL UNIT 5KA

10KA

6KA

6XE

DC BUS 1

4PB1

1PP

8PR

703PP BAT1 2PB1

6PN 3PN2

3PP

1PN2

204PP

601PP

202PP

602PP

DC BUS 2

1PC2

2PP 28VDC

7PN

DC SVCE BUS

8PN

2XB

28VDC

6PH

115

STATIC INV

5PU2

901XP

12XB

801XP

7XN1 26V

5XN1

8XH

15XN1

4XH

5XH 103XP

1XP 115VAC

5XN2

401XP

AC ESS BUS

231XP−A

26V 15XN2

115VAC

101XP

1XN1 AC BUS 1

431XP−A

26V

204XP

3XN2

4XP

2XC

AC BUS 2

2XP 115VAC

3XC 15XE

GLC−1 9XU1 GCU−1 1XU1

AES

BTC−1 11XU1

EPC 3XG

GLC−APU 3XS

4000XU

GCU−APU 1XS

FIGURE 24-41-00-14300-C SHEET 1 External Power Configuration - Block Diagram

APU GEN

8XS

GPCU 1XG

24-41-00 PB001

2PU2

14PU

10XN

12XN

3801GX 3805GX

BTC−2 11XU2

GLC−2 9XU2

FUEL PUMPS 28 − 21 − 00 GEN 1

4XX

202XP

1XN2

1XC

1XX

14XX

2XX

12XX

3802GX 3806GX EXTERNAL POWER RECEPTACLE

Page 17 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

1PE ESS TR

1PU2 TR2

210XP

7XN2

131XP−A

3XN1

2PU1

24 − 50 − 00

115VAC 110XP

3PE

1PX

AC SHED ESS BUS 8XP

24 − 50 − 00

1PU1 TR1

6PP

3PX

5XB

3XB 5PU1

28VDC

3PB1 28VDC

28

4PP

206PP

1PR SHUNT

DC ESS BUS

4PC

208PP

SHUNT 3PB2

701PP

12PB1

6PB1

28VDC

501PP 5PR

BAT2 2PB2

401PP

502PP

704PP

12PB2

BAT BUS

1PC1

2PR

702PP

5PB1

101PP

1PN1

8PH

20PC

5PB2

4PB2 6PB2 1PB1 BCL−1

103PP

8PP 28VDC

1PB2 BCL−2

3PN1

DC SHED ESS BUS

301PP

11PB

4000XU

214XP

216XP 212XP

4PE

ELEC PUMP−Y 29 − 24 − 00 GLC−EMERG 2XE

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_244100_0_AEL0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 801PP

APU START 49 − 42 − 00

CSM/G CONTROL UNIT 5KA

10KA

6KA

6XE

DC BUS 1

4PB1

1PP

8PR

703PP BAT1 2PB1

6PN 3PN2

28VDC

1PN2

204PP

601PP

202PP

602PP

3PB1 3PP

DC BUS 2

1PC2

2PP 28VDC

28VDC 3XB

7PN

DC SVCE BUS

8PN

115

2XB

6PP 28VDC

3PX

5XB

28

4PP

206PP

1PR SHUNT

DC ESS BUS

4PC

208PP

SHUNT 3PB2

701PP

12PB1

6PB1

28VDC

501PP 5PR

BAT2 2PB2

401PP

502PP

704PP

12PB2

BAT BUS

1PC1

2PR

702PP

5PB1

101PP

1PN1

8PH

20PC

5PB2

4PB2 6PB2 1PB1 BCL−1

103PP

8PP 28VDC

1PB2 BCL−2

3PN1

DC SHED ESS BUS

301PP

11PB

6PH

5PU1 STATIC INV

5PU2

901XP

12XB

801XP

21XN1 26V

5XN1

15XN1

8XH

110XP

7XN2

131XP−A

4XH

103XP

1XN1 1XP 115VAC

5XN2

401XP

AC ESS BUS

231XP−A

26V 15XN2

115VAC

101XP

21XN2

204XP

3XN2

4XP

2XC

AC BUS 2

2XP 115VAC

3XC 15XE

GLC−1 9XU1 GCU−1 1XU1

AES

BTC−1 11XU1

EPC 3XG

GLC−APU 3XS

4000XU

GCU−APU 1XS

FIGURE 24-41-00-14300-G SHEET 1 External Power Configuration - Block Diagram

APU GEN

8XS

GPCU 1XG

24-41-00 PB001

2PU2

14PU

10XN

12XN

3801GX 3805GX

BTC−2 11XU2

GLC−2 9XU2

FUEL PUMPS 28 − 21 − 00 GEN 1

4XX

202XP

1XN2

1XC

1XX

14XX

2XX

12XX

3802GX 3806GX EXTERNAL POWER RECEPTACLE

Page 18 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

1PE ESS TR

1PU2 TR2

210XP

431XP−A

26V 5XH

3XN1

AC BUS 1

24 − 50 − 00

115VAC

7XN1

2PU1

1PX

AC SHED ESS BUS 8XP

24 − 50 − 00

1PU1 TR1

3PE

4000XU

16XX

214XP

216XP 212XP

4PE

ELEC PUMP−Y 29 − 24 − 00 GLC−EMERG 2XE

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_244100_0_AET0_01_00

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FIGURE 24-41-00-14400-B SHEET 1 Ground Power Control Unit (GPCU) - Schematic Diagram

EXTERNAL POWER UNIT

CLOSE

28VDC

22XU1 EGIU−1

VOLTAGE AND FREQUENCY

CLASS 2 FAILURE

EXT PWR ON

EXT PWR AVAIL

INFO TO SDAC

CHANNEL B

TRIP

23XG

EXT PWR CTL

100

2XG

1XG GPCU

401XP 115VAC

21XG

3

CLASS 2 FAILURE

PMR

TR

10XG EXT PWR P/BSW

V(E) OR V(F) 42VDC

12XG

13XG

AVAIL ON

7.5

PR

GLC.BTC LOGIC

10LP

PR

4XG

3XG EPC

GROUND MODE

VALID EP INTERLOOK

PROTECTION AND CONTROL UV.OV.UF.OF.IPS

DC1

3PP 28VDC

DC1

B1

FLIGHT

3PH

8XG EXT PWR NOT IN USE

9XG EXT PWR/AVAIL

POWER SUPPLIES REGULATOR

5XG EPC AUX CTL RLY

11XG

6XG

12XX−AC GND SPLY CNTOR

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_244100_0_AGL0_01_00

24-41-00 PB001

Page 19 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 301PP 28VDC BAT BUS

2XU1 FAULT OFF

PMG PR

3XU1 ELEC/GEN1

LOCK−OUT BTC

4XU1 GLC 1 AUX CTL RLY

1XU1 GCU−1 301PP 28VDC BAT BUS

9XU1 GLC−1

11XU1 BTC−1

2XU2 FAULT OFF

PMG PR

3XU2 ELEC/GEN 2

LOCK−OUT BTC

11XU2 BTC−2

4XU2 GLC 2 AUX CTL RLY

1XU2 GCU−2 301PP 28VDC 6XS BAT BUS

9XU2 GLC−2 FAULT OFF

PMG

PR 2XS APU GEN

1XS GCU−APU

7XG G.P 1XG GPCU

4XS APU GLC AUX CTL RLY 301PP 28VDC BAT BUS

PR 3XS GLC−APU

3XG EPC

11XG EXT PWR CTL

22XU1 EGIU 1−CHANNEL B

5XG EPC AUX CTL

N_MM_244100_0_AJM0_01_00

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FIGURE 24-41-00-17800-A SHEET 1 External Power Contactor (EPC) Supply - Schematic Diagram

24-41-00 PB001

Page 20 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

EXT. PWR PARAMETERS

GEN 1 PARAMETERS

GPCU

GEN APU PARAMETERS

GCU − 1

GEN 2 PARAMETERS

GCU − APU

GCU − 2

BITE MESSAGE (CLASS 2 FAILURE)

CHANNEL 2

CHANNEL 1

CHANNEL 2

EGIU 1

CHANNEL 1

EGIU 2

TEST DISCRET

SDAC 1 (SYSTEM + ECAM)

SDAC 2 (SYSTEM + ECAM)

CFDIU

COMMUNICATION:

RS 422

. BITE

ARINC 429

. SDAC

ANALOG AND DISCRETE SIGNALS

N_MM_244100_0_ALM0_01_00

AES

FIGURE 24-41-00-18600-A SHEET 1 Communication - Block Diagram

24-41-00 PB001

Page 21 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

MCDU

MENU

FMGC

CFDS MENU

AIDS CFDS RETURN SELECT

DESIRED

1L

LAST LEG REPORT

1R

2L

LAST LEG ECAM REPORT

2R

3L

PREVIOUS LEGS REPORT

3R

4L

AVIONICS STATUS

4R

5L

SYSTEM REPORT/TEST

5R

6L

POST FLIGHT PRINT

6R

SYSTEM BRT

MCDU MENU

SYSTEM REPORT / TEST 1L

AIR COND

2L

AFS

3L

COM

4L

ELEC

5L

FIRE PROT

6L

RETURN

F/CTL

1R

FUEL

2R 3R

ICE & RAIN INST

4R

L/G

5R

NAV

6R

AC

SYSTEM REPORT / TEST ELEC

GEN

1L

AC GEN

TR 1

1R

1L

LAST LEG REPORT

1R

2L

GCU EMER

TR 2

2R

2L

TEST

2R

3L

BCL 1

TR 3

3R

3L

CLASS 3 FAULTS

3R

4L

BCL 2

4R

4L

4R

5R

5L

5R

6R

6L

5L 6L

RETURN

6R

RETURN

N_MM_244100_0_ANP0_01_00

AES

FIGURE 24-41-00-19200-B SHEET 1 Reading of Class 3 Faults on MCDU

24-41-00 PB001

Page 22 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC EXTERNAL POWER CONTROL - MAINTENANCE PRACTICES ** On A/C ALL Task 24-41-00-861-002-A Energize the Aircraft Electrical Circuits from the External Power WARNING : MAKE SURE THAT THE AIRCRAFT IS GROUNDED. WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. CAUTION :

1.

DO NOT USE A GROUND POWER UNIT WITH A CAPACITY LESS THAN 90 KVA. IF YOU USE A LESS POWERFUL UNIT: AN OVERLOAD OF THE GROUND POWER UNIT COULD OCCUR IT COULD BE NECESSARY TO RESET MANY COMPUTERS ON THE AIRCRAFT.

Reason for the Job NOTE :

2.

There are alternative methods for this procedure. This task gives one of the methods. For the other methods, refer to the other tasks in this page block.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE 98A24403000000 B.

QTY 1 CABLE HOLDING STRAP

DESIGNATION

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL C.

Referenced Information

REFERENCE 12-31-31-660-001-A

DESIGNATION Cold Weather Maintenance - Indicating/Recording systems and Navigation

12-34-24-869-002-A

Aircraft Grounding for the Maintenance Operations

24-41-00-040-001-A 31-60-00-860-001-A 31-60-00-860-002-A

Visual Inspection of the External Power Receptacle EIS Start Procedure EIS Stop Procedure

ESPM 20-55-10-0 24-41-51-000-001-A

Removal of the External Power Receptacle (for corrective action)

24-41-51-400-001-A

Installation of the External Power Receptacle (for corrective action)

(Ref. Fig. 24-41-00-991-00100-A - External Power Receptacle - Location) 3.

Job Set-up (Ref. Fig. 24-41-00-991-00100-A - External Power Receptacle - Location)

AES

24-41-00 PB201

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-41-00-860-050-A A.

Aircraft Maintenance Configuration NOTE :

In the avionics compartment, if the temperature is below -15 deg.C (5.00 deg.F), do the cold-weather maintenance procedure (Ref. TASK 12-31-31-660-001-A).

NOTE :

When you do maintenance work on the electrical circuits, it can be not possible to supply electrical power to the aircraft.

(1)

The aircraft must be grounded (Ref. TASK 12-34-24-869-002-A).

Subtask 24-41-00-010-050-A B.

Get Access (1)

Open the access door 121AL to get access to the external power receptacle and the panel 108VU.

Subtask 24-41-00-480-050-A C.

Install the cable holding strap (1)

Attach the CABLE HOLDING STRAP (98A24403000000) to the feeder cable.

(2)

Connect the snap hook of the cable holding strap to the fitting on the aircraft structure.

Subtask 24-41-00-420-050-A D.

Connection of the connector WARNING : BEFORE YOU CONNECT THE GROUND POWER UNIT TO THE EXTERNAL POWER RECEPTACLE OF THE AIRCRAFT, MAKE SURE THAT THE EXTERNAL ELECTRICAL POWER SUPPLY IS NOT ENERGIZED. IF IT IS ENERGIZED, DANGEROUS ARCING CAN OCCUR. CAUTION :

MAKE SURE THAT THE CABLE STRAP SUPPORTS ALL THE WEIGHT OF THE CABLE WHEN THE CONNECTOR IS CONNECTED. THIS PREVENTS DAMAGE TO THE EXTERNAL POWER RECEPTACLE.

CAUTION :

BEFORE YOU CONNECT THE GROUND POWER UNIT TO THE AIRCRAFT, MAKE SURE THAT THERE ARE NO FOREIGN OBJECTS OR FLUID IN THE EXTERNAL POWER RECEPTACLE OR THE GPU CONNECTOR. FOREIGN OBJECTS AND FLUID CAN CAUSE AN OVERHEAT AND/OR DAMAGE TO EQUIPMENT.

(1)

Examine the external power-supply cable and the external power receptacle before you do the connection. (a)

(2)

Do a visual inspection of the external power receptacle for overheat damage or cracks (Ref. TASK 24-41-00-040-001-A). (a)

(3)

AES

If you find corrosion or contamination: . Clean the external power receptacle or the GPU connector (Ref. ESPM 20-55-10-0).

If you find damage or if the pins are not aligned correctly: . Replace the external power receptacle (Ref. TASK 24-41-51-000-001-A) and (Ref. TASK 24-41-51-400-001-A).

Connect the connector of the ground power unit to the external receptacle of the aircraft.

24-41-00 PB201

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure ** On A/C 003-004 Subtask 24-41-00-861-051-A A.

Energize the Aircraft Electrical Circuit from the External Power (1)

On the ELEC panel 35VU, make sure that: . The GEN1, GEN2, APU GEN, BUS TIE, COMMERCIAL and AC ESS FEED pushbutton switches are pushed. . All the other pushbutton switches are released.

(2)

On the overhead CTL and IND panel 22VU, make sure that: . The BLOWER and EXTRACT pushbutton switches are pushed.

(3)

Start the ground power unit: WARNING : BEFORE YOU START THE GROUND POWER UNIT, MAKE SURE THAT THE CONNECTOR OF THE GROUND POWER UNIT IS CORRECTLY CONNECTED TO THE EXTERNAL POWER RECEPTACLE. THERE IS A RISK OF ARCING IF THE CONNECTOR IS NOT CORRECTLY CONNECTED. (a)

Obey the instructions given with the ground power unit and start the ground power unit.

(4)

If the protection circuits operate correctly: . On the panel 108VU, the EXT PWR/NOT IN USE indicator light and EXT PWR/AVAIL caution light come on. . On the panel 35VU, the AVAIL legend on the EXT PWR pushbutton switch comes on.

(5)

On the panel 35VU, push the EXT PWR pushbutton switch: . The AVAIL legend goes off.

(6)

If the electrical power supply of the aircraft circuits is correct, on the panel 35VU, these legends come on: . The ON legend of the EXT PWR pushbutton switch . The FAULT legend of the GEN1 and GEN2 pushbutton switches . The OFF legend of the BAT1 and BAT2 pushbutton switches . The OFF legend of the GALLEY pushbutton switch.

(7)

On the panel 22VU, make sure that the FAULT legend of the BLOWER and EXTRACT pushbutton switches is off. NOTE :

That means the electronics rack ventilation operates correctly.

(8)

On the panel 35VU, push the BAT1 and BAT2 pushbutton switches: . The OFF legends go off.

(9)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A). (a)

On the ECAM control panel, push the ELEC key (on the lower ECAM DU, the ELEC page comes into view).

(b)

On the ELEC page, make sure that these EXT PWR parameters are correct: . AC V = 115 + or - 5V, . FRQ HZ = 400 + or - 10HZ.

(10) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

AES

24-41-00 PB201

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Subtask 24-41-00-861-051-B A.

Energize the Aircraft Electrical Circuit from the External Power (1)

On the ELEC panel 35VU, make sure that: . The GEN1, GEN2, APU GEN, BUS TIE, COMMERCIAL and AC ESS FEED pushbutton switches are pushed. . All the other pushbutton switches are released.

(2)

On the overhead CTL and IND panel 22VU, make sure that: . The BLOWER and EXTRACT pushbutton switches are pushed.

(3)

Obey the instructions given with the ground power unit and start the ground power unit.

(4)

If the protection circuits operate correctly: . On the panel 108VU, the EXT PWR/NOT IN USE indicator light and EXT PWR/AVAIL caution light come on. . On the panel 35VU, the AVAIL legend on the EXT PWR pushbutton switch comes on.

(5)

On the panel 35VU, push the EXT PWR pushbutton switch: . The AVAIL legend goes off.

(6)

If the electrical power supply of the aircraft circuits is correct, on the panel 35VU, these legends come on: . The ON legend of the EXT PWR pushbutton switch . The FAULT legend of the GEN1 and GEN2 pushbutton switches . The OFF legend of the BAT1 and BAT2 pushbutton switches . The OFF legend of the GALY & CAB pushbutton switch.

(7)

On the panel 22VU, make sure that the FAULT legend of the BLOWER and EXTRACT pushbutton switches is off. NOTE :

That means the electronics rack ventilation operates correctly.

(8)

On the panel 35VU, push the BAT1 and BAT2 pushbutton switches: . The OFF legends go off.

(9)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A). (a)

On the ECAM control panel, push the ELEC key (on the lower ECAM DU, the ELEC page comes into view).

(b)

On the ELEC page, make sure that these EXT PWR parameters are correct: . AC V = 115 + or - 5V, . FRQ HZ = 400 + or - 10HZ.

(10) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

AES

24-41-00 PB201

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 121AL 108VU

A

121AL

N_MM_244100_2_AAM0_01_00

AES

FIGURE 24-41-00-991-00100-A SHEET 1 External Power Receptacle - Location

24-41-00 PB201

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-41-00-861-002-A-01 Energize the Aircraft Electrical Circuits from the APU WARNING : MAKE SURE THAT THE AIRCRAFT IS GROUNDED. WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Referenced Information

REFERENCE 12-31-31-660-001-A

DESIGNATION Cold Weather Maintenance - Indicating/Recording systems and Navigation

12-34-24-869-002-A

Aircraft Grounding for the Maintenance Operations

31-60-00-860-001-A ** On A/C 006-099

EIS Start Procedure

49-00-00-860-005-A

APU Start by External Power

49-00-00-860-005-A-01

APU Start by Batteries

** On A/C 003-005 49-00-00-860-008-A

APU Start by External Power

49-00-00-860-008-A-01

APU Start by Batteries

3.

Job Set-up ** On A/C ALL Subtask 24-41-00-860-051-A A.

Aircraft Maintenance Configuration NOTE :

4.

In the avionics compartment, if the temperature is below -15 deg.C (5.00 deg.F), do the cold-weather maintenance procedure (Ref. TASK 12-31-31-660-001-A).

(1)

The aircraft must be grounded (Ref. TASK 12-34-24-869-002-A).

(2)

On the ELEC panel 35VU, make sure that: . the GEN1, GEN2, APU GEN, BUS TIE and AC ESS FEED pushbutton switches are pushed,

(3)

On the overhead CTL and IND panel 22VU, make sure that BLOWER and EXTRACT pushbutton switches are pushed.

Procedure Subtask 24-41-00-861-052-A A.

Energize the aircraft electrical circuit from the APU. (1)

AES

Start the APU: . GTCP 36-300 (Ref. AMM 49-00-00-860-003) or . APS 3200

24-41-00 PB201

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

.

(2)

** On A/C 006-099 (Ref. TASK 49-00-00-860-005-A) or (Ref. TASK 49-00-00-860-005-A-01) or 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-00-00-860-008-A)(Ref. TASK 49-00-00-860-008-A-01).

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) ** On A/C ALL (Ref. TASK 31-60-00-860-001-A).

(3)

On the ECAM control panel, push the ELEC key (on the lower ECAM DU, the ELEC page comes into view).

(4)

Make sure that the APU energizes the aircraft electrical circuit correctly.

(5)

On the VENTILATION section of the panel 22VU: . make sure that the FAULT legends of the BLOWER and EXTRACT pushbutton switches are off. NOTE :

AES

This is an indication of the correct operation of the avionics equipment ventilation.

24-41-00 PB201

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-41-00-861-002-A-02 Energize the Aircraft Electrical Circuits from Engine 1(2) WARNING : MAKE SURE THAT THE AIRCRAFT IS GROUNDED. WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Referenced Information

REFERENCE 12-31-31-660-001-A

DESIGNATION Cold Weather Maintenance - Indicating/Recording systems and Navigation

12-34-24-869-002-A

Aircraft Grounding for the Maintenance Operations

24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 71-00-00-710-043-A

EIS Start Procedure Normal Engine Automatic Start Procedure

3.

Job Set-up Subtask 24-41-00-860-052-A A.

4.

Aircraft Maintenance Configuration NOTE :

In the avionics compartment, if the temperature is below -15 deg.C (5.00 deg.F), do the cold-weather maintenance procedure (Ref. TASK 12-31-31-660-001-A).

NOTE :

The procedure is the same for the engines 1 and 2.

(1)

The aircraft must be grounded (Ref. TASK 12-34-24-869-002-A).

(2)

Do not energize the aircraft electrical circuits from the external power.

(3)

Energize the aircraft electrical circuits from APU (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

Procedure Subtask 24-41-00-861-053-B A.

AES

Energize the aircraft electrical circuit from engine 1(2) (1)

Start the engine 1(2) with the automatic procedure (Ref. TASK 71-00-00-710-043-A): . on the ELEC panel 35VU, the FAULT legend of the GEN 1(2) pushbutton switch goes off.

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

24-41-00 PB201

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AES

(3)

On the ECAM control panel, push the ELEC key (on the lower ECAM DU, the ELEC page comes into view).

(4)

On . . . . . . .

(5)

On the ELEC panel 35VU, release the APU GEN pushbutton switch: . the OFF legend of the APU GEN pushbutton switch comes on.

(6)

On . . .

(7)

Stop the APU (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

the ELEC page, make sure that: the GEN 1(2) indication comes into view white, the parameters related to GEN 1(2) come into view green, the line between GEN 1(2) and AC 1(2) comes into view green, the GEN 2(1) indication and the related parameters come into view green, the APU GEN indication and the related parameters come into view green, the line between APU GEN and AC 2(1) comes into view green, the line between APU GEN and AC 1(2) goes out of view.

the ELEC page, make sure that: the APU GEN indication comes into view amber and the OFF indication white, the line between GEN 1(2) and AC 2(1) comes into view green, the line between APU GEN and AC 2(1) goes out of view.

24-41-00 PB201

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-41-00-862-002-A De-energize the Aircraft Electrical Circuits Supplied from the External Power 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL B.

Referenced Information

REFERENCE DESIGNATION (Ref. Fig. 24-41-00-991-00100-A - External Power Receptacle - Location) 3.

Job Set-up Subtask 24-41-00-869-067-A A.

4.

Not Applicable

Procedure ** On A/C 003-004 Subtask 24-41-00-862-051-A A.

De-energize the aircraft electrical circuits from the external power (1)

On the ELEC panel 35VU, push and release the BAT1 and BAT2 pushbutton switches: . the OFF legends come on.

(2)

On the panel 35VU, push the EXT PWR pushbutton switch: . the ON legend goes off, . the AVAIL legend comes on.

(3)

The aircraft electrical circuits are correctly de-energized if: (a)

On . . .

the panel 35VU, these legends go off: the FAULT legend of the GEN1 and GEN2 pushbutton switches, the OFF legend of the BAT1 and BAT2 pushbutton switches, the OFF legend of the GALLEY pushbutton switch.

(b)

On the panel 108VU, the EXT PWR/NOT IN USE indicator light comes on.

** On A/C 005-099 Subtask 24-41-00-862-051-B A.

AES

De-energize the aircraft electrical circuits from the external power (1)

On the ELEC panel 35VU, push and release the BAT1 and BAT2 pushbutton switches: . the OFF legends come on.

(2)

On the panel 35VU, push the EXT PWR pushbutton switch: . the ON legend goes off, . the AVAIL legend comes on.

24-41-00 PB201

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

5.

The aircraft electrical circuits are correctly de-energized if: (a)

On . . .

the panel 35VU, these legends go off: the FAULT legend of the GEN1 and GEN2 pushbutton switches, the OFF legend of the BAT1 and BAT2 pushbutton switches, the OFF legend of the GALY and CAB pushbutton switch.

(b)

On the panel 108VU, the EXT PWR/NOT IN USE indicator light comes on.

Close-up

** On A/C ALL (Ref. Fig. 24-41-00-991-00100-A - External Power Receptacle - Location) Subtask 24-41-00-080-051-A A.

Obey the instructions given with the ground power unit and stop the ground power unit. . On the panel 35VU, all the pushbutton switch legends are off. . On the panel 108VU, all the lights are off.

Subtask 24-41-00-020-050-A B.

Disconnect the connector WARNING : DE-ENERGIZE THE ELECTRICAL POWER SUPPLY BEFORE YOU DISCONNECT THE CONNECTOR OF THE GROUND POWER UNIT. IF NOT DANGEROUS ARCING CAN OCCUR. (1)

Disconnect the connector of the ground power unit from the external power receptacle.

Subtask 24-41-00-080-050-A C.

Remove the ground support and maintenance equipment, the special and standard tools and all other items. (1)

Disconnect the snap hook from the fitting on the aircraft structure.

(2)

Disconnect the aircraft electrical ground connector.

Subtask 24-41-00-410-051-A D.

Close Access (1)

AES

Close the access door 121AL.

24-41-00 PB201

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-41-00-862-002-A-01 De-energize the Aircraft Electrical Circuits Supplied from the APU 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Referenced Information

REFERENCE 31-60-00-860-002-A

DESIGNATION EIS Stop Procedure

** On A/C 006-099 49-00-00-860-006-A

APU Shutdown by External Power

49-00-00-860-006-A-01

APU Shutdown by Batteries

** On A/C 003-005 49-00-00-860-009-A

APU Shutdown by External Power (131-9(A))

49-00-00-860-009-A-01

APU Shutdown by Batteries (131-9(A))

3.

Job Set-up ** On A/C ALL Subtask 24-41-00-869-068-A A.

Aircraft Maintenance Configuration (1)

4.

On the panel 35VU, make sure that the APU GEN pushbutton switch is pushed (OFF legend is off).

Procedure Subtask 24-41-00-862-052-A A.

De-energize the aircraft electrical circuits from the APU (1)

5.

On the ELEC panel 35VU, release the APU GEN pushbutton switch.

Close-up Subtask 24-41-00-860-053-A A.

Put the aircraft back to its initial configuration. (1)

AES

Stop the APU: . GTCP 36-300 (Ref. AMM 49-00-00-860-004) or . APS 3200 ** On A/C 006-099 (Ref. TASK 49-00-00-860-006-A) or (Ref. TASK 49-00-00-860-006-A-01) or . 131-9(A) ** On A/C 003-005 EMB SB 49-1082 FOR A/C 003-005 (Ref. TASK 49-00-00-860-009-A)(Ref. TASK 49-00-00-860-009-A-01).

24-41-00 PB201

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Do the EIS stop procedure ** On A/C ALL (Ref. TASK 31-60-00-860-002-A).

AES

24-41-00 PB201

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-41-00-862-002-A-02 De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Referenced Information

REFERENCE 31-60-00-860-002-A

EIS Stop Procedure

71-00-00-710-018-A

Discontinued Start, Restart and Shutdown Procedures

3.

DESIGNATION

Job Set-up Subtask 24-41-00-869-069-A A.

4.

Not Applicable

Procedure Subtask 24-41-00-862-053-B A.

De-energize the aircraft electrical circuits from the engine 1(2) NOTE :

5.

The procedure is the same for the engine 1 and 2.

(1)

Stop the engine 1(2) (Ref. TASK 71-00-00-710-018-A).

(2)

On the panel 35VU, make sure that the FAULT legend of the GEN 1(2) pushbutton switch comes on.

Close-up Subtask 24-41-00-860-054-B A.

AES

Put the aircraft back to its initial configuration. (1)

On the panel 35VU, release the BAT1 and BAT2 pushbutton switches : . the FAULT legends of the GEN1 and GEN2 pushbutton switches go off.

(2)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A)

24-41-00 PB201

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC EXTERNAL POWER CONTROL DEACTIVATION/REACTIVATION ** On A/C ALL Task 24-41-00-040-001-A Visual Inspection of the External Power Receptacle 1.

Reason for the Job MMEL 24-41-02A External Power Receptacle (Old MMEL ref: 24-41-01-B)

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY AR GUN - HOT AIR

No specific

AR

B.

DESIGNATION

WARNING NOTICE(S)

Consumable Materials

REFERENCE Material No: 11-002

DESIGNATION CLEANING AGENTS DRY CLEANING SOLVENT (VARSOL/WHT SPIRIT)

Material No: 19-003

LINT-FREE COTTON CLOTH

C.

Referenced Information

REFERENCE 52-42-12-000-001-A

DESIGNATION Removal of the External-Power Receptacle Door (121AL)

52-42-12-400-001-A

Installation of the External-Power Receptacle Door (121AL)

SRM 512800 SRM 531113 (Ref. Fig. 24-41-00-991-00200-A - External Power Receptacle) 3.

Job Set-up Subtask 24-41-00-860-062-A A.

Safety Precautions (1)

Make sure that the ground power source is not connected to the aircraft external-power receptacle.

Subtask 24-41-00-010-053-A B.

4.

Get Access (1)

Put an access platform in position at the external-power receptacle door (121AL).

(2)

Open the external-power receptacle door (121AL).

Procedure (Ref. Fig. 24-41-00-991-00200-A - External Power Receptacle)

AES

24-41-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-41-00-210-051-A A.

Visual Inspection of the Electrical-Power Receptacle Assembly and the External-Power Receptacle Door (1)

Examine the electrical-power receptacle assembly. (a)

Examine the electrical-power receptacle assembly for overheat damage (Ref. SRM 512800). WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1

(b)

Examine the electrical-power receptacle assembly for cracks: 1

(c)

5.

If the aircraft structure is damaged: . Repair it (Ref. SRM 531113).

Examine the external-power receptacle door (121AL). (a)

Open and close the external-power receptacle door (121AL).

(b)

Make sure that the external-power receptacle door (121AL) operates correctly. 1

(3)

Make sure that there are no cracks on the external power receptacle and on the adjacent structure.

Examine the aircraft structure around the electrical power receptacle. 1

(2)

If there is overheat damage: . Clean the electrical-power receptacle assembly with a LINT-FREE COTTON CLOTH (Material No: 19-003) and CLEANING AGENTS (Material No: 11-002) . . Make sure that there are no holes on the receptacle and the adjacent structure.

If the external-power receptacle door (121AL) does not operate correctly: . Remove the external-power receptacle door (121AL) (Ref. TASK 52-42-12-000-001-A). Refer to CDL 52-7: External power ground connection access door assy, or . Replace the external-power receptacle door (121AL) (Ref. TASK 52-42-12-000-001-A) and (Ref. TASK 52-42-12-400-001-A).

If the electrical-power receptacle assembly is damaged and the external-power receptacle door (121AL) was not removed: . Put a WARNING NOTICE(S) in position to tell persons not to connect power connector to the electrical power receptacle. . Put a shrink sleeve ABS0916B07 in position below the pins A and B of the electrical power receptacle. Shrink it with a GUN - HOT AIR.

Close-up Subtask 24-41-00-410-053-A A.

Close Access (1)

AES

Close the external-power receptacle door (121AL).

24-41-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-41-00-942-051-A B.

AES

Put the aircraft back to its initial configuration. (1)

Remove the access platform(s).

(2)

Make an entry in the log book.

24-41-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR7

FR8 Z120

A

121AL

A

DOOR

STOP ANGLE

SPRING ROD ASSY

LATCH ASSY

N_MM_244100_4_AAN0_01_00

AES

FIGURE 24-41-00-991-00200-A SHEET 1 External Power Receptacle

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC EXTERNAL POWER CONTROL - ADJUSTMENT/TEST ** On A/C ALL Task 24-41-00-740-004-A Operational Check of the GPCU via the CFDS 1.

Reason for the Job (Ref. MPD 24-41-00-01-) OPERATIONAL CHECK OF GPCU VIA CFDS

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

210

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

B.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-32-00-860-004-A

Procedure to Get Access to the SYSTEM REPORT/TEST/ELEC Page

3.

Job Set-up Subtask 24-41-00-860-063-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GEN 1 and GEN 2 pushbutton switches are in the ON position (FAULT legend on).

(3)

On the MCDU, get access to the SYSTEM REPORT/TEST page of the ELEC system (Ref. TASK 31-32-00-860-004-A).

Subtask 24-41-00-865-054-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

DESIGNATION

FIN

LOCATION

122VU

ELEC/GCU/2

2XU2

T27

122VU

ELEC/GCU/1

2XU1

T26

122VU

ELEC/APU/GCU

6XS

Y25

122VU

ELEC/GPCU

7XG

Y24

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL 123VU 4.

DESIGNATION GND/PWR/PROT

FIN 2XG

LOCATION AB07

Procedure Subtask 24-41-00-710-069-A A.

Test of the GPCU from the Centralized Fault Display System (CFDS)

ACTION 1.On the MCDU, on the SYSTEM REPORT/TEST page of the ELEC system: . Push the line key adjacent to the AC GEN indication.

RESULT On the MCDU: . The AC GEN page comes into view.

2.On the AC GEN page: . Push the line key adjacent to the TEST indication.

On the MCDU, on the AC GEN page: . The TEST WAIT message comes into view (after some seconds). . Then the TEST OK message comes into view (after some seconds).

3.On the ELEC panel 35VU: . Release the GEN 1 and GEN 2 pushbutton switches.

On the ELEC panel 35VU: . The OFF legend of the GEN 1 and GEN 2 pushbutton switches comes on. . The FAULT legend of the GEN 1 and GEN 2 pushbutton switches comes on.

.

Push the GEN 1 and GEN 2 pushbutton switches.

4.On the MCDU: . Push the line key adjacent to the RETURN indication until the AC GEN page comes into view. Subtask 24-41-00-710-070-A B.

Check of the class 3 faults of the GPCU from the CFDS

ACTION 1.On the MCDU, on the SYSTEM REPORT/TEST page of the ELEC system: . Push the line key adjacent to the AC GEN indication.

RESULT On the MCDU: . The AC GEN page comes into view.

2.On the AC GEN page: . Push the line key adjacent to the CLASS 3 FAULTS indication.

On the AC GEN page: . The NO FAULT message comes into view.

5.

Close-up Subtask 24-41-00-860-064-A A.

AES

Put the aircraft back to its initial configuration. (1)

On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view.

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-41-00 PB501

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTROL UNIT - GROUND POWER (GPCU OR GAPCU) REMOVAL/INSTALLATION ** On A/C ALL Task 24-41-34-000-001-A Removal of the Ground Power Control Unit (GPCU) CAUTION :

MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF DAMAGE TO EQUIPMENT DURING ITS REMOVAL/ INSTALLATION IF THE AC OR DC POWER STAYS CONNECTED.

FIN 1XG 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

1

ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

122 121AL, 811 C.

ZONE DESCRIPTION AVIONICS COMPARTMENT

Referenced Information

REFERENCE DESIGNATION (Ref. Fig. 24-41-34-991-00100-A - Ground Power Control Unit (GPCU)) 3.

Job Set-up Subtask 24-41-34-010-050-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access door 811.

(2)

Open the access door 811.

(3)

Put an ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE at the access door 121AL.

(4)

Open the access door 121AL.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-41-34-941-051-A B.

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft receptacle.

(2)

Put WARNING NOTICE(S) on the access door 121AL to tell persons not to use the external power receptacle.

(3)

In . . . .

(4)

In the cockpit, put WARNING NOTICE(S) to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(5)

In the cockpit, on the APU section of the overhead panel 25VU, put WARNING NOTICE(S) to tell persons not to start the APU.

the cockpit, on the overhead ELEC panel 35VU, release these pushbutton switches: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

Subtask 24-41-34-865-056-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

122VU

DESIGNATION ELEC/EXT PWR/CTL

11XG

X29

122VU

ELEC/GPCU

7XG

Y24

123VU

GND/PWR/PROT

2XG

AB07

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-41-34-991-00100-A - Ground Power Control Unit (GPCU)) Subtask 24-41-34-020-050-A A.

AES

Removal of the GPCU (1)

Loosen the two knurled nuts (1).

(2)

Lower the two knurled nuts (1) to release the two studs (2).

(3)

Carefully pull on the handle (3) of the GPCU (4) until the fixed connector (5) is disconnected.

(4)

Remove the GPCU from its rack (6).

(5)

Put blanking caps on the disconnected electrical connector(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 1XG FR1

A

B

811

A

FR9

FWD ELECTRONICS RACK 90VU

B 4

3

2

5 6

1 N_MM_244134_4_AAM0_01_00

AES

FIGURE 24-41-34-991-00100-A SHEET 1 Ground Power Control Unit (GPCU)

24-41-34 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-41-34-400-001-A Installation of the Ground Power Control Unit (GPCU) CAUTION :

MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF DAMAGE TO EQUIPMENT DURING ITS REMOVAL/ INSTALLATION IF THE AC OR DC POWER STAYS CONNECTED.

FIN 1XG 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

1

ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

122 121AL, 811 C.

ZONE DESCRIPTION AVIONICS COMPARTMENT

Referenced Information

REFERENCE 24-41-00-740-004-A 24-41-00-861-002-A

DESIGNATION Operational Check of the GPCU via the CFDS Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

(Ref. Fig. 24-41-34-991-00100-A - Ground Power Control Unit (GPCU)) 3.

Job Set-up Subtask 24-41-34-860-050-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 811.

(2)

Make sure that the access door 811 is open.

(3)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

(5)

Make sure that the external power connector is not connected to the aircraft receptacle.

(6)

Make sure that a WARNING NOTICE(S) is in position on the access door 121AL to tell persons not to use the external power receptacle.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (7)

In the cockpit, on the overhead ELEC panel 35VU, make sure that these pushbutton switches are released: . BAT 1, BAT 2, . APU GEN, . GEN 1, GEN 2, . EXT PWR.

(8)

In the cockpit, make sure that a WARNING NOTICE(S) is in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(9)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

Subtask 24-41-34-865-057-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

122VU

PANEL

DESIGNATION ELEC/EXT PWR/CTL

11XG

X29

122VU

ELEC/GPCU

7XG

Y24

123VU

GND/PWR/PROT

2XG

AB07

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-41-34-991-00100-A - Ground Power Control Unit (GPCU)) Subtask 24-41-34-420-050-A A.

Installation of the GPCU (1)

Remove the blanking caps from the electrical connector(s).

(2)

Make sure that the electrical connectors are clean and in the correct condition.

(3)

Clean the component interface and/or the adjacent area.

(4)

Do an inspection of the component interface and/or the adjacent area.

(5)

Put the GPGU in position in its rack (6).

(6)

Slowly push the GPCU until it connects with the fixed connector (5).

(7)

Lift the 2 knurled nuts (1) over the 2 studs (2).

(8)

Tighten the 2 knurled nuts (1).

Subtask 24-41-34-865-058-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

122VU

PANEL

DESIGNATION ELEC/EXT PWR/CTL

11XG

X29

122VU

ELEC/GPCU

7XG

Y24

123VU

GND/PWR/PROT

2XG

AB07

AES

FIN

LOCATION

24-41-34 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-41-34-710-050-A C.

Operational Test of the Ground Power Control Unit (1)

Do the operational check of the GPCU with the CFDS (Ref. TASK 24-41-00-740-004-A). NOTE :

5.

As an alternative procedure for the operational test without the CFDS, you can do this procedure (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02). Make sure that the aircraft electrical circuits are correctly energized with the external power supply.

Close-up Subtask 24-41-34-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the warning notice(s).

(3)

Close the access door 811.

(4)

Close the access door 121AL.

(5)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

RECEPTACLE - EXTERNAL POWER - REMOVAL/INSTALLATION ** On A/C ALL Task 24-41-51-000-001-A Removal of the External Power Receptacle WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 20XG 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

1

ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

120 121AL, 811 C.

ZONE DESCRIPTION AVIONICS COMPARTMENT

Referenced Information

REFERENCE (Ref. Fig. 24-41-51-991-00100-A - External Power Receptacle) 3.

DESIGNATION

Job Set-up Subtask 24-41-51-010-050-A A.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access door 811.

(2)

Open the access door 811.

(3)

Put an ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-41-51-941-050-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft receptacle.

(2)

Put WARNING NOTICE(S) on the access door 121AL to tell persons not to use the external power receptacle.

(3)

In the cockpit, on the overhead ELEC panel 35VU, release these pushbutton switches: . BAT 1, BAT 2,

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . . .

4.

APU GEN, GEN 1, GEN 2, EXT PWR.

(4)

In the cockpit, put WARNING NOTICE(S) to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(5)

In the cockpit, on the APU section of the overhead panel 25VU, put WARNING NOTICE(S) to tell persons not to start the APU.

Procedure (Ref. Fig. 24-41-51-991-00100-A - External Power Receptacle) Subtask 24-41-51-020-050-A A.

Removal of the External Power Receptacle CAUTION :

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Loosen the 4 nuts (14).

(2)

Remove the 4 nuts (14) and the washers (15, 13).

(3)

Remove the protective cover (1).

(4)

Loosen the 6 nuts (3).

(5)

Remove the nuts (3) and the washers (4).

(6)

Remove the electrical wires (5).

(7)

Loosen the 3 screws (2).

(8)

Remove the screws (2) and the washers (6).

(9)

Remove the 4 studs (12) and the 4 washers (11).

(10) Remove the external power receptacle (10). (11) Remove and discard the seal (9).

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 14 15 13

1

A 3 FR8

12 4

FR7

5 11

20XG

10

2 6

9

7

N_MM_244151_4_AAM0_01_00

AES

FIGURE 24-41-51-991-00100-A SHEET 1 External Power Receptacle

24-41-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-41-51-400-001-A Installation of the External Power Receptacle WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 20XG 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

1

ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

120 121AL, 811 C.

ZONE DESCRIPTION AVIONICS COMPARTMENT

Expendable Parts

FIG.ITEM 9

DESIGNATION

IPC-CSN 24-41-01-01-040

seal D.

Referenced Information

REFERENCE 20-21-15-912-001-A

DESIGNATION Tightening Torques for Electrical Component Fasteners

24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

ESPM 20-45-93-0 (Ref. Fig. 24-41-51-991-00100-A - External Power Receptacle) 3.

Job Set-up Subtask 24-41-51-860-050-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 811.

(2)

Make sure that the access door 811 is open.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4.

(3)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

(5)

Make sure that the external power connector is not connected to the aircraft receptacle.

(6)

Make sure that a WARNING NOTICE(S) is in position on the access door 121AL to tell persons not to use the external power receptacle.

(7)

In the cockpit, on the overhead ELEC panel 35VU, make sure that these pushbutton switches are released: . BAT 1, BAT 2, . APU GEN, . GEN 1, GEN 2, . EXT PWR.

(8)

In the cockpit, make sure that WARNING NOTICE(S) are in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(9)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

Procedure (Ref. Fig. 24-41-51-991-00100-A - External Power Receptacle) Subtask 24-41-51-420-050-A A.

Installation of the External Power Receptacle CAUTION :

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Put a new (IPC-CSN 24-41-01-01) seal (9) on its support (7).

(2)

Put the external power receptacle (10) in position.

(3)

Install the washers (11) and the studs (12) on the external power receptacle (10), then tighten the studs (Ref. TASK 20-21-15-912-001-A) (Ref. ESPM 20-45-93-0).

(4)

Install the washers (6) and the 3 screws (2) and then tighten the screws (Ref. TASK 20-21-15-912-001A) (Ref. ESPM 20-45-93-0).

(5)

Install the electrical wires (5).

(6)

Install washers (4) and the nuts (3) and then tighten the nuts (Ref. TASK 20-21-15-912-001-A) (Ref. ESPM 20-45-93-0).

(7)

Install the protective cover (1).

(8)

Install the washers (13, 15) and the nuts (14) and then tighten the nuts (Ref. TASK 20-21-15-912-001A) (Ref. ESPM 20-45-93-0).

Subtask 24-41-51-710-050-A B.

Test of the External Power Supply (1)

AES

Make sure that the aircraft electrical circuits are correctly energized with the external power supply (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002A-02).

24-41-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-41-51-862-050-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Subtask 24-41-51-410-050-A B.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the warning notice(s).

(3)

Close the access door 811.

(4)

Close the access door 121AL.

(5)

Remove the access platform(s).

24-41-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-41-55-000-001-A Removal of the External Power Contactor (EPC) WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 3XG 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 25-11-41-000-001-A

DESIGNATION Removal of the Third Occupant Seat

(Ref. Fig. 24-41-55-991-00100-A - Contactor) (Ref. Fig. 24-41-55-991-00100-B - Contactor) 3.

Job Set-up Subtask 24-41-55-010-050-A A.

Get Access (1)

Remove the third occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

In the cokpit, remove the access panel (8) from the bottom left side of the panel 120VU.

(3)

Put an ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-41-55-941-050-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft receptacle.

(2)

Put WARNING NOTICE(S) on the access door 121AL to tell persons not to use the external power receptacle.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4.

(3)

In . . . .

the cockpit, on the overhead ELEC panel 35VU, release these pushbutton switches: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

(4)

In the cockpit, put WARNING NOTICE(S) to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(5)

In the cockpit, on the APU section of the overhead panel 25VU, put WARNING NOTICE(S) to tell persons not to start the APU.

Procedure

** On A/C 003-004 (Ref. Fig. 24-41-55-991-00100-A - Contactor) ** On A/C 005-099 (Ref. Fig. 24-41-55-991-00100-B - Contactor) ** On A/C ALL Subtask 24-41-55-020-050-A A.

Removal of the Contactor CAUTION :

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

(1)

Disconnect the electrical connector (1).

(2)

Put blanking caps on the disconnected electrical connector(s).

(3)

Loosen the 6 captive screws (2). NOTE :

(4)

Do not remove the captive screws (2) and the spring washers from the contactor (3).

Remove the contactor (3).

** On A/C 003-004 Subtask 24-41-55-020-051-A CAUTION :

B.

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Removal of the Contactor Base NOTE : (1)

(2)

AES

The removal of the base is necessary only if the base is damaged.

If the base has the components that follow: (a)

Remove the screws (9) and the washers (10).

(b)

Disconnect the electrical wires (11).

Remove the nuts (12) and the washers (13).

24-41-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Disconnect the cables (14) from the base (6).

(4)

Remove the nuts (15) and the washers (16).

(5)

Remove the jumpers (17) from the base (6) and from the adjacent bases.

(6)

Remove the four screws (19) and the four washers (18).

(7)

Remove the base (6).

** On A/C 005-099 Subtask 24-41-55-020-051-B CAUTION :

B.

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Removal of the Contactor Module NOTE : (1)

AES

The removal of the module is necessary only if the module is damaged.

If the module has the components that follow: (a)

Remove the screws (9) and the washers (10).

(b)

Disconnect the electrical wires (11).

(2)

Remove the nuts (12) and the washers (13).

(3)

Disconnect the cables (14) from the module (5).

(4)

Remove the nuts (19) and the washers (18).

(5)

Remove the jumpers (17) from the module (5) and from the adjacent modules.

(6)

Remove the eight screws (16) and the eight washers (15).

(7)

Remove the module (5).

24-41-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

A 122VU

120VU

121VU

125VU

124VU

3XG

123VU

B

8

A

16

17

15

B 14 5

13

11 12

6

10 3

9

2 CONTACTOR BASE

CONTACTOR 18 19

7 1 N_MM_244155_4_AAM0_01_00

AES

FIGURE 24-41-55-991-00100-A SHEET 1 Contactor

24-41-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A 120VU 122VU

121VU 29XN

B

125VU

124VU 123VU

3XG

8

B

14 13

A

11

12

10 9 3

2 17

CONTACTOR 18 7 19 5 1

MODULE

CONTACTOR

1

7

15 16 N_MM_244155_4_AAP0_01_00

AES

FIGURE 24-41-55-991-00100-B SHEET 1 Contactor

24-41-55 PB401

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-41-55-400-001-A Installation of the External Power Contactor (EPC) WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 3XG 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

No specific

B.

WARNING NOTICE(S) Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 20-21-15-912-001-A

DESIGNATION Tightening Torques for Electrical Component Fasteners

24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-11-41-000-001-A 25-11-41-400-001-A

Removal of the Third Occupant Seat Installation of the Third Occupant Seat

(Ref. Fig. 24-41-55-991-00100-A - Contactor) (Ref. Fig. 24-41-55-991-00100-B - Contactor) 3.

Job Set-up Subtask 24-41-55-860-050-A A.

AES

Aircraft Maintenance Configuration (1)

In the cockpit, make sure that the third occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(2)

In the cockpit, make sure that the access panel (8) is removed.

24-41-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4.

(3)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

(5)

Make sure that the external power connector is not connected to the aircraft receptacle.

(6)

Make sure that a WARNING NOTICE(S) is in position on the access door 121AL to tell persons not to use the external power receptacle.

(7)

In the cockpit, on the overhead ELEC panel 35VU, make sure that these pushbutton switches are released: . BAT 1, BAT 2, . APU GEN, . GEN 1, GEN 2, . EXT PWR.

(8)

In the cockpit, make sure that a WARNING NOTICE(S) is in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(9)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

Procedure

** On A/C 003-004 (Ref. Fig. 24-41-55-991-00100-A - Contactor) ** On A/C 005-099 (Ref. Fig. 24-41-55-991-00100-B - Contactor) ** On A/C 003-004 Subtask 24-41-55-420-051-A A.

Installation of the Contactor Base CAUTION :

AES

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Install the contactor base (6) in correct position.

(2)

Install the four screws (19) and washers (18) and tighten them.

(3)

Make sure that the electrical cables (14) are clean and in correct condition.

(4)

Install the cables (14).

(5)

Install the nuts (12) and the washers (13) and tighten them.

(6)

If the base has the components that follow: (a)

Install the three electrical wires (11).

(b)

Install the screws (10) and the washers (9) and tighten them.

(7)

Install the jumpers (17) between the base (6) and the adjacent bases.

(8)

Install the washers (15) and the nuts (16) and tighten them (Ref. TASK 20-21-15-912-001-A).

24-41-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Subtask 24-41-55-420-051-B A.

Installation of the Contactor Module CAUTION :

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Install the contactor module (5) in correct position.

(2)

Install the eight screws (16) and washers (15) and tighten them.

(3)

Make sure that the electrical cables (14) are clean and in correct condition.

(4)

Install the cables (14).

(5)

Install the nuts (13) and the washers (12) and tighten them.

(6)

If the base has the components that follow: (a)

Install the electrical wires (11).

(b)

Install the screws (10) and the washers (9) and tighten them.

(7)

Install the jumpers (17) between the module (5) and the adjacent modules.

(8)

Install the washers (19) and the nuts (18) and tighten them (Ref. TASK 20-21-15-912-001-A).

** On A/C ALL Subtask 24-41-55-420-050-A B.

Installation of the Contactor (1)

Install the contactor (3) on the 6 tapped barrels (5) of the contactor base (6).

(2)

TORQUE the six captive screws (2) to between 0.50 and 0.60 M.DAN (44.25 and 53.10 LBF.IN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (1).

Subtask 24-41-55-710-050-A C.

Test of the External Power Supply (1)

5.

Make sure that the aircraft electrical circuits are correctly energized with the external power supply (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002A-02).

Close-up Subtask 24-41-55-862-050-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-41-55-410-050-A B.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the warning notice(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AES

(3)

Install the access panel (8) on the panel 120VU.

(4)

Install the third occupant seat (Ref. TASK 25-11-41-400-001-A).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

24-41-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC GROUND SERVICE BUS CONTROL - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General

** On A/C 003-004 (Ref. Fig. 24-42-00-11200-A - AC Ground Service Network - Block Diagram) ** On A/C 005-099 (Ref. Fig. 24-42-00-11200-E - AC Ground Service Network - Block Diagram) AC ground/flight distribution network can be supplied: . either normally from the aircraft network, . or directly by the ground power unit upstream of the external power contactor, in ground service configuration. In ground service configuration this network can be supplied without energizing the whole aircraft network.

AES

24-42-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location

** On A/C 003-004 (Ref. Fig. 24-42-00-12400-A - AC Ground Service Bus - Component Location) ** On A/C 005-099 (Ref. Fig. 24-42-00-12400-D - AC Ground Service Bus - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS ATA REF. DOOR

** On A/C ALL 12XX CNTOR-AC GND SVCE SPLY 14XX CNTOR-AC & DC GND SVCE SPLY ** On A/C 005-099

120VU 120VU

212 212

24-42-55 24-42-55

16XX CNTOR-SVCE BUS 2 120VU 212 24-42-00 ------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA I I I I DOOR I REF. ------------------------------------------------------------------------------5XX SW-MAINT BUS 2000VU 220 841

AES

24-42-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description The AC ground/flight network comprises the sub-busbars: . 212XP, . 214XP, . 216XP-C.

AES

24-42-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Operation/Control and Indicating

** On A/C 003-004 (Ref. Fig. 24-42-00-15000-A - AC Ground Service Bus Control - Schematic Diagram) ** On A/C 005-099 (Ref. Fig. 24-42-00-15000-E - AC Ground Service Bus Control - Schematic Diagram) ** On A/C 003-004 Supply selection for ground service network is controlled from panel 2000VU, MAINT BUS switch: . one position corresponds to the normal supply configuration, . the other position controls the ground service network supply from the ground power unit, if available. This position is electromagnetically latched. The switch returns to the normal position in case of voluntary or automatic (GPCU protections) unlatching of the ground power unit. The normal supply configuration takes precedence over the ground service configuration. NOTE :

Overheat of TR2 results in the automatic unlatching of MAINT BUS switch. This entails the cut-off of the ground distribution network.

** On A/C 005-099 Supply selection for ground service network is controlled from panel 2000VU, MAINT BUS switch: . one position corresponds to the normal supply configuration. . the other position controls the ground service network supply from the ground power unit, if available and if the ”COMMERCIAL” pushbutton switch (commercial load shed) is pressed. This position is electromagnetically latched. The switch returns to the normal position in case of voluntary or automatic (GPCU protections) unlatching of the ground power unit. The normal supply configuration takes precedence over the ground service configuration. NOTE :

AES

Overheat of TR2 results in the automatic unlatching of MAINT BUS switch. This entails the cut-off of the ground distribution network.

24-42-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

24 − 67 − 00 601PP 602PP

24 − 61 − 00

DC SVCE BUS

6PP 28VDC

3PX

1PX 24 − 32 − 00

1PU2 TR2

24 − 32 − 00

24 − 50 − 00

24 − 50 − 00

AC BUS 1

1XP

24 − 25 − 00

24 − 25 − 00

4XX

AC BUS 2

2XP

115VAC

214XP

24 − 32 − 00

216XP

24 − 50 − 00

212XP

115VAC 24 − 34 − 00 24 − 24 − 00

GLC− 1 9XU1

BTC− 1 11XU1

EPLC 3XG

GLC−APU 3XS

1XX

BTC−2 11XU2

GLC−2 9XU2

FUEL PUMPS 28 − 21 − 00 GCU−1 1XU1

GEN 1

4000XU

GCU−APU 1XS

2XX

14XX

GLC−EMERG 2XE

12XX 24 − 50 − 00

APU GEN

8XS

GPCU 1XG

EXTERNAL POWER RECEPTACLE

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT CSM/G 1XE

8XE

N_MM_244200_0_AAM0_01_00

AES

FIGURE 24-42-00-11200-A SHEET 1 AC Ground Service Network - Block Diagram

24-42-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

24 − 67 − 00 601PP 602PP

24 − 61 − 00

DC SVCE BUS

6PP 28VDC

3PX

1PX 24 − 32 − 00

1PU2 TR2

24 − 32 − 00

24 − 50 − 00

24 − 50 − 00

AC BUS 1

1XP

24 − 25 − 00

24 − 25 − 00

4XX

AC BUS 2

2XP

115VAC

16XX

24 − 32 − 00

216XP

24 − 50 − 00

212XP

214XP

115VAC 24 − 34 − 00 24 − 24 − 00

GLC−1 9XU1

BTC−1 11XU1

BTC−2 11XU2

EPLC 3XG

GLC−APU 3XS

GLC−2 9XU2

FUEL PUMPS 28 − 21 − 00 GCU−1 1XU1

GEN 1

4000XU

GCU−APU 1XS

1XX

14XX

2XX

12XX

GLC−EMERG 2XE

24 − 50 − 00 APU GEN

8XS

GPCU 1XG

EXTERNAL POWER RECEPTACLE

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT CSM/G 1XE

8XE

N_MM_244200_0_AAQ0_01_00

AES

FIGURE 24-42-00-11200-E SHEET 1 AC Ground Service Network - Block Diagram

24-42-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU FR16 FR20

121AL

841

A B A 123VU

2000VU

C

C

12XX 14XX

B MAINT BUS ON

5XX

N_MM_244200_0_ACM0_01_00

AES

FIGURE 24-42-00-12400-A SHEET 1 AC Ground Service Bus - Component Location

24-42-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

FR16 FR20

D 121AL

841

A B 2000VU

A 123VU

C

20XX

12XX

14XX

C

B D MAINT BUS ON

16XX

18XX 5XX N_MM_244200_0_ACQ0_01_00

AES

FIGURE 24-42-00-12400-D SHEET 1 AC Ground Service Bus - Component Location

24-42-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

GPCU

1XG 12XX

2PU2

1XX

2XX

EXT PWR

GEN2

EPC

GLC − 2

BTC2

10XN

2XP 115VAC BUS 2

12XN

14XX

14P4

4XX

7XX

5XX

MAINT BUS ON

6XX

F

AC

6XG

202XP − C 115VAC BUS 2 PWR/SVCE/CTL

PR 2PP 28VDC BUS 2 5PU2

214XP

216XP − C

212XP

AC GND/FLT NETWORK

+ 28V

** On A/C 003-004

N_MM_244200_0_AEM0_01_00

AES

FIGURE 24-42-00-15000-A SHEET 1 AC Ground Service Bus Control - Schematic Diagram

24-42-00 PB001

Page 9 May 01/12 Revision n˚: 40

AES

EXT PXR

GEN2

1XX

2XX

EPC

GLC − 2

BTC2

12XX

2PU2

10XN

2XP 115VAC BUS 2

12XN

14XX

14P4

7XX

4XX

17XX

FIGURE 24-42-00-15000-E SHEET 1 AC Ground Service Bus Control - Schematic Diagram 5XX

MAINT BUS ON

23XN

16XX

6XX

F

22XN

OFF

18XX

24-42-00 PB001

AC

6XG

2PP 28VDC BUS 2

PR

1XA

+ 28V

501PP 28VDC SVCE BUS

AC GND/FLT NETWORK

202XP − C 115VAC BUS 2 PWR/SVCE/CTL

GPCU

1XG

5PU2

214XP

216XP − C

212XP

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C 005-099

N_MM_244200_0_AEQ0_01_00

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC GROUND SERVICE BUS CONTROL - MAINTENANCE PRACTICES ** On A/C ALL Task 24-42-00-861-001-A Energize the Ground Service Network from the External Power 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE 98A24403000000 B.

QTY 1 CABLE HOLDING STRAP

DESIGNATION

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL C.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-51-000-001-A

Removal of the External Power Receptacle

24-41-51-400-001-A

Installation of the External Power Receptacle

3.

Job Set-up Subtask 24-42-00-010-050-A A.

Get Access (1)

Open the door 121AL to have access to the external power receptacle and panel 108VU.

Subtask 24-42-00-480-050-A B.

Aircraft Maintenance Configuration (1)

Make sure that the CABLE HOLDING STRAP (98A24403000000) with the snap hook is in position on the feeder of the ground power unit.

(2)

Attach the feeder to the support with the snap hook.

Subtask 24-42-00-420-050-A CAUTION :

AES

MAKE SURE THAT THE CABLE STRAP SUPPORTS ALL THE WEIGHT OF THE CABLE WHEN THE CONNECTOR IS CONNECTED. THIS PREVENTS DAMAGE TO THE EXTERNAL POWER RECEPTACLE.

24-42-00 PB201

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Connect the connector NOTE :

(1)

4.

Examine the external power supply-cable and the external power receptacle before you do the connection. If you find corrosion or damage, or if the pins are not aligned correctly, replace the external power receptacle (Ref. TASK 24-41-51-000-001-A) and (Ref. TASK 24-41-51-400-001-A).

Connect the connector of the ground power unit to the external power receptacle of the aircraft (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002A-02).

Procedure Subtask 24-42-00-861-054-A A.

Energize the ground service network (1)

On the ELEC panel 35VU, make sure that all pushbutton switches are released except BUS TIE and AC ESS FEED pushbutton switches.

(2)

Start the ground power unit (obey the special instructions of the ground power unit).

(3)

When the protection circuit operates correctly: . on the panel 108VU, the EXT PWR/NOT IN USE indicator light and EXT PWR/AVAIL caution light come on, . in the cockpit, on the ELEC panel 35VU, the AVAIL legend of the EXT PWR pushbutton switch comes on.

(4)

On the front circuit breaker panel 2000VU which is in the middle of the cabin ceiling at the level of the FWD passenger/crew door, put the MAINT BUS switch in the ON position. NOTE :

(5)

AES

The ground MECH/CALL horn which is in the nose gear well operates when the BAT 1 and/or BAT 2 pushbutton switch(es) on the ELEC panel 35VU is(are) pushed.

On the panel 108VU, the EXT PWR/NOT IN USE indicator light goes off. This shows that the power supply from the ground service network is correct.

24-42-00 PB201

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-42-00-862-001-A De-energize the Ground Service Network Supplied from the External Power 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL 3.

Job Set-up Subtask 24-42-00-869-058-A A.

4.

Not Applicable

Procedure Subtask 24-42-00-862-054-A A.

5.

De-energize the ground service network (1)

On the front circuit breaker panel 2000VU which is in the middle of the cabin ceiling at the level of the FWD passenger/crew door, put the MAINT BUS switch in the OFF position.

(2)

On the panel 108VU, the EXT PWR/NOT IN USE indicator light comes on. This shows that the ground service network is de-energized correctly.

Close-up Subtask 24-42-00-080-050-A A.

Obey the instructions given with the ground power and stop the ground power unit: . on the panel 35VU, the legends of all the pushbutton switches are off, . on the panel 108VU, all the lights are off.

Subtask 24-42-00-020-050-A B.

Put the aircraft back to its initial configuration. WARNING : DE-ENERGIZE THE ELECTRICAL POWER SUPPLY BEFORE YOU DISCONNECT THE CONNECTOR OF THE GROUND POWER UNIT. IF NOT DANGEROUS ARCING CAN OCCUR. (1)

Disconnect the connector of the ground power unit and release the snap hook from the support.

Subtask 24-42-00-410-052-A C.

Close Access (1)

AES

Close the access door 121AL.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-42-55-000-001-A Removal of the Contactors WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 12XX, 14XX 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE ** On A/C 005-099 24-42-58-000-001-A 25-11-41-000-001-A

DESIGNATION Removal of the AC Service Bus Contactor Module Removal of the Third Occupant Seat

(Ref. Fig. 24-42-55-991-00100-A - Contactors) (Ref. Fig. 24-42-55-991-00100-B - Contactors) 3.

Job Set-up ** On A/C ALL Subtask 24-42-55-010-050-A A.

AES

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

Remove the front panel of the AC power center 123VU.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

24-42-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-42-55-941-050-A B.

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Put WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

(3)

In . . . .

(4)

In the cockpit, put WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

Subtask 24-42-55-865-050-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

DESIGNATION ELEC/EXT PWR/LT CLT/NOT IN/USE

122VU 4.

FIN 6XG

LOCATION X30

Procedure

** On A/C 003-004 (Ref. Fig. 24-42-55-991-00100-A - Contactors) ** On A/C 005-099 (Ref. Fig. 24-42-55-991-00100-B - Contactors) ** On A/C 003-004 Subtask 24-42-55-020-050-A A.

Removal of the Contactor CAUTION :

(1)

Disconnect the electrical connector (10).

(2)

Put blanking caps on the disconnected electrical connector (10) and the electrical receptacle (9).

(3)

Loosen the captive screws (8). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (8) and the spring washers from the contactor (11).

Remove the contactor (11).

24-42-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-42-55-020-052-A CAUTION :

B.

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Removal of the Contactor Base NOTE :

The removal of the contactor base is necessary only if it is damaged.

(1)

Remove the nuts (7) and the washers (6).

(2)

Disconnect the cables (5) from the contactor base (1).

(3)

Remove the nuts (12) and the washers (13).

(4)

Remove the jumper (14) from the contactor base (1) and from the adjacent contactor base.

(5)

Remove the screws (4) and the washers (3).

(6)

Remove the contactor base (1).

** On A/C 005-099 Subtask 24-42-55-020-050-B A.

Removal of the Contactor CAUTION :

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

(1)

Disconnect the electrical connector (1).

(2)

Put blanking caps on the disconnected electrical connector (1) and the electrical receptacle.

(3)

Loosen the captive screws (2). NOTE :

(4)

Do not remove the captive screws (2) and the spring washers from the contactor (3).

Remove the contactor (3).

Subtask 24-42-55-020-052-B B.

Removal of the Module 20XX NOTE : (1)

AES

The removal of the module is necessary only if it is damaged.

Remove the module 20XX (Ref. TASK 24-42-58-000-001-A).

24-42-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

A 122VU

123VU

121VU

125VU

124VU

12XX

123VU 14XX

B A

B 14

13 1 CONTACTOR BASE

12

11 CONTACTOR

2 3 10 5

4

8 9 7

6

N_MM_244255_4_AAM0_01_00

AES

FIGURE 24-42-55-991-00100-A SHEET 1 Contactors

24-42-55 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A 122VU

123VU

121VU

125VU

124VU 123VU

20XX

12XX 14XX

B A

B 3

2

4

MODULE 20XX

CONTACTOR

1 N_MM_244255_4_AAP0_01_00

AES

FIGURE 24-42-55-991-00100-B SHEET 1 Contactors

24-42-55 PB401

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-42-55-400-001-A Installation of the Contactors WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 12XX, 14XX 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

WARNING NOTICE(S)

No specific

Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

No specific

Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

B.

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE ** On A/C 003-004

DESIGNATION

20-21-15-912-001-A

Tightening Torques for Electrical Component Fasteners

24-42-00-861-001-A

Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

** On A/C 005-099 24-42-58-400-001-A 25-11-41-000-001-A

Installation of the AC Service Bus Contactor Module Removal of the Third Occupant Seat

25-11-41-400-001-A

Installation of the Third Occupant Seat

(Ref. Fig. 24-42-55-991-00100-A - Contactors) (Ref. Fig. 24-42-55-991-00100-B - Contactors) 3.

Job Set-up ** On A/C ALL Subtask 24-42-55-860-050-A A.

Aircraft Maintenance Configuration (1)

AES

In the cockpit, make sure that the third occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

24-42-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

In the cockpit, in the L lower section of the panel 120VU, make sure that the access panel of the panel 123VU is removed.

(3)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

(5)

Make sure that the external power connector is not connected to the aircraft receptacle.

(6)

Make sure that a WARNING NOTICE(S) is in position on the access door 121AL to tell persons not to use the external power receptacle.

(7)

In the cockpit, on the overhead ELEC panel 35VU, make sure that these pushbutton switches are released: . BAT 1, BAT 2, . APU GEN, . GEN 1, GEN 2, . EXT PWR.

(8)

In the cockpit, make sure that a WARNING NOTICE(S) is in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(9)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

Subtask 24-42-55-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

DESIGNATION ELEC/EXT PWR/LT CLT/NOT IN/USE

122VU 4.

FIN 6XG

LOCATION X30

Procedure

** On A/C 003-004 (Ref. Fig. 24-42-55-991-00100-A - Contactors) ** On A/C 005-099 (Ref. Fig. 24-42-55-991-00100-B - Contactors) ** On A/C 003-004 Subtask 24-42-55-420-052-A A.

Installation of the Contactor Base CAUTION :

AES

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Install the contactor base (1) in correct position.

(2)

Install the washers (3) and the screws (4) and tighten them.

(3)

Make sure that the electrical cables (5) are clean and in correct condition.

24-42-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

Installation of the electrical cables (5). (a)

Install the washers (6) and the nuts (7).

(b)

TORQUE the nuts (7) to between 0.27 and 0.3 M.DAN (23.89 and 26.55 LBF.IN).

(5)

Install the jumpers (14) between the contactor base (1) and the adjacent base.

(6)

Install the washers (13) and the nuts (12) and tighten them (Ref. TASK 20-21-15-912-001-A).

Subtask 24-42-55-420-050-A B.

Installation of the contactor CAUTION :

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Install the contactor (11) on the 6 tapped barrels (2) of the contactor base (1).

(2)

TORQUE the captive screws (8) to between 13.28 and 15.93 LBF.IN (0.15 and 0.18 M.DAN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (10).

** On A/C 005-099 Subtask 24-42-55-420-052-B A.

Installation of the Module 20XX NOTE : (1)

The installation of a module is necessary only if it was removed.

Install the module 20XX (Ref. TASK 24-42-58-400-001-A).

Subtask 24-42-55-420-050-B B.

Installation of the Contactor CAUTION :

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Install the contactor (3) on the module 20XX (4).

(2)

TORQUE the captive screws (2) to between 13.28 and 15.93 LBF.IN (0.15 and 0.18 M.DAN).

(3)

Remove the blanking caps from the electrical connector (1) and the electrical receptacle.

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (1) to the contactor (3).

** On A/C ALL Subtask 24-42-55-865-052-A C.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

122VU

AES

DESIGNATION ELEC/EXT PWR/LT CLT/NOT IN/USE

FIN 6XG

LOCATION X30

24-42-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-42-55-710-050-A D.

5.

Operational Test (1)

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

(2)

On the FWD attendant panel 120RH: . Push the MAIN ON membrane switch. . Make sure that all the entrance and cabin lights come on.

Close-up Subtask 24-42-55-862-050-A A.

Put the aircraft back to its initial configuration. (1)

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

Subtask 24-42-55-410-050-A B.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the front panel of the panel 123VU.

(3)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

24-42-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

MODULE - REMOVAL/INSTALLATION ** On A/C 005-099 Task 24-42-58-000-001-A Removal of the AC Service Bus Contactor Module WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL C.

Referenced Information

REFERENCE 24-32-55-000-001-A

DESIGNATION Removal of the TR 1 and TR 2 Contactors and the TR 2/AC Service Bus Normal Supply Contactor

24-42-55-000-001-A 24-51-55-000-001-A

Removal of the Contactors Removal of the AC Service Bus Normal Supply Contactor

25-11-41-000-001-A

Removal of the Third Occupant Seat

(Ref. Fig. 24-42-58-991-00100-A - AC Service Bus Contactor Module) 3.

Job Set-up Subtask 24-42-58-010-050-A A.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

Remove the front panel of the AC power center 123VU in the cockpit.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-42-58-860-050-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft external power receptacle.

(2)

Put a WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft external power receptacle.

24-42-58 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4.

(3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2 APU GEN GEN 1, GEN 2 EXT PWR.

(4)

In the cockpit, put a WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these panels: . 21VU (EMER ELEC PWR section) . 25VU (APU section) . 35VU (ELEC).

Procedure (Ref. Fig. 24-42-58-991-00100-A - AC Service Bus Contactor Module) Subtask 24-42-58-020-051-A A.

Removal of the Contactors Installed on the Contactor Module 20XX (1)

Remove the contactors 12XX and 14XX (Ref. TASK 24-42-55-000-001-A).

(2)

Remove the contactor 14PU (Ref. TASK 24-32-55-000-001-A).

(3)

Remove the contactor 12XN (Ref. TASK 24-51-55-000-001-A).

Subtask 24-42-58-020-053-A B.

Removal of the Electrical Components CAUTION :

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Remove the screws (5) and the washers (6).

(2)

Disconnect the electrical cables (7).

Subtask 24-42-58-020-050-A C.

AES

Removal of the Contactor Module 20XX (1)

Remove the protective plugs (2) from the screws (3).

(2)

Remove the screws (3).

(3)

Remove and discard the locking washers (4).

(4)

Remove the contactor module (1).

24-42-58 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A 123VU

122VU

121VU 20XX 124VU

125VU

123VU

B A

B 1

5

6

7

MODULE 20XX

5

6

7 2

3

4 N_MM_244258_4_AAM0_01_00

AES

FIGURE 24-42-58-991-00100-A SHEET 1 AC Service Bus Contactor Module

24-42-58 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-42-58-400-001-A Installation of the AC Service Bus Contactor Module WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL C.

Expendable Parts

FIG.ITEM 4

DESIGNATION

IPC-CSN 24-42-08-04-020

locking washers D.

Referenced Information

REFERENCE 24-32-55-400-001-A

DESIGNATION Installation of the TR 1 and TR 2 Contactors and the TR 2/AC Service Bus Normal Supply Contactor

24-42-55-400-001-A 24-51-55-400-001-A

Installation of the Contactors Installation of the AC Service Bus Normal Supply Contactor

25-11-41-000-001-A 25-11-41-400-001-A

Removal of the Third Occupant Seat Installation of the Third Occupant Seat

(Ref. Fig. 24-42-58-991-00100-A - AC Service Bus Contactor Module) 3.

