troubleshooting on a320 - a340
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Troubleshooting with A320 CFDS / A340 CMS - REFERENCE 952.1003/05
May 2005
Trouble shooting phi losophy withA320 CFDS / A340 CMS
Customer Support Engineering
Presented by
AUFFRET HervIndication / Warning / Maintenance System
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May 2005Troubleshooting with A320 CFDS / A340 CMS - REFERENCE 952.1003/05 Page 2AIRBUSS.A.S.
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
AGENDA
1. Maintenance Levels
2. Line Maintenance Concept
3. A/C Information Sharing
4. Message Classification
5. TSM Use
6. SIL 00-028, 00-038 & 00-041
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
AGENDA
1. Maintenance Levels
2. Line Maintenance Concept
3. A/C Information Sharing
4. Message Classification
5. TSM Use
6. SIL 00-028, 00-038 & 00-041
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
MAINTENANCE LEVELS
1st Level
2nd Level
No Log-Book complaint
Log-Book complaint (Class 1)
LRU level only
Maintenance status
LRU Level
No Maintenance Action required
PFR + System Report / Test +
Ref to MMEL
PFR (Class 2) +
System Report / Test
LINE MAINTENANCE
BASE MAINTENANCE / NIGHT STOP
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
MAINTENANCE LEVELS
3rd Level
4th Level
Class 3 faults
LRU Level
LRU removal
SRU Level
General Class 3 Report +
System Report / Test
Trouble Shooting Data +
BITE Shop Memory
SCHEDULED CHECKS
SHOP MAINTENANCE
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
AGENDA
1. Maintenance Levels
2. Line Maintenance Concept
3. A/C Information Sharing
4. Message Classification
5. TSM Use
6. SIL 00-028, 00-038 & 00-041
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
LINE MAINTENANCE CONCEPT: Decision Tree applies
AIRBUS
(TSD, ACMS Labels)
LOG BOOKMELNO
GO
Fault
on
PFRSIL 00-028 / -038/ 041/ -078
PART A (Fault Msg)
PART B (Cockpit Effect)
TSM
ECAM or CMS Index
TSM
EFIS, LOCAL or OBSV Index
FOLLOW TSM PROCEDURE
Crew or
Maintenance
Observation
Failure
Isolated
Spare
AvailableA/L Engineering
(ACMS Labels)Maint Action/
LRU Removal
A/C Return to Service
Carried Forward
item
No
YesNo
Yes
NoYes
No
Yes
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
AGENDA
1. Maintenance Levels
2. Line Maintenance Concept
3. A/C Information Sharing
4. Message Classification
5. TSM Use
6. SIL 00-028, 00-038 & 00-041
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
A/C INFORMATION SHARING
ECAM orEFISindications
FAULTLOCALindications
or
FWCs CMC
Operational failure messages(function lost) :
Maintenance failure messages(LRU lost) :
LOG BOOK
AIRCRAFT SYSTEMS
"Warnings/Malfunctions" "CMS Fault Messages"
OPERATIONAL INFORMATION FORFLIGHT CREW : A/C DISPATCH MAINTENANCE INFORMATION FORMECHANIC : A/C TROUBLESHOOTING
FAULTY LRU
HYDB RSVR LO PRESS
-BLUE ELEC PUMP....OFF
Warnings/MalfunctionsPOST FLIGHT
REPORT
Warnings/Malfunctions
CMSFault
MCDU
TEST>
TSM
Fault Isolation Proceduresassociated to Warnings/Malfunctionsand CMS Fault Messages
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
AGENDA
1. Maintenance Levels
2. Line Maintenance Concept
3. A/C Information Sharing
4. Message Classification
5. TSM Use
6. SIL 00-028, 00-038 & 00-041
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
MESSAGE CLASSIFICATION
1 2 3
NOT PRESENTEDPRESENTED
MESSAGE CLASS
INDICATION TO THE
FLIGHT CREW
DISPATCH (MMEL)
CONSEQUENCES
HANDLING
INDICATION TO THE
MAINTENANCE TEAM
Cockpit Effect
Any evidence of fault to the flight
crew: ECAM Warning, Flag on
SD, PFD or ND, Local warnings,
System misbehaviour ...
Maintenance Status
Status light flashing at the end
of the flight; Maintenance
Status messages on SD STS
page, presented only on
ground.
