Troubleshooting on A320 - A340

Customer Support Engineering

Presented by

AUFFRET Hervé Indication / Warning / Maintenance System

Trouble shooting philosophy with A320 CFDS / A340 CMS

Troubleshooting with A320 CFDS / A340 CMS - REFERENCE 952.1003/05

May 2005

TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS

AGENDA 1. Maintenance Levels 2. Line Maintenance Concept 3. A/C Information Sharing 4. Message Classification © AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.

5. TSM Use 6. SIL 00-028, 00-038 & 00-041


May 2005

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5. TSM Use 6. SIL 00-028, 00-038 & 00-041


May 2005

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MAINTENANCE LEVELS

1st Level

LINE MAINTENANCE

© AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.

No Log-Book complaint Log-Book complaint (Class 1) LRU level only

2nd Level

No Maintenance Action required PFR + System Report / Test + Ref to MMEL

BASE MAINTENANCE / NIGHT STOP

Maintenance status LRU Level


PFR (Class 2) + System Report / Test

May 2005

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MAINTENANCE LEVELS

3rd Level

SCHEDULED CHECKS General Class 3 Report + System Report / Test

Class 3 faults LRU Level


4th Level

SHOP MAINTENANCE

LRU removal SRU Level


Trouble Shooting Data + BITE Shop Memory

May 2005

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5. TSM Use 6. SIL 00-028, 00-038 & 00-041


May 2005

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LINE MAINTENANCE CONCEPT: Decision Tree applies MEL NO GO Yes

LOG BOOK

No Crew or Maintenance Observation

Fault on PFR Yes

Carried Forward item

SIL 00-028 / -038/ 041/ -078 •PART A (Fault Msg) •PART B (Cockpit Effect)

TSM EFIS, LOCAL or OBSV Index © AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.

No

TSM ECAM or CMS Index

FOLLOW TSM PROCEDURE

Maint Action/ LRU Removal

Yes

A/C Return to Service

Spare Available

Yes

Failure Isolated

No A/L Engineering (ACMS Labels)

AIRBUS (TSD, ACMS Labels)

No


May 2005

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5. TSM Use 6. SIL 00-028, 00-038 & 00-041


May 2005

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A/C INFORMATION SHARING OPERATIONAL INFORMATION FOR FLIGHT CREW : A/C DISPATCH

MAINTENANCE INFORMATION FOR MECHANIC : A/C TROUBLESHOOTING

AIRCRAFT SYSTEMS Operational failure messages (function lost) :

Maintenance failure messages (LRU lost) :

"Warnings/Malfunctions"

"CMS Fault Messages"

CMC

FWCs

LOG

BOOK POST FLIGHT REPORT


Warnings/Malfunctions

ECAM or EFIS indications

TSM

Warnings/ CMS Malfunctions Fault

HYDB RSVR LO PRESS -BLUE ELEC PUMP....OFF

or

LOCAL indications

TEST>

FAULT

Fault Isolation Procedures FAULTY LRU


associated to Warnings/Malfunctions and CMS Fault Messages May 2005

MCDU

Page 9



5. TSM Use 6. SIL 00-028, 00-038 & 00-041


May 2005

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MESSAGE CLASSIFICATION MESSAGE CLASS

1

2

3

PRESENTED INDICATION TO THE FLIGHT CREW


INDICATION TO THE MAINTENANCE TEAM DISPATCH (MMEL) CONSEQUENCES

Maintenance Status

Any evidence of fault to the flight crew: ECAM Warning, Flag on SD, PFD or ND, Local warnings, System misbehaviour ...

Status light flashing at the end of the flight; Maintenance Status messages on SD STS page, presented only on ground.

POST FLIGHT REPORT

MMEL ENTRY GO, GO IF or NO GO

To be manually issued

MMEL PREAMBLE

MMEL NOT APPLICABLE

GO

600 Hours

UNLIMITED TIME

for time delay, restrictions etc... (See also TSM Introduction)


No indication to the flight crew

AVIONIC STATUS

Can be automatically issued at 80 kts + 180 s

REF MMEL HANDLING

NOT PRESENTED

Cockpit Effect

However, correction is recommended to improve the dispatch reliability

May 2005

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5. TSM Use 6. SIL 00-028, 00-038 & 00-041


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TSM USE TSM LEVEL

ATA CHAPTER LEVEL

General Indexes

ATA SECTION LEVEL

ATA Indexes

TSM Procedure

PB 101

I-ECAM

Fault Symptoms

PB 201

XX-ECAM I-EFIS FAULT ISOLATION

XX-EFIS I-LOCAL © AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.

XX-LOCAL

PB 301

I-OBSV XX-OBSV

I-CFDS

BLOCK DIAGRAM

XX-CFDS (XX= ATA chapter)


May 2005

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TSM USE : Indexes A320

TROUBLE SHOOTING MANUAL INDEX OF WARNING/MALFUNCTIONS ECAM

PFR ATA TSM ATA CH/SE CH-PB101

A320

EWD WARNINGS


A.ICE CAPT AOA HEAT ECAM A.ICE CAPT PITOT HEAT ECAM A.ICE CAPT TAT HEAT ECAM A.ICE F/O AOA HEAT 30-ECAM A.ICE F/O PITOT HEAT ECAML INR WING HI PR A.ICE A.ICE F/O TAT HEAT ECAM ECAM AIR ENG 1 BLEED NOT CLOSED 36-ECAM AIR ENG 1 HPV NOT OPEN 36-ECAM AIR ENG 1 BLEED FAULT ECAM AIR ENG 1 BLEED LEAK ECAM EFF : ALL ENG 2 BLEED NOT CLOSED ECAM 01/94 XXX

30-00

30-

30-00

30-

30-00

30-

30-00 30-00

30-

30-00 30-00

3030-

36-00 36-00 36-00

CFDS MESSAGES

ATA

SOURCE CLASS CH-PB101

ACARS MU (1RB) ACCELEROMETER CFDS ACCLRM 1 12CE1 ACCLRM 1 12CE1 ACCLRM 2 12CE2 ACCLRM 2 12CE2 ACCLRM 3 12CE3 ACCLRM 3 12CE3

232434 ACARSMU 313316 FDIU

1

23-ECAM 2 31-

279216 279216 279216 279216 279216 279216

2 2 2 2 2 2

27-ECAM 27-ECAM 27-ECAM 27-ECAM 27-ECAM 27-ECAM

ADIRU1 ECAM ADIRU1 (1FP1)/GPWC (1WZ) ECAM ADIRU1 (1FP1)/ OVER TEMP CFDS ADIRU1 OR ADIRS CDU ECAM ADIRU1 OR AOA SENSOR 3FP1 ECAM EFF : ALL

341234 ADR 1

1

34-

341234 GPWC

1

34-

341234 ADR 1

2

34-

341234 IR 1

1

34-

EFCS 1 EFCS 2 EFCS 1 EFCS 2 EFCS 1 EFCS 2

36-

I-ECAM36-00 Page 36-00

TROUBLE SHOOTING MANUAL INDEX OF CFDS FAULT MESSAGES

361 36Jan

I-EFIS I-OBSV

I-CFDS 341234 ADR 1

1

27Page 1 Jan 01/94

XXX

I-LOCAL


May 2005

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TSM USE : Fault symptoms

A320 TROUBLE SHOOTING MANUAL AUTO FLIGHT FAULT SYMPTOMS

A320 FAULT ISOLATION C PROCEDURE

CFDS FAULT MESSAGES WARNINGS/MALFUNCTIONS SOURCE

MESSAGE

ATA

EWD WARNING(S)

UBLE SHOOTING MANUAL O FLIGHT FAULT SYMPTOMS FAULT ISOLATION C PROCEDURE

CFDS FAULT MESSAGES SOURCE

MESSAGE

ATA

CFDS MESSAGES

AUTO FLT AP OFF P205

AFS

FMGC 1 (1CA1)

228334

1 22100 T 810 805

AFS

AFS: FAC2/P-B SW 12C 226634

1

226600 P 243 T 810

837


22-ECAM EFF : ALL

Page 101 Jan 01/94

XXX

22-CFDS Page 101 Jan 01/94

34-EFIS EFF : ALL

Page 101 Jan 01/94

XXX

22-LOCAL EFF : ALL

22-OBSV Page 101 Jan 01/94

Page 101 Jan 01/94

XXX


May 2005

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TSM USE : Fault isolation A320 TROUBLE SHOOTING MANUAL TASK 21-26-00-810-808 Monitoring Discrete Output to Extract Fan

TASK 21-26-00-810-805

1. Possible Causes - FAN EXTRACT, AVCNS VENT (7HQ) - Wiring between the pin C of the extract fan and the AEVC (2HQ) 2. Job Set-up Information A. Referenced Information REFERENCE

DESIGNATION

AMM 21-26-00-710-803

Operational test of the Avionics-Equipment Ventilation System Removal of the Extract Fan (7HQ) Installation of the Extract Fan (7HQ)

AMM 21-26-51-000-804 AMM 21-26-51-400-804 ASM 21-26/01

3. Fault Confirmation A. Job set-up Get access Open access door 810 B. Test (1) Do the test of the avionics equipment ventilation (Ref. AMM TASK 21-26-00-710-803). 4. Fault Isolation A. If the test gives the maintenance message EXTRACT FAN (7HQ)/AEVC (2HQ) :


(1) Do a check to make sure that there is ground at pin C of the extract fan

FAULT CONFIRMATION

FAULT ISOLATION

5. Close-up Close Access

21-26-00 EFF : ALL

Page 213 Jan 01/94

XXX


May 2005

Page 16


TSM USE : Task supporting data

A320 TROUBLE SHOOTING MANUAL PCU VALVE BLOCK

A320

EXT

TROUBLE SHOOTING MANUAL FLAPS TASK SUPPORTING DATA

RET functions

FLIGHT WARNING COMPUTER 1 (REF 3-53-00) 26VAC


SYSTEM 2

FLIGHT WARNING COMPUTER 2 (REF 3-53-00) 26VAC SYSTEM 2

X INPUTS.