Job Set-up Subtask 24-42-58-010-051-A A.

AES

Get Access (1)

Make sure that the Third Occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(2)

Make sure that the front panel of the AC power center 123VU is removed in the cockpit.

(3)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

24-42-58 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-42-58-860-051-A B.

4.

Aircraft Maintenance Configuration (1)

Make sure that the external power connector is not connected to the aircraft external power receptacle.

(2)

Make sure that the WARNING NOTICE(S) is in position at the access door 121AL to tell persons not to connect the external power connector to the aircraft external power receptacle.

(3)

In . . . .

(4)

In the cockpit, make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the pushbutton switches on these panels: . 21VU (EMER ELEC PWR section) . 25VU (APU section) . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2 APU GEN GEN 1, GEN 2 EXT PWR.

Procedure (Ref. Fig. 24-42-58-991-00100-A - AC Service Bus Contactor Module) Subtask 24-42-58-420-050-A A.

Installation of the Contactor Module 20XX (1)

Put the contactor module (1) on its support.

(2)

Install the new (IPC-CSN 24-42-08-04) locking washers (4) and the screws (3).

(3)

Tighten the screws (3).

(4)

Install the protective plugs (2) on the screws (3).

Subtask 24-42-58-420-051-A B.

Installation of the Electrical Components CAUTION :

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Put the electrical cables (7) in position on the contactor module (1).

(2)

Install the washers (6) and the screws (5).

(3)

Tighten the screws (5).

Subtask 24-42-58-420-052-A C.

AES

Installation of the Contactors on the Module 20XX (1)

Install the contactors 12XX and 14XX (Ref. TASK 24-42-55-400-001-A).

(2)

Install the contactor 14PU (Ref. TASK 24-32-55-400-001-A).

(3)

Install the contactor 12XN (Ref. TASK 24-51-55-400-001-A).

24-42-58 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-42-58-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the front panel of the AC power center 123VU.

(3)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

24-42-58 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC GROUND SERVICE BUS CONTROL - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General (Ref. Fig. 24-43-00-11200-B - Ground Service Network-General) DC ground flight distribution network can be supplied: . either normally from the aircraft network, . or directly by the ground power unit upstream of the external power contactor. This is via the TR2 in ground service configuration, without energizing the whole aircraft network.

AES

24-43-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location

** On A/C 003-004 (Ref. Fig. 24-43-00-12500-A - DC Ground Service Bus Control-Component Location) ** On A/C 005-099 (Ref. Fig. 24-43-00-12500-B - DC Ground Service Bus Control - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS ATA REF. DOOR

** On A/C ALL 3PX

AES

CNTOR-DC SVCE BUS GND SPLY

120VU

212

24-43-00 PB001

24-43-55

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description (Ref. Fig. 24-43-00-11200-B - Ground Service Network-General) The DC ground/flight network comprises the following 28 VDC service busses: . 601PP, . 602PP. These sub-busbars are supplied directly from the ground power unit through the contactor 14XX via the TR2. The contactor 14XX is controlled by the MAINT BUS control switch 5XX located on panel 2000VU.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Operation/Control and Indicating The operation is described in ATA Ref. 24-42-00. NOTE :

AES

In case of TR2 overheat, the supply of the ground service network is cut off.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

24−35−00 301PP

11PB APU START 49−42−00

5KA

10KA

CSM/G CONTROL UNIT

6XE

6KA 1PB2

702PP

5PB2 12PB2

BAT2 2PB2

4PB2 6PB2 1PB1

701PP

12PB1

BCL−1

BAT1

24−62−00

DC BUS 1

1PP

1PC1

28VDC

2PB1

6PB1

BAT BUS

5PR

501PP

8PR

SHUNT 3PB2 1PR

703PP

5PB1 4PB1

502PP

704PP

BCL−2

24−61−00

2PR

3PP

601PP 602PP

SHUNT 3PB1 DC BUS 2

1PC2

28VDC

2PP

7PN

28VDC

DC SVCE BUS

8PN

6PP 28VDC

3PX 24−62−00

5PU1

24−28−00 5PU2

1PX 1PU1 TR1

1PU2 TR2

2PU1

AC BUS 1

1XP

24−25−00

24−25−00

AC BUS 2

115VAC

2XP 115VAC

24−22−00 24−22−00 GPCU 1GX

EXTERNAL POWER RECEPTACLE

2PU2

14PU

24−50−00

1XX

14XX

N_MM_244300_0_AAL0_01_00

AES

FIGURE 24-43-00-11200-B SHEET 1 Ground Service Network-General

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

FR16 FR20

841

120VU

A 122VU

121VU

124VU

125VU

123VU

A 3PX

B

B

N_MM_244300_0_ACM0_01_00

AES

FIGURE 24-43-00-12500-A SHEET 1 DC Ground Service Bus Control-Component Location

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

FR16 FR20

841

120VU

A 122VU

121VU

124VU

125VU

123VU

A 3PX

B 14PN

B

N_MM_244300_0_ACP0_01_00

AES

FIGURE 24-43-00-12500-B SHEET 1 DC Ground Service Bus Control - Component Location

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-43-55-000-001-A Removal of the DC Service Bus Ground Supply Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 3PX 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 25-11-41-000-001-A

DESIGNATION Removal of the Third Occupant Seat

(Ref. Fig. 24-43-55-991-00100-A - Contactor) (Ref. Fig. 24-43-55-991-00100-B - Contactor) 3.

Job Set-up Subtask 24-43-55-010-050-A A.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

In the cockpit, remove the front panel on the bottom right side of the panel 120VU.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-43-55-860-050-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Put WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the EXT PWR receptacle.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

(4)

In the cockpit, put WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

Subtask 24-43-55-865-050-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

122VU

DESIGNATION ELEC/DC SVCE/BUS/ON TR2

5PX

U30

124VU

SVCE/601PP/602PP/SPLY

1PX

BB01

4.

FIN

LOCATION

Procedure

** On A/C 003-004 (Ref. Fig. 24-43-55-991-00100-A - Contactor) ** On A/C 005-099 (Ref. Fig. 24-43-55-991-00100-B - Contactor) ** On A/C ALL Subtask 24-43-55-020-050-A A.

Removal of the Contactor CAUTION :

(1)

Disconnect the electrical connector (4).

(2)

Put blanking caps on the disconnected electrical connector (4) and the electrical receptacle.

(3)

Loosen the captive screws (2). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (2) and the spring washers from the contactor (3).

Remove the contactor (3).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

A

122VU

121VU

125VU

124VU 123VU

A

3PX

B

2

B CONTACTOR BASE

5

CONTACTOR

6

4

7

3

2

N_MM_244355_4_AAM0_01_00

AES

FIGURE 24-43-55-991-00100-A SHEET 1 Contactor

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A 122VU

121VU

125VU

124VU 123VU

A 3PX

14PN

2

B

5

B

MODULE 14PN

CONTACTOR 4

3

2

N_MM_244355_4_AAP0_01_00

AES

FIGURE 24-43-55-991-00100-B SHEET 1 Contactor

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-43-55-400-001-A Installation of the DC Service Bus Ground Supply Contactor FIN 3PX 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific

B.

QTY AR WARNING NOTICE(S)

Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

DESIGNATION

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

24-42-00-862-001-A

De-energize the Ground Service Network Supplied from the External Power

25-11-41-000-001-A

Removal of the Third Occupant Seat

25-11-41-400-001-A

Installation of the Third Occupant Seat

(Ref. Fig. 24-43-55-991-00100-A - Contactor) (Ref. Fig. 24-43-55-991-00100-B - Contactor) 3.

Job Set-up Subtask 24-43-55-860-051-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the access platform is in position at the access door 121AL.

(2)

Make sure that the access door 121AL is open.

(3)

Make sure that the external power connector is not connected to the aircraft receptacle.

(4)

Make sure that on the access door 121AL there is a WARNING NOTICE(S) to tell persons not to connect the external power connector.

(5)

In . . . .

(6)

Make sure that there is a WARNING NOTICE(S) in the cockpit to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR),

the cockpit, on the overhead panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL .

35VU (ELEC).

(7)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

(8)

In the cockpit, make sure that the third occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(9)

In the cockpit, make sure that the front panel is removed from the bottom right side of the panel 120VU.

Subtask 24-43-55-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

122VU

PANEL

DESIGNATION ELEC/DC SVCE/BUS/ON TR2

5PX

U30

124VU

SVCE/601PP/602PP/SPLY

1PX

BB01

4.

FIN

LOCATION

Procedure

** On A/C 003-004 (Ref. Fig. 24-43-55-991-00100-A - Contactor) ** On A/C 005-099 (Ref. Fig. 24-43-55-991-00100-B - Contactor) ** On A/C 003-004 Subtask 24-43-55-420-050-A A.

Installation of the Contactor CAUTION :

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Put the contactor (3) in position on the two tapped barrels (6) of the contactor base (5).

(2)

TORQUE the two captive screws (2) to between 23.9 and 26.55 LBF.IN (0.27 and 0.30 M.DAN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the connector (4) to the contactor (3).

** On A/C 005-099 Subtask 24-43-55-420-050-B A.

Installation of the Contactor CAUTION :

AES

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Install the contactor (3) on the module 14PN (5).

(2)

TORQUE the captive screws (2) to between 23.9 and 26.55 LBF.IN (0.27 and 0.30 M.DAN).

(3)

Remove the blanking caps from the electrical connector (4) and the electrical receptacle.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (4) to the contactor (3).

** On A/C ALL Subtask 24-43-55-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

122VU

PANEL

DESIGNATION ELEC/DC SVCE/BUS/ON TR2

5PX

FIN U30

LOCATION

124VU

SVCE/601PP/602PP/SPLY

1PX

BB01

Subtask 24-43-55-710-050-A C.

5.

Test of the Ground Service Network (1)

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

(2)

On the overhead panel 25VU, put the INT LT/DOME switch in the BRT position. On the panel 453VU, the L dome light comes on.

Close-up Subtask 24-43-55-862-050-A A.

De-energize the ground service network (Ref. TASK 24-42-00-862-001-A).

Subtask 24-43-55-410-050-A B.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the front panel on the bottom right side of the panel 120VU.

(3)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC ELECTRICAL LOAD DISTRIBUTION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The AC electrical power distribution on board is carried out in several steps corresponding to: . Power distribution: . from the different sources towards the main AC busbars located in panel 120VU, . then, from the main AC busbars, either directly towards important consumers (pumps, galleys...), or towards the associated distribution sub-busbars located in the circuit breaker panels. . Power distribution from sub-busbars: . the distribution from these sub-busbars towards the different AC consumers. This chapter deals only with power distribution. The referenced figure gives a schematic summary of the whole AC distribution on board:

** On A/C 003-004 (Ref. Fig. 24-50-00-11200-F - AC Electrical Load Distribution - General) ** On A/C 005-099 (Ref. Fig. 24-50-00-11200-U - AC Electrical Load Distribution - General) This can be broken down as follows: . the AC main distribution connected to 115 VAC busses 1XP and 2XP (Ref. 24-51-00, P. Block 1), . the AC essential distribution connected to 115 VAC ESS bus 4XP and 115 VAC SHED bus 8XP (Ref. 24-52-00, P. Block 1).

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location A.

Component Location ** On A/C 003-004 (Ref. Fig. 24-50-00-12700-B - AC Power Distribution Contactors - Component Location) ** On A/C 005-099 (Ref. Fig. 24-50-00-12700-C - AC Power Distribution Contactors - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS ATA REF. DOOR

** On A/C ALL 5XH

A/XFMR-115/26VAC, ESS

125

24-52-51

12XN 15XN1

CNTOR-AC SVCE BUS NORM SPLY A/XFMR-115/26VAC, 1

120VU 120VU

212 212

24-51-55 24-51-51

15XN2

A/XFMR-115/26VAC, 2

120VU

212

24-51-51

49VU

OVERHEAD C/B PNL

210

93-00-00

105VU 106VU

POWER CENTER-BATTERY POWER CENTER-AC/DC EMERGENCY

126 125

93-00-00 93-00-00

121VU

REAR C/B PNL

212

93-00-00

122VU

REAR C/B PNL

212

93-00-00

123VU 124VU 125VU

POWER CENTER-AC POWER CENTER-DC REAR C/B PNL

212 212 212

93-00-00 93-00-00 93-00-00

2000VU

C/B PNL 2000VU

220

93-00-00

2001VU

C/B PNL 2001VU

260

93-00-00

8XH CNTOR-AC SHED ESS BUS ** On A/C 005-099

106VU

125

24-52-55

21XN1 21XN2 22XN

CNTOR-115 VAC BUS 1 SPLY CNTOR-115 VAC BUS 2 SPLY P/BSW-ELEC/COMMERCIAL

120VU 120VU 35VU

212 212 210

24-51-00 24-51-00 24-51-00

27XN

CONTACTOR

120VU

212

24-51-55

The panel 123VU mainly contains: . the channel 1 line and transfer contactor and 115 VAC bus 1 (1XP), . the channel 2 line and transfer contactor and 115 VAC bus 2 (2XP), . the APU generator line contactor (APU GLC) and the external power contactor. The panel 106VU mainly contains contactors related to the electrical emergency power. ** On A/C 003-004 The panel 105VU comprises the static inverter contactor. ** On A/C 005-099 The panel 105VU comprises the static inverter contactor.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL B.

Spare Fuses ** On A/C 003-004 (Ref. Fig. 24-50-00-12700-B - AC Power Distribution Contactors - Component Location) Panel 120VU also contains a set of 3 spare fuses of different amperage for replacement of the fuses given below if defective: . 350A spare fuse to replace fuses 4PB11 and 4PB21 (Ref. 24-30-00, P. Block 1), . 400A spare fuse to replace fuse 6KA (Ref. 49-42-00, P. Block 1), . 80A spare fuse to replace fuse 20PC1 (Ref. 24-30-00, P. Block 1). ** On A/C 005-099 (Ref. Fig. 24-50-00-12700-C - AC Power Distribution Contactors - Component Location)

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description The distribution busbars are supplied according to various configurations depending on: . the procedures applied by the crew members in the different failure configurations, . the availability of the various power sources. The possible configurations are: . normal flight configuration:

.

.

** On A/C 003-004 (Ref. Fig. 24-50-00-14600-C - Normal Flight Configuration for the Whole Network (AC/DC)) ** On A/C 005-099 (Ref. Fig. 24-50-00-14600-H - Normal Flight Configuration for the Whole Network (AC/DC)) emergency configuration corresponding to the loss of the two main generators with the auxiliary generator not available: ** On A/C 003-004 (Ref. Fig. 24-50-00-14700-C - Emergency Configuration for the Whole Network (AC/DC)) ** On A/C 005-099 (Ref. Fig. 24-50-00-14700-G - Emergency Configuration for the Whole Network (AC/DC)) smoke configuration: ** On A/C 003-004 (Ref. Fig. 24-50-00-14800-C - Smoke Configuration for the Whole Network (AC/DC)) ** On A/C 005-099 (Ref. Fig. 24-50-00-14800-G - Smoke Configuration for the Whole Network (AC/DC))

NOTE :

AES

These configurations are dealt with in their respective ATA chapter.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Interface A.

Circuit Breakers Panels (1) Overhead circuit breaker panel 49VU (a) General The overhead circuit breaker panel 49VU is accessible to the Captain and First Officer. The circuit breakers are connected either to an AC or a DC power source. 1

AC Power Supply . 115 VAC . 26 VAC

2

DC Power Supply . 28 VDC

(b) Description (Ref. Fig. 24-50-00-16200-B - Provision for C/B(s) Installation on the Panel 49VU) A simplified drawing shows the provision for circuit breakers installation on the panel 49VU. On the aircraft, the Functional Item Number (FIN) is shown on the rear side of the VU panel. (2) Circuit Breaker Panel 105VU (a) General The circuit breaker panel 105VU (Battery Power Center) is located in the avionics compartment next to access door 822. You must open the access door from the panel 105VU. The circuit breakers are connected to BAT 1(2) power source. 1

BAT power supply . 28 VDC

(b) Description (Ref. Fig. 24-50-00-16400-A - Provision for C/B(s) Installation on the Panels 105VU and 106VU) A simplified drawing shows the provision for circuit breakers installation on the panel 105VU. On the aircraft, the FIN is marked below the head of each circuit breaker. (3) Circuit Breaker Panel 106VU (a) General The circuit breaker panel 106VU (AC/DC emergency power center) is located in the avionics compartment next to access door 812. You must open the access door from the panel 106VU. The circuit breakers are connected either to an AC or a DC power source. 1

AC Power Supply . 115 VAC . 26 VAC

2

DC Power Supply . 28 VDC

(b) Description (Ref. Fig. 24-50-00-16400-A - Provision for C/B(s) Installation on the Panels 105VU and 106VU) A simplified drawing shows the provision for circuit breakers installation on the panel 106VU. On the aircraft, the labels and the FINs are marked behind the access door of the panel 106VU opposite the circuit breaker panel.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 (4) Rear Circuit Breaker Panel 120VU It comprises the following panels: . 121VU, . 122VU, . 123VU, . 124VU, . 125VU. (a) General These circuit breaker panels are located on the rear panel 120VU. The circuit breakers are connected either to an AC or a DC power source. 1

AC Power Supply . 115 VAC . 26 VAC

2

DC Power Supply . 28 VDC

(b) Description (Ref. Fig. 24-50-00-16700-A - Provision for C/B(s) Installation on the Panel 121VU) (Ref. Fig. 24-50-00-16800-A - Provision for C/B(s) Installation on the Panel 122VU) (Ref. Fig. 24-50-00-16900-A - Provision for C/B(s) Installation on the Panel 123VU) (Ref. Fig. 24-50-00-17000-A - Provision for C/B(s) Installation on the Panels 124VU and 125VU) Simplified drawings show the provision for circuit breakers installation on panels 121VU, 122VU, 123VU, 124VU and 125VU. On the aircraft, the FIN is marked below the head of each circuit breaker. NOTE :

Panels 121VU/122VU and their placards are not customized. Therefore, there can be placards for circuit breakers that are not installed on a given aircraft.

** On A/C 005-099 (5) Rear Circuit Breaker Panel 120VU It comprises the following panels: . 121VU, . 122VU, . 123VU, . 124VU, . 125VU. (a) General These circuit breaker panels are located on the rear panel 120VU. The circuit breakers are connected either to an AC or a DC power source. 1

AC Power Supply . 115 VAC . 26 VAC

2

DC Power Supply . 28 VDC

(b) Description (Ref. Fig. 24-50-00-16700-A - Provision for C/B(s) Installation on the Panel 121VU) (Ref. Fig. 24-50-00-16800-A - Provision for C/B(s) Installation on the Panel 122VU) (Ref. Fig. 24-50-00-16900-A - Provision for C/B(s) Installation on the Panel 123VU)

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (Ref. Fig. 24-50-00-17000-A - Provision for C/B(s) Installation on the Panels 124VU and 125VU) Simplified drawings show the provision for circuit breakers installation on panels 121VU, 122VU, 123VU, 124VU and 125VU. On the aircraft, the FIN is marked below the head of each circuit breaker. ** On A/C ALL (6) Circuit Breaker Panel 2000VU (a) General The front circuit breaker panel 2000VU faces the FWD passenger/crew door (841) and is located in the center of the cabin ceiling. The circuit breakers are connected to either an AC or a DC power source. 1

AC Power Supply . 115 VAC . 26 VAC

2

DC Power Supply . 28 VDC

(b) Description (Ref. Fig. 24-50-00-17200-A - Provision for C/B(s) Installation on the Panel 2000VU) A simplified drawing shows the provision for circuit breakers installation on the panel 2000VU. (7) Circuit Breaker Panel 2001VU (a) General The circuit breaker panel 2001VU faces the aft passenger door (842) and is located in the center of the cabin ceiling. The circuit breakers are connected to either an AC or a DC power source. 1

AC Power Supply . 115 VAC . 26 VAC

2

DC Power Supply . 28 VDC

(b) Description (Ref. Fig. 24-50-00-17400-A - Provision for C/B(s) Installation on the Panel 2001VU) A simplified drawing shows the provision for circuit breakers installation on the panel 2001VU. B.

Configuration of Circuit Breakers (1) Black head circuit breaker This type of circuit breaker does not have an auxiliary contact. It is standard. (2) Green head circuit breaker This type of circuit breaker holds an auxiliary contact connected to SDAC when it is tripped. (3) Circuit breaker with a red threaded bush For safety reasons, to avoid that the crew resets it in flight, the C/B is guarded. If it is necessary to open it, the red threaded bush must first be removed, unscrewed with a standard wrench. (4) Circuit breaker with a yellow collar Some circuit breakers have a yellow collar to help the crew to find them more easily on the circuit breaker panel. (5) For clipped circuit breaker, there are two types of collars, metallic or plastic, secured by lockwire, (Ref. ESPM 20-46-10).

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Circuit Breakers Data Tables by Circuit PANEL

49VU

DESIGNATION FLIGHT CONTROLS/SLT FLP/POS/IND 1

FIN

LOCATION

1CN

B12

122VU

ANTI ICE/PROBES/1/TAT

1DA1

Z12

122VU

ANTI ICE/PROBES/2/TAT

1DA2

Y15

49VU

ANTI ICE/RAIN/RPLNT/CAPT

1DB1

D01

ANTI ICE/RAIN/RPLNT/F/O

1DB2

W11

123VU

ANTI ICE/L/WHSLD

1DG1

AF10

123VU

ANTI ICE/R/WHSLD

1DG2

AF03

49VU

ANTI ICE/WING/MONG

1DL

C01

122VU

ANTI ICE/ENG/1

1DN1

X10

122VU

** On A/C ALL EMB SB 30-1037 FOR A/C 003-004 122VU ** On A/C ALL

ANTI ICE/ENG/2

1DN2

W10

122VU ** On A/C 003-004

DUMMY CB

1DR

X15

2000VU ** On A/C 005-099

WASTE WIP-DRAINMAST-FWD

1DU

B06

2000VU ** On A/C ALL

WASTE WIP-DRAINMAST-FWD

1DU

B08

2000VU

POT/WASTE WIP HEATER LINE

1DW

A02

121VU

ENG1/REV/LOCK

1EG1

N44

121VU

ENG2/REV/LOCK

1EG2

N45

121VU

ENGINE/ENG1/OIL/QTY

1EN1

N39

121VU

ENGINE/ENG2/OIL/QTY

1EN2

N41

121VU

ENGINE/ENG1 AND 2/EVMU

1EV

R44

49VU

L/G/LGCIU/SYS1/NORM

1GA

C09

121VU

HYDRAULIC/BRAKING AND STEERING/SYS1/CTL

1GG

M34

1GS

L32

HYDRAULIC/BRK FAN/WHEELS/1 AND 2

1GS

L32

121VU 121VU

DUMMY CB HYDRAULIC/BRK/TEMP/DET/UNIT

1GV 1GW

M31 M37

49VU

AIR COND/FLOW/CTL &/IND1

1HB

D07

122VU

AIR COND/RECIRC FAN/L/SPLY

1HG

X18

** On A/C ALL PRE SB 32-1235 FOR A/C 003-008 121VU

HYDRAULIC/BRK FAN/WHEELS/1 AND 2

** On A/C POST SB 32-1235 FOR A/C 003-008 121VU ** On A/C ALL

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL 122VU

DESIGNATION AIR COND/PACK TEMP/CTL SYS1/1/115VAC

FIN

LOCATION

1HH

X22

122VU

AIR COND/ZONE TEMP CTL/115VAC/SYS1

1HK

V17

49VU

AIR COND/CAB/PRESS/CTL1

1HL

D09

123VU

AVNCS VENT/BLOWER/FAN

1HQ

AD10

49VU

OXYGEN/CREW/OXY/SPLY

1HT

HA01

122VU

AIR BLEED/X FEED VALVE/NORM

1HV

Z20

49VU

AIR COND/RAM/AIR/INLET

1HZ

D10

49VU

ENGINE/1 AND 2/IGN/SYS A

1JH

A03

49VU

ENGINE/1/HP FUEL SOV

1KC1

A01

49VU

ENGINE/2/HP FUEL SOV

1KC2

A02

121VU

APU/ECB/SPLY

1KD

L41

121VU

APU/OIL/HTR/SPLY

1KT

K41

122VU

LIGHTING/EXT LT/NAV1/AND LOGO/LT

1LA

T03

122VU

LIGHTING/LANDING LT/L/SPLY

1LB

T04

122VU

LIGHTING/EXT LT/RWY TURN OFF/L

1LC1

W06

122VU

LIGHTING/EXT LT/RWY TURN OFF/R

1LC2

W05

49VU

LIGHTING/EMER LT/CKPT/DOME

1LE

H08

49VU

LIGHTING/ICE AND STBY/COMP/LIGHT

1LF

H04

2001VU 2000VU 122VU

LIGHT-SEC 19 AIR CONDTN COMPT OUTLET LIGHTING/WHL WELL/LTG/OUT

1LJ 1LK 1LL

E07 G08 X07

2000VU 122VU

LAV LIGHT LIGHTING/EXT LT/TAXI AND TAKE OFF/TAXI

1LQ 1LR

J01 W08

LIGHTING/AVNCS COMPT/DOME

1LS

Z07

2000VU 122VU

LIGHT-CARGO COMPT-FWD LIGHTING/EXT LT/BEACON/UPPER

1LU 1LV

J06 U06

2000VU 122VU

PASSENGER READING LIGHT LIGHTING/EXT LT/WING/AND ENG SCAN/R

1LW 1LX

G01 W03

LIGHTING/LOGO/R

1LY

V02

LIGHT-ATTND WORK WATER SYS LAV-FWD-HOT WATER-A

1LZ 1MA 1MB

J03 D06 F02

FWD GALLEY/FEEDER C

1MC

AE10

FWD GALLEY/FEEDER C

1MC

AE10

122VU

122VU 2000VU 2000VU 2000VU ** On A/C 005-099 123VU ** On A/C 003-004 123VU

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C ALL 2000VU 122VU

DESIGNATION VACU CLEANER SKT-CAB-Z222 DOORS/CARGO

FIN

LOCATION

1ME 1MJ

F07 T12

2001VU WATER SYS-DRAIN ** On A/C 006-099 EMB SB 11-1047 FOR A/C 006-008 EMB SB 25-1326 FOR A/C 006-008

1MP

B05

122VU DOORS CKPT LOCK ** On A/C 003-005 EMB SB 11-1047 FOR A/C 003-005 EMB SB 25-1305 FOR A/C 003-005

1MQ

T13

122VU ** On A/C ALL

COCKPIT DOOR LOCK SYSTEM

1MQ

T13

122VU

COCKPIT SEATS/SEAT CTL/CAPT

1MS1

U11

122VU

COCKPIT SEATS/SEAT CTL/F/O

1MS2

U14

LAV SHAVER SOCKET

1MT

B01

106VU

EMER/SHED/CNTOR/SPLY

1PH

C07

125VU

101PP/SPLY

1PN1

CD01

124VU

202PP/SPLY

1PN2

BG01

122VU

ELEC/REFLNG/ON/BAT

1PR

U28

124VU

SVCE/601PP/602PP/SPLY

1PX

BB01

121VU

FUEL/L WING TK/PUMP1 SPLY

1QA

N23

121VU

APU/FUEL/BLOW OFF/CTL

1QC

K39

121VU

FUEL/X FEED/VALVE/MOT2

1QE

M24

121VU

APU/FUEL/LP VALVE/CTL

1QF

M40

49VU

FUEL/LP VALVE/MOT1/ENG1

1QG

A08

121VU

FUEL/HI/LVL/SPLY

1QJ

L25

49VU

FUEL/XFR VALVE1/WING/L

1QP

A10

49VU

FUEL/FQI/CHAN/1

1QT

A13

121VU

FUEL/RFL/DFL/XFR/DEFUEL/VALVE

1QU

L23

1RE1

HA14

1RE2

L13

** On A/C 003-004 2001VU ** On A/C ALL

** On A/C 003-005 EMB SB 23-1049 FOR A/C 003-005 EMB SB 23-1365 FOR A/C 003-005 EMB SB 23-1387 FOR A/C 003-005 49VU COM HF1 ** On A/C 003-005 EMB SB 23-1387 FOR A/C 003-005 121VU

AES

COM NAV/HF2

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C ALL

DESIGNATION

FIN

LOCATION

49VU

NAV/ADF/1

1RP1

H14

121VU

COM NAV/ADF/2

1RP2

K02

121VU

COM NAV/RAD ALTM/1

1SA1

K11

121VU

COM NAV/RAD ALTM/2

1SA2

K12

49VU

NAV/DME/1

1SD1

G14

121VU

COM NAV/DME/2

1SD2

K06

121VU

ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A

1WE1

Q43

121VU

ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A

1WE2

Q41

121VU

APU/FIRE/EXTIG/SQUIB/A

1WF

L38

121VU

APU/FIRE AND OVHT/DET/LOOP A

1WG

L43

LAV FWD-OCCUPIED LIGHTING/EMER LT/CABIN

1WJ 1WL

F01 H05

OXYGEN/PASSENGER/CTL AND WARN

1WR

HA02

AIR COND/CARGO/FIRE/EXTIG

1WX

T19

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

106VU

AC/SHED/ESS BUS/CNTOR/CTL

1XH

C04

123VU

BUS 1/101XP/SPLY

1XN1

AD11

123VU

BUS 2/202XP/SPLY

1XN2

AD02

122VU

ELEC/IDG1/DISC

1XT

T24

123VU

TR2/SVCE/BUS 2/SPLY

1XX

AB08

121VU

FLIGHT CONTROLS/SLT FLP/POS/IND2

2CN

P16

49VU

ANTI ICE/PROBES/PHC/1

2DA1

D03

122VU

ANTI ICE/PROBES/PHC/2

2DA2

Y12

122VU

ANTI ICE/PROBES/PHC/3

2DA3

Y16

49VU

ANTI ICE/WING/CTL

2DL

C02

POT/WASTE WIP HEATER CTL

2DW

A01

121VU

ENGINE/ENG1/OIL/PRESS/AND REV SNSR/CHAN A

2EN1

N40

121VU

ENGINE/ENG2/OIL/PRESS/AND REV SNSR/CHAN A

2EN2

N42

121VU

HYDRAULIC/LGCIU/SYS2

2GA

Q35

2000VU 49VU 49VU ** On A/C 005-099 122VU ** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

2000VU

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL 121VU

DESIGNATION HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY

FIN

LOCATION

2GG

M33

2GS

L35

HYDRAULIC/BRK FAN/WHEELS/3 AND 4

2GS

L35

49VU

AIR BLEED/ENG 1/MONG

2HA1

D11

122VU

AIR BLEED/ENG 2/MONG

2HA2

Z22

122VU

AIR COND/FLOW/CTL AND IND/2

2HB

V21

122VU

AIR COND/RECIRC FAN/L/CTL

2HG

X20

122VU

AIR COND/PACK TEMP CTL SYS2/1/115VAC

2HH

Y18

122VU

AIR COND/ZONE TEMP CTL/115VAC/SYS2

2HK

V18

122VU

AIR COND/CAB PRESS/CTL/2

2HL

Y22

123VU

AVNCS VENT/EXTC/FAN

2HQ

AE02

49VU

AIR BLEED/X FEED/VALVE/BAT

2HV

D13

121VU

ENGINE/IGN/ENG1/SYS A BAT

2JH1

P39

121VU

ENGINE/IGN/ENG2/SYS A BAT

2JH2

P40

121VU

APU/APU/CTL

2KD

L42

49VU

ENGINE/1/FADEC A/AND EIU 1

2KS1

A04

49VU

ENGINE/2/FADEC A/AND EIU 2

2KS2

A05

122VU

LIGHTING/EXT LT/NAV2/AND LOGO/LT

2LA

T02

122VU

LIGHTING/LANDING LT/R/SPLY

2LB

T06

122VU

LIGHTING/FLOOD/CTR INST/PNL

2LE

Z04

2001VU 122VU

LIGHT-APU LIGHTING/WHL WELL/LTG/DOME

2LJ 2LL

E08 X08

LIGHTING/EXT LT/TAXI AND TAKE OFF/CTL

2LR

W09

2000VU 2000VU 122VU

LIGHT-CARGO COMPT-AFT PASSENGER READING LIGHT LIGHTING/LOGO/L

2LU 2LW 2LY

J07 G02 V03

2001VU 123VU

LAV AFT-HOT WATER FWD GALLEY/FEEDER D

2MB 2MC

C02 AD04

122VU

ELEC/REFLNG/NORM

2PR

S27

123VU

TR1/SPLY

2PU1

AB10

123VU

TR2/214XP/SPLY

2PU2

AB04

121VU

FUEL/R WING TK/PUMP1 SPLY

2QA

Q23

** On A/C ALL PRE SB 32-1235 FOR A/C 003-008 121VU

HYDRAULIC/BRK FAN/WHEELS/3 AND 4

** On A/C POST SB 32-1235 FOR A/C 003-008 121VU ** On A/C ALL

122VU

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

49VU

PANEL

DESIGNATION APU/FUEL/BLOW OFF/PUMP

2QC

FIN B14

LOCATION

49VU

FUEL/X FEED/VALVE/MOT1

2QE

A12

121VU

APU/FUEL/LP VALVE/SPLY

2QF

M39

49VU

FUEL/LP VALVE/MOT1/ENG2

2QG

A09

49VU

FUEL/XFR VALVE1/WING/R

2QP

A11

121VU

FUEL/FQI/CHAN/2

2QT

M27

121VU

FUEL/RFL/DFL/SPLY

2QU

L24

DUMMY CB

2RB

L06

COM NAV/ACARS/MU

2RB

L06

49VU

COM/VHF/1

2RC1

G09

121VU

COM NAV/VHF/2

2RC2

L04

121VU

COM NAV/VHF/3

2RC3

L05

49VU

COM/RMP/1

2RG1

G10

121VU

COM NAV/RMP/2

2RG2

L02

121VU

COM NAV/RMP/3

2RG3

L03

49VU

COM/CVR/SPLY

2RK

E14

49VU

NAV/VOR/1

2RS1

G13

121VU

COM NAV/VOR/2

2RS2

K08

2000VU ** On A/C 006-099

PRAM

2RX

E01

2000VU ** On A/C 003-004

CABIN COMMUNICATION SYSTEMS PRAM 2RX

E01

2000VU ** On A/C ALL

PRAM

2RX

E01

121VU

CFDS/CFDIU/SPLY

2TW

J18

121VU

EIS/HORN/SPLY

2WC

P09

121VU

ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B

2WE1

Q44

121VU

ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B

2WE2

Q42

121VU

APU/FIRE/EXTIG/SQUIB/B

2WF

L39

121VU

APU/FIRE AND OVHT/DET/LOOP B

2WG

L44

49VU

LIGHTING/EMER LT/CABIN

2WL

H06

49VU

OXYGEN/PASSENGER/CTL AND WARN

2WR

HA03

121VU

EIS/SDAC/2/SPLY

2WV

Q06

121VU

EIS/FWC2/SPLY

2WW

Q07

** On A/C 005-099 121VU ** On A/C 003-004 121VU ** On A/C ALL

** On A/C 005-005

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

121VU

PANEL

DESIGNATION EIS/GPWS/28VDC

2WZ

FIN P06

LOCATION

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

123VU

GND/PWR/PROT

2XG

AB07

106VU

AC ESS BUS/MONG/SPLY

2XH

C05

122VU

ELEC/IDG2/DISC

2XT

T25

122VU

ELEC/GCU/1

2XU1

T26

122VU

ELEC/GCU/2

2XU2

T27

123VU

SVCE/BUS 2/212XP SPLY

2XX

AB05

49VU

ANTI ICE/PROBES/PITOT/1

3DA1

D02

122VU

ANTI ICE/PROBES/2/PITOT

3DA2

Y14

122VU

ANTI ICE/PROBES/3/PITOT

3DA3

Z16

121VU

HYDRAULIC/BRAKING AND STEERING/SYS2/CTL

3GG

M35

3GS

M32

HYDRAULIC/BRK/FAN/CTL

3GS

M32

49VU

AIR BLEED/ENG 1/CTL

3HA1

D12

122VU

AIR BLEED/ENG 2/CTL

3HA2

Z23

122VU

AIR COND/FLOW/MIXER/FLAP

3HB

V22

122VU

AIR COND/RECIRC FAN/R/SPLY

3HG

W18

122VU

AIR COND/PACK TEMP/CTL SYS1/1/28VDC

3HH

X21

122VU

AIR COND/ZONE TEMP CTL/28VDC/SYS1

3HK

V19

122VU

AIR COND/CAB PRESS/CTL/MAN

3HL

Y23

122VU

AIR COND/AVNCS/VENT/MONG

3HQ

Y17

121VU

ENGINE/IGN/ENG1/SYS B

3JH1

P41

121VU

ENGINE/IGN/ENG2/SYS B

3JH2

P42

122VU

LIGHTING/LANDING LT/L/CTL

3LB

T05

122VU

LIGHTING/CKPT/DOME

3LE

Y06

122VU

LIGHTING/INSTL LT/OVHD/PNL

3LF

Y03

122VU

LIGHTING/EXT LT/TAXI AND TAKE OFF/TO

3LR

W07

LIGHT-LDG-AREA PASSENGER READING LIGHT AFT GALLEY/FEEDER A

3LU 3LW 3MC

J08 G03 AF04

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

** On A/C ALL PRE SB 32-1235 FOR A/C 003-008 121VU

HYDRAULIC/BRK/FAN/CTL

** On A/C POST SB 32-1235 FOR A/C 003-008 121VU ** On A/C ALL

2000VU 2000VU 123VU 122VU

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL

DESIGNATION

FIN

LOCATION

125VU

103PP/SPLY

3PN1

CE01

124VU

204PP/SPLY

3PN2

BF01

122VU

ELEC/TR1/MONG

3PU1

X25

122VU

ELEC/TR2/MONG

3PU2

X26

121VU

FUEL/PUMPS/1/L CTL AND R IND

3QA

R23

121VU

APU/FUEL/PUMP/CTL

3QC

M38

121VU

FUEL/LP VALVE/MOT2/ENG1

3QG

M25

121VU

FUEL/XFR VALVE2/WING/L

3QP

M22

121VU

DATA/LOADER/SPLY

3TD

J16

121VU ** On A/C 004-004

ATSU 1

3TX1

L16

121VU ** On A/C ALL

ATSU 1

3TX1

L16

121VU

APU/FIRE/LP VALVE/STBY

3WF

M41

122VU

LIGHTING/CABIN/EMER/LT

3WL

V07

49VU

OXYGEN/PASSENGER/CTL AND WARN

3WR

HA04

49VU

SDAC/1/SPLY

3WV

F04

49VU

FWS/FWC1/SPLY

3WW

F01

121VU

EIS/GPWS/115VAC

3WZ

P07

123VU

BUS 1/103XP/SPLY

3XN1

AB11

123VU

BUS 2/204XP/SPLY

3XN2

AB02

122VU

ELEC/AC PWR/SVCE/CTL

3XX

V29

49VU

ANTI ICE/PROBES/AOA/1

4DA1

D04

122VU

ANTI ICE/PROBES/2/AOA

4DA2

Y13

122VU

ANTI ICE/PROBES/3/AOA

4DA3

Z15

122VU

ANTI ICE/WIPER/CAPT

4DB1

X12

122VU

ANTI ICE/F/O/WIPER

4DB2

W12

122VU

ANTI ICE/WINDOWS/L

4DG1

X14

122VU

ANTI ICE/WINDOWS/R

4DG2

W14

49VU

NAV PROBES/ADIRU1/115VAC

4FP1

F06

ADIRS/ADIRU/2/115VAC

4FP2

N07

ADIRS/ADIRU/2/115VAC

4FP2

N06

ADIRS/ADIRU/3/115VAC

4FP3

N06

ADIRS/ADIRU/3/115VAC

4FP3

N05

** On A/C 005-099

** On A/C 003-004 121VU ** On A/C 005-099 121VU ** On A/C 003-004 121VU ** On A/C 005-099 121VU

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C 003-004 121VU

DESIGNATION

FIN

LOCATION

CLOCK/STBY/SPLY

4FS

N03

CLOCK/STBY/SPLY

4FS

N02

121VU

HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY

4GG

M36

122VU

AIR COND/PACK TEMP CTL SYS2/1/28VDC

4HH

Y19

122VU

AIR COND/ZONE TEMP CTL/28VDC/SYS2

4HK

V20

121VU

ENGINE/ENG1/FADEC B/AND EIU 1

4KS1

R41

121VU

ENGINE/ENG2/FADEC B

4KS2

Q40

122VU

LIGHTING/LANDING LT/R/CTL

4LB

T07

122VU

LIGHTING/FLOOD/F/O/SIDE

4LE

Z06

122VU

LIGHTING/INSTL LT/MAIN INST/PNL AND/PED

4LF

Y04

PASSENGER READING LIGHT ESS TR/SPLY

4LW 4PE

G04 C01

122VU

ELEC/RFL/SPLY/LOGIC

4PR

U29

125VU

TR1/CNTOR/SPLY

4PU1

CF01

124VU

TR2/CNTOR/SPLY

4PU2

BC01

121VU

FUEL/PUMPS/1/R CTL AND L IND

4QA

R28

121VU

FUEL/LP VALVE/MOT2/ENG2

4QG

M26

121VU

FUEL/XFR VALVE2/WING/R

4QP

M23

49VU

COM/CVR/CTL

4RK

E13

COM/AUDIO/ACP/CAPT

4RN

G06

ACP CAPT SELCAL INT 1 AUDIO AVNCS

4RN

G06

COM NAV/TCAS

4SG

K10

COM NAV/TCAS

4SG

K10

AIDS/DMU

4TV

K15

121VU

APU/FIRE/LP VALVE/NORM

4WF

M42

49VU

OXYGEN/PASSENGER/ACTUATION

4WR

HA05

121VU

EIS/F/O/LOUD/SPKR

4WW

P08

** On A/C 005-099 121VU ** On A/C ALL

2000VU 106VU

** On A/C 003-004 49VU ** On A/C 005-099 49VU ** On A/C 003-004 121VU ** On A/C 005-099 121VU ** On A/C 003-004 121VU ** On A/C ALL

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

106VU

PANEL

DESIGNATION AC ESS/BUS NORM/CNTOR/CTL

4XC

FIN B03

LOCATION

122VU

ELEC/EXT PWR/LT CLT/AVAIL

4XG

X31

106VU

26VAC/ESS BUS/SPLY

4XH

B06

123VU

SVCE/BUS 2/214XP SPLY

4XX

AA05

49VU

AUTO FLT/FAC1/28VDC

5CC1

B04

121VU

AUTO FLT/FAC2/28VDC

5CC2

M19

49VU

FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1

5CV

B06

122VU

ANTI ICE/PROBES/1/STATIC

5DA1

Z13

122VU

ANTI ICE/PROBES/2/STATIC

5DA2

Y11

122VU

ANTI ICE/PROBES/3/STATIC

5DA3

Z14

122VU

ANTI ICE/WHC/1

5DG1

X13

122VU

ANTI ICE/WHC/2

5DG2

W13

49VU

NAV/STBY/HORIZON

5FN

F12

49VU

NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1

F07

ADIRS/ADIRU/2/26VAC AND AOA

5FP2

N09

ADIRS/ADIRU/2/26VAC AND AOA

5FP2

N08

ADIRS/ADIRU/3/26VAC AND AOA

5FP3

N08

ADIRS/ADIRU/3/26VAC AND AOA

5FP3

N07

49VU

AIR COND/AVNCS VENT/CTL

5HQ

D05

122VU

AIR COND/LAV/GALLEY VENT CTL/EXTRACT FAN/CTL

5HU

U21

122VU

LIGHTING/FLOOD/CAPT/SIDE

5LE

Z05

122VU

LIGHTING/INSTL LT/GLARE/SHLD

5LF

Y05

122VU

LIGHTING/EXT LT/BEACON/LOWER

5LV

U03

2000VU 122VU

PASSENGER READING LIGHT LIGHTING/EXT LT/WING/AND ENG SCAN/L

5LW 5LX

G05 W02

2001VU 105VU

VACU CLEANER SKT-CAB-Z261 ELEC/HOT BUS/701PP SPLY

5ME 5PB1

F06 D01

105VU

ELEC/HOT BUS/702PP SPLY

5PB2

D02

106VU

ESS TR/CNTOR/CTL

5PE

C02

122VU

ELEC/DC/SVCE/BUS

5PN

X24

122VU

ELEC/DC SVCE/BUS/ON TR2

5PX

U30

** On A/C 003-004 121VU ** On A/C 005-099 121VU ** On A/C 003-004 121VU ** On A/C 005-099 121VU ** On A/C ALL

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C 003-004 49VU

DESIGNATION

FIN

LOCATION

COM/AUDIO/ACP/F/O

5RN

G07

ACP F/O BITE INT 2 AUDIO 3/5 OCCPNT

5RN

G07

49VU

COM NAV/ATC/1

5SH1

G11

121VU

COM NAV/ATC/2

5SH2

K07

121VU

COM NAV/RADAR/1

5SQ1

K13

121VU

AIDS & RCDR/FDIMU

5TV

K15

121VU

ATSU 1/SWTG

5TX1

L15

ATSU 1/SWTG

5TX1

L15

49VU

OXYGEN/PASSENGER/ACTUATION

5WR

HA06

49VU

SDAC/1/26VAC SYNC/AC ESS BUS

5WV

F02

49VU

CAPT/LOUD/SPKR

5WW

F10

106VU

AC ESS BUS/STBY/CNTOR/CTL

5XC

B08

106VU

AC ESS BUS/EMER/CNTOR/CTL

5XE

B07

123VU

BUS 1/131XP-A/SPLY

5XN1

AB12

123VU

BUS 2/231XP-A/SPLY

5XN2

AB01

122VU

ELEC/GEN1/OFF/BTC1 SPLY

5XU

T28

49VU

FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1

6CV

B07

105VU

ADIRS/ADIRU1/28VDC

6FP1

C02

ADIRS/ADIRU/2/28VDC

6FP2

N05

ADIRS/ADIRU/2/28VDC

6FP2

N04

ADIRS/ADIRU/3/28VDC

6FP3

N04

ADIRS/ADIRU/3/28VDC

6FP3

N03

49VU

CLOCK/NORM/SPLY

6FS

F11

49VU

AIR COND/AVNCS VENT/CTL

6HQ

D06

122VU

AIR COND/LAV/GALLEY VENT CTL/EXTRACT FAN/SPLY

6HU

U19

PASSENGER READING LIGHT

6LW

G06

** On A/C 005-099 49VU ** On A/C ALL

** On A/C 005-099

** On A/C 004-004 121VU ** On A/C ALL

** On A/C 003-004 121VU ** On A/C 005-099 121VU ** On A/C 003-004 121VU ** On A/C 005-099 121VU ** On A/C ALL

2000VU

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

124VU

PANEL

DESIGNATION 206PP/208PP/SPLY

6PN

FIN BE01

LOCATION

121VU

COM NAV/ACP/THIRD/OCCPNT

6RN

M02

121VU

PTR/SPLY

6TW

J21

DCDU 1 DCDU 2

6TX1 6TX2

L17 L18

49VU

OXYGEN/PASSENGER/ACTUATION

6WR

HA07

49VU

SDAC/2/26VAC SYNC/AC ESS BUS

6WV

F03

ESS NTWK AUTO ALTN

6XC

V24

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

122VU

ELEC/EXT PWR/LT CLT/NOT IN/USE

6XG

X30

49VU

ELEC/AC BUS/8XP/MONG

6XH

H11

122VU

ELEC/APU/GCU

6XS

Y25

121VU

FLIGHT CONTROLS/SLT/CTL/SYS2

7CV

R21

122VU

ELEC/GALLEY/CNTOR

7MC

S28

122VU

ELEC/TR1/FAULT/DC BUS TIE/CONFIG

7PC1

W29

122VU

ELEC/TR2/FAULT/DC BUS TIE/CONFIG

7PC2

W30

124VU

DC SVCE/602PP/SPLY

7PN

BD01

121VU

FUEL/L WING TK/PUMP2 SPLY

7QA

N26

121VU

COM NAV/ACP/AVNCS/COMPT

7RN

M03

121VU

RCDR/DFDR

7TU

K16

49VU

ENGINE/1/FIRE DET/LOOP A

7WD1

A06

121VU

ENGINE/ENG2/FIRE DET/LOOP A

7WD2

Q39

49VU

OXYGEN/PASSENGER/ACTUATION

7WR

HA08

121VU

EIS/SDAC/1/BUS2/26VAC SYNC AC

7WV

Q03

ELEC/GALLEY/GND/FLT/LOGIC

7XA

S24

ELEC/GALY & CAB/GND/FLT/LOGIC

7XA

S24

105VU

ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

122VU

ELEC/GPCU

7XG

Y24

123VU

BUS 1/110XP/SPLY

7XN1

AF11

123VU

BUS 2/210XP/SPLY

7XN2

AF02

** On A/C 005-099 121VU 121VU ** On A/C ALL

** On A/C 004-099 EMB SB 24-1120 FOR A/C 004-008 POST SB 24-1120 FOR A/C 003-003 122VU ** On A/C ALL

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

121VU

PANEL

DESIGNATION FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2

8CV

FIN Q21

LOCATION

49VU

NAV PROBES/ADIRU3/PWR/SWTG

8FP

F09

105VU

ELEC/BAT BUS/REF/BCL1

8PB1

G01

105VU

ELEC/BAT BUS/REF/BCL2

8PB2

J02

121VU

FUEL/R WING TK/PUMP2 SPLY

8QA

Q26

121VU

FUEL/FQI/CHANNEL/1 AND 2

8QT

L26

121VU

COM NAV/SELCAL

8RN

M04

FDIU

8TU

K17

121VU

CFDS/CFDIU/BACK/UP

8TW

J17

121VU

ENGINE/ENG1/FIRE DET/LOOP B

8WD1

Q38

49VU

ENGINE/2/FIRE DET/LOOP B

8WD2

A07

121VU

EIS/SDAC/2/BUS2/26VAC SYNC AC

8WV

Q02

ELEC/GALLEY/FAULT/LT CTL

8XA

S25

122VU

ELEC/GALY & CAB/FAULT/LT CTL

8XA

S25

122VU

ELEC/COML/SHED/SYS2

8XN

V28

122VU

ELEC/GEN2/OFF/BTC2 SPLY

8XU

T31

49VU

AUTO FLT/FCU/1

9CA1

B05

121VU

AUTO FLT/FCU/2

9CA2

M21

122VU

FLIGHT CONTROLS/WTB/SLT/SYS1

9CV

S06

ADIRS/ADIRU/3PWR/SWTG

9FP

N10

ADIRS/ADIRU/3PWR/SWTG

9FP

N09

LAV AFT&MID HOT WATER ELEC/BAT REF/BCL1

9MB 9PB1

B03 F01

105VU

ELEC/BAT REF/BCL2

9PB2

F02

122VU

ELEC/CNTOR/DC/BUS/TIE1

9PC

W25

ELEC/DC SHED BUS/CNTR

9PN

U26

FUEL/PUMPS/2/L CTL AND R IND

9QA

R24

** On A/C 003-004 121VU ** On A/C ALL

** On A/C 003-004 122VU ** On A/C 005-099

** On A/C ALL

** On A/C 003-004 121VU ** On A/C 005-099 121VU ** On A/C ALL 2001VU 105VU

** On A/C 005-099 122VU ** On A/C ALL 121VU

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C 003-004 49VU

DESIGNATION

FIN

LOCATION

COM/AUDIO/FLT/INTPH

9RN

G08

INT 1 + 2

9RN

G08

121VU

RCDR/ACCLRM

9TU

K18

121VU

CFDS/TEST PLUG/1

9TW

J19

121VU

EIS/SDAC/1/BUS1/26VAC SYNC AC

9WV

Q04

122VU

ELEC/EMER GEN AUTO/2

9XE

Z26

ELEC/COML/SHED/SYS1

9XN

V26

49VU

AUTO FLT/FMGC/1

10CA1

B02

121VU

AUTO FLT/FMGC/2

10CA2

M17

122VU

FLIGHT CONTROLS/WTB/FLP/SYS1

10CV

S07

ADIRS/ADIRU/2PWR/SHED

10FP

N11

ADIRS/ADIRU/2PWR/SHED

10FP

N10

122VU

LIGHTING/WING/STROBE

10LV

V05

121VU

FUEL/PUMPS/2/R CTL AND L IND

10QA

R29

121VU

CFDS/TEST PLUG/2

10TW

J20

49VU

EIS/DMC1/SPLY

10WT1

E11

121VU

EIS/DMC2/SPLY

10WT2

Q08

121VU

EIS/DMC3/SPLY

10WT3

Q09

121VU

EIS/SDAC/2/BUS1/26VAC SYNC AC

10WV

Q05

106VU

AC ESS BUS/EMER/STBY/CNTOR/SPLY

10XE

C06

123VU

BUS 2/212XP/SPLY

10XN

AD03

49VU

AUTO FLT/MCDU/1

11CA1

B01

121VU

AUTO FLT/MCDU/2

11CA2

N20

121VU 121VU

DUMMY CB FLIGHT CONTROLS/WTB/SLT/SYS2

11CA3 11CV

N21 P19

122VU

ANTI ICE/PROBES/P2/T2/ENG1

11DA1

Z10

122VU

ANTI ICE/PROBES/P2/T2/ENG2

11DA2

Y10

2001VU 122VU

WASTE WIP DRAINMAST AFT AIR COND/RECIRC FAN/R/CTL

11DU 11HG

E01 W20

122VU

LIGHTING/AVNCS COMPT/OUT/28VDC

11LS

Z08

125VU

BAT BUS/301PP/SPLY

11PB

CC01

** On A/C 005-099 49VU ** On A/C ALL

** On A/C 005-099 122VU ** On A/C ALL

** On A/C 003-004 121VU ** On A/C 005-099 121VU ** On A/C ALL

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C 005-099 124VU

DESIGNATION

FIN

LOCATION

SHED BUS 210PP/212PP/SPLY

11PN

BA01

L WING TK/PUMP 1/STBY SPLY

11QA

AD12

LAVATORY AFT-OCCUPIED LIGHTING/EMER LT/CABIN

11WJ 11WL.

B04 H05

49VU

AIR COND/SDCU/CHAN1

11WQ

C06

49VU

EIS/PFD CAPT/SPLY

11WT1

E03

121VU

EIS/PFD/F/O

11WT2

R03

122VU

ELEC/EMER GEN AUTO/1

11XE

Z25

122VU

ELEC/EXT PWR/CTL

11XG

X29

121VU

FLIGHT CONTROLS/WTB/FLP/SYS2

12CV

P20

49VU

NAV/VOR/DME/RMI

12FN

F13

122VU

LIGHTING/AVNCS COMPT/OUT/115VAC

12LS

Z09

123VU

AFT GALLEY/FEEDER B

12MC

AD09

105VU

ELEC/HOT BUS/701PP SPLY

12PB1

E01

105VU

ELEC/HOT BUS/702PP SPLY

12PB2

E02

123VU

R WING TK/PUMP 1/STBY SPLY

12QA

AE12

49VU

LIGHTING/EMER LT/CABIN

12WL.

H06

122VU

AIR COND/SDCU/CHAN2

12WQ

T18

49VU

EIS/ND CAPT/SPLY

12WT1

E01

121VU

EIS/ND/F/O

12WT2

R04

49VU

SDAC/1 AND 2/28VDC/ESS BUS

12WV

F05

105VU

ELEC/STAT INV/BUS 901XP/SPLY

12XB

H02

122VU

ELEC/EXT PWR/COCKPIT/AVAIL/LT

12XG

X28

121VU

AUTO FLT/STICK/LOCK

13CA

N16

121VU

EIS/SLIDES/ARM AND WARN/GND

13WN

P10

49VU

EIS/ECAM DU/UPPER/SPLY

13WT1

E05

121VU

EIS/ECAM DU/LOWER/SPLY

13WT2

R11

49VU

ELEC/LT/CTL

13XG

H10

121VU

AUTO FLT/RUDDER/ARTF/FEEL

14CA

N17

49VU

AUTO FLT/FAC1/26VAC

14CC1

B03

121VU

AUTO FLT/FAC2/26VAC

14CC2

M18

121VU 123VU

DUMMY CB AFT GALLEY/FEEDER E

14FN 14MC

K04 AF09

122VU

ELEC/CNTOR/DC BUS/TIE 1/FAULT

14PC

U24

AIDS & RCDR/QAR

14TU

K17

** On A/C ALL 123VU 2001VU 49VU

** On A/C 005-099 121VU

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C ALL

DESIGNATION

FIN

LOCATION

49VU

EIS/DMC3/STBY/SPLY

14WT1

E10

121VU

EIS/SDAC1 AND 2/BUS1/28VDC

14WV

P04

105VU

ELEC/STAT INV/CNTOR/CTL

14XB

G02

122VU

ELEC/GEN1/OFF/BTC2 SPLY

14XU

T30

121VU

AUTO FLT/RUDDER/TRIM/IND

15CC

M20

49VU

FLIGHT CONTROLS/ELAC1/NORM/SPLY

15CE1

B11

121VU

FLIGHT CONTROLS/ELAC2/NORM/SPLY

15CE2

R20

2001VU ** On A/C 005-099

POT WIP-SVCE-PNL

15DV

D01

2001VU

POT/WASTE WIP SVCE PNL

15DV

D01

AC ESS/BUS/EMER/CNTOR/SPLY

15PC

C08

DOORS/CKPT/VIDEO/SPLY

15RA

T16

121VU

EIS/SLIDES/ARM AND WARN/FLT

15WN

P11

49VU

EIS/ECAM/CTL/PNL

15WT

E12

122VU

ELEC/GEN2/OFF/BTC1 SPLY

15XU

T29

105VU

FLT CTL/ELAC1/STBY SPLY

16CE1

A01

105VU

FLIGHT CONTROLS/ELAC2/STBY SPLY

16CE2

A02

49VU

NAV/STBY/ALTM

16FN

F14

123VU

FWD GALLEY/FEEDER F

16MC

AC10

49VU

EIS/RLY/BOX/CAPT

17WT1

E08

121VU

EIS/RLY/BOX/F/O

17WT2

R07

122VU

ELEC/AC/BUS1/CTL

17XN1

V25

122VU

ELEC/BUS/2XP/CTL

17XN2

V27

122VU

ELEC/DC BUS/TIE2//APU/START

18PC

W31

121VU

FLIGHT CONTROLS/THS ACTR/MOT1

19CE1

Q16

49VU

FLIGHT CONTROLS/THS/ACTR/MOT2

19CE2

B09

121VU

FLIGHT CONTROLS/THS ACTR/MOT3

19CE3

Q17

49VU

FLIGHT CONTROLS/FCDC1/SPLY

20CE1

B10

121VU

FLIGHT CONTROLS/FCDC2/SPLY

20CE2

Q20

PES-VIDEO-CONTROL-MAIN

20MH

C01

** On A/C 003-004

** On A/C ALL 106VU

** On A/C ALL EMB SB 23-1205 FOR A/C 003-005 EMB SB 23-1277 FOR A/C 003-008 122VU ** On A/C ALL

** On A/C 006-099 2000VU

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C 005-005 2000VU ** On A/C ALL

DESIGNATION

FIN

LOCATION

PES-VIDEO-CONTROL-MAIN

20MH

C01

49VU

FLIGHT CONTROLS/SEC1/NORM/SPLY

21CE1

B08

121VU

FLIGHT CONTROLS/SEC2/SPLY

21CE2

Q18

121VU

FLIGHT CONTROLS/SEC3/SPLY

21CE3

Q19

122VU

AIR COND/PACK TEMP/CTL SYS1/2/115VAC

21HH

W22

2000VU ** On A/C 005-005

PES VIDEO-CTL

21MH

C01

2000VU

PES VIDEO CONTROL/VCC

21MH

C02

PES VIDEO CONTROL/VCC

21MH

C02

** On A/C 003-004

** On A/C 006-099 2000VU

** On A/C 003-004 006-099 2000VU ** On A/C 005-005

PES MUSIC-CTL

21MK

D01

2000VU ** On A/C ALL

PES MUSIC CTL

21MK

D01

49VU

EIS/DMC1/SWTG

21WT1

E09

121VU

EIS/DMC2/SWTG

21WT2

R08

49VU

EIS/DMC3/SWTG

21WT3

E07

105VU

FLT CTL/SEC1/STBY SPLY

22CE

B01

122VU

AIR COND/PACK TEMP CTL SYS2/2/115VAC

22HH

Y20

2000VU ** On A/C 006-099

PES VIDEO CABIN-LH

22MH

C02

2000VU ** On A/C 005-005

PES VIDEO CABIN LH

22MH

C03

2000VU ** On A/C 006-099

PES VIDEO CABIN LH

22MH

C03

2000VU ** On A/C ALL

PES MUSIC AFT

22MK

D04

49VU

EIS/PFD CAPT/SWTG

22WT1

E04

121VU

EIS/PFD/F/O/SWTG

22WT2

R05

23FN

J01

** On A/C 003-004

** On A/C 004-099 EMB SB 33-1057 FOR A/C 004-008 POST SB 33-1057 FOR A/C 003-003 105VU

AES

NAV/STBY/INST/BAT

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C ALL 122VU

DESIGNATION

FIN

LOCATION

AIR COND/PACK TEMP/CTL SYS1/2/28VDC

23HH

W21

2000VU ** On A/C 006-099

PES VIDEO CABIN-RH

23MH

C03

2000VU ** On A/C 005-005

PES-MUSIC-CABIN-LH

23MK

D02

2000VU ** On A/C ALL

PES-MUSIC-CABIN-LH

23MK

D02

49VU

EIS/ND CAPT/SWTG

23WT1

E02

121VU

EIS/ND/F/O/SWTG

23WT2

R06

123VU

EXT PWR/EGIU1/115VAC

23XG

AA07

123VU

APU GEN/EGIU2/115VAC

23XS

AA08

123VU

GEN1/EGIU1/115VAC

23XU1

AF12

123VU

GEN2/EGIU2/115VAC

23XU2

AF01

122VU

AIR COND/PACK TEMP CTL SYS2/2/28VDC

24HH

Y21

2000VU ** On A/C 006-099

PES VIDEO CABIN RH

24MH

C04

2000VU ** On A/C 005-005

PES VIDEO CABIN RH

24MH

C04

2000VU ** On A/C 006-099

PES-MUSIC-CABIN-RH

24MK

D03

2000VU ** On A/C ALL

PES-MUSIC-CABIN-RH

24MK

D03

49VU

EIS/ECAM DU/UPPER/SWTG

24WT1

E06

121VU

EIS/ECAM DU/LOWER/SWTG

24WT2

R10

122VU

ELEC/GEN1/EGIU1/28VDC

24XU1

Z30

122VU

GEN2/EGIU2/28VDC

24XU2

Y30

2000VU

PES VIDEO CABIN RH/AFT

25MH

C05

2000VU ** On A/C ALL

PES MUSIC AFT

25MK

D05

LIGHTING/ANN LT SPLY/XFMR/BUS 1

26LP

X04

ELEC/AC SHED BUS/CNTOR

26XN

U25

ELEC/EXT PWR/EGIU1/28VDC

26XU1

Z31

** On A/C 003-004

** On A/C 005-005

** On A/C 006-099

122VU ** On A/C 005-099 122VU ** On A/C ALL 122VU

AES

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Page 25 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

122VU

PANEL

DESIGNATION APU GEN/EGIU2/28VDC

26XU2

FIN Y31

LOCATION

122VU

LIGHTING/ANN LT SPLY/XFMR/BUS 2

27LP

X05

106VU

EMER/GEN/REF

27WV

B05

122VU

LIGHTING/ANN LT SPLY/XFMR/STAT INV 28LP

X03

PES-VIDEO-INDICATOR

28MH

C07

SHED BUS/218XP/220XP SPLY

28XN

AC02

49VU

LIGHTING/XFMR/115V.5V/ESS BUS

29LP

H03

121VU

FUEL/CTR TK/PUMP1 SPLY

29QA

P23

122VU

AIR COND/AFT CARGO VENT/FAN

30HN

S22

122VU

LIGHTING/TST/BOARD/SPLY

30LP

X06

121VU

FUEL/CTR TK/PUMP2 SPLY

30QA

P26

121VU

APU/AUTO/EXTIG/GND/TEST

30WF

L40

AIR COND/AFT CARGO/VENT/CTL & MONG

31HN

C07

AIR COND/AFT CARGO/VENT & HTG/CTL 31HN & MONG

C07

FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND VACUUM TOILET SYSTEM/LAVATORY POWER A FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND VACUUM TOILET SYSTEM/VACUUM GEN

31QA

R25

32MG

A01

32QA

R26

33MG

A08

34MG

A04

35MG

A06

39MG

A03

42RT1

G12

COM NAV/MMR/2

42RT2

K09

COM NAV/MMR/2

42RT2

L07

** On A/C 006-099 2000VU ** On A/C 005-099 123VU ** On A/C ALL

** On A/C 003-004 49VU ** On A/C 005-099 49VU ** On A/C ALL 121VU 2001VU 121VU 2001VU 2001VU 2001VU 2001VU

VACUUM TOILET SYSTEM/LAVATORY POWER E VACUUM TOILET SYSTEM/VACUUM SYS VACUUM TOILET SYSTEM LAVATORY POWER D

** On A/C ALL EMB SB 34-1147 FOR A/C 003-004 49VU

NAV/MMR/1

** On A/C 003-004 EMB SB 34-1147 FOR A/C 003-004 121VU ** On A/C 005-099 121VU

AES

24-50-00 PB001

Page 26 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C ALL 121VU

DESIGNATION

FIN

LOCATION

EIS/SDAC1 AND 2/BUS2/28VDC

44WV

P03

45MG

A02

121VU

VACUUM TOILET SYSTEM LAVATORY POWER EIS/SDAC1 AND 2/DOOR/DET/AVNCS

46WV

P02

121VU

FUEL/CTR TK/AUTO/CTL

47QA

R27

121VU

EIS/SDAC1 AND 2/DOOR/DET/PAX

48WV

P05

PED PED

50HP 51HP

B06 B05

HYDRAULIC/LGCIU/SYS1/GRND SPLY

52GA

Q34

2000VU ** On A/C 005-005

PED

52HP

B04

2000VU ** On A/C 006-099

PED

53HP

B03

2000VU ** On A/C ALL

PED

53HP

B01

FUEL/SMOKE/CONFIG/PUMP CTL

55QA

A14

2001VU

** On A/C 005-099 2000VU 2000VU ** On A/C ALL 121VU ** On A/C 005-099

49VU

** On A/C POST SB 32-1346 FOR A/C 003-008 121VU

LGCIU/BAT SPLY/SYS1

58GA

R32

121VU

LGCIU/BAT SPLY/SYS2

59GA

R33

49VU

L/G/Y BRK/PRESS/IND

61GG

C10

106VU

DC BUS/1 AND 2/MONG

68WV

C03

121VU

HYDRAULIC/PARK BRK/CTL/NORM

70GG

N36

121VU

HYDRAULIC/PARK BRK/CTL/STBY

71GG

N37

RUDDER FTU

75CE

R16

49VU

LIGHTING/EMER LT/CABIN

79WL

H07

49VU

COM/CIDS/DIR 1 AND 2/ESS

150RH

G02

121VU

COM NAV/CIDS/DIR 1 AND 2/NORM

151RH

M05

49VU

COM/CIDS/DEU B/ESS

153RH

G03

49VU

COM/CIDS/DEU A ESS/LINE 1

154RH

G04

49VU

COM/CIDS/DEU A ESS/LINE 2

155RH

G05

121VU

COM NAV/CIDS/PROG AND TST PNL

161RH

M06

121VU

COM NAV/CIDS/DEU B/NORM

162RH

M07

** On A/C ALL

** On A/C 006-099 121VU ** On A/C ALL

AES

24-50-00 PB001

Page 27 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

121VU

PANEL

DESIGNATION COM NAV/CIDS/DEU A NORM/L FWD

163RH

FIN M08

LOCATION

121VU

COM NAV/CIDS/DEU A NORM/R FWD

164RH

M09

121VU

COM NAV/CIDS/DEU A NORM/L MID

165RH

M10

121VU

COM NAV/CIDS/DEU A NORM/R MID

166RH

M11

121VU

COM NAV/CIDS/DEU A NORM/L AFT

167RH

M12

121VU

COM NAV/CIDS/DEU A NORM/R AFT

168RH

M13

COM NAV/CIDS/FWD ATTND/PNL

170RH

M14

COM NAV/CIDS/FWD ATTND/PNL

170RH

Q14

PES PFIS RADVR PES/PFIS

188MH 189MH

C08 G09

CAB LIGHT PWR-WINDOW-FWD CAB LIGHT PWR-WINDOW-AFT CAB LIGHT PWR-WINDOW-AFT CAB LIGHT PWR-WINDOW-FWD CAB LIGHT PWR-CEILING-AFT CAB LIGHT PWR-CEILING-FWD CAB LIGHT PWR-CEILING-FWD CAB LIGHT PWR-CEILING-AFT LIGHT-CABIN ENTRY HYDRAULIC/G HYD/PUMP ENG1/CTL

300LG 301LG 302LG 303LG 304LG 305LG 306LG 307LG 308LG 1701GK

H01 H03 H04 H02 H07 H05 H06 H08 J02 R35

121VU

HYDRAULIC/G HYD/PUMP ENG1/MONG

1702GK

R34

49VU

HYD/FIRE VALVE/G/ENG1

1703GK

C13

121VU

HYDRAULIC/SOL VALVES/G/Y/PTU

1801GL

N34

1807GL

Q32

1807GL

Q32

1808GL

Q33

** On A/C 003-004 121VU ** On A/C 005-099 121VU ** On A/C 006-099 2000VU 2000VU ** On A/C ALL 2000VU 2000VU 2000VU 2000VU 2000VU 2000VU 2000VU 2000VU 2000VU 121VU

** On A/C POST SB 29-1115 FOR A/C 003-008 PRE SB 29-1126 FOR A/C 003-008 121VU

PTU INHIT/G SYS

** On A/C PRE SB 29-1115 FOR A/C 003-008 POST SB 29-1126 FOR A/C 003-008 121VU

PTU INHIT/G SYS

** On A/C POST SB 29-1115 FOR A/C 003-008 PRE SB 29-1126 FOR A/C 003-008 121VU

AES

PTU INHIT/Y SYS

24-50-00 PB001

Page 28 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C PRE SB 29-1115 FOR A/C 003-008 POST SB 29-1126 FOR A/C 003-008 121VU

DESIGNATION

FIN

LOCATION

PTU INHIT/Y SYS

1808GL

Q33

121VU

HYDRAULIC/HYD/QTY/IND

1831GQ

P35

121VU

HYDRAULIC/LOW/LVL/IND

1832GQ

N32

49VU

HYD/HYD/PRESS/XMTR

1841GN

C11

121VU

HYDRAULIC/SOL VALVES/G/Y/B/LEAK/TST

1881GP

N35

HYDRAULIC/B RSVR/AIR/PRESS/XMTR

2386GH

P34

123VU

B HYD/ELEC PUMP

2701GJ

AB09

49VU

HYD/HYD PWR/B WARN/& CTL

2702GJ

C12

HYDRAULIC/RAT/CTL

2801GE

P32

HYD/RAT/CTL

2801GE

D14

121VU

HYDRAULIC/RAT/SPLY/EXTN/SOL1

2803GE

P33

121VU

HYDRAULIC/Y HYD/PUMP ENG2/MONG

3700GD

Q37

121VU

HYDRAULIC/Y HYD/PUMP ENG2/CTL

3701GD

Q36

49VU

HYD/FIRE VALVE/Y/ENG2

3702GD

C14

123VU

Y HYD/ELEC/ELEC PUMP/NORM

3801GX

AB03

123VU

Y HYD/ELEC/PUMP

3802GX

AB06

121VU

HYDRAULIC/HYD POWER/Y

3803GX

N30

** On A/C ALL

** On A/C 003-004 121VU ** On A/C ALL

** On A/C 003-004 121VU ** On A/C 005-099 49VU ** On A/C ALL

AES

24-50-00 PB001

Page 29 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 5.

Operation/Control and Indicating A.

AES

Reset of the Circuit Breaker . in flight, it is not permitted to close a tripped circuit breaker, . on ground, you must not close a tripped circuit breaker without trouble shooting of the related system.