No indication to the flight
crew
POST FLIGHT REPORT AVIONIC STATUS
MMEL ENTRY MMEL PREAMBLE MMEL NOT
APPLICABLE
REF MMEL 600 Hours UNLIMITED TIME
Can be automatically issued at 80 kts + 180 s To be manually issued
GO, GO IF or NO GO GO
for time delay, restrictions etc... (See also TSM Introduction) However, correction is
recommended to improve
the dispatch reliability
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
AGENDA
1. Maintenance Levels
2. Line Maintenance Concept
3. A/C Information Sharing
4. Message Classification
5. TSM Use
6. SIL 00-028, 00-038 & 00-041
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
TSM USE
I-OBSV
I-LOCAL
I-EFIS
I-ECAM
General Indexes
I-CFDS
XX-CFDS
XX-OBSV
XX-LOCAL
XX-EFIS
XX-ECAM
PB 101
Fault
Symptoms
ATA Indexes
(XX= ATA ch apter)
TSM LEVEL ATA CHAPTER LEVEL
BLOCK
DIAGRAM
FAULT
ISOLATION
PB 201
PB 301
ATA SECTION LEVEL
TSM Procedure
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
TSM USE : Indexes
I-CFDS
EFF : ALL Page 1
Jan 01/94XXX
TROUBLE SHOOTING MANUALINDEX OF CFDS FAULT MESSAGES
CFDS MESSAGES ATA SOURCE CLASS CH-PB101
ACARS MU (1RB) 232434 ACARSMU 1 23-ECAMACCELEROMETER 313316 FDIU 2 31-
CFDSACCLRM 1 12CE1 279216 EFCS 1 2 27-ECAMACCLRM 1 12CE1 279216 EFCS 2 2 27-ECAMACCLRM 2 12CE2 279216 EFCS 1 2 27-ECAMACCLRM 2 12CE2 279216 EFCS 2 2 27-ECAMACCLRM 3 12CE3 279216 EFCS 1 2 27-ECAMACCLRM 3 12CE3 279216 EFCS 2 2 27-ECAM
A320
ADIRU1 341234 ADR 1 1 34-ECAM
ADIRU1 (1FP1)/GPWC (1WZ) 341234 GPWC 1 34-ECAM
ADIRU1 (1FP1)/ OVER TEMP 341234 ADR 1 2 34-
CFDSADIRU1 OR ADIRS CDU 341234 IR 1 1 34-
ECAMADIRU1 OR AOA SENSOR 3FP1 341234 ADR 1 1 27-ECAM
I-OBSV
I-LOCAL
I-ECAM
EFF : ALL Page 1Jan
01/94
XXX
A.ICE L INR WING HI PR 30-00 30-ECAM
AIR ENG 1 BLEED NOT CLOSED 36-0036-ECAM
AIR ENG 1 HPV NOT OPEN 36-0036-ECAM
AIR ENG 1 BLEED FAULT 36-00 36-
ECAMAIR ENG 1 BLEED LEAK 36-00 36-ECAM
ENG 2 BLEED NOT CLOSED 36-00 36-ECAM
A320
I-EFIS
TROUBLE SHOOTING MANUALINDEX OF WARNING/MALFUNCTIONS
ECAM PFR ATA TSM ATA
CH/SE CH-PB101EWD WARNINGS
A.ICE CAPT AOA HEAT 30-00 30-ECAM
A.ICE CAPT PITOT HEAT 30-00 30-ECAM
A.ICE CAPT TAT HEAT 30-00 30-ECAM
A.ICE F/O AOA HEAT 30-0030-ECAMA.ICE F/O PITOT HEAT 30-00 30-ECAM
A.ICE F/O TAT HEAT 30-00 30-ECAM
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
TSM USE : Fault symptoms
22-OBSV
Page 101
Jan 01/94
UBLE SHOOTING MANUAL
O FLIGHT FAULT SYMPTOMS
A320
CFDS FAULT MESSAGES FAULT
ISOLATIONSOURCE MESSAGE ATA C PROCEDURE
CFDS MESSAGES
22-CFDS
Page 101Jan 01/94
AFS AFS: FAC2/P-B SW12C 226634 1 226600 P 243T 810
837
22-LOCAL
EFF : ALL Page 101Jan 01/94
XXX
34-EFISEFF : ALL Page 101
Jan 01/94XXX
TROUBLE SHOOTING MANUALAUTO FLIGHT FAULT SYMPTOMS
A320
CFDS FAULT MESSAGES FAULT
WARNINGS/MALFUNCTIONS ISOLATIONSOURCE MESSAGE ATA C PROCEDURE
EWD WARNING(S)
22-ECAM
EFF : ALL Page 101
Jan 01/94XXX
AUTO FLTAP OFF AFS FMGC 1 (1CA1) 228334 1 22100P205
T 810 805
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
TSM USE : Fault isolation
21-26-00
EFF : ALL Page 213
Jan 01/94XXX
5. Close-upClose Access
TROUBLE SHOOTING MANUAL
A320
TASK 21-26-00-810-808Monitoring Discrete Output to Extract Fan
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 InformationA. Referenced Information
REFERENCE DESIGNATION
AMM 21-26-00-710-803 Operational test of the Avionics-EquipmentVentilation System
AMM 21-26-51-000-804 Removal of the Extract Fan (7HQ)AMM 21-26-51-400-804 Installation of the Extract Fan (7HQ)
ASM 21-26/01
3. Fault Confirmation
A. Job set-upGet access
Open access door 810B. 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
TASK 21-26-00-810-805
FAULT CONFIRMATION
FAULT ISOLATION
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
TSM USE : Task supporting data
TROUBLE SHOOTING MANUALFLAPS TASK SUPPORTING DATA
A320
functions
SHOOTING DATACs have TROUBLE SHOOTING DATA for a given fault which shows :antennae messagesmplementary information, if applicable; The complementary information is
X INPUTS.