Flap Power Distribution - Block Diagram Figure 306

age shows the synchro angles in decimal and hexadecimal values of the

LH 27-50-00 EFF : ALL

SHOOTING DATA Cs have TROUBLE SHOOTING DATA for a given fault which shows : antennae messages mplementary information, if applicable; The complementary information is

27-50-00

Page 308 Jan 01/94

LL

XXX

Page 308 Jan 01/94

XXX


May 2005

Page 17


AGENDA 1. Maintenance Levels 2. Line Maintenance Concept 3. A/C Information Sharing 4. TSM Use © AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.

5. SIL 00-028, 00-038 & 00-041


May 2005

Page 18

TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS SIL 00-028 (A320), 00-038 (A340), 00-041 (A330)


•

SILs issued to cover BITE deviations

Part A

PFR Failure Messages

Part B

PFR Cockpit Effects

Part C

Class 3 Fault Messages

Part D

CFDS/CMS Anomalies (Interactive Mode)

Part E

AI Envelope Filter

•

PART E covers items (Cockpit Effect and Fault messages) that AIRBUS recommend to filter from the PFR.

•

Purpose: • •

Reduce number of items in the PFR Improve PFR pertinance


May 2005

Page 19

© AIRBUS S.A.S. All rights reserved. Confidential and proprietary document. This document and all information contained herein is the sole property of AIRBUS S.A.S.. No intellectual property rights are granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced or disclosed to a third party without the express written consent of AIRBUS S.A.S. This document and its content shall not be used for any purpose other than that for which it is supplied. The statements made herein do not constitute an offer. They are based on the mentioned assumptions and are expressed in good faith. Where the supporting grounds for these statements are not shown, AIRBUS S.A.S. will be pleased to explain the basis thereof.


AIRBUS, its logo, A300, A310, A318, A319, A320, A321, A330, A340, A350, A380, A400M are registered trademarks.


May 2005

Page 20

A340-500/600 TECHNICAL TRAINING MANUAL ONBOARD MAINTENANCE SYSTEMS A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/ AVIONICS)

This Page Intentionnaly Left Blank

This document must be used for training purposes only

Under no circumstances should this document be used as a reference

It will not be updated.

All rights reserved No part of this manual may be reproduced in any form, by photostat, microfilm, retrieval system, or any other means, without the prior written permission of AIRBUS S.A.S.

This Page Intentionnaly Left Blank

A340-500/600 TECHNICAL TRAINING MANUAL

ONBOARD MAINTENANCE SYSTEMS

Table Of Contents

CENTRAL MAINTENANCE SYSTEM PRESENTATION . . . . . . . . . . . . . 2 CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION . 14 CMS MENUS PRESENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 MENU NORMAL MODE D/O . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 MENU INTERACTIVE MODE D/O . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48 MENU SERVICING D/O . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62 MENU AVIONICS CONFIGURATION D/O . . . . . . . . . . . . . . . . . . . . . . . 74 MESSAGE D/O . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86 MESSAGE PROCESSING D/O . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 96 BACK UP FUNCTIONS D/O . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 106 PRINTER PRESENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 108 PRINTER D/O . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 110 UP AND DOWN LOADING SYSTEM PRESENTATION. . . . . . . . . . . . 112 UP AND DOWN LOADING SYSTEM D/O . . . . . . . . . . . . . . . . . . . . . . . 118 ON BOARD MAINTENANCE SYSTEM TEST . . . . . . . . . . . . . . . . . . . . 126 ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE . . . . . 134 ON BOARD MAINTENANCE SYSTEMS BASE MAINTENANCE . . . 150

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) TABLE OF CONTENTS FWUT200

Jan 5/05 Page 1


CENTRAL MAINTENANCE SYSTEM PRESENTATION CMS PHILOSOPHY CJanEuNaTrRAyL03M/0A5INTENANCESYSTEMPRESENTATOIN

The Central Maintenance System (CMS) includes the Built-In Test Equipment (BITE) of all electronic systems and two fully redundant Central Maintenance Computers (CMCs). The CMS is used for short term trouble shooting, Line Replaceable Unit (LRU) removal and system failure analysis or test. The CMCs centralize and memorize warnings generated by the Flight Warning Computers (FWCs) and failure messages produced by the aircraft system BITEs. The CMS enables maintenance personnel to perform system operational tests, functional checks and read out of BITE memory through the MCDU. Reports can be printed on-board, saved on a floppy disk via the Multipurpose Disk Drive Unit (MDDU) or transmitted to ground through the Air Traffic Service Unit (ATSU). CMS data can also be loaded into the CMCs through the MDDU.

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P3000000001 01 FWUT200

45 - ONBOARD MAINTENANCE SYSTEMS

January 03/05 Page 2


CENTRAL MAINTENANCE SYSTEM PRESENTATION / CMS PHILOSOPHY A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P3000000001 01 FWUT200




CENTRAL MAINTENANCE SYSTEM PRESENTATION BITE PHILOSOPHY A system is composed of LRUs which can be: - computers, - sensors, - actuators, - and probes. A function of the system computer is to detect and memorize any failure occurring within the systems, it is called the Built-In Test Equipment (BITE). The BITE memory content of each system is sent to the CMCs.





CENTRAL MAINTENANCE SYSTEM PRESENTATION / BITE PHILOSOPHY A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P3000000001 01 FWUT200




CENTRAL MAINTENANCE SYSTEM PRESENTATION TESTS A BITE can perform 4 types of test: - POWER UP TEST, which are safety tests, they check the system integrity. They are carried out on the ground after a power cut, - CYCLIC TESTS, which are executed in flight and do not disturb system operation. It is a permanent monitoring of the system, - SYSTEM TESTS, which enable the maintenance staff to check that the systems are safe for flight and enable trouble shooting. They are carried out on the ground, - SPECIFIC TESTS, which are available for some systems. They generate stimuli to various command devices such as actuators or valves. As they have major effects on the aircraft, they are only executed on the ground. SYSTEM TESTS and SPECIFIC TESTS are initiated manually via the CMCs.





CENTRAL MAINTENANCE SYSTEM PRESENTATION / TESTS A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P3000000001 01 FWUT200




CENTRAL MAINTENANCE SYSTEM PRESENTATION CENTRAL MAINTENANCE COMPUTER Two CMCs are provided: - number one is active, - and number two is a hot standby. A pushbutton is provided for manual transfer from one to the other. The CMCs continuously scan the buses from the aircraft systems. During flight, if a failure message from a BITE is present on a bus, the CMCs copy and store it. The CMCs also store warning messages generated by the FWCs during flight operation. The CMS operator's interface is the MCDU. Only two of the three MCDUs available can be operated simultaneously.





CENTRAL MAINTENANCE SYSTEM PRESENTATION / CENTRAL MAINTENANCE COMPUTER A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P3000000001 01 FWUT200




CENTRAL MAINTENANCE SYSTEM PRESENTATION OPERATION MODES The CMS operates in two modes, a normal mode and an interactive mode. In normal mode, the CMS records fault messages from system BITEs and warnings from the FWCs. In the interactive mode, which is available on the ground only, the CMS allows the operator to retrieve trouble shooting data and to initiate system tests.





CENTRAL MAINTENANCE SYSTEM PRESENTATION / OPERATION MODES A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P3000000001 01 FWUT200




CENTRAL MAINTENANCE SYSTEM PRESENTATION SYSTEM TYPES The systems are of three different types depending on their complexity. Most of the systems are type 1 systems. Type 1 systems can memorize failures that occurred during the last 64 flights. They are connected to both CMCs by an ARINC 429 output bus and to CMC 1 by an ARINC 429 input bus. This enables on ground trouble shooting and interactive testing of the systems and their components. The type 2 systems only memorize failures from the last flight. The output connection is an ARINC 429 bus. A discrete input allows initiation of the system test. The TYPE 3 systems do not generate failure messages. A discrete output indicates the system status. A discrete input permits initiation of the test or reset.





CENTRAL MAINTENANCE SYSTEM PRESENTATION / SYSTEM TYPES A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P3000000001 01 FWUT200




CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION FAILURE CLASSES CJanEuNaTrRAyL03M/0A5INTENANCESYSTEMMES AGESPRESENTATOIN

Failures are divided into three classes depending on the effect they have on the flight.

CLASS 1 FAILURE Class 1 failures are the failures which have an operational consequence to the current flight. Some of them are displayed as a warning in real time on the ECAM and available on the MCDU.

CLASS 2 FAILURE Class 2 failures are the failures which have no operational consequence on the current flight. Some affected systems are identified on the ECAM status page. As for class 1 failures, the maintenance team can identify them on the post flight report.

CLASS 3 FAILURES Class 3 failures have neither operational nor safety consequences on the aircraft. They are not indicated to the flight crew during flight. They are only available on ground through the MCDU class 3 report.





CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION / FAILURE CLASSES A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P4000000001 01 FWUT200




CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION INTERNAL / EXTERNAL FAILURES Failure messages transmitted to the CMCs can be internal or external.

INTERNAL FAILURES If a failure appears within a system, the BITE will send an internal failure message to the CMCs.

EXTERNAL FAILURES The BITE of each system interfacing with the affected system will send an external failure message to the CMCs.





CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION / INTERNAL / EXTERNAL FAILURES A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P4000000001 01 FWUT200




CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION FAILURE MESSAGES STRUCTURE The maintenance messages are all made up of one or several parts. Each part includes the following data : - the name of the suspected component, - its FIN if it is a LRU, - complementary information if necessary.





CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION / FAILURE MESSAGES STRUCTURE A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P4000000001 01 FWUT200




CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION TYPES OF MESSAGE Any part is given in one of these five forms depending on the failure reported: An "LRU (FIN)" message appears when: - either the computer declares itself suspect, - or a computer or a system receiving its signals declares the affected computer as suspect. An "LRU (FIN) COMPLEMENTARY INFO" message appears when the suspected computer is generating several signals. The complementary info helps to identify the suspected signal. A "WRG : SIGNAL NAME" message appears when a wiring failure is identified, with the name of the transmitted signal. An "LRU (FIN) SPLY" message appears when an LRU supply loss is identified without ambiguity. Specific messages are used for some faulty situations that would require a too complex BITE to identify the affected LRU. In these cases, only the operator can identify the faulty LRU. The procedure required is in the Maintenance Manual.





CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION / TYPES OF MESSAGE A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P4000000001 01 FWUT200




CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION AMBIGUOUS / MULTIPLE FAULTS In the case of ambiguous faults, up to three possible failures may be indicated in the most probable order. A "/" sign separates the message parts. In some cases of multiple faults, a BITE may generate a single maintenance message which concerns several defective components. A "+"sign separates the faulty components.





CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION / AMBIGUOUS / MULTIPLE FAULTS A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P4000000001 01 FWUT200




CMS MENUS PRESENTATION CMS MCDU MENUS CJanMuSarMEy0NU3/0S5PRESENTATION

The functions are displayed on a ground and a flight menu. The flight menu presents only a part of the ground menu. The CMS menu switches to flight mode, when at least 3 engines are running for 180 seconds with the flight number inserted (or the aircraft speed is above 80 knots). The ground menu comes back during roll-out, when the aircraft speed is below 80 knots for more than 30 seconds.





CMS MENUS PRESENTATION / CMS MCDU MENUS A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P5000000001 01 FWUT200




CMS MENUS PRESENTATION FLIGHT LEGS A flight LEG starts at startup of the third engine plus three minutes, if the flight plan is available in the Flight Management System (FMS), or speed higher than 80 knots if the flight plan is not available. At the beginning of a new LEG, the content of the POST FLIGHT REPORT is transferred to the previous flight report memory.





CMS MENUS PRESENTATION / FLIGHT LEGS A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P5000000001 01 FWUT200




CMS MENUS PRESENTATION NORMAL MODE In normal mode, the CMCs memorize the fault messages from type 1 and type 2 systems and the fault status from type 3 systems. The three types of system have a different behavior depending on flight phases in the normal mode: - type 1 systems receive CMC data for flight phase synchronization. They memorize failure messages at the start of each flight LEG until 80 knots +30s after touch down. - type 2 systems only memorize failure messages when the aircraft is airborne (i.e. as soon as the landing gear is not compressed). - type 3 systems transmit a permanent signal if they are faulty. In the normal mode, several functions provide aircraft status reports. The CURRENT FLIGHT REPORT function is available on the flight menu. It provides the list of ECAM warnings/cautions and faults related to class 1 and class 2 failures recorded during the current flight. The POST FLIGHT REPORT function is available on the first page of the ground menu. It provides the list of ECAM warnings/cautions and faults related to class 1 and class 2 failures recorded during the last flight. The PREVIOUS FLIGHT REPORT function is available on the first page of the ground menu. It gives the list of the POST FLIGHT REPORTS over the last 63 previous flights.





CMS MENUS PRESENTATION / NORMAL MODE A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P5000000001 01 FWUT200




CMS MENUS PRESENTATION / NORMAL MODE A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P5000000001 01 FWUT200




This Page Intentionally Left Blank





CMS MENUS PRESENTATION INTERACTIVE MODE The SYSTEM REPORT/TEST function of the ground menu enables access to the interactive mode. In the interactive mode, which is available on the ground only, the CMS allows the operator to retrieve troubleshooting data and to initiate system tests.





CMS MENUS PRESENTATION / INTERACTIVE MODE A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P5000000001 01 FWUT200




CMS MENUS PRESENTATION COMPLEMENTARY FUNCTIONS Several complementary functions are available via the MCDU menus. The AVIONICS STATUS function is accessible on both flight and ground menus. It provides a real time list of the systems affected by a fault. The CLASS 3 REPORT function is available on the second page of the ground menu. It provides the list of class 3 faults. The REPORTS PROGRAMMING function allows an automatic print or download of the POST FLIGHT REPORT at engine shut down. The report filter can also be activated from here. The REPORTS FILTERS function allows spurious messages in the flight reports to be filtered. This filter can be inserted either manually via the MCDU or by uploading in the CMCs. The AVIONICS CONFIGURATION REPORTS function manages the inventory of the aircraft computer part numbers and software diskettes. The SERVICING REPORT function provides reports with different parameters which have to be periodically checked and which may induce servicing actions. The UTC/DATE INIT function is accessible on both flight and ground menus. It appears after a long power interrupt of the CMCs. It enables initialization of the backup clock in case of main clock failure.





CMS MENUS PRESENTATION / COMPLEMENTARY FUNCTIONS A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P5000000001 01 FWUT200




MENU NORMAL MODE D/O GENERAL MJanEuNaUrNyO0R3/0M5ALMODED/O

This is the Multipurpose Control & Display Unit (MCDU) menu page which presents the systems connected to the MCDU. From the MAINTENANCE MENU displayed on 2 pages, all the Normal Mode Central Maintenance System (CMS) reports can be shown. These reports will be explained in the following topics, supposing the aircraft on ground and engines shut down.

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D1F45C60301 01 FWUT200




MENU NORMAL MODE D/O / GENERAL A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D1F45C60301 01 FWUT200




MENU NORMAL MODE D/O POST FLIGHT REPORT

topic.

The POST FLIGHT REPORT displays the Electronic Centralized Aircraft Monitoring (ECAM) messages such as WARNINGS/CAUTIONS and MAINTENANCE STATUS messages, and also CLASS 1 and 2 FAULT messages which occurred during the last flight and have been memorized in the Central Maintenance Computer (CMC). It can display a maximum of 64 warnings and 64 faults. The first item of the POST FLIGHT REPORT, are the ECAM messages. The first page contains only one of these messages. If there are several messages, they will be displayed 2 at a time only, on the following pages. In this example, there are 2 ECAM message pages. The ECAM messages are displayed in the order of acquisition by the CMC, minute by minute. The last message memorized is displayed first. If there is no warning, the NO WARNING message will be displayed. From each "warning messages" item page, we can access the first "fault messages" item page by pressing the right arrow key. The first page contains only one message. If there are several messages, they will be displayed 2 at a time only, on the following pages. In this example there are 2 fault message pages.The number of ECAM message item pages and FAULT message item pages is not necessarily the same. The fault messages are displayed in the order of acquisition by the CMC, minute by minute. The last message memorized is displayed first. If there are no failures, the NO FAULT message will be displayed. From each fault message item page, it is possible to go back to the first warning message item page by pressing the left arrow key. In our example, the prompt (<) before the second fault message means that this fault is also detected by other systems as external failures. These systems are called IDENTIFIERS. The IDENTIFIERS page lists the fault message and the name of the systems, other than the source, which detected the fault. A maximum of 6 systems can be displayed. This screen shows a summary of the main pages of the MCDU described in the A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D1F45C60301 01 FWUT200




MENU NORMAL MODE D/O / POST FLIGHT REPORT A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D1F45C60301 01 FWUT200




MENU NORMAL MODE D/O POST FLIGHT REPORT PRINT All the information presented on the POST FLIGHT REPORT on different MCDU screens, is printed together on one page. Extra information is added in this POST FLIGHT REPORT print out. In flight, this report is called the CURRENT FLIGHT REPORT. It can be printed at any time. The ECAM and FAULT messages concerning the same event and recorded in the same minute are printed side by side. The header presents general information about the flight and the report print out. The cockpit effects list presents the ECAM messages. If a warning is generated during a flight phase inhibit it will not be presented to the crew. On the Post Flight Report Cockpit Effects, the warning will be presented and "NOT DISPLAYED" added to the message. The time of warning or fault message occurrence and the name of the flight phase are displayed. The FAULTS list presents intermittent failures and permanent failures called hard failures with their source and their identifiers.





MENU NORMAL MODE D/O / POST FLIGHT REPORT PRINT A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D1F45C60301 01 FWUT200




MENU NORMAL MODE D/O PREVIOUS FLIGHT REPORTS The PREVIOUS FLIGHT REPORTS item gives access to the previous POST FLIGHT REPORTS affected by failures, with a maximum of 64 previous flights. It will display a maximum of 252 warning and fault messages. This report presents the list of the previous flights, 4 per page, and allows access to the corresponding PREVIOUS FLIGHT REPORTS. The flights are presented in reverse order on the MCDU screen. To study the details of these reports, please refer to the POST FLIGHT REPORT topic. In case of CMC removal/installation, if the new CMC comes from another aircraft, the previous POST FLIGHT REPORTS concerning this aircraft will not be displayed. If the new CMC comes from the shop, a pseudo flight (00) is created to indicate the date of the first computer installation on the aircraft.

AVIONICS STATUS In flight or on ground, the AVIONICS STATUS report displays the identity of systems affected by, at least, one CLASS 1 or 2, internal or external failure at the moment of the request. The entire report can be printed. This is the list of systems affected by a failure. If no systems are affected, the NO FAULT message is displayed. On ground, a prompt (<) indicates that a direct access to interactive mode of the selected system is possible. If the SYSTEM REPORT/TEST mode is selected on one of the other MCDUs, the "DUAL SYSTEM ACCESS" message is displayed on the scratchpad line. This screen shows a summary of the main pages of the MCDU described in the topic.





MENU NORMAL MODE D/O / AVIONICS STATUS A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D1F45C60301 01 FWUT200




MENU NORMAL MODE D/O CLASS 3 REPORT This report displays the list of the systems affected by class 3 faults and the failures by system on request. This report is created, on ground only, by the CMC upon selection. A page tells the operator to check that all systems are in normal configuration and enables the CLASS 3 REPORT to be printed. The affected systems list is the one shown on the MCDU. To see the list of the class 3 failures sent to the CMC by a computer, you have to select the corresponding adjacent line key. If there are no failures, the NO FAULT message will be displayed. In the complete CLASS 3 REPORT print out, class 3 failures and affected systems are printed side by side. The header presents general information about the aircraft identification and the report print out. A list presents the systems affected by at least one CLASS 3 fault. A list presents the associated CLASS 3 fault messages.