24-50-00 PB001

Page 30 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

24−35−00 2701GJ

2705GJ

ELEC PUMP−B 29−12−00

1HQ

8HQ

FAN BLOWER 21−26−00

28

115

3XB STATIC INV

WHC−1 30−42−00

1DG1 16MC

17MC

14MC

15MC

12MC

13MC

1MC

4MC

2HQ

12XB

26V

5XN1

15XN1 3XN1

3MC

6MC

2MC

5MC

8XH 431XP−A

26V 5XH

AC ESS BUS

15XN2

4XP

202XP

1XN2 AC BUS 2

2XC

2XP

3XC

10XN

1XU1

GEN 1

4000XU

GCU−APU 1XS

APU GEN

8XS

GPCU 1XG

216XP 12XN

3801GX 3805GX

EPC 3XG

GLC−APU 3XS

FUEL PUMPS 28−21−00 GCU−1

24−32−00

115VAC

15XE

GCL−1 9XU1

204XP

3XN2

1XC

BTC−1 11XU1

231XP−A

26V

5XN2

401XP

103XP

GALLEYS 24−56−00

210XP

7XN2

4XH

131XP−A

101XP

1XN1

115VAC

801XP

115VAC

24−32−00

1XP

1DG2

115VAC

FAN EXTRACT 21−26−00 WHC−2 30−42−00

901XP

AC SHED ESS BUS 8XP

110XP

7XN1

AC BUS 1

GALLEYS 24−56−00

7HQ

24−34−00 ELEC PUMP−Y 29−24−00

24−42−00

BTC−2 11XU2

EXTERNAL POWER RECEPTACLE

212XP

GLC−2 9XU2

2XX

GLC−EMERG 2XE

12XX

3802GX 3806GX GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT

CSM/G 8XE

1XE

N_MM_245000_0_YAT0_01_00

AES

FIGURE 24-50-00-11200-F SHEET 1 AC Electrical Load Distribution - General

24-50-00 PB001

Page 31 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

24−35−00 2701GJ

2705GJ

ELEC PUMP−B 29−12−00

1HQ

8HQ

FAN BLOWER 21−26−00

28

115

3XB STATIC INV

2HQ

WHC−1 30−42−00

1DG1

901XP

12XB 14MC

15MC

12MC

13MC

1MC 7XN1

21XN1

5XN1

26V

3XN1

3MC

6MC

2MC

5MC

8XH

110XP

4XH

131XP−A

431XP−A

26V 5XH

220XP

28XN

27XN

7XN2

21XN2

AC ESS BUS

1XU1

GEN 1

4000XU

202XP

AC BUS 2

2XP

10XN

8XS

GPCU 1XG

216XP 12XN

3801GX 3805GX

EPC 3XG

GLC−APU 3XS

APU GEN

24−32−00

115VAC

3XC

1XS

204XP

1XN2 2XC

GCU−APU

231XP−A

15XN2

4XP

FUEL PUMPS 28−21−00 GCU−1

210XP

3XN2

15XE

GCL−1 9XU1

218XP

26V

5XN2

401XP

103XP

1XC

BTC−1 11XU1

GALLEYS 24−56−00

115VAC

101XP

1XN1

115VAC

AC SHED ESS BUS 8XP

115VAC

24−32−00

1XP

801XP

4MC

15XN1

AC BUS 1

GALLEYS 24−56−00

FAN EXTRACT 21−26−00 WHC−2 30−42−00

1DG2

17MC

16MC

7HQ

24−34−00 ELEC PUMP−Y 29−24−00

24−42−00

BTC−2 11XU2

EXTERNAL POWER RECEPTACLE

212XP

GLC−2 9XU2

2XX

GLC−EMERG 2XE

12XX

3802GX 3806GX GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT

CSM/G 8XE

1XE

N_MM_245000_0_YBV0_01_00

AES

FIGURE 24-50-00-11200-U SHEET 1 AC Electrical Load Distribution - General

24-50-00 PB001

Page 32 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

2000VU

2001VU

ACCESS

RADOME

FR1 FR3 109VU

FR5

811

FDW EKECTRONICS RACK 90VU 108VU

FR9 105VU 106VU

103VU

FR11

TR

BAT 1

TR

FR13

812

822 BAT 2

FR15

107VU NOSE LDG/GR WELL

FR21 824 FR23

187VU

63VU

188VU

AFT ELECTRONICS RACK 80VU

N_MM_245000_0_YCL0_01_00

AES

FIGURE 24-50-00-12700-B SHEET 1 AC Power Distribution Contactors - Component Location

24-50-00 PB001

Page 33 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

49VU 35VU

120VU

A 122VU 121VU

125VU 124VU 123VU SPARE FUSES

A

N_MM_245000_0_YCL0_02_00

AES

FIGURE 24-50-00-12700-B SHEET 2 AC Power Distribution Contactors - Component Location

24-50-00 PB001

Page 34 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

2000VU

2001VU

ACCESS

RADOME

FR1 FR3 109VU

FR5

811

FDW EKECTRONICS RACK 90VU 108VU

FR9 105VU 106VU

103VU

FR11

TR

BAT 1

TR

FR13

812

822 BAT 2

FR15

107VU NOSE LDG/GR WELL

FR21 824 FR23

187VU

63VU

188VU

AFT ELECTRONICS RACK 80VU

N_MM_245000_0_YCP0_01_00

AES

FIGURE 24-50-00-12700-C SHEET 1 AC Power Distribution Contactors - Component Location

24-50-00 PB001

Page 35 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

49VU 35VU

120VU

A 122VU 121VU

125VU 124VU 123VU

A

N_MM_245000_0_YCP0_02_00

AES

FIGURE 24-50-00-12700-C SHEET 2 AC Power Distribution Contactors - Component Location

24-50-00 PB001

Page 36 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 801PP 301PP

11PB APU STAR 49−42−00

5KA

1PB2

5PB2

BCL−2 12PB2 4PB2 6PB2

3PN1

DC BUS 1

12PB1

501PP

BAT1 4PB1 6PB1

1PP

2PB1

BAT BUS

1PC1

28VDC

5PR

3PP

8PH 401PP

208PP

3PB2

DC ESS BUS

4PC

1PR

6PN 3PN2

SHUNT

1PN2

3PB1

DC BUS 2

1PC2

28VDC

20PC

8PR

SHUNT

703PP

5PB1

101PP

1PN1

704PP

701PP

BCL−1

103PP

502PP

2PB2

1PB1

2PR

702PP

BAT2

4PP

206PP

28VDC

204PP

601PP

202PP

602PP

2PP 28VDC

7PN

DC SVCE BUS

8PN

6PP 28VDC

3PX

5XB 3XB

5PU1

28 29−12−00

21−26−00

5XN1

15XN1 3XN1

2PU1

AC BUS 1

1XP 115VAC

1PX

24−56−00 1PU2 TR2

8XH 431XP−A

26V

4XH

401XP

15XN2

115VAC AC ESS BUS

231XP−A

26V

5XN2

5XH

103XP

204XP

3XN2

4XP

202XP

1XN2

1XC

2XC

3XC

AC BUS 2

2XP 115VAC

15XE

BTC−1 11XU1 GCL−1 9XU1

GCU−1 1XU1

GEN 1

4000XU

FUEL PUMPS 28−21−00 GCU−APU 1XS

4XX

2PU2

14PU

10XN

12XN

3801GX 3805GX

BTC−2 11XU2

EPC 3XG

GLC−APU 3XS

1PE ESS TR

210XP

7XN2

101XP

1XN1

30−42−00

115VAC

131XP−A

3PE

5PU2

AC SHED ESS BUS 8XP

110XP

26V

901XP

12XB

24−56−00 7XN1

6PH

801XP

30−42−00 1PU1 TR1

2XB 115

STATIC INV

21−26−00

AES

8PP 28VDC

CSM/G CONTROL UNIT

6XE

6KA

10KA

DC SHED ESS BUS

GLC−2 9XU2

1XX

14XX

2XX

12XX

214XP 216XP 212XP

4PE

ELEC PUMP−Y 29−24−00

GLC−EMERG 2XE

3802GX 3806GX APU GEN

FIGURE 24-50-00-14600-C SHEET 1 Normal Flight Configuration for the Whole Network (AC/DC)

8XS

GPCU 1XG

24-50-00 PB001

EXTERNAL POWER RECEPTACLE

Page 37 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_245000_0_YEL0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 801PP 301PP

11PB APU START 49−42−00

6XE 5KA

6KA

10KA

1PB2

2PR

5PB2 12PB2

2PB2 701PP

12PB1

BCL−1

BAT1 4PB1

1PP

2PB1

6PB1

BAT BUS

1PC1

28VDC

5PR

3PP

SHUNT

8PH 401PP

208PP

3PB2

DC ESS BUS

4PC

1PR

3PN2 SHUNT

1PN2

3PB1

4PP 28VDC

206PP

6PN

DC BUS 2

1PC2

28VDC

20PC

501PP

8PR

703PP

5PB1

101PP

1PN1 DC BUS 1

BAT2

6PB2

1PB1 103PP

502PP

704PP

4PB2

204PP

601PP

202PP

602PP

2PP 28VDC

7PN

DC SVCE BUS

8PN

29−12−00

28

21−26−00 30−42−00

7XN1

21XN1 26V

5XN1

2XB

21−26−00

STATIC INV

30−42−00

1XP 115VAC

431XP−A

26V

27XN

218XP

15XN2 401XP

101XP

AC ESS BUS

204XP

3XN2

4XP

202XP

1XN2

1XC

2XC

AC BUS 2

2XP 115VAC

3XC

15XE

GCL−1 9XU1

BTC−1 11XU1 FUEL PUMPS 28−21−00

GCU−1 1XU1

GEN 1

4000XU

GCU−APU

4XX

2PU2

14PU

10XN

12XN

3801GX 3805GX

BTC−2 11XU2

EPC 3XG

GLC−APU 3XS

GLC−2 9XU2

1XX

14XX

2XX

12XX

3802GX 3806GX APU GEN

1XS

8XS

1PE ESS TR

231XP−A

26V

5XH

1PU2 TR2

210XP

21XN2

5XN2

115VAC

1XN1

220XP

7XN2

103XP

2PU1

24−56−00 28XN

8XH

4XH

3PE

5PU2

115VAC

131XP−A

212PP

1PX

AC SHED ESS BUS 8XP

15XN1 3XN1

AC BUS 1

901XP

12XB

801XP

110XP

10PN

3PX

5PH

115

24−56−00 1PU1 TR1

11PN

3XB

6PP 28VDC

210PP 5XB 5PU1

8PP 28VDC

702PP

BCL−2

3PN1

DC SHED ESS BUS

CSM/G CONTROL UNIT

GPCU 1XG

EXTERNAL POWER RECEPTACLE

GCU−2 1XU2

GEN 2

4000XU

16XX

214XP

216XP 212XP

4PE

ELEC PUMP−Y 29−24−00

GLC−EMERG 2XE

CSM/G CONTROL UNIT

CSM/G 8XE

1XE N_MM_245000_0_YEU0_01_00

AES

FIGURE 24-50-00-14600-H SHEET 1 Normal Flight Configuration for the Whole Network (AC/DC)

24-50-00 PB001

Page 38 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 801PP 301PP

11PB APU STAR 49−42−00

5KA

1PB2

5PB2

BCL−2 12PB2 4PB2 6PB2

DC BUS 1

501PP

BAT1 4PB1 6PB1

1PP

2PB1

BAT BUS

1PC1

28VDC

5PR

3PP

8PH 401PP

208PP

3PB2

DC ESS BUS

4PC

1PR

6PN 3PN2

SHUNT

1PN2

3PB1

DC BUS 2

1PC2

28VDC

20PC

8PR

SHUNT

703PP

5PB1

101PP

1PN1

704PP

701PP

12PB1

BCL−1

103PP

3PN1

502PP

2PB2

1PB1

2PR

702PP

BAT2

4PP

206PP

28VDC

204PP

601PP

202PP

602PP

2PP 28VDC

7PN

DC SVCE BUS

8PN

6PP 28VDC

3PX

5XB 3XB

5PU1

28 29−12−00

21−26−00

5XN1 3XN1

2PU1

AC BUS 1

1XP 115VAC

1PX

24−56−00 1PU2 TR2

8XH 431XP−A

26V

4XH

401XP

15XN2

115VAC AC ESS BUS

231XP−A

26V

5XN2

5XH

103XP

204XP

3XN2

4XP

202XP

1XN2

1XC

2XC

3XC

AC BUS 2

2XP 115VAC

15XE

BTC−1 11XU1 GCL−1 9XU1

GCU−1 1XU1

GEN 1

4000XU

FUEL PUMPS 28−21−00 GCU−APU 1XS

4XX

2PU2

14PU

10XN

12XN

3801GX 3805GX

BTC−2 11XU2

EPC 3XG

GLC−APU 3XS

1PE ESS TR

210XP

7XN2

101XP

1XN1

30−42−00

115VAC

131XP−A

3PE

5PU2

AC SHED ESS BUS 8XP

110XP

26V 15XN1

901XP

12XB

24−56−00 7XN1

6PH

801XP

30−42−00 1PU1 TR1

2XB 115

STATIC INV

21−26−00

AES

8PP 28VDC

CSM/G CONTROL UNIT

6XE

6KA

10KA

DC SHED ESS BUS

GLC−2 9XU2

1XX

14XX

2XX

12XX

214XP 216XP 212XP

4PE

ELEC PUMP−Y 29−24−00

GLC−EMERG 2XE

3802GX 3806GX APU GEN

FIGURE 24-50-00-14700-C SHEET 1 Emergency Configuration for the Whole Network (AC/DC)

8XS

GPCU 1XG

24-50-00 PB001

EXTERNAL POWER RECEPTACLE

Page 39 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_245000_0_YGL0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 801PP 301PP

11PB APU STAR 49 − 42 − 00

5KA

1PB2

5PB2

BCL− 2 12PB2 4PB2 6PB2

DC BUS 1

501PP

BAT1 4PB1 6PB1

1PP

2PB1

BAT BUS

1PC1

28VDC

5PR

3PP

8PH 401PP

208PP

3PB2

DC ESS BUS

4PC

1PR

6PN 3PN2

SHUNT

1PN2

3PB1

DC BUS 2

1PC2

28VDC

20PC

8PR

SHUNT

703PP

5PB1

101PP

1PN1

704PP

701PP

12PB1

BCL− 1

103PP

3PN1

502PP

2PB2

1PB1

2PR

702PP

BAT2

4PP

206PP

28VDC

204PP

601PP

202PP

602PP

2PP 28VDC

7PN

DC SVCE BUS

8PN

6PP 28VDC

3PX

5XB 3XB

5PU1

28 29 − 12 − 00

21 − 26 − 00

21XN1 26V 15XN1

5XN1 3XN1

2PU1

AC BUS 1

1XP 115VAC

30 − 42 − 00

1PU2 TR2

8XH 7XN2

401XP

103XP

15XN2

115VAC AC ESS BUS

231XP−A

26V

5XN2

5XH

204XP

3XN2

4XP

202XP

1XN2 2XC

3XC

AC BUS 2

2XP 115VAC

15XE

BTC − 1 11XU1

GCU−1 1XU1

GEN 1

4000XU

GLC − APU 3XS FUEL PUMPS 28 − 21 − 00 GCU−APU 1XS

4XX

2PU2

14PU

10XN

12XN

3801GX 3805GX

BTC − 2 11XU2

EPC 3XG

1PE ESS TR

210XP

21XN2

431XP−A

26V

4XH

131XP−A

1XC

GCL − 1 9XU1

1PX

24 − 56 − 00

115VAC 110XP

3PE

5PU2

AC SHED ESS BUS 8XP

101XP

1XN1

901XP

12XB

24 − 56 − 00 7XN1

6PH

801XP

30 − 42 − 00 1PU1 TR1

2XB 115

STATIC INV

21 − 26 − 00

AES

8PP 28VDC

CSM/G CONTROL UNIT

6XE

6KA

10KA

DC SHED ESS BUS

GLC − 2 9XU2

1XX

14XX

2XX

12XX

16XX

214XP

216XP 212XP

4PE

ELEC PUMP − Y 29 − 24 − 00

GLC − EMERG 2XE

3802GX 3806GX APU GEN

FIGURE 24-50-00-14700-G SHEET 1 Emergency Configuration for the Whole Network (AC/DC)

8XS

GPCU 1XG

24-50-00 PB001

EXTERNAL POWER RECEPTACLE

Page 40 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT CSM/G 8XE 1XE N_MM_245000_0_YGU0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 801PP 301PP

11PB APU STAR 49 − 42 − 00

5KA

1PB2

5PB2

BCL− 2 12PB2 4PB2 6PB2

DC BUS 1

501PP

BAT1 4PB1 6PB1

1PP

2PB1

BAT BUS

1PC1

28VDC

5PR

3PP

8PH 401PP

208PP

3PB2

DC ESS BUS

4PC

1PR

6PN 3PN2

SHUNT

1PN2

3PB1

DC BUS 2

1PC2

28VDC

20PC

8PR

SHUNT

703PP

5PB1

101PP

1PN1

704PP

701PP

12PB1

BCL− 1

103PP

3PN1

502PP

2PB2

1PB1

2PR

702PP

BAT2

4PP

206PP

28VDC

204PP

601PP

202PP

602PP

2PP 28VDC

7PN

DC SVCE BUS

8PN

6PP 28VDC

3PX

5XB 3XB

5PU1

28 29 − 12 − 00

21 − 26 − 00

26V 15XN1

3XN1

2PU1

AC BUS 1

1XP 115VAC

1PU2 TR2

431XP−A

26V

4XH

401XP

15XN2

115VAC AC ESS BUS

231XP−A

26V

5XN2

5XH

103XP

204XP

3XN2

4XP

202XP

1XN2 2XC

3XC

AC BUS 2

2XP 115VAC

15XE

BTC − 1 11XU1

GCU−1 1XU1

GEN 1

4000XU

FUEL PUMPS 28 − 21 − 00 GCU−APU 1XS

4XX

2PU2

14PU

10XN

12XN

3801GX 3805GX

BTC − 2 11XU2

EPC 3XG

GLC − APU 3XS

1PE ESS TR

210XP

7XN2

1XC

GCL − 1 9XU1

1PX

24 − 56 − 00

8XH

101XP

1XN1

30 − 42 − 00

115VAC

131XP−A

3PE

5PU2

AC SHED ESS BUS 8XP

110XP

5XN1

901XP

12XB

24 − 56 − 00 7XN1

6PH

801XP

30 − 42 − 00 1PU1 TR1

2XB 115

STATIC INV

21 − 26 − 00

AES

8PP 28VDC

CSM/G CONTROL UNIT

6XE

6KA

10KA

DC SHED ESS BUS

GLC − 2 9XU2

1XX

14XX

2XX

12XX

214XP 216XP 212XP

4PE

ELEC PUMP − Y 29 − 24 − 00

GLC − EMERG 2XE

3802GX 3806GX APU GEN

FIGURE 24-50-00-14800-C SHEET 1 Smoke Configuration for the Whole Network (AC/DC)

8XS

GPCU 1XG

24-50-00 PB001

EXTERNAL POWER RECEPTACLE

Page 41 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT 1XE

EMER GEN

8XE

N_MM_245000_0_YJL0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 801PP 301PP

11PB APU STAR 49−42−00

5KA

1PB2

5PB2

BCL−1 12PB2 4PB2 6PB2

DC BUS 1

501PP

BAT1 4PB1 6PB1

1PP

2PB1

BAT BUS

1PC1

28VDC

5PR

3PP

8PH 401PP

208PP

3PB2

DC ESS BUS

4PC

1PR

6PN 3PN2

SHUNT

1PN2

3PB1

DC BUS 2

1PC2

28VDC

20PC

8PR

SHUNT

703PP

5PB1

101PP

1PN1

704PP

701PP

12PB1

BCL−2

103PP

3PN1

502PP

2PB2

1PB1

2PR

702PP

BAT2

4PP

206PP

28VDC

204PP

601PP

202PP

602PP

2PP 28VDC

7PN

DC SVCE BUS

8PN

6PP 28VDC

3PX

5XB 3XB

5PU1

28 29−12−00

21−26−00

21XN1 26V 15XN1

5XN1 3XN1

2PU1

AC BUS 1

1XP 115VAC

30−42−00 1PX

24−56−00 1PU2 TR2

115VAC 8XH

110XP

7XN2

401XP

103XP

15XN2

115VAC AC ESS BUS

231XP−A

26V

5XN2

5XH

204XP

3XN2

4XP

202XP

1XN2

1XC

2XC

3XC

AC BUS 2

2XP 115VAC

15XE

BTC−1 11XU1 GCL−1 9XU1

GCU−1 1XU1

GEN 1

4000XU

GLC−APU 3XS FUEL PUMPS 28−21−00 GCU−APU 1XS

4XX

2PU2

14PU

10XN

12XN

3801GX 3805GX

BTC−2 11XU2

EPC 3XG

1PE ESS TR

210XP

21XN2

431XP−A

26V

4XH

131XP−A

3PE

5PU2

AC SHED ESS BUS 8XP

101XP

1XN1

901XP

12XB

24−56−00 7XN1

6PH

801XP

30−42−00 1PU1 TR1

2XB 115

STATIC INV

21−26−00

AES

8PP 28VDC

CSM/G CONTROL UNIT

6XE

6KA

10KA

DC SHED ESS BUS

GLC−2 9XU2

1XX

14XX

2XX

12XX

16XX

214XP

216XP 212XP

4PE

ELEC PUMP−Y 29−24−00

GLC−EMERG 2XE

3802GX 3806GX APU GEN

FIGURE 24-50-00-14800-G SHEET 1 Smoke Configuration for the Whole Network (AC/DC)

8XS

GPCU 1XG

24-50-00 PB001

EXTERNAL POWER RECEPTACLE

Page 42 May 01/12 Revision n˚: 40

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT 1XE

EMER GEN

8XE

N_MM_245000_0_YJU0_01_00

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL HIGH VOLTAGE INSIDE

49VU

HA

HA

H

H

G

G

F

F

E

E

D

D

C

C

B

B

A

A 1

2

3

4

5

6

7

8

9

10

11

12

13

14

N_MM_245000_0_YPB0_01_00

AES

FIGURE 24-50-00-16200-B SHEET 1 Provision for C/B(s) Installation on the Panel 49VU

24-50-00 PB001

Page 43 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

105VU

106VU

RELAYS

CONTACTORS

N_MM_245000_0_YQA0_01_00

AES

FIGURE 24-50-00-16400-A SHEET 1 Provision for C/B(s) Installation on the Panels 105VU and 106VU

24-50-00 PB001

Page 44 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

R

Q

P

N

M

L

K

J 1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

22

N_MM_245000_0_YRAA_01_00

AES

FIGURE 24-50-00-16700-A SHEET 1 Provision for C/B(s) Installation on the Panel 121VU

24-50-00 PB001

Page 45 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

R

Q

P

N

M

L

K

J 23

24

25

26

27

28

29

30

31

32

33

34

35

36

37

38

39

40

41

42

43

44

45

N_MM_245000_0_YRAA_02_00

AES

FIGURE 24-50-00-16700-A SHEET 2 Provision for C/B(s) Installation on the Panel 121VU

24-50-00 PB001

Page 46 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z

Y

X

W

V

U

T

S 1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

N_MM_245000_0_YRDA_01_00

AES

FIGURE 24-50-00-16800-A SHEET 1 Provision for C/B(s) Installation on the Panel 122VU

24-50-00 PB001

Page 47 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z

Y

X

W

V

U

T

S 16

17

18

19

20 21

22

23

24

25 26

27

28

29

30

31

N_MM_245000_0_YRDA_02_00

AES

FIGURE 24-50-00-16800-A SHEET 2 Provision for C/B(s) Installation on the Panel 122VU

24-50-00 PB001

Page 48 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AB

AD AD

AC

AE AE

AB

AC

1

2

3

4

123VU

AB

AA

5

6

7

8

123VU

AF AF

9

10

11

12

123VU

** On A/C ALL

N_MM_245000_0_YRG0_01_00

AES

FIGURE 24-50-00-16900-A SHEET 1 Provision for C/B(s) Installation on the Panel 123VU

24-50-00 PB001

Page 49 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 124VU

BG

125VU

CK

CJ BF

CH BE

CG

BD CF

BC CE

CD

BB

CC BA

1 CB

CA

N_MM_245000_0_YRK0_01_00

AES

FIGURE 24-50-00-17000-A SHEET 1 Provision for C/B(s) Installation on the Panels 124VU and 125VU

24-50-00 PB001

Page 50 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2000VU

A

B

C

D

E

F

G

H

J 1

2

3

4

5

6

7

8

N_MM_245000_0_YVA0_01_00

AES

FIGURE 24-50-00-17200-A SHEET 1 Provision for C/B(s) Installation on the Panel 2000VU

24-50-00 PB001

Page 51 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

2001VU

A

B

C

D

E

F 1

2

3

4

5

6

7

8

N_MM_245000_0_YXA0_01_00

AES

FIGURE 24-50-00-17400-A SHEET 1 Provision for C/B(s) Installation on the Panel 2001VU

24-50-00 PB001

Page 52 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC ELECTRICAL LOAD DISTRIBUTION DEACTIVATION/REACTIVATION ** On A/C ALL Task 24-50-00-040-001-A Deactivation of the C/B TRIPPED Warning on the Upper ECAM DU 1.

Reason for the Job MMEL 24-09-02A C/B TRIPPED Alert (Old MMEL ref: 24-50-01-A))

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

812, 822 C.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

3.

Job Set-up Subtask 24-50-00-860-054-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

Subtask 24-50-00-010-051-A B.

Get Access (1)

AES

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 822.

24-50-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4.

(2)

Open the access door 822.

(3)

On the battery power center 105VU: . Loosen the two screws and remove the protective cover.

(4)

Open the access door 812.

(5)

On the AC/DC emergency power center 106VU: . Loosen the five screws and remove the protective cover.

Procedure Subtask 24-50-00-040-052-A A.

Check for C/B TRIPPED (1)

If the C/B TRIPPED ECAM warning comes into view, do this check:

ACTION 1.If the C/B TRIPPED ON OVHD PANEL warning comes into view on the upper ECAM DU: . On the overhead circuit breaker panel 49VU, make . sure that all the circuit breakers are closed.

RESULT

If all the circuit breakers are closed, no maintenance procedure is necessary.

2.If the C/B TRIPPED R ELEC BAY warning comes into view on the upper ECAM DU: . On the battery power center 105VU, make sure that all the circuit breakers are closed.

.

If all the circuit breakers are closed, no maintenance procedure is necessary.

On the AC/DC emergency power center 106VU, make . sure that all the circuit breakers are closed.

If all the circuit breakers are closed, no maintenance procedure is necessary.

3.If the C/B TRIPPED L ELEC BAY warning comes into view on the upper ECAM DU: .

4.If the C/B TRIPPED REAR PNL J-M warning comes into view on the upper ECAM DU: . On the rear circuit breaker panel 121VU between lines . J and M, make sure that all the circuit breakers are closed. 5.If the C/B TRIPPED REAR PNL N-R warning comes into view on the upper ECAM DU:

If all the circuit breakers are closed, no maintenance procedure is necessary.

.

On the rear circuit breaker panel 121VU between lines . N and R, make sure that all the circuit breakers are closed. 6.If C/B TRIPPED REAR PNL S-V warning comes into view on the upper ECAM DU:

If all the circuit breakers are closed, no maintenance procedure is necessary.

.

If all the circuit breakers are closed, no maintenance procedure is necessary.

On the rear circuit breaker panel 122VU between lines . S and V, make sure that all the circuit breakers are closed. 7.If the C/B TRIPPED REAR PNL W-Z warning comes into view on the upper ECAM DU: . On the rear circuit breaker panel 122VU between lines . W and Z, make sure that all the circuit breakers are closed.

AES

If all the circuit breakers are closed, no maintenance procedure is necessary.

24-50-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-50-00-410-051-A A.

Close Access (1)

Install the protective cover on the battery power center 105VU.

(2)

Tighten the two screws.

(3)

Install the protective cover on the AC/DC emergency power center 106VU.

(4)

Tighten the five screws.

(5)

Close the access doors 822 and 812.

(6)

Make sure that the work area is clean and clear of tool(s) and other items.

(7)

Remove the access platform(s).

Subtask 24-50-00-860-055-A B.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.

(3)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-50-00 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-50-00-440-001-A Reactivation of the C/B TRIPPED Warning on the Upper ECAM DU 1.

Reason for the Job MMEL 24-09-02A C/B TRIPPED Alert (Old MMEL ref: 24-50-01-A))

2.

Job Set-up Information A.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

TSM 24-00-00-810-803

Circuit Breaker Tripped and/or C/B TRIPPED Warning

3.

Job Set-up Subtask 24-50-00-860-056-A A.

4.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

Procedure Subtask 24-50-00-440-052-A A.

5.

Do the troubleshooting procedure given in the TSM task (Ref. TSM 24-00-00-810-803).

Close-up Subtask 24-50-00-860-057-A A.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-50-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC MAIN DISTRIBUTION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General

** On A/C 003-004 (Ref. Fig. 24-51-00-11200-A - AC Main Distribution - Block Diagram) ** On A/C 005-099 (Ref. Fig. 24-51-00-11200-F - AC Main Distribution - Block Diagram) The AC main distribution network corresponds to busbars 1XP and 2XP and their associated sub-busbars.

AES

24-51-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location

** On A/C 003-004 (Ref. Fig. 24-51-00-12400-A - AC Main Distribution - Component Location) ** On A/C 005-099 (Ref. Fig. 24-51-00-12400-D - AC Main Distribution - Component Location) (Ref. Fig. 24-51-00-12500-A - AC Main Distribution - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS ATA REF. DOOR

** On A/C ALL 12XN 15XN1

CNTOR-AC SVCE BUS NORM SPLY A/XFMR-115/26VAC, 1

120VU 120VU

212 212

24-51-55 24-51-51

15XN2

A/XFMR-115/26VAC, 2

120VU

212

24-51-51

21XN1 21XN2 22XN

CNTOR-115 VAC BUS 1 SPLY CNTOR-115 VAC BUS 2 SPLY P/BSW-ELEC/COMMERCIAL

120VU 120VU 35VU

212 212 210

24-51-00 24-51-00 24-51-00

27XN

CONTACTOR

120VU

212

24-51-55

** On A/C 005-099

AES

24-51-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

Operation/Control and Indicating The main busbars can be supplied: . either by the corresponding generator, . or by the other main generator, or by the APU generator or the ground power unit by means of the transfer circuit. The major part of the network is supplied with three-phase 115 VAC/400 Hz. A 115/26 VAC single-phase autotransformer supplying a normal 26 VAC/400 Hz sub-busbar (131XP.A and 231XP.A) is connected to each main busbar. Part of the AC main network (212XP, 214XP, 216XP.C) can be supplied directly by the ground power unit in ground service configuration (Ref. 24-42-00, P. Block 1). For each main busbar, a warning is triggered on the ECAM to indicate a loss of supply (Ref. Fig. 24-51-00-13800-B - AC Main Distribution - ECAM Warnings)

AES

24-51-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

24−50−00

24−50−00 110XP

7XN1 26V

5XN1

15XN1 3XN1

231XP−A

26V

5XN2

15XN2

103XP

204XP

101XP

1XN1 1XP

131XP−A

3XN2

24−32−00

AC BUS 1

210XP

7XN2

202XP

1XN2 24−25−00

24−25−00

AC BUS 2

2XP

115VAC

24−32−00

216XP

115VAC 10XN

12XN

212XP 24−34−00

24−50−00 24−24−00

GCL−1 9XU1

GCU−1 1XU1

GEN 1

4000XU

BTC−1 11XU1 FUEL PUMPS 28−21−00 GCU−APU 1XS

GLC−APU 3XS

24−42−00

BTC−2 11XU2

EPC 3XG

GLC−2 9XU2

2XX

12XX

GLC−EMERG 2XE

24−50−00 APU GEN

8XS

GPCU 1XG

EXTERNAL POWER RECEPTACLE

GCU−2 1XU2

GEN 2

4000XU

CSM/G CSM/G 8XE CONTROL UNIT 1XE

N_MM_245100_0_AAM0_01_00

AES

FIGURE 24-51-00-11200-A SHEET 1 AC Main Distribution - Block Diagram

24-51-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

24−50−00

24−50−00

7XN1

21XN1 26V

5XN1

220XP

28XN

27XN

7XN2

21XN2

110XP

210XP

131XP−A

231XP−A

26V

5XN2

15XN1

15XN2

103XP

3XN1

218XP

204XP

3XN2 24−32−00

101XP

1XN1 AC BUS 1

1XP

202XP

1XN2

24−25−00

24−25−00

AC BUS 2

2XP

115VAC

24−32−00

216XP

115VAC 10XN

12XN

212XP 24−34−00

24−50−00 24−24−00 24−42−00 GCL−1 9XU1

GCU−1 1XU1

GEN 1

4000XU

BTC−1 11XU1 FUEL PUMPS 28−21−00 GCU−APU 1XS

GLC−APU 3XS

EPC 3XG

BTC−2 11XU2

GLC−2 9XU2

2XX

GLC−EMERG 2XE

12XX

24−50−00 APU GEN

8XS

GPCU 1XG

EXTERNAL POWER RECEPTACLE

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT

CSM/G 8XE

1XE

N_MM_245100_0_AAW0_01_00

AES

FIGURE 24-51-00-11200-F SHEET 1 AC Main Distribution - Block Diagram

24-51-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

A

C A

122VU

15XN1 15XN2

121VU

124VU

125VU

123VU

B 6 5

D

3

4 CONTACTOR BASE

2

B 123VU

D

12XN

CONTACTOR

C 7 1

N_MM_245100_0_ACM0_01_00

AES

FIGURE 24-51-00-12400-A SHEET 1 AC Main Distribution - Component Location

24-51-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

C

A

A

15XN1

122VU

15XN2 121VU

124VU

125VU 21XN1

123VU

25XN1

B

21XN2

25XN2

D

3

4

2

B 123VU

D

12XN

20XX CONTACTOR

C 7 1

N_MM_245100_0_ACQ0_01_00

AES

FIGURE 24-51-00-12400-D SHEET 1 AC Main Distribution - Component Location

24-51-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

A

A

22XN

PANEL 35VU

N_MM_245100_0_AGM0_01_00

AES

FIGURE 24-51-00-12500-A SHEET 1 AC Main Distribution - Component Location

24-51-00 PB001

Page 8 May 01/12 Revision n˚: 40

AES

202XP−A 115VAC BUS 2

101XP−A 115VAC BUS 1

17XN2

17XN1

OFF

ON

16XC

OFF

ON

15XC

FIGURE 24-51-00-13800-B SHEET 1 AC Main Distribution - ECAM Warnings SDAC−1

09B 09C 09D

09G 09H 09J

SDAC 1 DATA BUS 1

TO FWC 2 SDAC 1 FWC 1 DATA BUS 2 DATA BUS 2

RMP

LMP

RMP 12B 12C 12A

04J 04K

LMP

FWC−1

BUS

TO SDAC−2

BUS

BUS

RMP

05J 05K

LMP

04A 04B

FWC 2 DATA BUS 2

SDAC 2 DATA BUS 2

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_245100_0_YEL0_01_00

24-51-00 PB001

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC MAIN DISTRIBUTION - DEACTIVATION/REACTIVATION ** On A/C 005-099 Task 24-51-00-040-001-A Deactivation of the Galley Supply System 1.

Reason for the Job MMEL 24-26-02B Galley Manual Load Shed System (GALLEY) (Old MMEL ref: 24-56-01-B)

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY 1 PLACARD

DESIGNATION

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

3.

Job Set-up Subtask 24-51-00-861-051-B A.

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002A-02).

Subtask 24-51-00-865-052-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

122VU

DESIGNATION ELEC/GALY & CAB/CTL

1XA

S26

122VU

ELEC/GALY & CAB/FAULT/LT CTL

8XA

S25

122VU

ELEC/GALY & CAB/GND/FLT/LOGIC

7XA

S24

CAB CAB CAB CAB CAB

307LG 304LG 306LG 305LG 302LG

H08 H07 H06 H05 H04

2000VU 2000VU 2000VU 2000VU 2000VU

AES

LIGHT LIGHT LIGHT LIGHT LIGHT

PWR-CEILING-AFT PWR-CEILING-AFT PWR-CEILING-FWD PWR-CEILING-FWD PWR-WINDOW-AFT

FIN

LOCATION

24-51-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL 2000VU 2000VU 2000VU

DESIGNATION CAB LIGHT PWR-WINDOW-AFT CAB LIGHT PWR-WINDOW-FWD CAB LIGHT PWR-WINDOW-FWD

FIN 301LG 303LG 300LG

LOCATION H03 H02 H01

Subtask 24-51-00-860-058-B C.

In the forward and aft galleys, make sure that all the circuit breakers are closed.

Subtask 24-51-00-860-052-B D.

4.

Aircraft Maintenance Configuration (1)

On the ELEC panel 35VU, make sure that the GALY & CAB pushbutton switch is pushed (the OFF legend is off).

(2)

On this panel, make sure that the ELEC/COMMERCIAL pushbutton switch is released (the OFF legend is on).

(3)

On the FWD ATTENDANT panel 120RH, make sure that the MAIN ON pushbutton switch is ON (CABIN WDO and CABIN CLG pushbutton switches green lights are ON).

(4)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

Procedure Subtask 24-51-00-040-050-B A.

Deactivation of the Galley Supply System (1)

Test of the Commercial Electrical Load-Shedding

ACTION 1.On the ECAM control panel: . Get the ELEC system page. 2.On the ELEC panel 35VU: . Push the ELEC/COMMERCIAL pushbutton switch.

RESULT On the lower display unit of the ECAM system: . The ELEC page comes into view with the white GALLEY SHED indication. On the panel 35VU: . The OFF legend of the ELEC/COMMERCIAL pushbutton switch goes off. On the lower display unit of the ECAM system: . The GALLEY SHED indication goes out of view. In the forward and aft galleys: . Make sure that the galleys operate. In the passenger cabin: . The CEILING and WINDOW lights come on.

3.On the ELEC panel 35VU: On the panel 35VU: . Release the ELEC/COMMERCIAL pushbutton switch. . The OFF legend of the ELEC/COMMERCIAL pushbutton switch comes on. On the lower display unit of the ECAM system: . The white GALLEY SHED indication comes into view. In the forward and aft galleys: . Make sure that no equipment operate. In the passenger cabin: . The CEILING and WINDOW lights go off.

AES

24-51-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-51-00-860-053-B A.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

Make an entry in the logbook.

(3)

Put a PLACARD in the cockpit to tell persons that the galley supply system is deactivated.

(4)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-51-00 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-51-00-440-001-A Reactivation of the Galley Supply System 1.

Reason for the Job MMEL 24-26-02B Galley Manual Load Shed System (GALLEY) (Old MMEL ref: 24-56-01-B)

2.

Job Set-up Information A.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

TSM 24-56-00-810-801

Galley Supply Fault

3.

Job Set-up Subtask 24-51-00-861-052-B A.

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002A-02).

Subtask 24-51-00-865-054-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

122VU

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

122VU

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER C

1MC

AE10

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

FWD GALLEY/FEEDER F

16MC

AC10

4.

FIN

LOCATION

Procedure Subtask 24-51-00-440-050-B A.

AES

Do the trouble shooting of the galley supply system (Ref. TSM 24-56-00-810-801).

24-51-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-51-00-862-051-B A.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-51-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC MAIN DISTRIBUTION - ADJUSTMENT/TEST ** On A/C 005-099 Task 24-51-00-710-001-A Operational Test of the Commercial Electrical Load Shedding 1.

Reason for the Job (Ref. MPD 24-51-00-02-) OPERATIONAL CHECK OF COMMERCIAL ELECTRIC LOAD SHEDDING Make sure that the commercial electrical load shedding is effective

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

210

CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD B.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

3.

Job Set-up Subtask 24-51-00-861-050-A A.

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002A-02).

Subtask 24-51-00-865-050-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

122VU

DESIGNATION ELEC/GALY & CAB/CTL

1XA

S26

122VU

ELEC/GALY & CAB/FAULT/LT CTL

8XA

S25

122VU

ELEC/GALY & CAB/GND/FLT/LOGIC

7XA

S24

CAB CAB CAB CAB CAB

307LG 304LG 306LG 305LG 302LG

H08 H07 H06 H05 H04

2000VU 2000VU 2000VU 2000VU 2000VU

AES

LIGHT LIGHT LIGHT LIGHT LIGHT

PWR-CEILING-AFT PWR-CEILING-AFT PWR-CEILING-FWD PWR-CEILING-FWD PWR-WINDOW-AFT

FIN

LOCATION

24-51-00 PB501

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL 2000VU 2000VU 2000VU

DESIGNATION CAB LIGHT PWR-WINDOW-AFT CAB LIGHT PWR-WINDOW-FWD CAB LIGHT PWR-WINDOW-FWD

FIN 301LG 303LG 300LG

LOCATION H03 H02 H01

Subtask 24-51-00-860-057-A C.

In the forward and aft galleys, make sure that all the circuits breakers are closed.

Subtask 24-51-00-860-050-A D.

4.

Aircraft Maintenance Configuration (1)

On the ELEC panel 35VU, make sure that the GALLEY pushbutton switch is pushed (the OFF legend is off).

(2)

On this panel, make sure that the ELEC/COMMERCIAL pushbutton switch is released (the OFF legend is on).

(3)

On the FWD ATTENDANT panel 120RH, make sure that the MAIN ON, CABIN WDO and CABIN CLG pushbutton switches are pushed.

(4)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

Procedure Subtask 24-51-00-710-050-A A.

Test of the Commercial Electrical Load Shedding

ACTION 1.On the ECAM control panel: . get the ELEC system page. 2.On the ELEC panel 35VU: . push the ELEC/COMMERCIAL pushbutton switch.

RESULT On the lower display unit of the ECAM system: . the ELEC page comes into view with the white GALLEY SHED indication. On the panel 35VU: . the OFF legend of the ELEC/COMMERCIAL pushbutton switch goes off. On the lower display unit of the ECAM system: . the GALLEY SHED indication goes out of view. In the forward and aft galleys: . make sure that the galleys operate. In the passenger cabin: . the CEILING and WINDOW lights come on.

3.On the ELEC panel 35VU: . release the ELEC/COMMERCIAL pushbutton switch

On the panel 35VU: . the OFF legend of the ELEC/COMMERCIAL pushbutton switch comes on. On the lower display unit of the ECAM system: . the white GALLEY SHED indication comes into view. In the forward and aft galleys: . make sure that no equipment operate. In the passenger cabin: . the CEILING and WINDOW lights go off.

AES

24-51-00 PB501

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-51-00-860-051-A A.

AES

Put the aircraft back to its initial configuration. (1)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(2)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-51-00 PB501

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

TRANSFORMER - 115/26VAC - REMOVAL/INSTALLATION ** On A/C ALL Task 24-51-51-000-001-A Removal of the 115/26VAC Autotransformer WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 15XN1, 15XN2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE (Ref. Fig. 24-51-51-991-00100-A - Autotransformers) 3.

DESIGNATION

Job Set-up Subtask 24-51-51-010-050-A A.

Get Access (1)

In the cockpit, remove the panel (6) which gives access to the panel 122VU. The panel 122VU is at the top of the panel 120VU.

(2)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(3)

Open the access door 121AL.

Subtask 24-51-51-860-050-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft receptacle.

(2)

Put WARNING NOTICE(S) on the access door 121AL to tell persons not to connect the external power connector.

(3)

In the cockpit, on the overhead ELEC panel 35VU, release these pushbutton switches: . BAT 1, BAT 2,

24-51-51 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . . .

APU GEN, GEN 1(2), EXT PWR.

(4)

In the cockpit, put WARNING NOTICE(S) to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(5)

In the cockpit, on the APU section of the overhead panel 25VU, put WARNING NOTICE(S) to tell persons not to start the APU.

Subtask 24-51-51-865-050-A C.

Open, safety and tag this(these) circuit breaker(s):

PANEL FOR FIN 15XN1 123VU

BUS 1/131XP-A/SPLY

5XN1

AB12

FOR FIN 15XN2 123VU

BUS 2/231XP-A/SPLY

5XN2

AB01

4.

DESIGNATION

FIN

LOCATION

Procedure (Ref. Fig. 24-51-51-991-00100-A - Autotransformers) Subtask 24-51-51-020-050-A A.

AES

Removal of the Autotransformer (1)

Disconnect the electrical connector (1).

(2)

Put blanking caps on the disconnected electrical connectors (1) and (5).

(3)

Loosen the 4 screws (4).

(4)

Hold the transformer (2).

(5)

Remove the screws (4) and the washers (3).

(6)

Remove the transformer (2).

24-51-51 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 120VU

A A

120VU 122VU

6 15XN1 121VU

124VU

B

15XN2

125VU

123VU

120VU

B

3 2

4

1

5

N_MM_245151_4_AAM0_01_00

AES

FIGURE 24-51-51-991-00100-A SHEET 1 Autotransformers

24-51-51 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-51-51-400-001-A Installation of the 115/26VAC Autotransformer WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 15XN1, 15XN2 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

(Ref. Fig. 24-51-51-991-00100-A - Autotransformers) FOR FIN 15XN1(A/XFMR-115/26VAC, 1) 31-60-00-860-001-A 31-60-00-860-002-A 3.

EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 24-51-51-860-051-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(2)

Make sure that the access door 121AL is open.

(3)

Make sure that the external power connector is not connected to the aircraft receptacle.

(4)

Make sure that, on the access door 121AL, there is a WARNING NOTICE(S) to tell persons not to connect the external power connector.

24-51-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (5)

In the cockpit, on the overhead ELEC panel 35VU, make sure that these pushbutton switches are released: . BAT 1, BAT 2, . APU GEN, . GEN 1, GEN 2, . EXT PWR.

(6)

Make sure that there is a WARNING NOTICE(S) in the cockpit to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(7)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

(8)

In the cockpit, make sure that the panel (6) which gives access to the panel 122VU is removed.

Subtask 24-51-51-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL FOR FIN 15XN1 123VU

BUS 1/131XP-A/SPLY

5XN1

AB12

FOR FIN 15XN2 123VU

BUS 2/231XP-A/SPLY

5XN2

AB01

4.

DESIGNATION

FIN

LOCATION

Procedure (Ref. Fig. 24-51-51-991-00100-A - Autotransformers) Subtask 24-51-51-420-050-A A.

Installation of the Autotransformer (1)

Put the transformer (2) in position.

(2)

Install the washers (3) and the screws (4) and then tighten the screws.

(3)

Remove the blanking caps from the electrical connectors (1) and (5).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (1).

Subtask 24-51-51-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL FOR FIN 15XN1 123VU

DESIGNATION

FIN

LOCATION

BUS 1/131XP-A/SPLY

5XN1

AB12

FOR FIN 15XN2 123VU

BUS 2/231XP-A/SPLY

5XN2

AB01

Subtask 24-51-51-710-050-A C.

Operational Test of the Autotransformer (1)

AES

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

(3)

5.

FOR 15XN1 (A/XFMR-115/26VAC, 1) (a)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(b)

Get the HYD page.

(c)

Make sure that there is no cross on the HYDRAULIC quantity indications.

(d)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

FOR 15XN2 (A/XFMR-115/26VAC, 2) (a)

On the ADIRS CDU, put the OFF/NAV/ATT selector switch of the ADIRU 2 in NAV position.

(b)

Make sure that the FAULT legend on the ADR 2 pushbutton switch does not remain on.

Close-up Subtask 24-51-51-862-050-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-51-51-410-050-A B.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the warning notice(s).

(3)

Install the panel (6) which gives access to panel 122VU.

(4)

Close the access door 121AL.

(5)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-51-55-000-001-A Removal of the AC Service Bus Normal Supply Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 12XN 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 25-11-41-000-001-A

DESIGNATION Removal of the Third Occupant Seat

(Ref. Fig. 24-51-55-991-00100-A - Contactor) (Ref. Fig. 24-51-55-991-00100-B - Contactor) 3.

Job Set-up Subtask 24-51-55-010-050-A A.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

Remove the front panel (8) of the panel 123VU.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-51-55-860-050-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Put WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

(4)

In the cockpit, put WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

Subtask 24-51-55-865-050-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

DESIGNATION ELEC/AC PWR/SVCE/CTL

122VU 4.

FIN 3XX

LOCATION V29

Procedure

** On A/C 003-004 (Ref. Fig. 24-51-55-991-00100-A - Contactor) ** On A/C 005-099 (Ref. Fig. 24-51-55-991-00100-B - Contactor) ** On A/C ALL Subtask 24-51-55-020-050-A A.

Removal of the Contactor CAUTION :

(1)

Disconnect the electrical connector (1).

(2)

Put blanking caps on the disconnected electrical connector (1) and electrical receptacle (7).

(3)

Loosen the captive screws (2). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (2) and the spring washers from the contactor (3).

Remove the contactor (3).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

A 122VU

123VU

B

121VU 12XN

125VU

124VU 123VU

8

A

6 5

B

2

3

CONTACTOR

CONTACTOR BASE

7 1

N_MM_245155_4_AAM0_01_00

AES

FIGURE 24-51-55-991-00100-A SHEET 1 Contactor

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A 123VU

122VU

B 121VU

125VU

124VU

12XN

123VU 8

20XX

A

B 3

2 6

MODULE 20XX

CONTACTOR

7 1

N_MM_245155_4_AAP0_01_00

AES

FIGURE 24-51-55-991-00100-B SHEET 1 Contactor

24-51-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-51-55-400-001-A Installation of the AC Service Bus Normal Supply Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 12XN 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

No specific

B.

WARNING NOTICE(S) Torque wrench: range to between 0.00 and 1.20 M.DAN (0.00 and 9.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-11-41-000-001-A

Removal of the Third Occupant Seat

25-11-41-400-001-A

Installation of the Third Occupant Seat

(Ref. Fig. 24-51-55-991-00100-A - Contactor) (Ref. Fig. 24-51-55-991-00100-B - Contactor) 3.

Job Set-up Subtask 24-51-55-860-051-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(2)

Make sure that the access door 121AL is open.

(3)

Make sure that the external power connector is not connected to the aircraft receptacle.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

Make sure that, on the access door 121AL, there is a WARNING NOTICE(S) to tell persons not to connect the external power connector.

(5)

In the cockpit, on the overhead ELEC panel 35VU, make sure that these pushbutton switches are released: . BAT 1, BAT 2, . APU GEN, . GEN 1, GEN 2, . EXT PWR.

(6)

Make sure that there is a WARNING NOTICE(S) in the cockpit to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(7)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

(8)

In the cockpit, make sure that the third occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(9)

Make sure that the front panel (8) of the panel 123VU is removed.

Subtask 24-51-55-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

122VU 4.

DESIGNATION ELEC/AC PWR/SVCE/CTL

FIN 3XX

LOCATION V29

Procedure

** On A/C 003-004 (Ref. Fig. 24-51-55-991-00100-A - Contactor) ** On A/C 005-099 (Ref. Fig. 24-51-55-991-00100-B - Contactor) ** On A/C 003-004 Subtask 24-51-55-420-050-A A.

Installation of the Contactor (1)

Install the contactor (3) on the 6 tapped barrels (5) of the contactor base (6).

(2)

TORQUE the six captive screws (2) to between 0.14 and 0.17 M.DAN (12.39 and 15.04 LBF.IN).

(3)

Remove the blanking caps from the electrical connectors (1) and (7).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (1).

** On A/C 005-099 Subtask 24-51-55-420-050-B A.

AES

Installation of the Contactor (1)

Install the contactor (3) on the module 20XX (6).

(2)

TORQUE the six captive screws (2) to between 0.14 and 0.17 M.DAN (12.39 and 15.04 LBF.IN).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the blanking caps from the electrical connector (1) and the electrical receptacle (7).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (1) to the contactor (3).

** On A/C ALL Subtask 24-51-55-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

DESIGNATION ELEC/AC PWR/SVCE/CTL

122VU

FIN 3XX

LOCATION V29

Subtask 24-51-55-710-050-A C.

5.

Test of Lights in the Cockpit (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

On the FWD ATTENDANT panel 120RH, push the MAIN ON pushbutton switch. Make sure that these lights come on: . CEILING FWD RH, . CEILING AFT RH, . WINDOW FWD LH, . WINDOW AFT LH.

Close-up Subtask 24-51-55-862-050-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-51-55-410-050-A B.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the front panel (8) of the panel 123VU.

(3)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

24-51-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-51-55-000-002-A Removal of the Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 27XN 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE (Ref. Fig. 24-51-55-991-00300-B - Contactor) 3.

DESIGNATION

Job Set-up Subtask 24-51-55-010-051-A A.

Get Access (1)

In the cockpit, remove the panel (6) which gives access to the panel 122VU. The panel 122VU is at the top of the panel 120VU.

(2)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(3)

Open the access door 121AL.

Subtask 24-51-55-860-052-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft external power receptacle.

(2)

Put WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft external power receptacle.

(3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2. APU GEN. GEN 1, GEN 2. EXT PWR.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

In the cockpit, put a WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section). . 25VU (APU section). . 35VU (ELEC).

Subtask 24-51-55-865-053-A C.

Open, safety and tag this(these) circuit breaker(s):

122VU

PANEL

DESIGNATION ELEC/AC SHED BUS/CNTOR

26XN

U25

123VU

SHED BUS/218XP/220XP SPLY

28XN

AC02

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-51-55-991-00300-B - Contactor) Subtask 24-51-55-020-052-B A.

Removal of the Contactor CAUTION :

(1)

Disconnect the electrical connector (4) from the electrical receptacle (5).

(2)

Put CAP - BLANKING on the disconnected electrical connector (4) and the electrical receptacle (5).

(3)

Loosen the six captive screws (2). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (2) and the spring washers from the contactor (3).

Remove the contactor (3) from the module (1).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

A A

122VU 122VU

6 121VU

125VU

124VU 123VU

27XN

B

1

B

2

3

4 5 N_MM_245155_4_AAS0_01_00

AES

FIGURE 24-51-55-991-00300-B SHEET 1 Contactor

24-51-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-51-55-400-002-A Installation of the Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 27XN 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

No specific

B.

WARNING NOTICE(S) Torque wrench: range to between 0.00 and 1.20 M.DAN (0.00 and 9.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

(Ref. Fig. 24-51-55-991-00300-B - Contactor) 3.

Job Set-up Subtask 24-51-55-860-053-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(2)

Make sure that the access door 121AL is open.

(3)

Make sure that the external power connector is not connected to the aircraft receptacle.

(4)

Make sure that, on the access door 121AL, a WARNING NOTICE(S) is in position to tell persons not to connect the external power connector.

(5)

In the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: . BAT 1, BAT 2.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . . .

APU GEN. GEN 1, GEN 2. EXT PWR.

(6)

Make sure that a WARNING NOTICE(S) is in position in the cockpit to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section). . 25VU (APU section). . 35VU (ELEC).

(7)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

(8)

In the cockpit, make sure that the panel (6) which gives access to the panel 122VU is removed.

Subtask 24-51-55-865-054-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

122VU

PANEL

DESIGNATION ELEC/AC SHED BUS/CNTOR

26XN

U25

123VU

SHED BUS/218XP/220XP SPLY

28XN

AC02

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-51-55-991-00300-B - Contactor) Subtask 24-51-55-420-052-B A.

Installation of the Contactor (1)

Remove blanking caps from the electrical receptacle (5).

(2)

Install the contactor (3) on the module (1).

(3)

TORQUE the six captive screws (2) to between 0.15 and 0.18 M.DAN (13.27 and 15.93 LBF.IN).

(4)

Remove the blanking caps from the electrical connector(s).

(5)

Make sure that the electrical connectors are clean and in the correct condition.

(6)

Connect the electrical connector (4) to the electrical receptacle (5).

Subtask 24-51-55-865-055-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

122VU

DESIGNATION ELEC/AC SHED BUS/CNTOR

FIN

LOCATION

26XN

U25

123VU

SHED BUS/218XP/220XP SPLY

28XN

AC02

Subtask 24-51-55-710-051-B C.

AES

Test (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

On the overhead ELEC panel 35VU, push the ELEC/COMMERCIAL pushbutton switch (22XN) (the white indication light goes off).

(3)

On the overhead ELEC panel 35VU, push the GALY & CAB pushbutton switch (2XA) (the white indication light goes off).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

5.

(4)

On the rear panel 120VU, make sure that there is 115VAC on busbars 218XP and 220XP.

(5)

On the overhead ELEC panel 35VU, release the GALY & CAB pushbutton switch (2XA) (the white indication light goes on).

(6)

On the overhead ELEC panel 35VU, release the ELEC/COMMERCIAL pushbutton switch (22XN) (the white indication light goes on).

Close-up Subtask 24-51-55-410-051-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the panel (6) of the panel 122VU.

(3)

Remove the warning notice(s).

(4)

Close the access door 121AL.

(5)

Remove the access platform(s).

Subtask 24-51-55-862-051-A B.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AC ESSENTIAL DISTRIBUTION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General (Ref. Fig. 24-52-00-11200-B - AC Essential Distribution - Block Diagram) The AC essential distribution network corresponds to busbars 4XP (115 VAC ESS bus) and 8XP (115 VAC SHED essential bus) and their associated sub-busbars.

AES

24-52-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-52-00-12400-A - AC Essential Distribution - Component Location) (Ref. Fig. 24-52-00-12500-A - AC Essential Distribution - Component Location) FIN

FUNCTIONAL DESIGNATION

5XH

A/XFMR-115/26VAC, ESS

8XH

CNTOR-AC SHED ESS BUS

AES

PANEL

106VU

ZONE ACCESS ATA REF. DOOR 125 24-52-51 125

24-52-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

Operation

** On A/C 003-004 The AC essential distribution network can be supplied: . either by 115 VAC BUS1 1XP, . or by 115 VAC BUS2 2XP in case of loss of power from main busbar 1XP (in this case, the crew has to select ALTN on AC ESS FEED pushbutton switch to recover 115 VAC ESS BUS), . or by the emergency generator in emergency configuration or smoke emergency configuration, . or by the static inverter in emergency configuration during RAT extension and when the landing gear is extended. The major part of this network is supplied with three-phase 115 VAC/400 Hz. A 115/26 VAC single-phase autotransformer, identical to those of the main distribution supplies an essential 26 VAC/400 Hz sub-busbar (431XP-A). In case of loss of supply of 115 VAC ESS bus and 115 VAC SHED bus, a warning is tiggered on the ECAM (Ref. Fig. 24-52-00-13900-A - AC Essential Distribution - ECAM Warnings) (Ref. Fig. 24-52-00-14000-A - 115 VAC SHED BUS - Upper and Lower ECAM Display Unit) (Ref. Fig. 24-52-00-14100-A - Loss of the 115 VAC ESS BUS (Class 1 - Level 2)) NOTE :

Part of this network (115 VAC SHED BUS 8XP) is automatically shed in emergency configuration when the static inverter is operating.

** On A/C 005-099 The AC essential distribution network can be supplied: . either by 115 VAC BUS1 1XP, . or by 115 VAC BUS2 2XP in case of loss of power from main busbar 1XP (in this case, the crew has to select ALTN on AC ESS FEED pushbutton switch to recover 115 VAC ESS BUS), . or by the emergency generator in emergency configuration or smoke emergency configuration, . or by the static inverter in emergency configuration during RAT extension and when the CSM/G is switched off after landing. The major part of this network is supplied with three-phase 115 VAC/400 Hz. A 115/26 VAC single-phase autotransformer, identical to those of the main distribution supplies an essential 26 VAC/400 Hz sub-busbar (431XP-A). In case of loss of supply of 115 VAC ESS bus and 115 VAC SHED bus, a warning is triggered on the ECAM (Ref. Fig. 24-52-00-13900-A - AC Essential Distribution - ECAM Warnings) (Ref. Fig. 24-52-00-14000-A - 115 VAC SHED BUS - Upper and Lower ECAM Display Unit) (Ref. Fig. 24-52-00-14100-A - Loss of the 115 VAC ESS BUS (Class 1 - Level 2)) NOTE :

AES

Part of this network (115 VAC SHED bus 8XP) is automatically shed in emergency configuration when the static inverter is operating.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

24−35−00 24−34−00

801XP AC SHED ESS BUS 8XP

1PE ESS TR

115VAC 8XH 431XP−A

26V

4XH

5XH 401XP 115VAC 24−32−00

24−50−00

AC BUS 1

1XP 115VAC

AC ESS BUS

1XC

24−50−00

4XP

2XC

3XC

AC BUS 2

2XP 115VAC

24−32−00 24−50−00 4PE

15XE 24−28−00

GCL−1 9XU1

GCU−1 1XU1

GEN 1

4000XU

BTC−1 11XU1

FUEL PUMPS 28−21−00 GCU−APU 1XS

BTC−2 11XU2

EPC 3XG

GLC−APU 3XS

GLC−2 9XU2

GLC−EMERG 2XE

24−42−00 24−50−00

APU GEN

8XS

GPCU 1XG

EXTERNAL POWER RECEPTACLE

GCU−2 1XU2

GEN 2

4000XU

CSM/G CONTROL UNIT 1XE

CSM/G 8XE

N_MM_245200_0_AAL0_01_00

AES

FIGURE 24-52-00-11200-B SHEET 1 AC Essential Distribution - Block Diagram

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR13 FR15

121AL 812

A 106VU 8XH

A FR16

B

FR9

B

N_MM_245200_0_ACM0_01_00

AES

FIGURE 24-52-00-12400-A SHEET 1 AC Essential Distribution - Component Location

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

Z125

FR13

A

FR12

5XH

N_MM_245200_0_AEM0_01_00

AES

FIGURE 24-52-00-12500-A SHEET 1 AC Essential Distribution - Component Location

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

FWC 2 DATA BUS 2

SDAC 2 DATA BUS 2

FWC−1

BUS TO FWC 2 FWC 1 SDAC 1 DATA BUS 2 DATA BUS 2

BUS SDAC 1 DATA BUS 1

4XP 115VAC ESS BUS

SDAC−1

OFF

3XH

ON

AC ESS/AC ESS SHED CNTOR OFF

BUS

TO SDAC−2

7XH

6XH

801XP 115VAC ESS BUS/ SHEDDABLE

** On A/C ALL

N_MM_245200_0_AGM0_01_00

AES

FIGURE 24-52-00-13900-A SHEET 1 AC Essential Distribution - ECAM Warnings

24-52-00 PB001

Page 7 May 01/12 Revision n˚: 40

AES

FIGURE 24-52-00-14000-A SHEET 1 115 VAC SHED BUS - Upper and Lower ECAM Display Unit

− ACTION ON CLEAR P/BSW (ON ECAM CP)

− SELECT ATC SYS 2

MANUAL CREW ACTION

LOSS OF AC SHEDDABLE ESS BUS

CONFIG. SYSTEM OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

AC ESS BUS SHED

NORMAL CONFIG.

− ATC........................SYS 2

ELEC

ECAM UPPER DISPLAY

AC ESS BUS SHED (CLASS 1 − LEVEL 2)

NORMAL CONFIG.

RETURN TO PRESELELECTED PAGE

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_245200_0_AJM0_01_00

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

BAT 2 28V 0A

DC BAT

DC 1

DC 2 DC ESS

TR 1 28V 11 0A

AC 1

ESS TR

EMER GEN

AC ESS

TR 2 28V 82A

AC 2

SHED GEN 1 62% 11 6 V 400 HZ IDG 1

APU GEN

° C110

GEN 2 60% 11 6 V 400 HZ 110C °

IDG 2

4WT2 DU − ECAM, LOWER

N_MM_245200_0_AJM0_02_00

AES

FIGURE 24-52-00-14000-A SHEET 2 115 VAC SHED BUS - Upper and Lower ECAM Display Unit

24-52-00 PB001

Page 9 May 01/12 Revision n˚: 40

AES

FIGURE 24-52-00-14100-A SHEET 1 Loss of the 115 VAC ESS BUS (Class 1 - Level 2)

− ATC SYS2

− EIS DMC SWTG CAPT

− ALTN

SELECT:

MANUAL CREW ACTION

AC ESS BUS SUPPLIED BY AC2

LOSS OF AC ESS BUS

CONFIG. SYSTEM

WHITE "ALTN "

ALTN

FAULT

AC ESS FEED

AMBER "FAULT "

ALTN

FAULT

AC ESS FEED

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

NORMAL CONFIG.

ECAM UPPER DISPLAY

AC ESS BUS FAULT (CLASS 1 − LEVEL 2)

NORMAL CONFIG.

PAGE

PRESELECTED

RETURN TO

− ATC....................SYS2

− EIS DMC SWTG....CAPT3

− IF UNSUCCESSFUL:

ELEC AC ESS BUS FAULT AC ESS FEED.........ALTN

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_245200_0_AKM0_01_00

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

TRANSFORMER - 115/26VAC - REMOVAL/INSTALLATION ** On A/C ALL Task 24-52-51-000-001-A Removal of the Essential 115/26VAC Autotransformer FIN 5XH 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

B.

Work Zones and Access Panels ZONE/ACCESS

125 812

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-42-00-861-001-A

DESIGNATION Energize the Ground Service Network from the External Power

(Ref. Fig. 24-52-51-991-00100-A - AutoTransformer) 3.

Job Set-up Subtask 24-52-51-861-051-A A.

Energize the ground service network (Ref. TASK 24-42-00-861-001-A).

Subtask 24-52-51-010-050-A B.

Get access to the Avionics Compartment (1)

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access door 812 to get access to the avionics compartment.

(2)

Open the access door 812.

(3)

Open the access panel of the AC/DC emergency power center 106VU.

Subtask 24-52-51-865-050-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

106VU

AES

DESIGNATION 26VAC/ESS BUS/SPLY

FIN 4XH

LOCATION B06

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Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-52-51-991-00100-A - AutoTransformer) Subtask 24-52-51-020-050-A A.

AES

Removal of the Autotransformer (1)

Disconnect the electrical connector (3).

(2)

Put blanking caps on the disconnected electrical connector(s).

(3)

Loosen the 4 screws (4).

(4)

Hold the transformer (1).

(5)

Remove the screws (4) and the washers (5).

(6)

Remove the transformer (1).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

5XH

A

B A

FR13 Z 125

FR12

B

1 2 3

5

4

N_MM_245251_4_AAM0_01_00

AES

FIGURE 24-52-51-991-00100-A SHEET 1 AutoTransformer

24-52-51 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-52-51-400-001-A Installation of the Essential 115/26VAC Autotransformer FIN 5XH 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

125 812

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

24-42-00-861-001-A

Energize the Ground Service Network from the External Power

(Ref. Fig. 24-52-51-991-00100-A - AutoTransformer) 3.

Job Set-up Subtask 24-52-51-860-050-A A.

Aircraft Maintenance Configuration (1)

Make sure that the ground service network is energized (Ref. TASK 24-42-00-861-001-A).

(2)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 812.

(3)

Make sure that the access door 812 is open.

(4)

Make sure that the access panel of the AC/DC emergency power center 106VU is open.

Subtask 24-52-51-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

106VU

AES

DESIGNATION 26VAC/ESS BUS/SPLY

FIN 4XH

LOCATION B06

24-52-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-52-51-991-00100-A - AutoTransformer) Subtask 24-52-51-420-050-A A.

Installation of the Autotransformer (1)

Put the transformer (1) in position.

(2)

Install the washers (5) and the screws (4), then tighten the screws.

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (3).

Subtask 24-52-51-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

DESIGNATION 26VAC/ESS BUS/SPLY

106VU

FIN 4XH

LOCATION B06

Subtask 24-52-51-710-050-A C.

5.

Test of the Essential 115/26 VAC Autotransformer (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

On the ADIRS CDU, put the OFF/NAV/ATT selector switch of the ADIRU 1 and ADIRU 3 in NAV position.

(3)

Make sure that the FAULT legend on the ADR 1 and ADR 3 pushbutton switches does not stay on.

(4)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Close-up Subtask 24-52-51-410-050-A A.

AES

Close Access (1)

In the avionics compartment, close the access panel of the AC/DC emergency power center 106VU.

(2)

Close the access door 812.

(3)

Remove the access platform(s).

24-52-51 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-52-55-000-001-A Removal of the AC Shed Essential Bus Contactor FIN 8XH 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE (Ref. Fig. 24-52-55-991-00100-A - AC SHED ESS BUS Contactor) 3.

DESIGNATION

Job Set-up Subtask 24-52-55-010-050-A A.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the avionics compartment doors 812 and 822.

(2)

Open the access doors 812 and 822.

(3)

Open the access panels of the AC/DC emergency power center 106VU and the access panels of the BATTERY power center 105VU.

Subtask 24-52-55-865-050-A B.

Open, safety and tag this(these) circuit breaker(s):

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

AC/SHED/ESS BUS/CNTOR/CTL

1XH

C04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

AES

FIN

LOCATION

24-52-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL

DESIGNATION AC ESS/BUS ON/BUS 2

123VU 4.

FIN 2XC

LOCATION AC01

Procedure (Ref. Fig. 24-52-55-991-00100-A - AC SHED ESS BUS Contactor) Subtask 24-52-55-020-050-A A.

Removal of the Contactor (1)

Loosen the 3 captive screws (1). NOTE :

(2)

AES

Do not remove the captive screws (1) and the spring washers from the contactor (2).

Remove the contactor (2).

24-52-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR16 FR12

A 106VU 822 8XH

A

812

105VU

B

CONTACTOR BASE

3

B

1

2

CONTACTOR

N_MM_245255_4_AAM0_01_00

AES

FIGURE 24-52-55-991-00100-A SHEET 1 AC SHED ESS BUS Contactor

24-52-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-52-55-400-001-A Installation of the AC Shed Essential Bus Contactor FIN 8XH 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

B.

Torque wrench: range to between 0.00 and 1.20 M.DAN (0.00 and 9.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

812, 822 C.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

(Ref. Fig. 24-52-55-991-00100-A - AC SHED ESS BUS Contactor) 3.

Job Set-up Subtask 24-52-55-860-050-A A.

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access doors 812 and 822.

(2)

Make sure that the access doors 812 and 822 are open.

(3)

In the avionics compartment, make sure that the access panel of the AC/DC emergency power center 106VU and BATTERY power center 105VU are open.

Subtask 24-52-55-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

105VU

AES

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

FIN 7XE

LOCATION C01

24-52-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

106VU

PANEL

DESIGNATION CSM/G /EV/MAN/SPLY

6XE

B04

106VU

AC/SHED/ESS BUS/CNTOR/CTL

1XH

C04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-52-55-991-00100-A - AC SHED ESS BUS Contactor) Subtask 24-52-55-420-050-A A.

Installation of the Contactor (1)

Install the contactor (2) on the 3 tapped barrels (3) of the contactor base.

(2)

TORQUE the 3 captive screws (1) to between 0.05 and 0.068 M.DAN (4.42 and 6.02 LBF.IN).

Subtask 24-52-55-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

105VU

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

FIN

LOCATION

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

AC/SHED/ESS BUS/CNTOR/CTL

1XH

C04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

Subtask 24-52-55-710-050-A C.

AES

Test of the AC Shed Essential Bus Contactor (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

Make sure that the AC SHED ESS BUS OFF warning does not come into view.

(4)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(5)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-52-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-52-55-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

In the avionics compartment, close the access panels of the AC/DC emergency power center 106VU and the BATTERY power center 105VU.

(3)

Close the access doors 812 and 822.

(4)

Remove the access platform(s).

24-52-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

GALLEY SUPPLY - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The power supply provides the galleys with 115 V AC. There are 50 KVA available for all galleys. This power is divided into two parts, the AFT galley power with 30 KVA and the FWD galley power with 20 KVA. The galleys are electrically connected with cable lugs to the aircraft terminal blocks.

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location

** On A/C 005-099 (Ref. Fig. 24-56-00-12300-B - Galley Supply - Component Location) ------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANEL I ZONE I ACCESS I I I I DOOR ------------------------------------------------------------------------------4MC CONTACTOR 220 5MC CONTACTOR 220 6MC CONTACTOR 220 13MC CONTACTOR 220 15MC CONTACTOR 220 17MC CONTACTOR 220 6475MM GALLEY (LOC.I) 222 6478MM GALLEY (LOC.II) 222 6483MM GALLEY (LOC.V) 262 ** On A/C 003-004 (Ref. Fig. 24-56-00-12300-B - Galley Supply - Component Location) ------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANEL I ZONE I ACCESS I I I I DOOR ------------------------------------------------------------------------------4MC CONTACTOR 220 5MC CONTACTOR 220 6MC CONTACTOR 220 13MC CONTACTOR 220 15MC CONTACTOR 220 17MC CONTACTOR 220 6475MM GALLEY (LOC.I) 222 6483MM GALLEY (LOC.V) 262

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description

** On A/C 003-004 (Ref. Fig. 24-56-00-14600-H - Galley Power Supply and Distribution - Schematic) ** On A/C 005-099 (Ref. Fig. 24-56-00-14600-B - Galley Power Supply and Distribution - Schematic) The power supply provides the galley assemblies with 115 V AC through the three phase normal busbars 1XP and 2XP. Six triple core wires (feeders A to F) distribute the power to terminal blocks in the forward and aft galley area. Vendor wiring distributes the power to the galley units. The wiring is connected to the terminal blocks by the electrical connector. The maximum available load for all galleys is 50 KVA. The load is distributed as follows: . Network 1 = feeder A, B and E with 30 KVA, . Network 2 = feeder C, D and F with 20 KVA. Circuit breakers protect the feeders. Power contactors switch the power.

AES

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Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 4.

Operation/Control and Indicating The power contactors for the galleys are controlled through control relays as follows: With the APU generator running or with external power supplied you can supply all feeders with power (on the ground). With both engine driven generators running, you can supply all feeders with power (on the ground or in flight). With only engine 1 driven generator running, only feeders B and D is supplied. Feeders A, C, E and F are shed automatically (on the ground or in flight). You can manually shed all the feeders to the galley with the pushbutton switch 2XA GALLEY OFF in the cockpit (on the overhead panel 35VU).

AES

24-56-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A OVERHEAD PANEL 35VU

GALLEY AT LOCATION II

Z220 2XA

GALLEY AT LOCATION I

6478MM

GALLEY AT LOCATION V Z260

FR23 6475MM

FR13 6483MM

FR70

FR63

N_MM_245600_0_AAN0_01_00

AES

FIGURE 24-56-00-12300-B SHEET 1 Galley Supply - Component Location

24-56-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR20

FR21

200VU Z220

A

FR23

FR13

A 200VU

5MC

17MC 6MC

16MC

200VU

13MC

EQUIPMENT TYPE MICRO CONTACTOR

4MC

CONTACTOR

N_MM_245600_0_AAN0_02_00

AES

FIGURE 24-56-00-12300-B SHEET 2 Galley Supply - Component Location

24-56-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 1

2XP AC BUS 2 115VAC

2 123VU 3MC C/B MAIN GALLEY A

3 4 120VU 42XU4 CT−AC2

200VU 6MC

5

1XP AC BUS 1 115VAC

6 7

123VU 12MC C/B GALLEY B 1XP AC BUS 1 115VAC

1XP AC BUS 1 115VAC

1XP AC BUS 1 115VAC

200VU 13MC

8 9 10 11

123VU 14MC C/B MAIN GALLEY E

200VU 15MC

13 14 15

123VU 1MC C/B MAIN GALLEY C

200VU 4MC

16 17

123VU 16MC C/B MAIN GALLEY F POWER

18 19 120VU 42XU3 CT−AC1

200VU 17MC

20

2XP AC BUS 2 115VAC

21 123VU 2MC C/B GALLEY D

601PP SVCE BUS 28VDC

601PP SVCE BUS 28VDC

12

122VU/B 7MC C/B ELEC GALLEY CONTACTOR

22

120VU 42XU4 CT−AC2

200VU 5MC 23

UNSD

24

UNSD

FAULT

UNSD

OFF UNSD

UNSD

1XA C / B 122VU ELEC GALLEY CONTROL

UNSD

35VU 2XA P/BSW ELEC GALLEY AUTO

103VU 4XA RELAY GROUND FAIL MONG

103VU 5XA RELAY GALLEY SPLY CTL 25 26 N_MM_245600_0_ACNA_01_00

AES

FIGURE 24-56-00-14600-B SHEET 1 Galley Power Supply and Distribution - Schematic

24-56-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 1 2

15.0 KVA/43.5A

3 4

5.0 KVA/14.5A

5 6

10.0 KVA/29.0A

7 AFT GALLEY LOCATION 5

8 9 10 11

12 13

5.0 KVA/14.5A

14 15

16 17

10.0 KVA/9.0A

18 19 5.0 KVA/14.5A

20

GALLEY LOCATION 2

21 22

5.0 KVA/14.5A 23 24 10.0 KVA/9.0A

5.0 KVA/14.5A

25 26

103VU 9XA RELAY GALLEY SPLY CONTROL

103VU 6XA RELAY MAN GALLEY SPLY CONTROL

GALLEY LOCATION 1 FWD DOOR 1

N_MM_245600_0_ACNA_02_00

AES

FIGURE 24-56-00-14600-B SHEET 2 Galley Power Supply and Distribution - Schematic

24-56-00 PB001

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 1

2XP AC BUS 2 115VAC

2 123VU 3MC C/B MAIN AFT GALLEY FEEDER A

3 4 120VU 42XU4 CT−AC2

200VU 6MC

5

1XP AC BUS 1 115VAC

6 7

123VU 12MC C/B AFT GALLEY FEEDER B 1XP AC BUS 1 115VAC

1XP AC BUS 1 115VAC

1XP AC BUS 1 115VAC

200VU 13MC

8 9 10 11

123VU 14MC C/B MAIN AFT GALLEY FEEDER E

200VU 15MC

12 13 14 15

123VU 1MC C/B MAIN FWD GALLEY FEEDER C

200VU 4MC

16 17

123VU 16MC C/B MAIN FWD GALLEY FEEDER F

18 19 120VU 42XU3 CT−AC1

200VU 17MC

20

2XP AC BUS 2 115VAC

21 123VU 2MC C/B FWD GALLEY FEEDER D

601PP SVCE BUS 28VDC 122VU 7MC C/B ELEC GALLEY CONTACTOR 601PP SVCE BUS 28VDC

22

120VU 42XU4 CT−AC2

200VU 5MC

23 24 25 UNSD

26

UNSD

FAULT

UNSD

OFF

UNSD

UNSD 1XA C / B 122VU ELEC GALLEY CONTROL

35VU 2XA P/BSW ELEC GALLEY AUTO

103VU 4XA RELAY GROUND FAIL MONG

103VU 5XA RELAY GALLEY SPLY CTL N_MM_245600_0_ACZA_01_00

AES

FIGURE 24-56-00-14600-H SHEET 1 Galley Power Supply and Distribution - Schematic

24-56-00 PB001

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 1 2

15.0 KVA/43.5A

3 4

5 6

5.0 KVA/14.5A

7

8 9

10.0 KVA/29.0A

10 11

GALLEY LOCATION 5

12 13

5.0 KVA/43.5A

14 15

16 17

10.0 KVA/29.0A

18 19

20 21

5.0 KVA/14.5A

22 GALLEY LOCATION 1 FWD DOOR 1

23 24 25 26

103VU 9XA RELAY GALLEY SPLY CONTROL

103VU 6XA RELAY MAN SPLY CONTROL N_MM_245600_0_ACZA_02_00

AES

FIGURE 24-56-00-14600-H SHEET 2 Galley Power Supply and Distribution - Schematic

24-56-00 PB001

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

GALLEY SUPPLY - DEACTIVATION/REACTIVATION ** On A/C ALL Task 24-56-00-040-001-A Deactivation of the Galley Supply System 1.

Reason for the Job MMEL 24-26-01B Galley Automatic Load Shed System (Old MMEL ref: 24-56-01-A))

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Consumable Materials REFERENCE

No specific C.

DESIGNATION PLACARD

Referenced Information

REFERENCE 11-00-00-400-021-A 24-41-00-861-002-A

DESIGNATION Installation of the Cabin Placards Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

3.

Job Set-up ** On A/C 003-004 Subtask 24-56-00-860-052-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Make sure that the pushbutton switch GALLEY 2XA on the overhead panel 35VU is in the OFF position (white indication light shows OFF).

** On A/C 005-099 Subtask 24-56-00-860-052-B A.

Aircraft Maintenance Configuration (1)

AES

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

24-56-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Make sure that the C/B 1XA on the 122VU is closed.

(3)

Make sure that the pushbutton switch GALLEY 2XA on the overhead panel 35VU is in the OFF position (white indication light shows OFF).

(4)

Make sure that the pushbutton switch ELEC/COMMERCIAL 22XN on the overhead panel 35VU is in the on position (white indication OFF is off).

** On A/C ALL Subtask 24-56-00-865-050-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

FWD GALLEY/FEEDER F

16MC

AC10

FWD GALLEY/FEEDER C

1MC

AE10

122VU

FIN

LOCATION

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

** On A/C 005-099 123VU 4.

Procedure ** On A/C ALL Subtask 24-56-00-040-050-A A.

5.

Deactivation of the Galley Supply (1)

Make sure that the galley electrical panel(s) and galley equipment(s) does (do) not operate.

(2)

Install a PLACARD ”INOP” on the galley electrical panel(s) and galley equipment(s) to tell persons not to use it (Ref. TASK 11-00-00-400-021-A).

(3)

Make an entry in the log book.

Close-up Subtask 24-56-00-862-050-A A.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-56-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-56-00-040-002-A Deactivation of the Galley Supply System 1.

Reason for the Job MMEL 24-26-02A Galley Manual Load Shed System (GALLEY) (Old MMEL ref: 24-56-01-B))

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Consumable Materials REFERENCE

No specific C.

DESIGNATION PLACARD

Referenced Information

REFERENCE 11-00-00-400-021-A 24-41-00-861-002-A

DESIGNATION Installation of the Cabin Placards Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

3.

Job Set-up Subtask 24-56-00-860-055-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Make sure that the C/B 1XA on the 122VU is closed.

(3)

Make sure that the pushbutton switch GALLEY 2XA on the overhead panel 35VU is in the OFF position (white indication light shows OFF).

(4)

Make sure that the pushbutton switch ELEC/COMMERCIAL 22XN on the overhead panel 35VU is in the ON position (white indication OFF is off).

Subtask 24-56-00-865-057-A B.

Open, safety and tag this(these) circuit breaker(s):

122VU

PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

123VU

FWD GALLEY/FEEDER C

1MC

AE10

123VU

FWD GALLEY/FEEDER D

2MC

AD04

AES

FIN

LOCATION

24-56-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

123VU

PANEL

DESIGNATION AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

FWD GALLEY/FEEDER F

16MC

AC10

4.

FIN

LOCATION

Procedure Subtask 24-56-00-040-052-A A.

5.

Deactivation of the Galley Supply (1)

Make sure that the galley electrical panel(s) and galley equipment(s) does (do) not operate.

(2)

Install a PLACARD ”INOP” on the galley electrical panel(s) and galley equipment(s) to tell persons not to use it (Ref. TASK 11-00-00-400-021-A).

(3)

Make an entry in the log book.

Close-up Subtask 24-56-00-862-054-A A.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-56-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 Task 24-56-00-040-003-A Deactivation of the Galley Supply System 1.

Reason for the Job MMEL 24-26-02A Galley Manual Load Shed System (GALLEY) (Old MMEL ref: 24-56-01-B))

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Consumable Materials REFERENCE

No specific C.

DESIGNATION PLACARD

Referenced Information

REFERENCE 11-00-00-400-021-A 24-41-00-861-002-A

DESIGNATION Installation of the Cabin Placards Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

3.

Job Set-up Subtask 24-56-00-860-054-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Make sure that the pushbutton switch GALLEY 2XA on the overhead panel 35VU is in the OFF position (white indication light shows OFF).

Subtask 24-56-00-865-055-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL

122VU

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

122VU

ELEC/GALLEY/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

AES

FIN

LOCATION

24-56-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

123VU

PANEL

DESIGNATION AFT GALLEY/FEEDER E

14MC

AF09

123VU

FWD GALLEY/FEEDER F

16MC

AC10

4.

FIN

LOCATION

Procedure Subtask 24-56-00-040-051-A A.

5.

Deactivation of the Galley Supply (1)

Make sure that the galley electrical panel(s) and galley equipment(s) does (do) not operate.

(2)

Install a PLACARD ”INOP” on the galley electrical panel(s) and galley equipment(s) to tell persons not to use it (Ref. TASK 11-00-00-400-021-A).

(3)

Make an entry in the log book.

Close-up Subtask 24-56-00-862-053-A A.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-56-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-56-00-440-001-A Reactivation of the Galley Supply System 1.

Reason for the Job MMEL 24-26-01B Galley Automatic Load Shed System (Old MMEL ref: 24-56-01-A))

2.

Job Set-up Information A.

Referenced Information

REFERENCE 11-00-00-000-003-A 24-41-00-861-002-A

DESIGNATION Removal of the Cabin Placards Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

TSM 24-56-00-810-801

Galley Supply Fault

3.

Job Set-up Subtask 24-56-00-861-051-A A.

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002A-01) or (Ref. TASK 24-41-00-861-002-A-02).

Subtask 24-56-00-865-051-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

FWD GALLEY/FEEDER F

16MC

AC10

FWD GALLEY/FEEDER C

1MC

AE10

122VU

FIN

LOCATION

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

** On A/C 005-099 123VU

AES

24-56-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure ** On A/C ALL Subtask 24-56-00-440-050-A A.

5.

Reactivation of the Galley Supply (1)

Do the trouble shooting procedure of the galley supply system (Ref. TSM 24-56-00-810-801).

(2)

Remove the PLACARD ”INOP” from the galley electrical panel(s) and galley equipment(s) (Ref. TASK 11-00-00-000-003-A).

(3)

Make an entry in the log book.

Close-up Subtask 24-56-00-862-052-A A.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-56-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-56-00-440-002-A Reactivation of the Galley Supply System 1.

Reason for the Job MMEL 24-26-02A Galley Manual Load Shed System (GALLEY) (Old MMEL ref: 24-56-01-B))

2.

Job Set-up Information A.

Referenced Information

REFERENCE 11-00-00-000-003-A 24-41-00-861-002-A

DESIGNATION Removal of the Cabin Placards Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

TSM 24-56-00-810-801

Galley Supply Fault

3.

Job Set-up Subtask 24-56-00-861-053-A A.

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002A-01) or (Ref. TASK 24-41-00-861-002-A-02).

Subtask 24-56-00-865-059-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

122VU

PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

123VU

FWD GALLEY/FEEDER C

1MC

AE10

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

FWD GALLEY/FEEDER F

16MC

AC10

4.

FIN

LOCATION

Procedure Subtask 24-56-00-440-051-A A.

AES

Reactivation of the Galley Supply (1)

Do the trouble shooting procedure of the galley supply system (Ref. TSM 24-56-00-810-801).

(2)

Remove the PLACARD ”INOP” from the galley electrical panel(s) and galley equipment(s) (Ref. TASK 11-00-00-000-003-A).

(3)

Make an entry in the log book.

24-56-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-56-00-862-055-A A.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-56-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 Task 24-56-00-440-003-A Reactivation of the Galley Supply System 1.

Reason for the Job MMEL 24-26-02A Galley Manual Load Shed System (GALLEY) (Old MMEL ref: 24-56-01-B))

2.

Job Set-up Information A.

Referenced Information

REFERENCE 11-00-00-000-003-A 24-41-00-861-002-A

DESIGNATION Removal of the Cabin Placards Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

TSM 24-56-00-810-801

Galley Supply Fault

3.

Job Set-up Subtask 24-56-00-861-054-A A.

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002A-01) or (Ref. TASK 24-41-00-861-002-A-02).

Subtask 24-56-00-865-060-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

122VU

PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

122VU

ELEC/GALLEY/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

FWD GALLEY/FEEDER F

16MC

AC10

4.

FIN

LOCATION

Procedure Subtask 24-56-00-440-052-A A.

AES

Reactivation of the Galley Supply (1)

Do the trouble shooting procedure of the galley supply system (Ref. TSM 24-56-00-810-801).

(2)

Remove the PLACARD ”INOP” from the galley electrical panel(s) and galley equipment(s) (Ref. TASK 11-00-00-000-003-A).

(3)

Make an entry in the log book.

24-56-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-56-00-862-056-A A.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-56-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

GALLEY SUPPLY - ADJUSTMENT/TEST ** On A/C ALL Task 24-56-00-710-001-A Operational Test of the Galley Supply WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

3.

Job Set-up Subtask 24-56-00-860-050-A A.

Aircraft Maintenance Configuration (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Make sure that the pushbutton switch GALLEY 2XA, on the overhead panel 35VU is in the OFF position (a white indication light shows OFF).

Subtask 24-56-00-865-052-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

122VU

FIN

LOCATION

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

AES

24-56-00 PB501

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

123VU

PANEL

DESIGNATION AFT GALLEY/FEEDER E

14MC

FIN AF09

LOCATION

123VU

FWD GALLEY/FEEDER F

16MC

AC10

FWD GALLEY/FEEDER C

1MC

AE10

** On A/C 005-099 123VU 4.

Procedure ** On A/C ALL Subtask 24-56-00-710-050-A A.

Operational test of the Gally Supply

ACTION 1.On the overhead panel 35VU: . push the GALLEY pushbutton switch 2XA. .

RESULT On the overhead panel 35VU: . the white indicator light goes off.

push and release the GALLEY pushbutton switch 2XA . again.

the white indicator light comes on.

In the FWD and AFT galleys: . no galley equipment operates. 5.

Close-up Subtask 24-56-00-860-051-A A.

AES

Put the aircraft back to the serviceable condition. (1)

In all galleys, make sure that the equipment is off.

(2)

Make sure that the pushbutton switch GALLEY 2XA, on the overhead panel 35VU is in the OFF position (a white indication light shows OFF).

(3)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-56-00 PB501

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - GALLEY SUPPLY - REMOVAL/INSTALLATION ** On A/C ALL Task 24-56-55-000-001-A Removal of the Micro Contactor Located in the Panel 200VU WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 4MC, 5MC, 6MC, 13MC, 15MC, 17MC 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

B.

WARNING NOTICE(S)

Referenced Information

REFERENCE 25-23-41-000-001-A

Removal of the Ceiling Panels

DESIGNATION

25-23-42-000-001-A

Removal of the Ceiling Panels - Forward Utility Area

(Ref. Fig. 24-56-55-991-00100-A - Micro Contactor Located in the Panel 200VU) 3.

Job Set-up ** On A/C 003-004 Subtask 24-56-55-860-050-A A.

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALLEY pushbutton switch is released (the OFF legend is on).

(2)

Put a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALLEY pushbutton switch.

** On A/C 005-099 Subtask 24-56-55-860-050-B A.

AES

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALY & CAB pushbutton switch is released (the OFF legend is on).

(2)

Put a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALY & CAB pushbutton switch.

24-56-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Subtask 24-56-55-010-050-A B.

Removal of the Ceiling Panels (1)

Remove the ceiling panels (Ref. TASK 25-23-41-000-001-A) and the forward utility area ceiling panels (Ref. TASK 25-23-42-000-001-A).

Subtask 24-56-55-865-050-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

FWD GALLEY/FEEDER F

16MC

AC10

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

FWD GALLEY/FEEDER C

1MC

AE10

122VU

FIN

LOCATION

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

** On A/C 005-099 123VU 4.

Procedure

** On A/C ALL (Ref. Fig. 24-56-55-991-00100-A - Micro Contactor Located in the Panel 200VU) Subtask 24-56-55-020-050-A A.

Removal of the micro contactor CAUTION :

AES

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Disconnect the wires (5) from the contactor (6).

(2)

Remove the 6 screws (4) and washers (3).

(3)

Remove the power supply wires (2).

(4)

Loosen the 4 nuts (1).

(5)

Hold the contactor (6).

(6)

Remove the 4 nuts (1).

(7)

Remove the contactor (6).

24-56-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

200VU

A

FR21

A

FR20

200VU

B

B

1

2

3 4 6

5 N_MM_245655_4_AAM0_01_00

AES

FIGURE 24-56-55-991-00100-A SHEET 1 Micro Contactor Located in the Panel 200VU

24-56-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-56-55-400-001-A Installation of the Micro Contactor Located in the Panel 200VU WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 4MC, 5MC, 6MC, 13MC, 15MC, 17MC 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY AR WARNING NOTICE(S)

DESIGNATION

Referenced Information

REFERENCE 25-23-41-400-001-A

DESIGNATION Installation of the Ceiling Panels

25-23-42-400-001-A

Installation of the Ceiling Panels - Forward Utility Area

(Ref. Fig. 24-56-55-991-00100-A - Micro Contactor Located in the Panel 200VU) 3.

Job Set-up ** On A/C 003-004 Subtask 24-56-55-860-051-A A.

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALLEY pushbutton switch is released (the OFF legend is on).

(2)

Make sure that there is a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALLEY pushbutton switch.

** On A/C 005-099 Subtask 24-56-55-860-051-B A.

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALY & CAB pushbutton switch is released (the OFF legend is on).

(2)

Make sure that there is a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALY & CAB pushbutton switch.

** On A/C ALL Subtask 24-56-55-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

122VU

AES

DESIGNATION ELEC/GALLEY/CNTOR

FIN 7MC

LOCATION S28

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Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C 003-004 122VU

DESIGNATION

FIN

LOCATION

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

FWD GALLEY/FEEDER F

16MC

AC10

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

FWD GALLEY/FEEDER C

1MC

AE10

** On A/C 005-099 122VU ** On A/C ALL

** On A/C 005-099 123VU 4.

Procedure

** On A/C ALL (Ref. Fig. 24-56-55-991-00100-A - Micro Contactor Located in the Panel 200VU) Subtask 24-56-55-420-050-A A.

Installation of the micro contactor CAUTION :

5.

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

(1)

Put the contactor (6) in position.

(2)

Install the nuts (1) and tighten them.

(3)

Install the power supply wires (2).

(4)

Install the 6 washers (3) and screws (4). Tighten the screws (4).

(5)

Connect the wires (5) to the contactor (6).

Close-up Subtask 24-56-55-865-052-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

122VU

DESIGNATION ELEC/GALLEY/CNTOR

7MC

FIN S28

LOCATION

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

** On A/C 003-004 122VU ** On A/C 005-099 122VU

AES

24-56-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C ALL

DESIGNATION

FIN

LOCATION

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

FWD GALLEY/FEEDER F

16MC

AC10

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

FWD GALLEY/FEEDER C

1MC

AE10

** On A/C 005-099 123VU ** On A/C ALL Subtask 24-56-55-410-050-A B.

Installation of the Ceiling Panels (1)

Install the ceiling panels (Ref. TASK 25-23-41-400-001-A) and the forward utility area ceiling panels (Ref. TASK 25-23-42-400-001-A).

Subtask 24-56-55-942-050-A C.

AES

Put the aircraft back to its initial configuration. (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the warning notice(s).

24-56-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-56-55-000-002-A Removal of the Contactor Located in the Panel 200VU WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 4MC, 5MC, 6MC, 13MC, 15MC, 17MC 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific

QTY DESIGNATION AR CAP - BLANKING AR SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

B.

WARNING NOTICE(S)

Referenced Information

REFERENCE 25-23-41-000-001-A

Removal of the Ceiling Panels

DESIGNATION

25-23-42-000-001-A

Removal of the Ceiling Panels - Forward Utility Area

(Ref. Fig. 24-56-55-991-00200-A - Contactor Located in the Panel 200VU) 3.

Job Set-up ** On A/C 003-004 Subtask 24-56-55-860-052-A A.

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALLEY pushbutton switch is released (the OFF legend is on).

(2)

Put a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALLEY pushbutton switch.

** On A/C 005-099 Subtask 24-56-55-860-052-B A.

AES

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALY & CAB pushbutton switch is released (the OFF legend is on).

(2)

Put a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALY & CAB pushbutton switch.

24-56-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Subtask 24-56-55-010-051-A B.

Removal of the Ceiling Panels (1)

Remove the ceiling panels (Ref. TASK 25-23-41-000-001-A) and the forward utility area ceiling panels (Ref. TASK 25-23-42-000-001-A).

Subtask 24-56-55-865-053-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

FWD GALLEY/FEEDER F

16MC

AC10

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

FWD GALLEY/FEEDER C

1MC

AE10

122VU

FIN

LOCATION

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

** On A/C 005-099 123VU 4.

Procedure

** On A/C ALL (Ref. Fig. 24-56-55-991-00200-A - Contactor Located in the Panel 200VU) Subtask 24-56-55-020-051-A A.

Removal of the Contactor CAUTION :

(1)

Disconnect the electrical connector (4).

(2)

Put blanking caps on the disconnected electrical connector(s).

(3)

Loosen the 6 captive screws (5). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (5) and the spring washers (6) from the contactor (3).

Remove the contactor (3).

24-56-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

200VU

A

A 200VU

FR21 FR20

B

1

B

2 6 CONTACTOR BASE

CONTACTOR 5

4 3

N_MM_245655_4_BAM0_01_00

AES

FIGURE 24-56-55-991-00200-A SHEET 1 Contactor Located in the Panel 200VU

24-56-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-56-55-400-002-A Installation of the Contactor Located in the Panel 200VU WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 4MC, 5MC, 6MC, 13MC, 15MC, 17MC 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific

B.

QTY AR WARNING NOTICE(S)

DESIGNATION

Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

Referenced Information

REFERENCE 25-23-41-400-001-A

DESIGNATION Installation of the Ceiling Panels

25-23-42-400-001-A

Installation of the Ceiling Panels - Forward Utility Area

(Ref. Fig. 24-56-55-991-00200-A - Contactor Located in the Panel 200VU) 3.

Job Set-up ** On A/C 003-004 Subtask 24-56-55-860-053-A A.

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALLEY pushbutton switch is released (the OFF legend is on).

(2)

Make sure that there is a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALLEY pushbutton switch.

** On A/C 005-099 Subtask 24-56-55-860-053-B A.

AES

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALY & CAB pushbutton switch is released (the OFF legend is on).

(2)

Make sure that there is a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALY & CAB pushbutton switch.

24-56-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Subtask 24-56-55-865-054-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

FWD GALLEY/FEEDER F

16MC

AC10

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

FWD GALLEY/FEEDER C

1MC

AE10

122VU

FIN

LOCATION

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

** On A/C 005-099 123VU 4.

Procedure

** On A/C ALL (Ref. Fig. 24-56-55-991-00200-A - Contactor Located in the Panel 200VU) Subtask 24-56-55-420-051-A A.

Installation of the Contactor CAUTION :

5.

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Install the contactor (3) on the 6 tapped barrels (2) of the contactor base (1).

(2)

TORQUE the captive screws (5) to between 23.90 and 26.55 LBF.IN (0.27 and 0.30 M.DAN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (4).

Close-up Subtask 24-56-55-865-055-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

122VU

AES

DESIGNATION ELEC/GALLEY/CNTOR

FIN 7MC

LOCATION S28

24-56-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL ** On A/C 003-004 122VU

DESIGNATION

FIN

LOCATION

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

FWD GALLEY/FEEDER F

16MC

AC10

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

FWD GALLEY/FEEDER C

1MC

AE10

** On A/C 005-099 122VU ** On A/C ALL

** On A/C 005-099 123VU ** On A/C ALL Subtask 24-56-55-410-051-A B.

Installation of the Ceiling Panels (1)

Install the ceiling panels (Ref. TASK 25-23-41-400-001-A) and the forward utility area ceiling panels (Ref. TASK 25-23-42-400-001-A).

Subtask 24-56-55-942-051-A C.

AES

Put the aircraft back to its initial configuration. (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the warning notice(s).

24-56-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-56-55-000-003-A Removal of the Micro Contactor or/and Contactor Located in the Panel 200VU WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 4MC, 5MC, 6MC, 13MC, 15MC, 17MC 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

B.

WARNING NOTICE(S)

Referenced Information

REFERENCE 24-56-55-000-001-A 24-56-55-000-002-A 25-23-41-000-001-A

DESIGNATION Removal of the Micro Contactor Located in the Panel 200VU Removal of the Contactor Located in the Panel 200VU Removal of the Ceiling Panels

25-23-42-000-001-A

Removal of the Ceiling Panels - Forward Utility Area

(Ref. Fig. 24-56-55-991-00300-E - Micro Contactor or/and Contactor Located in the Panel 200VU) 3.

Job Set-up ** On A/C 003-004 Subtask 24-56-55-860-054-A A.

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALLEY pushbutton switch is released (the OFF legend is on).

(2)

Put a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALLEY pushbutton switch.

** On A/C 005-099 Subtask 24-56-55-860-054-B A.

AES

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALY & CAB pushbutton switch is released (the OFF legend is on).

(2)

Put a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALY & CAB pushbutton switch.

24-56-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Subtask 24-56-55-010-052-A B.

Removal of the Ceiling Panels (1)

Remove the ceiling panels (Ref. TASK 25-23-41-000-001-A) and the forward utility area ceiling panels (Ref. TASK 25-23-42-000-001-A).

Subtask 24-56-55-865-056-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

FWD GALLEY/FEEDER F

16MC

AC10

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

FWD GALLEY/FEEDER C

1MC

AE10

122VU

FIN

LOCATION

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

** On A/C 005-099 123VU 4.

Procedure

** On A/C ALL (Ref. Fig. 24-56-55-991-00300-E - Micro Contactor or/and Contactor Located in the Panel 200VU) Subtask 24-56-55-020-052-A A.

Removal of the Micro Contactor (1)

Remove the micro contactor (Ref. TASK 24-56-55-000-001-A).

Subtask 24-56-55-020-053-A B.

Removal of the Contactor (1)

AES

Remove the contactor (Ref. TASK 24-56-55-000-002-A).

24-56-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

200VU

A

FR21 FR20

A 200VU

5MC

17MC 6MC 4MC

15MC

13MC

200VU

EQUIPMENT TYPE MICRO CONTACTOR CONTACTOR

N_MM_245655_4_CEM0_01_00

AES

FIGURE 24-56-55-991-00300-E SHEET 1 Micro Contactor or/and Contactor Located in the Panel 200VU

24-56-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-56-55-400-003-A Installation of the Micro Contactor or/and Contactor Located in the Panel 200VU WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 4MC, 5MC, 6MC, 13MC, 15MC, 17MC 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY AR WARNING NOTICE(S)

DESIGNATION

Referenced Information

REFERENCE 24-56-00-710-001-A

DESIGNATION Operational Test of the Galley Supply

24-56-55-400-001-A 24-56-55-400-002-A 25-23-41-400-001-A

Installation of the Micro Contactor Located in the Panel 200VU Installation of the Contactor Located in the Panel 200VU Installation of the Ceiling Panels

25-23-42-400-001-A

Installation of the Ceiling Panels - Forward Utility Area

(Ref. Fig. 24-56-55-991-00300-E - Micro Contactor or/and Contactor Located in the Panel 200VU) 3.

Job Set-up ** On A/C 003-004 Subtask 24-56-55-860-055-A A.

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALLEY pushbutton switch is released (the OFF legend is on).

(2)

Make sure that there is a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALLEY pushbutton switch.

** On A/C 005-099 Subtask 24-56-55-860-055-B A.

AES

Safety Precautions (1)

In the cockpit, on the overhead ELEC panel 35VU, make sure that the GALY & CAB pushbutton switch is released (the OFF legend is on).

(2)

Make sure that there is a WARNING NOTICE(S) on the ELEC panel 35VU to tell persons not to operate the GALY & CAB pushbutton switch.

24-56-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Subtask 24-56-55-865-057-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

DESIGNATION ELEC/GALLEY/CNTOR

7MC

S28

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

123VU

FWD GALLEY/FEEDER D

2MC

AD04

123VU

FWD GALLEY/FEEDER F

16MC

AC10

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

FWD GALLEY/FEEDER C

1MC

AE10

122VU

FIN

LOCATION

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL

** On A/C 005-099 123VU 4.

Procedure

** On A/C ALL (Ref. Fig. 24-56-55-991-00300-E - Micro Contactor or/and Contactor Located in the Panel 200VU) Subtask 24-56-55-420-052-A A.

Installation of the Micro Contactor (1)

Install the micro contactor (Ref. TASK 24-56-55-400-001-A).

Subtask 24-56-55-420-053-A B.

Installation of the Contactor (1)

Install the contactor (Ref. TASK 24-56-55-400-002-A).

Subtask 24-56-55-865-058-A C.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

122VU

DESIGNATION ELEC/GALLEY/CNTOR

FIN

LOCATION

7MC

S28

ELEC/GALLEY/CTL

1XA

S26

ELEC/GALY & CAB/CTL

1XA

S26

FWD GALLEY/FEEDER D

2MC

AD04

** On A/C 003-004 122VU ** On A/C 005-099 122VU ** On A/C ALL 123VU

AES

24-56-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

123VU

PANEL

DESIGNATION FWD GALLEY/FEEDER F

16MC

FIN AC10

LOCATION

123VU

AFT GALLEY/FEEDER E

14MC

AF09

123VU

AFT GALLEY/FEEDER A

3MC

AF04

123VU

AFT GALLEY/FEEDER B

12MC

AD09

FWD GALLEY/FEEDER C

1MC

AE10

** On A/C 005-099 123VU ** On A/C ALL Subtask 24-56-55-710-050-A D. 5.

Do an Operational Test of the Galley Supply (Ref. TASK 24-56-00-710-001-A).

Close-up Subtask 24-56-55-410-052-A A.

Installation of the Ceiling Panels (1)

Install the ceiling panels (Ref. TASK 25-23-41-400-001-A) and the forward utility area ceiling panels (Ref. TASK 25-23-42-400-001-A).

Subtask 24-56-55-942-052-A B.

AES

Put the aircraft back to its initial configuration. (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the warning notice(s).

24-56-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC ELECTRICAL LOAD DISTRIBUTION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The DC electrical distribution on board is carried out in several steps corresponding to: . power distribution from the transformers rectifiers towards the main DC busbars located in the DC electrical power center, then from the main busbars towards the associated distribution sub-busbars, . distribution from these sub-busbars towards the different consumers. This chapter deals only with power distribution. The referenced figure gives a schematic summary of the whole DC distribution on board. ** On A/C 003-004 (Ref. Fig. 24-60-00-11300-B - DC Electrical Load Distribution - General) ** On A/C 005-099 (Ref. Fig. 24-60-00-11300-C - DC Electrical Load Distribution - General) This can be broken down as follows: . the DC main distribution connected to 28 VDC BUS1 1PP, 28 VDC BUS2 2PP and 28 VDC BAT BUS 3PP (Ref. 24-61-00, P. Block 1), . the DC essential distribution connected to busbars 28 VDC ESS BUS 4PP and 28 VDC SHED ESS BUS 8PP (Ref. 24-62-00, P. Block 1).

AES

24-60-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-60-00-12600-B - DC Electrical Load Distribution - Component Location) (Ref. Fig. 24-60-00-12800-A - Spare Fuse - Component Location) FIN

FUNCTIONAL DESIGNATION

8PH CNTOR-DC SHED ESS BUS 8PN CNTOR-DC SVCE BUS NORM SPLY ** On A/C 005-099

PANEL 106VU 120VU

ZONE ACCESS ATA REF. DOOR 125 24-62-55 212 24-61-55

10PN CONTACTOR 120VU 212 24-61-55 ------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA I I I I DOOR I REF. ------------------------------------------------------------------------------6PH HOLDER-FUSE 105VU 126 24-62-00 6PH1 FUSE 105VU 126 24-62-00 The main DC power is located in the DC power center 124VU. It mainly contains: . contactors related to channel 1 as well as busses 1PP and 3PP, . contactors related to channel 2 as well as busses 2PP and 6PP, . the APU start contactor. The DC part of the electrical emergency generation is located in the electrical emergency power center 106VU. The battery line contactors are located in the battery power center 105VU.

AES

24-60-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

System Description Different distribution configurations: (See ATA Ref. 24-50-00). In case of loss of the DC BUS 1, DC BUS 2, DC BAT BUS and DC ESS BUS (DC power snag), the crew must extend the RAT by pressing the RAT & EMER GEN/MAN ON pushbutton switch located on the EMER ELEC PWR section of the overhead panel: (Ref. Fig. 24-60-00-14400-A - DC EMER CONFIG - Upper and Lower ECAM Display Unit) (Ref. Fig. 24-60-00-14500-A - DC Emergency Configuration - Supply of the Network by the CSM/G) (Ref. Fig. 24-60-00-14600-A - DC Emergency Configuration - Supply of the Network with the Landing Gear Extended)

AES

24-60-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

801PP 301PP

DC SHED ESS BUS

11PB APU START 49−42−00

5KA

10KA

CSM/G CONTROL UNIT

6XE

6KA 1PB2

BAT2 2PB2

4PB2 6PB2 1PB1

5PB1 4PB1

1PP

1PC1

28VDC

BAT BUS

20PC

BAT1 2PB1

6PB1

5PR

3PB2

DC ESS BUS

4PC

204PP

3PN2 SHUNT

601PP

24−28−00

202PP

1PN2 DC BUS 2

4PP 28VDC

206PP

6PN

1PR

1PC2

28VDC

401PP

8PR 208PP

3PB1

3PP

8PH

501PP

SHUNT

703PP

3PN1

DC BUS 1

701PP

12PB1

BCL−1

101PP

502PP

704PP 12PB2

103PP

2PR

702PP

5PB2

BCL−2

1PN1

8PP 28VDC

2PP

602PP

7PN

28VDC

DC SVCE BUS

8PN

6PP 28VDC

3PX 24−62−00

5PU1

24−28−00 3PE

5PU2

1PX 1PU1 TR1

1PU2 TR2

2PU1

24−50−00

24−50−00 AC BUS 1

1XP

1PE ESS TR

24−25−00

24−25−00

AC BUS 2

2XP 115VAC

115VAC

2PU2

14PU

24−42−00 4PE

24−22−00

24−22−00

24−50−00

24−43−00

24−24−00

N_MM_246000_0_AAL0_01_00

AES

FIGURE 24-60-00-11300-B SHEET 1 DC Electrical Load Distribution - General

24-60-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

801PP 301PP

DC SHED ESS BUS

11PB APU START 49−42−00

5KA

10KA

CSM/G CONTROL UNIT

6XE

6KA 1PB2

BAT2 2PB2

4PB2 6PB2 1PB1

5PB1 4PB1

1PP

1PC1

28VDC

BAT BUS

20PC

BAT1 2PB1

6PB1

5PR

3PB2

DC ESS BUS

4PC

204PP

3PN2 SHUNT

601PP

24−28−00

202PP

1PN2 DC BUS 2

2PP

602PP

7PN

28VDC

DC SVCE BUS

8PN

10PN

11PN

24−62−00

6PP 28VDC

210PP 5PU1

4PP 28VDC

206PP

6PN

1PR

1PC2

28VDC

401PP

8PR 208PP

3PB1

3PP

8PH

501PP

SHUNT

703PP

3PN1

DC BUS 1

701PP

12PB1

BCL−1

101PP

502PP

704PP 12PB2

103PP

2PR

702PP

5PB2

BCL−2

1PN1

8PP 28VDC

3PX

212PP

24−28−00 3PE

5PU2

1PX 1PU1 TR1

1PU2 TR2

2PU1

24−50−00

24−50−00 AC BUS 1

1XP

1PE ESS TR

24−25−00

24−25−00

AC BUS 2

2XP 115VAC

115VAC

2PU2

14PU

24−42−00 4PE

24−22−00

24−22−00

24−50−00

24−43−00

24−24−00

N_MM_246000_0_AAP0_01_00

AES

FIGURE 24-60-00-11300-C SHEET 1 DC Electrical Load Distribution - General

24-60-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

PANEL 49VU PANEL 120VU

122VU

121VU

123VU

124VU

ACCESS DOOR

RADOME

FR1

109VU FR5

811

FWD ELEKS RACK 90VU 108VU

105VU

FR9 FR11

103VU ESS TR TR

FR13

822

BCL1

812 106VU

BAT 1

TR BCL2

FR15

BAT 2

107VU FR17

STATIC INVERTER

NOSE LDG/GR WELL

FR19 FR21

824 FR23

187VU

63VU 188VU

AFT ELEKS RACK 80VU

N_MM_246000_0_ACL0_01_00

AES

FIGURE 24-60-00-12600-B SHEET 1 DC Electrical Load Distribution - Component Location

24-60-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR24

A FR20 FR13

A

FR16

FR1

B

B

SPARE FUSE

N_MM_246000_0_ACP0_01_00

AES

FIGURE 24-60-00-12800-A SHEET 1 Spare Fuse - Component Location

24-60-00 PB001

Page 7 May 01/12 Revision n˚: 40

AES

FIGURE 24-60-00-14400-A SHEET 1 DC EMER CONFIG - Upper and Lower ECAM Display Unit

− LDG DOWN

− RAT&EMER GEN MAN ON

MANUAL CREW ACTION

LOSS OF DC ESS BUS

AC ESS BUS SUPPLIED BY AC1

CSM/G IS SWITCHED OFF

AFTER RAT DEPLOYMENT AND WHEN CSM/G AVAILABLE: − DC AND AC ESS BUS ON CSM/G

DC EMER CONFIG: − LOSS OF DC1, DC2, DC BAT AND DC ESS BUSBARS.

CONFIG. SYSTEM OVHD SYST PANEL IND.

MASTER CAUTION

MASTER CAUTION

MASTER CAUTION

+

SINGLE CHIME

WARNING

DC EMER CONFIG

ELEC

ELEC

DC EMER CONFIG

DC EMER CONFIG

−EMER ELEC PWR..MAN ON

ELEC

ECAM UPPER DISPLAY

DC EMER CONFIG (CLASS 1 − LEVEL 2)

SEE THREE PAGES FARTHER

SEE TWO PAGES FARTHER

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_246000_0_AEL0_01_00

24-60-00 PB001

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 10A

BAT 2 28V 10A

DC BAT

DC 1

DC 2 DC ESS

TR 1 0 V

ESS TR

EMER GEN

TR 2 0 V 0 A

0 A

AC 1

GEN 1 62% 11 6 V 400 HZ IDG 1

AC ESS

APU GEN

° C110

AC 2

GEN 2 60% 11 6 V 400 HZ 110C °

IDG 2

4WT2 DU − ECAM, LOWER

N_MM_246000_0_AEL0_02_00

AES

FIGURE 24-60-00-14400-A SHEET 2 DC EMER CONFIG - Upper and Lower ECAM Display Unit

24-60-00 PB001

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

DC BAT

BAT 2 28V 0A

DC 1

DC 2 DC ESS

TR 1 0 V 0 A

AC 1

GEN 1 62% 11 6 V 400 HZ IDG 1

ESS TR

EMER GEN

28V 62A

TR 2 0 V

116 V 400 HZ AC ESS

APU GEN

° C110

0 A

AC 2

GEN 2 60% 11 6 V 400 HZ 110C °

IDG 2

4WT2 DU − ECAM, LOWER

N_MM_246000_0_AJL0_01_00

AES

FIGURE 24-60-00-14500-A SHEET 1 DC Emergency Configuration - Supply of the Network by the CSM/G

24-60-00 PB001

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 8A

BAT 2 28V 10A

DC BAT

DC 1

DC 2 DC ESS

TR 1 0 V

ESS TR

EMER GEN

TR 2 0 V 0 A

0 A

AC 1

GEN 1 62% 11 6 V 400 HZ IDG 1

AC ESS

APU GEN

° C110

AC 2

GEN 2 60% 11 6 V 400 HZ 110C °

IDG 2

4WT2 DU − ECAM, LOWER

N_MM_246000_0_ALL0_01_00

AES

FIGURE 24-60-00-14600-A SHEET 1 DC Emergency Configuration - Supply of the Network with the Landing Gear Extended

24-60-00 PB001

Page 11 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC MAIN DISTRIBUTION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General The main 28 VDC distribution network corresponds to busbars 1PP, 2PP, 3PP, 6PP and associated sub-busbars, ** On A/C 003-004 (Ref. Fig. 24-61-00-11200-B - DC Main Distribution - General) ** On A/C 005-099 (Ref. Fig. 24-61-00-11200-C - DC Main Distribution - General)

AES

24-61-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location

** On A/C 003-004 (Ref. Fig. 24-61-00-12500-A - DC Main Distribution - Component Location) ** On A/C 005-099 (Ref. Fig. 24-61-00-12500-B - DC Main Distribution - Component Location) FIN

FUNCTIONAL DESIGNATION

PANEL

ZONE ACCESS ATA REF. DOOR

** On A/C ALL 8PN CNTOR-DC SVCE BUS NORM SPLY ** On A/C 005-099

120VU

212

24-61-55

10PN

120VU

212

24-61-55

AES

CONTACTOR

24-61-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

Operation/Control and Indicating Busbars 1PP, 3PP are supplied by TR1. Busbars 2PP, 6PP are supplied by TR2. NOTE :

In case of loss of one main TR, both main busbars are supplied by the remaining main TR.

Busbar 6PP is supplied in flight and/or on ground. This busbar can be supplied, independently from the main network, by the ground power unit via TR2 in ground service configuration (Ref. 24-43-00, P. Block 1). In case of loss of supply, a warning is triggered on the ECAM system, (Ref. Fig. 24-61-00-13700-A - DC Main Distribution - ECAM Warnings) In case of loss of main busbars, the ELEC page is automatically displayed on the ECAM lower display unit: (Ref. Fig. 24-61-00-13800-A - DC BUS 1 FAULT - Upper and Lower ECAM display Unit) (Ref. Fig. 24-61-00-13900-A - DC BUS 2 FAULT - Upper and Lower ECAM Display Unit) (Ref. Fig. 24-61-00-14000-A - DC BUS 1 and DC BUS 2 FAULT - Upper and Lower ECAM Display Unit) (Ref. Fig. 24-61-00-14100-A - DC BAT BUS FAULT - Upper and Lower ECAM Display Unit)

AES

24-61-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004

24−35−00 301PP

11PB APU START 49−42−00

10KA

5KA

CSM/G CONTROL UNIT

6XE

6KA 1PB2

502PP

702PP

5PB2

BCL−2

704PP 12PB2

BAT2 2PB2

4PB2 6PB2 1PB1

701PP

12PB1

501PP

8PR

5PR SHUNT

208PP

3PB2 1PR

206PP

6PN

BCL−1

103PP

703PP

5PB1

3PN1

BAT1

101PP

4PB1 6PB1

1PN1 DC BUS 1

2PR

1PP

1PC1

28VDC

BAT BUS

2PB1 3PP

3PN2 SHUNT

1PN2

3PB1

DC BUS 2

1PC2

28VDC

204PP

601PP

202PP

602PP

2PP

7PN

28VDC

DC SVCE BUS

8PN

6PP 28VDC

3PX 24−62−00

5PU1

24−28−00 5PU2

1PX 1PU1 TR1

1PU2 TR2

2PU1

AC BUS 1

1XP

24−25−00

24−25−00

AC BUS 2

115VAC

2XP 115VAC

2PU2

14PU

24−50−00 24−22−00

24−22−00

24−43−00

N_MM_246100_0_AAL0_01_00

AES

FIGURE 24-61-00-11200-B SHEET 1 DC Main Distribution - General

24-61-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

24−35−00 301PP

11PB APU START 49−42−00

10KA

5KA

CSM/G CONTROL UNIT

6XE

6KA 1PB2

702PP

5PB2 12PB2

BAT2 2PB2

4PB2 6PB2 1PB1

BAT1

101PP 1PP

1PC1

28VDC

4PB1 6PB1 BAT BUS 3PP

2PB1

SHUNT

208PP

3PB2 1PR

206PP

6PN 3PN2

SHUNT

1PN2

3PB1

DC BUS 2

1PC2

28VDC

501PP

8PR

5PR

703PP

5PB1

3PN1

DC BUS 1

701PP

12PB1

BCL− 1

1PN1

502PP

704PP

BCL− 2

103PP

2PR

204PP

601PP

202PP

602PP

2PP 28VDC

7PN

DC SVCE BUS

8PN 210PP

11PN

24 − 62 − 00

5PU1

10PN

6PP 28VDC

3PX

212PP

24 − 28 − 00 5PU2

1PX 1PU1 TR1

1PU2 TR2

2PU1

AC BUS 1

1XP

24 − 25 − 00

24 − 25 − 00

AC BUS 2

115VAC

2XP 115VAC

2PU2

14PU

24 − 50 − 00 24 − 22 − 00

24 − 22 − 00

24 − 43 − 00

N_MM_246100_0_AAP0_01_00

AES

FIGURE 24-61-00-11200-C SHEET 1 DC Main Distribution - General

24-61-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 FR16 FR20

841

A

120VU

122VU

121VU

124VU

125VU

123VU

A

8PN

B

B

N_MM_246100_0_ACM0_01_00

AES

FIGURE 24-61-00-12500-A SHEET 1 DC Main Distribution - Component Location

24-61-00 PB001

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 FR16 FR20

841

A

120VU

122VU

121VU

124VU

125VU

123VU

A

8PN

B 14PN

B

N_MM_246100_0_ACP0_01_00

AES

FIGURE 24-61-00-12500-B SHEET 1 DC Main Distribution - Component Location

24-61-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

FWC 2 DATA BUS 2 LMP

14WV DC 1

FWC 1 DATA BUS 2 SDAC 1 DATA BUS 2

TO FWC 2 RMP

SDAC 1

44WV DC 2

LMP

SDAC 1 DATA BUS 1

LMP

RMP

BUS

FWC 1

BUS

BUS

TO SDAC 2

RMP

SDAC 2 DATA BUS 2

** On A/C ALL

N_MM_246100_0_AEM0_01_00

AES

FIGURE 24-61-00-13700-A SHEET 1 DC Main Distribution - ECAM Warnings

24-61-00 PB001

Page 8 May 01/12 Revision n˚: 40

AES

FIGURE 24-61-00-13800-A SHEET 1 DC BUS 1 FAULT - Upper and Lower ECAM display Unit − CLEAR P/BSW (ON ECAM CP)

− CLEAR P/BSW (ON ECAM CP)

− BLOWER OVRD − EXTRACT OVRD

SELECT:

MANUAL CREW ACTION

− DC ESS BUS AND DC SHEDDABLE ESS BUS SUPPLIED BY TR ESS.

− TR1 INOP

− LOSS OF DC1

CONFIG. SYSTEM OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

DC BUS 1 FAULT

24-61-00 PB001

NORMAL CONFIG.

STS

NORMAL CONFIG.

− BLOWER.................OVRD − EXTRACT................OVRD

ELEC

ECAM UPPER DISPLAY

DC BUS 1 FAULT (CLASS 1 − LEVEL 2)

TR 1

INOP SYS:

NORMAL CONFIG.

RETURN TO PRESELECTED PAGE

CAB ZONE AT FIXED TEMP CAT 2 ONLY

STATUS

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_246100_0_AGM0_01_00

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

BAT 2 28V 0A

DC BAT

DC 1

DC 2 DC ESS

TR 1 0 V 0 A

AC 1

GEN 1 62% 11 6 V 400 HZ IDG 1

ESS TR

EMER GEN

28V 62A AC ESS

APU GEN

° C110

TR 2 28V 13 0A

AC 2

GEN 2 60% 11 6 V 400 HZ 110C °

IDG 2

4WT2 DU − ECAM, LOWER

N_MM_246100_0_AGM0_02_00

AES

FIGURE 24-61-00-13800-A SHEET 2 DC BUS 1 FAULT - Upper and Lower ECAM display Unit

24-61-00 PB001

Page 10 May 01/12 Revision n˚: 40

AES

FIGURE 24-61-00-13900-A SHEET 1 DC BUS 2 FAULT - Upper and Lower ECAM Display Unit − CLEAR P/BSW (ON ECAM CP)

− CLEAR P/BSW (ON ECAM CP)

MANUAL CREW ACTION

− DC ESS BUS AND DC SHEDDABLE ESS BUS SUPPLIED BY TR ESS.

− TR2 INOP

− LOSS OF DC2

CONFIG. SYSTEM OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

DC BUS 2 FAULT

24-61-00 PB001

NORMAL CONFIG.

STS

NORMAL CONFIG.

− AIR DATA SWITCH.....F/O

ELEC

ECAM UPPER DISPLAY

DC BUS 2 FAULT (CLASS 1 − LEVEL 2)

NORMAL CONFIG.

RETURN TO PRESELECTED PAGE

INCREASED LDG DIST TR 2 PACK 2 AT FIXED TEMP FLAPS/LATS SLOW CAT 2 ONLY

INOP SYS:

STATUS

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_246100_0_AJM0_01_00

Page 11 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

ELEC

BAT 1 28V 0A

BAT 2 28V 0A

DC BAT

DC 2

DC 1 DC ESS TR 1 28V 130A

AC 1

GEN 1 62% 11 6 V 400 HZ IDG 1

ESS TR

EMER GEN

TR 2 0 V

28V 62A

0 A

AC ESS

APU GEN

° C110

AC 2

GEN 2 60% 11 6 V 400 HZ 110C °

IDG 2

4WT2 DU − ECAM, LOWER

N_MM_246100_0_AJM0_02_00

AES

FIGURE 24-61-00-13900-A SHEET 2 DC BUS 2 FAULT - Upper and Lower ECAM Display Unit

24-61-00 PB001

Page 12 May 01/12 Revision n˚: 40

AES

FIGURE 24-61-00-14000-A SHEET 1 DC BUS 1 and DC BUS 2 FAULT - Upper and Lower ECAM Display Unit

− CLEAR P/BSW (ON ECAM CP)

− CLEAR P/BSW (ON ECAM CP)

ACTION ON:

MANUAL CREW ACTION

− DC ESS BUS AND DC SHEDDABLE ESS BUS SUPPLIED BY TR ESS.

− TR1 AND TR2 INOP

− LOSS OF DC1, DC BAT AND DC2

CONFIG. SYSTEM

OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

DC BUS 1 + 2 FAULT

24-61-00 PB001

NORMAL CONFIG.

STS

NORMAL CONFIG.

FUEL GRVTY FEED MAX FL........................150 (FL 100 IF JET B) AVOID ICING CONDITIONS MAX BRK.............1000PSI DC BAT BUS FAULT

ELEC

ECAM UPPER DISPLAY

DC BUS 1 + 2 FAULT (CLASS 1 − LEVEL 2)

NORMAL CONFIG.

RETURN TO PRESELECTED PAGE

TR 1 TR 2

INOP SYS:

STATUS

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_246100_0_ALM0_01_00

Page 13 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

DC ESS V

AC 1

V

AC ESS

GEN 1

AC 2

GEN 2 APU GEN

4WT2 DU − ECAM, LOWER

N_MM_246100_0_ALM0_02_00

AES

FIGURE 24-61-00-14000-A SHEET 2 DC BUS 1 and DC BUS 2 FAULT - Upper and Lower ECAM Display Unit

24-61-00 PB001

Page 14 May 01/12 Revision n˚: 40

AES

FIGURE 24-61-00-14100-A SHEET 1 DC BAT BUS FAULT - Upper and Lower ECAM Display Unit − CLEAR P/BSW (ON ECAM CP)

ACTION ON:

MANUAL CREW ACTION

− LOSS OF DC BAT BUS

CONFIG. SYSTEM OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

NORMAL CONFIG.

ELEC DC BAT BUS FAULT

ECAM UPPER DISPLAY

DC BAT BUS FAULT (CLASS 1 − LEVEL 2)

APU FIRE DET

NORMAL CONFIG.

APU START NOT AVAIL

INOP SYS

STATUS

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_246100_0_ANM0_01_00

24-61-00 PB001

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

DC 1

DC 2 DC ESS

TR 1

AC 1

TR 2

AC ESS

GEN 1

AC 2

GEN 2 APU GEN

4WT2 DU − ECAM, LOWER

N_MM_246100_0_ANM0_02_00

AES

FIGURE 24-61-00-14100-A SHEET 2 DC BAT BUS FAULT - Upper and Lower ECAM Display Unit

24-61-00 PB001

Page 16 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-61-55-000-001-A Removal of the DC Service Bus Normal Supply Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 8PN 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

125 121AL C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 25-11-41-000-001-A

DESIGNATION Removal of the Third Occupant Seat

(Ref. Fig. 24-61-55-991-00100-A - Contactor) (Ref. Fig. 24-61-55-991-00100-B - Contactor) 3.

Job Set-up Subtask 24-61-55-010-050-A A.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

Remove the front panel on the bottom right side of the panel 120VU.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-61-55-860-050-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft EXT PWR receptacle.

(2)

Put WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft EXT PWR receptacle.

24-61-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4.

(3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

(4)

In the cockpit, put WARNING NOTICE(S) in position to tell the persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

(5)

In the cockpit, on the APU section of the overhead panel 25VU, put a WARNING NOTICE(S) to tell persons not to start the APU.

Procedure

** On A/C 003-004 (Ref. Fig. 24-61-55-991-00100-A - Contactor) ** On A/C 005-099 (Ref. Fig. 24-61-55-991-00100-B - Contactor) ** On A/C ALL Subtask 24-61-55-020-050-A A.

Removal of the Contactor CAUTION :

(1)

Disconnect the electrical connector (4).

(2)

Put a blanking caps on the disconnected electrical connector (4) and the electrical receptacle.

(3)

Loosen the captive screws (2). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (2) and the spring washers from the contactor (3).

Remove the contactor (3).

24-61-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 003-004 120VU

A

122VU

121VU

125VU

124VU 123VU

A

8PN

B

2

B CONTACTOR BASE

5

CONTACTOR

6

4

3

2

N_MM_246155_4_AAM0_01_00

AES

FIGURE 24-61-55-991-00100-A SHEET 1 Contactor

24-61-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

122VU

A

121VU

125VU

124VU 123VU

A

8PN

B 14PN

2

5

B

MODULE 14PN

CONTACTOR 4

3

2

N_MM_246155_4_AAP0_01_00

AES

FIGURE 24-61-55-991-00100-B SHEET 1 Contactor

24-61-55 PB401

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-61-55-400-001-A Installation of the DC Service Bus Normal Supply Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 8PN 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific

B.

QTY AR WARNING NOTICE(S)

Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

Work Zones and Access Panels ZONE/ACCESS

125 121AL C.

DESIGNATION

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-11-41-000-001-A 25-11-41-400-001-A

Removal of the Third Occupant Seat Installation of the Third Occupant Seat

(Ref. Fig. 24-61-55-991-00100-A - Contactor) (Ref. Fig. 24-61-55-991-00100-B - Contactor) 3.

Job Set-up Subtask 24-61-55-860-051-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the access platform is in position at the access door 121AL.

(2)

Make sure that the access door 121AL is open.

(3)

Make sure that the external power connector is not connected to the aircraft receptacle.

(4)

Make sure that, on the access door 121AL, there is a WARNING NOTICE(S) to tell persons not to connect the external power connector.

24-61-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4.

(5)

In . . . .

the cockpit, on the overhead panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2, APU GEN, GEN 1, GEN 2, EXT PWR.

(6)

Make sure that there is a WARNING NOTICE(S) in the cockpit to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR), . 35VU (ELEC).

(7)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

(8)

In the cockpit, make sure that the third occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(9)

In the cockpit, make sure that the front panel on the bottom right side of the panel 120VU is removed.

Procedure

** On A/C 003-004 (Ref. Fig. 24-61-55-991-00100-A - Contactor) ** On A/C 005-099 (Ref. Fig. 24-61-55-991-00100-B - Contactor) ** On A/C 003-004 Subtask 24-61-55-420-050-A A.

Installation of the Contactor CAUTION :

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Put the contactor (3) in position on the tapped barrels (6) of the connecting base (5).

(2)

TORQUE the two captive screws (2) to between 23.9 and 26.55 LBF.IN (0.27 and 0.30 M.DAN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the connector (4) on the contactor (3).

** On A/C 005-099 Subtask 24-61-55-420-050-B A.

Installation of the Contactor CAUTION :

AES

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Install the contactor (3) in position on the module 14PN (5).

(2)

TORQUE the captive screws (2) to between 23.9 and 26.55 LBF.IN (0.27 and 0.30 M.DAN).

(3)

Remove the blanking caps from the electrical connector (4) and the electrical receptacle.

24-61-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the electrical connector (4) to the contactor (3).

** On A/C ALL Subtask 24-61-55-710-050-A B.

5.

Test of the Dome Lights in the Cockpit (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

On the overhead panel 25VU, put the INT LT/DOME switch in the BRT position. The dome lights on the panel 453VU, on the left of the cockpit, come on.

(3)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Close-up Subtask 24-61-55-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the front panel on the bottom right side of the panel 120VU.

(3)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

24-61-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-61-55-000-002-A Removal of the DC Shed-Bus Normal-Supply Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 10PN 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 25-11-41-000-001-A

DESIGNATION Removal of the Third Occupant Seat

(Ref. Fig. 24-61-55-991-00300-B - Contactor) 3.

Job Set-up Subtask 24-61-55-010-051-A A.

Get Access (1)

Remove the third occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

Remove the front panel on the bottom right side of the panel 120VU.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-61-55-860-052-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft external power receptacle.

(2)

Put WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft external power receptacle.

(3)

In the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: . BAT 1, BAT 2. . APU GEN.

24-61-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . .

GEN 1, GEN 2. EXT PWR.

(4)

In the cockpit, put WARNING NOTICE(S) in position to tell the persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section), . 25VU (APU section), . 35VU (ELEC).

(5)

In the cockpit, on the APU section of the overhead panel 25VU, put a WARNING NOTICE(S) to tell persons not to start the APU.

Subtask 24-61-55-865-050-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL

122VU

DESIGNATION ELEC/DC SHED BUS/CNTR

9PN

U26

124VU

SHED BUS 210PP/212PP/SPLY

11PN

BA01

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-61-55-991-00300-B - Contactor) Subtask 24-61-55-020-051-B A.

Removal of the Contactor CAUTION :

(1)

Disconnect the electrical connector (5) from the electrical receptacle (4).

(2)

Put CAP - BLANKING on the disconnected electrical connector (5) and the electrical receptacle (4).

(3)

Loosen the two captive screws (2). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (2) and the spring washers from the contactor (3).

Remove the contactor (3) from the module (1).

24-61-55 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 120VU

122VU

A

121VU

125VU

124VU 123VU

A

10PN

B

2

1

B

5

4

3

2

N_MM_246155_4_AAT0_01_00

AES

FIGURE 24-61-55-991-00300-B SHEET 1 Contactor

24-61-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-61-55-400-002-A Installation of the DC Shed-Bus Normal-Supply Contactor WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. FIN 10PN 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

No specific

B.

WARNING NOTICE(S) Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

212 121AL C.

ZONE DESCRIPTION COCKPIT

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-11-41-000-001-A

Removal of the Third Occupant Seat

25-11-41-400-001-A

Installation of the Third Occupant Seat

(Ref. Fig. 24-61-55-991-00300-B - Contactor) 3.

Job Set-up Subtask 24-61-55-860-053-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(2)

Make sure that the access door 121AL is open.

(3)

Make sure that the external power connector is not connected to the aircraft receptacle.

24-61-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

Make sure that on the access door 121AL, a WARNING NOTICE(S) is in position to tell persons not to connect the external power connector.

(5)

In . . . .

(6)

Make sure that a WARNING NOTICE(S) is in position in the cockpit to tell persons not to operate the pushbutton switches on these overhead panels: . 21VU (EMER ELEC PWR section). . 25VU (APU section). . 35VU (ELEC).

(7)

In the cockpit, on the APU section of the overhead panel 25VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the APU.

(8)

In the cockpit, make sure that the third occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(9)

In the cockpit, make sure that the front panel on the bottom right side of the panel 120VU is removed.

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2. APU GEN. GEN 1, GEN 2. EXT PWR.

Subtask 24-61-55-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

122VU

DESIGNATION ELEC/DC SHED BUS/CNTR

9PN

U26

124VU

SHED BUS 210PP/212PP/SPLY

11PN

BA01

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-61-55-991-00300-B - Contactor) Subtask 24-61-55-420-051-B A.

Installation of the Contactor CAUTION :

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Install the contactor (3) on the module (1).

(2)

TORQUE the two captive screws (2) to between 0.27 and 0.30 M.DAN (23.89 and 26.55 LBF.IN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Remove the blanking caps from the electrical receptacle (4).

(5)

Make sure that the electrical connectors are clean and in the correct condition.

(6)

Connect the electrical connector (5) to the electrical receptacle (4).

Subtask 24-61-55-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

122VU

PANEL

DESIGNATION ELEC/DC SHED BUS/CNTR

9PN

U26

124VU

SHED BUS 210PP/212PP/SPLY

11PN

BA01

AES

FIN

LOCATION

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-61-55-710-051-B C.

5.

Test (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

On the overhead ELEC panel 35VU, push the ELEC/COMMERCIAL pushbutton switch (22XN) (the white indication light goes off).

(3)

On the overhead ELEC panel 35VU, push the GALY & CAB pushbutton switch (2XA) (the white indication light goes off).

(4)

On the rear panel 120VU, make sure that there is 28VDC on busbar 210PP.

(5)

On the panel 2000VU, make sure that there is 28VDC on busbar 212PP.

(6)

On the overhead ELEC panel 35VU, release the GALY & CAB pushbutton switch (2XA) (the white indication light goes on).

(7)

On the overhead ELEC panel 35VU, release the ELEC/COMMERCIAL pushbutton switch (22XN) (the white indication light goes on).

Close-up Subtask 24-61-55-410-051-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the front panel on the bottom right side of the panel 120VU.

(3)

Install the third occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

Subtask 24-61-55-862-051-A B.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

MODULE - REMOVAL/INSTALLATION ** On A/C 005-099 Task 24-61-58-000-001-A Removal of the DC Bus 1 Contactor Module WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL C.

Referenced Information

REFERENCE 24-32-55-000-001-A 24-35-55-000-001-A 25-11-41-000-001-A 49-42-55-000-001-A (Ref. Fig. 24-61-58-991-00100-A - DC 3.

DESIGNATION Removal of the TR 1 and TR 2 Contactors and the TR 2/AC Service Bus Normal Supply Contactor Removal of the Contactor Removal of the Third Occupant Seat Removal of the Start Contactors Bus 1 Contactor Module)

Job Set-up Subtask 24-61-58-010-050-A A.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

In the cockpit, remove the front panel on the bottom right side of the rear panel 120VU.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-61-58-860-050-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft external-power receptacle.

(2)

Put a WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft external-power receptacle.

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4.

(3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2 APU GEN GEN 1, GEN 2 EXT PWR.

(4)

In the cockpit, put a WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on the overhead panel: . 21VU (EMER ELEC PWR section) . 25VU (APU section) . 35VU (ELEC).

Procedure (Ref. Fig. 24-61-58-991-00100-A - DC Bus 1 Contactor Module) Subtask 24-61-58-020-051-A A.

Removal of the Contactors Installed on the Contactor Module 13PN (1)

Remove the contactor 5PU1 (Ref. TASK 24-32-55-000-001-A).

(2)

Remove the contactor 1PC1 (Ref. TASK 24-35-55-000-001-A).

(3)

Remove the contactors 5KA and 10KA (Ref. TASK 49-42-55-000-001-A).

Subtask 24-61-58-020-052-A B.

Removal of the Electrical Components CAUTION :

(1)

(2)

(3)

(4)

AES

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Removal of the fuses (4). (a)

Remove the nuts (1).

(b)

Remove and discard the locking washers (2) and disconnect the electrical cables (3).

(c)

Remove the screws (17) and the washers (16).

(d)

Remove the fuses (4).

Removal of the fuse (10). (a)

Remove the nut (13).

(b)

Remove and discard the locking washer (12) and disconnect the electrical cable (11).

(c)

Remove the screw (15) and the washer (14).

(d)

Remove the fuse (10) and the spacer (6).

Removal of the busbar (7). (a)

Remove the screw (9) and the washer (8).

(b)

Remove the busbar (7).

Disconnection of the electrical cables. (a)

Remove the screws (20), the washers (19) and disconnect the electrical cables (18).

(b)

Remove the screw (23), the washer (22) and disconnect the electrical cable (21).

(c)

Remove the screw (27), the washer (28) and disconnect the electrical cables (29) and (30).

24-61-58 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-61-58-020-050-A C.

AES

Removal of the DC Bus 1 Contactor Module (13PN) (1)

Remove the protective plugs (24) from the screws (25).

(2)

Remove the screws (25).

(3)

Remove and discard the locking washers (26).

(4)

Remove the contactor module (5).

24-61-58 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

A 120VU

122VU

121VU

124VU 123VU

A

13PN

B B 15 13

14

12 11

23 20

10 17

9

22 19

24

21

18

8

25

16

7

26

4

27 28 29

6

30 20

5

1

19

2 3

18

4 N_MM_246158_4_AAM0_01_00

AES

FIGURE 24-61-58-991-00100-A SHEET 1 DC Bus 1 Contactor Module

24-61-58 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-61-58-400-001-A Installation of the DC Bus 1 Contactor Module WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

No specific

B.

WARNING NOTICE(S) Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL C.

Expendable Parts

FIG.ITEM 26

DESIGNATION

IPC-CSN 24-61-08-03-020

locking washers D.

Referenced Information

REFERENCE 24-32-55-400-001-A

DESIGNATION Installation of the TR 1 and TR 2 Contactors and the TR 2/AC Service Bus Normal Supply Contactor

24-35-55-400-001-A 25-11-41-000-001-A

Installation of the Contactor Removal of the Third Occupant Seat

25-11-41-400-001-A Installation of the Third Occupant Seat 49-42-55-400-001-A Installation of the Start Contactors (Ref. Fig. 24-61-58-991-00100-A - DC Bus 1 Contactor Module) 3.

Job Set-up Subtask 24-61-58-010-051-A A.

AES

Get Access (1)

Make sure that the Third Occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(2)

In the cockpit, make sure that the front panel on the bottom right side of the rear panel 120VU is removed.

(3)

Make sure that an ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-61-58-860-051-A B.

4.

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft external-power receptacle.

(2)

Make sure that a WARNING NOTICE(S) is in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft external-power receptacle.

(3)

In . . . .

(4)

In the cockpit, make sure that a WARNING NOTICE(S) is in position to tell persons not to operate the pushbutton switches on the overhead panel: . 21VU (EMER ELEC PWR section) . 25VU (APU section) . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2 APU GEN GEN 1, GEN 2 EXT PWR.

Procedure (Ref. Fig. 24-61-58-991-00100-A - DC Bus 1 Contactor Module) Subtask 24-61-58-420-050-A A.

Installation of the DC Bus 1 Contactor Module (13PN) (1)

Put the contactor module (5) in position on its support.

(2)

Install the new (IPC-CSN 24-61-08-03) locking washers (26) and the screws (25).

(3)

Tighten the screws (25).

(4)

Install the protective plugs (24) on the screws (25).

Subtask 24-61-58-420-052-A B.

Installation of the Electrical Components CAUTION :

(1)

(2)

AES

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Installation of the fuses (4). (a)

Install the fuses (4) on the contactor module (5).

(b)

Connect the electrical cables (3).

(c)

Install the new locking washers (2) and the nuts (1).

(d)

Tighten the nuts (1).

(e)

Install the washers (16) and the screws (17).

(f)

Tighten the screws (17).

Installation of the fuse (10). (a)

Install the busbar (7) between the contactor modules 13PN and 14PN.

(b)

Install the spacer (6).

(c)

Install the fuse (10).

(d)

Install the washers (8) and (14) and the screws (9) and (15).

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(3)

(e)

Tighten the screws (9) and (15).

(f)

Put the electrical cable (11) in position on the contactor module (5).

(g)

Install the new locking washer (12) and the nut (13).

(h)

Tighten the nut (13).

Connection of the electrical cables. (a)

Put the electrical cables (18) in position on the contactor module (5).

(b)

Install the washers (19) and the screws (20).

(c)

TORQUE the screws (20) to between 0.27 and 0.3 M.DAN (23.89 and 26.55 LBF.IN).

(d)

Put the electrical cable (21) in position on the contactor module (5).

(e)

Install the washer (22) and the screw (23).

(f)

Tighten the screw (23).

(g)

Put the electrical cables (29) and (30) in position on the contactor module (5).

(h)

Install the washer (28) and the screw (27).

(i)

Tighten the screw (27).

Subtask 24-61-58-420-051-A C.

5.

Installation of the Contactors on the Contactor Module 13PN (1)

Install the contactor 5PU1 (Ref. TASK 24-32-55-400-001-A).

(2)

Install the contactor 1PC1 (Ref. TASK 24-35-55-400-001-A).

(3)

Install the contactors 5KA and 10KA (Ref. TASK 49-42-55-400-001-A).

Close-up Subtask 24-61-58-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the front panel on the bottom right side of the rear panel 120VU.

(3)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

24-61-58 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-61-58-000-002-A Removal of the DC Bus 2 Contactor Module WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

B.

WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL C.

Referenced Information

REFERENCE 24-32-55-000-001-A

DESIGNATION Removal of the TR 1 and TR 2 Contactors and the TR 2/AC Service Bus Normal Supply Contactor

24-35-55-000-001-A 24-43-55-000-001-A

Removal of the Contactor Removal of the DC Service Bus Ground Supply Contactor

24-61-55-000-001-A

Removal of the DC Service Bus Normal Supply Contactor

24-61-55-000-002-A

Removal of the DC Shed-Bus Normal-Supply Contactor

25-11-41-000-001-A

Removal of the Third Occupant Seat

(Ref. Fig. 24-61-58-991-00200-A - DC Bus 2 Contactor Module) 3.

Job Set-up Subtask 24-61-58-010-053-A A.

Get Access (1)

Remove the Third Occupant seat (Ref. TASK 25-11-41-000-001-A).

(2)

In the cockpit, remove the front panel on the bottom right side of the rear panel 120VU.

(3)

Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position at the access door 121AL.

(4)

Open the access door 121AL.

Subtask 24-61-58-860-053-A B.

AES

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft external-power receptacle.

(2)

Put a WARNING NOTICE(S) in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft external-power receptacle.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4.

(3)

In . . . .

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2 APU GEN GEN 1, GEN 2 EXT PWR.

(4)

In the cockpit, put a WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on the overhead panel: . 21VU (EMER ELEC PWR section) . 25VU (APU section) . 35VU (ELEC).

Procedure (Ref. Fig. 24-61-58-991-00200-A - DC Bus 2 Contactor Module) Subtask 24-61-58-020-056-A A.

Removal of the Contactors Installed on the Contactor Module 14PN (1)

Remove the contactor 5PU2 (Ref. TASK 24-32-55-000-001-A).

(2)

Remove the contactor 1PC2 (Ref. TASK 24-35-55-000-001-A).

(3)

Remove the contactor 8PN (Ref. TASK 24-61-55-000-001-A).

(4)

Remove the contactor 10PN (Ref. TASK 24-61-55-000-002-A).

(5)

Remove the contactor 3PX (Ref. TASK 24-43-55-000-001-A).

Subtask 24-61-58-020-057-A B.

Removal of Electrical Components CAUTION :

(1)

(2)

MAKE MATCH MARKS ON ALL THE ELECTRICAL WIRES BEFORE YOU DISCONNECT THEM. INCORRECT CONNECTION OF WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Removal of the busbar (8). (a)

Remove the nut (4).

(b)

Remove and discard the locking washer (5) and disconnect the electrical cable (6).

(c)

Remove the screw (1) and the washer (2).

(d)

Remove the fuse (3) and the spacer (7).

(e)

Remove the screw (10) and the washer (9).

(f)

Remove the busbar (8).

Disconnection of the electrical cables. (a)

Remove the screws (27), the washers (28) and disconnect the electrical cables (29).

(b)

Remove the screw (25), the washer (24) and disconnect the electrical cables (23) and (22).

(c)

Remove the screws (13), the washers (12) and disconnect the electrical cables (11).

(d)

Remove the screw (21), the washer (20) and disconnect the electrical cables (19), (18) and (17).

Subtask 24-61-58-020-058-A C.

AES

Removal of the DC Bus 2 Contactor Module (14PN) (1)

Remove the protective plugs (16) from the screws (15).

(2)

Remove the screws (15).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AES

(3)

Remove and discard the locking washers (14).

(4)

Remove the contactor module (26).

24-61-58 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099

A 120VU

122VU

121VU

124VU 123VU

A

14PN

B B

27 25

28

16 21

24

20

23 22

15 14 13

29 26

19 18 17

12 11 10

6

4

1

5

2 3

9 8

7 CONTACTOR MODULE 13PN N_MM_246158_4_ABM0_01_00

AES

FIGURE 24-61-58-991-00200-A SHEET 1 DC Bus 2 Contactor Module

24-61-58 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C 005-099 Task 24-61-58-400-002-A Installation of the DC Bus 2 Contactor Module WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT ELECTRICAL CIRCUITS. THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS CONNECTED. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE

No specific

AR

No specific

B.

WARNING NOTICE(S) Torque wrench: range to between 0.20 and 3.60 M.DAN (2.00 and 26.00 LBF.FT)

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

121AL C.