MENU NORMAL MODE D/O / CLASS 3 REPORT A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D1F45C60301 01 FWUT200




MENU NORMAL MODE D/O COMPLEMENTARY FUNCTIONS Filtering and Report programming functions are available via the second page of the maintenance menu. The SERVICING REPORT and AVIONICS CONFIGURATION REPORT will be studied in dedicated modules.

REPORTS PROGRAMMING This function allows automatic printout and transmission via the Air Traffic Service Unit (ATSU), of the POST FLIGHT REPORT at the end of the flight. It also allows the activation of the report filter. In the displayed configuration, printout and transmission are automatic, but the filter is not activated.

REPORTS FILTERS Remember that this function allows spurious messages in the POST FLIGHT REPORT to be filtered. The purpose of this item is to print the content of the filter database and to transmit the filter database to the opposite CMC. The programming of the filter can be manually performed via a password at engineering level. This screen shows a summary of the main pages of the MCDU described in the topic.





MENU NORMAL MODE D/O / COMPLEMENTARY FUNCTIONS A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D1F45C60301 01 FWUT200




MENU INTERACTIVE MODE D/O GENERAL MJanEuNaUrIyN0T3E/0R5ACTIVEMODED/O

This module is developed by supposing that the aircraft is on ground and engines shut down. From the first page of the MCDU Maintenance Menu, the access to the interactive mode through the System report/Test function is gained. This function ensures the dialog between the MCDUs and each system, type 1, 2, or 3, connected to the Central Maintenance Computers (CMCs), on ground only. The page displayed by the CMC gives the list of all the systems sorted by function in the ATA chapter sequence. This list is displayed on 6 pages, which are shown in the following figures. Each function allows access to the related computers or units dealing with that function.





MENU INTERACTIVE MODE D/O / GENERAL A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D2F45C70601 01 FWUT200




MENU INTERACTIVE MODE D/O TYPE 1 SYSTEM TYPICAL MENU This is a typical type 1 system menu. However, most of the radio-navigation, navigation and communication systems, which are interchangeable with other aircraft, may have a different menu presentation. The following items shown in the table are always available.

LAST LEG REPORT The purpose of this item is to present the internal and external class 1 and 2 fault messages, concerning the system, that appeared during the last flight.

PREVIOUS LEGS REPORT The purpose of this item is to present the internal and external fault messages, concerning the system that appeared during the previous 64 flights. This item is the sum of the LAST LEG REPORT items over several flights.

LRU IDENT The purpose of this item is to present the part number of the selected system. The serial number and the data base number can also be indicated for certain systems.

GROUND SCANNING The purpose of this item is to reconfigure the computer BITE as being in flight. Fault messages Class 1or 2, internal and external Fault messages, detected by the BITE during the activation of this function, are displayed in real time.

TROUBLE SHOOTING DATA The purpose of this item is to present internal snapshot data concerning any failure of any class for airline engineering use. In most cases, it is coded data and sometimes can be accessed from other reports as, LAST LEG REPORT, PREVIOUS LEGS REPORT, TEST and GROUND REPORT.

CLASS 3 FAULTS The purpose of this item is to present the class 3 fault messages, concerning the system, that appeared during the last flight.

TEST The purpose of this item is to initiate tests from the MCDU and display the test results with their failure class. If the test takes more than 1 second, TEST IN PROGRESS xxS and the maximun waiting time are displayed. If several types of test exist for a system, they must be displayed in line 2R, 3R, 4R or even on a sub-menu page accessible from line key 6R. Tests are divided into 3 groups : - Basic or system tests, which have no effect on the aircraft, are accessibles via key 2R. - Complementary tests, which affect the A/C and require safety precaution, are accessibles via key 3R. - Additional tests, which are menu guided tests, are accessibles via key 4R.

GROUND REPORT The purpose of this item is to present the internal fault messages which appeared since the last flight at the moment of the request.




A340-500/600 TECHNICAL TRAINING MANUAL SPECIFIC DATA The purpose of this item is to display specific information in order to help the trouble shooting. If only one type of specific data exists in the system, the exact name will be displayed in place of SPECIFIC DATA. If more than 2 types of SPECIFIC DATA exist in a system, they must be displayed on a sub-menu page accessible from line key 6R.

MENU INTERACTIVE MODE D/O / GENERAL A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D2F45C70601 01 FWUT200









MENU INTERACTIVE MODE D/O / TYPE 1 SYSTEM TYPICAL MENU A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D2F45C70601 01 FWUT200




MENU INTERACTIVE MODE D/O TYPE 1 SYSTEM EXAMPLE MENU To describe the contents of the different items of a type 1 system, it has been chosen the Electric Power Generation System (EPGS), part of the AC ELECTRICAL GENERATION function. The Ground and Auxiliary Power Control Unit (GAPCU) is the interface unit between the EPGS and the CMCs, but as the EPGS is controlled by 6 computers (1 GAPCU and 5 GCUs), an intermediate page is added to choose the computer from which we have selected the report. The EPGS menu, which contains most of the type 1 system items, is shown on the figure and will be explained in the following subtopics.

LAST LEG REPORT This report presents only 2 messages at a time. The fault messages are recorded by the system with the Universal Time Coordinated (UTC) at which the fault occurred, the 6 digit ATA reference and the class of the failure. When no failure has been recorded during the last flight, NO FAULT DETECTED message is displayed on the MCDU.

PREVIOUS LEGS REPORT As the LAST LEG REPORT, this report presents only two messages at a time. The fault messages is identical to the LAST LEG REPORT plus the date at which the failure occurred and the leg number. In addition, the identification of the A/C where the failure occurred is included in the header.

TROUBLE SHOOTING DATA This report presents snapshot coded information. The information presented is aircraft configuration and system configuration. If no failure has been recorded by the system, NO FAULT DETECTED message is displayed on the MCDU.

CLASS 3 FAULT This report presents only 2 messages at a time. The class 3 faults are recorded during the last flight. Only the time and the ATA reference are presented.

SYSTEM TEST This item, which is a system test, enables initialization of the power up test, among other things. All faults detected and presented by the system will be analyzed and reported by this test. If the test is OK, "TEST OK "is displayed on the MCDU.

GROUND REPORT The characteristics of this report are the same as those of the LAST LEG REPORT but limited to the internal failures of any class. The following screens represent a summary of the main screens shown in this topic.

LRU IDENT This report presents: the name, the part number and, in this example, the serial number of the electronic Line Replaceable Units (LRUs) which are included in the EPGS. Only 2 are displayed at a time, and in this example, on 3 pages.





MENU INTERACTIVE MODE D/O / TYPE 1 SYSTEM EXAMPLE MENU A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D2F45C70601 01 FWUT200




MENU INTERACTIVE MODE D/O TYPE 2 SYSTEM TYPICAL MENU Unlike the Type 1 Systems, there is no Menu Mode for the Type 2 Systems. These functions are presented on the MCDU by the CMC (Pseudo mode Menu). The following items shown in the table are always available.

LAST LEG/GND REPORT The purpose of this item is to present the class 1 and 2 fault messages, concerning the system that appeared during the last flight and on ground.

LRU IDENT The purpose of this item is to present the part number of the selected system.

CLASS 3 FAULTS The purpose of this item is to present the class 3 fault messages concerning the system during the last flight.

TEST The purpose of this item is to initiate the system test from the MCDU and to display the test result with its failure class. If the test takes more than 1 second, the CMC displays TEST IN PROGRESS xxS with the maximum waiting time.





MENU INTERACTIVE MODE D/O / TYPE 2 SYSTEM TYPICAL MENU A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D2F45C70601 01 FWUT200




MENU INTERACTIVE MODE D/O TYPE 2 SYSTEM EXAMPLE MENU To describe the contents of the different items of a type 2 system, we have chosen the Battery Charge Limiter 1(BCL 1) , part of the DC ELECTRICAL GENERATION function. This is the BCL 1 menu.

LAST LEG/GND REPORT This report, formatted by the active CMC, presents, only 2 at a time, the fault messages with the 6 digit ATA reference and the class of the failure, which are permanently transmitted by the system. In case of failure detected on ground, after touch down, the fault message will be preceded by "GND".

LRU IDENT This report, formatted by the active CMC , presents the part number of the BCL 1.

CLASS 3 FAULTS This report formatted by the active CMC, presents, only 2 at a time, the class 3 fault messages with the 6 digits, ATA reference, which are permanently transmitted by the system.

TEST During the progress of the test, some information is provided on the MCDU. If the test is OK, the CMC displays "TEST OK" on the MCDU screen. The following screens represent a summary of the main screens shown in the topic.









MENU INTERACTIVE MODE D/O TYPE 3 SYSTEM TYPICAL MENU This is a typical type 3 system menu. The menu is fully generated by the active CMC.

TEST AND RESET The only possible item is TEST function or RESET function. In case of failure, the CMC displays the name of the tested or reset component. If the test or reset is OK the CMC displays "TEST or RESET OK".

TYPE 3 SYSTEM EXAMPLE MENU To describe the contents of the different items, we have chosen 2 examples: Generator Control Unit (GCU) EMERGENCY and then Transformer Rectifier (TR) 1, in the AC and DC GENERATION function.

GCU EMR MENU If the test is OK the CMC displays "TEST OK" on the MCDU screen. If the test is not successful the respective messages will appear on the MCDU screen.

TR 1 MENU If the reset is not successful, the fault message shown on the figure is displayed.









MENU SERVICING D/O GENERAL MJanEuNaUrSyE0R3V/0I5CINGD/O

This function provides reports with different parameters, which have to be periodically checked, and which may induce servicing actions. The servicing report is accessible through the MCDU. It can also be printed, dumped if a data loader is installed, or transmitted to the Air Traffic Service Unit (ATSU) via the Aircraft Communication Addressing and Reported System function (ACARS function).