Expendable Parts

FIG.ITEM 14

DESIGNATION

IPC-CSN 24-61-08-03-020

locking washers D.

Referenced Information

REFERENCE 24-32-55-400-001-A

DESIGNATION Installation of the TR 1 and TR 2 Contactors and the TR 2/AC Service Bus Normal Supply Contactor

24-35-55-400-001-A 24-43-55-400-001-A

Installation of the Contactor Installation of the DC Service Bus Ground Supply Contactor

24-61-55-400-001-A

Installation of the DC Service Bus Normal Supply Contactor

24-61-55-400-002-A

Installation of the DC Shed-Bus Normal-Supply Contactor

25-11-41-000-001-A 25-11-41-400-001-A

Removal of the Third Occupant Seat Installation of the Third Occupant Seat

(Ref. Fig. 24-61-58-991-00200-A - DC Bus 2 Contactor Module) 3.

Job Set-up Subtask 24-61-58-010-052-A A.

AES

Get Access (1)

Make sure that the Third Occupant seat is removed (Ref. TASK 25-11-41-000-001-A).

(2)

In the cockpit, make sure that the front panel on the bottom right side of the rear panel 120VU is removed.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Make sure that an ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position at the access door 121AL.

(4)

Make sure that the access door 121AL is open.

Subtask 24-61-58-860-052-A B.

4.

Safety Precautions (1)

Make sure that the external power connector is not connected to the aircraft external-power receptacle.

(2)

Make sure that a WARNING NOTICE(S) is in position on the access door 121AL to tell persons not to connect the external power connector to the aircraft external-power receptacle.

(3)

In . . . .

(4)

In the cockpit, make sure that a WARNING NOTICE(S) is in position to tell persons not to operate the pushbutton switches on the overhead panel: . 21VU (EMER ELEC PWR section) . 25VU (APU section) . 35VU (ELEC).

the cockpit, on the ELEC panel 35VU, make sure that these pushbutton switches are released: BAT 1, BAT 2 APU GEN GEN 1, GEN 2 EXT PWR.

Procedure (Ref. Fig. 24-61-58-991-00200-A - DC Bus 2 Contactor Module) Subtask 24-61-58-420-053-A A.

Installation of the DC Bus 2 Contactor Module (14PN) (1)

Put the contactor module (26) in position on its support.

(2)

Install the new (IPC-CSN 24-61-08-03) locking washers (14) and the screws (15).

(3)

Tighten the screws (15).

(4)

Install the protective plugs (16) on the screws (15).

Subtask 24-61-58-420-055-A B.

Installation of the Electrical Components CAUTION :

(1)

AES

REFER TO THE MATCH MARKS MADE DURING THE REMOVAL WHEN YOU CONNECT THE ELECTRICAL WIRES. INCORRECT CONNECTION OF THE WIRES WILL CAUSE DAMAGE TO EQUIPMENT.

Installation of the busbar (8). (a)

Install the busbar (8) between the contactor modules 14PN and 13PN.

(b)

Install the spacer (7).

(c)

Install the fuse (3).

(d)

Install the washers (2) and (9) and the screws (1) and (10).

(e)

Tighten the screws (1) and (10).

(f)

Put the electrical cable (6) in position on the contactor module (13PN).

(g)

Install the new locking washer (5) and the nut (4).

(h)

Tighten the nut (4).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Connection of the electrical cables. (a)

Put the electrical cables (19), (18) and (17) in position on the contactor module (26).

(b)

Install the washer (20) and the screw (21).

(c)

TORQUE the screw (21) to between 0.27 and 0.3 M.DAN (23.89 and 26.55 LBF.IN).

(d)

Put the electrical cables (11) in position on the contactor module (26).

(e)

Install the washers (12) and the screws (13).

(f)

TORQUE the screws (13) to between 0.27 and 0.3 M.DAN (23.89 and 26.55 LBF.IN).

(g)

Put the electrical cables (22) and (23) in position on the contactor module (26).

(h)

Install the washer (24) and the screw (25).

(i)

Tighten the screw (25).

(j)

Put the electrical cables (29) in position on the contactor module (26).

(k)

Install the washers (28) and the screws (27).

(l)

TORQUE the screws (27) to between 0.27 and 0.3 M.DAN (23.89 and 26.55 LBF.IN).

Subtask 24-61-58-420-054-A C.

5.

Installation of the Contactors on the Contactor Module 14PN (1)

Install the contactor 5PU2 (Ref. TASK 24-32-55-400-001-A).

(2)

Install the contactor 1PC2 (Ref. TASK 24-35-55-400-001-A).

(3)

Install the contactor 8PN (Ref. TASK 24-61-55-400-001-A).

(4)

Install the contactor 10PN (Ref. TASK 24-61-55-400-002-A).

(5)

Install the contactor 3PX (Ref. TASK 24-43-55-400-001-A).

Close-up Subtask 24-61-58-410-051-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the front panel on the bottom right side of the rear panel 120VU.

(3)

Install the Third Occupant seat (Ref. TASK 25-11-41-400-001-A).

(4)

Remove the warning notice(s).

(5)

Close the access door 121AL.

(6)

Remove the access platform(s).

24-61-58 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

DC ESSENTIAL DISTRIBUTION - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General (Ref. Fig. 24-62-00-11200-B - DC Essential Distribution - General) The essential 28 VDC distribution network corresponds to busbars 4PP, 8PP and associated sub-busbars.

AES

24-62-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-62-00-12400-B - DC Essential Distribution - Component Location) FIN

ZONE ACCESS ATA REF. DOOR 8PH CNTOR-DC SHED ESS BUS 106VU 125 24-62-55 ------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA I I I I DOOR I REF. ------------------------------------------------------------------------------6PH HOLDER-FUSE 105VU 126 24-62-00 6PH1 FUSE 105VU 126 24-62-00

AES

FUNCTIONAL DESIGNATION

PANEL

24-62-00 PB001

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 3.

Operation

** On A/C 005-099 The essential 28 VDC distribution network can be supplied: . either by busbar 3PP (in fact by TR1) in normal configuration, . by Essential TR in case of loss of one main TR, loss of both main TRs or in emergency configuration. Part of this network (busbar 8PP) can be shed in emergency configuration during RAT extension and as soon as the landing gear is extended (case of battery supply). In case of loss of supply, a warning is triggered on the ECAM system, (Ref. Fig. 24-62-00-13800-A - DC Essential Distribution - ECAM Warnings) In case of loss of busbars 4PP or 8PP, the ELEC page is automatically displayed on the ECAM lower display unit: (Ref. Fig. 24-62-00-13900-A - DC ESS BUS FAULT - Upper and Lower ECAM Display Unit) (Ref. Fig. 24-62-00-14000-A - DC ESS BUS SHED - Upper and Lower ECAM Display Unit) ** On A/C 003-004 The essential 28 VDC distribution network can be supplied: . either by busbar 3PP (in fact by TR1) in normal configuration, . by Essential TR in case of loss of one main TR, loss of both main TRs or in emergency configuration. Part of this network (busbar 8PP) can be shed in emergency configuration during RAT extension and when CSM/G is switched off after landing (case of battery supply). In case of loss of supply, a warning is triggered on the ECAM system, (Ref. Fig. 24-62-00-13800-A - DC Essential Distribution - ECAM Warnings) In case of loss of busbars 4PP or 8PP, the ELEC page is automatically displayed on the ECAM lower display unit: (Ref. Fig. 24-62-00-13900-A - DC ESS BUS FAULT - Upper and Lower ECAM Display Unit) (Ref. Fig. 24-62-00-14000-A - DC ESS BUS SHED - Upper and Lower ECAM Display Unit) It must be noted that due to segregation rules between DC channels, the TR2 cannot supply the DC ESS busbar.

AES

24-62-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

801PP 301PP

DC SHED ESS BUS

11PB APU START 49−42−00

5KA

10KA

CSM/G CONTROL UNIT

6XE

6KA 1PB2

24−60−00

BCL−2

2PB2

4PB2 6PB2

701PP

12PB1 5PB1

1PP

1PC1

28VDC

BAT BUS

8PH 401PP

8PR

SHUNT 3PB2

DC ESS BUS

4PC

1PR

BAT1 2PB1

6PB1

4PP 28VDC

24−28−00

703PP

24−61−00

DC BUS 1

5PR

BAT2

1PB1

20PC

24−60−00

704PP 12PB2

4PB1

2PR

702PP

5PB2

BCL−1

8PP 28VDC

24−43−00

24−43−00

24−61−00

SHUNT 3PB1

3PP

DC BUS 2

1PC2

28VDC

2PP 28VDC

7PN

DC SVCE BUS

8PN

6PP 28VDC

3PX 24−62−00

5PU1

24−28−00 3PE

5PU2

1PX 1PU1 TR1

1PU2 TR2

1PE ESS. TR

24−52−00 115VAC 2PU1

AC ESS BUS

AC BUS 1

4XP AC BUS 2

1XP 115VAC

1XC

2XC

2XP 115VAC

2PU2

14PU

3XC

4PE 15XE

24−22−00

24−22−00

24−43−00

24−28−00 EMER GLC 2XE

CSM/GCU 1XE

EMER GEN

8XE

N_MM_246200_0_AAL0_01_00

AES

FIGURE 24-62-00-11200-B SHEET 1 DC Essential Distribution - General

24-62-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR16

A

FR9

106VU

D

B

A

812

8PH

D B 105VU

6PH

C

C 6PH1 6PH

N_MM_246200_0_ACL0_01_00

AES

FIGURE 24-62-00-12400-B SHEET 1 DC Essential Distribution - Component Location

24-62-00 PB001

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

FWC 2 DATA BUS 2 BUS SDAC 1 FWC 1 DATA BUS 2 DATA BUS 2

TO FWC 2

12WV

8PH

SDAC 1

RMP

LMP

SDAC 1 DATA BUS 1

LMP

RMP

BUS

FWC 1

TO SDAC 2

BUS

RMP

LMP

SDAC 2 DATA BUS 2

** On A/C ALL

N_MM_246200_0_AEM0_01_00

AES

FIGURE 24-62-00-13800-A SHEET 1 DC Essential Distribution - ECAM Warnings

24-62-00 PB001

Page 6 May 01/12 Revision n˚: 40

AES

FIGURE 24-62-00-13900-A SHEET 1 DC ESS BUS FAULT - Upper and Lower ECAM Display Unit − CLEAR (ON ECAM CP)

− VHF 2 OR 3

SELECT:

MANUAL CREW ACTION

LOSS OF DC ESS BUS.

CONFIG. SYSTEM OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

NORMAL CONFIG.

− VHF 2 OR 3................USE

ELEC DC ESS BUS FAULT

ECAM UPPER DISPLAY

DC ESS BUS FAULT (CLASS 1 − LEVEL 2)

INOP SYS

NORMAL CONFIG.

SLATS/FLAPS SLOW

INCREASED LDG DIST

STATUS

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_246200_0_AGL0_01_00

24-62-00 PB001

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

DC BAT

DC 1

DC 2

TR 1

TR 2

AC 1

AC ESS

GEN 1

AC 2

GEN 2 APU GEN

4WT2 DU − ECAM, LOWER

N_MM_246200_0_AGL0_02_00

AES

FIGURE 24-62-00-13900-A SHEET 2 DC ESS BUS FAULT - Upper and Lower ECAM Display Unit

24-62-00 PB001

Page 8 May 01/12 Revision n˚: 40

AES

FIGURE 24-62-00-14000-A SHEET 1 DC ESS BUS SHED - Upper and Lower ECAM Display Unit

− CLEAR (ON ECAM CP)

− EXTRACT OVRD

SELECT:

MANUAL CREW ACTION

LOSS OF DC SHEDDABLE ESS BUS

CONFIG. SYSTEM OVHD SYST PANEL IND.

MASTER CAUTION

+

SINGLE CHIME

WARNING

NORMAL CONFIG.

EXTRACT..................OVRD

ELEC DC ESS BUS SHED

ECAM UPPER DISPLAY

DC ESS BUS SHED (CLASS 1 − LEVEL 2)

INOP SYS

NORMAL CONFIG.

SLATS/FLAPS SLOW

STATUS

SEE FOLLOWING PAGE

ECAM LOWER DISPLAY

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_246200_0_AJM0_01_00

24-62-00 PB001

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

DC BAT

DC 1

DC 2

TR 1

TR 2

AC 1

AC ESS

GEN 1

AC 2

GEN 2 APU GEN

4WT2 DU − ECAM, LOWER

N_MM_246200_0_AJM0_02_00

AES

FIGURE 24-62-00-14000-A SHEET 2 DC ESS BUS SHED - Upper and Lower ECAM Display Unit

24-62-00 PB001

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

CONTACTOR - REMOVAL/INSTALLATION ** On A/C ALL Task 24-62-55-000-001-A Removal of the DC Shed Essential Bus Contactor FIN 8PH 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

B.

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE (Ref. Fig. 24-62-55-991-00100-B - DC Shed Essential Bus Contactor) 3.

DESIGNATION

Job Set-up Subtask 24-62-55-010-050-A A.

Get access to the Avionics Compartment (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the avionics compartment doors 812 and 822.

(2)

Open the access doors 812 and 822.

(3)

Open the access panels of the AC/DC emergency power center 106VU and the access panels of the BATTERY power center 105VU.

Subtask 24-62-55-865-050-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL

105VU

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

AES

FIN

LOCATION

24-62-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL

DESIGNATION AC ESS/BUS ON/BUS 2

123VU 4.

FIN 2XC

LOCATION AC01

Procedure (Ref. Fig. 24-62-55-991-00100-B - DC Shed Essential Bus Contactor) Subtask 24-62-55-020-050-A A.

Removal of the Contactor CAUTION :

(1)

Disconnect the connector (4).

(2)

Put blanking caps on the disconnected electrical connector(s).

(3)

Loosen the two captive screws (2). NOTE :

(4)

AES

REMOVE THE CONTACTOR ONLY AND NOT THE BASE OR THE MODULE WHERE THE WIRES ARE CONNECTED.

Do not remove the captive screws (2) and the spring washers from the contactor (3).

Disengage the contactor (3) from the base (5) and then remove the contactor.

24-62-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR16

FR9

A 106VU

B

822

A

812

105VU

8PH

B 6

CONTACTOR BASE

2

5

CONTACTOR 3

2

7

4

N_MM_246255_4_AAL0_01_00

AES

FIGURE 24-62-55-991-00100-B SHEET 1 DC Shed Essential Bus Contactor

24-62-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-62-55-400-001-A Installation of the DC Shed Essential Bus Contactor FIN 8PH 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific No specific

B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE Torque wrench: range to between 0.00 and 50.00 LBF.IN (0.00 and 0.56 M.DAN)

Work Zones and Access Panels ZONE/ACCESS

125 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

31-60-00-860-001-A 31-60-00-860-002-A

EIS Start Procedure EIS Stop Procedure

(Ref. Fig. 24-62-55-991-00100-B - DC Shed Essential Bus Contactor) 3.

Job Set-up Subtask 24-62-55-860-050-A A.

AES

Aircraft Maintenance Configuration (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access doors 812 and 822.

(2)

Make sure that the access doors 812 and 822 are open.

(3)

In the avionics compartment, make sure that the access panel of the AC/DC emergency power center 106VU and BATTERY power center 105VU are open.

24-62-55 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-62-55-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

105VU

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

C01

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

4.

FIN

LOCATION

Procedure (Ref. Fig. 24-62-55-991-00100-B - DC Shed Essential Bus Contactor) Subtask 24-62-55-420-050-A A.

Installation of the Contactor CAUTION :

MAKE SURE THAT THE CONTACTOR LOCATING PIN IS CORRECTLY ENGAGED IN ITS RECESS LOCATED IN ONE POWER TERMINAL. THIS PREVENTS DAMAGE TO THE LOCATING PIN WHEN YOU APPLY THE TORQUE.

(1)

Put the contactor (3) on the tapped barrels (6) of the contactor base (5).

(2)

TORQUE the two captive screws (2) to between 23.9 and 26.55 LBF.IN (0.27 and 0.30 M.DAN).

(3)

Remove the blanking caps from the electrical connector(s).

(4)

Make sure that the electrical connectors are clean and in the correct condition.

(5)

Connect the connector (4) on the contactor (3).

Subtask 24-62-55-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

105VU

PANEL

DESIGNATION ELEC/CSM/G /EV AUTO/SPLY

7XE

FIN C01

LOCATION

106VU

CSM/G /EV/MAN/SPLY

6XE

B04

106VU

ESS TR/SPLY

4PE

C01

122VU

ELEC/CNTOR/ESS/DC BUS/TIE

3PC

W26

123VU

AC ESS/BUS ON/BUS 1

1XC

AC12

123VU

AC ESS/BUS ON/BUS 2

2XC

AC01

Subtask 24-62-55-710-050-A C.

AES

Test of the DC Shed Essential Bus Contactor (1)

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. TASK 31-60-00-860-001-A).

(3)

Make sure that the DC ESS BUS SHED warning does not come into view.

24-62-55 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

5.

(4)

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A).

(5)

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

Close-up Subtask 24-62-55-410-050-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

In the avionics compartment, close the access panels of the AC/DC emergency power center 106VU and the BATTERY power center 105VU.

(3)

Close the access doors 812 and 822.

(4)

Remove the access platform(s).

24-62-55 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

REFUELING ON BATTERY - DESCRIPTION AND OPERATION ** On A/C ALL 1.

General (Ref. Fig. 24-67-00-11200-C - Refueling on Battery - Simplified Schematic) The network consists of busbars 501PP and 502PP (28 VDC). It is supplied as soon as the refuel door located on the fuselage below the right wing is opened. Two supplies are then possible: . 28 VDC service bus 601PP if at least ground service busses are energized, . 28 VDC hot bus 701PP (directly linked to battery 1) if no other power is available on board. NOTE :

AES

Refueling power supply is automatically cut off ten minutes after.

24-67-00 PB001

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 2.

Component Location (Ref. Fig. 24-67-00-12500-B - Refuel/Defuel Panel - Component Location)

AES

24-67-00 PB001

Page 2 May 01/12 Revision n˚: 40

AES

FIGURE 24-67-00-11200-C SHEET 1 Refueling on Battery - Simplified Schematic 1PR

701PP 28VDC HOT BUS

4PR

2PR

601PP 28VDC SVCE BUS

28−25−00

5PR REFLNG NORM/BAT

28−25

3PX

11PR

12PR

8PN

10PR BATTERY POWER

NORM ON

8PR REFLNG BUS 501PP/502PP CTL

3QU MODE SELECT/REFUEL/ OFF/DEFUEL/XFR

20QU REFUEL DOOR POS

OPEN

502PP REFLNG BUS 2

2QU

UP DOWN 6GA LEVER L/G NORM CTL

501PP REFLNG BUS 1

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

** On A/C ALL

N_MM_246700_0_ACP0_01_00

24-67-00 PB001

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FUEL CTY KGx1000 LEFT

CTR

HI. LEFT

RIGHT

LVL. CTR

INDICATOR

RIGHT

REFUEL VALVES OPEN NORM SHUT MODE SELECT REFUEL

OPEN OPEN NORM NORM SHUT SHUT TEST BATT POWER HI.LVL ON

OFF DEFUEL XFR PRESELECTED

DEC

OPEN REFUEL KGx1000

INC CKPT

LTS

NORM ACTUAL

END

PRESELECTOR

N_MM_246700_0_AAP0_01_00

AES

FIGURE 24-67-00-12500-B SHEET 1 Refuel/Defuel Panel - Component Location

24-67-00 PB001

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

ELECTRICAL ROUTING - DEACTIVATION/REACTIVATION ** On A/C ALL Task 24-92-00-000-001-A Removal of the IDG Feeders from the Pylon 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels

ZONE/ACCESS 414AR, 424AR FOR FIN 1000EM1(ENGINE-1)

ZONE DESCRIPTION

438AR FOR FIN 1000EM2(ENGINE-2) 448AR C.

Referenced Information

REFERENCE 71-13-00-010-010-A

DESIGNATION Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

(Ref. Fig. 24-92-00-991-04000-A - IDG Feeders on the Pylon) 3.

Job Set-up Subtask 24-92-00-860-081-A A.

Aircraft Maintenance Configuration (1)

On the center pedestal, on the ENG panel 115VU: (a)

Put a WARNING NOTICE(S) in position to tell persons not to start the engine 1(2).

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-92-00-010-073-C B.

Get Access (1)

AES

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position on the right side of the engine.

24-92-00 PB401

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

4.

(2)

Remove these access panels: . For the left pylon: 414AR . For the right pylon: 424AR

(3)

Open the right fan cowl (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 438AR

(b)

FOR 1000EM2 (ENGINE-2) 448AR

Procedure (Ref. Fig. 24-92-00-991-04000-A - IDG Feeders on the Pylon) Subtask 24-92-00-020-050-A A.

Removal of the IDG feeder cables (1)

AES

Disconnect the feeder cables from the right side of the pylon: (a)

Remove the bolts (18), the washers (17) and the plate (16).

(b)

Disconnect the IDG feeder connector from the connector (14).

(c)

Put blanking caps on the disconnected electrical connector(s).

(d)

Remove and discard the lockwire from the attachment plate (13) and the connector (14).

(e)

Remove the four nuts (12), the four bolts (15) and one attachment plate (13).

(f)

Remove the nuts (10) and the washers (9).

(g)

Disengage the two clamps (8) and remove the spacers (7).

(h)

Remove the clamp blocks (6), the bobbins (11) and the spacers (5).

(i)

Remove and discard the lockwire (2) from the plate (4).

(j)

Remove the cover (3).

(k)

Remove the nuts (1) and disconnect the four electrical feeders.

(l)

Remove the IDG feeders from the pylon.

24-92-00 PB401

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A A

A

B C

SECTION

A−A B

A

400VT

A 2

C

1

5

18

4

11 17

6 7

8

5

16 9 7

3

6

8 10

9 10

12 13

15 14 400VC

N_MM_249200_4_AAM0_01_00

AES

FIGURE 24-92-00-991-04000-A SHEET 1 IDG Feeders on the Pylon

24-92-00 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-400-001-A Installation of the IDG Feeders on the Pylon 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

B.

Consumable Materials

REFERENCE Material No: 19-010 C.

WARNING NOTICE(S)

DESIGNATION LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

414AR, 424AR FOR FIN 1000EM1(ENGINE-1) 438AR FOR FIN 1000EM2(ENGINE-2) 448AR D.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

ESPM 20-44-52 AWM 24-22-01 AWM 24-22-02 (Ref. Fig. 24-92-00-991-04000-A - IDG Feeders on the Pylon) 3.

Job Set-up Subtask 24-92-00-860-082-A A.

Aircraft Maintenance Configuration (1)

AES

On the center pedestal, on the panel 115VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the engine.

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Make sure that a WARNING NOTICE(S) is in position to tell persons not to energize the FADEC 1(2).

Subtask 24-92-00-010-074-C B.

4.

Get Access (1)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position on the right side of the engine.

(2)

Make sure that these access panels are removed: . For the right pylon: 424AR . For the left pylon: 414AR

(3)

Make sure that the right fan cowl is open (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 438AR

(b)

FOR 1000EM2 (ENGINE-2) 448AR

Procedure (Ref. Fig. 24-92-00-991-04000-A - IDG Feeders on the Pylon) Subtask 24-92-00-420-052-A A.

Installation of the IDG feeder cables (1)

Connection of the feeder cables on the right side of the pylon: (a)

Install the IDG feeders in the engine electrical box 400VC.

(b)

Install the attachment plate (13), the four bolts (15), the four nuts (12) and tighten the nuts (12).

(c)

Install the new LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA (Material No: 19-010) on the attachment plate and the connector (14).

(d)

Install the plate (16) on the engine electrical box.

(e)

Install the washers (17), the bolts (18) and tighten the bolts.

(f)

Install the spacers (5), the clamp blocks (6) and the bobbins (11) on the pylon.

(g)

Install the spacers (7) and the clamps (8).

(h)

Install the washers (9), the nuts (10) and tighten the nuts (10).

(i)

Install the four electrical feeders on the plate 400VT (4) with the nuts (1) (Ref. AWM 24-22-01) and (Ref. AWM 24-22-02).

(j)

Tighten the nuts (1) (Ref. ESPM 20-44-52).

(k)

Install the cover (3) and the new LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA (Material No: 19-010) (2) on the plate (4).

(l)

Remove the blanking caps from the electrical connector(s).

(m) Make sure that the electrical connectors are clean and in the correct condition. (n)

AES

Connect the IDG feeder connector to the connector (14).

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-410-075-C B.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the right fan cowl (Ref. TASK 71-13-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 438AR

(b)

FOR 1000EM2 (ENGINE-2) 448AR

(3)

Close these access panels: . For the right pylon: 424AR . For the left pylon: 414AR

(4)

Remove the access platform(s).

(5)

Remove the warning notice(s).

Subtask 24-92-00-710-050-A C.

5.

Test (1)

Energize the aircraft electrical circuits from engine 1(2) (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

On the ECAM control panel, push the ELEC key to get the ELEC page: . Make sure that the voltage of the IDG is 115 VAC. . Make sure that the frequency of the IDG is 400Hz + or - 5Hz.

Close-up Subtask 24-92-00-942-054-A A.

Put the aircraft back to its initial configuration (1)

AES

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002-A-02).

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-000-002-A Removal of the IDG Feeders from the Wing and the Pylon 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

CAP - BLANKING

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels

ZONE/ACCESS 131MW, 131PW, 132MW, 132PW, 414AR, 414CR, 414FR, 423FL, 424AR, 424CR, 424ER, 521AB, 521BT, 521CB, 521EB, 621AB, 621BT, 621CB, 621EB, 825AR C.

ZONE DESCRIPTION

Referenced Information

REFERENCE 25-54-12-000-001-A

DESIGNATION Removal of the Forward Cargo-Compartment Partition FR34

25-54-12-000-003-A

Removal of the Sidewall Panels in the Forward Cargo-Compartment

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump 57-41-37-000-004-A Removal of the Pressure-Relief Panels (Ref. Fig. 24-92-00-991-04200-B - IDG Feeders) 3.

Job Set-up Subtask 24-92-00-860-083-A A.

Aircraft Maintenance Configuration (1)

On the center pedestal, on the ENG panel 115VU: (a)

AES

Put a WARNING NOTICE(S) in position to tell persons not to start the engine 1(2).

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-010-075-A B.

Get Access (1)

4.

Removal of the access panels (a)

For the left pylon: . 414FR 414CR 414AR

(b)

For the right pylon: . 424ER 424CR 424AR 423FL

(c)

For the left wing: . 521EB 521CB 521AB (Ref. TASK 57-41-37-000-004-A) . 521BT.

(d)

For the right wing: . 621EB 621CB 621AB (Ref. TASK 57-41-37-000-004-A) . 621BT.

(2)

Open the FWD cargo-compartment door 825AR (Ref. TASK 52-30-00-860-001-A).

(3)

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 825AR.

(4)

In the zone 131, remove the sidewall and partition panels (Ref. TASK 25-54-12-000-003-A) and (Ref. TASK 25-54-12-000-001-A). (a)

For the left IDG feeders: . 131PW 131MW

(b)

For the right IDG feeders: . 132PW 132MW

Procedure (Ref. Fig. 24-92-00-991-04200-B - IDG Feeders) Subtask 24-92-00-020-051-A A.

Removal of the IDG feeder cables (1)

AES

Disconnect the feeder cables from the right side of the pylon: (a)

Remove the bolts (27), the washers (28) and the plate (29).

(b)

Disconnect the electrical connector from the connector (19).

(c)

Put blanking caps on the disconnected electrical connector(s).

(d)

Remove the four nuts (18) and the four screws (21).

(e)

Disengage the connector (19) from the engine electrical box (20).

(f)

Remove the nut (14), the washer (15) and the bolt (17) from the clamp (16).

(g)

Remove the bolt (13) and the washer (12) from the clamp (11).

(h)

Remove and discard the lockwire (22) from the two screws (23).

(i)

Remove the screws (23) and the cover (24) from the terminal block (25).

(j)

Remove the nuts (26) and disconnect the electrical feeders from the terminal block (25).

(2)

Loosen the nut (31) of the pressure seal (32) on the wing above the pylon.

(3)

Remove the bolt (33) and the washer (34) from the clamp (37).

(4)

Remove the sealant from the bolt (35).

(5)

Remove the bolt (35) from the ground point (36).

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (6)

Loosen the nut (45) of the pressure seal (46) at the wing and cargo compartment junction.

(7)

Disconnect the electrical feeders in the cargo compartment:

(8)

(9)

(a)

Remove and discard the lockwire (42) from the two screws (41).

(b)

Remove the screws (41) and the cover (43) from the terminal block (44).

(c)

Remove the nuts (40) and disconnect the electrical feeders from the terminal block (44).

Removal of the cable supports along the IDG feeder cables: (a)

Cut and remove all the cable ties (1).

(b)

Remove all the bolts (3), the plate (4) and the spacers (5).

(c)

Remove all the bolts (7) and the nuts (8).

(d)

Remove all the nuts (9) and the bolts (10).

(e)

Disengage all the cable supports (2).

Removal of the IDG feeder cables: CAUTION :

(a)

AES

BE CAREFUL NOT TO CAUSE DAMAGE TO THE IDG FEEDERS WHEN YOU REMOVE/INSTALL THEM.

Remove the IDG feeder cables from the wing, the pylon and the cargo compartment.

24-92-00 PB401

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

E

K

A

A

G

TYPICAL 1

A B

9

2

A TYPICAL

10

TYPICAL TYPICAL

3 8

2

2

4

2

5

7

N_MM_249200_4_ACM0_01_00

AES

FIGURE 24-92-00-991-04200-B SHEET 1 IDG Feeders

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

B D

A C SECTION 11

A−A

12

13

C 14 15 16 26 17

27

28

D

23 29

22

24

18

19 401VC1 (401VC2)

25

A 400VT1 (400VT2)

A 21

20 N_MM_249200_4_ACM0_02_00

AES

FIGURE 24-92-00-991-04200-B SHEET 2 IDG Feeders

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

E

F

F

30 33.5mm minimum (1.32in.)

N_MM_249200_4_ACM0_03_00

AES

FIGURE 24-92-00-991-04200-B SHEET 3 IDG Feeders

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

G

H

J

4049VN (4050VN)

J 37

H

4019VP (4020VP)

34 33 36

31

32

35

N_MM_249200_4_ACM0_04_00

AES

FIGURE 24-92-00-991-04200-B SHEET 4 IDG Feeders

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

K

M L

SECTION

A−A

40

FW

D

L

1999VT (1998VT)

42 41

M

4009VP (4010VP)

43

44

45

46

A

A N_MM_249200_4_ACM0_05_00

AES

FIGURE 24-92-00-991-04200-B SHEET 5 IDG Feeders

24-92-00 PB401

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-400-002-A Installation of the IDG Feeders on the Wing and the Pylon 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

TIE WRAP

No specific

AR

WARNING NOTICE(S)

B.

Consumable Materials

REFERENCE Material No: 09-002 Material No: 19-010 C.

DESIGNATION SEALANTS LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

131MW, 131PW, 132MW, 132PW, 414AR, 414CR, 414FR, 423FL, 424AR, 424CR, 424ER, 521AB, 521BT, 521CB, 521EB, 621AB, 621BT, 621CB, 621EB, 825AR D.

Referenced Information

REFERENCE 24-41-00-861-002-A

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

25-54-12-000-001-A

Removal of the Forward Cargo-Compartment Partition FR34

25-54-12-000-003-A

Removal of the Sidewall Panels in the Forward Cargo-Compartment

25-54-12-400-001-A

Installation of the Forward Cargo-Compartment Partition FR34

25-54-12-400-003-A

Installation of the Sidewall Panels in the Forward Cargo- Compartment

31-60-00-860-002-A

EIS Stop Procedure

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Removal of the Pressure-Relief Panels Installation of the Pressure-Relief Panels

52-30-00-860-002-A 57-41-37-000-004-A 57-41-37-400-002-A ESPM 20-44-52-0 ESPM 20-46-10-0

AES

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE ESPM 20-48-19-0 AWM 24-22-01 AWM 24-22-02 (Ref. Fig. 24-92-00-991-04200-B - IDG Feeders) 3.

DESIGNATION

Job Set-up Subtask 24-92-00-860-084-A A.

Aircraft Maintenance Configuration (1)

On the center pedestal, on the panel 115VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the engine.

(2)

On the overhead maintenance panel 50VU: (a)

Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b)

Make sure that a WARNING NOTICE(S) is in position to tell persons not to energize the FADEC 1(2).

Subtask 24-92-00-010-076-A B.

Get Access (1)

4.

Make sure that these access panels are removed: (a)

For the left pylon: . 414FR 414CR 414AR

(b)

For the right pylon: . 424ER 424CR 424AR 423FL

(c)

For the left wing: . 521EB 521CB 521AB (Ref. TASK 57-41-37-000-004-A) . 521BT.

(d)

For the right wing: . 621EB 621CB 621AB (Ref. TASK 57-41-37-000-004-A) . 621BT.

(2)

Make sure that the FWD cargo-compartment door 825AR is open (Ref. TASK 52-30-00-860-001-A).

(3)

Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 825AR.

(4)

In the zone 131, make sure that these sidewall and partition panels are removed (Ref. TASK 25-54-12-000-003-A) and (Ref. TASK 25-54-12-000-001-A): (a)

For the left IDG feeders: . 131PW 131MW

(b)

For the right IDG feeders: . 132PW 132MW

Procedure (Ref. Fig. 24-92-00-991-04200-B - IDG Feeders)

AES

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-420-053-A A.

Installation of the IDG feeder cables CAUTION :

BE CAREFUL NOT TO CAUSE DAMAGE TO THE IDG FEEDERS WHEN YOU REMOVE/INSTALL THEM.

(1)

Put the feeder cables in position in the cargo compartment, the wing and the pylon.

(2)

Connection of the feeder cables on the right side of the pylon: (a)

Install the electrical feeder cables on the terminal block (25) with the nuts (26) (Ref. AWM 24-22-01) or (Ref. AWM 24-22-02).

(b)

Tighten the nuts (26) (Ref. ESPM 20-44-52-0).

(c)

Install the cover (24) with the screws (23) on the terminal block (25).

(d)

Tighten the screws (23) and safety with new LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA (Material No: 19-010) (22).

(e)

Install the connector (19) in the engine electrical box (20). NOTE :

When you put the connector in place, make sure that the harness is not twisted.

(f)

Install the screws (21) and the nuts (18) and tighten the nuts (18).

(g)

Install the clamp (16) with the bolt (17), the washer (15) and the nut (14).

(h)

Install the clamp (11) with the bolt (13) and the washer (12).

(i)

Tighten the nut (14) and the bolt (13).

(j)

Remove the blanking caps from the electrical connector(s).

(k)

Make sure that the electrical connectors are clean and in the correct condition.

(l)

Connect the electrical connector to the connector (19).

(m) Install the plate (29) on the engine electrical box. (n)

AES

Install the washers (28), the bolts (27) and tighten the bolts (27).

(3)

Install the nut (31) on the pressure seal (32) on the wing above the pylon and tighten it.

(4)

Install the bolt (33) with the washer (34) on the clamp (37).

(5)

Install the bolt (35) on the ground point (36) (Ref. ESPM 20-48-19-0).

(6)

Tighten the bolts (33) and (35).

(7)

Apply SEALANTS (Material No: 09-002) on the ground point (36).

(8)

Install the nut (45) on the pressure seal (46) at the wing and cargo compartment junction and tighten it.

(9)

Connection of the feeder cables in the cargo compartment: (a)

Install the electrical feeder cables on the terminal block (44) with the nuts (40) (Ref. AWM 24-22-01) or (Ref. AWM 24-22-02).

(b)

Tighten the nuts (40) (Ref. ESPM 20-44-52-0).

(c)

Install the cover (43) with the screws (41) on the terminal block (44).

(d)

Tighten the screws (41) and safety with new LOCKWIRE STAINLSS STL ANNEALED 0.8MM DIA (Material No: 19-010) (42).

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (10) Installation of the cable supports along the IDG feeder cables: CAUTION :

MAKE SURE THAT THE IDG CABLES DO NOT TOUCH THE PYLON FITTING. IF THE IDG CABLES TOUCH THE PYLON FITTING, DAMAGE WILL OCCUR TO THE CABLES AND/OR PYLON FITTING.

(a)

Install the clamp block (30) on the rod with a clearance of 33.5 mm (1.32 in.) minimum between the top axis attachment of the rod and the top axis attachment of the clamp block.

(b)

Make sure that there is a clearance of 25 mm (0.98 in.) minimum between the IDG feeder cables and the pylon fitting.

(c)

Make sure that there is a clearance of 20 mm (0.79 in.) minimum between the IDG feeder cables and the other components of the structure.

(d)

Turn the clamp block to give maximum clearance between the pylon fitting and the feeder cables.

(e)

Put all the cable supports (2) in position.

(f)

Install all the bolts (7) and the nuts (8) and tighten the nuts (8).

(g)

Install all the bolts (10) and the nuts (9) and tighten the nuts (9).

(h)

Install all the spacers (5), the plate (4) and the bolts (3) and tighten the bolts (3).

(i)

Install all the new TIE WRAP (1) (Ref. ESPM 20-46-10-0).

Subtask 24-92-00-710-051-A B.

5.

Test (1)

Energize the aircraft electrical circuits from engine 1(2) (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002-A-02).

(2)

On the ECAM control panel, push the ELEC key to get the ELEC page: . Make sure that the voltage of the IDG is 115 VAC. . Make sure that the frequency of the IDG is 400Hz + or - 5Hz.

Close-up Subtask 24-92-00-410-076-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close these access panels: (a)

For the left pylon: . 414FR 414CR 414AR

(b)

For the right pylon: . 424ER 424CR 424AR 423FL

(c)

For the left wing: . 521EB 521CB 521AB (Ref. TASK 57-41-37-400-002-A) . 521BT.

(d)

For the right wing: . 621EB 621CB 621AB (Ref. TASK 57-41-37-400-002-A) . 621BT.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

In the zone 131, install the sidewall and partition panels (Ref. TASK 25-54-12-400-003-A) and (Ref. TASK 25-54-12-400-001-A). (a)

For the left IDG feeders: . 131PW 131MW

(b)

For the right IDG feeders: . 132PW 132MW

(4)

Close the FWD cargo-compartment door 825AR (Ref. TASK 52-30-00-860-002-A).

(5)

Remove the warning notice(s).

(6)

Remove the access platform(s).

Subtask 24-92-00-942-055-A B.

Put the aircraft back to its initial configuration (1)

AES

Do the EIS stop procedure (Ref. TASK 31-60-00-860-002-A)

24-92-00 PB401

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

ELECTRICAL ROUTING - INSPECTION/CHECK ** On A/C ALL Task 24-92-00-210-003-A Inspection of the End Fittings of Electrical Conduits in Wing Inboard Leading- Edge WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-04-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN WING INBOARD LEADING EDGE Apply temporary protection to end fittings of electrical conduits in wing inboard leading-edge.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004 Material No: 15-008

AES

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM) STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE Material No: 19-003 C.

DESIGNATION LINT-FREE COTTON CLOTH

Work Zones and Access Panels ZONE/ACCESS

521 621 471CL, 482CR, 521GB, 621GB D.

ZONE DESCRIPTION INBOARD FIXED L.E STRUCTURE INBOARD FIXED L.E STRUCTURE

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

27-80-00-866-004-A

Extending the Slats on the Ground

27-80-00-866-005-A

Retracting the Slats on the Ground

(Ref. Fig. 24-92-00-991-00500-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-00700-A - Location of Conduit Fittings) 3.

Job Set-up Subtask 24-92-00-860-055-A A.

Aircraft Maintenance Configuration (1)

Extend the slats (Ref. TASK 27-80-00-866-004-A).

Subtask 24-92-00-862-052-A B.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-054-A C.

Connect the aircraft to the ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-052-A D.

Get Access (1)

Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the wing inboard leadingedge.

(2)

For the left wing. (a)

(3)

For the right wing. (a)

AES

Remove and retain the access panels: 521GB 471CL. Remove and retain the access panels: 621GB 482CR.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure Subtask 24-92-00-210-052-A A.

Inspection of the End Fittings of Electrical Conduits (Ref. Fig. 24-92-00-991-00500-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-00700-A - Location of Conduit Fittings) WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP. (1)

At each fitting use the procedure that follows to protect against corrosion: (a)

Use CLEANING AGENTS (Material No: 11-004) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

(b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or a EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-053-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

For the left wing. (a)

(3)

Install the access panels: 521GB 471CL.

For the right wing. (a)

Install the access panels: 621GB 482CR.

Subtask 24-92-00-860-056-A B.

AES

Put the aircraft back to its initial configuration. (1)

Disconnect the aircraft from the ground (Ref. TASK 12-34-24-869-002-A).

(2)

Retract the slats (Ref. TASK 27-80-00-866-005-A).

(3)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

CONDUIT FITTINGS

CONDUIT FITTINGS

N_MM_249200_6_AJM0_01_00

AES

FIGURE 24-92-00-991-00500-A SHEET 1 Electrical Harness Conduits - Corrosion Protection

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

BACKSHELL

A

TRANSITION CONNECTOR

B

A

B

3 AND 4 WAY 45° TRANSITIONS 3 AND 4 WAY 90° TRANSITIONS

45° ELBOW ADAPTER

MALE BULKHEAD ADAPTER

BULKHEAD ADAPTER

90° ELBOW ADAPTER

NUT

JOINER

TRANSITION JOINER

CLAMPFITTING

N_MM_249200_6_ALM0_01_00

AES

FIGURE 24-92-00-991-00600-A SHEET 1 Typical Fittings

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A FALSE REAR SPAR

Z520 (Z620)

C

FWD

B

N_MM_249200_6_ANM0_01_00

AES

FIGURE 24-92-00-991-00700-A SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

1

B

PROTECT FITTING AGAINST CORROSION.

1

1

C 1 1

1

N_MM_249200_6_ANM0_02_00

AES

FIGURE 24-92-00-991-00700-A SHEET 2 Location of Conduit Fittings

24-92-00 PB601

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-004-A Inspection of the End Fittings of Electrical Conduits in Wing Outboard Leading-Edge WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-05-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN WING OUTBOARD LEADING EDGE Apply temporary protection to end fittings of electrical conduits in wing outboard leading-edge.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)

Material No: 15-008

STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY LINT-FREE COTTON CLOTH

Material No: 19-003

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Work Zones and Access Panels ZONE/ACCESS

522 622 522AB, 622AB D.

ZONE DESCRIPTION OUTBOARD FIXED L.E STRUCTURE OUTBOARD FIXED L.E STRUCTURE

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

27-80-00-866-004-A

Extending the Slats on the Ground

27-80-00-866-005-A

Retracting the Slats on the Ground

57-41-37-000-004-A Removal of the Pressure-Relief Panels 57-41-37-400-002-A Installation of the Pressure-Relief Panels (Ref. Fig. 24-92-00-991-00800-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-00900-A - Location of Conduit Fittings) 3.

Job Set-up Subtask 24-92-00-860-057-A A.

Aircraft Maintenance Configuration (1)

Extend the slats (Ref. TASK 27-80-00-866-004-A).

Subtask 24-92-00-862-053-A B.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-057-A C.

Connect the aircraft to the ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-053-A D.

Get Access (1)

Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the wing outboard leadingedge.

(2)

For the left wing. (a)

(3)

For the right wing. (a)

AES

Remove and retain the access panels: 522AB (Ref. TASK 57-41-37-000-004-A). Remove and retain the access panels: 622AB (Ref. TASK 57-41-37-000-004-A).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure Subtask 24-92-00-210-053-A A.

Inspection of the End Fittings of Electrical Conduits (Ref. Fig. 24-92-00-991-00800-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-00900-A - Location of Conduit Fittings) WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP. (1)

At each fitting use the procedure that follows to protect against corrosion: (a)

Use CLEANING AGENTS (Material No: 11-004) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

(b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or a EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-054-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

For the left wing. (a)

(3)

Install the access panels: 522AB (Ref. TASK 57-41-37-400-002-A).

For the right wing. (a)

Install the access panels: 622AB (Ref. TASK 57-41-37-400-002-A).

Subtask 24-92-00-860-058-A B.

AES

Put the aircraft back to its initial configuration. (1)

Disconnect the aircraft from the ground (Ref. TASK 12-34-24-869-002-A).

(2)

Retract the slats (Ref. TASK 27-80-00-866-005-A).

(3)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

CONDUIT FITTINGS

CONDUIT FITTINGS

N_MM_249200_6_AQM0_01_00

AES

FIGURE 24-92-00-991-00800-A SHEET 1 Electrical Harness Conduits - Corrosion Protection

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A FALSE REAR SPAR

Z520 (Z620)

A

FWD

B

N_MM_249200_6_ASM0_01_00

AES

FIGURE 24-92-00-991-00900-A SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

B

1

PROTECT FITTING AGAINST CORROSION

1

1

1

1

N_MM_249200_6_ASM0_02_00

AES

FIGURE 24-92-00-991-00900-A SHEET 2 Location of Conduit Fittings

24-92-00 PB601

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-005-A Inspection of the End Fittings of Electrical Conduits in the Wing Tip WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-09-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN WING TIP Apply temporary protection to end fittings of electrical conduits in the wing tip.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)

Material No: 15-008

STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY LINT-FREE COTTON CLOTH

Material No: 19-003

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Work Zones and Access Panels ZONE/ACCESS

534 634 534AB, 634AB D.

ZONE DESCRIPTION WING TIP WING TIP

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

33-41-11-000-001-A

Removal of the Wingtip Navigation Light

33-41-11-400-001-A

Installation of the Wingtip Navigation Light

33-48-14-000-001-A

Removal of the Strobe Light

33-48-14-400-001-A

Installation of the Strobe Light

(Ref. Fig. 24-92-00-991-01000-A - Electrical Harness Conduits) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-01100-A - Location of Conduit Fittings) 3.

Job Set-up Subtask 24-92-00-862-054-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-059-A B.

Connect the aircraft to the ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-054-B C.

Get Access (1)

Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the wing tip.

(2)

For the left wing. (a)

(3)

For the right wing. (a)

4.

Remove and retain the access panel: 534AB. Remove and retain the access panel: 634AB.

(4)

Remove the Wingtip Navigation Light 9LA (10LA) (Ref. TASK 33-41-11-000-001-A).

(5)

Remove the strobe light (Ref. TASK 33-48-14-000-001-A).

Procedure Subtask 24-92-00-210-054-A A.

AES

Inspection of the End Fittings of Electrical Conduits (Ref. Fig. 24-92-00-991-01000-A - Electrical Harness Conduits) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings)

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (Ref. Fig. 24-92-00-991-01100-A - Location of Conduit Fittings) WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP. (1)

At each fitting use the procedure that follows to protect against corrosion: (a)

Use CLEANING AGENTS (Material No: 11-004) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

(b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or a EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-055-B A.

Close Access (1)

Install the strobe light (Ref. TASK 33-48-14-400-001-A).

(2)

Install the Wingtip Navigation Light 9LA (10LA) (Ref. TASK 33-41-11-400-001-A).

(3)

Make sure that the work area is clean and clear of tool(s) and other items.

(4)

For the left wing. (a)

(5)

For the right wing. (a)

AES

Install the access panel: 534AB. Install the access panel: 634AB.

(6)

Disconnect the aircraft from the ground (Ref. TASK 12-34-24-869-002-A).

(7)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

CONDUIT FITTINGS

CONDUIT FITTINGS

N_MM_249200_6_AUM0_01_00

AES

FIGURE 24-92-00-991-01000-A SHEET 1 Electrical Harness Conduits

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

1

PROTECT FITTING AGAINST CORROSION.

A

A

Z534 (Z634)

1

1

1 1

N_MM_249200_6_AWM0_01_00

AES

FIGURE 24-92-00-991-01100-A SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-006-A Inspection of the End Fittings of Electrical Conduits in Wing Outboard Trailing -Edge WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-07-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN WING OUTBOARD TRAILING EDGE Apply temporary protection to end fittings of electrical conduits in wing outboard trailing-edge.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)

Material No: 15-008

STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY LINT-FREE COTTON CLOTH

Material No: 19-003

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Work Zones and Access Panels ZONE/ACCESS

575 675 575BB, 575CB, 575DB, 575EB, 575FB, 575GB, 575HB, 575KB, 575LB, 575MB, 675BB, 675CB, 675DB, 675EB, 675FB, 675GB, 675HB, 675KB, 675LB, 675MB D.

ZONE DESCRIPTION AFT OUTBD SE OF WING AND TE FIXED STRUCT AFT OUTBD SE OF WING AND TE FIXED STRUCT

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

27-50-00-866-008-A

Extension of the Flaps on the Ground

27-50-00-866-008-A-01

Extension of the Flaps/Slats on the Ground

27-50-00-866-009-A

Retraction of the Flaps on the Ground

27-50-00-866-009-A-01

Retraction of the Flaps/Slats on the Ground

27-60-00-866-002-A

Extension-Retraction of the Spoilers for Maintenance

(Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-01200-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-01300-C - Location of Conduit Fittings) 3.

Job Set-up Subtask 24-92-00-860-061-A A.

Aircraft Maintenance Configuration (1)

Extend the flaps (Ref. TASK 27-50-00-866-008-A) or (Ref. TASK 27-50-00-866-008-A-01).

(2)

Extend the spoilers (Ref. TASK 27-60-00-866-002-A).

Subtask 24-92-00-862-055-A B.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-061-A C.

Connect the aircraft to the ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-055-A D.

Get Access (1)

AES

Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the wing outboard trealingedge.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

For the left wing. (a)

(3)

For the right wing. (a)

4.

Remove and retain the access panel: 575BB 575CB 575DB 575EB 575FB 575GB 575HB 575KB 575LB 575MB. Remove and retain the access panel: 675BB 675CB 675DB 675EB 675FB 675GB 675HB 675KB 675LB 675MB.

Procedure (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-01200-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-01300-C - Location of Conduit Fittings) Subtask 24-92-00-210-055-A A.

Inspection of the End Fittings of Electrical Conduits WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP. (1)

At each fitting, use the procedure that follows to protect against corrosion: (a)

Use CLEANING AGENTS (Material No: 11-004) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

(b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or a EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-056-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

For the left wing. (a)

(3)

Install the access panel: 575BB 575CB 575DB 575EB 575FB 575GB 575HB 575KB 575LB 575MB.

For the right wing. (a)

Install the access panel: 675BB 675CB 675DB 675EB 675FB 675GB 675HB 675KB 675LB 675MB.

Subtask 24-92-00-860-062-A B.

AES

Put the aircraft back to its initial configuration. (1)

Disconnect the aircraft from the ground (Ref. TASK 12-34-24-869-002-A).

(2)

Retract the spoilers (Ref. TASK 27-60-00-866-002-A).

(3)

Retract the flaps (Ref. TASK 27-50-00-866-009-A) or (Ref. TASK 27-50-00-866-009-A-01).

(4)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

CONDUIT FITTINGS

CONDUIT FITTINGS

N_MM_249200_6_AYM0_01_00

AES

FIGURE 24-92-00-991-01200-A SHEET 1 Electrical Harness Conduits - Corrosion Protection

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

1

PROTECT END−FITTING AGAINST CORROSION

Z575 (Z675)

A

A

RIB14

RIB13

RIB11

RIB12

1

N_MM_249200_6_BFM0_01_00

AES

FIGURE 24-92-00-991-01300-C SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

1

PROTECT FITTING AGAINST CORROSION

Z575 (Z675)

B

B RIB14

RIB17

1

1

1

1

1

RIB18

RIB21

1

1

1

N_MM_249200_6_BFM0_02_00

AES

FIGURE 24-92-00-991-01300-C SHEET 2 Location of Conduit Fittings

24-92-00 PB601

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

1

C

PROTECT FITTING AGAINST CORROSION

Z575 (Z675)

RIB22

C

1

1

RIB27

N_MM_249200_6_BFM0_03_00

AES

FIGURE 24-92-00-991-01300-C SHEET 3 Location of Conduit Fittings

24-92-00 PB601

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

RIB 27 575MB (675MB) 575LB (675LB)

C 575KB (675KB)

RIB 22

575HB (675HB) 575GB (675GB)

B 575FB (675FB)

RIB 17

575EB (675EB)

RIB 14

575DB (675DB) 575CB (675CB)

RIB 11

A 575BB (675BB)

N_MM_249200_6_BFM0_04_00

AES

FIGURE 24-92-00-991-01300-C SHEET 4 Location of Conduit Fittings

24-92-00 PB601

Page 8 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-007-A Inspection of the End Fittings of Electrical Conduits in the Air Conditioning Compartment WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-11-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN AIR CONDITIONING COMPARTMENT Apply temporary protection to end fittings of electrical conduits in the air conditioning compartment.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)

Material No: 15-008

STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY LINT-FREE COTTON CLOTH

Material No: 19-003

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Work Zones and Access Panels ZONE/ACCESS

191

ZONE DESCRIPTION AIR CONDITONING COMPT AND FAIRING AIR CONDITONING COMPT AND FAIRING AIR CONDITONING COMPT AND FAIRING AIR CONDITONING COMPT AND FAIRING

192 191BB, 191KB, 192FB, 192KB D.

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

32-12-00-010-001-A

Open the Main Gear Doors for Access

32-12-00-410-001-A Close the Main Gear Doors after Access (Ref. Fig. 24-92-00-991-01400-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-01500-A - Location of Conduit Fittings) 3.

Job Set-up Subtask 24-92-00-862-056-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-063-A B.

Connect the aircraft to the ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-056-A C.

4.

Get Access (1)

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the wing and the center fuselage.

(2)

For the center fuselage. (a)

Remove the access panels: 191BB, 191KB, 192FB, 192KB.

(b)

Open the L and R main landing-gear doors at zone 734 and 744 (Ref. TASK 32-12-00-010-001A).

Procedure Subtask 24-92-00-210-056-A A.

AES

Inspection of the End Fittings of Electrical Conduits (Ref. Fig. 24-92-00-991-01400-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-01500-A - Location of Conduit Fittings)

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP. (1)

At each fitting use the procedure that follows to protect against corrosion: (a)

Use CLEANING AGENTS (Material No: 11-004) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

(b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or a EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-057-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

For the center fuselage. (a)

Install the access panels: 191BB, 191KB, 192FB, 192KB.

(b)

Close the L and R main landing-gear doors at zone 734 and 744 (Ref. TASK 32-12-00-410-001A).

(3)

Disconnect the aircraft from the ground (Ref. TASK 12-34-24-869-002-A).

(4)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

CONDUIT FITTINGS

CONDUIT FITTINGS

N_MM_249200_6_BCM0_01_00

AES

FIGURE 24-92-00-991-01400-A SHEET 1 Electrical Harness Conduits - Corrosion Protection

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR47

FR43 FR42

D D

FR35

E E

B

C 1

A 1

C

A 1

B

1

1

PROTECT FITTING AGAINST CORROSION

N_MM_249200_6_BEM0_01_00

AES

FIGURE 24-92-00-991-01500-A SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR43

E 1

FR42

D FR43 1

4X

1 1

1

3X

PROTECT FITTING AGAINST CORROSION

N_MM_249200_6_BEM0_02_00

AES

FIGURE 24-92-00-991-01500-A SHEET 2 Location of Conduit Fittings

24-92-00 PB601

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-008-A Inspection of the End Fittings of electrical Conduits in Vertical Stabilizer Trailing-Edge WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-13-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN VERTICAL STABILIZER TRAILING EDGE Apply temporary protection to end fittings of electrical conduits in vertical stabilizer trailing-edge.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 8M (26 FT) - ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)

Material No: 15-008

STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY LINT-FREE COTTON CLOTH

Material No: 19-003

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Work Zones and Access Panels ZONE/ACCESS

325 325BL, 325BR, 325CL, 325DL D.

ZONE DESCRIPTION VERTICAL STABILIZER TRAILING EDGE

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

(Ref. Fig. 24-92-00-991-01600-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-01700-A - Location of Conduit Fittings) 3.

Job Set-up Subtask 24-92-00-862-057-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-065-A B.

Connect the aircraft to ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-057-A C.

Get Access (1)

Put the ACCESS PLATFORM 8M (26 FT) - ADJUSTABLE in position at the vertical stabilizer trailingedge.

(2)

For the left vertical stabilizer trailing-edge. (a)

(3)

For the right vertical stabilizer trailing-edge. (a)

4.

Remove and retain the access panels: 325CL 325DL.

Remove and retain the access panels 325BL 325BR.

Procedure Subtask 24-92-00-210-057-A A.

Inspection of the End Fittings of Electrical Conduits (Ref. Fig. 24-92-00-991-01600-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-01700-A - Location of Conduit Fittings) WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP. (1)

At each fitting use the procedure that follows to protect against corrosion: (a)

AES

Use CLEANING AGENTS (Material No: 11-004) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or a EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-058-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

For the left vertical stabilizer trailing-edge. (a)

(3)

For the right vertical stabilizer trailing-edge. (a)

AES

Install the access panels: 325CL 325DL.

Install the access panels: 325BL 325BR.

(4)

Disconnect the aircraft from ground (Ref. TASK 12-34-24-869-002-A).

(5)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

B

CONDUIT FITTINGS

CONDUIT FITTINGS

A

A VERTICAL STABILIZER

325DL 325CL 325BL

B VERTICAL STABILIZER

325BR

N_MM_249200_6_BGM0_01_00

AES

FIGURE 24-92-00-991-01600-A SHEET 1 Electrical Harness Conduits - Corrosion Protection

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

1

A 1

FR73

A

1

PROTECT FITTING AGAINST CORROSION

RIB4 1 1 1 1 1 1 1

1

1

1

RIB2 N_MM_249200_6_BJM0_01_00

AES

FIGURE 24-92-00-991-01700-A SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-010-A Inspection of the End Fittings of Electrical Conduits in the Fuselage Tail Area WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-12-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN FUSELAGE TAIL AREA Apply temporary protection to end fittings of electrical conduits in the fuselage tail area.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)

Material No: 11-016

CLEANING AGENTS CLEANING SOLVENT CLEANING AGENTS SOLVENT GENERAL PURPOSE CLEANING AGENTS LIQUID CLEANING AGENT

Material No: 11-026 Material No: 11-027

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE Material No: 15-008 Material No: 19-003 C.

DESIGNATION STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY LINT-FREE COTTON CLOTH

Work Zones and Access Panels ZONE/ACCESS

311 312 312AR, 314AR, 315AL, 316AR D.

ZONE DESCRIPTION AFT FUSLG TAIL SECTION AFT FUSLG TAIL SECTION

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

(Ref. Fig. 24-92-00-991-02000-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-02100-A - Location of Conduit Fittings) 3.

Job Set-up Subtask 24-92-00-862-059-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-069-A B.

Connect the aircraft to the ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-059-A C.

4.

Get Access (1)

Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the fuselage tail area.

(2)

Remove and retain the access panels: 312AR 314AR.

(3)

Open the access doors: 315AL 316AR.

Procedure Subtask 24-92-00-210-059-A A.

Inspection of the End Fittings of Electrical Conduits (Ref. Fig. 24-92-00-991-02000-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-02100-A - Location of Conduit Fittings) WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP.

AES

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (1)

At each fitting use the procedure that follows to protect against corrosion: (a)

Use CLEANING AGENTS (Material No: 11-004) or CLEANING AGENTS (Material No: 11-016) or CLEANING AGENTS (Material No: 11-026) or CLEANING AGENTS (Material No: 11-027) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

(b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or a EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-060-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the access panels: 312AR 314AR.

(3)

Close the access doors: 315AL 316AR.

(4)

Disconnect the aircraft from the ground (Ref. TASK 12-34-24-869-002-A).

(5)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

CONDUIT FITTINGS

N_MM_249200_6_BQM0_01_00

AES

FIGURE 24-92-00-991-02000-A SHEET 1 Electrical Harness Conduits - Corrosion Protection

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR77

A

1

PROTECT FITTING AGAINST CORROSION FR74

FR70

FR73 FR72

A 1

1 1

1

1

1

N_MM_249200_6_BSM0_01_00

AES

FIGURE 24-92-00-991-02100-A SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 1

PROTECT FITTING AGAINST CORROSION FR77

B

C D

B

Z310

C

1

1 1

D

1

1 1

1

1 N_MM_249200_6_BSM0_02_00

AES

FIGURE 24-92-00-991-02100-A SHEET 2 Location of Conduit Fittings

24-92-00 PB601

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-011-A Inspection of the End Fittings of Electrical Conduits in Trimmable Horizontal Stabilizer (THS) WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-16-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN TRIMMABLE HORIZONTAL STABILIZER Apply temporary protection to end fittings of electrical conduits in the THS.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 6M (20 FT) - ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)

Material No: 15-008

STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY LINT-FREE COTTON CLOTH

Material No: 19-003

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Work Zones and Access Panels ZONE/ACCESS

334 344 334CB, 334DB, 334EB, 344CB, 344DB, 344EB D.

ZONE DESCRIPTION THS TRAILING EDGE THS TRAILING EDGE

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

(Ref. Fig. 24-92-00-991-02200-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-02300-A - Location of Conduit Fittings) 3.

Job Set-up Subtask 24-92-00-862-060-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02)

Subtask 24-92-00-869-071-A B.

Connect the aircraft to ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-060-A C.

Get Access (1)

Put the ACCESS PLATFORM 6M (20 FT) - ADJUSTABLE in position at the THS.

(2)

For the left THS: (a)

(3)

For the right THS: (a)

4.

Remove and retain the access panels: 334CB 334DB 334EB.

Remove and retain the access panels: 344CB 344DB 344EB.

Procedure Subtask 24-92-00-210-060-A A.

Inspection of the End Fittings of Electrical Conduits (Ref. Fig. 24-92-00-991-02200-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-02300-A - Location of Conduit Fittings) WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP. (1)

At each fitting use the procedure that follows to protect against corrosion: (a)

AES

Use CLEANING AGENTS (Material No: 11-004) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-061-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

For the left THS: (a)

(3)

For the right THS: (a)

AES

Install the access panels: 334CB 334DB 334EB.

Install the access panels: 344CB 344DB 344EB.

(4)

Disconnect the aircraft from ground (Ref. TASK 12-34-24-869-002-A).

(5)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

CONDUIT FITTINGS

CONDUIT FITTINGS

N_MM_249200_6_BUM0_01_00

AES

FIGURE 24-92-00-991-02200-A SHEET 1 Electrical Harness Conduits - Corrosion Protection

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

1

PROTECT FITTING AGAINST CORROSION

A

A

A 1 1 TE−R0 TE−R3 TE−R5

TE−R2 TE−R1

TE−R4

ZONE : Z335 (Z345)

1

N_MM_249200_6_BWM0_01_00

AES

FIGURE 24-92-00-991-02300-A SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-012-A Inspection of the End Fittings of Electrical Conduits in Vertical Stabilizer Leading-Edge WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-15-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN VERTICAL STABILIZER LEADING EDGE Apply temporary protection to end fittings of electrical conduits in vertical stabilizer leading-edge.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)

Material No: 15-008

STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY LINT-FREE COTTON CLOTH

Material No: 19-003

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Work Zones and Access Panels ZONE/ACCESS

321 322 324 321AL, 322BL, 324AT D.

ZONE DESCRIPTION DORSAL FIN VERTICAL STABILIZER LEADING EDGE VERTICAL STABILIZER TIP

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

(Ref. Fig. 24-92-00-991-02400-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-02500-A - Location of Conduit Fittings) 3.

Job Set-up Subtask 24-92-00-862-061-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-073-A B.

Connect the aircraft to ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-061-A C.

4.

Get Access (1)

Put the ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE in position at the vertical stabilizer leading-edge.

(2)

Remove and retain the access panels: 321AL 322BL 324AT.

Procedure Subtask 24-92-00-210-061-A A.

Inspection of the End Fittings of Electrical Conduits (Ref. Fig. 24-92-00-991-02400-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-02500-A - Location of Conduit Fittings) WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP. (1)

At each fitting use the procedure that follows to protect against corrosion: (a)

AES

Use CLEANING AGENTS (Material No: 11-004) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or a EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-062-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the access panels: 321AL 322BL 324AT.

(3)

Disconnect the aircraft from ground (Ref. TASK 12-34-24-869-002-A).

(4)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

CONDUIT FITTINGS

A VERTICAL STABILIZER 324AT

322BL

321AL

N_MM_249200_6_BYM0_01_00

AES

FIGURE 24-92-00-991-02400-A SHEET 1 Electrical Harness Conduits - Corrosion Protection

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

1

PROTECT FITTING AGAINST CORROSION

1

RIB11

1

1

1 1

N_MM_249200_6_CAM0_01_00

AES

FIGURE 24-92-00-991-02500-A SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-013-A Inspection of the End Fittings of Electrical Conduits in Flap Track No. 2 Fairing WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-08-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN FLAP TRACK NUMBER 2 FAIRING Apply temporary protection to end fittings of electrical conduits in flap track No. 2 fairing.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)

Material No: 15-008

STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY LINT-FREE COTTON CLOTH

Material No: 19-003

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Work Zones and Access Panels ZONE/ACCESS

531 631 531AT, 631AT D.

ZONE DESCRIPTION FLAP TRACK 2 FAIRING FLAP TRACK 2 FAIRING

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

(Ref. Fig. 24-92-00-991-02600-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-02700-D - Location of Conduit Fittings) 3.

Job Set-up Subtask 24-92-00-862-063-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-077-A B.

Connect the aircraft to the ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-063-A C.

Get Access (1)

Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the flap track No. 2 fairing.

(2)

For the left wing: (a)

(3)

For the right wing: (a)

4.

Remove and retain the top cover of the movable fairing of the No. 2 flap track: 531AT.

Remove and retain the top cover of the movable fairing of the No. 2 flap track: 631AT.

Procedure Subtask 24-92-00-210-063-A A.

Inspection of the End Fittings of Electrical Conduits (Ref. Fig. 24-92-00-991-02600-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-02700-D - Location of Conduit Fittings) WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP. (1)

At each fitting use the procedure that follows to protect against corrosion: (a)

AES

Use CLEANING AGENTS (Material No: 11-004) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or a EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-064-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

For the left wing: (a)

(3)

For the right wing: (a)

AES

Install the top cover of the movable fairing of the No. 2 flap track: 531AT.

Install the top cover of the movable fairing of the No. 2 flap track: 631AT.

(4)

Disconnect the aircraft from the ground (Ref. TASK 12-34-24-869-002-A).

(5)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

CONDUIT FITTINGS

CONDUIT FITTINGS

N_MM_249200_6_CCM0_01_00

AES

FIGURE 24-92-00-991-02600-A SHEET 1 Electrical Harness Conduits - Corrosion Protection

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z531 (Z631)

A REAR SPAR

1

1

1

FLAP TRACK N°2 CENTER LINE

1

1

N_MM_249200_6_CEN0_01_00

AES

FIGURE 24-92-00-991-02700-D SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-014-A Inspection of the End Fittings of Electrical Conduits in the Main Landing Gear (MLG) Well and False Spar Box WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-06-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN MAIN LANDING GEAR BAY AND FALSE SPAR BOX Apply temporary protection to end fittings of electrical conduits in the MLG well and false spar box.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)

Material No: 15-008

STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY LINT-FREE COTTON CLOTH

Material No: 19-003

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Work Zones and Access Panels ZONE/ACCESS

571 574 671 674 574AB, 574BB, 674AB, 674BB D.

ZONE DESCRIPTION MLG BAY FALSE SPAR BOX MLG BAY FALSE SPAR BOX

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

(Ref. Fig. 24-92-00-991-02800-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-02900-A - Location of Conduit Fittings) (Ref. Fig. 24-92-00-991-03000-C - Location of Conduit Fittings) 3.

Job Set-up Subtask 24-92-00-862-064-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-079-A B.

Connect the aircraft to the ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-064-A C.

4.

Get Access (1)

Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the MLG well and false spar box.

(2)

Remove and retain the access panels: . For the left wing: 574AB 574BB. . For the right wing: 674AB 674BB.

Procedure Subtask 24-92-00-210-064-A A.

Inspection of the End Fittings of Electrical Conduits (Ref. Fig. 24-92-00-991-02800-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) (Ref. Fig. 24-92-00-991-02900-A - Location of Conduit Fittings) (Ref. Fig. 24-92-00-991-03000-C - Location of Conduit Fittings) WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP.

AES

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (1)

At each fitting use the procedure that follows to protect against corrosion: (a)

Use CLEANING AGENTS (Material No: 11-004) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

(b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or a EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-065-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the access panels: . For the left wing: 574AB 574BB. . For the right wing: 674AB 674BB.

(3)

Disconnect the aircraft from the ground (Ref. TASK 12-34-24-869-002-A).

(4)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

CONDUIT FITTINGS

CONDUIT FITTINGS

N_MM_249200_6_CGM0_01_00

AES

FIGURE 24-92-00-991-02800-A SHEET 1 Electrical Harness Conduits - Corrosion Protection

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Z571 (Z671)

1

PROTECT FITTING AGAINST CORROSION.

B A

A

1

1

1

1

1

1

1 1

1

N_MM_249200_6_CJM0_01_00

AES

FIGURE 24-92-00-991-02900-A SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

1

PROTECT FITTING AGAINST CORROSION.

UP

B OUTBOARD

FORWARD 1 OUTBOARD

1

1

C

1 1 1

RIB2

RH VIEW ON

LH VIEW ON

C−C 1

RIB1

C−C 1

LH LANDING LAMP

RH LANDING LAMP

N_MM_249200_6_CJM0_02_00

AES

FIGURE 24-92-00-991-02900-A SHEET 2 Location of Conduit Fittings

24-92-00 PB601

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Z574 (Z674)

1

PROTECT FITTING AGAINST CORROSION.

A

1

1

1

1

1 1

B 1

C

C 1

B

1 1 1

1

1 1 1

1 1 1 N_MM_249200_6_CLN0_01_00

AES

FIGURE 24-92-00-991-03000-C SHEET 1 Location of Conduit Fittings

24-92-00 PB601

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-015-A Inspection of tne End Fittings of Electrical Conduits in the Dry Bay (Outboard) WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. 1.

Reason for the Job (Ref. MPD 24-00-00-10-) APPLY TEMPORARY PROTECTION TO END FITTINGS OF ELECTRICAL CONDUITS IN DRY BAY (OUTBOARD) Apply temporary protection to end fittings of electrical conduits in the dry bay (outboard).

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

No specific

AR

BRUSH - BRISTLED

No specific

AR

EXTRACTION TOOL - SEAL

No specific

AR

SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL)

B.

Consumable Materials

REFERENCE Material No: 11-004

DESIGNATION CLEANING AGENTS 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)

Material No: 15-008

STORAGE PRESERVATION CORROSION PREVENTIVE COMPOUND, TEMPORARY LINT-FREE COTTON CLOTH

Material No: 19-003

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL C.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

560

DRY BAY (OUTBOARD)

660

DRY BAY (OUTBOARD)

560AB, 660AB D.

Referenced Information

REFERENCE 12-34-24-869-002-A

DESIGNATION Aircraft Grounding for the Maintenance Operations

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

(Ref. Fig. 24-92-00-991-03100-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) 3.

Job Set-up Subtask 24-92-00-862-062-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-075-A B.

Connect the aircraft to the ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-062-A C.

Get Access (1)

Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the dry bay.

(2)

For the left wing. (a)

(3)

For the right wing. (a)

4.

Remove and retain the access panel: 560AB. Remove and retain the access panel: 660AB.

Procedure Subtask 24-92-00-210-062-A A.

Inspection of the End Fittings of Electrical Conduits (Ref. Fig. 24-92-00-991-03100-A - Electrical Harness Conduits - Corrosion Protection) (Ref. Fig. 24-92-00-991-00600-A - Typical Fittings) WARNING : BE CAREFUL NOT TO CUT YOUR FINGERS. FLAKES OF NICKEL ARE SHARP. (1)

At each fitting use the procedure that follows to protect against corrosion: (a)

AES

Use CLEANING AGENTS (Material No: 11-004) and a LINT-FREE COTTON CLOTH (Material No: 19-003) to remove any contamination from the fitting.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b)

Remove any flakes or blisters, make sure that the you do not damage the base metal while you do this task. NOTE :

(c)

5.

A dental or a EXTRACTION TOOL - SEAL are recommended for the removal of flakes and blisters.

Use a BRUSH - BRISTLED or an SPRAY - BOTTLE, PUMP TYPE (NON AEROSOL) to apply a continuous coat of STORAGE PRESERVATION (Material No: 15-008) with a thickness of 0.030 mm (0.001 in.), to cover all the fitting.

Close-up Subtask 24-92-00-410-063-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

For the left wing. (a)

(3)

For the right wing. (a)

AES

Install the access panel: 560AB.

Install the access panel: 660AB.

(4)

Disconnect the aircraft from the ground (Ref. TASK 12-34-24-869-002-A).

(5)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

560AB

660AB

B A

B

D

C

D CONDUIT FITTING

C CONDUIT FITTING

N_MM_249200_6_CNM0_01_00

AES

FIGURE 24-92-00-991-03100-A SHEET 1 Electrical Harness Conduits - Corrosion Protection

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-018-A General Visual Inspection of Elements Fitted on the Following Harnesses: 405VB to 409VB (LH side) and 400VB to 404VB (RH side) WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. 1.

Reason for the Job (Ref. MPD 20-00-02-01-) GENERAL VISUAL INSPECTION OF ELEMENTS FITTED ON THE FOLLOWING HARNESSES: - 405VB, 406VB, 407VB, 408VB, 409VB, LH SIDE - 400VB, 401VB, 402VB, 403VB, 404VB, RH SIDE

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION AR ACCESS PLATFORM 6M (20 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

334 344 334AB, 334BB, 334CB, 334DB, 334EB, 344AB, 344BB, 344CB, 344DB, 344EB C.

ZONE DESCRIPTION THS TRAILING EDGE THS TRAILING EDGE

Referenced Information

REFERENCE 55-13-11-000-001-A

DESIGNATION Remove/Open of the THS Trailing Edge Access Panels

55-13-11-400-001-A

Install/Close of the THS Trailing Edge Access Panels

ESPM 20-53-32-0 ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-03200-A - Electrical Harnesses - Inspection) (Ref. Fig. 24-92-00-991-03800-B - Electrical Harnesses - Inspection) 3.

Job Set-up Subtask 24-92-00-860-069-A A.

Aircraft Maintenance Configuration (1)

AES

Put a warning notice in the cockpit to tell persons not to operate the pitch controls.

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Put a warning notice in position to tell persons not to pressurize the Green and Yellow hydraulic systems.

Subtask 24-92-00-010-067-A B.

4.

Get Access (1)

Put an ACCESS PLATFORM 6M (20 FT) - ADJUSTABLE in position below the access panels 334AB, 334BB, 334CB, 334DB, 334EB, 344AB, 344BB, 344CB, 344DB and 344EB.

(2)

Remove the access panels (Ref. TASK 55-13-11-000-001-A): (a)

For the left Trimmable Horizontal Stabilizer (THS): 334AB, 334BB, 334CB, 334DB and 334EB.

(b)

For the right THS: 344AB, 344BB, 344CB, 344DB and 344EB.

Procedure Subtask 24-92-00-210-067-A A.

Inspection (Ref. Fig. 24-92-00-991-03200-A - Electrical Harnesses - Inspection) (Ref. Fig. 24-92-00-991-03800-B - Electrical Harnesses - Inspection) (1)

5.

Do a general visual inspection of the components on these harnesses: . 405VB, 406VB, 407VB, 408VB, 409VB for the left THS, . 400VB, 401VB, 402VB, 403VB, 404VB for the right THS. (a)

Do a check of the general condition of these components and make sure that they are correctly attached: . electrical bonding leads, . braided conduits, . clamps, . electrical connectors, . braided shields.

(b)

Make sure that there is no sign of contamination (Ref. ESPM 20-55-00-0) and corrosion (Ref. ESPM 20-53-32-0).

Close-up Subtask 24-92-00-410-068-A A.

Close Access (1)

Install the access panels (Ref. TASK 55-13-11-400-001-A): (a)

For the left THS: 334AB, 334BB, 334CB, 334DB and 334EB.

(b)

For the right THS: 344AB, 344BB, 344CB, 344DB and 344EB.

Subtask 24-92-00-860-070-A B.

AES

Aircraft Maintenance Configuration (1)

Remove the access platform(s).

(2)

Remove the warning notice(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A Z345 344AB 344BB 344CB 344DB 344EB

A Z335

334AB 334BB 334CB 334DB 334EB

RIB 3 405VB (401VB)

A

RIB 4

RIB 5 408VB (403VB) RIB 6

407VB (400VB) RIB 8

406VB (402VB)

NOTE: LH SIDE SHOWN, RH SIDE SYMMETRICAL N_MM_249200_6_AAM0_01_00

AES

FIGURE 24-92-00-991-03200-A SHEET 1 Electrical Harnesses - Inspection

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A Z345

344AB 344BB 344CB 344DB 344EB

A Z335

334AB 334BB 334CB 334DB 334EB RIB 3

A

RIB 4 RIB 5

RIB 6

409VB (404VB) RIB 8

RIB 9

NOTE: LH SIDE SHOWN, RH SIDE SYMMETRICAL

AES

FIGURE 24-92-00-991-03800-B SHEET 1 Electrical Harnesses - Inspection

N_MM_249200_6_ABM0_01_00

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-019-A General Visual Inspection of Elements Fitted on the Following Harnesses: 4202VB, 4204VB WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. 1.

Reason for the Job (Ref. MPD 20-00-03-01-) GENERAL VISUAL INSPECTION OF ELEMENTS FITTED ON THE FOLLOWING HARNESSES: - 4202VB, 4204VB

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

321 321AL C.

ZONE DESCRIPTION DORSAL FIN

Referenced Information

REFERENCE ESPM 20-53-32-0 ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-03300-A - Electrical Harnesses - Inspection) 3.

DESIGNATION

Job Set-up Subtask 24-92-00-860-071-A A.

Aircraft Maintenance Configuration (1)

Put a warning notice in the cockpit to tell persons not to operate the pitch controls.

(2)

Put a warning notice in position to tell persons not to pressurize the Green and Yellow hydraulic systems.

Subtask 24-92-00-010-068-A B.

AES

Get Access (1)

Put an ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE in position at the vertical stabilizer leading-edge.

(2)

Remove the access panel 321AL.

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure Subtask 24-92-00-210-068-A A.

Inspection (Ref. Fig. 24-92-00-991-03300-A - Electrical Harnesses - Inspection) (1)

5.

Do a general visual inspection of the components on these harnesses: . 4202VB, . 4204VB. (a)

Do a check of the general condition of these components and make sure that they are correctly attached: . electrical bonding leads, . braided conduits, . clamps, . electrical connectors, braided shields.

(b)

Make sure that there is no sign of contamination (Ref. ESPM 20-55-00-0) and corrosion (Ref. ESPM 20-53-32-0).

Close-up Subtask 24-92-00-410-069-A A.

Close Access (1)

Install the access panel 321AL.

Subtask 24-92-00-860-072-A B.

AES

Aircraft Maintenance Configuration (1)

Remove the access platform(s).

(2)

Remove the warning notice(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 321AL

RIB11

N_MM_249200_6_ADM0_01_00

AES

FIGURE 24-92-00-991-03300-A SHEET 1 Electrical Harnesses - Inspection

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-020-A General Visual Inspection of Elements Fitted on the Following Harnesses: 4202VB, 4204VB WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. 1.

Reason for the Job (Ref. MPD 20-00-03-02-) GENERAL VISUAL INSPECTION OF ELEMENTS FITTED ON THE FOLLOWING HARNESSES: - 4202VB, 4204VB

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

322 322BL C.

ZONE DESCRIPTION VERTICAL STABILIZER LEADING EDGE

Referenced Information

REFERENCE ESPM 20-53-32-0 ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-03400-A - Electrical Harnesses - Inspection) 3.

DESIGNATION

Job Set-up Subtask 24-92-00-860-073-A A.

Aircraft Maintenance Configuration (1)

Put a warning notice in the cockpit to tell persons not to operate the pitch controls.

(2)

Put a warning notice in position to tell persons not to pressurize the Green and Yellow hydraulic systems.

Subtask 24-92-00-010-069-A B.

AES

Get Access (1)

Put an ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE in position at the vertical stabilizer leading-edge.

(2)

Remove the access panel 322BL.

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure Subtask 24-92-00-210-069-A A.

Inspection (Ref. Fig. 24-92-00-991-03400-A - Electrical Harnesses - Inspection) (1)

5.

Do a general visual inspection of the components on these harnesses : . 4202VB, . 4204VB. (a)

Do a check of the general condition of these components and make sure that they are correctly attached: . electrical bonding leads, . braided conduits, . clamps, . electrical connectors, . braided shields.

(b)

Make sure that there is no sign of contamination (Ref. ESPM 20-55-00-0) and corrosion (Ref. ESPM 20-53-32-0).

Close-up Subtask 24-92-00-410-070-A A.

Close Access (1)

Install the access panel 322BL.

Subtask 24-92-00-860-074-A B.

AES

Aircraft Maintenance Configuration (1)

Remove the access platform(s).

(2)

Remove the warning notice(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 322BL

RIB11

N_MM_249200_6_AFM0_01_00

AES

FIGURE 24-92-00-991-03400-A SHEET 1 Electrical Harnesses - Inspection

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-021-A General Visual Inspection of Elements Fitted on the Following Harnesses: 4202VB, 4204VB WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. 1.

Reason for the Job (Ref. MPD 20-00-03-03-) GENERAL VISUAL INSPECTION OF ELEMENTS FITTED ON THE FOLLOWING HARNESSES: - 4202VB, 4204VB

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

324 324AT C.

ZONE DESCRIPTION VERTICAL STABILIZER TIP

Referenced Information

REFERENCE ESPM 20-53-32-0 ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-03500-A - Electrical Harnesses - Inspection) 3.

DESIGNATION

Job Set-up Subtask 24-92-00-860-075-A A.

Aircraft Maintenance Configuration (1)

Put a warning notice in the cockpit to tell persons not to operate the pitch controls.

(2)

Put a warning notice in position to tell persons not to pressurize the Green and Yellow hydraulic systems.

Subtask 24-92-00-010-070-A B.

AES

Get Access (1)

Put an ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE in position at the vertical stabilizer leading-edge.

(2)

Remove the access panel 324AT.

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure Subtask 24-92-00-210-070-A A.

Inspection (Ref. Fig. 24-92-00-991-03500-A - Electrical Harnesses - Inspection) (1)

5.

Do a general visual inspection of the components on these harnesses: . 4202VB, . 4204VB. (a)

Do a check of the general condition of these components and make sure that they are correctly attached: . electrical bonding leads, . braided conduits, . clamps, . electrical connectors, . braided shields.

(b)

Make sure that there is no sign of contamination (Ref. ESPM 20-55-00-0) and corrosion (Ref. ESPM 20-53-32-0).

Close-up Subtask 24-92-00-410-071-A A.

Close Access (1)

Install the access panel 324AT.

Subtask 24-92-00-860-076-A B.

AES

Aircraft Maintenance Configuration (1)

Remove the access platform(s).

(2)

Remove the warning notice(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 324AT

A

RIB11

N_MM_249200_6_AHM0_01_00

AES

FIGURE 24-92-00-991-03500-A SHEET 1 Electrical Harnesses - Inspection

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-023-A Check that Connector is Correctly Tightened by Measurement of the Resistance with a Loop Tester WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. 1.

Reason for the Job (Ref. MPD 20-00-01-02-) CHECK THAT THE CONNECTOR IS CORRECTLY TIGHTENED BY MEASUREMENT OF THE RESISTANCE WITH A LOOP TESTER: - 4005VC, 4007VC, 4009VC, 4011VC, LH SIDE - 4013VC, 4015VC, 4017VC, 4019VC, LH SIDE - 4006VC, 4008VC, 4010VC, 4012VC, RH SIDE - 4014VC, 4016VC, 4018VC, 4020VC, RH SIDE Do this procedure to make sure that these connectors are correctly tightened; to do this check, measure the resistance with a loop tester: . 4005VC, 4007VC, 4009VC, 4011VC, 4013VC, 4015VC, 4017VC, 4019VC, LH side . 4006VC, 4008VC, 4010VC, 4012VC, 4014VC, 4016VC, 4018VC, 4020VC, RH side

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific

AR

MULTIMETER - STANDARD

No specific

AR

TEST UNIT - LOOP RESISTANCE (INDUCING CURRENT 1A 1KHZ)

B.

Work Zones and Access Panels ZONE/ACCESS

511 520 611 620 521EB, 521GB, 522AB, 621EB, 621GB, 622AB C.

SLAT N˚ 1 LEFT WING FIXED LEADING EDGE SLAT N˚ 1 RIGHT WING FIXED LEADING EDGE

Referenced Information

REFERENCE 12-34-24-869-002-A 20-28-00-720-014-A

AES

ZONE DESCRIPTION

DESIGNATION Aircraft Grounding for the Maintenance Operations Loop Impedance Test

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 20-28-00-912-003-A

DESIGNATION Electrical Bonding of Electrical Connectors

20-28-00-912-004-A

Electrical Bonding of Components With Conductive Bolts and Screws and Bonding Straps in the Fuselage and in the Wings (this does not include the tanks)-

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

27-80-00-866-004-A

Extending the Slats on the Ground

27-80-00-866-005-A

Retracting the Slats on the Ground

57-41-37-000-004-A Removal of the Pressure-Relief Panels 57-41-37-000-010-A Removal of the Access Panel 57-41-37-400-002-A Installation of the Pressure-Relief Panels 57-41-37-400-010-A Installation of the Access Panel (Ref. Fig. 24-92-00-991-03700-A - Location of the Loop Tester Measurement Points) 3.

Job Set-up Subtask 24-92-00-860-079-A A.

Aircraft Maintenance Configuration (1)

Extend the slats fully (Ref. TASK 27-80-00-866-004-A).

Subtask 24-92-00-862-066-A B.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-869-082-A C.

Connect the aircraft to ground (Ref. TASK 12-34-24-869-002-A).

Subtask 24-92-00-010-072-A D.

4.

Get Access (1)

Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the wings.

(2)

At the left wing: . Remove the access panels 521EB, 522AB (Ref. TASK 57-41-37-000-004-A) and 521GB (Ref. TASK 57-41-37-000-010-A).

(3)

At the right wing: . Remove the access panels 621EB, 622AB (Ref. TASK 57-41-37-000-004-A) and 621GB (Ref. TASK 57-41-37-000-010-A).

Procedure Subtask 24-92-00-280-051-A A.

AES

Measurement of the Resistance with a Loop Tester (Ref. Fig. 24-92-00-991-03700-A - Location of the Loop Tester Measurement Points)

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (1)

Install the TEST UNIT - LOOP RESISTANCE (INDUCING CURRENT 1A 1KHZ) and measure the resistance (Ref. TASK 20-28-00-720-014-A) around the applicable braided conduit. NOTE :

(2)

Measure the resistance. NOTE :

(3)

The below instructions are applicable using a loop resistance test unit and a multimeter. If another type of loop resistance test unit is used, refer to the instructions given by the tool manufacturer to do the resistance measurement.

(a)

Connect the MULTIMETER - STANDARD to the output of the current measuring transformer (4mm plugs connected to the ”COM” and ”mA” sockets of the multimeter).

(b)

Set the multimeter to the ”mA” position (push the ”AC” button).

(c)

Set the test set to on and adjust the RANGE and SETTING controls until you get a current of 1 mA on the multimeter.

(d)

The test set meter shows directly the loop resistance in milliohms.

Make sure that the measured values are not more than the maximum permitted value of 200 milliohms. (a)

5.

It is not necessary to do a test of the conduits connected to the non-conductive connectors (9QG-A and 10QG-A) because they are not part of the general electromagnetic protection.

If the measured value is more than the maximum permitted value of 200 milliohms: . Do the electrical bonding of the electrical connectors (Ref. TASK 20-28-00-912-003-A) and of the components. Use conductive bolts and screws and bonding straps in the fuselage and in the wings (Ref. TASK 20-28-00-912-004-A).

Close-up Subtask 24-92-00-410-074-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

At the left wing: . Install the access panels 521EB, 522AB (Ref. TASK 57-41-37-400-002-A) and 521GB (Ref. TASK 57-41-37-400-010-A).

(3)

At the right wing: . Install the access panels 621EB, 622AB (Ref. TASK 57-41-37-400-002-A) and 621GB (Ref. TASK 57-41-37-400-010-A).

Subtask 24-92-00-860-080-A B.

AES

Put the aircraft back to its initial configuration. (1)

Disconnect the aircraft from ground (Ref. TASK 12-34-24-869-002-A).

(2)

Retract the slats (Ref. TASK 27-80-00-866-005-A)

(3)

Remove the access platform(s).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 4009VC (4010VC) 4005VC 4007VC (4006VC) (4008VC)

A

B

4013VC (4014VC) 4011VC (4012VC)

4015VC (4016VC)

RIB 7

A

C 4017VC 4019VC (4018VC) (4020VC)

INBD

1

C DE−ICE DUCT

TORQUE SHAFT

1

RIB 8

B 4017VC (4018VC)

1

4015VC(4016VC)

4019VC (4020VC)

1

1 2M

BLEED AIR DUCT 1M

1S 1S

6HA CONDUIT

TORQUE SHAFT

4011VC (4012VC) 4013VC (4014VC)

4009VC(4010VC) 4005VC(4006VC) 1 1 LOOP RESISTANCE TEST AREA

4007VC(4008VC) N_MM_249200_6_AMM0_01_00

AES

FIGURE 24-92-00-991-03700-A SHEET 1 Location of the Loop Tester Measurement Points

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-024-A Detailed Inspection of the Bonding Leads Installed on the Movable Surfaces WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: THE FLIGHT CONTROLS THE FLIGHT CONTROL SURFACES THE LANDING GEAR AND THE RELATED DOORS COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. CAUTION :

1.

BE -

CAREFUL WHEN YOU DO MAINTENANCE TASKS ON THE WING TRAILING EDGE: DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE RACEWAYS. DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE INSTALLATIONS. MAKE SURE THAT THE ELECTRICAL CABLES ARE INSTALLED CORRECTLY. INCORRECT INSTALLATION CAN CAUSE DAMAGE.

Reason for the Job (Ref. MPD 20-28-00-01-) DETAILED INSPECTION OF BONDING LEADS LOCATED ON THE FOLLOWING MOVABLE SURFACES: ELEVATOR, RUDDER, FLAPS, FLAP TRACK FAIRINGS, SLATS, SPOILERS, AILERONS, LANDING GEAR DOORS AND PASSENGER/CREW DOORS Do this inspection on the movable surfaces that follow: . Flaps . Flap track fairings . Slats . Spoilers . Ailerons . Elevator . Rudder . Nose landing gear doors . Main landing gear doors . Passenger/crew doors.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific

AR

MIRROR - INSPECTION

No specific

AR

SAFETY BARRIER(S)

No specific

AR

SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

98D27803000000

1

LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION

B.

Work Zones and Access Panels ZONE/ACCESS

300

AES

ZONE DESCRIPTION STABILIZERS AND TAIL UNIT

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Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ZONE/ACCESS 500 600 700 800 325BL, 325BR, 325CL, 325CR, 325DL, 325DR, 325EL, 325ER, 334BB, 334DB, 334FB, 334GB, 334HB, 344BB, 344DB, 344FB, 344GB, 344HB, 521AB, 522AB, 522FB, 522NB, 522SB, 571AB, 573AB, 573BB, 573CB, 575AB, 575AT, 575BB, 575CB, 575DB, 575EB, 575FB, 575GB, 575KB, 575LB, 575MB, 590AB, 590BB, 621AB, 622AB, 622FB, 622NB, 622SB, 671AB, 673AB, 673BB, 673CB, 675AB, 675AT, 675BB, 675CB, 675DB, 675EB, 675FB, 675GB, 675KB, 675LB, 675MB, 690AB, 690BB, 831FZ, 831GZ, 832FZ, 832GZ, 841FZ, 841GZ, 842FZ, 842GZ C.

ZONE DESCRIPTION LEFT WING RIGHT WING LANDING GEAR AND LANDING GEAR DOORS DOORS

Referenced Information

REFERENCE 20-28-00-912-004-A

DESIGNATION Electrical Bonding of Components With Conductive Bolts and Screws and Bonding Straps in the Fuselage and in the Wings (this does not include the tanks)-

24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

24-41-00-861-002-A-01

Energize the Aircraft Electrical Circuits from the APU

24-41-00-861-002-A-02

Energize the Aircraft Electrical Circuits from Engine 1(2)

24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-46-000-001-A

Removal of the Door Linings at the FWD Passenger/Crew Doors

25-23-46-000-002-A

Removal of the Door Linings at the AFT Passenger/Crew Doors

25-23-46-400-001-A

Installation of the Door Linings at the FWD Passenger/Crew Doors

25-23-46-400-002-A

Installation of the Door Linings at the AFT Passenger/Crew Doors

27-50-00-866-008-A

Extension of the Flaps on the Ground

27-50-00-866-008-A-01

Extension of the Flaps/Slats on the Ground

27-50-00-866-009-A

Retraction of the Flaps on the Ground

27-50-00-866-009-A-01

Retraction of the Flaps/Slats on the Ground

27-80-00-866-004-A

Extending the Slats on the Ground

27-80-00-866-005-A

Retracting the Slats on the Ground

29-10-00-863-001-A

Pressurize the Green Hydraulic System

AES

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 29-10-00-863-002-A

DESIGNATION Pressurize the Yellow Hydraulic System

29-10-00-863-003-A

Pressurize the Blue Hydraulic System with a Ground Power Supply

29-10-00-863-003-A-01

Pressurize the Blue Hydraulic System with the Blue Electric Pump

29-10-00-864-001-A

Depressurize the Green Hydraulic System

29-10-00-864-002-A

Depressurize the Yellow Hydraulic System

29-10-00-864-003-A

Depressurize the Blue Hydraulic System

29-14-00-614-001-A

Depressurization of the Hydraulic Reservoirs

29-14-00-614-002-A

Pressurization of the Hydraulic Reservoirs through the Ground Connector

32-00-00-481-002-A

Installation of the Safety Devices on the Landing Gear Doors

32-12-00-010-001-A 32-12-00-410-001-A 32-22-00-010-001-A

Open the Main Gear Doors for Access Close the Main Gear Doors after Access Nose Gear Doors - Ground Doors Opening

32-22-00-410-001-A

Nose Gear Doors - Ground Doors Closing

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

55-13-11-000-001-A

Remove/Open of the THS Trailing Edge Access Panels

55-13-11-400-001-A

Install/Close of the THS Trailing Edge Access Panels

55-33-13-010-002-A

Opening/Removal of the Trailing Edge Access-Panels of the Vertical Stabilizer

55-33-13-410-002-A

Closing/Installation of the Trailing Edge Access-Panels of the Vertical Stabilizer

57-41-37-000-004-A Removal of the Pressure-Relief Panels 57-41-37-000-006-A Removal of the Access Panels 57-41-37-400-002-A Installation of the Pressure-Relief Panels 57-41-37-400-006-A Installation of the Access Panels (Ref. Fig. 24-92-00-991-09000-A - Bonding Leads located on Movable Surfaces) 3.

Job Set-up Subtask 24-92-00-861-055-A A.

Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002-A) or (Ref. TASK 24-41-00-861-002-A-01) or (Ref. TASK 24-41-00-861-002A-02).

Subtask 24-92-00-941-052-A B.

AES

Safety Precautions (1)

Install the ground safety locks on the landing gear doors (Ref. TASK 32-00-00-481-002-A).

(2)

Put a WARNING NOTICE(S) in position to tell persons not to pressurize the hydraulic systems: . On the ground service panel 197CB. . In the cockpit, on the HYD/FUEL panel 40VU.

(3)

Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to operate the flight controls.

(4)

Put a WARNING NOTICE(S) in position on the panel 400VU to tell persons not to operate the landing gear doors.

(5)

Put the safety barriers in position.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-860-086-A C.

Aircraft Maintenance Configuration WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE. (1)

Extend the slats to the fully extended position (Ref. TASK 27-80-00-866-004-A).

(2)

Extend the flaps to the fully extended position (Ref. TASK 27-50-00-866-008-A) or (Ref. TASK 27-50-00-866-008-A-01).

(3)

Install the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) on the flap/slat control lever.

(4)

Depressurize the aircraft hydraulic systems (Ref. TASK 29-10-00-864-001-A), (Ref. TASK 29-10-00-864-003-A) (Ref. TASK 29-10-00-864-002-A).

(5)

Depressurize the hydraulic reservoirs (Ref. TASK 29-14-00-614-001-A).

Subtask 24-92-00-865-050-A D.

Open, safety and tag this(these) circuit breaker(s):

49VU

PANEL

DESIGNATION FLIGHT CONTROLS/ELAC1/NORM/SPLY

15CE1

B11

49VU

FLIGHT CONTROLS/THS/ACTR/MOT2

19CE2

B09

49VU

FLIGHT CONTROLS/SEC1/NORM/SPLY

21CE1

B08

49VU

FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1

6CV

B07

49VU

FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1

5CV

B06

49VU

AUTO FLT/FAC1/28VDC

5CC1

B04

49VU

AUTO FLT/FAC1/26VAC

14CC1

B03

105VU

FLIGHT CONTROLS/ELAC2/STBY SPLY

16CE2

A02

105VU

FLT CTL/ELAC1/STBY SPLY

16CE1

A01

105VU

FLT CTL/SEC1/STBY SPLY

22CE

B01

121VU

AUTO FLT/RUDDER/TRIM/IND

15CC

M20

121VU

AUTO FLT/FAC2/28VDC

5CC2

M19

121VU

AUTO FLT/FAC2/26VAC

14CC2

M18

121VU

FLIGHT CONTROLS/WTB/FLP/SYS2

12CV

P20

121VU

FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2

8CV

Q21

121VU

FLIGHT CONTROLS/SEC3/SPLY

21CE3

Q19

121VU

FLIGHT CONTROLS/SEC2/SPLY

21CE2

Q18

121VU

FLIGHT CONTROLS/THS ACTR/MOT3

19CE3

Q17

121VU

FLIGHT CONTROLS/THS ACTR/MOT1

19CE1

Q16

121VU

FLIGHT CONTROLS/SLT/CTL/SYS2

7CV

R21

121VU

FLIGHT CONTROLS/ELAC2/NORM/SPLY

15CE2

R20

122VU

FLIGHT CONTROLS/WTB/FLP/SYS1

10CV

S07

AES

FIN

LOCATION

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-010-078-A E.

Get Access (1)

Open the MLG doors (Ref. TASK 32-12-00-010-001-A).

(2)

Open the NLG doors (Ref. TASK 32-22-00-010-001-A).

(3)

Open the passenger/crew doors (Ref. TASK 52-10-00-010-001-A) and remove the door lining panels (Ref. TASK 25-23-46-000-001-A) (Ref. TASK 25-23-46-000-002-A): . 831FZ 841FZ 831GZ 841GZ, 832FZ 842FZ 832GZ 842GZ.

(4)

Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the applicable zone.

(5)

Open the access doors.

(6)

4.

(a)

For the flaps: . For the left wing, open 571AB 573AB 573BB 573CB 575AB 575BB 575CB 575DB 575EB 575FB 575GB. . For the right wing, open 671AB 673AB 673BB 673CB 675AB 675BB 675CB 675DB 675EB 675FB 675GB.

(b)

For the spoilers: . For the left wing, open 573BB 575BB 575DB 575EB 575GB. . For the right wing, open 673BB 675BB 675DB 675EB 675GB.

Remove the access panels. (a)

For the slats: . For the left wing, remove 521AB 522AB 522FB 522NB 522SB (Ref. TASK 57-41-37-000-004A) and (Ref. TASK 57-41-37-000-006-A). . For the right wing, remove 621AB 622AB 622FB 622NB 622SB (Ref. TASK 57-41-37-000-004-A) and (Ref. TASK 57-41-37-000-006-A).

(b)

For the ailerons: . For the left wing, remove 575AT 575MB 575KB 575LB 590AB 590BB. . For the right wing, remove 675AT 675MB 675KB 675LB 690AB 690BB.

(c)

For the elevators: . 334BB 344BB 334DB 344DB 334FB 344FB 334GB 344GB 334HB 344HB (Ref. TASK 55-13-11-000-001-A).

(d)

For the rudder: . 325BL 325BR 325CL 325CR 325DL 325DR 325EL 325ER (Ref. AMM 55-33-13-010-001) or (Ref. TASK 55-33-13-010-002-A).

Procedure (Ref. Fig. 24-92-00-991-09000-A - Bonding Leads located on Movable Surfaces) Subtask 24-92-00-220-061-A A.

General Inspection Recommendations (1)

AES

Do . . . . . . . .

a detailed inspection of the bonding leads on the movable surfaces that follow: MLG, NLG and passenger/crew doors Flaps Flap track movable fairings Spoilers Surfaces between slats 2 and 3, 3 and 4, 4 and 5 Slat tracks No. 1, No. 5 and No. 11 Ailerons Elevators

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL .

Rudder.

NOTE : (2)

During the inspection, replace all the bonding leads if they are found broken or if more than 25 per cent of their strands are damaged (Ref. TASK 20-28-00-912-004-A). NOTE :

(3)

Use an MIRROR - INSPECTION, if necessary.

Because it is not possible to know with precision the number of damaged strands when a bonding lead is damaged: 25 per cent is equal to 1/4 of the section (i.e.: 3.25 mm2 (0.01 in.2) for a section of 13 mm2 (0.02 in.2) or 1.75 mm2 (0.00 in.2) for a section of 7 mm2 (0.01 in.2)).

If you cannot replace all the bonding leads before the planned aircraft release, the bonding lead installations that follow are satisfactory.

Subtask 24-92-00-220-062-A B.

Inspection of the Bonding Leads Installed on the Flaps, Flap Track Fairings, Slats, Spoilers, Ailerons, Nose Landing-Gear Doors, Main Landing-Gear Doors and Passenger/Crew Doors (1)

(2)

During the inspection, if you cannot replace the bonding leads that are broken or damaged, the bonding lead installations that follow are satisfactory: (a)

Movable surface bonded with two leads: . If one lead is broken, and less than 25 percent of the strands of the other bonding lead is damage.

(b)

Movable surface bonded with three leads: . If two leads are broken, and less than 25 percent of the strands of the other bonding lead is damage.

Replace all the remaining broken or damages bonding leads at the next maintenance opportunity but before 20 months (or 6000 flight hours, 4500 flight cycles), whichever occurs first.

Subtask 24-92-00-220-063-A C.

Inspection of the Elevator Bonding Leads (1)

(2)

During the inspection, if you cannot replace the bonding leads that are broken or damaged, the bonding lead installations that follow are satisfactory: (a)

Bonding lead installed near the elevator tip: . If less than 25 percent of its strands is damaged.

(b)

And for the other bonding leads installed on the elevator: . If only one lead is broken or has more than 25 percent of its strands damaged and the other bonding leads have less than 25 percent of their strands damaged.

Replace all the remaining broken or damaged bonding leads at the next maintenance opportunity but before 20 months (or 6000 flight hours, 4500 flight cycles), wichever occurs first.

Subtask 24-92-00-220-064-A D.

Inspection of the Rudder Bonding Leads (1)

AES

During the inspection, if you cannot replace the bonding leads that are broken or damaged, the installations that follow are satisfactory: (a)

Bonding leads installed on the rudder hinge arms No. 1 and 7 (on the top and bottom part of the rudder): . If less than 25 percent of their strands are damaged.

(b)

And for bonding leads installed on the rudder hinge arms No. 2, 3, 4, 5 and 6: . If only one lead is broken or has more than 25 percent of its strand damaged. . And if the other bonding leads have less than 25 percent of their strands damaged.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2) 5.

Replace all the remaining broken or damaged bonding leads at the next maintenance opportunity but before 100 days (or 600 flight hours, 750 flight cycles), whichever occurs first.

Close-up Subtask 24-92-00-410-078-A A.

Close Access (1)

(2)

Close these access panels. (a)

For the slats: . For the left wing, install 521AB 522AB 522FB 522NB 522SB (Ref. TASK 57-41-37-400-002A) and (Ref. TASK 57-41-37-400-006-A). . For the right wing, install 621AB 622AB 622FB 622NB 622SB (Ref. TASK 57-41-37-400-002A) and (Ref. TASK 57-41-37-400-006-A).

(b)

For the ailerons: . For the left wing, install 575AT 575MB 575KB 575LB 590AB 590BB. . For the right wing, install 675AT 675MB 675KB 675LB 690AB 690BB.

(c)

For the elevators: . 334BB 344BB 334DB 344DB 334FB 344FB 334GB 344GB 334HB 344HB (Ref. TASK 55-13-11-400-001-A).

(d)

For the rudder: . 325BL 325BR 325CL 325CR 325DL 325DR 325EL 325ER (Ref. AMM 55-33-13-410-001) or (Ref. TASK 55-33-13-410-002-A).

Close these access doors. (a)

For the flaps: . For the left wing, close 571AB 573AB 573BB 573CB 575AB 575BB 575CB 575DB 575EB 575FB 575GB. . For the right wing, close 671AB 673AB 673BB 673CB 675AB 675BB 675CB 675DB 675EB 675FB 675GB.

(b)

For the spoilers: . For the left wing, close 573BB 575BB 575DB 575EB 575GB. . For the right wing, close 673BB 675BB 675DB 675EB 675GB.

(3)

Close the MLG doors (Ref. TASK 32-12-00-410-001-A).

(4)

Close the NLG doors (Ref. TASK 32-22-00-410-001-A).

(5)

Install the door lining panels (Ref. TASK 25-23-46-400-001-A) (Ref. TASK 25-23-46-400-002-A) and close the passenger/crew doors (Ref. TASK 52-10-00-410-001-A): . 831FZ 841FZ 831GZ 841GZ 832FZ 842FZ 832GZ 842GZ.

Subtask 24-92-00-865-052-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

49VU

PANEL

DESIGNATION FLIGHT CONTROLS/ELAC1/NORM/SPLY

15CE1

B11

49VU

FLIGHT CONTROLS/THS/ACTR/MOT2

19CE2

B09

49VU

FLIGHT CONTROLS/SEC1/NORM/SPLY

21CE1

B08

49VU

FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1

6CV

B07

AES

FIN

LOCATION

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

49VU

PANEL

DESIGNATION FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1

5CV

FIN B06

LOCATION

49VU

AUTO FLT/FAC1/28VDC

5CC1

B04

49VU

AUTO FLT/FAC1/26VAC

14CC1

B03

105VU

FLIGHT CONTROLS/ELAC2/STBY SPLY

16CE2

A02

105VU

FLT CTL/ELAC1/STBY SPLY

16CE1

A01

105VU

FLT CTL/SEC1/STBY SPLY

22CE

B01

121VU

AUTO FLT/RUDDER/TRIM/IND

15CC

M20

121VU

AUTO FLT/FAC2/28VDC

5CC2

M19

121VU

AUTO FLT/FAC2/26VAC

14CC2

M18

121VU

FLIGHT CONTROLS/WTB/FLP/SYS2

12CV

P20

121VU

FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2

8CV

Q21

121VU

FLIGHT CONTROLS/SEC3/SPLY

21CE3

Q19

121VU

FLIGHT CONTROLS/SEC2/SPLY

21CE2

Q18

121VU

FLIGHT CONTROLS/THS ACTR/MOT3

19CE3

Q17

121VU

FLIGHT CONTROLS/THS ACTR/MOT1

19CE1

Q16

121VU

FLIGHT CONTROLS/SLT/CTL/SYS2

7CV

R21

121VU

FLIGHT CONTROLS/ELAC2/NORM/SPLY

15CE2

R20

122VU

FLIGHT CONTROLS/WTB/FLP/SYS1

10CV

S07

Subtask 24-92-00-860-087-A C.

Put the aircraft back to its initial configuration. (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Pressurize the aircraft hydraulic systems (Ref. TASK 29-10-00-863-001-A), (Ref. TASK 29-10-00-863-003-A) or (Ref. TASK 29-10-00-863-003A-01) and (Ref. TASK 29-10-00-863-002-A).

(3)

Pressurize the hydraulic reservoirs (Ref. TASK 29-14-00-614-002-A).

(4)

Retract the slats (Ref. TASK 27-80-00-866-005-A).

(5)

Retract the flaps (Ref. TASK 27-50-00-866-009-A) or (Ref. TASK 27-50-00-866-009-A-01).

(6)

Remove the ground support and maintenance equipment, the special and standard tools and all other items.

(7)

Remove the warning notice(s).

(8)

Remove the access platform(s).

Subtask 24-92-00-862-068-A D.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

FWD PASSENGER/CREW DOOR

SLATS

AILERON

FLAPS

SPOILERS

AFT PASSENGER/CREW DOOR

ELEVATOR

RUDDER

** On A/C ALL

N_MM_249200_6_CPM0_01_00

AES

FIGURE 24-92-00-991-09000-A SHEET 1 Bonding Leads located on Movable Surfaces

24-92-00 PB601

Page 9 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

FLAP TRACK FAIRING MAIN LANDING GEAR DOORS

NOSE LANDING GEAR DOORS

** On A/C ALL

N_MM_249200_6_CPM0_02_00

AES

FIGURE 24-92-00-991-09000-A SHEET 2 Bonding Leads located on Movable Surfaces

24-92-00 PB601

Page 10 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-025-A General Visual Inspection of G and P Routes Installed in the Tail Cone and APU Accessory Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-03-15-01-) GENERAL VISUAL INSPECTION OF G AND P ROUTES INSTALLED IN THE TAIL CONE AND APU ACCESSORY COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

315 316 315AL, 316AR C.

ZONE DESCRIPTION TAIL CONE APU AND ACCESSORY COMPARTMENT TAIL CONE APU AND ACCESSORY COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-04300-A - Tail Cone and APU Accessory Compartment - Inspection Area - Zones 315-316) 3.

Job Set-up Subtask 24-92-00-010-079-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the fuselage tail cone.

(2)

Remove the access panels 315AL 316AR.

Subtask 24-92-00-862-069-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-04300-A - Tail Cone and APU Accessory Compartment - Inspection Area - Zones 315-316)

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-210-075-A A.

General Visual Inspection of G and P Route Wiring Installed in the Tail Cone and APU Accessory Compartment (1)

(2) 5.

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder route: 3G.

(b)

On the AC/DC power-distribution route: 3P.

Make sure that there is no oil or fuel contamination.

Close-up Subtask 24-92-00-410-079-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the access panels 315AL 316AR.

(3)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A FR78

FR80

FR82

FR84

INSPECTION AREA ZONE 315−316

316AR

315AL N_MM_249200_6_AMP0_01_00

AES

FIGURE 24-92-00-991-04300-A SHEET 1 Tail Cone and APU Accessory Compartment - Inspection Area - Zones 315-316

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-220-001-A Detailed Inspection of EWIS Installed in the Upper Forward Pylon (EWIS) FIN 1000EM1, 1000EM2 1.

Reason for the Job (Ref. MPD 20-04-13-01-) DETAILED INSPECTION OF EWIS INSTALLED IN THE UPPER FORWARD PYLON (EWIS) (Ref. MPD 20-04-13-03-) DETAILED INSPECTION OF EWIS INSTALLED IN THE UPPER FORWARD PYLON (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific

AR

FLASHLIGHT

No specific

AR

MIRROR - INSPECTION, FLEXIBLE

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

413 414 423 424 FOR FIN 1000EM1(ENGINE-1)

ZONE DESCRIPTION UPPER UPPER UPPER UPPER

FWD FWD FWD FWD

PYLON PYLON PYLON PYLON

413AL, 413BL, 413CL, 413DL, 413EL, 414AR, 414AZ, 414BR, 414CR, 414FR FOR FIN 1000EM2(ENGINE-2) 423AL, 423AZ, 423BL, 423CL, 423DL, 423FL, 424AR, 424BR, 424CR, 424ER C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

ESPM 20-52-12-0 (Ref. Fig. 24-92-00-991-04400-B - Upper Forward Pylon - Access Panels) (Ref. Fig. 24-92-00-991-10600-A - Upper Forward Pylon - Inspection Area - Zones 413-414-423-424)

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-92-00-941-054-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: . Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: . Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(4)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-92-00-862-070-A B.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-010-080-A C.

4.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the upper forward pylon.

(2)

Remove these access panels: (a)

FOR 1000EM1 (ENGINE-1) 413AL 413BL 413CL 413DL 413EL 414AR 414AZ 414BR 414CR 414FR

(b)

FOR 1000EM2 (ENGINE-2) 423AL 423AZ 423BL 423CL 423DL 423FL 424AR 424BR 424CR 424ER.

Procedure (Ref. Fig. 24-92-00-991-04400-B - Upper Forward Pylon - Access Panels) (Ref. Fig. 24-92-00-991-10600-A - Upper Forward Pylon - Inspection Area - Zones 413-414-423-424) Subtask 24-92-00-220-051-A A.

Detailed Inspection of All Wiring Installed in the Upper Forward Pylon (1)

Make sure that there is no hydraulic or fuel contamination. NOTE :

(2)

This inspection is necessary to prevent wiring routes of contamination that are immediately near the fuel and hydraulic area.

Do a detailed inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-12-0): (a)

On the AC/DC feeder routes: 1G, 2G.

(b)

On the engine control routes: 1S, 2S.

(c)

On the other routes: 1M, 2M.

(d)

On the generator excitation routes: 1E, 2E. NOTE :

AES

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-92-00-410-080-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install these access panels: (a)

FOR 1000EM1 (ENGINE-1) 413AL 413BL 413CL 413DL 413EL 414AR 414AZ 414BR 414CR 414FR

(b)

FOR 1000EM2 (ENGINE-2) 423AL 423AZ 423BL 423CL 423DL 423FL 424AR 424BR 424CR 424ER.

(3)

Remove the access platform(s).

(4)

Remove the warning notice(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A B 413EL 413DL 413BL

413CL 413AL

B

414FR 414BR

414AZ 414CR 414AR N_MM_249200_6_FLM0_01_00

AES

FIGURE 24-92-00-991-04400-B SHEET 1 Upper Forward Pylon - Access Panels

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

B

423FL 423DL 423BL

423AZ 423CL 423AL

B 424ER 424BR

424CR 424AR N_MM_249200_6_FLM0_02_00

AES

FIGURE 24-92-00-991-04400-B SHEET 2 Upper Forward Pylon - Access Panels

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A A

B

A

B

INSPECTION AREA Z413−423

B

INSPECTION AREA Z414−424

N_MM_249200_6_CMM0_01_00

AES

FIGURE 24-92-00-991-10600-A SHEET 1 Upper Forward Pylon - Inspection Area - Zones 413-414-423-424

24-92-00 PB601

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-220-003-A Detailed Inspection of EWIS in the Fan and Accessory Gear Box (EWIS) FIN 1000EM1, 1000EM2 1.

Reason for the Job (Ref. MPD 20-04-35-01-) DETAILED INSPECTION OF EWIS IN THE FAN AND ACCESSORY GEAR BOX (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific

1

FLASHLIGHT

No specific

1

MIRROR - INSPECTION

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

435 436 445 446 FOR FIN 1000EM1(ENGINE-1)

ZONE DESCRIPTION FAN FAN FAN FAN

AND AND AND AND

ACCESSORY ACCESSORY ACCESSORY ACCESSORY

GEARBOX GEARBOX GEARBOX GEARBOX

437AL, 438AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

ESPM 20-52-12-0 AWM 94-08-01 AWM 94-08-02 (Ref. Fig. 24-92-00-991-04600-B - Fan and Accessory Gear Box - Access)

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-92-00-941-056-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: . Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: . Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(4)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-92-00-862-072-A B.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-010-082-B C.

4.

Get Access (1)

Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the engine.

(2)

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Procedure (Ref. Fig. 24-92-00-991-04600-B - Fan and Accessory Gear Box - Access) Subtask 24-92-00-220-053-A A.

Detailed Inspection of All Wiring in the Fan and Accessory Gear Box (1)

Do a detailed inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-12-0): (a)

5.

Start the detailed inspection of the wiring at the forward tip of the pylon and then continue into the fan and accessory gear box. Use FLASHLIGHT a or a MIRROR - INSPECTION, if necessary.

(2)

On the AC/DC feeder routes: 1G (Ref. AWM 94-08-01), 2G (Ref. AWM 94-08-02).

(3)

On the engine control routes: 1S (Ref. AWM 94-08-02), 2S (Ref. AWM 94-08-01).

(4)

On the other routes: 1M (Ref. AWM 94-08-01), 2M (Ref. AWM 94-08-02).

(5)

On the generator excitation routes: 1E (Ref. AWM 94-08-01), 2E (Ref. AWM 94-08-02).

(6)

Make sure that there is no dust, fuel, oil or hydraulic contamination.

Close-up Subtask 24-92-00-410-082-B A.

Close Access (1)

AES

Make sure that the work area is clean and clear of tool(s) and other items.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

AES

Close the fan cowls (Ref. TASK 71-13-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

(3)

Remove the access platform(s).

(4)

Remove the warning notice(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A B A

A B

INSPECTION AREA ZONE 435−445 437AL (447AL)

B

INSPECTION AREA ZONE 436−446

438AR (448AR)

AES

FIGURE 24-92-00-991-04600-B SHEET 1 Fan and Accessory Gear Box - Access

N_MM_249200_6_LLM0_01_00

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-220-004-A Detailed Inspection of EWIS Installed in the Hot Section (EWIS) FIN 1000EM1, 1000EM2 1.

Reason for the Job (Ref. MPD 20-04-53-01-) DETAILED INSPECTION OF EWIS INSTALLED IN THE HOT SECTION (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific

1

FLASHLIGHT

No specific

1

MIRROR - INSPECTION

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

453 454 463 464 FOR FIN 1000EM1(ENGINE-1)

ZONE DESCRIPTION HOT HOT HOT HOT

SECTION SECTION SECTION SECTION

437AL, 438AR, 451AL, 452AR FOR FIN 1000EM2(ENGINE-2) 447AL, 448AR, 461AL, 462AR C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

71-13-00-010-010-A

Opening of the Fan Cowls 437AL(447AL),438AR(448AR)

71-13-00-410-010-A

Closing of the Fan Cowls 437AL(447AL),438AR(448AR)

78-30-00-040-012-A

78-32-00-010-010-A

Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance Opening of the Thrust Reverser Halves

78-32-00-410-010-A

Closing of the Thrust Reverser Halves

78-30-00-440-012-A

ESPM 20-52-12-0 AWM 94-08-01

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE AWM 94-08-02 (Ref. Fig. 24-92-00-991-04700-B - Hot Section - Access) 3.

DESIGNATION

Job Set-up Subtask 24-92-00-941-057-A A.

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: . Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: . Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(4)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 24-92-00-010-083-B B.

Get Access (1)

Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the engine.

(2)

Open the fan cowls (Ref. TASK 71-13-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

Subtask 24-92-00-040-051-B C.

Deactivation of the Thrust Reverser WARNING : THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) MUST BE DEACTIVATED BEFORE WORKING ON OR AROUND THE THRUST REVERSER. FAILURE TO DEACTIVATE THE HCU CAN RESULT IN INADVERTENT THRUST REVERSER OPERATION AND INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT. (1)

Deactivate the thrust-reverser Hydraulic Control Unit (HCU) (Ref. TASK 78-30-00-040-012-A).

Subtask 24-92-00-862-073-A D.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-010-084-B E.

Get Access (1)

AES

Open the thrust reverser halves (Ref. TASK 78-32-00-010-010-A): (a)

FOR 1000EM1 (ENGINE-1) 451AL 452AR

(b)

FOR 1000EM2 (ENGINE-2) 461AL 462AR.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-92-00-991-04700-B - Hot Section - Access) Subtask 24-92-00-220-054-A A.

Detailed Inspection of All Wiring installed in the Hot Section (1)

Do a detailed inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-12-0): (a)

(2) 5.

Start the detailed inspection of the wiring at the forward tip of the pylon and then continue into the hot engine section. Use a FLASHLIGHT or a MIRROR - INSPECTION, if necessary. 1

On the engine control routes: 1S (Ref. AWM 94-08-02), 2S (Ref. AWM 94-08-01).

2

On the other routes: 1M (Ref. AWM 94-08-01), 2M (Ref. AWM 94-08-02).

Make sure that there is no dust, fuel or oil contamination.

Close-up Subtask 24-92-00-410-163-B A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the thrust reverser halves (Ref. TASK 78-32-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 451AL 452AR

(b)

FOR 1000EM2 (ENGINE-2) 461AL 462AR.

Subtask 24-92-00-440-050-B B.

Activate the thrust reverser HCU (Ref. TASK 78-30-00-440-012-A).

Subtask 24-92-00-410-083-B C.

Close Access (1)

AES

Close the fan cowls (Ref. TASK 71-13-00-410-010-A): (a)

FOR 1000EM1 (ENGINE-1) 437AL 438AR

(b)

FOR 1000EM2 (ENGINE-2) 447AL 448AR.

(2)

Remove the access platform(s).

(3)

Remove the warning notice(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A B B

A

INSPECTION AREA ZONE 453−463 451AL (461AL) 437AL (447AL)

B INSPECTION AREA ZONE 454−464

452AR (462AR)

438AR (448AR) N_MM_249200_6_PLM0_01_00

AES

FIGURE 24-92-00-991-04700-B SHEET 1 Hot Section - Access

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-026-A General Visual Inspection of EWIS installed in the Wing Center Box (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-41-01-) GENERAL VISUAL INSPECTION OF EXPOSED EWIS INSTALLED IN THE WING CENTRE BOX (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

141 142 147AZ, 148AZ C.

ZONE DESCRIPTION WING CENTER BOX WING CENTER BOX

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

32-12-00-010-001-A 32-12-00-410-001-A 57-17-11-000-001-A

Open the Main Gear Doors for Access Close the Main Gear Doors after Access Removal of the Access Covers 147AZ (148AZ)

57-17-11-000-001-A-01

Removal of the Access Cover 148AZ or/and the ACT-Equipment Support Door

57-17-11-400-001-A

Installation of the Access Covers 147AZ (148AZ)

57-17-11-400-001-A-01

Installation of the Access Cover 148AZ or/and the ACT-Equipment Support Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-04800-A - Wing Center Box - Access - Zones 141-142) 3.

Job Set-up Subtask 24-92-00-010-086-A A.

AES

Get Access (1)

Open the main gear doors for access (Ref. TASK 32-12-00-010-001-A).

(2)

Put a WARNING NOTICE(S) in position to tell persons not to operate the landing gear.

(3)

Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

Remove the access panels from the wing center box (Ref. TASK 57-17-11-000-001-A) or (Ref. TASK 57-17-11-000-001-A-01): . 147AZ 148AZ.

Subtask 24-92-00-862-074-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-04800-A - Wing Center Box - Access - Zones 141-142) Subtask 24-92-00-210-076-A A.

Inspection of All Exposed Wiring Installed in the Wing Center Box (1)

Do a visual inspection of the wiring to make sure that there are no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the fuel quantity indication routes: 4S and 5S. NOTE :

5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Close-up Subtask 24-92-00-410-084-A A.

AES

Close Access (1)

Install the access panels on the wing center box (Ref. TASK 57-17-11-400-001-A) or (Ref. TASK 57-17-11-400-001-A-01): . 147AZ 148AZ.

(2)

Close the main gear doors after access (Ref. TASK 32-12-00-410-001-A).

(3)

Remove the access platform(s).

(4)

Remove the ground support and maintenance equipment, the special and standard tools and all other items.

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A B ZONE 141/142

Z140

A

FR42 FR36 INSPECTION AREA

B

147AZ

148AZ

N_MM_249200_6_ATM0_01_00

AES

FIGURE 24-92-00-991-04800-A SHEET 1 Wing Center Box - Access - Zones 141-142

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-027-A General Visual Inspection of EWIS Installed in the Forward Avionic Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-21-02-) GENERAL VISUAL INSPECTION OF EWIS INSTALLED IN THE FORWARD AVIONIC COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

121 122 121AF, 121AL, 121BF, 121CF, 122BF, 811 C.

ZONE DESCRIPTION AVIONICS COMPARTMENT AVIONICS COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

53-12-13-000-001-A Removal of the avionics compartment floor panels 53-12-13-400-001-A Installation of the avionics compartment floor panels ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-06100-A - Forward Avionic Compartment - Access) (Ref. Fig. 24-92-00-991-11000-A - Forward Avionic Compartment - Inspection Area - Zones 121-122) 3.

Job Set-up Subtask 24-92-00-010-089-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the access doors 121AL 811.

(3)

Remove the forward avionic-compartment floor-panels 121AF 121BF 121CF 122BF (Ref. TASK 53-12-13-000-001-A).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-862-077-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-06100-A - Forward Avionic Compartment - Access) (Ref. Fig. 24-92-00-991-11000-A - Forward Avionic Compartment - Inspection Area - Zones 121-122) Subtask 24-92-00-210-077-A A.

General Visual Inspection of All Wiring Installed in the Forward Avionic Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 4G, 5G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 6P.

(c)

On the flight control wiring.

(d)

On the engine-control routes: 1S and 2S.

(e)

On the other routes: 1M and 2M.

(f)

On the audio route: 1R.

(g)

On the coaxial cable routes: 4T, 3U and 4U.

(h)

On the generator excitation routes: 1E, 2E and 3E. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust, lint or hydraulic contamination.

Close-up Subtask 24-92-00-410-087-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the forward avionics-compartment floor-panels 121AF 121BF 121CF 122BF (Ref. TASK 53-12-13-400-001-A).

(3)

Close the access doors 121AL 811.

(4)

Remove the access platform(s).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

B A

FR12 FR6 FR1

A

811 121AL

B

FR1

FR7 FR3 FR5

FR2

122BF

121AF

121CF

121BF

N_MM_249200_6_RLM0_01_00

AES

FIGURE 24-92-00-991-06100-A SHEET 1 Forward Avionic Compartment - Access

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A Z120

A

INSPECTION AREA Z121−122

FR24 FR20

FR9 FR1

N_MM_249200_6_EMM0_01_00

AES

FIGURE 24-92-00-991-11000-A SHEET 1 Forward Avionic Compartment - Inspection Area - Zones 121-122

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-028-A General Visual Inspection of 90VU, 108VU and 109VU in the Forward Avionic Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-21-03-) GENERAL VISUAL INSPECTION OF 90, 108, 109 VU IN THE FORWARD AVIONIC COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

121 122 121AL, 811, 812, 822 C.

ZONE DESCRIPTION AVIONICS COMPARTMENT AVIONICS COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-05300-A - 90VU, 108VU and 109VU Location) 3.

Job Set-up Subtask 24-92-00-010-090-A A.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the access doors 121AL 811 812 822.

(3)

Remove the external power panel 108VU.

Subtask 24-92-00-862-078-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-05300-A - 90VU, 108VU and 109VU Location)

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-210-078-A A.

General Visual Inspection of 90VU, 108VU and 109VU in the Forward Avionic Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 4G, 5G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 6P.

(c)

On the flight control wiring.

(d)

On the engine control routes: 1S and 2S.

(e)

On the other routes: 1M and 2M.

(f)

On the audio route: 1R.

(g)

On the coaxial cable routes: 4T, 3U and 4U.

(h)

On the generator excitation routes: 1E, 2E and 3E. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust, lint or hydraulic contamination.

Close-up Subtask 24-92-00-410-088-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the external power panel 108VU.

(3)

Close the access doors 121AL 811 812 822.

(4)

Remove the access platform(s).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

90VU

INSPECTION AREA ZONE 121−122

FR12

B A 109VU

B

A

811

121AL 812 108VU 822

N_MM_249200_6_SLM0_01_00

AES

FIGURE 24-92-00-991-05300-A SHEET 1 90VU, 108VU and 109VU Location

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-220-005-A Detailed Inspection of G, E and P Routes in the Forward Avionic Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-21-04-) DETAILED INSPECTION OF G, E AND P ROUTES IN THE FORWARD AVIONIC COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

121 122 121AF, 121AL, 121BF, 121CF, 122BF, 811 C.

ZONE DESCRIPTION AVIONICS COMPARTMENT AVIONICS COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

53-12-13-000-001-A Removal of the avionics compartment floor panels 53-12-13-400-001-A Installation of the avionics compartment floor panels ESPM 20-52-12-0 (Ref. Fig. 24-92-00-991-06100-A - Forward Avionic Compartment - Access) (Ref. Fig. 24-92-00-991-11000-A - Forward Avionic Compartment - Inspection Area - Zones 121-122) 3.

Job Set-up Subtask 24-92-00-010-091-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the access doors 121AL 811.

(3)

Remove the forward avionic-compartment floor-panels 121AF 121BF 121CF 122BF (Ref. TASK 53-12-13-000-001-A).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-862-079-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-06100-A - Forward Avionic Compartment - Access) (Ref. Fig. 24-92-00-991-11000-A - Forward Avionic Compartment - Inspection Area - Zones 121-122) Subtask 24-92-00-220-055-A A.

Detailed Inspection of G, E and P Route Wiring in the Forward Avionic Compartment (1)

Do a detailed inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-12-0): (a)

On the AC/DC feeder routes: 4G, 5G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 6P.

(c)

On the generator excitation routes: 1E, 2E and 3E. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust, lint or hydraulic contamination.

Close-up Subtask 24-92-00-410-089-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the forward avionics-compartment floor-panels 121AF 121BF 121CF 122BF (Ref. TASK 53-12-13-400-001-A).

(3)

Close the access doors 121AL 811.

(4)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-029-A General Visual Inspection of EWIS of the 2000VU (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-23-02-) GENERAL VISUAL INSPECTION OF EWIS OF THE 2000VU (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

223 224

ZONE DESCRIPTION FWD CAB OVERHEAD COMPARTMENT FWD CAB OVERHEAD COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-05500-A - Forward Cabin Overhead Compartment - Inspection Area -Zones 223-224) 3.

Job Set-up Subtask 24-92-00-010-093-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 831 (841).

(2)

Open the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-010-001-A).

(3)

Open the circuit breaker panel 2000VU at the zone 220.

Subtask 24-92-00-862-081-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-05500-A - Forward Cabin Overhead Compartment - Inspection Area -Zones 223-224)

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-210-079-A A.

General Visual Inspection of All Wiring of the 2000VU (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust contamination.

Close-up Subtask 24-92-00-410-091-A A.

AES

Close Access (1)

Remove the ground support and maintenance equipment, the special and standard tools and all other items.

(2)

Close the circuit breaker panel 2000VU at the zone 220.

(3)

Close the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-410-001-A).

(4)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

Z220

B

A

FR23

B FR11

2000VU

INSPECTION AREA

N_MM_249200_6_AVM0_01_00

AES

FIGURE 24-92-00-991-05500-A SHEET 1 Forward Cabin Overhead Compartment - Inspection Area Zones 223-224

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-030-A General Visual Inspection of 105VU, 106VU, 103VU, 107VU and 70VU Installed in the Lateral Avionic Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-25-05-) GENERAL VISUAL INSPECTION OF 105, 106, 103, 107 AND 70 VUS INSTALLED IN THE LATERAL AVIONIC COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

125 126 812, 822 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-05800-A - 105VU, 106VU, 103VU, 107VU and 70VU - Location) 3.

Job Set-up Subtask 24-92-00-010-095-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

(2)

Open the forward passenger/crew door 831 (Ref. TASK 52-10-00-010-001-A).

(3)

Open the access doors 812 822.

Subtask 24-92-00-862-083-A B.

AES

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-92-00-991-05800-A - 105VU, 106VU, 103VU, 107VU and 70VU - Location) Subtask 24-92-00-210-080-A A.

General Visual Inspection of the 105VU, 106VU, 103VU, 107VU and 70VU Installed in the Lateral Avionic Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 1G, 2G, 4G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 6P.

(c)

On the flight control wiring.

(d)

On the engine control routes: 1S and 2S.

(e)

On the others routes: 1M, 2M and 6M.

(f)

On the audio route: 1R.

(g)

On the coaxial cable routes: 3T and 4T.

(h)

On the generator excitation routes: 1E, 2E, 3E and 6E. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust, lint or hydraulic contamination.

Close-up Subtask 24-92-00-410-093-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the forward passenger/crew door 831 (Ref. TASK 52-10-00-410-001-A).

(3)

Close the access doors 812 822.

(4)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A FR9 FR20

INSPECTION AREA Z125−126

812

A

107VU 822

831 70VU 103VU

FR20

FR9

106VU

105VU

N_MM_249200_6_TLM0_01_00

AES

FIGURE 24-92-00-991-05800-A SHEET 1 105VU, 106VU, 103VU, 107VU and 70VU - Location

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-031-A General Visual Inspection of G Route(s) Installed at FR47 (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-41-03-) GENERAL VISUAL INSPECTION OF G ROUTES INSTALLED AT FR 47 (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific No specific

AR AR

B.

Work Zones and Access Panels ZONE/ACCESS

241 242 242UW, 242VW, 242WW C.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

ZONE DESCRIPTION CENTER PASSENGER COMPARTMENT CENTER PASSENGER COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-43-000-001-A

Removal of the Upper Sidewall Panel(s)

25-23-43-400-001-A

Installation of the Upper Sidewall Panel(s)

25-23-44-000-001-A

Removal of the Lower Sidewall-Panels (Dado Panels)

25-23-44-400-001-A

Installation of the Lower Sidewall-Panels (Dado Panels)

25-23-48-000-001-A

Removal of the Cove Light Panels

25-23-48-400-001-A

Installation of the Cove Light Panels

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-06200-A - Center Passenger Compartment - Inspection -Route 6G) 3.

Job Set-up Subtask 24-92-00-010-097-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the furnishings in the zone 242 at FR47: (a)

(4)

Remove the lavatories, if installed (Ref. AMM 25-42-41-000-001) .

Remove the linings and insulation panels in the zone 242 at FR47: (a)

Remove the upper sidewall panels (Ref. TASK 25-23-43-000-001-A): . 242VW.

(b)

Remove the lower sidewall panels (Ref. TASK 25-23-44-000-001-A): . 242UW.

(c)

Remove the cove light panels (Ref. TASK 25-23-48-000-001-A): . 242WW.

Subtask 24-92-00-862-085-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-06200-A - Center Passenger Compartment - Inspection -Route 6G) Subtask 24-92-00-210-081-A A.

General Visual Inspection of G Route Wiring Installed at FR47 (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder wiring: route 6G. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust or lint contamination.

Close-up Subtask 24-92-00-410-095-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the linings and insulation panels in the zone 242 at FR47:

(3)

(a)

Install the upper sidewall panels (Ref. TASK 25-23-43-400-001-A): . 242VW.

(b)

Install the lower sidewall panels (Ref. TASK 25-23-44-400-001-A): . 242UW.

(c)

Install the cove light panels (Ref. TASK 25-23-48-400-001-A): . 242WW.

Install the furnishings in the zone 242 at FR47: (a)

AES

Install the lavatories, if removed (Ref. AMM 25-42-41-400-001) .

(4)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(5)

Remove the access platform(s).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A A

FR47 FR45

B 242WW

Z240

B

242VW INSPECTION OF ROUTE 6G

FR47 242UW

FR35 Z242

N_MM_249200_6_ARM0_01_00

AES

FIGURE 24-92-00-991-06200-A SHEET 1 Center Passenger Compartment - Inspection -Route 6G

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-033-A General Visual Inspection of EWIS Installed in the Rear Avionic Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-27-04-) GENERAL VISUAL INSPECTION OF EWIS INSTALLED IN THE REAR AVIONIC COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

B.

Work Zones and Access Panels ZONE/ACCESS

127 128 127BF, 127BG, 127CF, 127DF, 128CF, 128EG, 131AW, 131BW, 131CW, 131DW, 132BW, 132EW, 824, 825 C.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

ZONE DESCRIPTION REAR AVIONIC COMPARTMENT REAR AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-54-11-000-001-A

Removal of the Forward Cargo-Compartment Partition FR24

25-54-11-400-001-A

Installation of the Forward Cargo-Compartment Partition FR24

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

52-30-00-860-002-A 52-30-00-860-003-A

Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

53-12-13-000-001-A Removal of the avionics compartment floor panels 53-12-13-400-001-A Installation of the avionics compartment floor panels ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-07700-C - Rear Avionic Compartment - Access) (Ref. Fig. 24-92-00-991-11300-B - Rear Avionic Compartment - Inspection Area - Zones 127-128)

AES

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-92-00-010-107-C A.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the access door 824.

(3)

Open the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-001-A) or (Ref. TASK 52-30-00-860-003-A).

(4)

Remove the aft avionic-compartment floor-panels 127BG 127BF 127CF 127DF 128CF 128EG (Ref. TASK 53-12-13-000-001-A).

(5)

Remove the FWD cargo-compartment partition-panels 131AW 131BW 131CW 131DW 132BW 132EW (Ref. TASK 25-54-11-000-001-A).

Subtask 24-92-00-862-095-B B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-07700-C - Rear Avionic Compartment - Access) (Ref. Fig. 24-92-00-991-11300-B - Rear Avionic Compartment - Inspection Area - Zones 127-128) Subtask 24-92-00-210-083-B A.

General Visual Inspection of All Wiring Installed in the Rear Avionic Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 1G and 2G.

(b)

On the AC/DC power-distribution routes: 1P and 2P.

(c)

On the flight control wiring.

(d)

On the engine control routes: 1S and 2S.

(e)

On the other routes: 1M and 2M.

(f)

On the audio route: 1R.

(g)

On the coaxial wiring routes: 3T and 4T.

(h)

On the generator excitation routes: 1E and 2E. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust, lint or hydraulic contamination.

Close-up Subtask 24-92-00-410-105-C A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the aft avionic-compartment floor-panels 127BG 127BF 127CF 127DF 128CF 128EG (Ref. TASK 53-12-13-400-001-A).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AES

(3)

Install the FWD cargo-compartment partition-panels 131AW 131BW 131CW 131DW 132BW 132EW (Ref. TASK 25-54-11-400-001-A).

(4)

Close the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-002-A) or (Ref. TASK 52-30-00-860-004-A).

(5)

Close the access door 824.

(6)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 825

B A

824

B

FR21 127BG

127CF

FR23

127BF

128CF

128EG

127DF

FR24

C C PARTITION FR24.A 131BW

131AW

132BW

131DW

131CW

132EW

N_MM_249200_6_ZLM0_01_00

AES

FIGURE 24-92-00-991-07700-C SHEET 1 Rear Avionic Compartment - Access

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

Z120

A FR24

INSPECTION AREA Z127−128 FR20

N_MM_249200_6_GMM0_01_00

AES

FIGURE 24-92-00-991-11300-B SHEET 1 Rear Avionic Compartment - Inspection Area - Zones 127-128

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-220-007-A Detailed Inspection of G, E and P Routes Installed in the Rear Avionic Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-27-07-) DETAILED INSPECTION OF G, E AND P ROUTES INSTALLED IN THE REAR AVIONIC COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

B.

Work Zones and Access Panels ZONE/ACCESS

127 128 127BF, 127BG, 127CF, 127DF, 128CF, 128EG, 131AW, 131BW, 131CW, 131DW, 132BW, 132EW, 824, 825 C.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

ZONE DESCRIPTION REAR AVIONIC COMPARTMENT REAR AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-54-11-000-001-A

Removal of the Forward Cargo-Compartment Partition FR24

25-54-11-400-001-A

Installation of the Forward Cargo-Compartment Partition FR24

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

52-30-00-860-002-A 52-30-00-860-003-A

Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

53-12-13-000-001-A Removal of the avionics compartment floor panels 53-12-13-400-001-A Installation of the avionics compartment floor panels ESPM 20-52-12-0 (Ref. Fig. 24-92-00-991-07700-C - Rear Avionic Compartment - Access) (Ref. Fig. 24-92-00-991-11300-B - Rear Avionic Compartment - Inspection Area - Zones 127-128)

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-92-00-010-109-E A.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the access door 824.

(3)

Open the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-001-A) and (Ref. TASK 52-30-00-860-003-A).

(4)

Remove the aft avionic-compartment floor-panels 127BG 127BF 127CF 127DF 128CF 128EG (Ref. TASK 53-12-13-000-001-A).

(5)

Remove the FWD cargo-compartment partition-panels 131AW 131BW 131CW 131DW 132BW 132EW (Ref. TASK 25-54-11-000-001-A).

Subtask 24-92-00-862-097-B B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-07700-C - Rear Avionic Compartment - Access) (Ref. Fig. 24-92-00-991-11300-B - Rear Avionic Compartment - Inspection Area - Zones 127-128) Subtask 24-92-00-220-057-B A.

Detailed Inspection of G, E and P Route Wiring Installed in the Rear Avionic Compartment (1)

Do a detailed inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-12-0): (a)

On the AC/DC feeder routes: 1G and 2G.

(b)

On the AC/DC power-distribution routes: 1P and 2P.

(c)

On the generator excitation routes: 1E and 2E. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust, lint or hydraulic contamination.

Close-up Subtask 24-92-00-410-107-E A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the aft avionic-compartment floor-panels 127BG 127BF 127CF 127DF 128CF 128EG (Ref. TASK 53-12-13-400-001-A).

(3)

Install the FWD cargo-compartment partition-panels 131AW 131BW 131CW 131DW 132BW 132EW (Ref. TASK 25-54-11-400-001-A).

(4)

Close the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-002-A) and (Ref. TASK 52-30-00-860-004-A).

(5)

Close the access door 824.

(6)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-034-A General Visual Inspection of 63VU, 80VU, 187VU and 188VU Installed in the Rear Avionic Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-27-05-) GENERAL VISUAL INSPECTION OF 80, 63, 187, 188 VU INSTALLED IN THE REAR AVIONIC COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

127 128 824, 825 C.

ZONE DESCRIPTION REAR AVIONIC COMPARTMENT REAR AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-54-11-000-001-A

Removal of the Forward Cargo-Compartment Partition FR24

25-54-11-400-001-A

Installation of the Forward Cargo-Compartment Partition FR24

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

52-30-00-860-002-A 52-30-00-860-003-A

Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-07900-A - 63VU, 80VU, 187VU and 188VU - Location) 3.

Job Set-up Subtask 24-92-00-010-110-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the access door 824.

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Open the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-001-A) or (Ref. TASK 52-30-00-860-003-A).

(4)

Remove the FWD cargo-compartment partition FR24 (Ref. TASK 25-54-11-000-001-A).

Subtask 24-92-00-862-098-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-07900-A - 63VU, 80VU, 187VU and 188VU - Location) Subtask 24-92-00-210-084-A A.

General Visual Inspection of 63VU, 80VU, 187VU and 188VU Installed in the Rear Avionic compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 1G and 2G.

(b)

On the AC/DC power-distribution routes: 1P and 2P.

(c)

On the flight control wiring.

(d)

On the engine control routes: 1S and 2S.

(e)

On the other routes: 1M and 2M.

(f)

On the audio route: 1R.

(g)

On the coaxial wiring routes: 3T and 4T.

(h)

On the generator excitation routes: 1E and 2E. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust, lint or hydraulic contamination.

Close-up Subtask 24-92-00-410-108-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the FWD cargo-compartment partition FR24 (Ref. TASK 25-54-11-400-001-A).

(3)

Close the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-002-A) or (Ref. TASK 52-30-00-860-004-A).

(4)

Close the access door 824.

(5)

Remove the access platform(s).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

B

A

INSPECTION AREA Z127−128

824 825

B 63VU 188VU

80VU

187VU FR16

FR9

N_MM_249200_6_BMM0_01_00

AES

FIGURE 24-92-00-991-07900-A SHEET 1 63VU, 80VU, 187VU and 188VU - Location

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-035-A General Visual Inspection of EWIS of the 49VU and the 120VU (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-11-03-) GENERAL VISUAL INSPECTION OF EWIS OF 49VU AND THE 120VU (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

211 212

ZONE DESCRIPTION COCKPIT COCKPIT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-08200-A - 49VU and 120VU - Location) 3.

Job Set-up Subtask 24-92-00-862-099-A A.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-010-111-A B.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

(2)

Open the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-010-001-A).

(3)

Open the overhead circuit-breaker panel 49VU.

(4)

On the rear panel 120VU, open: . the rear circuit-breaker panel 121VU . the rear circuit-breaker panel 122VU

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . . . 4.

the AC power center 123VU the AC power center 124VU the rear circuit-breaker panel 125VU.

Procedure (Ref. Fig. 24-92-00-991-08200-A - 49VU and 120VU - Location) Subtask 24-92-00-210-085-A A.

General Visual Inspection of All Wiring of the 49VU and the 120VU (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 1G, 3G and 4G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 6P.

(c)

On the flight control wiring.

(d)

On the engine control routes: 1S and 2S.

(e)

On the other routes: 1M and 2M.

(f)

On the audio route: 1R.

(g)

On the generator excitation routes: 1E, 2E and 3E. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust or lint contamination.

Close-up Subtask 24-92-00-410-109-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

On . . . . .

(3)

Close the overhead circuit-breaker 49VU.

(4)

Close the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-410-001-A).

(5)

Remove the access platform(s).

the rear panel 120VU, close: the rear circuit-breaker panel 121VU the rear circuit-breaker panel 122VU the AC power center 123VU the AC power center 124VU the rear circuit-breaker panel 125VU.

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR24A

841

Z210

A B

831

A 49VU

FR1

INSPECTION AREA Z211−212

B 120VU

N_MM_249200_6_HMM0_01_00

AES

FIGURE 24-92-00-991-08200-A SHEET 1 49VU and 120VU - Location

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-036-A General Visual Inspection of EWIS Between Seat and A/C Installed in the Forward Passenger Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-31-03-) GENERAL VISUAL INSPECTION OF EWIS CONNECTIONS, ATTACHEMENT POINTS AND ELECTRICAL CONNECTORS BETWEEN SEAT AND A/C INSTALLED IN THE FORWARD PASSENGER COMPARTEMENT (EWIS)

2.

NOTE :

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

NOTE :

This task is applicable only for aircraft with seats and with wiring connections between seats and aircraft.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

231 232

ZONE DESCRIPTION FWD PASSENGER COMPARTMENT FWD PASSENGER COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-08300-A - Forward Passenger Compartment - Inspection Area - Zones 231-232) 3.

Job Set-up Subtask 24-92-00-010-112-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

(2)

Open the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the seat covers in zones 231 and 232, if necessary.

Subtask 24-92-00-862-100-A B.

AES

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-92-00-991-08300-A - Forward Passenger Compartment - Inspection Area - Zones 231-232) Subtask 24-92-00-210-086-A A.

5.

General Visual Inspection of All Wiring Connections Between Seat and Aircraft Installed in the Forward Passenger Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0).

(2)

Make sure that there is no dust or lint contamination.

Close-up Subtask 24-92-00-410-110-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the seat covers in zones 231 and 232, if necessary.

(3)

Close the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-410-001-A).

(4)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A Z230 841

831

A INSPECTION AREA Z231−232

FR35

FR20

N_MM_249200_6_KMM0_01_00

AES

FIGURE 24-92-00-991-08300-A SHEET 1 Forward Passenger Compartment - Inspection Area - Zones 231-232

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-810-A General Visual Inspection of All G and P Routes Installed in the Forward Passenger Overhead-Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-33-03-) GENERAL VISUAL INSPECTION OF ALL G & P ROUTES INSTALLED IN THE FORWARD PASSENGER COMPARTMENT OVERHEAD COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

233 234 231AC, 231BC, 231CC, 231DC, 231EC, 231FC, 231GC, 231HC, 232AC C.