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D4F45SA0201 01 FWUT200




MENU SERVICING D/O / GENERAL A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D4F45SA0201 01 FWUT200




MENU SERVICING D/O REPORT The report is available either in flight or on ground. The servicing report is composed of the different items listed in the table as: - Engines - Integrated Drive Generator (IDG) - APU - Hydraulic - Fuel - Landing gear - Oxygen - Door and slide bottles - Water/waste - Air conditioning The servicing report can be presented in 3 ways. These are: complete format, coupon mode printout and MCDU presentation that will be shown next.

COMPLETE FORMAT In this case the report is composed of all servicing and summary items presented on two pages. The report shown in the next figure is presented as an example.





MENU SERVICING D/O / REPORT A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D4F45SA0201 01 FWUT200




MENU SERVICING D/O REPORT (CONTINUED) COUPON MODE The purpose of this is to present to the user only items needing action. First, a SUMMARY COUPON is printed, followed by the items where a parameter is under the minimum or above the maximum value of a threshold. If a servicing item status is "CHECK" in the summary coupon, the summary coupon will be followed by the servicing item coupon, otherwise the status is OK.





MENU SERVICING D/O / REPORT (CONTINUED) A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D4F45SA0201 01 FWUT200




MENU SERVICING D/O REPORT (CONTINUED) MCDU PRESENTATION The servicing report, which is displayed on MCDU is complete and therefore includes all parameters. It consists of 11 MCDU pages. Pressing the up and down arrow keys gives you access to the next (or previous) pages that make up the servicing report.





MENU SERVICING D/O / REPORT (CONTINUED) A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D4F45SA0201 01 FWUT200




MENU SERVICING D/O PROGRAMMING It is possible to program, through the MCDU, certain functions related to the servicing report. You can program a complete report or a coupon mode report. You can also program the automatic transmission to the printer, the ATSU via the ACARS function, and the Multipurpose Disk Drive Unit. Non programmed printouts, dumps or transmissions to the ground have to be made manually.





MENU SERVICING D/O / PROGRAMMING A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D4F45SA0201 01 FWUT200




MENU SERVICING D/O THRESHOLD AND TEXT INSERTIONS The airline engineering first needs to define the various thresholds which will be used for the servicing report. The purpose of these thresholds is to automatically trigger a coupon if they are exceeded. The airline can also add comments and information texts between the coupons. Report threshold and text insertions are made on a personal computer using software called a Maintenance Option Tool (MOT). Then, when this programming is made, it is loaded in the Central Maintenance Computers (CMCs) using the data loader, if installed. The servicing report thresholds and information texts database is printed automatically after uploading. Manual printing of the servicing report thresholds and information texts data base can be done through an MCDU menu. The report shown in the next figure is presented as an example.





MENU SERVICING D/O / THRESHOLD AND TEXT INSERTIONS A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D4F45SA0201 01 FWUT200




MENU AVIONICS CONFIGURATION D/O GENERAL MJanEuNaUrAyV0I3O/0N5ICSCONFIGURATIOND/O

This function is used to manage the inventory of the aircraft computer part numbers and software diskettes. It is only available on ground and with the Central Maintenance Computer 1 (CMC1). From the CMS MCDU MENU, the function AVIONICS CONFIGURATION REPORTS enables access to: - the EQUIPMENT CONFIGURATION REPORT - DISKETTE CONFIGURATION REPORT, and - CONFIGURATION CHANGE

EQUIPMENT CONFIGURATION REPORT This item displays the list of computer part numbers and, for some, the serial number and/or the data base number. The part number and serial number are directly read from the computer memory or On Board Replaceable Modules, thus no updating is necessary.

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D5F45AA0101 01 FWUT200




MENU AVIONICS CONFIGURATION D/O / EQUIPMENT CONFIGURATION REPORT A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D5F45AA0101 01 FWUT200




MENU AVIONICS CONFIGURATION D/O EQUIPMENT CONFIGURATION REPORT CONT´D They are displayed on the MCDU or they can be printed.





MENU AVIONICS CONFIGURATION D/O / EQUIPMENT CONFIGURATION REPORT CONT´D A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D5F45AA0101 01 FWUT200




MENU AVIONICS CONFIGURATION D/O DISKETTE CONFIGURATION REPORT The purpose of this item is to record and check the version of these floppy disks. On each aircraft, a set of floppy disks is available in the cockpit. They contain databases necessary for the operation of some computers. The diskette configuration report is first defined by the airline engineering using a Maintenance Option Tool (MOT), then loaded in CMC1. The CMC will keep this report updated because it can read the data base numbers directly from the computers. This report is displayed on the MCDU or can be printed.





MENU AVIONICS CONFIGURATION D/O / DISKETTE CONFIGURATION REPORT A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D5F45AA0101 01 FWUT200




MENU AVIONICS CONFIGURATION D/O DISKETTE CONFIGURATION REPORT CONT´D Pushing the line key adjacent to Avionics Configuration Reports gives you access to the different MCDU screens as presented in the following example.





MENU AVIONICS CONFIGURATION D/O / DISKETTE CONFIGURATION REPORT CONT´D A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D5F45AA0101 01 FWUT200




MENU AVIONICS CONFIGURATION D/O CONFIGURATION CHANGE This function is designed to validate the part number, data base number and software reference changes through the Central Maintenance System (CMS), and is presented on the MCDU only if new part numbers are detected by the CMS. The philosophy is that if a person changes a computer part number, creating a new part number then the change is checked and validated on the MCDU by another person called the controller. The items of equipment that are listed are those for which the change has not yet been validated. A password will be entered to validate the new part number. After validation, the equipment disappears from the list. It is still available in the Equipment Configuration Report. The configuration change report can be printed through the MCDU. The screens and reports are presented as an example.





MENU AVIONICS CONFIGURATION D/O / CONFIGURATION CHANGE A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D5F45AA0101 01 FWUT200




MENU AVIONICS CONFIGURATION D/O PROGRAMMING It is possible to program the automatic transmission of the configuration change report, to the printer, the ATSU via the ACARS function, or the data loader. Non programmed printouts, dumps or transmissions to the ground have to be made manually.





MENU AVIONICS CONFIGURATION D/O / PROGRAMMING A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D5F45AA0101 01 FWUT200




MESSAGE D/O GENERAL MJanEuSaArGyE03D/05O

A maintenance message is generated by the system BITE each time a fault is detected and isolated. This message is memorized in the BITE memory and transmitted to the Central Maintenance Computers (CMCs). The maintenance message must indicate, as directly as possible, the faulty Line Replaceable Unit (LRU). Each message is limited to a maximum of 48 characters in 2 lines of 24 characters. It can be composed of one or several parts depending on the number of suspected LRUs. In addition, the ATA 6-digit reference of the suspected LRU is provided. Even if the message is composed of several suspected LRUs, only one suspected element is faulty. Each part of the maintenance message is composed in accordance with the syntax presented in the next figure.

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D6F45F10101 01 FWUT200




MESSAGE D/O / GENERAL A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D6F45F10101 01 FWUT200




MESSAGE D/O MESSAGE CATEGORIES Any part of these maintenance messages necessarily belongs to one of the 5 categories presented as follows.

CATEGORY 1 When a computer requires maintenance, this may be detected and declared by the computer itself, or a system using the computer. In this case an LRU(FIN) message appears.

CATEGORY 2 In this category, the primary suspected element is a computer generating several signals. The complementary information makes it possible to identify the suspected signal. This signal may be controlled on the aircraft. In this case LRU Functional Item Number (FIN) complementary information messages appear, for example as LRU(FIN) SIGNAL NAME, LRU(FIN) BUS NAME and LRU(FIN) DISCRETE NAME.





MESSAGE D/O / MESSAGE CATEGORIES A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D6F45F10101 01 FWUT200




MESSAGE D/O MESSAGE CATEGORIES (CONTINUED) CATEGORY 3 Wiring is only indicated when the conclusion of the BITE analysis is a wiring fault. The wiring can always be involved even if there is no mention of wiring in the message. In this case wiring signal name messages appear. Some of these messages are shown on the following figure.

CATEGORY 4 These are cases where precise identification of the faulty LRU would require a too complex BITE. In this case SPECIFIC messages appear. In this type, only an analysis of the problem by the technicians makes it possible to identify the component involved. The procedure to be followed is described in the TROUBLE SHOOTING MANUAL (TSM).

CATEGORY 5 The part of the message belongs to this type when the loss of LRU power supply is unambiguously identified. The LRU power supply must then be precisely checked before LRU replacement. In this case LRU(FIN)Sply messages appear. It should be noted that the LRU itself may be one of the causes for this loss of supply.





MESSAGE D/O / MESSAGE CATEGORIES (CONTINUED) A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D6F45F10101 01 FWUT200




MESSAGE D/O MESSAGE CONSTRUCTION In case of ambiguous faults, up to 3 possible faulty LRUs may be indicated in the most probable order, each possibility being separated by the slash sign ("/ "). Only one component is effectively responsible. In some cases of multiple faults, it is possible that a BITE generate a single maintenance message, which may concern several defective components. These components are then separated by the plus sign ("+"), LRU1(FIN)+LRU2(FIN). The ATA reference next to the message corresponds to the first suspected component. When the "FIN" part of the message is absent, this means that no LRU is directly involved in this part. The possible combinations are shown as follows, for example: LRU1(FIN)/LRU2(FIN) LRU1(FIN) BUS NAME/LRU2(FIN) Two examples are shown in case of LRU1 (FIN)/WRG type. LRU2 BUS NAME TO LRU1... And LRU1 (FIN)/SPECIFIC/SPECIFIC. And lastly, SPECIFIC/LRU1 (FIN).





MESSAGE D/O / MESSAGE CONSTRUCTION A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D6F45F10101 01 FWUT200




MESSAGE D/O MESSAGE HANDLING Each Central Maintenance System message is covered by the TSM and is an entry point to trouble shooting.





MESSAGE D/O / MESSAGE HANDLING A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D6F45F10101 01 FWUT200




MESSAGE PROCESSING D/O GENERAL PARAMETERS MJanEuSaArGyE03P/0R5OCES INGD/O

The Central Maintenance Computer (CMC) acquires and dispatches general information to the type 1 systems. and is the interface between the main clock and the system BITEs, which use time and date data. If the main clock has failed, the CMC back-up clock takes over. The CMC is the interface between the Flight Management Guidance and Envelope Computers (FMGECs) and the systems, which use Flight Number and City Pair, such as the Air Traffic Service Unit (ATSU) and the Aircraft Condition Monitoring System (ACMS) only. The CMC is the interface between the Digital Flight Data Recording System (FDRS) and the system BITEs which use the Aircraft Identification. In addition to its own warnings, the CMC processes the FDRS and ACMS warnings, which are sent to the Flight Warning Computers (FWCs). The CMC is the interface between the FWCs and the system BITEs concerning the flight phases. The CMC transmits the aircraft configuration, which is processed by pin programming to all type 1 system BITEs. This configuration is used to know the installation of optional equipment. The CMC processes the DC1, DC2 and NULL maintenance phases independently from the flight phases and transmits them to all type 1 systems. These maintenance phases control the memorization of the BITE data and the leg management. For the constitution of these maintenance phases, the CMC receives the information included in the table shown in the next figure: Type 2 systems process their own FLIGHT/GROUND condition and consequently manage their own data, whereas in type 1 systems, this condition is given by the maintenance phases sent by the CMC. The CMC must process a FLIGHT/GROUND condition to manage type 2 system BITE data. It (the CMC) considers type 2 systems 'in flight' after takeoff and on ground' after "landing gear compressed". Note: for type 1 systems, the flight condition is given by the NULL maintenance phase while the ground condition is given by the DC1+DC2 maintenance phases, sent by the CMC. A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D7F45C80101 01 FWUT200




MESSAGE PROCESSING D/O / GENERAL PARAMETERS A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D7F45C80101 01 FWUT200




MESSAGE PROCESSING D/O CENTRAL MAINTENANCE COMPUTER /TYPE 1 SYSTEM The fault processing, memorization and transmission to the CMC is different in each maintenance phase.

DC2 MAINTENANCE PHASE When the leg starts, in the type 1 system computer, the contents of the LAST FLIGHT memory are transferred to the PREVIOUS FLIGHTS memory. The GROUND and the CLASS 3 FAULT memories are erased in the CMC, and the contents of the POST FLIGHT memory zone are transferred to the PREVIOUS FLIGHT memory zone. When an internal class 1 or class 2 fault occurs, after detection and isolation of the faulty Line Replaceable Unit (LRU), the BITE processes a fault message, which is stored in the system BITE memory and transmitted to the CMC, where it is also memorized. At the same time, if there is a warning message, it is also memorized by the CMC. The AVIONICS STATUS zone memorizes the name of the system affected as long as an external or internal fault is present. If an internal class 3 fault occurs, it is memorized in the system BITE memory.


DC1 MAINTENANCE PHASE When an internal or external class 1 or class 2 fault occurs, after detection and isolation of the faulty LRU, the BITE processes a fault message, which is stored in the system BITE memory and transmitted to the CMC, where it is also memorized. At the same time, if there is a warning message, it is also memorized by the CMC. The AVIONICS STATUS zone memorizes the name of the system affected as long as the fault is present. If a class 3 fault occurs, it is only memorized in the system BITE memory. At the end of the flight, DC1/NULL transition, the CMC reanalyzes the fault message consolidation, to determine if it is HARD OR INTERMITTENT, and processes the POST FLIGHT REPORT, according to the spurious message filter, which is applied.

NULL MAINTENANCE PHASE The system BITE transmits to the CMC, fault messages of any class, which are due to faults detected in the last flight. This is used to feed the "class 3 zone" when the CLASS 3 REPORT is requested. When an internal fault of any class occurs, after detection and isolation of the faulty LRU, the BITE processes a fault message which is stored in the system BITE ground memory only. The AVIONICS STATUS zone memorizes the name of the system affected as long as an external or internal fault is present. If an internal class 3 fault occurs, it is memorized in the system BITE memory.




MESSAGE PROCESSING D/O / CENTRAL MAINTENANCE COMPUTER /TYPE 1 SYSTEM A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D7F45C80101 01 FWUT200




MESSAGE PROCESSING D/O CENTRAL MAINTENANCE COMPUTER/TYPE 2 SYSTEM For type 2 systems, the leg starts at take-off.

FLIGHT MAINTENANCE PHASE When the leg starts, the flight and ground system BITE memories are erased. When an internal or external fault of any class occurs, after detection and isolation of the faulty LRU, the BITE processes a fault message, which is stored in the system BITE memory and transmitted to the CMC, where it is also memorized, except for class 3 faults. At the same time, if there is a warning message, it is also memorized by the CMC. The AVIONICS STATUS zone memorizes the name of the system as long as the fault is present.

GROUND MAINTENANCE PHASE The system BITE transmits to the CMC, fault messages of any class, which are due to internal faults detected in the last flight. This is used to feed the "class 3 zone" when the CLASS 3 REPORT is requested. The type 2 system fault message consolidation is reanalyzed by the CMC at the DC1/NULL transition to process the Post Flight Report. When an internal fault of any class occurs, after detection and isolation of the faulty LRU, the BITE processes a fault message in the system BITE ground memory and transmits it to the CMC to update the AVIONICS STATUS zone. The AVIONICS STATUS zone memorizes the name of the system as long as the fault is present.





MESSAGE PROCESSING D/O / CENTRAL MAINTENANCE COMPUTER/TYPE 2 SYSTEM A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D7F45C80101 01 FWUT200




MESSAGE PROCESSING D/O CENTRAL MAINTENANCE COMPUTER/TYPE 3 SYSTEM The type 3 system BITE has no memory.

DC 1+ DC 2 MAINTENANCE PHASE When a type 3 system unit fails, the system status is sent to the CMC. The CMC processes the class 1 fault message and stores it in its CURRENT FLIGHT memory zone. At the same time, if there is a warning message, it is also memorized. The AVIONICS STATUS zone memorizes the name of the system as long as the fault is present. The CMC consolidates the fault status at DC1/NULL transition to process the POST FLIGHT REPORT.

NULL MAINTENANCE PHASE The system status is continuously sent to the CMC, but only the AVIONICS STATUS zone is updated (No memorization). The AVIONICS STATUS zone memorizes the name of the system as long as the fault is present.





MESSAGE PROCESSING D/O / CENTRAL MAINTENANCE COMPUTER/TYPE 3 SYSTEM A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D7F45C80101 01 FWUT200




MESSAGE PROCESSING D/O CORRELATION The purpose of correlation is to group all the fault messages related to the same event. The association provided between fault messages and ECAM messages on the Post Flight Report print-out, is also a correlation: it is based on time and on the ATA references. When a fault message "A" appears, the CMC opens a correlation item. During 1 mn, it associates all the fault messages with the same ATA chapter identification, taking the first 3 or 4 digits, and memorizes, in the correlation item, only the name of the first 6 systems (called IDENTIFIERs) which sent the fault messages. The CMC also associates the fault messages generated by other systems, operationally affected by this failure, which is an external failure for them. Remember that the fault messages are always memorized in their own system BITE memories. After 1 mn, the IDENTIFERS item is closed. 9 correlation items can be opened at the same time. If the message "A" is an internal fault message, it is displayed with its associated source. If it is an external fault message, it is displayed only if there is no internal message concerning the same event. Otherwise, the internal fault will be displayed instead.





MESSAGE PROCESSING D/O / CORRELATION A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D7F45C80101 01 FWUT200




BACK UP FUNCTIONS D/O NORMAL OPERATION BJanAuCaKryUP0F3U/0N5 CTOINSD/O

In normal operation, the main clock provides date and time data to the ECAM and the Aircraft System computers through Central Maintenance Computer (CMC) 1 or CMC 2. The latter cyclically check and validate the time and the date from the clock every second.

ABNORMAL OPERATION In case of main clock failure, the active CMC internal clock takes over. The CMC internal clock supplies time and date to the ECAM and the Aircraft System computers. In addition, if a long power interrupt affects both CMCs, for more than 5 seconds, the Universal Time Coordinate (UTC)-DATE INIT item is added in the Central Maintenance System menu. In this case time and date are no longer provided to the ECAM and Aircraft System computers. These functions enable the crew to initialize the time and date. In this menu, UTC and date can be initialized by entering data in the scratchpad and by pressing the corresponding INIT key. Supposing that you have already initialized the date and entered the UTC in the scratchpad, you have to validate it by pressing the correct key.

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D8F45D80301 01 FWUT200




BACK UP FUNCTIONS D/O / ABNORMAL OPERATION A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D8F45D80301 01 FWUT200




PRINTER PRESENTATION GENERAL PJRanuINaTrEyR0P3R/0E5SENTATION

The printer is used for printing Central Maintenance System reports and other system reports. It is loaded with a 8.5 inch (216 mm) wide paper roll.

CONTROLS The printer face features two pushbutton switches and two annunciator pushbutton switches. The TEST switch is used to perform a functional test of the printer. The SLEW switch is used to feed the paper out. The PAPER ALARM switch includes an amber caution light which illuminates if a new paper roll is required. The OFF switch is used to switch the printer ON or OFF. It includes a status indicator light which illuminates if the printer is set OFF.





PRINTER PRESENTATION / CONTROLS A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P6000000001 01 FWUT200




PRINTER D/O GENERAL

CENTRAL MAINTENANCE SYSTEM

Several systems can be connected to the printer, which uses a multiplexed input receiver, so that the printer is in communication with only one of the possible source systems at a time. The input data is transmitted on ARINC 429 buses and is ready to be printed. The output data is transmitted on a single low speed ARINC 429 bus to indicate the printer status (Ready, Busy, etc...). The printer is usually connected to the following systems: - the Flight Management Guidance and Envelope Computers (FMGECs). - the Central Maintenance System (CMS). - the Engine Interface and Vibration Monitoring Units (EIVMU). - the Air Traffic Service Unit (ATSU). - the Aircraft Condition Monitoring System (ACMS). Some examples of prints are given hereafter.