ZONE DESCRIPTION FWD PASSENGER COMPT OVERHEAD COMPARTMENT FWD PASSENGER COMPT OVERHEAD COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-41-000-001-A

Removal of the Ceiling Panels

25-23-41-400-001-A

Installation of the Ceiling Panels

25-24-41-000-001-A

Removal of the Overhead Stowage Compartments

25-24-41-400-001-A

Installation of the Overhead Stowage Compartments

25-27-44-000-002-A

Removal of a Stowage FWD LH (Zone 231)

25-27-44-000-003-A

Removal of a Stowage FWD RH (Zone 232)

25-27-44-400-002-A

Installation of a Stowage FWD LH (Zone 231)

25-27-44-400-003-A

Installation of a Stowage FWD RH (Zone 232)

25-31-41-000-001-A

Removal of the Forward Galley Unit

25-31-41-400-001-A

Installation of the Forward Galley Unit

25-41-41-000-001-A

Removal of the Lavatory A

25-41-41-400-001-A

Installation of the Lavatory A

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE DESIGNATION ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-16000-A - Forward Passenger Overhead-Compartment - Access Panels - Zones 233-234) (Ref. Fig. 24-92-00-991-16100-A - Forward Passenger Overhead-Compartment - Inspection Area - Zones 233-234) 3.

Job Set-up Subtask 24-92-00-010-163-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 831 (841).

(2)

Open the passenger/crew door 831 (841) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the furnishings in the zones 231 and 232: (a)

Remove the lavatories, if installed (Ref. TASK 25-41-41-000-001-A) and (Ref. AMM 25-41-42-000-001) .

(b)

Remove the stowage, if installed (Ref. TASK 25-27-44-000-002-A) and (Ref. TASK 25-27-44-000-003-A).

(c)

Remove the galleys, if installed (Ref. AMM 25-31-41-000-002) and (Ref. TASK 25-31-41-000-001A).

(4)

Remove the overhead stowage compartments between FR20 and FR35 (Ref. TASK 25-24-41-000-001A).

(5)

Remove the ceiling panels in the zones 233 and 234 (Ref. TASK 25-23-41-000-001-A): . 231AC 232AC 231BC 231CC 231DC 231EC 231FC 231GC 231HC.

Subtask 24-92-00-862-145-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-16000-A - Forward Passenger Overhead-Compartment - Access Panels - Zones 233-234) (Ref. Fig. 24-92-00-991-16100-A - Forward Passenger Overhead-Compartment - Inspection Area - Zones 233-234) Subtask 24-92-00-210-110-A A.

General Visual Inspection of All G and P Route Wiring Installed in the Forward Passenger Overhead Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 3G and 6G. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust contamination.

Close-up Subtask 24-92-00-410-161-A A.

Close Access (1)

AES

Make sure that the work area is clean and clear of tool(s) and other items.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AES

(2)

Install the ceiling panels in the zones 233 and 234 (Ref. TASK 25-23-41-400-001-A): . 231AC 232AC 231BC 231CC 231DC 231EC 231FC 231GC 231HC.

(3)

Install the overhead stowage compartments between FR20 and FR35 (Ref. TASK 25-24-41-400-001-A).

(4)

Install the furnishings in the zones 231 and 232: (a)

Install the lavatories, if removed (Ref. TASK 25-41-41-400-001-A) and (Ref. AMM 25-41-42-400-001) .

(b)

Install the stowage, if removed (Ref. TASK 25-27-44-400-002-A) and (Ref. TASK 25-27-44-400-003-A).

(c)

Install the galleys, if removed (Ref. AMM 25-31-41-400-002) and (Ref. TASK 25-31-41-400-001A).

(5)

Close the passenger/crew door 831 (841) (Ref. TASK 52-10-00-410-001-A).

(6)

Remove the access platform(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FR20

FR36

FR34

FR32

FR30

FR28

FR26

FR24

FR21

231AC AD 232AC

231HC

231GC

231FC

231EC

231DC

231CC

231BC

N_MM_249200_6_EFM0_01_00

AES

FIGURE 24-92-00-991-16000-A SHEET 1 Forward Passenger Overhead-Compartment - Access Panels - Zones 233-234

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z230

A

A INSPECTION AREA Z233−Z234

FR35

FR20

N_MM_249200_6_DJM0_01_00

AES

FIGURE 24-92-00-991-16100-A SHEET 1 Forward Passenger Overhead-Compartment - Inspection Area - Zones 233-234

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-037-A General Visual Inspection of EWIS Connections Between Seats and A/C Installed in the Center Passenger Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-41-04-) GENERAL VISUAL INSPECTION OF EWIS CONNECTIONS, ATTACHMENT POINTS AND ELECTRICAL CONNECTORS BETWEEN SEATS AND A/C INSTALLED IN THE CENTER PASSENGER COMPARTMENT (EWIS)

2.

NOTE :

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

NOTE :

This task is applicable only for aircraft with seats and with wiring connections between seats and aircraft.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

241 242

ZONE DESCRIPTION CENTER PASSENGER COMPARTMENT CENTER PASSENGER COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-08400-A - Center Passenger Compartment - Inspection Area - Zones 241-242) 3.

Job Set-up Subtask 24-92-00-010-114-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

(2)

Open the aft passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the seat covers in zones 241 and 242, if necessary.

Subtask 24-92-00-862-102-A B.

AES

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-92-00-991-08400-A - Center Passenger Compartment - Inspection Area - Zones 241-242) Subtask 24-92-00-210-087-A A.

5.

General Visual Inspection of Wiring Connections Between Seats and Aircraft Installed in the Center Passenger Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0).

(2)

Make sure that there is no dust or lint contamination.

Close-up Subtask 24-92-00-410-112-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the seat covers in zones 241 and 242, if necessary.

(3)

Close the aft passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(4)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A Z240

842

832

A INSPECTION AREA Z241−242

FR42

FR36

N_MM_249200_6_JMM0_01_00

AES

FIGURE 24-92-00-991-08400-A SHEET 1 Center Passenger Compartment - Inspection Area - Zones 241-242

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-039-A General Visual Inspection of EWIS connections Between Seats and A/C Installed in the Aft Passenger Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-51-03-) GENERAL VISUAL INSPECTION OF EWIS CONNECTIONS, ATTACHMENT POINTS AND ELECTRICAL CONNECTORS BETWEEN SEATS AND A/C INSTALLED IN THE AFT PASSENGER COMPARTMENT (EWIS)

2.

NOTE :

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

NOTE :

This task is applicable only for aircraft with seats and with wiring connections between seats and aircraft.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

251 252

ZONE DESCRIPTION AFT PASSENGER COMPARTMENT AFT PASSENGER COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-09300-A - Aft Passenger Compartment - Inspection Area - Zones 251-252) 3.

Job Set-up Subtask 24-92-00-010-120-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

(2)

Open the aft passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the seat covers in zones 251 and 252, if necessary.

Subtask 24-92-00-862-108-A B.

AES

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-92-00-991-09300-A - Aft Passenger Compartment - Inspection Area - Zones 251-252) Subtask 24-92-00-210-089-A A.

5.

General Visual Inspection of Wiring Connections Between Seats and Aircraft Installed in the Aft Passenger Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0).

(2)

Make sure that there is no dust or lint contamination.

Close-up Subtask 24-92-00-410-118-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the seat covers in zones 251 and 252, if necessary.

(3)

Close the aft passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(4)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

842

Z250 832

A

INSPECTION AREA Z251−252

FR64

FR47

N_MM_249200_6_LMM0_01_00

AES

FIGURE 24-92-00-991-09300-A SHEET 1 Aft Passenger Compartment - Inspection Area - Zones 251-252

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-040-A General Visual Inspection of EWIS Connections Between Seats and A/C Installed in the Aft Cabin Utility (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-61-03-) GENERAL VISUAL INSPECTION OF EWIS CONNECTIONS, ATTACHMENT POINTS AND ELECTRICAL CONNECTORS BETWEEN SEATS AND A/C INSTALLED IN THE AFT CABIN UTILITY AREA (EWIS)

2.

NOTE :

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

NOTE :

This task is applicable only for aircraft with seats and with wiring connections between seats and aircraft.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

261 262

ZONE DESCRIPTION AFT CABIN UTILITY AREA AFT CABIN UTILITY AREA

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-09500-A - Aft Cabin Utility - Inspection Area - Zones 261-262) 3.

Job Set-up Subtask 24-92-00-010-121-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

(2)

Open the aft passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the seat covers in zones 261 and 262, if necessary.

Subtask 24-92-00-862-109-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-09500-A - Aft Cabin Utility - Inspection Area - Zones 261-262)

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-210-090-A A.

5.

General Visual Inspection of Wiring Connections Between Seats and Aircraft Installed in the Aft Cabin Utility Area (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0).

(2)

Make sure that there is no dust or lint contamination.

Close-up Subtask 24-92-00-410-119-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the seat covers in zones 261 and 262, if necessary.

(3)

Close the aft passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(4)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 842 Z260

832

A

A INSPECTION AREA Z261−262

FR70

FR64

N_MM_249200_6_MMM0_01_00

AES

FIGURE 24-92-00-991-09500-A SHEET 1 Aft Cabin Utility - Inspection Area - Zones 261-262

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-041-A General Visual Inspection of G and P Routes Installed in the Center Passenger Overhead Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-43-03-) GENERAL VISUAL INSPECTION OF G AND P ROUTES INSTALLED IN THE CENTER PASSENGER OVERHEAD COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific No specific

AR AR

B.

Work Zones and Access Panels ZONE/ACCESS

243 244 241AC, 241BC, 241CC, 241DC, 241EC, 241FC C.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

ZONE DESCRIPTION CENTER PASSENGER COMPT OVERHEAD COMPT CENTER PASSENGER COMPT OVERHEAD COMPT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-41-000-001-A

Removal of the Ceiling Panels

25-23-41-400-001-A

Installation of the Ceiling Panels

25-24-41-000-001-A

Removal of the Overhead Stowage Compartments

25-24-41-400-001-A

Installation of the Overhead Stowage Compartments

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-09800-A - Center Passenger Overhead-Compartment - Inspection Area - Zones 243-244) (Ref. Fig. 24-92-00-991-09900-A - Center Passenger Overhead-Compartment - Access Panels - Zones 243-244) 3.

Job Set-up Subtask 24-92-00-010-123-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the furnishings in the zones 241 and 242: (a)

Remove the lavatories, if installed (Ref. AMM 25-42-41-000-001) .

(4)

Remove the overhead stowage compartments between FR35 and FR47 (Ref. TASK 25-24-41-000-001A).

(5)

Remove the ceiling panels in the zones 243 and 244 (Ref. TASK 25-23-41-000-001-A): . 241AC 241BC 241CC 241DC 241EC 241FC.

Subtask 24-92-00-862-111-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-09800-A - Center Passenger Overhead-Compartment - Inspection Area - Zones 243-244) (Ref. Fig. 24-92-00-991-09900-A - Center Passenger Overhead-Compartment - Access Panels - Zones 243-244) Subtask 24-92-00-210-091-A A.

General Visual Inspection of G and P Route wiring Installed in the Center Passenger Overhead Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 3G and 6G.

(b)

On the AC/DC power- distribution routes: 1P, 2P and 3P. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust contamination.

Close-up Subtask 24-92-00-410-121-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the ceiling panels in the zones 243 and 244 (Ref. TASK 25-23-41-400-001-A): . 241AC 241BC 241CC 241DC 241EC 241FC.

(3)

Install the overhead stowage compartments between FR35 and FR47 (Ref. TASK 25-24-41-400-001-A).

(4)

Install the furnishings in the zones 241 and 242: (a)

AES

Install the lavatories, if removed (Ref. AMM 25-42-41-400-001) .

(5)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(6)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z240

A

A

INSPECTION AREA Z243−244

FR47

FR35

N_MM_249200_6_BAS0_01_00

AES

FIGURE 24-92-00-991-09800-A SHEET 1 Center Passenger Overhead-Compartment - Inspection Area - Zones 243-244

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FR38 FR43 FR47

FR41

FR36

FR39

FR45

AD

241BC 241FC

241EC

241DC 241CC

241AC

N_MM_249200_6_BBM0_01_00

AES

FIGURE 24-92-00-991-09900-A SHEET 1 Center Passenger Overhead-Compartment - Access Panels Zones 243-244

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-042-A General Visual Inspection of G and P Routes Installed in the Aft Passenger Overhead-Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-53-02-) GENERAL VISUAL INSPECTION OF G AND P ROUTES INSTALLED IN THE AFT PASSENGER OVERHEAD COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

253 AFT PASSENGER COMPARTMENT OVERHEAD COMPT 254 AFT PASSENGER COMPARTMENT OVERHEAD COMPT 251AC, 251BC, 251CC, 251DC, 251EC, 251FC, 251GC, 251HC, 251JC C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-41-000-001-A

Removal of the Ceiling Panels

25-23-41-400-001-A

Installation of the Ceiling Panels

25-24-41-000-001-A

Removal of the Overhead Stowage Compartments

25-24-41-400-001-A

Installation of the Overhead Stowage Compartments

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-10000-A - Aft Passenger Overhead-Compartment - Inspection Area -Zones 253-254) (Ref. Fig. 24-92-00-991-10100-A - Aft Passenger Overhead-Compartment - Access Panels - Zones 253-254) 3.

Job Set-up Subtask 24-92-00-010-124-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the furnishings in the zones 251 and 252: (a)

Remove the lavatories, if installed (Ref. AMM 25-42-41-000-001) .

(4)

Remove the overhead stowage compartments between FR47 and FR64 (Ref. TASK 25-24-41-000-001A).

(5)

Remove the ceiling panels in the zones 253 and 254 (Ref. TASK 25-23-41-000-001-A): . 251AC 251BC 251CC 251DC 251EC 251FC 251GC 251HC 251JC.

Subtask 24-92-00-862-112-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-10000-A - Aft Passenger Overhead-Compartment - Inspection Area -Zones 253-254) (Ref. Fig. 24-92-00-991-10100-A - Aft Passenger Overhead-Compartment - Access Panels - Zones 253-254) Subtask 24-92-00-210-092-A A.

General Visual Inspection of G and P Route Wiring Installed in the Aft Passenger Overhead-Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 3G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 3P. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust contamination.

Close-up Subtask 24-92-00-410-122-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the ceiling panels in the zones 253 and 254 (Ref. TASK 25-23-41-400-001-A): . 251AC 251BC 251CC 251DC 251EC 251FC 251GC 251HC 251JC.

(3)

Install the overhead stowage compartments between FR47 and FR64 (Ref. TASK 25-24-41-400-001-A).

(4)

Install the furnishings in the zones 251 and 252: (a)

AES

Install the lavatories, if removed (Ref. AMM 25-42-41-400-001) .

(5)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(6)

Remove the access platform(s).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z250

A

A

INSPECTION AREA Z253−254

FR64

FR47

N_MM_249200_6_EEM0_01_00

AES

FIGURE 24-92-00-991-10000-A SHEET 1 Aft Passenger Overhead-Compartment - Inspection Area Zones 253-254

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FR65

FR63

FR61

FR59

FR57

FR55

FR53

FR51

FR49

FR47

AD

251JC

251HC

251GC

251FC

251EC

251DC

251CC

251BC

251AC

N_MM_249200_6_EAM0_01_00

AES

FIGURE 24-92-00-991-10100-A SHEET 1 Aft Passenger Overhead-Compartment - Access Panels Zones 253-254

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-043-A General Visual Inspection of G and P Routes Installed in the Aft Cabin Overhead-Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-63-02-) GENERAL VISUAL INSPECTION OF G AND P ROUTES INSTALLED IN THE AFT CABIN OVERHEAD COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

263 AFT CABIN OVERHEAD COMPARTMENT 264 AFT CABIN OVERHEAD COMPARTMENT 251JC, 261BC, 261CC, 262BC, 262CC C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-41-000-001-A

Removal of the Ceiling Panels

25-23-41-400-001-A

Installation of the Ceiling Panels

25-23-42-000-002-A

Removal of the Ceiling Panels - Aft Utility Area

25-23-42-400-002-A

Installation of the Ceiling Panels - Aft Utility Area

25-24-41-000-001-A

Removal of the Overhead Stowage Compartments

25-24-41-400-001-A

Installation of the Overhead Stowage Compartments

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-11500-A - Aft Cabin Overhead-Compartment - Inspection Area - Zones 261-262) (Ref. Fig. 24-92-00-991-11600-A - Aft Cabin Overhead-Compartment - Access Panels - Zones 261-262) 3.

Job Set-up Subtask 24-92-00-010-128-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the overhead stowage compartments between FR64 and FR70 (Ref. TASK 25-24-41-000-001A).

(4)

Remove the ceiling panel in the zones 263 and 264 (Ref. TASK 25-23-41-000-001-A): . 251JC.

(5)

Remove the ceiling panels in the aft utility area (Ref. TASK 25-23-42-000-002-A): . 261BC 261CC 262BC 262CC.

Subtask 24-92-00-862-116-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-11500-A - Aft Cabin Overhead-Compartment - Inspection Area - Zones 261-262) (Ref. Fig. 24-92-00-991-11600-A - Aft Cabin Overhead-Compartment - Access Panels - Zones 261-262) Subtask 24-92-00-210-093-A A.

General Visual Inspection of G and P Route Wiring Installed in the Aft Cabin Overhead-Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 3G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 3P. NOTE :

(2) 5.

Use a flash light or a mirror if necessary.

Make sure that there is no dust contamination.

Close-up Subtask 24-92-00-410-126-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the ceiling panels in the aft utility area (Ref. TASK 25-23-42-400-002-A): . 261BC 261CC 262BC 262CC.

(3)

Install the ceiling panel in the zones 263 and 264 (Ref. TASK 25-23-41-400-001-A): . 251JC.

(4)

Install the overhead stowage compartments between FR64 and FR70 (Ref. TASK 25-24-41-400-001-A).

(5)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(6)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Z260

A

A INSPECTION AREA Z263−264

FR70

FR64

N_MM_249200_6_FBM0_01_00

AES

FIGURE 24-92-00-991-11500-A SHEET 1 Aft Cabin Overhead-Compartment - Inspection Area - Zones 261-262

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FR68

FR66

261BC 261CC

262CC 251JC 262BC

N_MM_249200_6_FAM0_01_00

AES

FIGURE 24-92-00-991-11600-A SHEET 1 Aft Cabin Overhead-Compartment - Access Panels - Zones 261-262

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-044-A General Visual Inspection of P Route Installed in the Aft Cabin Utility-Area (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-61-02-) GENERAL VISUAL INSPECTION OF P ROUTES INSTALLED IN THE AFT CABIN UTILITY AREA (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

261 262

ZONE DESCRIPTION AFT CABIN UTILITY AREA AFT CABIN UTILITY AREA

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-33-41-000-002-A

Removal of the Aft Galley Unit

25-33-41-400-002-A

Installation of the Aft Galley Unit

25-43-41-000-001-A

Removal of the Lavatory D

25-43-41-400-001-A

Installation of the Lavatory D

25-43-42-000-001-A

Removal of the Lavatory E

25-43-42-400-001-A

Installation of the Lavatory E

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-11800-A - Aft Cabin Utility Area - Inspection Area - Zones 261-262) (Ref. Fig. 24-92-00-991-11900-A - Aft Cabin Utility-Area - Access Panels - Zones 261-262) 3.

Job Set-up Subtask 24-92-00-010-129-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the furnishings in the zones 261 and 262: (a)

Remove the lavatories, if installed (Ref. TASK 25-43-41-000-001-A), (Ref. TASK 25-43-42-000-001-A), (Ref. AMM 25-43-43-000-001) , (Ref. AMM 25-43-44-000-001) , (Ref. AMM 25-43-44-000-003) and (Ref. AMM 25-43-48-000-001) .

(b)

Remove the galleys and stowage, if installed (Ref. AMM 25-33-41-000-001) , (Ref. TASK 25-33-41-000-002-A), (Ref. AMM 25-33-41-000-008) , (Ref. AMM 25-33-42-000-001) , (Ref. AMM 25-33-43-000-001) , (Ref. AMM 25-33-45-000-001) , (Ref. AMM 25-33-46-000-001) and (Ref. AMM 25-33-49-000-001) .

Subtask 24-92-00-862-117-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-11800-A - Aft Cabin Utility Area - Inspection Area - Zones 261-262) (Ref. Fig. 24-92-00-991-11900-A - Aft Cabin Utility-Area - Access Panels - Zones 261-262) Subtask 24-92-00-210-094-A A.

General Visual Inspection of P Route Wiring Installed in the Aft Cabin Utility Area (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC power-distribution routes: 2P installed between FR68 and FR70 on R side only. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust or lint contamination.

Close-up Subtask 24-92-00-410-127-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the furnishings in the zones 261 and 262: (a)

Install the lavatories, if removed (Ref. TASK 25-43-41-400-001-A), (Ref. TASK 25-43-42-400-001A), (Ref. AMM 25-43-43-400-001) , (Ref. AMM 25-43-44-400-001) , (Ref. AMM 25-43-44-400-003) and (Ref. AMM 25-43-48-400-001) .

(b)

Install the galleys and stowage, if removed (Ref. AMM 25-33-41-400-001) , (Ref. TASK 25-33-41-400-002-A), (Ref. AMM 25-33-41-400-008) , (Ref. AMM 25-33-42-400-001) , (Ref. AMM 25-33-43-400-001) , (Ref. AMM 25-33-45-400-001) , (Ref. AMM 25-33-46-400-001) and (Ref. AMM 25-33-49-400-001) .

(3)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(4)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z260

A

A INSPECTION AREA ZONE 261−262

FR70

FR64

N_MM_249200_6_DAM0_01_00

AES

FIGURE 24-92-00-991-11800-A SHEET 1 Aft Cabin Utility Area - Inspection Area - Zones 261-262

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

B

A

FR65

A

FR63 251CX

B

251BX 251AX

FR63

FR65 252CX

252AX

252BX N_MM_249200_6_DBM0_01_00

AES

FIGURE 24-92-00-991-11900-A SHEET 1 Aft Cabin Utility-Area - Access Panels - Zones 261-262

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-045-A General Visual Inspection of EWIS of 2001VU (EWIS) 1.

Reason for the Job (Ref. MPD 20-02-63-03-) GENERAL VISUAL INSPECTION OF ALL EWIS OF 2001 VU (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

263 264

ZONE DESCRIPTION AFT CABIN OVERHEAD COMPARTMENT AFT CABIN OVERHEAD COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-12100-A - Forward Cabin Overhead-Compartment - Inspection Area - Zones 263-264) 3.

Job Set-up Subtask 24-92-00-010-130-A A.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

(3)

Open the circuit breaker panel 2001VU at the zone 260.

Subtask 24-92-00-862-118-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-12100-A - Forward Cabin Overhead-Compartment - Inspection Area - Zones 263-264)

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-210-095-A A.

General Visual Inspection of All Wiring of the 2001VU (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust contamination.

Close-up Subtask 24-92-00-410-128-A A.

AES

Close Access (1)

Remove the ground support and maintenance equipment, the special and standard tools and all other items.

(2)

Close the circuit breaker panel 2001VU at the zone 260.

(3)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(4)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

Z260

A

B

FR68

B 2001VU

INSPECTION AREA

N_MM_249200_6_BDM0_01_00

AES

FIGURE 24-92-00-991-12100-A SHEET 1 Forward Cabin Overhead-Compartment - Inspection Area Zones 263-264

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-801-A General Visual Inspection of All Exposed EWIS Within the Wing Fuel Tank (EWIS) 1.

Reason for the Job (Ref. MPD 20-05-40-02-) GENERAL VISUAL INSPECTION OF EXPOSED EWIS WITHIN THE WING FUEL TANK (EWIS) (Ref. MPD 20-05-40-03-) GENERAL VISUAL INSPECTION OF EXPOSED EWIS WITHIN THE WING FUEL TANK (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 5M (16 FT)

No specific

AR

SAFETY BARRIER(S)

No specific

AR

WARNING NOTICE(S)

98D27803500001

1

TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER

B.

Work Zones and Access Panels ZONE/ACCESS

540 640 521AZ, 521BZ, 540AB, 540AZ, 540BB, 540BZ, 540CB, 540DB, 540EB, 540FB, 540GB, 540HB, 540JB, 540KB, 540LB, 540MB, 540NB, 540PB, 540QB, 540RB, 621AZ, 621BZ, 640AB, 640AZ, 640BB, 640BZ, 640CB, 640DB, 640EB, 640FB, 640GB, 640HB, 640JB, 640KB, 640LB, 640MB, 640NB, 640PB, 640QB, 640RB C.

ZONE DESCRIPTION FUEL TANK FUEL TANK

Referenced Information

REFERENCE 12-11-28-650-003-A 24-41-00-862-002-A

DESIGNATION Pressure Refuel with Automatic Control De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

28-10-00-910-001-A 28-10-00-910-002-A 28-25-00-650-001-A 28-25-00-650-003-A

Safety Procedures When You Do Work in a Fuel Tank Access to the Fuel Tanks and the Work Areas Pressure Defuel To Drain Remaining Fuel from the Wing Tanks and the Center Tank

28-25-00-650-003-A-01

To Drain Remaining Fuel from the Wing Tanks and the Center Tank

28-25-00-869-001-A

Fuel Transfer

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE DESIGNATION 57-27-11-000-001-A Removal of the Access Panel 57-27-11-000-002-A Removal of the Access Panel 57-27-11-000-005-A Removal of the Access Panel 57-27-11-400-001-A Installation of the Access Panel 57-27-11-400-002-A Installation of the Access Panel 57-27-11-400-005-A Installation of the Access Panel ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-13100-A - Wing Fuel Tank - Inspection Area - Zones 540-640) (Ref. Fig. 24-92-00-991-13500-A - Wing Fuel Tank - Access Panels - Zone 540) (Ref. Fig. 24-92-00-991-13600-A - Wing Fuel Tank - Access Panels - Zone 640) 3.

Job Set-up Subtask 24-92-00-941-058-A A.

Safety Precautions WARNING : OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK. (1)

Put the safety barriers in position. NOTE :

You must obey the fuel safety procedures (Ref. TASK 28-10-00-910-001-A) and (Ref. TASK 28-10-00-910-002-A) when you do work in a fuel tank.

(2)

Install the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) on the flap/slat control lever.

(3)

Put WARNING NOTICE(S) in position in the cockpit to tell persons not to operate the flaps or slats.

Subtask 24-92-00-650-050-A B.

Fuel Configuration (1)

Defuel the applicable fuel tank (Ref. TASK 28-25-00-650-001-A).

(2)

Drain the remaining fuel from the applicable fuel tank (Ref. TASK 28-25-00-650-003-A) or (Ref. TASK 28-25-00-650-003-A-01).

Subtask 24-92-00-010-135-A C.

Get Access (1)

Put an adjustable ACCESS PLATFORM 5M (16 FT) in position at the zones 540 and 640.

(2)

Open the RIB2 surge doors:

(3)

(a)

For the left wing: . 540AZ 540BZ.

(b)

For the right wing: . 640AZ 640BZ.

Remove the access panels between RIB2 to RIB13 (Ref. TASK 57-27-11-000-001-A) and (Ref. TASK 57-27-11-000-005-A): (a)

AES

For the left wing: . 540AB 540BB 540CB 540DB 540EB 540FB 540GB . 521AZ 521BZ.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (b)

(4)

For the right wing: . 640AB 640BB 640CB 640DB 640EB 640FB 640GB . 621AZ 621BZ.

Remove the access panels between RIB13 to RIB22 (Ref. TASK 57-27-11-000-002-A): (a)

For the left wing: . 540HB 540JB 540KB 540LB 540MB 540NB 540PB 540QB 540RB.

(b)

For the right wing: . 640HB 640JB 640KB 640LB 640MB 640NB 640PB 640QB 640RB.

Subtask 24-92-00-862-123-A D.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-13100-A - Wing Fuel Tank - Inspection Area - Zones 540-640) (Ref. Fig. 24-92-00-991-13500-A - Wing Fuel Tank - Access Panels - Zone 540) (Ref. Fig. 24-92-00-991-13600-A - Wing Fuel Tank - Access Panels - Zone 640) Subtask 24-92-00-210-099-A A.

General Visual Inspection of All Exposed Wiring Within the Wing Fuel Tank (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

5.

On sensitive routes: 1S and 2S and fuel quantity probes.

Close-up Subtask 24-92-00-410-133-A A.

Close Access (1)

(2)

(3)

AES

Close the RIB2 surge doors: (a)

For the left wing: . 540AZ 540BZ.

(b)

For the right wing: . 640AZ 640BZ.

Install the access panels between RIB2 to RIB13 (Ref. TASK 57-27-11-400-001-A) and (Ref. TASK 57-27-11-400-005-A): (a)

For the left wing: . 540AB 540BB 540CB 540DB 540EB 540FB 540GB . 521AZ 521BZ.

(b)

For the right wing: . 640AB 640BB 640CB 640DB 640EB 640FB 640GB . 621AZ 621BZ.

Install the access panels between RIB13 to RIB22 (Ref. TASK 57-27-11-400-002-A): (a)

For the left wing: . 540HB 540JB 540KB 540LB 540MB 540NB 540PB 540QB 540RB

(b)

For the right wing: . 640HB 640JB 640KB 640LB 640MB 640NB 640PB 640QB 640RB.

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-650-052-A B.

Fuel Configuration (1)

Refuel, defuel or transfer fuel as necessary (Ref. TASK 12-11-28-650-003-A), (Ref. TASK 28-25-00-650-001-A), (Ref. TASK 28-25-00-869-001-A).

Subtask 24-92-00-942-056-A C.

AES

Removal of Equipment (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) from the flap/slat control lever.

(3)

Remove the safety barriers.

(4)

Remove the access platform(s).

(5)

Remove the warning notice(s).

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z640

A

Z540

A INSPECTION AREA Z540−640

N_MM_249200_6_DDM0_01_00

AES

FIGURE 24-92-00-991-13100-A SHEET 1 Wing Fuel Tank - Inspection Area - Zones 540-640

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

RIB 22 540RB 540QB 540PB 540NB 540MB 540LB 540KB 540JB RIB 13

540HB 540GB 540FB

540EB

B

540DB 540CB

521AZ

521BZ

540BB

B RIB5

RIB 5

RIB 6

RIB 6B

RIB2 540AB

540AZ

540BZ N_MM_249200_6_DGM0_01_00

AES

FIGURE 24-92-00-991-13500-A SHEET 1 Wing Fuel Tank - Access Panels - Zone 540

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

640AZ

640BZ 640AB

RIB 2

A

B 640BB

640CB 640DB 640EB 640FB 640GB RIB 13 640HB 640JB 640KB 640LB 640MB 640NB

B 621 BZ

640PB

621 AZ

640QB 640RB RIB 22

RIB 6B

RIB 6

RIB 5

N_MM_249200_6_DHM0_01_00

AES

FIGURE 24-92-00-991-13600-A SHEET 1 Wing Fuel Tank - Access Panels - Zone 640

24-92-00 PB601

Page 7 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-802-A General Visual Inspection of All Exposed EWIS Within the Vent Surge Tank (EWIS) 1.

Reason for the Job (Ref. MPD 20-05-50-01-) GENERAL VISUAL INSPECTION OF EXPOSED EWIS WITHIN THE VENT SURGE TANK (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE

No specific

AR

SAFETY BARRIER(S)

No specific

AR

WARNING NOTICE(S)

98D27803500001

1

TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER

B.

Work Zones and Access Panels ZONE/ACCESS

550 650 550AB, 550BB, 550CB, 550DB, 650AB, 650BB, 650CB, 650DB C.

ZONE DESCRIPTION VENT SURGE TANK VENT SURGE TANK

Referenced Information

REFERENCE 12-11-28-650-003-A 24-41-00-862-002-A

DESIGNATION Pressure Refuel with Automatic Control De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

28-10-00-910-001-A 28-10-00-910-002-A 28-25-00-650-001-A 28-25-00-650-003-A

Safety Procedures When You Do Work in a Fuel Tank Access to the Fuel Tanks and the Work Areas Pressure Defuel To Drain Remaining Fuel from the Wing Tanks and the Center Tank

28-25-00-650-003-A-01

To Drain Remaining Fuel from the Wing Tanks and the Center Tank

28-25-00-869-001-A Fuel Transfer 57-27-11-000-002-A Removal of the Access Panel 57-27-11-400-002-A Installation of the Access Panel ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-13800-A - Vent Surge Tank - Access Panels - Zones 550-650) (Ref. Fig. 24-92-00-991-13900-A - Vent Surge Tank - Inspection Area - Zones 550-650)

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-92-00-941-061-A A.

Safety Precautions WARNING : OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK. (1)

Put the safety barriers in position. NOTE :

You must obey the fuel safety procedures when you do work in a fuel tank (Ref. TASK 28-10-00-910-001-A) and (Ref. TASK 28-10-00-910-002-A).

(2)

Install the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) on the flap/slat control lever.

(3)

Put WARNING NOTICE(S) in the cockpit to tell persons not to operate the flaps or slats.

Subtask 24-92-00-650-056-A B.

Fuel Configuration (1)

Drain the remaining fuel from the applicable surge tank (Ref. TASK 28-25-00-650-003-A) or (Ref. TASK 28-25-00-650-003-A-01).

Subtask 24-92-00-010-138-A C.

Get Access (1)

Put an ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the zones 550 and 650.

(2)

Remove the access panels between RIB22 to RIB26 (Ref. TASK 57-27-11-000-002-A): (a)

For the left wing: . 550AB 550BB 550CB 550DB.

(b)

For the right wing: . 650AB 650BB 650CB 650DB.

Subtask 24-92-00-862-126-A D.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-13800-A - Vent Surge Tank - Access Panels - Zones 550-650) (Ref. Fig. 24-92-00-991-13900-A - Vent Surge Tank - Inspection Area - Zones 550-650) Subtask 24-92-00-210-102-A A.

General Visual Inspection of All Exposed Wiring Within the Vent Surge Tank (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

AES

On sensitive routes: 1S and 2S, surge tank overflow-sensor and electrical harness.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-92-00-410-136-A A.

Close Access (1)

Install the access panels between RIB22 to RIB26 (Ref. TASK 57-27-11-400-002-A): (a)

For the left wing: . 550AB 550BB 550CB 550DB.

(b)

For the right wing: . 650AB 650BB 650CB 650DB.

Subtask 24-92-00-650-057-A B.

Fuel Configuration (1)

Refuel, defuel or transfer fuel as necessary (Ref. TASK 12-11-28-650-003-A), (Ref. TASK 28-25-00-650-001-A), (Ref. TASK 28-25-00-869-001-A).

Subtask 24-92-00-942-059-A C.

AES

Removal of Equipment (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) from the flap/slat control lever.

(3)

Remove the safety barriers.

(4)

Remove the access platform(s).

(5)

Remove the warning notice(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

RIB 26 550DB (650DB)

550CB (650CB)

550BB (650BB)

RIB 22

550AB (650AB)

N_MM_249200_6_BRM0_01_00

AES

FIGURE 24-92-00-991-13800-A SHEET 1 Vent Surge Tank - Access Panels - Zones 550-650

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z650

Z550

A

A

INSPECTION AREA Z550−650

N_MM_249200_6_BPM0_01_00

AES

FIGURE 24-92-00-991-13900-A SHEET 1 Vent Surge Tank - Inspection Area - Zones 550-650

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-803-A General Visual Inspection of All Exposed EWIS Within Dry Bay (Outboard)(EWIS) 1.

Reason for the Job (Ref. MPD 20-05-60-01-) GENERAL VISUAL INSPECTION OF EXPOSED EWIS WITHIN THE DRY BAY (OUTBOARD) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE

No specific

AR

SAFETY BARRIER(S)

No specific

AR

WARNING NOTICE(S)

98D27803500001

1

TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

560

DRY BAY (OUTBOARD)

660

DRY BAY (OUTBOARD)

560AB, 660AB C.

Referenced Information

REFERENCE 12-11-28-650-003-A 24-41-00-862-002-A

DESIGNATION Pressure Refuel with Automatic Control De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

28-10-00-910-001-A 28-10-00-910-002-A 28-25-00-650-001-A 28-25-00-650-003-A

Safety Procedures When You Do Work in a Fuel Tank Access to the Fuel Tanks and the Work Areas Pressure Defuel To Drain Remaining Fuel from the Wing Tanks and the Center Tank

28-25-00-650-003-A-01

To Drain Remaining Fuel from the Wing Tanks and the Center Tank

28-25-00-869-001-A 57-27-11-000-002-A 57-27-11-400-002-A ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-14000-A - Dry

Fuel Transfer Removal of the Access Panel Installation of the Access Panel Bay (Outboard) - Access Panels - Zones 560-660)

(Ref. Fig. 24-92-00-991-14100-A - Dry Bay (Outboard) - Inspection Area - Zones 560-660)

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-92-00-941-062-A A.

Safety Precautions WARNING : OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK. (1)

Put the safety barriers in position. NOTE :

You must obey the fuel safety procedures (Ref. TASK 28-10-00-910-001-A) and (Ref. TASK 28-10-00-910-002-A) when you do work in a fuel tank.

(2)

Install the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) on the flap/slat control lever.

(3)

Put WARNING NOTICE(S) in position in the cockpit to tell persons not to operate the flaps or slats.

Subtask 24-92-00-650-058-A B.

Fuel Configuration (1)

Drain the remaining fuel from the applicable surge tank (Ref. TASK 28-25-00-650-003-A) or (Ref. TASK 28-25-00-650-003-A-01).

Subtask 24-92-00-010-139-A C.

Get Access (1)

Put an ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the zones 560 and 660.

(2)

Open the access panels (Ref. TASK 57-27-11-000-002-A): (a)

For the left wing: . 560AB.

(b)

For the right wing: . 660AB.

Subtask 24-92-00-862-127-A D.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-14000-A - Dry Bay (Outboard) - Access Panels - Zones 560-660) (Ref. Fig. 24-92-00-991-14100-A - Dry Bay (Outboard) - Inspection Area - Zones 560-660) Subtask 24-92-00-210-103-A A.

General Visual Inspection of All Exposed Wiring Within Dry Bay (Outboard) (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

AES

On sensitive routes: 1S and 2S, vent surge tank overflow sensor.

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-92-00-410-137-A A.

Close Access (1)

Install the access panels (Ref. TASK 57-27-11-400-002-A): (a)

For the left wing: . 560AB.

(b)

For the right wing: . 660AB.

Subtask 24-92-00-650-059-A B.

Fuel Configuration (1)

Refuel, defuel or transfer fuel as necessary (Ref. TASK 12-11-28-650-003-A), (Ref. TASK 28-25-00-650-001-A), (Ref. TASK 28-25-00-869-001-A).

Subtask 24-92-00-942-060-A C.

AES

Removal of Equipment (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Remove the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) from the flap/slat control lever.

(3)

Remove the safety barriers.

(4)

Remove the access platform(s).

(5)

Remove the warning notice(s).

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

560AB (660AB) RIB 26

RIB 22

N_MM_249200_6_BTM0_01_00

AES

FIGURE 24-92-00-991-14000-A SHEET 1 Dry Bay (Outboard) - Access Panels - Zones 560-660

24-92-00 PB601

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z660

Z560

A

A

INSPECTION AREA Z560−660

N_MM_249200_6_TPM0_01_00

AES

FIGURE 24-92-00-991-14100-A SHEET 1 Dry Bay (Outboard) - Inspection Area - Zones 560-660

24-92-00 PB601

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-804-A General Visual Inspection of P Route Pump Feeder EWIS (EWIS) 1.

Reason for the Job (Ref. MPD 20-05-71-01-) GENERAL VISUAL INSPECTION OF P ROUTE PUMP FEEDER (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

No specific

AR

SAFETY BARRIER(S)

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

571 671

ZONE DESCRIPTION MLG BAY MLG BAY

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

28-21-49-000-001-A

Removal of the Fuel Pump Fairings

28-21-49-400-001-A

Installation of the Fuel Pump Fairings

32-00-00-481-001-A

Installation of the Safety Devices on the Landing Gears

32-12-00-010-001-A Open the Main Gear Doors for Access 32-12-00-410-001-A Close the Main Gear Doors after Access ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-14200-A - MLG Bay - Inspection Area - Zones 571-671) 3.

Job Set-up Subtask 24-92-00-941-063-A A.

AES

Safety Precautions (1)

Put the safety barriers in position.

(2)

Make sure that the ground safety locks are on the landing gear (Ref. TASK 32-00-00-481-001-A).

(3)

On the R center instrument panel 400VU: . Make sure that the landing-gear control-lever 6GA is in the DOWN position. . Put a WARNING NOTICE(S) in position to tell persons not to operate the landing gear.

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-010-140-A B.

Get Access (1)

Open the MLG doors (Ref. TASK 32-12-00-010-001-A):

(2)

Make sure that the GROUND LOCK SLEEVE is correctly installed on the applicable MLG door actuating-cylinder.

(3)

Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the zones 571 and 671.

(4)

Remove the fuel pump fairings (Ref. TASK 28-21-49-000-001-A).

Subtask 24-92-00-862-128-A C.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-14200-A - MLG Bay - Inspection Area - Zones 571-671) Subtask 24-92-00-210-104-A A.

General Visual Inspection of P Route Pump Feeder Wiring (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

5.

On the AC/DC power-distribution routes: 1P and 2P.

Close-up Subtask 24-92-00-410-138-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the fuel pump fairings (Ref. TASK 28-21-49-400-001-A).

(3)

Close the MLG doors (Ref. TASK 32-12-00-410-001-A).

(4)

Remove the safety barriers.

(5)

Remove the access platform(s).

(6)

Remove the warning notice(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z540 Z640

A

B A Z571 Z671

B

N_MM_249200_6_BZM0_01_00

AES

FIGURE 24-92-00-991-14200-A SHEET 1 MLG Bay - Inspection Area - Zones 571-671

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-805-A General Visual Inspection of G, E and P Routes Installed in the Forward Cargo Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-31-02-) GENERAL VISUAL INSPECTION OF G, E AND P ROUTES INSTALLED IN THE FORWARD CARGO COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

131 132 825

ZONE DESCRIPTION FORWARD CARGO COMPARTMENT FORWARD CARGO COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-54-12-000-002-A

Removal of the Ceiling Panels in the Forward Cargo-Compartment

25-54-12-000-003-A

Removal of the Sidewall Panels in the Forward Cargo-Compartment

25-54-12-400-002-A

Installation of the Ceiling Panels in the Forward Cargo-Compartment

25-54-12-400-003-A

Installation of the Sidewall Panels in the Forward Cargo- Compartment

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

52-30-00-860-002-A 52-30-00-860-003-A

Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-14600-A - Forward Cargo Compartment - Inspection Area - Zones 131-132)

AES

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-92-00-010-143-A A.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-001-A) and (Ref. TASK 52-30-00-860-003-A).

(3)

Remove the ceiling panels in the FWD cargo compartment from FR24 to FR34 (Ref. TASK 25-54-12-000-002-A).

(4)

Remove the sidewall panels in the FWD cargo compartment from FR24 to FR34 (Ref. TASK 25-54-12-000-003-A).

Subtask 24-92-00-862-131-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-14600-A - Forward Cargo Compartment - Inspection Area - Zones 131-132) Subtask 24-92-00-210-105-A A.

General Visual Inspection of G, E and P Routes Installed in the Forward Cargo Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 1G and 2G.

(b)

On the AC/DC power-distribution routes: 1P and 2P.

(c)

On the generator excitation routes: 1E and 2E. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust, lint or hydraulic contamination.

Close-up Subtask 24-92-00-410-141-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the sidewall panels in the FWD cargo compartment from FR24 to FR34 (Ref. TASK 25-54-12-400-003-A).

(3)

Install the ceiling panels in the FWD cargo compartment from FR24 to FR34 (Ref. TASK 25-54-12-400-002-A).

(4)

Close the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-002-A) and (Ref. TASK 52-30-00-860-004-A).

(5)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

825

A

A FR34

FR24

INSPECTION AREA Z131−132

N_MM_249200_6_SMM0_01_00

AES

FIGURE 24-92-00-991-14600-A SHEET 1 Forward Cargo Compartment - Inspection Area - Zones 131-132

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-806-A General Visual Inspection of P Route(s) Installed in the Aft Cargo Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-51-02-) GENERAL VISUAL INSPECTION OF P ROUTES INSTALLED IN AFT CARGO COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

151 152 826

ZONE DESCRIPTION AFT CARGO COMPARTMENT AFT CARGO COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-55-11-000-002-A

Removal of the Ceiling Panels in the Aft Cargo-Compartment - FR47/FR59

25-55-11-000-003-A

Removal of the Sidewall Panels in the Aft Cargo-Compartment - FR47/FR59

25-55-11-400-002-A

Installation of the Ceiling Panels in the Aft Cargo-Compartment -FR47/FR59

25-55-11-400-003-A

Installation of the Sidewall Panels in the Aft Cargo-Compartment - FR47/FR59

52-30-00-860-001-A

52-30-00-860-003-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-002-A

ESPM 20-52-11-0 AWM 94-42-20 AWM 94-42-21 (Ref. Fig. 24-92-00-991-14700-A - Aft Cargo Compartment - Inspection Area - Zones 151-152) 3.

Job Set-up Subtask 24-92-00-010-144-A A.

Get Access (1)

AES

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Open the AFT cargo-compartment door 826 (Ref. TASK 52-30-00-860-001-A) and (Ref. TASK 52-30-00-860-003-A).

(3)

Remove the additional center tanks No. 1, No. 2 and No. 3 in zones 151 and 152, if installed (Ref. AMM 28-11-27-000-002) , (Ref. AMM 28-11-27-000-003) and (Ref. AMM 28-11-27-000-004) .

(4)

Remove the sidewall panels in the AFT cargo compartment from FR47 to FR59 (Ref. TASK 25-55-11-000-003-A). NOTE :

(5)

To see the panels that you must remove, refer to (Ref. AWM 94-42-20) or (Ref. AWM 94-42-21).

Remove the ceiling panels in the AFT cargo compartment from FR47 to FR59 (Ref. TASK 25-55-11-000-002-A). NOTE :

To see the panels that you must remove, refer to (Ref. AWM 94-42-20) or (Ref. AWM 94-42-21).

Subtask 24-92-00-862-132-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-14700-A - Aft Cargo Compartment - Inspection Area - Zones 151-152) Subtask 24-92-00-210-106-A A.

General Visual Inspection of P Route Wiring Installed in the Aft Cargo Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

(2) 5.

On the AC/DC power-distribution routes: 1P and 2P.

Make sure that there is no dust, lint or hydraulic contamination.

Close-up Subtask 24-92-00-410-142-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the ceiling panels in the AFT cargo compartment from FR47 to FR59 (Ref. TASK 25-55-11-400-002-A).

(3)

Install the sidewall panels in the AFT cargo compartment from FR47 to FR59 (Ref. TASK 25-55-11-400-003-A).

(4)

Install the additional center tanks No. 1, No. 2 and No. 3 in zones 151 and 152, if removed (Ref. AMM 28-11-27-400-002) , (Ref. AMM 28-11-27-400-003) and (Ref. AMM 28-11-27-400-004) .

(5)

Close the AFT cargo-compartment door 826 (Ref. TASK 52-30-00-860-002-A) and (Ref. TASK 52-30-00-860-004-A).

(6)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 826

A FR59

FR47

INSPECTION AREA Z151−152 N_MM_249200_6_UMM0_01_00

AES

FIGURE 24-92-00-991-14700-A SHEET 1 Aft Cargo Compartment - Inspection Area - Zones 151-152

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-808-A General Visual Inspection of EWIS Installed in the Lateral Avionic Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-25-03-) GENERAL VISUAL INSPECTION OF EWIS INSTALLED IN THE LATERAL AVIONIC COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific No specific

AR AR

B.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

Work Zones and Access Panels ZONE/ACCESS

125 126 812, 813, 822, 824 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-52-11-0 (Ref. Fig. 24-92-00-991-15600-A - Lateral Avionic Compartment - Inspection Area - Zones 125-126) 3.

Job Set-up Subtask 24-92-00-010-153-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

(2)

Open the forward passenger/crew door 831 (Ref. TASK 52-10-00-010-001-A).

(3)

Open the access doors 812 822 824.

(4)

Open the access door 813, if installed.

Subtask 24-92-00-862-139-A B.

AES

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-92-00-991-15600-A - Lateral Avionic Compartment - Inspection Area - Zones 125-126) Subtask 24-92-00-210-108-A A.

General Visual Inspection of All Wiring Installed in the Lateral Avionic Compartment (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-11-0): (a)

On the AC/DC feeder routes: 1G, 2G, 4G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 6P.

(c)

On the flight control wiring.

(d)

On the engine control routes: 1S and 2S.

(e)

On the other routes: 1M, 2M and 6M.

(f)

On the audio route: 1R.

(g)

On the coaxial wiring routes: 3T and 4T.

(h)

On the generator excitation routes: 1E, 2E, 3E and 6E. NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust, lint or hydraulic contamination.

Close-up Subtask 24-92-00-410-151-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access door 813, if installed.

(3)

Close the access doors 812 822 824.

(4)

Close the forward passenger/crew door 831 (Ref. TASK 52-10-00-410-001-A).

(5)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR9

B FR20

A 831 813

A 812

822 824

B FR20

FR9

INSPECTION AREA Z125−126

N_MM_249200_6_VMM0_01_00

AES

FIGURE 24-92-00-991-15600-A SHEET 1 Lateral Avionic Compartment - Inspection Area - Zones 125-126

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-220-008-A Detailed Inspection of G, E and P Routes Installed in the Lateral Avionic Compartment (EWIS) 1.

Reason for the Job (Ref. MPD 20-01-25-06-) DETAILED INSPECTION OF G, E AND P ROUTES INSTALLED IN THE LATERAL AVIONIC COMPARTMENT (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific No specific

AR AR

B.

Work Zones and Access Panels ZONE/ACCESS

125 126 812, 813, 822, 824 C.

FLASHLIGHT MIRROR - INSPECTION, FLEXIBLE

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

53-12-11-000-001-A

Removal of the Cockpit Floor Panels from FR1 Thru FR12

53-12-11-400-001-A Installation of the Cockpit Floor Panels from FR1 thru FR12 53-12-12-000-001-A Removal of the Cabin Floor Panels from FR12 thru FR24 53-12-12-400-001-A Installation of the Cabin Floor Panels from FR12 thru FR24 ESPM 20-52-12-0 AWM 94-21-06 AWM 94-21-20 AWM 94-23-05 (Ref. Fig. 24-92-00-991-15600-A - Lateral Avionic Compartment - Inspection Area - Zones 125-126) 3.

Job Set-up Subtask 24-92-00-010-154-A A.

Get Access (1)

AES

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Open the forward passenger/crew door 831 (Ref. TASK 52-10-00-010-001-A).

(3)

Open the access doors 812 822 824.

(4)

Open the access door 813, if installed.

(5)

Remove the cabin floor panels FR9 to FR16 (Ref. TASK 53-12-11-000-001-A) and (Ref. TASK 53-12-12-000-001-A).

Subtask 24-92-00-862-140-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-15600-A - Lateral Avionic Compartment - Inspection Area - Zones 125-126) Subtask 24-92-00-220-058-A A.

Detailed Inspection of G, E and P Routes Installed in the Lateral Avionic Compartment (1)

Do a detailed inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-12-0): (a)

On the AC/DC feeder routes: 1G, 2G (Ref. AWM 94-23-05), 4G, 6G (Ref. AWM 94-21-06).

(b)

On the AC/DC power-distribution routes: 1P, 2P and 6P (Ref. AWM 94-23-05), (Ref. AWM 94-21-06) and (Ref. AWM 94-21-20).

(c)

On the generator excitation routes: 1E, 2E, 3E and 6E. (Ref. AWM 94-23-05), (Ref. AWM 94-21-06) and (Ref. AWM 94-21-20). NOTE :

(2) 5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Make sure that there is no dust, lint or hydraulic contamination.

Close-up Subtask 24-92-00-410-152-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the cabin floor panels FR9 to FR16 (Ref. TASK 53-12-11-400-001-A) and (Ref. TASK 53-12-12-400-001-A).

(3)

Close the access door 813, if installed.

(4)

Close the access doors 812 822 824.

(5)

Close the forward passenger/crew door 831 (Ref. TASK 52-10-00-410-001-A).

(6)

Remove the access platform(s).

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-812-A Visual Inspection of EWIS Installed in the Forward Pylon After an Engine Bleed Leak (EWIS) 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

No specific

AR

FLASHLIGHT

No specific No specific

AR AR

MIRROR - INSPECTION, FLEXIBLE SAFETY CLIP - CIRCUIT BREAKER

No specific

AR

WARNING NOTICE(S)

B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

FOR FIN 1000EM1(ENGINE-1) 414AR FOR FIN 1000EM2(ENGINE-2) 424AR C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

ESPM 20-52-00-0 (Ref. Fig. 24-92-00-991-16400-A - Visual Inspection of the Wiring Installed in the Forward Pylon Between Rib01 and Rib07 at Zone B2) 3.

Job Set-up Subtask 24-92-00-941-064-A A.

AES

Safety Precautions (1)

On the center pedestal, on the ENG panel 115VU: . Put a WARNING NOTICE(S) in position to tell persons not to start the engine.

(2)

Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

(3)

On the overhead maintenance panel 50VU: . Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(4)

Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

24-92-00 PB601

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-865-061-A WARNING : MAKE SURE THAT YOU OPEN THE CIRCUIT BREAKERS AS FOLLOWS: 1JH, 2JH1 AND 3JH1 BEFORE 2KS1 1JH, 2JH2 AND 3JH2 BEFORE 2KS2. IF YOU DO NOT OBEY THIS SEQUENCE, THERE IS A RISK OF ELECTROCUTION. THIS IS BECAUSE YOU WILL START CONTINUOUS IGNITION IF YOU OPEN CIRCUIT BREAKER 2KS1 OR 2KS2 FIRST. B.

Open, safety and tag this(these) circuit breaker(s):

PANEL FOR FIN 1000EM1 49VU

DESIGNATION

FIN

LOCATION

ENGINE/1/FADEC A/AND EIU 1

2KS1

A04

49VU

ENGINE/1 AND 2/IGN/SYS A

1JH

A03

121VU

ENGINE/IGN/ENG1/SYS B

3JH1

P41

121VU

ENGINE/IGN/ENG1/SYS A BAT

2JH1

P39

121VU

ENGINE/ENG1/FADEC B/AND EIU 1

4KS1

R41

ENGINE/2/FADEC A/AND EIU 2

2KS2

A05

49VU

ENGINE/1 AND 2/IGN/SYS A

1JH

A03

121VU

ENGINE/IGN/ENG2/SYS B

3JH2

P42

121VU

ENGINE/IGN/ENG2/SYS A BAT

2JH2

P40

121VU

ENGINE/ENG2/FADEC B

4KS2

Q40

FOR FIN 1000EM2 49VU

Subtask 24-92-00-010-165-A C.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the forward pylon.

(2)

Remove the access panels: (a)

FOR 1000EM1 (ENGINE-1) 414AR.

(b)

FOR 1000EM2 (ENGINE-2) 424AR.

Subtask 24-92-00-862-147-A D.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-16400-A - Visual Inspection of the Wiring Installed in the Forward Pylon Between Rib01 and Rib07 at Zone B2)

AES

24-92-00 PB601

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-210-114-A A.

Visual Inspection of the Wiring Installed in the Forward Pylon After an Engine Bleed Leak (1)

Do a visual inspection of the wiring to make sure that there is no sign of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-00-0): (a)

(b)

For the left pylon: 1

On the AC/DC feeder route: 1G.

2

On the sensitive system routes: 1S and 2S.

3

On the not sensitive system route: 1M.

For the right pylon: 1

On the AC/DC feeder route: 2G.

2

On the sensitive system routes: 1S and 2S.

3

On the not sensitive system route: 2M. NOTE :

5.

Use a FLASHLIGHT or a MIRROR - INSPECTION, FLEXIBLE if necessary.

Close-up Subtask 24-92-00-410-164-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the access panels: (a)

FOR 1000EM1 (ENGINE-1) 414AR.

(b)

FOR 1000EM2 (ENGINE-2) 424AR.

(3)

Remove the access platform(s).

(4)

Remove the warning notice(s).

Subtask 24-92-00-865-062-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL FOR FIN 1000EM1 49VU

DESIGNATION

FIN

LOCATION

ENGINE/1/FADEC A/AND EIU 1

2KS1

A04

49VU

ENGINE/1 AND 2/IGN/SYS A

1JH

A03

121VU

ENGINE/IGN/ENG1/SYS B

3JH1

P41

121VU

ENGINE/IGN/ENG1/SYS A BAT

2JH1

P39

121VU

ENGINE/ENG1/FADEC B/AND EIU 1

4KS1

R41

ENGINE/2/FADEC A/AND EIU 2

2KS2

A05

49VU

ENGINE/1 AND 2/IGN/SYS A

1JH

A03

121VU

ENGINE/IGN/ENG2/SYS B

3JH2

P42

121VU

ENGINE/IGN/ENG2/SYS A BAT

2JH2

P40

FOR FIN 1000EM2 49VU

AES

24-92-00 PB601

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL PANEL 121VU

AES

DESIGNATION ENGINE/ENG2/FADEC B

FIN 4KS2

LOCATION Q40

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z420

A A

Z410

A

RIB07

A RIB01

A SECTION

AA FEEDERS

ROUTE M

ROUTES S

ZONE B2 N_MM_249200_6_GAM0_01_00

AES

FIGURE 24-92-00-991-16400-A SHEET 1 Visual Inspection of the Wiring Installed in the Forward Pylon Between Rib01 and Rib07 at Zone B2

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-813-A General Visual Inspection of EWIS Installed in the Keel Beam Area of MLG-Well and Hydraulic Compartment (EWIS) 1.

Reason for the Job (Ref. MPD ---) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT)

Work Zones and Access Panels ZONE/ACCESS

147 148 734, 744 C.

ZONE DESCRIPTION MAIN GEAR WELL AND HYDRAULIC COMPARTMENT MAIN GEAR WELL AND HYDRAULIC COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

32-12-00-010-001-A Open the Main Gear Doors for Access 32-12-00-410-001-A Close the Main Gear Doors after Access ESPM 20-52-00-0 (Ref. Fig. 24-92-00-991-16600-A - Aft Cargo Compartment - Inspection Area - Zones 147-148) 3.

Job Set-up Subtask 24-92-00-010-168-A A.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) in position at zones 147 and 148.

(2)

Open the main landing gear doors 734 744 (Ref. TASK 32-12-00-010-001-A).

Subtask 24-92-00-862-150-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-16600-A - Aft Cargo Compartment - Inspection Area - Zones 147-148)

AES

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-210-117-A A.

General Visual Inspection of EWIS installed in the Keel Beam Area of the Main Landing Gear (MLG) Well and Hydraulic Compartment (EWIS) (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-00-0). (a)

(2) 5.

On the routes: 1M, 2M.

Make sure that there is no dust or lint contamination.

Close-up Subtask 24-92-00-410-166-A A.

AES

Close Access (1)

Close the main landing gear doors 734 744 (Ref. TASK 32-12-00-410-001-A).

(2)

Remove the access platform(s).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A Z140

A FR47

FR42

INSPECTION AREA Z147−148

N_MM_249200_6_CTM0_01_00

AES

FIGURE 24-92-00-991-16600-A SHEET 1 Aft Cargo Compartment - Inspection Area - Zones 147-148

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-814-A General Visual Inspection of P Routes Installed in Bulk Cargo Compartment (EWIS) 1.

Reason for the Job (Ref. MPD ---) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

161 162 826

ZONE DESCRIPTION BULK CARGO COMPARTMENT BULK CARGO COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-55-12-000-003-A

Removal of the Sidewall Panels in the Aft Cargo Compartment - FR59/FR65

25-55-12-400-003-A

Installation of the Sidewall Panels in the Aft Cargo Compartment - FR59/FR65

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

52-30-00-860-002-A 52-30-00-860-003-A

Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

ESPM 20-52-00-0 (Ref. Fig. 24-92-00-991-16700-A - Bulk Cargo Compartment - Inspection Area - Zones 161-162) 3.

Job Set-up Subtask 24-92-00-010-169-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position.

(2)

Open the AFT cargo-compartment door 826 (Ref. TASK 52-30-00-860-001-A) or (Ref. TASK 52-30-00-860-003-A).

(3)

Remove the sidewall panels in the AFT cargo-compartment from FR59 to FR65 (Ref. TASK 25-55-12-000-003-A).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-862-149-A B.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-16700-A - Bulk Cargo Compartment - Inspection Area - Zones 161-162) Subtask 24-92-00-210-116-A A.

General Visual Inspection of P Routes Installed in Bulk Cargo-Compartment (EWIS) (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-00-0). (a)

(2) 5.

On the AC/DC power distribution route: 1P and 2P.

Make sure that there is no dust or lint contamination.

Close-up Subtask 24-92-00-410-167-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the sidewall panels in the AFT cargo-compartment from FR59 to FR65 (Ref. TASK 25-55-12-400-003-A).

(3)

Close the AFT cargo-compartment door 826 (Ref. TASK 52-30-00-860-002-A) or (Ref. TASK 52-30-00-860-004-A).

(4)

Remove the access platform(s).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 826

A FR65

FR59

INSPECTION AREA Z161−162 N_MM_249200_6_BVM0_01_00

AES

FIGURE 24-92-00-991-16700-A SHEET 1 Bulk Cargo Compartment - Inspection Area - Zones 161-162

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-210-815-A General Visual Inspection of G Routes Installed in Inboard-Fixed-Leading Edge Structure (EWIS) 1.

Reason for the Job (Ref. MPD ---) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION AR ACCESS PLATFORM 3M (10 FT)

Work Zones and Access Panels ZONE/ACCESS

511 611 521AB, 521AT, 521BT, 521CB, 521EB, 521GB, 521HB, 621AB, 621AT, 621BT, 621CB, 621EB, 621GB, 621HB C.

ZONE DESCRIPTION SLAT N˚ 1 SLAT N˚ 1

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

27-80-00-866-004-A

Extending the Slats on the Ground

27-80-00-866-005-A

Retracting the Slats on the Ground

57-41-37-000-004-A Removal of the Pressure-Relief Panels 57-41-37-000-009-A Removal of the Access Panel 57-41-37-000-010-A Removal of the Access Panel 57-41-37-000-011-A Removal of the Access Panel 57-41-37-400-002-A Installation of the Pressure-Relief Panels 57-41-37-400-009-A Installation of the Access Panel 57-41-37-400-010-A Installation of the Access Panel 57-41-37-400-011-A Installation of the Access Panel ESPM 20-52-00-0 (Ref. Fig. 24-92-00-991-16500-A - Access Panels - Wing Upper and Lower Surfaces) 3.

Job Set-up Subtask 24-92-00-866-054-A A.

Aircraft Maintenance Configuration (1)

AES

Extend the slats (Ref. TASK 27-80-00-866-004-A).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-010-167-A B.

Get Access (1)

Put an ACCESS PLATFORM 3M (10 FT) in position at the zone 511 (611).

(2)

Remove the applicable access panels, (Ref. TASK 57-41-37-000-004-A), (Ref. TASK 57-41-37-000-009A), (Ref. TASK 57-41-37-000-010-A) and (Ref. TASK 57-41-37-000-011-A): (a)

For the left wing: . 521AB 521AT 521BT 521CB 521EB 521GB 521HB.

(b)

For the right wing: . 621AB 621AT 621BT 621CB 621EB 621GB 621HB.

Subtask 24-92-00-862-148-A C.

4.

Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-16500-A - Access Panels - Wing Upper and Lower Surfaces) Subtask 24-92-00-210-115-A A.

General Visual Inspection of G Routes Installed in Inboard-Fixed-Leading Edge Structure (EWIS) (1)

Do a visual inspection of the wiring to make sure that there is no signs of ageing, alteration, overheating, scaling and deformation (Ref. ESPM 20-52-00-0). (a)

(2) 5.

On the AC/DC feeders route: 1G and 2G.

Make sure that there is no dust or lint contamination.

Close-up Subtask 24-92-00-410-165-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the applicable access panels, (Ref. TASK 57-41-37-400-002-A), (Ref. TASK 57-41-37-400-009A), (Ref. TASK 57-41-37-400-010-A) and (Ref. TASK 57-41-37-400-011-A):

(3)

(a)

For the left wing: . 521AB 521AT 521BT 521CB 521EB 521GB 521HB.

(b)

For the right wing: . 621AB 621AT 621BT 621CB 621EB 621GB 621HB.

Remove the access platform(s).

Subtask 24-92-00-866-055-A B.

Aircraft Maintenance Configuration (1)

AES

Fully retract the slats (Ref. TASK 27-80-00-866-005-A).

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

B A B A

A

521HB (621HB) 521GB (621GB)

521EB (621EB)

521CB (621CB) 521AB (621AB)

N_MM_249200_6_AXM0_01_00

AES

FIGURE 24-92-00-991-16500-A SHEET 1 Access Panels - Wing Upper and Lower Surfaces

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

B

521AT (621AT) (UNDER SLAT)

521BT (621BT)

N_MM_249200_6_AXM0_02_00

AES

FIGURE 24-92-00-991-16500-A SHEET 2 Access Panels - Wing Upper and Lower Surfaces

24-92-00 PB601

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

ELECTRICAL ROUTING - CLEANING/PAINTING ** On A/C ALL Task 24-92-00-100-001-A Cleaning of EWIS Installed in the Aft Cabin Underfloor Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-01-71-01-) CLEANING OF EWIS INSTALLED IN THE AFT CABIN UNDERFLOOR COMPARTMENT (ONLY IF CONTAMINATED)(EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

171

AFT CABIN U/FLOOR COMPARTMENT

172

AFT CABIN U/FLOOR COMPARTMENT

171AL, 172AR C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-55-12-000-001-A

Removal of the Aft Cargo-Compartment Partition FR65

25-55-12-400-001-A

Installation of the Aft Cargo-Compartment Partition FR65

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-04900-A - Aft Cabin Underfloor Compartment - Access Panels - Zones 171-172) (Ref. Fig. 24-92-00-991-05000-A - Aft Cabin Underfloor Compartment - Cleaning Area - Zones 171-172) 3.

Job Set-up Subtask 24-92-00-010-087-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the access panels: . 172AR 171AL.

(2)

Remove the access panels: . 172AR and 171AL.

(3)

Remove the AFT cargo-compartment partition FR65 (Ref. TASK 25-55-12-000-001-A).

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-862-075-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-04900-A - Aft Cabin Underfloor Compartment - Access Panels - Zones 171-172) (Ref. Fig. 24-92-00-991-05000-A - Aft Cabin Underfloor Compartment - Cleaning Area - Zones 171-172) Subtask 24-92-00-160-050-A A.

Cleaning of All Wiring Installed in the AFT Cabin Underfloor Compartment (Only Contaminated Wiring). (1)

5.

Clean wiring if there is dust or lint contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC power-distribution routes: 1P and 2P.

(b)

On the flight control routes: 7S and 8S.

(c)

On the engine control routes: 1S and 2S APU.

(d)

On other routes: 1M and 2M.

Close-up Subtask 24-92-00-410-085-A A.

AES

Close Access (1)

Install the access panels: . 172AR and 171AL.

(2)

Install the AFT cargo-compartment partition FR65 (Ref. TASK 25-55-12-400-001-A).

(3)

Remove the access platform(s).

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z170

A

A

FR65

FR70

171AL 172AR

N_MM_249200_7_AAM0_01_00

AES

FIGURE 24-92-00-991-04900-A SHEET 1 Aft Cabin Underfloor Compartment - Access Panels - Zones 171-172

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z170

A

A

FR70

FR65 CLEANING AREA ZONES 171−172

N_MM_249200_7_BAM0_01_00

AES

FIGURE 24-92-00-991-05000-A SHEET 1 Aft Cabin Underfloor Compartment - Cleaning Area - Zones 171-172

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-002-A Cleaning of EWIS Installed in the Forward Passenger Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-31-01-) CLEANING OF EWIS INSTALLED IN THE FORWARD PASSENGER COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

231 232 231AW, 231BW, 231CW, 231DW, 231EW, 231FW, 231GW, 231HW, 231JW, 231KW, 231LW, 231MW, 231NW, 231PW, 231QW, 231RW, 231SW, 231TW, 231UW, 231VW, 231WW, 231XW, 231YW, 231ZW, 232AW, 232BW, 232CW, 232DW, 232EW, 232FW, 232GW, 232HW, 232JW, 232KW, 232LW, 232MW, 232NW, 232PW, 232QW, 232RW, 232SW, 232TW, 232UW, 232VW, 232WW, 232XW, 232YW, 232ZW C.

ZONE DESCRIPTION FWD PASSENGER COMPARTMENT FWD PASSENGER COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-21-41-000-001-A

Removal of the Passenger Seats

25-21-41-400-001-A

Installation of the Passenger Seats

25-23-43-000-001-A

Removal of the Upper Sidewall Panel(s)

25-23-43-400-001-A

Installation of the Upper Sidewall Panel(s)

25-23-44-000-001-A

Removal of the Lower Sidewall-Panels (Dado Panels)

25-23-44-400-001-A

Installation of the Lower Sidewall-Panels (Dado Panels)

25-23-45-000-002-A

Removal of the Door Frame Linings at the Right FWD Passenger/Crew Door

25-23-45-000-005-A

Removal of the Door Frame Linings at the Left FWD Passenger/Crew Door

AES

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 25-23-45-400-006-A

DESIGNATION Installation of the Door Frame Linings at the Left FWD Passenger/Crew Door

25-23-45-400-007-A

Installation of the Door Frame Linings at the Right FWD Passenger/Crew Door

25-23-48-000-001-A

Removal of the Cove Light Panels

25-23-48-400-001-A

Installation of the Cove Light Panels

25-27-44-000-002-A

Removal of a Stowage FWD LH (Zone 231)

25-27-44-000-003-A

Removal of a Stowage FWD RH (Zone 232)

25-27-44-400-002-A

Installation of a Stowage FWD LH (Zone 231)

25-27-44-400-003-A

Installation of a Stowage FWD RH (Zone 232)

25-31-41-000-001-A

Removal of the Forward Galley Unit

25-31-41-400-001-A

Installation of the Forward Galley Unit

25-41-41-000-001-A

Removal of the Lavatory A

25-41-41-400-001-A

Installation of the Lavatory A

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-05100-A - Forward Passenger Compartment - Cleaning Area - Zones 231-232) (Ref. Fig. 24-92-00-991-05200-A - Forward Passenger Compartment - Access Panels - Zones 231-232) 3.

Job Set-up Subtask 24-92-00-010-088-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 831 (841).

(2)

Open the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the furnishings in the zones 231 and 232: (a)

Remove the lavatories, if installed (Ref. TASK 25-41-41-000-001-A) and (Ref. AMM 25-41-42-000-001) .

(b)

Remove the stowage, if installed (Ref. TASK 25-27-44-000-002-A) and (Ref. TASK 25-27-44-000-003-A).

(c)

Remove the galleys, if installed (Ref. AMM 25-31-41-000-002) and (Ref. TASK 25-31-41-000-001A).

(d)

Remove the passenger seats, if installed (Ref. TASK 25-21-41-000-001-A).

(4)

Remove the door frame linings at the left and right FWD passenger/crew doors at FR20 (Ref. TASK 25-23-45-000-005-A) and (Ref. TASK 25-23-45-000-002-A).

(5)

Remove the linings and insulation panels in the zones 231 and 232: (a)

Remove the upper sidewall panels (Ref. TASK 25-23-43-000-001-A): . 231BW 231EW 231HW 231LW 231PW 231SW 231VW 231YW, 232BW 232EW 232HW 232LW 232PW 232SW 232VW 232YW.

(b)

Remove the lower sidewall panels (Ref. TASK 25-23-44-000-001-A): . 231AW 231DW 231GW 231KW 231NW 231RW 231UW 231XW, 232AW 232DW 232GW 232KW 232NW 232RW 232UW 232XW.

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (c)

Remove the cove light panels (Ref. TASK 25-23-48-000-001-A): . 231BW 231EW 231HW 231LW 231PW 231SW 232BW 232EW 232HW 232LW 232PW 232SW.

Subtask 24-92-00-862-076-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-05100-A - Forward Passenger Compartment - Cleaning Area - Zones 231-232) (Ref. Fig. 24-92-00-991-05200-A - Forward Passenger Compartment - Access Panels - Zones 231-232) Subtask 24-92-00-160-051-A A.

Cleaning of All Wiring Installed in the Forward Passenger Compartment (Only Contaminated Wiring) (1)

5.

Clean wiring if there is dust or lint contamination (Ref. ESPM 20-55-00-0). (a)

On the flight control wiring: routes 7S, 8S and 7M.

(b)

On the engine control wiring: routes 1S and 2S.

(c)

On the generator excitation wiring: routes 3E and 6E.

(d)

On other wiring: routes 1M and 2M.

(e)

On the coaxial wiring: routes 1T, 3T, 7T, 8T, 9T and 1U.

Close-up Subtask 24-92-00-410-086-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the linings and insulation panels in the zones 231 and 232: (a)

Install the upper sidewall panels (Ref. TASK 25-23-43-400-001-A): . 231BW 231EW 231HW 231LW 231PW 231SW 231VW 231YW, 232BW 232EW 232HW 232LW 232PW 232SW 232VW 232YW.

(b)

Install the lower sidewall panels (Ref. TASK 25-23-44-400-001-A): . 231AW 231DW 231GW 231KW 231NW 231RW 231UW 231XW, 232AW 232DW 232GW 232KW 232NW 232RW 232UW 232XW.

(c)

Install the cove light panels (Ref. TASK 25-23-48-400-001-A): . 231CW 231FW 231JW 231MW 231QW 231TW 231WW 231ZW, 232CW 232FW 232JW 232MW 232QW 232TW 232WW 232ZW.

(3)

Install the door frame linings at the left and right FWD passenger/crew doors at FR20 (Ref. TASK 25-23-45-400-006-A) and (Ref. TASK 25-23-45-400-007-A).

(4)

Install the furnishings in the zones 231 and 232: (a)

Install the lavatories, if removed (Ref. TASK 25-41-41-400-001-A) and (Ref. AMM 25-41-42-400-001) .

(b)

Install the stowage, if removed (Ref. TASK 25-27-44-400-002-A) and (Ref. TASK 25-27-44-400-003-A).

(c)

Install the galleys, if removed (Ref. AMM 25-31-41-400-002) and (Ref. TASK 25-31-41-400-001A).

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (d)

AES

Install the passenger seats, if removed (Ref. TASK 25-21-41-400-001-A).

(5)

Close the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-410-001-A).

(6)

Remove the access platform(s).

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z230

A

A CLEANING AREA Z231− Z232

FR35

FR20

N_MM_249200_7_KAM0_01_00

AES

FIGURE 24-92-00-991-05100-A SHEET 1 Forward Passenger Compartment - Cleaning Area - Zones 231-232

24-92-00 PB701

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

B

A FR20

FR32

FR21

231JW

231FW

FR26

FR28

FR30

FR24

FR34 FR36

A

231ZW

231TW

231WW

231QW

231MW

231CW 231BW

231XW 231YW

231UW

231VW

231RW

231SW

231NW

231PW

231KW

231LW

231GW

231HW

231DW

231EW

231AW

B FR30

FR28

FR26

FR34

FR36

232WW

232ZW

FR32

FR24 FR21 FR20

232FW

232JW

232MW

232QW

232TW

232CW 232BW 232AW

232DW

232GW

232EW

AES

232KW

232HW

232NW

232LW

FIGURE 24-92-00-991-05200-A SHEET 1 Forward Passenger Compartment - Access Panels - Zones 231-232

232RW

232PW

232UW

232SW

232XW

232VW

232YW N_MM_249200_7_LAM0_01_00

24-92-00 PB701

Page 6 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-003-A Cleaning of EWIS installed in the Center Passenger Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-41-01-) CLEANING OF EWIS INSTALLED IN THE CENTER PASSENGER COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

241 242 241AW, 241BW, 241CW, 241DW, 241EW, 241HW, 241JW, 241KW, 241LW, 241MW, 241NW, 241PW, 241QW, 241RW, 241SW, 241TW, 241UW, 241VW, 241WW, 242AW, 242CW, 242DW, 242EW, 242HW, 242JW, 242KW, 242LW, 242MW, 242NW, 242PW, 242QW, 242RW, 242SW, 242TW, 242UW, 242VW, 242WW C.

ZONE DESCRIPTION CENTER PASSENGER COMPARTMENT CENTER PASSENGER COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-21-41-000-001-A

Removal of the Passenger Seats

25-21-41-400-001-A

Installation of the Passenger Seats

25-23-43-000-001-A

Removal of the Upper Sidewall Panel(s)

25-23-43-400-001-A

Installation of the Upper Sidewall Panel(s)

25-23-44-000-001-A

Removal of the Lower Sidewall-Panels (Dado Panels)

25-23-44-400-001-A

Installation of the Lower Sidewall-Panels (Dado Panels)

25-23-47-000-002-A

Removal of the Upper Sidewall Panel Assy 241LW, (242LW), 241CW, (242CW) and 241FW, (242FW)

25-23-47-400-002-A

Installation of the Upper Sidewall Panel Assy 241LW, (242LW), 241CW, (242CW) and 241FW, (242FW)

25-23-48-000-001-A

Removal of the Cove Light Panels

AES

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 25-23-48-400-001-A

DESIGNATION Installation of the Cove Light Panels

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-05600-A - Center Passenger Compartment - Cleaning Area - Zones 241-242) (Ref. Fig. 24-92-00-991-05700-A - Center Passenger Compartment - Access Panels - Zones 241-242) 3.

Job Set-up Subtask 24-92-00-010-094-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the furnishings in the zones 241 and 242:

(4)

(a)

Remove the lavatories, if installed (Ref. AMM 25-42-41-000-001) .

(b)

Remove the passenger seats, if removed (Ref. TASK 25-21-41-000-001-A).

Remove the linings and insulation panels in the zones 241 and 242: (a)

Remove the upper sidewall panel assembly (Ref. TASK 25-23-47-000-002-A): . 241CW 241LW 242CW 242LW.

(b)

Remove the upper sidewall panels (Ref. TASK 25-23-43-000-001-A): . 241PW 241SW 241VW 242PW 242SW 242VW.

(c)

Remove the lower sidewall panels (Ref. TASK 25-23-44-000-001-A): . 241AW 241BW 241EW 241KW 241JW, 241NW 241RW 241UW 242AW 242EW, 242KW 242JW 242NW 242RW 242UW.

(d)

Remove the cove light panels (Ref. TASK 25-23-48-000-001-A): . 241DW 241HW 241MW 241QW 241TW, 241WW 242DW 242HW 242MW 242QW 242TW 242WW.

Subtask 24-92-00-862-082-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-05600-A - Center Passenger Compartment - Cleaning Area - Zones 241-242) (Ref. Fig. 24-92-00-991-05700-A - Center Passenger Compartment - Access Panels - Zones 241-242) Subtask 24-92-00-160-053-A A.

Cleaning of All Wiring Installed in the Center Passenger Compartment (Only Contaminated Wiring) (1)

AES

Clean wiring if there is dust or lint contamination (Ref. ESPM 20-55-00-0). (a)

On routes: 1M and 2M

(b)

Audio and video cables: 1R and 2T

(c)

On coaxial cables: 2U

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-92-00-410-092-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the linings and insulation panels in the zones 241 and 242:

(3)

AES

(a)

Install the upper sidewall panel assembly (Ref. TASK 25-23-47-400-002-A): . 241CW 241LW 242CW 242LW.

(b)

Install the upper sidewall panels (Ref. TASK 25-23-43-400-001-A): . 241PW 241SW 241VW 242PW 242SW, 242VW.

(c)

Install the lower sidewall panels (Ref. TASK 25-23-44-400-001-A): . 241AW 241BW 241EW 241KW 241JW, 241NW 241RW 241UW 242AW 242EW, 242KW 242JW 242NW 242RW 242UW.

(d)

Install the cove light panels (Ref. TASK 25-23-48-400-001-A): . 241DW 241HW 241MW 241QW 241TW, 241WW 242DW 242HW 242MW 242QW 242TW 242WW.

Install the furnishings in the zones 241 and 242: (a)

Install the lavatories, if removed (Ref. AMM 25-42-41-400-001) .

(b)

Install the passenger seats, if removed (Ref. TASK 25-21-41-400-001-A).

(4)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(5)

Remove the access platform(s).

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z240

A

A

FR47

FR35

CLEANING AREA Z241− Z242

N_MM_249200_7_QAM0_01_00

AES

FIGURE 24-92-00-991-05600-A SHEET 1 Center Passenger Compartment - Cleaning Area - Zones 241-242

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A A FR38

FR36

FR39

B

FR45

FR47

D

241WW

FR43

241TW

241QW 241MW 241DW 241HW

FR36

FR37 FR39

FR41

FR38

FR40

FR41

D

241VW 241UW

241SW

241RW

241PW

241NW

241KW 241BW

241JW 241EW 241AW

B FR47 FR45 241LW

241CW

FR43 FR42 FR41

C

FR39 FR36

FR37 FR36 242CW

FR38

FR38

FR41

FR39

242DW

FR40

242HW 242MW 242QW

242TW

242WW

242LW

C 242KW 242AW 242EW

242JW 242PW 242SW 242VW 242NW 242RW 242UW N_MM_249200_7_RAM0_01_00

AES

FIGURE 24-92-00-991-05700-A SHEET 1 Center Passenger Compartment - Access Panels - Zones 241-242

24-92-00 PB701

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-004-A Cleaning of EWIS Installed in the Forward Avionic Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-01-21-01-) CLEANING OF EWIS INSTALLED IN THE FORWARD AVIONIC COMPARTMENT (ONLY IF CONTAMINATED)(EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

121 122 121AF, 121AL, 121BF, 121CF, 122BF, 811 C.

ZONE DESCRIPTION AVIONICS COMPARTMENT AVIONICS COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

53-12-13-000-001-A 53-12-13-400-001-A

Removal of the avionics compartment floor panels Installation of the avionics compartment floor panels

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-05400-A - Forward Avionic Compartment - Access) (Ref. Fig. 24-92-00-991-11700-A - Forward Avionic Compartment - Cleaning Area - Zones 121-122) 3.

Job Set-up Subtask 24-92-00-010-092-A A.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the access doors 121AL 811.

(3)

Remove the forward avionic-compartment floor-panels 121AF 121BF 121CF 122BF (Ref. TASK 53-12-13-000-001-A).

Subtask 24-92-00-862-080-A B.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-92-00-991-05400-A - Forward Avionic Compartment - Access) (Ref. Fig. 24-92-00-991-11700-A - Forward Avionic Compartment - Cleaning Area - Zones 121-122) Subtask 24-92-00-160-052-A A.

Cleaning of All Wiring Installed in the Forward Avionic Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust, lint or hydraulic contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 4G, 5G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 6P.

(c)

On the flight control wiring.

(d)

On the engine control routes: 1S and 2S.

(e)

On the other routes: 1M and 2M.

(f)

On the audio route: 1R.

(g)

On the coaxial cable routes: 4T, 3U and 4U.

(h)

On the generator excitation routes: 1E, 2E and 3E.

Close-up Subtask 24-92-00-410-090-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the forward avionics-compartment floor-panels 121AF 121BF 121CF 122BF (Ref. TASK 53-12-13-400-001-A).

(3)

Close the access doors 121AL 811.

(4)

Remove the access platform(s).

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

B A

FR12 FR6 FR1

A

811 121AL

B

FR1

FR7 FR3 FR5

FR2

122BF

121AF

121CF

121BF

N_MM_249200_7_ALM0_01_00

AES

FIGURE 24-92-00-991-05400-A SHEET 1 Forward Avionic Compartment - Access

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A Z120

A

CLEANING AREA Z121−122

FR24 FR20

FR9 FR1

N_MM_249200_7_JLM0_01_00

AES

FIGURE 24-92-00-991-11700-A SHEET 1 Forward Avionic Compartment - Cleaning Area - Zones 121-122

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-005-A Cleaning of EWIS Installed in the Forward Passenger Overhead Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-33-01-) CLEANING OF EWIS INSTALLED IN THE FORWARD PASSENGER COMPARTMENT OVERHEAD COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

233 234 231AC, 231BC, 231CC, 231DC, 231EC, 231FC, 231GC, 231HC, 232AC C.

ZONE DESCRIPTION FWD PASSENGER COMPT OVERHEAD COMPARTMENT FWD PASSENGER COMPT OVERHEAD COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-41-000-001-A

Removal of the Ceiling Panels

25-23-41-400-001-A

Installation of the Ceiling Panels

25-24-41-000-001-A

Removal of the Overhead Stowage Compartments

25-24-41-400-001-A

Installation of the Overhead Stowage Compartments

25-27-44-000-002-A

Removal of a Stowage FWD LH (Zone 231)

25-27-44-000-003-A

Removal of a Stowage FWD RH (Zone 232)

25-27-44-400-002-A

Installation of a Stowage FWD LH (Zone 231)

25-27-44-400-003-A

Installation of a Stowage FWD RH (Zone 232)

25-31-41-000-001-A

Removal of the Forward Galley Unit

25-31-41-400-001-A

Installation of the Forward Galley Unit

25-41-41-000-001-A

Removal of the Lavatory A

25-41-41-400-001-A

Installation of the Lavatory A

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-05900-A - Forward Passenger Overhead Compartment - Cleaning - Zones 233-234)

AES

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE DESIGNATION (Ref. Fig. 24-92-00-991-06000-A - Forward Passenger Overhead-Compartment - Access Panels - Zones 231-232) 3.

Job Set-up Subtask 24-92-00-010-096-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 831 (841).

(2)

Open the passenger/crew door 831 (841) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the furnishings in the zones 231 and 232: (a)

Remove the lavatories, if installed (Ref. TASK 25-41-41-000-001-A) and (Ref. AMM 25-41-42-000-001) .

(b)

Remove the stowage, if installed (Ref. TASK 25-27-44-000-002-A) and (Ref. TASK 25-27-44-000-003-A).

(c)

Remove the galleys, if installed (Ref. AMM 25-31-41-000-002) and (Ref. TASK 25-31-41-000-001A).

(4)

Remove the overhead stowage compartments between FR20 and FR35 (Ref. TASK 25-24-41-000-001A).

(5)

Remove the ceiling panels in the zones 233 and 234 (Ref. TASK 25-23-41-000-001-A): . 231AC 232AC 231BC 231CC 231DC 231EC 231FC 231GC 231HC.

Subtask 24-92-00-862-084-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-05900-A - Forward Passenger Overhead Compartment - Cleaning - Zones 233-234) (Ref. Fig. 24-92-00-991-06000-A - Forward Passenger Overhead-Compartment - Access Panels - Zones 231-232) Subtask 24-92-00-160-054-A A.

Cleaning of All Wiring Installed in the Forward Passenger Overhead Compartment (Only Contaminated Wiring) (1)

AES

Clean the wiring if there is dust contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 3G and 6G.

(b)

On the AC/DC power- distribution routes: 1P, 2P and 3P.

(c)

On the flight control routes: 7M and 7S.

(d)

On the engine control route: 1S.

(e)

On other routes: 1M and 2M.

(f)

On the coaxial routes: 1T, 3T, 8T, 9T and 1U.

(g)

On the generator excitation route: 6E.

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-92-00-410-094-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the ceiling panels in the zones 233 and 234 (Ref. TASK 25-23-41-400-001-A): . 231AC 232AC 231BC 231CC 231DC 231EC 231FC 231GC 231HC.

(3)

Install the overhead stowage compartments between FR20 and FR35 (Ref. TASK 25-24-41-400-001-A).

(4)

Install the furnishings in the zones 231 and 232: (a)

Install the lavatories, if removed (Ref. TASK 25-41-41-400-001-A) and (Ref. AMM 25-41-42-400-001) .

(b)

Install the stowage, if removed (Ref. TASK 25-27-44-400-002-A) and (Ref. TASK 25-27-44-400-003-A).

(c)

Install the galleys, if removed (Ref. AMM 25-31-41-400-002) and (Ref. TASK 25-31-41-400-001A).

(5)

Close the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-410-001-A).

(6)

Remove the access platform(s).

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z230

A

A CLEANING AREA Z233− Z234

FR35

FR20

N_MM_249200_7_EBM0_01_00

AES

FIGURE 24-92-00-991-05900-A SHEET 1 Forward Passenger Overhead Compartment - Cleaning Zones 233-234

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FR20

FR36

FR34

FR32

FR30

FR28

FR26

FR24

FR21

231AC AD 232AC

231HC

231GC

231FC

231EC

231DC

231CC

231BC

N_MM_249200_7_EAM0_01_00

AES

FIGURE 24-92-00-991-06000-A SHEET 1 Forward Passenger Overhead-Compartment - Access Panels - Zones 231-232

24-92-00 PB701

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-007-A Cleaning of EWIS Installed in the Forward Cabin Utility-Area (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-21-01-) CLEANING OF EWIS INSTALLED IN THE FORWARD CABIN UTILITY AREA (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

221 222

ZONE DESCRIPTION FWD CAB UTILITY AREA FWD CAB UTILITY AREA

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-45-000-002-A

Removal of the Door Frame Linings at the Right FWD Passenger/Crew Door

25-23-45-000-005-A

Removal of the Door Frame Linings at the Left FWD Passenger/Crew Door

25-23-45-400-006-A

Installation of the Door Frame Linings at the Left FWD Passenger/Crew Door

25-23-45-400-007-A

Installation of the Door Frame Linings at the Right FWD Passenger/Crew Door

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

53-12-12-000-001-A Removal of the Cabin Floor Panels from FR12 thru FR24 53-12-12-400-001-A Installation of the Cabin Floor Panels from FR12 thru FR24 ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-06500-A - Forward Cabin Utility-Area - Cleaning Area - Zones 221-222) (Ref. Fig. 24-92-00-991-06600-B - Forward Cabin Utility-Area - Access Panels - Zones 221-222) 3.

Job Set-up Subtask 24-92-00-010-100-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 831 (841).

(2)

Open the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the door frame linings at the left and right FWD passenger/crew door (Ref. TASK 25-23-45-000-005-A) and (Ref. TASK 25-23-45-000-002-A).

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Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

Remove the cabin floor panels from FR12 to FR20 (Ref. TASK 53-12-12-000-001-A).

Subtask 24-92-00-862-088-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-06500-A - Forward Cabin Utility-Area - Cleaning Area - Zones 221-222) (Ref. Fig. 24-92-00-991-06600-B - Forward Cabin Utility-Area - Access Panels - Zones 221-222) Subtask 24-92-00-160-056-A A.

Cleaning of All Wiring Installed in the Forward Cabin Utility-Area (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust or lint contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC power-distribution route: 1P.

(b)

On other routes: 2M and 1R.

Close-up Subtask 24-92-00-410-098-A A.

AES

Close Access (1)

Install the cabin floor panels from FR12 to FR20 (Ref. TASK 53-12-12-400-001-A).

(2)

Install the door frame linings at the left and right FWD passenger/crew door (Ref. TASK 25-23-45-400-006-A) and (Ref. TASK 25-23-45-400-007-A).

(3)

Close the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-410-001-A).

(4)

Remove the access platform(s).

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z220

CLEANING AREA ZONES 221−222

FR20

FR12

N_MM_249200_7_VAM0_01_00

AES

FIGURE 24-92-00-991-06500-A SHEET 1 Forward Cabin Utility-Area - Cleaning Area - Zones 221-222

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR16

A C

221VW

FR20

221SW

A

221FW 221EW

B

FR16

221BW 221RW

221SW FR20

B 221CW 221AW

221VW

221RW

N_MM_249200_7_XAM0_01_00

AES

FIGURE 24-92-00-991-06600-B SHEET 1 Forward Cabin Utility-Area - Access Panels - Zones 221-222

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR16

C

222VW

FR20

222SW

222UW

D

FR16

D

222SW FR20 222RW 222TW

222VW

222RW

N_MM_249200_7_XAM0_02_00

AES

FIGURE 24-92-00-991-06600-B SHEET 2 Forward Cabin Utility-Area - Access Panels - Zones 221-222

24-92-00 PB701

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-009-A Cleaning of EWIS Installed in the Center Passenger Overhead-Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-43-01-) CLEANING OF EWIS INSTALLED IN THE CENTER PASSENGER OVERHEAD COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

Work Zones and Access Panels ZONE/ACCESS

243 244 241AC, 241BC, 241CC, 241DC, 241EC, 241FC C.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

ZONE DESCRIPTION CENTER PASSENGER COMPT OVERHEAD COMPT CENTER PASSENGER COMPT OVERHEAD COMPT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-41-000-001-A

Removal of the Ceiling Panels

25-23-41-400-001-A

Installation of the Ceiling Panels

25-24-41-000-001-A

Removal of the Overhead Stowage Compartments

25-24-41-400-001-A

Installation of the Overhead Stowage Compartments

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-06900-A - Center Passenger Overhead-Compartment - Cleaning Area - Zones 243-244) (Ref. Fig. 24-92-00-991-07000-A - Center Passenger Overhead-Compartment - Access Panels - Zones 243-244) 3.

Job Set-up Subtask 24-92-00-010-102-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

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Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the furnishings in the zones 241 and 242: (a)

Remove the lavatories, if installed (Ref. AMM 25-42-41-000-001) .

(4)

Remove the overhead stowage compartments between FR35 and FR47 (Ref. TASK 25-24-41-000-001A).

(5)

Remove the ceiling panels in the zones 243 and 244 (Ref. TASK 25-23-41-000-001-A): . 241AC 241BC 241CC 241DC 241EC 241FC.

Subtask 24-92-00-862-090-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-06900-A - Center Passenger Overhead-Compartment - Cleaning Area - Zones 243-244) (Ref. Fig. 24-92-00-991-07000-A - Center Passenger Overhead-Compartment - Access Panels - Zones 243-244) Subtask 24-92-00-160-058-A A.

Cleaning of All Wiring Installed in the Center Passenger Overhead-Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 3G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 3P.

(c)

On the engine control routes: 1S, 2S and 6S.

(d)

On other routes: 1M and 2M.

(e)

On the coaxial wiring route: 1U.

(f)

On the generator excitation routes: 6E and 3E.

(g)

On the audio or video routes: 7T, 8T and 9T.

Close-up Subtask 24-92-00-410-100-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the ceiling panels in the zones 243 and 244 (Ref. TASK 25-23-41-400-001-A): . 241AC 241BC 241CC 241DC 241EC 241FC.

(3)

Install the overhead stowage compartments between FR35 and FR47 (Ref. TASK 25-24-41-400-001-A).

(4)

Install the furnishings in the zones 241 and 242: (a)

AES

Install the lavatories, if removed (Ref. AMM 25-42-41-400-001) .

(5)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(6)

Remove the access platform(s).

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z240

A

A

CLEANING AREA Z243− Z244

FR47

FR35

N_MM_249200_7_YAM0_01_00

AES

FIGURE 24-92-00-991-06900-A SHEET 1 Center Passenger Overhead-Compartment - Cleaning Area Zones 243-244

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FR38 FR43 FR47

FR41

FR36

FR39

FR45

AD

241BC 241FC

241EC

241DC 241CC

241AC

N_MM_249200_7_ZAM0_01_00

AES

FIGURE 24-92-00-991-07000-A SHEET 1 Center Passenger Overhead-Compartment - Access Panels Zones 243-244

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-010-A Cleaning of EWIS Installed in the Forward Cabin Overhead-Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-23-01-) CLEANING OF EWIS INSTALLED IN THE FORWARD CABIN OVERHEAD COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

223 224 221AC, 221BC, 222BC C.

ZONE DESCRIPTION FWD CAB OVERHEAD COMPARTMENT FWD CAB OVERHEAD COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-42-000-001-A

Removal of the Ceiling Panels - Forward Utility Area

25-23-42-400-001-A

Installation of the Ceiling Panels - Forward Utility Area

25-31-41-000-001-A

Removal of the Forward Galley Unit

25-31-41-400-001-A

Installation of the Forward Galley Unit

25-41-41-000-001-A

Removal of the Lavatory A

25-41-41-400-001-A

Installation of the Lavatory A

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-07300-A - Forward Cabin Overhead-Compartment - Cleaning Area - Zones 223-224) (Ref. Fig. 24-92-00-991-11100-A - Forward Cabin Overhead-Compartment - Access Panels - Zones 223-224) 3.

Job Set-up Subtask 24-92-00-010-103-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 831 (841).

(2)

Open the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-010-001-A).

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Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the ceiling panels in the forward utility area (Ref. TASK 25-23-42-000-001-A): . 221AC 221BC 222BC.

(4)

Remove the lavatory A (Ref. TASK 25-41-41-000-001-A) or stowage (Ref. AMM 25-27-44-000-001) if installed.

(5)

Remove the forward galley unit (6475MM) (Ref. TASK 25-31-41-000-001-A) or (Ref. AMM 25-31-42-000-001) if installed.

Subtask 24-92-00-862-091-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-07300-A - Forward Cabin Overhead-Compartment - Cleaning Area - Zones 223-224) (Ref. Fig. 24-92-00-991-11100-A - Forward Cabin Overhead-Compartment - Access Panels - Zones 223-224) Subtask 24-92-00-160-059-A A.

Cleaning of All Wiring Installed in the Forward Cabin Overhead-Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 3G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 3P.

(c)

On the generator excitation routes: 3E and 6E.

(d)

On other routes: 1M and 2M.

Close-up Subtask 24-92-00-410-101-A A.

AES

Close Access (1)

Install the ceiling panels in the forward utility area (Ref. TASK 25-23-42-400-001-A). . 221AC 221BC 222BC.

(2)

Install the forward galley unit (6475MM) (Ref. TASK 25-31-41-400-001-A) or (Ref. AMM 25-31-42-400-001) if removed.

(3)

Install the lavatory A (Ref. TASK 25-41-41-400-001-A) or stowage (Ref. AMM 25-27-44-400-001) if removed.

(4)

Close the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-410-001-A).

(5)

Remove the access platform(s).

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

CLEANING AREA ZONES 223−224

Z220

A

FR20

FR12

N_MM_249200_7_PAM0_01_00

AES

FIGURE 24-92-00-991-07300-A SHEET 1 Forward Cabin Overhead-Compartment - Cleaning Area Zones 223-224

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FR14 FR16 FR20 FR21

221BC 221AC

AD

222BC

N_MM_249200_7_PAN0_01_00

AES

FIGURE 24-92-00-991-11100-A SHEET 1 Forward Cabin Overhead-Compartment - Access Panels Zones 223-224

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-013-A Cleaning of EWIS Installed in the Rear Avionic Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-01-27-02-) CLEANING OF EWIS INSTALLED IN THE REAR AVIONIC COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

127 128 127BF, 127BG, 127CF, 127DF, 128CF, 128EG, 131AW, 131BW, 131CW, 131DW, 132BW, 132EW, 824, 825 C.

ZONE DESCRIPTION REAR AVIONIC COMPARTMENT REAR AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-54-11-000-001-A

Removal of the Forward Cargo-Compartment Partition FR24

25-54-11-400-001-A

Installation of the Forward Cargo-Compartment Partition FR24

52-30-00-860-001-A

52-30-00-860-003-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

53-12-13-000-001-A 53-12-13-400-001-A

Removal of the avionics compartment floor panels Installation of the avionics compartment floor panels

52-30-00-860-002-A

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-07800-E - Rear Avionic Compartment - Access)

AES

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-92-00-010-108-E A.

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the access door 824.

(3)

Open the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-001-A) or (Ref. TASK 52-30-00-860-003-A).

(4)

Remove the aft avionic-compartment floor-panels 127BG 127BF 127CF 127DF 128CF 128EG (Ref. TASK 53-12-13-000-001-A).

(5)

Remove the FWD cargo-compartment partition-panels 131AW 131BW 131CW 131DW 132BW 132EW (Ref. TASK 25-54-11-000-001-A).

Subtask 24-92-00-862-096-B B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-07800-E - Rear Avionic Compartment - Access) Subtask 24-92-00-160-062-B A.

Cleaning of All Wiring Installed in the Rear Avionic Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust, lint or hydraulic contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 1G and 2G.

(b)

On the AC/DC power-distribution routes: 1P and 2P.

(c)

On the flight control wiring.

(d)

On the engine control routes: 1S and 2S.

(e)

On the other routes: 1M and 2M.

(f)

On the audio route: 1R.

(g)

On the coaxial wiring routes: 3T and 4T.

(h)

On the generator excitation routes: 1E and 2E.

Close-up Subtask 24-92-00-410-106-E A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the aft avionic-compartment floor-panels 127BG 127BF 127CF 127DF 128CF 128EG (Ref. TASK 53-12-13-400-001-A).

(3)

Install the FWD cargo-compartment partition-panels 131AW 131BW 131CW 131DW 132BW 132EW (Ref. TASK 25-54-11-400-001-A).

(4)

Close the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-002-A) or (Ref. TASK 52-30-00-860-004-A).

(5)

Close the access door 824.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (6)

AES

Remove the access platform(s).

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 825

B A

824

B

FR21 127BG

127CF

FR23

127BF

128CF

128EG

127DF

FR24

C C PARTITION FR24.A 131BW

131AW

132BW

131DW

131CW

132EW

N_MM_249200_7_GLM0_01_00

AES

FIGURE 24-92-00-991-07800-E SHEET 1 Rear Avionic Compartment - Access

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-015-A Cleaning of EWIS Installed in the Zone Under Cabin Floor (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-01-45-01-) CLEANING OF EWIS INSTALLED IN THE ZONE UNDER CABIN FLOOR (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

145 146

ZONE DESCRIPTION PRESS ZONE BETW WING CTR BOX MAIN GEAR PRESS ZONE BETW WING CTR BOX MAIN GEAR

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

53-32-12-000-002-A Removal of the Cabin Floor Panels 53-32-12-400-002-A Installation of the Cabin Floor Panels ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-08700-A - Zone Under Cabin Floor - Cleaning Area - Zones 145-146) 3.

Job Set-up Subtask 24-92-00-010-116-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

(2)

Open the aft passenger/crew doors 832 (842) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the cabin floor panels from FR36 to FR46 (Ref. TASK 53-32-12-000-002-A).

Subtask 24-92-00-862-104-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-08700-A - Zone Under Cabin Floor - Cleaning Area - Zones 145-146)

AES

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-160-064-A A.

Cleaning of All Wiring Installed in the Zone Under Cabin Floor (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust, lint or hydraulic contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC power-distribution route: 1P.

(b)

On the engine control routes: 1S and 2S.

(c)

On the other routes: 1M and 2M.

Close-up Subtask 24-92-00-410-114-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the cabin floor panels from FR36 to FR46 (Ref. TASK 53-32-12-400-002-A).

(3)

Close the aft passenger/crew doors 832 (842) (Ref. TASK 52-10-00-410-001-A).

(4)

Remove the access platform(s).

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

842

A Z140 832

A CLEANING AREA Z145−146 FR46

FR36

N_MM_249200_7_QLM0_01_00

AES

FIGURE 24-92-00-991-08700-A SHEET 1 Zone Under Cabin Floor - Cleaning Area - Zones 145-146

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-016-A Cleaning of EWIS Installed in the Cockpit (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-11-01-) CLEANING OF EWIS INSTALLED IN THE COCKPIT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

211 212 211BC, 211FC, 211HC, 212BC, 212FC, 212KW C.

ZONE DESCRIPTION COCKPIT COCKPIT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-13-41-000-001-A

Removal of the Ceiling Panels

25-13-41-400-001-A

Installation of the Ceiling Panels

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-08800-A - Cockpit - Sidewall Panels and Ceiling Panels - Zones 211-212) (Ref. Fig. 24-92-00-991-13000-A - Cockpit - Cleaning Area - Zones 211-212) 3.

Job Set-up Subtask 24-92-00-010-117-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

(2)

Open the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the cockpit ceiling panels 211BC 211FC 211HC 212BC 212FC 212KW (Ref. TASK 25-13-41-000-001-A).

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL Subtask 24-92-00-862-105-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-08800-A - Cockpit - Sidewall Panels and Ceiling Panels - Zones 211-212) (Ref. Fig. 24-92-00-991-13000-A - Cockpit - Cleaning Area - Zones 211-212) Subtask 24-92-00-160-065-A A.

Cleaning of All Wiring Installed in the Cockpit (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust or lint contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 1G, 3G and 4G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 6P.

(c)

On the flight control wiring.

(d)

On the engine control routes: 1S and 2S.

(e)

On the other routes: 1M and 2M.

(f)

On the audio route: 1R.

(g)

On the generator excitation routes: 1E, 2E and 3E.

Close-up Subtask 24-92-00-410-115-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the cockpit ceiling panels 211BC 211FC 211HC 212BC 212FC 212KW (Ref. TASK 25-13-41-400-001-A).

(3)

Close the forward passenger/crew door 831 (Ref. TASK 52-10-00-410-001-A).

(4)

Remove the access platform(s).

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL FR24A

841

Z210

A

831

FR1

A 211BC

211FC

211HC

212BC 212FC

212KW

N_MM_249200_7_NLM0_01_00

AES

FIGURE 24-92-00-991-08800-A SHEET 1 Cockpit - Sidewall Panels and Ceiling Panels - Zones 211-212

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z210

A

A FR24A

CLEANING AREA ZONE 211−212 FR1

N_MM_249200_7_MLM0_01_00

AES

FIGURE 24-92-00-991-13000-A SHEET 1 Cockpit - Cleaning Area - Zones 211-212

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-017-A Cleaning of EWIS Installed in 49VU and 120VU (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-11-02-) CLEANING OF EWIS INSTALLED IN 49VU AND 120VU (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

211 212

ZONE DESCRIPTION COCKPIT COCKPIT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-08900-A - 49VU and 120VU - Location) 3.

Job Set-up Subtask 24-92-00-862-106-A A.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Subtask 24-92-00-010-118-A B.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

(2)

Open the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-010-001-A).

(3)

Open the overhead circuit-breaker panel 49VU.

(4)

On . . . .

the rear panel 120VU, open: The rear circuit-breaker panel 121VU The rear circuit-breaker panel 122VU The AC power center 123VU The AC power center 124VU

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Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL . 4.

The rear circuit-breaker panel 125VU.

Procedure (Ref. Fig. 24-92-00-991-08900-A - 49VU and 120VU - Location) Subtask 24-92-00-160-066-A A.

Cleaning of All Wiring Installed in 49VU and 120VU (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust or lint contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 1G, 3G and 4G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 6P.

(c)

On the flight control wiring.

(d)

On the engine control routes: 1S and 2S.

(e)

On the other routes: 1M and 2M.

(f)

On the audio route: 1R.

(g)

On the generator excitation routes: 1E, 2E and 3E.

Close-up Subtask 24-92-00-410-116-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

On . . . . .

(3)

Close the overhead circuit-breaker panel 49VU.

(4)

Close the forward passenger/crew door 831 (841) (Ref. TASK 52-10-00-410-001-A).

(5)

Remove the access platform(s).

the rear panel 120VU, close: The rear circuit-breaker panel 121VU The rear circuit-breaker panel 122VU The AC power center 123VU The AC power center 124VU The rear circuit-breaker panel 125VU.

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

841

FR24A

B A 831

CLEANING AREA Z211−212

FR1

A 49VU

B 120VU

N_MM_249200_7_LLM0_01_00

AES

FIGURE 24-92-00-991-08900-A SHEET 1 49VU and 120VU - Location

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-019-A Cleaning of EWIS Installed in the Aft Passenger Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-51-02-) CLEANING OF EWIS INSTALLED IN THE AFT PASSENGER COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

251 252 251AW, 251AX, 251BW, 251BX, 251CW, 251CX, 251DW, 251EW, 251FW, 251GW, 251HW, 251JW, 251KW, 251LW, 251MW, 251NW, 251PW, 251QW, 251RW, 251SW, 251TW, 251UW, 251VW, 251WW, 251XW, 251YW, 251ZW, 252AW, 252AX, 252BW, 252BX, 252CW, 252CX, 252DW, 252EW, 252FW, 252GW, 252HW, 252JW, 252KW, 252LW, 252MW, 252NW, 252PW, 252QW, 252RW, 252SW, 252TW, 252UW, 252VW, 252WW, 252XW, 252YW, 252ZW C.

ZONE DESCRIPTION AFT PASSENGER COMPARTMENT AFT PASSENGER COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-21-41-000-001-A

Removal of the Passenger Seats

25-21-41-400-001-A

Installation of the Passenger Seats

25-23-43-000-001-A

Removal of the Upper Sidewall Panel(s)

25-23-43-400-001-A

Installation of the Upper Sidewall Panel(s)

25-23-44-000-001-A

Removal of the Lower Sidewall-Panels (Dado Panels)

25-23-44-400-001-A

Installation of the Lower Sidewall-Panels (Dado Panels)

25-23-48-000-001-A

Removal of the Cove Light Panels

AES

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE 25-23-48-400-001-A

DESIGNATION Installation of the Cove Light Panels

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-09600-A - Aft Passenger Compartment - Cleaning Area - Zones 251-252) (Ref. Fig. 24-92-00-991-09700-A - Aft Passenger Compartment - Access Panels - Zones 251-252) 3.

Job Set-up Subtask 24-92-00-010-122-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the furnishings in the zones 251 and 252:

(4)

(a)

Remove the lavatories, if installed (Ref. AMM 25-42-41-000-001) .

(b)

Remove the passenger seats, if installed (Ref. TASK 25-21-41-000-001-A).

Remove the linings and insulation panels in the zones 251 and 252: (a)

Remove the upper sidewall panels (Ref. TASK 25-23-43-000-001-A): . 251BW 251EW 251HW 251LW 251PW 251SW 251VW 251YW 251BX, 252BW 252EW 252HW 252LW 252PW 252SW 252VW 252YW 252BX.

(b)

Remove the lower sidewall panels (Ref. TASK 25-23-44-000-001-A): . 251AW 251DW 251GW 251KW 251NW 251RW 251UW 251XW 251AX, 252AW 252DW 252GW 252KW 252NW 252RW 252UW 252XW 252AX.

(c)

Remove the cove light panels (Ref. TASK 25-23-48-000-001-A): . 251CW 251FW 251JW 251MW 251QW 251TW 251WW 251ZW 251CX, 252CW 252FW 252JW 252MW 252QW 252TW 252WW 252ZW 252CX.

Subtask 24-92-00-862-110-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-09600-A - Aft Passenger Compartment - Cleaning Area - Zones 251-252) (Ref. Fig. 24-92-00-991-09700-A - Aft Passenger Compartment - Access Panels - Zones 251-252) Subtask 24-92-00-160-068-A A.

Cleaning of All Wiring Installed in the Aft Passenger Compartment (Only Contaminated Wiring) (1)

AES

Clean the wiring if there is dust or lint contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC power-distribution route: 2P.

(b)

On the engine control route: 1S.

(c)

On other routes: 1M, 2M and 8M.

(d)

On the audio and video route: 1R.

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-92-00-410-120-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the linings and insulation panels in the zones 251 and 252:

(3)

AES

(a)

Install the upper sidewall panels (Ref. TASK 25-23-43-400-001-A): . 251BW 251EW 251HW 251LW 251PW 251SW 251VW 251YW 251BX, 252BW 252EW 252HW 252LW 252PW 252SW 252VW 252YW 252BX.

(b)

Install the lower sidewall panels (Ref. TASK 25-23-44-400-001-A): . 251AW 251DW 251GW 251KW 251NW 251RW 251UW 251XW 251AX, 252AW 252DW 252GW 252KW 252NW 252RW 252UW 252XW 252AX.

(c)

Install the cove light panels (Ref. TASK 25-23-48-400-001-A): . 251CW 251FW 251JW 251MW 251QW 251TW 251WW 251ZW 251CX, 252CW 252FW 252JW 252MW 252QW 252TW 252WW 252ZW 252CX.

Install the furnishings in the zones 251 and 252: (a)

Install the lavatories, if removed (Ref. AMM 25-42-41-400-001) .

(b)

Install the passenger seats, if removed (Ref. TASK 25-21-41-400-001-A).

(4)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(5)

Remove the access platform(s).

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z250

A

A

CLEANING AREA Z251−252

FR64

FR47

N_MM_249200_7_ACM0_01_00

AES

FIGURE 24-92-00-991-09600-A SHEET 1 Aft Passenger Compartment - Cleaning Area - Zones 251-252

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

B

A

A

FR65

FR61

FR63

251CX

251ZW

251AX

251WW

251XW

251BX 251YW

251TW

251UW

251VW

FR55

FR57

FR59

251QW 251MW

251RW

251SW

251NW

251PW

251JW

251KW

251LW

FR47

FR49

FR51

FR53

251FW

251GW

251HW

251CW

251DW

251EW

251AW

251BW

B

FR47

FR49

FR51

FR53

FR55

FR57

FR59

FR61

FR63

252CW

252FW

252JW

252MW

252QW

252TW

252WW

252ZW

252CX

252AW 252BW

252DW

252EW

252GW

252HW

252KW

252LW

252NW

252PW

252RW

252SW

252UW

252VW

252XW

252YW

FR65

252BX

252AX N_MM_249200_7_ADM0_01_00

AES

FIGURE 24-92-00-991-09700-A SHEET 1 Aft Passenger Compartment - Access Panels - Zones 251-252

24-92-00 PB701

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-021-A Cleaning of EWIS Installed in the Aft Passenger Overhead-Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-53-01-) CLEANING OF EWIS INSTALLED IN THE AFT PASSENGER OVERHEAD COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

253 AFT PASSENGER COMPARTMENT OVERHEAD COMPT 254 AFT PASSENGER COMPARTMENT OVERHEAD COMPT 251AC, 251BC, 251CC, 251DC, 251EC, 251FC, 251GC, 251HC, 251JC C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-41-000-001-A

Removal of the Ceiling Panels

25-23-41-400-001-A

Installation of the Ceiling Panels

25-24-41-000-001-A

Removal of the Overhead Stowage Compartments

25-24-41-400-001-A

Installation of the Overhead Stowage Compartments

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-10200-A - Aft Passenger Overhead-Compartment - Cleaning Area - Zones 253-254) (Ref. Fig. 24-92-00-991-10300-A - Aft Passenger Overhead-Compartment - Access Panels - Zones 253-254) 3.

Job Set-up Subtask 24-92-00-010-125-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the furnishings in the zones 251 and 252: (a)

Remove the lavatories, if installed (Ref. AMM 25-42-41-000-001) .

(4)

Remove the overhead stowage compartments between FR47 and FR64 (Ref. TASK 25-24-41-000-001A).

(5)

Remove the ceiling panels in the zones 253 and 254 (Ref. TASK 25-23-41-000-001-A): . 251AC 251BC 251CC 251DC 251EC 251FC 251GC 251HC 251JC.

Subtask 24-92-00-862-113-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-10200-A - Aft Passenger Overhead-Compartment - Cleaning Area - Zones 253-254) (Ref. Fig. 24-92-00-991-10300-A - Aft Passenger Overhead-Compartment - Access Panels - Zones 253-254) Subtask 24-92-00-160-069-A A.

Cleaning of All Wiring Installed in the Aft Passenger Overhead-Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 3G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 3P.

(c)

On the engine control route: 1S.

(d)

On other routes: 1M, 2M and 3M.

(e)

On the excitation wiring routes: 6E and 3E.

(f)

On the audio or video route: 1R.

Close-up Subtask 24-92-00-410-123-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the ceiling panels in the zones 253 and 254 (Ref. TASK 25-23-41-400-001-A): . 251AC 251BC 251CC 251DC 251EC 251FC 251GC 251HC 251JC.

(3)

Install the overhead stowage compartments between FR47 and FR64 (Ref. TASK 25-24-41-400-001-A).

(4)

Install the furnishings in the zones 251 and 252: (a)

AES

Install the lavatories, if removed (Ref. AMM 25-42-41-400-001) .

(5)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(6)

Remove the access platform(s).

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z250

A

A

CLEANING AREA Z253−254

FR64

FR47

N_MM_249200_7_AGM0_01_00

AES

FIGURE 24-92-00-991-10200-A SHEET 1 Aft Passenger Overhead-Compartment - Cleaning Area Zones 253-254

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FR65

FR63

FR61

FR59

FR57

FR55

FR53

FR51

FR49

FR47

AD

251JC

251HC

251GC

251FC

251EC

251DC

251CC

251BC

251AC

N_MM_249200_7_AHM0_01_00

AES

FIGURE 24-92-00-991-10300-A SHEET 1 Aft Passenger Overhead-Compartment - Access Panels Zones 253-254

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-022-A Cleaning of EWIS Installed in the Aft Cabin Utility-Area (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-61-01-) CLEANING OF EWIS INSTALLED IN THE AFT CABIN UTILITY AREA (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

261 262 251AX, 251BX, 251CX, 252AX, 252BX, 252CX C.

ZONE DESCRIPTION AFT CABIN UTILITY AREA AFT CABIN UTILITY AREA

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-21-41-000-001-A

Removal of the Passenger Seats

25-21-41-400-001-A

Installation of the Passenger Seats

25-23-43-000-001-A

Removal of the Upper Sidewall Panel(s)

25-23-43-400-001-A

Installation of the Upper Sidewall Panel(s)

25-23-44-000-001-A

Removal of the Lower Sidewall-Panels (Dado Panels)

25-23-44-400-001-A

Installation of the Lower Sidewall-Panels (Dado Panels)

25-23-48-000-001-A

Removal of the Cove Light Panels

25-23-48-400-001-A

Installation of the Cove Light Panels

25-33-41-000-002-A

Removal of the Aft Galley Unit

25-33-41-400-002-A

Installation of the Aft Galley Unit

25-43-41-000-001-A

Removal of the Lavatory D

25-43-41-400-001-A

Installation of the Lavatory D

25-43-42-000-001-A

Removal of the Lavatory E

25-43-42-400-001-A

Installation of the Lavatory E

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0

AES

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL REFERENCE DESIGNATION (Ref. Fig. 24-92-00-991-10400-A - Aft Cabin Utility-Area - Cleaning Area - Zones 261-262) (Ref. Fig. 24-92-00-991-10500-A - Aft Cabin Utility-Area - Access Panels - Zones 261-262) 3.

Job Set-up Subtask 24-92-00-010-126-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the furnishings in the zones 261 and 262:

(4)

(a)

Remove the lavatories, if installed (Ref. TASK 25-43-41-000-001-A), (Ref. TASK 25-43-42-000-001-A), (Ref. AMM 25-43-43-000-001) , (Ref. AMM 25-43-44-000-001) , (Ref. AMM 25-43-44-000-001) , (Ref. AMM 25-43-44-000-003) and (Ref. AMM 25-43-48-000-001) .

(b)

Remove the galleys and stowage, if installed (Ref. AMM 25-33-41-000-001) , (Ref. TASK 25-33-41-000-002-A), (Ref. AMM 25-33-41-000-008) , (Ref. AMM 25-33-42-000-001) , (Ref. AMM 25-33-43-000-001) , (Ref. AMM 25-33-45-000-001) and (Ref. AMM 25-33-49-000-001) .

(c)

Remove the passenger seats (Ref. TASK 25-21-41-000-001-A), if installed.

Remove the linings and insulation panels in the zones 261 and 262: (a)

Remove the upper sidewall panels (Ref. TASK 25-23-43-000-001-A): . 251BX 252BX.

(b)

Remove the lower sidewall panels (Ref. TASK 25-23-44-000-001-A): . 251AX 252AX.

(c)

Remove the cove light panels (Ref. TASK 25-23-48-000-001-A): . 251CX 252CX.

Subtask 24-92-00-862-114-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-10400-A - Aft Cabin Utility-Area - Cleaning Area - Zones 261-262) (Ref. Fig. 24-92-00-991-10500-A - Aft Cabin Utility-Area - Access Panels - Zones 261-262) Subtask 24-92-00-160-070-A A.

Cleaning of All Wiring Installed in the Aft Cabin Utility-Area (Only Contaminated Wiring) (1)

AES

Clean the wiring if there is dust or lint contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC power-distribution route: 2P.

(b)

On other routes: 1M, 2M and 8M.

(c)

On the audio and video route: 1R.

(d)

On the coaxial wiring routes: 9T and 10T.

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 5.

Close-up Subtask 24-92-00-410-124-A A.

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the linings and insulation panels in the zones 261 and 262:

(3)

AES

(a)

Install the upper sidewall panels (Ref. TASK 25-23-43-400-001-A): . 251BX 252BX.

(b)

Install the lower sidewall panels (Ref. TASK 25-23-44-400-001-A): . 251AX 252AX.

(c)

Install the cove light panels (Ref. TASK 25-23-48-400-001-A): . 251CX 252CX.

Install the furnishings in the zones 261 and 262: (a)

Install the lavatories, if removed (Ref. TASK 25-43-41-400-001-A), (Ref. TASK 25-43-42-400-001A), (Ref. AMM 25-43-43-400-001) , (Ref. AMM 25-43-44-400-001) , (Ref. AMM 25-43-44-400-001) , (Ref. AMM 25-43-44-400-003) and (Ref. AMM 25-43-48-400-001) .

(b)

Install the galleys and stowage, if removed (Ref. AMM 25-33-41-400-001) , (Ref. TASK 25-33-41-400-002-A), (Ref. AMM 25-33-41-400-008) , (Ref. AMM 25-33-42-400-001) , (Ref. AMM 25-33-43-400-001) , (Ref. AMM 25-33-45-400-001) and (Ref. AMM 25-33-49-400-001) .

(c)

Install the passenger seats (Ref. TASK 25-21-41-400-001-A), if removed.

(4)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(5)

Remove the access platform(s).

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Z260

A

A CLEANING AREA Z261−262

FR70

FR64

N_MM_249200_7_AVM0_01_00

AES

FIGURE 24-92-00-991-10400-A SHEET 1 Aft Cabin Utility-Area - Cleaning Area - Zones 261-262

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

B A

A FR65

FR63 251CX

251AX 251BX

B FR63

FR65

252CX

252BX 252AX

N_MM_249200_7_AXM0_01_00

AES

FIGURE 24-92-00-991-10500-A SHEET 1 Aft Cabin Utility-Area - Access Panels - Zones 261-262

24-92-00 PB701

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-023-A Cleaning of EWIS Installed in the Aft Cabin Overhead-Compartment (Only IF Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-02-63-01-) CLEANING OF EWIS INSTALLED IN THE AFT CABIN OVERHEAD COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

263 AFT CABIN OVERHEAD COMPARTMENT 264 AFT CABIN OVERHEAD COMPARTMENT 251JC, 261BC, 261CC, 262BC, 262CC C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-23-41-000-001-A

Removal of the Ceiling Panels

25-23-41-400-001-A

Installation of the Ceiling Panels

25-23-42-000-002-A

Removal of the Ceiling Panels - Aft Utility Area

25-23-42-400-002-A

Installation of the Ceiling Panels - Aft Utility Area

25-24-41-000-001-A

Removal of the Overhead Stowage Compartments

25-24-41-400-001-A

Installation of the Overhead Stowage Compartments

25-33-41-000-002-A

Removal of the Aft Galley Unit

25-33-41-400-002-A

Installation of the Aft Galley Unit

25-43-41-000-001-A

Removal of the Lavatory D

25-43-41-400-001-A

Installation of the Lavatory D

25-43-42-000-001-A

Removal of the Lavatory E

25-43-42-400-001-A

Installation of the Lavatory E

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-10800-A - Aft Cabin Overhead Compartment - Cleaning Area - Zones 263-264) (Ref. Fig. 24-92-00-991-10900-A - Aft Cabin Overhead Compartment - Access Panels -Zones 263-264)

AES

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 3.

Job Set-up Subtask 24-92-00-010-127-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 832 (842).

(2)

Open the passenger/crew door 832 (842) (Ref. TASK 52-10-00-010-001-A).

(3)

Remove the furnishings in the zones 261 and 262: (a)

Remove the lavatories, if installed (Ref. TASK 25-43-41-000-001-A), (Ref. TASK 25-43-42-000-001-A), (Ref. AMM 25-43-43-000-001) , (Ref. AMM 25-43-44-000-001) , (Ref. AMM 25-43-44-000-003) and (Ref. AMM 25-43-48-000-001) .

(b)

Remove the galleys and stowage, if installed (Ref. AMM 25-33-41-000-001) , (Ref. TASK 25-33-41-000-002-A), (Ref. AMM 25-33-41-000-008) , (Ref. AMM 25-33-42-000-001) , (Ref. AMM 25-33-43-000-001) , (Ref. AMM 25-33-45-000-001) , (Ref. AMM 25-33-46-000-001) and (Ref. AMM 25-33-49-000-001) .

(4)

Remove the overhead stowage compartments between FR64 and FR70 (Ref. TASK 25-24-41-000-001A).

(5)

Remove the ceiling panel in the zones 263 and 264 (Ref. TASK 25-23-41-000-001-A): . 251JC.

(6)

Remove the ceiling panels in the aft utility area (Ref. TASK 25-23-42-000-002-A): . 261BC 261CC 262BC 262CC.

Subtask 24-92-00-862-115-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-10800-A - Aft Cabin Overhead Compartment - Cleaning Area - Zones 263-264) (Ref. Fig. 24-92-00-991-10900-A - Aft Cabin Overhead Compartment - Access Panels -Zones 263-264) Subtask 24-92-00-160-071-A A.

Cleaning of All Wiring Installed in the Aft Cabin Overhead-Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 3G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 3P.

(c)

On other routes: 1M, 2M and 8M.

(d)

On the audio and video route: 1R.

(e)

On coaxial wiring routes : 9T and 10T.

(f)

On the excitation routes: 3E and 6E.

Close-up Subtask 24-92-00-410-125-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the ceiling panels in the aft utility area (Ref. TASK 25-23-42-400-002-A): . 261BC 261CC 262BC 262CC.

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL

AES

(3)

Install the ceiling panel in the zones 263 and 264 (Ref. TASK 25-23-41-400-001-A): . 251JC.

(4)

Install the furnishings in the zones 261 and 262: (a)

Install the lavatories, if removed (Ref. TASK 25-43-41-400-001-A), (Ref. TASK 25-43-42-400-001A), (Ref. AMM 25-43-43-400-001) , (Ref. AMM 25-43-44-400-001) , (Ref. AMM 25-43-44-400-003) and (Ref. AMM 25-43-48-400-001) .

(b)

Install the galleys and stowage, if removed (Ref. AMM 25-33-41-400-001) , (Ref. TASK 25-33-41-400-002-A), (Ref. AMM 25-33-41-400-008) , (Ref. AMM 25-33-42-400-001) , (Ref. AMM 25-33-43-400-001) , (Ref. AMM 25-33-45-400-001) , (Ref. AMM 25-33-46-400-001) and (Ref. AMM 25-33-49-400-001) .

(5)

Install the overhead stowage compartments between FR64 and FR70 (Ref. TASK 25-24-41-400-001-A).

(6)

Close the passenger/crew door 832 (842) (Ref. TASK 52-10-00-410-001-A).

(7)

Remove the access platform(s).

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Z260

A

A CLEANING AREA Z263−264

FR70

FR64

N_MM_249200_7_AWM0_01_00

AES

FIGURE 24-92-00-991-10800-A SHEET 1 Aft Cabin Overhead Compartment - Cleaning Area - Zones 263-264

24-92-00 PB701

Page 4 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A FR68 FR66

261BC 261CC

262CC

251JC 262BC

N_MM_249200_7_AZM0_01_00

AES

FIGURE 24-92-00-991-10900-A SHEET 1 Aft Cabin Overhead Compartment - Access Panels -Zones 263-264

24-92-00 PB701

Page 5 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-024-A Cleaning of EWIS Installed in the Underfloor Bay of Forward Cargo Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-01-33-01-) CLEANING OF EWIS INSTALLED IN THE UNDERFLOOR BAY OF FORWARD CARGO COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

133 134 133AL, 134AR, 825 C.

ZONE DESCRIPTION BAY UNDER FWD CAR COMPT FLOOR BAY UNDER FWD CAR COMPT FLOOR

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

52-30-00-860-002-A 52-30-00-860-003-A

Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

53-22-14-000-001-A

Removal of the Forward Cargo-Compartment Floor-Panels

53-22-14-400-001-A

Installation of the Forward Cargo-Compartment Floor-Panels

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-12200-A - Forward Cargo Compartment - Cleaning Area - Zones 133-134) 3.

Job Set-up Subtask 24-92-00-010-131-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-001-A) and (Ref. TASK 52-30-00-860-003-A).

(3)

Open the access doors 133AL 134AR.

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (4)

Remove the FWD cargo-compartment floor-panels from FR24 to FR34 (Ref. TASK 53-22-14-000-001A).

Subtask 24-92-00-862-119-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-12200-A - Forward Cargo Compartment - Cleaning Area - Zones 133-134) Subtask 24-92-00-160-072-A A.

Cleaning of All Wiring Installed in the Underfloor Bay of Forward Cargo Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust, lint or hydraulic contamination (Ref. ESPM 20-55-00-0). (a)

On the flight control routes: 8S and 8M.

(b)

On the engine control route: 2S.

(c)

On the other routes: 1M and 2M.

(d)

On the coaxial wiring route: 5U.

Close-up Subtask 24-92-00-410-129-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the FWD cargo-compartment floor-panels from FR24 to FR34 (Ref. TASK 53-22-14-400-001-A).

(3)

Close the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-002-A) and (Ref. TASK 52-30-00-860-004-A).

(4)

Close the access doors 133AL 134AR.

(5)

Remove the access platform(s).

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL 825 134AR

A

133AL

A FR34

FR24

CLEANING AREA Z133−134

N_MM_249200_7_RLM0_01_00

AES

FIGURE 24-92-00-991-12200-A SHEET 1 Forward Cargo Compartment - Cleaning Area - Zones 133-134

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-025-A Cleaning of EWIS Installed in the Forward Cargo Compartment (Only IF Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-01-31-01-) CLEANING OF EWIS INSTALLED IN THE FORWARD CARGO COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

131 132 825

ZONE DESCRIPTION FORWARD CARGO COMPARTMENT FORWARD CARGO COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-54-12-000-002-A

Removal of the Ceiling Panels in the Forward Cargo-Compartment

25-54-12-000-003-A

Removal of the Sidewall Panels in the Forward Cargo-Compartment

25-54-12-400-002-A

Installation of the Ceiling Panels in the Forward Cargo-Compartment

25-54-12-400-003-A

Installation of the Sidewall Panels in the Forward Cargo- Compartment

52-30-00-860-001-A

52-30-00-860-003-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-002-A

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-14400-A - Forward Cargo Compartment - Cleaning Area - Zones 131-132) 3.

Job Set-up Subtask 24-92-00-010-141-A A.

Get Access (1)

AES

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

24-92-00 PB701

Page 1 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Open the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-001-A) and (Ref. TASK 52-30-00-860-003-A).

(3)

Remove the ceiling panels in the FWD cargo compartment from FR24 to FR34 (Ref. TASK 25-54-12-000-002-A).

(4)

Remove the sidewall panels in the FWD cargo compartment from FR24 to FR34 (Ref. TASK 25-54-12-000-003-A).

Subtask 24-92-00-862-129-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-14400-A - Forward Cargo Compartment - Cleaning Area - Zones 131-132) Subtask 24-92-00-160-073-A A.

Cleaning of All Wiring Installed in the Forward Cargo Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust, lint or hydraulic contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 1G and 2G.

(b)

On the AC/DC power-distribution routes: 1P and 2P.

(c)

On the flight control routes: 7S, 8S, 7M and 8M.

(d)

On the engine control routes: 1S, 2S, 4S and 5S.

(e)

On the other routes: 1M and 2M.

(f)

On the coaxial wiring routes: 1U, 2U, 1T, 2T, 3T, 4T, 9T and 5V.

(g)

On the audio route: 1R.

(h)

On the generator excitation routes: 1E and 2E.

Close-up Subtask 24-92-00-410-139-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the sidewall panels in the FWD cargo compartment from FR24 to FR34 (Ref. TASK 25-54-12-400-003-A).

(3)

Install the ceiling panels in the FWD cargo compartment from FR24 to FR34 (Ref. TASK 25-54-12-400-002-A).

(4)

Close the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-002-A) and (Ref. TASK 52-30-00-860-004-A).

(5)

Remove the access platform(s).

24-92-00 PB701

Page 2 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

825

A

A FR34

FR24

CLEANING AREA Z131−132

N_MM_249200_7_TLM0_01_00

AES

FIGURE 24-92-00-991-14400-A SHEET 1 Forward Cargo Compartment - Cleaning Area - Zones 131-132

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-026-A Cleaning of EWIS Installed in the Aft Cargo Compartment (Only IF Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-01-51-01-) CLEANING OF EWIS INSTALLED IN THE AFT CARGO COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

151 152 826

ZONE DESCRIPTION AFT CARGO COMPARTMENT AFT CARGO COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-55-11-000-002-A

Removal of the Ceiling Panels in the Aft Cargo-Compartment - FR47/FR59

25-55-11-000-003-A

Removal of the Sidewall Panels in the Aft Cargo-Compartment - FR47/FR59

25-55-11-400-002-A

Installation of the Ceiling Panels in the Aft Cargo-Compartment -FR47/FR59

25-55-11-400-003-A

Installation of the Sidewall Panels in the Aft Cargo-Compartment - FR47/FR59

52-30-00-860-001-A

52-30-00-860-003-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-002-A

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-14500-A - Aft Cargo Compartment - Cleaning Area - Zones 151-152) 3.

Job Set-up Subtask 24-92-00-010-142-A A.

Get Access (1)

AES

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (2)

Open the AFT cargo-compartment door 826 (Ref. TASK 52-30-00-860-001-A) and (Ref. TASK 52-30-00-860-003-A).

(3)

Remove the additional center tanks No. 1, No. 2 and No. 3 in zones 151 and 152, if installed (Ref. AMM 28-11-27-000-002) , (Ref. AMM 28-11-27-000-003) and (Ref. AMM 28-11-27-000-004) .

(4)

Remove the sidewall panels in the AFT cargo compartment from FR47 to FR59 (Ref. TASK 25-55-11-000-003-A).

(5)

Remove the ceiling panels in the AFT cargo compartment from FR47 to FR59 (Ref. TASK 25-55-11-000-002-A).

Subtask 24-92-00-862-130-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-14500-A - Aft Cargo Compartment - Cleaning Area - Zones 151-152) Subtask 24-92-00-160-074-A A.

Cleaning of EWIS Installed in the Aft Cargo Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust, lint or other contamination (Ref. ESPM 20-55-00-0).

Close-up Subtask 24-92-00-410-140-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the ceiling panels in the AFT cargo compartment from FR47 to FR59 (Ref. TASK 25-55-11-400-002-A).

(3)

Install the sidewall panels in the AFT cargo compartment from FR47 to FR59 (Ref. TASK 25-55-11-400-003-A).

(4)

Install the additional center tanks No. 1, No. 2 and No. 3 in zones 151 and 152, if removed (Ref. AMM 28-11-27-400-002) , (Ref. AMM 28-11-27-400-003) and (Ref. AMM 28-11-27-400-004) .

(5)

Close the AFT cargo-compartment door 826 (Ref. TASK 52-30-00-860-002-A) and (Ref. TASK 52-30-00-860-004-A).

(6)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 826

A FR59

FR47

CLEANING AREA Z151−152 N_MM_249200_7_VLM0_01_00

AES

FIGURE 24-92-00-991-14500-A SHEET 1 Aft Cargo Compartment - Cleaning Area - Zones 151-152

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-027-A Cleaning of EWIS Installed in the Air Conditioning Compartment and Fairings (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-01-91-01-) CLEANING OF EWIS INSTALLED IN THE AIR CONDITIONING COMPARTMENT AND FAIRINGS (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

191

ZONE DESCRIPTION AIR CONDITONING COMPT AND FAIRING AIR CONDITONING COMPT AND FAIRING AIR CONDITONING COMPT AND FAIRING AIR CONDITONING COMPT AND FAIRING

192 191AB, 191AT, 191BT, 191CT, 191DT, 191EB, 191ET, 191GB, 191HB, 191JB, 191KB, 191LB, 192AB, 192AT, 192BT, 192CT, 192DT, 192EB, 192ET, 192FB, 192KB, 192LB, 192MB C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-14800-A - Air Conditioning Compartment and Fairings - Access Panels on the Left Side) (Ref. Fig. 24-92-00-991-15000-A - Air Conditioning Compartment and Fairings - Access Panels on the Right Side) (Ref. Fig. 24-92-00-991-15100-A - Air Conditioning Compartment and Fairings - Cleaning Area - Zones 191-192) 3.

Job Set-up Subtask 24-92-00-010-145-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Remove the access panels: . For the left side: 191AB 191AT 191BT 191CT 191DT 191EB 191ET 191GB 191HB 191JB 191KB 191LB.

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL .

For the right side: 192AB 192AT 192BT 192CT 192DT 192EB 192ET 192FB 192KB 192LB 192MB.

Subtask 24-92-00-862-133-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-14800-A - Air Conditioning Compartment and Fairings - Access Panels on the Left Side) (Ref. Fig. 24-92-00-991-15000-A - Air Conditioning Compartment and Fairings - Access Panels on the Right Side) (Ref. Fig. 24-92-00-991-15100-A - Air Conditioning Compartment and Fairings - Cleaning Area - Zones 191-192) Subtask 24-92-00-160-075-A A.

Cleaning of All Wiring Installed in the Air Conditioning Compartment and Fairings (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust or lint contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC power-distribution routes: 1P and 2P.

(b)

On the other routes: 1M and 2M.

(c)

On the overheat detection.

Close-up Subtask 24-92-00-410-143-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the access panels: . For the left side: 191AB 191AT 191BT 191CT 191DT 191EB 191ET 191GB 191HB 191JB 191KB 191LB. . For the right side: 192AB 192AT 192BT 192CT 192DT 192EB 192ET 192FB 192KB 192LB 192MB.

(3)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

A

FR31 FR34 FR36 191AT 191BT 191EB

FR42

191CT 191DT 191LB FR47

191AB 191ET

FR50

FR53

191GB 191HB 191KB 191JB

N_MM_249200_7_YLM0_01_00

AES

FIGURE 24-92-00-991-14800-A SHEET 1 Air Conditioning Compartment and Fairings - Access Panels on the Left Side

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A

FR31 FR34

A

FR36

192AT

192DT FR42

192BT

192CT 192LB

FR47 192ET FR50

FR53

192AB 192EB 192FB 192KB 192MB

N_MM_249200_7_BMM0_01_00

AES

FIGURE 24-92-00-991-15000-A SHEET 1 Air Conditioning Compartment and Fairings - Access Panels on the Right Side

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

Z190

A

A

CLEANING AREA Z191−192

FR31

FR47

N_MM_249200_7_EMM0_01_00

AES

FIGURE 24-92-00-991-15100-A SHEET 1 Air Conditioning Compartment and Fairings - Cleaning Area - Zones 191-192

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-029-A Cleaning of EWIS Installed in the Bay Behind FWD Cargo Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-01-37-01-) CLEANING OF EWIS INSTALLED IN THE BAY BEHIND FWD CARGO COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

137 138 825

ZONE DESCRIPTION BAY BETW AFT PART. BULKHEAD OF FWD CARGO BAY BETW AFT PART. BULKHEAD OF FWD CARGO

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-54-12-000-001-A

Removal of the Forward Cargo-Compartment Partition FR34

25-54-12-400-001-A

Installation of the Forward Cargo-Compartment Partition FR34

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

52-30-00-860-002-A 52-30-00-860-003-A

Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-15200-A - Bay Behind FWD Cargo Compartment - Cleaning Area - Zones 137-138) 3.

Job Set-up Subtask 24-92-00-010-148-A A.

AES

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-001-A) and (Ref. TASK 52-30-00-860-003-A).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the additional center tanks No. 4 and No. 6 in zones 137 and 138, if installed (Ref. AMM 28-11-27-000-005) and (Ref. AMM 28-11-27-000-007) .

(4)

Remove the FWD cargo-compartment partition FR34 (Ref. TASK 25-54-12-000-001-A).

Subtask 24-92-00-862-135-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-15200-A - Bay Behind FWD Cargo Compartment - Cleaning Area - Zones 137-138) Subtask 24-92-00-160-077-A A.

Cleaning of All Wiring Installed in the Bay Behind FWD Cargo Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust, lint or hydraulic contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 1G and 2G.

(b)

On the AC/DC power-distribution routes: 1P and 2P.

(c)

On the flight control routes: 7S and 8S.

(d)

On the engine control routes: 1S and 2S.

(e)

On the other routes: 1M and 2M.

(f)

On the coaxial wiring routes: 2T and 2U.

(g)

On the generator excitation routes: 1E and 2E.

Close-up Subtask 24-92-00-410-146-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the additional center tanks No. 4 and No. 6 in zones 137 and 138, if removed (Ref. AMM 28-11-27-400-005) and (Ref. AMM 28-11-27-400-007) .

(3)

Install the FWD cargo-compartment partition FR34 (Ref. TASK 25-54-12-400-001-A).

(4)

Close the FWD cargo-compartment door 825 (Ref. TASK 52-30-00-860-002-A) and (Ref. TASK 52-30-00-860-004-A).

(5)

Remove the access platform(s).

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

825

A

A FR36

CLEANING AREA Z137−138

FR35

FR34

N_MM_249200_7_XLM0_01_00

AES

FIGURE 24-92-00-991-15200-A SHEET 1 Bay Behind FWD Cargo Compartment - Cleaning Area Zones 137-138

24-92-00 PB701

Page 3 May 01/12 Revision n˚: 40

@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-030-A Cleaning of EWIS Installed in the Bulk Cargo Compartment (Only If Contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-01-61-01-) CLEANING OF EWIS INSTALLED IN THE BULK CARGO COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

161 162 826

ZONE DESCRIPTION BULK CARGO COMPARTMENT BULK CARGO COMPARTMENT

C.

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

25-55-12-000-003-A

Removal of the Sidewall Panels in the Aft Cargo Compartment - FR59/FR65

25-55-12-400-003-A

Installation of the Sidewall Panels in the Aft Cargo Compartment - FR59/FR65

52-30-00-860-001-A

Open the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump

52-30-00-860-002-A 52-30-00-860-003-A

Open the FWD or AFT Cargo-Compartment Door with the Hand Pump

52-30-00-860-004-A

Close the FWD or AFT Cargo-Compartment Door with the Hand Pump

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-15300-A - Bulk Cargo Compartment - Cleaning Area - Zones 161-162) 3.

Job Set-up Subtask 24-92-00-010-149-B A.

AES

Get Access (1)

Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.

(2)

Open the AFT cargo-compartment door 826 (Ref. TASK 52-30-00-860-001-A) and (Ref. TASK 52-30-00-860-003-A).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL (3)

Remove the sidewall panels in the AFT cargo compartment from FR59 to FR65 (Ref. TASK 25-55-12-000-003-A).

Subtask 24-92-00-862-136-A B.

4.

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

Procedure (Ref. Fig. 24-92-00-991-15300-A - Bulk Cargo Compartment - Cleaning Area - Zones 161-162) Subtask 24-92-00-160-078-A A.

Cleaning of All Wiring Installed in the Bulk Cargo Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust, lint or hydraulic contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC power-distribution routes: 1P and 2P.

(b)

On the flight control routes: 7S and 8S.

(c)

On the engine control routes: 1S, 2S and APU.

(d)

On the other routes: 1M and 2M.

(e)

On the coaxial wiring routes: 5T and 6T.

Close-up Subtask 24-92-00-410-147-B A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Install the sidewall panels in the AFT cargo compartment from FR59 to FR65 (Ref. TASK 25-55-12-400-003-A).

(3)

Close the AFT cargo-compartment door 826 (Ref. TASK 52-30-00-860-002-A) and (Ref. TASK 52-30-00-860-004-A).

(4)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

A 826

A

FR65

FR59

CLEANING AREA Z161−162 N_MM_249200_7_WLM0_01_00

AES

FIGURE 24-92-00-991-15300-A SHEET 1 Bulk Cargo Compartment - Cleaning Area - Zones 161-162

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL Task 24-92-00-100-031-A Cleaning of EWIS Installed in the Lateral Avionic Compartment (Only If contaminated)(EWIS) 1.

Reason for the Job (Ref. MPD 20-01-25-01-) CLEANING OF EWIS INSTALLED IN THE LATERAL AVIONIC COMPARTMENT (ONLY IF CONTAMINATED) (EWIS) NOTE :

2.

This is an EWIS (Electrical Wiring Interconnection System) procedure. EWIS is defined in ESPM 20-33-11.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

REFERENCE No specific B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS

125 126 812, 813, 822, 824 C.

ZONE DESCRIPTION LATERAL AVIONIC COMPARTMENT LATERAL AVIONIC COMPARTMENT

Referenced Information

REFERENCE 24-41-00-862-002-A

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power

24-41-00-862-002-A-01

De-energize the Aircraft Electrical Circuits Supplied from the APU

24-41-00-862-002-A-02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

52-10-00-010-001-A

Opening of the Passenger/Crew Door

52-10-00-410-001-A

Closing of the Passenger/Crew Door

ESPM 20-55-00-0 (Ref. Fig. 24-92-00-991-15500-A - Lateral Avionic Compartment - Cleaning Area - Zones 125-126) 3.

Job Set-up Subtask 24-92-00-010-152-A A.

Get Access (1)

Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position.

(2)

Open the forward passenger/crew door 831 (Ref. TASK 52-10-00-010-001-A).

(3)

Open the access doors 812 822 824.

(4)

Open the access door 813, if installed.

Subtask 24-92-00-862-138-A B.

AES

De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002-A) or (Ref. TASK 24-41-00-862-002-A-01) or (Ref. TASK 24-41-00-862-002A-02).

24-92-00 PB701

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL 4.

Procedure (Ref. Fig. 24-92-00-991-15500-A - Lateral Avionic Compartment - Cleaning Area - Zones 125-126) Subtask 24-92-00-160-080-A A.

Cleaning of All Wiring Installed in the Lateral Avionic Compartment (Only Contaminated Wiring) (1)

5.

Clean the wiring if there is dust, lint or hydraulic contamination (Ref. ESPM 20-55-00-0). (a)

On the AC/DC feeder routes: 1G, 2G, 4G and 6G.

(b)

On the AC/DC power-distribution routes: 1P, 2P and 6P.

(c)

On the flight control wiring.

(d)

On the engine control routes: 1S and 2S.

(e)

On the other routes: 1M, 2M and 6M.

(f)

On the audio route: 1R.

(g)

On the coaxial wiring routes: 3T and 4T.

(h)

On the generator excitation routes: 1E, 2E, 3E and 6E.

Close-up Subtask 24-92-00-410-150-A A.

AES

Close Access (1)

Make sure that the work area is clean and clear of tool(s) and other items.

(2)

Close the access door 813, if installed.

(3)

Close the access doors 812 822 824.

(4)

Close the forward passenger/crew door 831 (Ref. TASK 52-10-00-410-001-A).

(5)

Remove the access platform(s).

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@A318/A319/A320/A321 AIRCRAFT MAINTENANCE MANUAL ** On A/C ALL

FR9

B

831 FR20

A 813

A 812

822 824

B FR20

FR9

CLEANING AREA Z125−126

N_MM_249200_7_JMM0_01_00

AES

FIGURE 24-92-00-991-15500-A SHEET 1 Lateral Avionic Compartment - Cleaning Area - Zones 125-126

24-92-00 PB701

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