The CMS is connected to the printer in order to print fault reports for maintenance in flight or on ground. When the last engine is shut down, a Post Flight Report may be automatically printed. It is possible to print data displayed on the MCDU by pressing the Print line select key.

PJRanuINaTrEyR0D3/0O5

FLIGHT MANAGEMENT GUIDANCE AND ENVELOPE COMPUTERS The FMGECs are connected to the printer so the following types of report can be printed: - Flight plans, - take-off data, - wind data - and flight reports. The print function allows various Flight Management (FM) reports to be printed, either automatically or manually. The FM pre-flight report becomes available when the current flight phase is PREFLIGHT, whether or not any data has actually been entered.

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D9F45P40301 01 FWUT200

ENGINE INTERFACE VIBRATION MONITORING UNIT Each EIVMU automatically constitutes a report in case of an excessive vibration level or upon a manual request, before the flight, via the CMS in interactive mode. The report is stored in the EIVMU in a volatile memory. Therefore it may be lost before printing in case of a power supply interruption. The report is printed on ground as soon as the engine shuts down. The MCDU page is accessed from the MCDU EIVMU main menu page and allows frequency analysis acquisition requests. When all the values are correctly entered the request is validated by pressing on the RETURN key.

AIR TRAFFIC SERVICE UNIT The ATSU is connected to the printer in order to print: - The data elaborated by itself received from the ground and from peripheral computers and the data entered by the MCDUs.

AIRCRAFT CONDITION MONITORING SYSTEM The ACMS collects data from aircraft systems and formats it to suit various standard reports, which can be printed. The ACMS report prints can be done manually via the MCDU or automatically. Depending on programming, some reports can be triggered and then printed by the remote ACMS print push button. 45 - ONBOARD MAINTENANCE SYSTEMS



PRINTER D/O / AIRCRAFT CONDITION MONITORING SYSTEM A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45D9F45P40301 01 FWUT200




UP AND DOWN LOADING SYSTEM PRESENTATION GENERAL UJanPAuaNrDy0O3/0W5NLOADINGSYSTEMPRESENTATION

The Data loading system includes: - a Data Loading Selector (DLS) located on the overhead panel to select the target computer, - a Multipurpose Disk Drive Unit (MDDU) to upload or download data from or to a disk unit, - a Data Loading Routing Box (DLRB) to route the input/output data between the disk unit and the target computer.





UP AND DOWN LOADING SYSTEM PRESENTATION / GENERAL A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P7000000001 01 FWUT200




UP AND DOWN LOADING SYSTEM PRESENTATION UPLOADING FUNCTION The onboard computers use the uploading function to update their data bases or to modify part of their operational software. The operator selects the target computer using the "PREV" or "NEXT" pushbutton of the DLS. A 3.5 inch disk, containing the data to be transferred, is inserted in the MDDU and the MDDU sends the data to the target computer via the DLRB.





UP AND DOWN LOADING SYSTEM PRESENTATION / UPLOADING FUNCTION A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P7000000001 01 FWUT200




UP AND DOWN LOADING SYSTEM PRESENTATION DOWNLOADING FUNCTION The downloading function is used to transfer to a 3.5 inch disk the data recorded by certain computers during aircraft operation. This disk-stored data can be directly analyzed on the ground by the airlines on a suitable data processing tool. The DLS is used to select the target computer from which the data has to be downloaded.





UP AND DOWN LOADING SYSTEM PRESENTATION / DOWNLOADING FUNCTION A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P7000000001 01 FWUT200




UP AND DOWN LOADING SYSTEM D/O GENERAL UJanPAuaNrDy0O3/0W5NLOADINGSYSTEMD/O

The up and down data loading system is defined as an interface between the onboard computers and the ground-based data processing stations (PCs). The system has two functions, a main uploading function and a downloading function. From a data processing media (3.5 inch disk), the onboard computers use the uploading function to update their databases or to modify part of their operational software (no OBRM on the front face of the computers). The downloading function is used to transfer to a 3.5 inch disk the data recorded by certain computers during aircraft operation. This disk-stored data can be directly analyzed on ground by the airlines. Note that all the computers involved by the system use the uploading function. Only a limited number also use the downloading function. Interconnection between the onboard data loader, called Multipurpose Disk Drive Unit (MDDU), and the onboard computers using the system, called target computers, is mainly ensured by input and output ARINC 429 buses. Loading operation is basically controlled by the Data Loading Routing Box (DLRB) by means of the Data Loading Selector (DLS).

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45DALOADGDO01 01 FWUT200




UP AND DOWN LOADING SYSTEM D/O / GENERAL A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45DALOADGDO01 01 FWUT200




UP AND DOWN LOADING SYSTEM D/O SYSTEM DESCRIPTION DLRB/DLS The interface between the DLRB and the DLS is achieved through two RS422 bi-directional serial links (for dialog and maintenance purposes) and two discretes. The DLS sends user commands to the DLRB and displays the result of these commands on its LCD screen. The list of the computers displayed on the DLS is extracted from the DLRB database. This database has to be uploaded to fit the aircraft configuration (by selecting the DLRB itself in the list of targets). The DLRB and the DLS only operate in ground condition, right hand main landing gear shock absorber compressed, according to the discrete signal sent by Landing Gear Control and Interface Unit 1 (LGCIU 1). Note that the DLS ON/OFF selector switch is used to activate the DLRB through the ON/OFF discrete and not to command the DLS power supply. The DLS power is supplied by the DLRB through the POWER SUPPLY discrete.

LOAD ENABLE A LOAD ENABLE discrete, depending on the state of the LGCIU 1 discrete signal, is wired to each target computer to enable the loading functions on ground and inhibit them in flight.


TARGET COMPUTERS The target computers can be separated into two groups. Most of the computers (up to 26) belong to the first group. These computers are connected to the DLRB by two ARINC 429 buses. The DLRB routes the data to be transferred between the MDDU and the computer selected on the pull-down menu of the DLS. The three computers belonging to the second group have direct ARINC 429 links with the MDDU. In addition, these computers are internally programmed so that they will not consider the LOAD ENABLE discrete signal for downloading operations. As a consequence, for the computers of the second group, the downloading function is also operational in flight.

SYSTEM TYPES The DLRB/DLS is a type 3 system. Note that the DLS BITE is first processed by the DLRB (via RS422). The MDDU is a type 2 system with the following particularity: Instead of a discrete, this is the Central Maintenance Computer (CMC) to MDDU ARINC 429 bus, required for downloading operations, which is also used by the CMC to activate the MDDU test.




UP AND DOWN LOADING SYSTEM D/O / SYSTEM DESCRIPTION A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45DALOADGDO01 01 FWUT200




UP AND DOWN LOADING SYSTEM D/O SEMI-AUTOMATIC LOADING OPERATION The semi-automatic loading mode is used, on ground only, for either uploading or downloading operations. Before performing a semi-automatic loading operation, refer to the relevant procedure for the corresponding system in the Aircraft Maintenance Manual (AMM). The operator actions are limited to: - first, selecting the target computer on the pull-down menu of the DLS (e.g. FMGEC 1 for NAV database uploading), - then, inserting in the disk drive the relevant disk containing the configuration file in which is defined the data to be transferred. 1) Until the disk is inserted in the drive, the system is in the standby state and the "<< MDDU READY >>" message is displayed on the MDDU. Once the disk is inserted, several automatic actions occur with associated MDDU messages. 2) The MDDU is activated and reads the configuration file ("READY" message). 3) The MDDU processes the information contained in the configuration file and a bi-directional protocol dialog is initiated through the ARINC 429 buses between the MDDU and the target computer ("WAIT RESPONSE" message). 4) As soon as the dialog is established, the data is transferred ("TRANSF IN PROG" message). 5) When the data transfer is terminated and no anomalies are detected, the "TRANSF COMPLETE" message is displayed to inform the operator that the transfer is successfully completed. Then, in case of uploading, the operator has to check on the relevant MCDU page that the reference of the uploaded software corresponds to the software reference of the disk used for uploading. Note that, for a semi-automatic downloading, a quick and automatic uploading is first performed to configure the target computer before downloading. That is the reason why, whatever the target computer is, semi-automatic downloading is never possible in flight.





UP AND DOWN LOADING SYSTEM D/O / SEMI-AUTOMATIC LOADING OPERATION A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45DALOADGDO01 01 FWUT200




UP AND DOWN LOADING SYSTEM D/O MANUAL LOADING OPERATION The manual loading mode is only used, either on ground or in flight, for specific downloading operations (e.g. POST FLIGHT REPORT DUMP from the CMCs or SAR unload from the Data Management Unit (DMU) part of the Flight Data Interface and Management Unit (FDIMU)). A manual downloading operation differs from a semi-automatic downloading operation by the two following main points: - no selection is made from the DLS. The data to be transferred is manually selected on the relevant MCDU page - the configuration file contained in the inserted disk only defines the label of the target computer. Note that, in case of an empty or unformatted disk, downloading is nevertheless possible following a successful identification procedure between the MDDU and the target computer.





UP AND DOWN LOADING SYSTEM D/O / MANUAL LOADING OPERATION A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45DALOADGDO01 01 FWUT200




ON BOARD MAINTENANCE SYSTEM TEST GENERAL OJanNuaBrOAyR0D3/0M5AINTENANCESYSTEMTEST

The On board Maintenance System (OMS) BITE is split into a Central Maintenance System (CMS) BITE, an up and down data loading system BITE and a report printing system BITE. The CMS BITE is located in both Central Maintenance Computers (CMCs). They report their related failure information to each other and to their integral maintenance function. The up and down data loading system BITE is located in the Data Loading Routing Box (DLRB) and the Multipurpose Disk Drive Unit (MDDU). Each one provides an interface with the CMC. The DLRB reports its own failures and those related to the Data Loading Selector (DLS). The MDDU reports its own failures only. The report printing system BITE is located in the onboard printer. It provides an interface with the CMC and reports its failures to it. The OMS system BITE information is available through the MCDU SYSTEM REPORT TEST page ATA 45 MAINTENANCE.

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P8MCDUTST01 01 FWUT200




ON BOARD MAINTENANCE SYSTEM TEST / GENERAL A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P8MCDUTST01 01 FWUT200




ON BOARD MAINTENANCE SYSTEM TEST CMS MCDU MENU CAPABILITY The CMS can be interrogated for failure report display and testing by selection of the ATA 45 MAINTENANCE ON BOARD MAINT SYSTEM key on the SYSTEM REPORT / TEST page. The selection of one of the 2 CMCs gives access to the related CMC BITE page. Each CMC is a type 1 computer with a BITE menu providing a GROUND SCANNING and specific functions like TEST and CURRENT REPORT. The TEST function permits the operator to trigger an automatic test of the CMC internal circuits as well as of the ARINC 429 and / or discrete interface with peripheral systems. Note that the master CMC cannot be tested, "no prompt" appears adjacent to the TEST line Key. Only the slave CMC test is enabled. The CURRENT REPORT displays information related to the aircraft configuration (PIN program etc...), to the uploading of CMC data bases from a data loader, to the peripherals status and to the value of the discrete ports.





ON BOARD MAINTENANCE SYSTEM TEST / CMS MCDU MENU CAPABILITY A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P8MCDUTST01 01 FWUT200




ON BOARD MAINTENANCE SYSTEM TEST REPORT PRINTING SYSTEM MCDU MENU CAPABILITY The PRINTER can be interrogated for failure report display and testing by selection of the ATA 45 MAINTENANCE ON BOARD MAINT SYSTEM key on the SYSTEM REPORT / TEST page. The selection of PRINTER gives access to the related PRINTER BITE page. The PRINTER is a type 2 computer with a BITE menu providing a specific TEST function. When the TEST is initiated, a power up test of the on board printer is done and a test pattern is printed out to check the print head condition, the input ports status, the printer P/N and the paper advance motor.





ON BOARD MAINTENANCE SYSTEM TEST / REPORT PRINTING SYSTEM MCDU MENU CAPABILITY A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P8MCDUTST01 01 FWUT200




ON BOARD MAINTENANCE SYSTEM TEST UP/DOWN DATA LOADING SYSTEM MCDU MENU CAPABILITY The MDDU and DLRB-DLS can be interrogated for failure report display and testing by selection of the ATA 45 MAINTENANCE ON BOARD MAINT SYSTEM key on the SYSTEM REPORT / TEST page.

MDDU - MCDU MENU CAPABILITY The selection of the MDDU gives access to the related MDDU BITE page. The MDDU is a type 2 computer with a BITE menu providing a specific TEST function. The test function permits a check of the MDDU internal circuits. Note that to perform this test, a test disk stored in the flexible panel of the COAT storage compartment must be inserted in the MDDU before the test is activated.

DLRB DLS - MCDU MENU CAPABILITY The selection of the DLRB-DLS gives access to the related DLRBDLS BITE page. The DLRB-DLS is a type 3 system with a BITE menu providing a specific TEST function. This self-test allows the maintenance operator to check the internal status of the DLRB and of the DLS through the DLRB BITE facility. It is identical to the test performed systematically at power-up.





ON BOARD MAINTENANCE SYSTEM TEST / UP/DOWN DATA LOADING SYSTEM MCDU MENU CAPABILITY A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45P8MCDUTST01 01 FWUT200




ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE PROCEDURE TO LOAD THE DATA BASE OF THE CMC (DLS/DLRB) OJanNuaBrOAyR0D3/0M5AINTENANCESYSTEMLINEMAINTENANCE

The Central Maintenance Computer (CMC) data base is made up of a CMC filter database, a servicing report database and a diskette configuration database. Each database must be individually prepared prior to the loading of the entire CMC database, by using the appropriate MAINTENANCE TOOL.

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45Y1LINEMCE01 01 FWUT200




ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE / PROCEDURE TO LOAD THE DATA BASE OF THE CMC (DLS/DLRB) A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45Y1LINEMCE01 01 FWUT200




ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE PROCEDURE TO LOAD THE DATA BASE OF THE CMC (DLS/DLRB) (CONTINUED) LOADING OF THE DATA BASE OF THE CMC Note: This procedure is similar for any computer, which can receive uploads through the up and down loading system Switch the DLS ON and check that MDDU is ready. Check that the targeted CMC is not selected on the DLS. Reset both CMCs by using their respective circuit breaker. Select the targeted CMC through the DLS. Insert the prepared disk into the MDDU, monitor the data base transfer and make a check on completion . Note that if a problem occurs during the uploading procedure and that the "TRANSFER COMPLETE" indication is not shown at the end, you must do the procedure again in order to ensure that the computer is fully loaded with data. Deselect the targeted CMC on DLS. Perform the same procedure for the opposite CMC. Wait for completion of the automatic data base content printout and remove the disk. Deselect the target CMC and switch the DLS OFF.





ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE / PROCEDURE TO LOAD THE DATA BASE OF THE CMC (DLS/DLRB) (CONTINUED) A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45Y1LINEMCE01 01 FWUT200




















ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE PROCEDURE TO LOAD THE DATA BASE OF THE CMC (DLS/DLRB) (CONTINUED) DO A CHECK ON THE MCDU OF THE REFERENCE OF THE DATA LOADED INTO BOTH CMCS From the SYSTEM REPORT/TEST page get access to the target CMC bite menu. Make sure that the data base reference shown on the LRU IDENTIFICATION page is the same as the disk data base reference. Note: The three first digits refer to the CMC filter Data Base Number (DB/N), the three following ones refer to the servicing report data base and the three last digits to the diskette configuration data base. Return to the SYSTEM REPORT/TEST page. Perform the same check for opposite CMC.









ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE ENABLE/DISABLE OF THE FLIGHT REPORT FILTER From the second page of the MAINTENANCE MENU access the first REPORTS PROGRAMMING page. Push the FILTER ACTIVATED toggle key to activate or inhibit the flight report filtering. Check the MCDU programming display for confirmation: YES (activation) or NO (inhibition).





ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE / ENABLE/DISABLE OF THE FLIGHT REPORT FILTER A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45Y1LINEMCE01 01 FWUT200




ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE ENABLE/DISABLE OF THE SERVICING REPORT (COUPON OR COMPLETE MODE) From the second page of the MAINTENANCE MENU access the second REPORTS PROGRAMMING page. Push the SERVICING COUPONS toggle key to change the SERVICING REPORT programming. Check the MCDU programming display for confirmation: YES (coupon mode active) or NO (complete mode active).





ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE / ENABLE/DISABLE OF THE SERVICING REPORT (COUPON OR COMPLETE MODE) A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45Y1LINEMCE01 01 FWUT200




ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE PROCEDURE TO INSTALL PAPER IN THE PRINTER REMOVAL OF THE SPOOL NOTE: If there is still paper on the spool: - cut the paper, - Slew the engaged paper until it is fully out.

INSTALLATION OF THE PAPER ROLL Install the new paper roll in the two grooves. Engage the paper tip in the gap between the two paper guides and push it until it engages automatically. Close the door and check that the paper feeds automatically.





ON BOARD MAINTENANCE SYSTEM LINE MAINTENANCE / PROCEDURE TO INSTALL PAPER IN THE PRINTER A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45Y1LINEMCE01 01 FWUT200




ON BOARD MAINTENANCE SYSTEMS BASE MAINTENANCE GENERAL OJanNuaBrOAyR0D3/0M5AINTENANCESYSTEMSBASEMAINTENANCE

Menu The Onboard Maintenance System (OMS), beside its basic functions, provides the maintenance operator with a compilation of LRU P/N, data base numbers and, software references installed on the aircraft, called AVIONICS CONFIGURATION DATABASE. On the A/C, when one of these LRU, software or database is changed or updated, the CMS detects this new configuration, thanks to the AVIONICS CONFIGURATION DATABASE. It displays it through an onboard printed coupon. Then the AVIONICS CONFIGURATION DATABASE may be updated and validated through the following task.

A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45Y2BASEMCE01 01 FWUT200




ON BOARD MAINTENANCE SYSTEMS BASE MAINTENANCE / GENERAL A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45Y2BASEMCE01 01 FWUT200




ON BOARD MAINTENANCE SYSTEMS BASE MAINTENANCE VALIDATION OF AN AVIONICS CONFIGURATION CHANGE Menu NOTE: The validation of the Avionics configuration change is done in the active CMC only. There is no automatic validation transmission to the slave CMC. From the second page of the MAINTENANCE MENU access the AVIONICS CONFIGURATION REPORTS page. NOTE: Make sure that all systems are powered and not in interactive mode, to allow the active CMC to check the actual avionics configuration. Pushing the START key launches the CMC avionics configuration reports construction. Push the CONFIGURATION CHANGE key to access to the corresponding page. NOTE: This line is displayed only if the active CMC has detected a configuration change. The CONFIGURATION CHANGE page(s) shows all changes detected by the active CMC, one change per page. The VALIDATE key will validate the LRU change displayed on the page. This key is protected by a passcode. Switch off the two other MCDUs and enter the access code "XXX" on the scratchpad to be able to validate the change. Push the VALIDATE key to access the CONFIGURATION VALIDATION page. Push the VALIDATE CHANGE key and check for confirmation. You can now transmit to the slave CMC, the active CMC as memorized the AVIONICS CONFIGURATION DATABASE. This allows you to use the slave CMC in case of active CMC failure. Put the aircraft back into its initial configuration.





ON BOARD MAINTENANCE SYSTEMS BASE MAINTENANCE / VALIDATION OF AN AVIONICS CONFIGURATION CHANGE A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS) FM45Y2BASEMCE01 01 FWUT200












































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AIRBUS S.A.S. 31707 BLAGNAC CEDEX, FRANCE AI/STDC REFERENCE FWU04451 JANUARY 2005 PRINTED IN FRANCE AIRBUS S.A.S. 2002 ALL RIGHTS RESERVED AN EADS JOINT COMPANY WITH BAE SYSTEMS

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