age shows the synchro angles in decimal and hexadecimal values of theLH
27-50-00LL Page 308Jan 01/94
XXX
27-50-00EFF : ALL Page 308
Jan 01/94XXX
Flap Power Distribution - Block Diagram
Figure 306
FLIGHT WARNINGCOMPUTER 2(REF 3-53-00)
26VACSYSTEM 2
FLIGHT WARNINGCOMPUTER 1(REF 3-53-00)
26VACSYSTEM 2
TROUBLE SHOOTING MANUAL
A320
PCU VALVE BLOCK
EXT
RET
TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
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TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
AGENDA
1. Maintenance Levels
2. Line Maintenance Concept
3. A/C Information Sharing
4. TSM Use
5. SIL 00-028, 00-038 & 00-041
TROUBLE SHOOTING PHILOSOPHY WITH A320 CFDS/A340 CMS
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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 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
Part A
Part B
Part C
Part D
PFR Failure Messages
PFR Cockpit Effects
Class 3 Fault Messages
CFDS/CMS Anomalies (Interactive Mode)
Part E AI Envelope Filter
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AIRBUS S.A.S. All rights reserved. Confidential andproprietary document.
This document and all information contained herein is the sole
property of AIRBUS S.A.S.. No intellectual property rights aregranted 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 consentof 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. Theyare 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.
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A340-500/600
TECHNICAL TRAINING MANUAL
ONBOARD MAINTENANCE SYSTEMS
A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/
AVIONICS)
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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.
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A340-500/600 T2 MAINTENANCE COURSE (ELECTRICS/AVIONICS)TABLE OF CONTENTS
FWUT200
A340-500/600 TECHNICAL TRAINING MANUAL
Jan 5/05Page 1
ONBOARD MAINTENANCE SYSTEMS
Table Of ContentsCENTRAL MAINTENANCE SYSTEM PRESENTATION . . . . . . . . . . . . . 2CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION . 14CMS 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 108PRINTER 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
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CENTRAL MAINTENANCE SYSTEM PRESENTATION
A340-500/600 TECHNICAL TRAINING MANUAL
January 03/05Page 2
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FWUT200
January03/05CENTRALMA INTENANCESYSTEMPRESENTATION
CMS PHILOSOPHY
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.
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January 03/05Page 3
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CENTRAL MAINTENANCE SYSTEM PRESENTATION / CMS PHILOSOPHY
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CENTRAL MAINTENANCE SYSTEM PRESENTATION
A340-500/600 TECHNICAL TRAINING MANUAL
January 03/05Page 4
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FWUT200
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.
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January 03/05Page 5
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FWUT200
CENTRAL MAINTENANCE SYSTEM PRESENTATION / BITE PHILOSOPHY
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CENTRAL MAINTENANCE SYSTEM PRESENTATION
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FWUT200
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 generatestimuli 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.
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FWUT200
CENTRAL MAINTENANCE SYSTEM PRESENTATION / TESTS
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FWUT200
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.
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FWUT200
CENTRAL MAINTENANCE SYSTEM PRESENTATION / CENTRAL MAINTENANCE COMPUTER
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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.
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CENTRAL MAINTENANCE SYSTEM PRESENTATION / OPERATION MODES
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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.
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CENTRAL MAINTENANCE SYSTEM PRESENTATION / SYSTEM TYPES
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January03/05CENTRALMA INTENANCESYSTEMMESSAGESPRESENTATION
FAILURE CLASSES
Failures are divided into three classes depending on the effect they have on theflight.
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 onthe aircraft. They are not indicated to the flight crew during flight.
They are only available on ground through the MCDU class 3 report.
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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.
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CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION / INTERNAL / EXTERNAL FAILURES
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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.
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CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION / FAILURE MESSAGES STRUCTURE
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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 isidentified, 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.
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AMBIGUOUS / MULTIPLE FAULTS
In the case of ambiguous faults, up to three possible failures may be indicatedin 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.
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CENTRAL MAINTENANCE SYSTEM MESSAGES PRESENTATION / AMBIGUOUS / MULTIPLE FAULTS
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CMS MENUS PRESENTATION
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CMS MCDU MENUS
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.
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CMS MENUS PRESENTATION / CMS MCDU MENUS
CMS MENUS PRESENTATION
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FLIGHT LEGS
A flight LEG starts at startup of the third engine plus three minutes, if the flightplan 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.
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CMS MENUS PRESENTATION / FLIGHT LEGS
CMS MENUS PRESENTATION
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NORMAL MODE
In normal mode, the CMCs memorize the fault messages from type 1 and type2 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.
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CMS MENUS PRESENTATION / NORMAL MODE
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CMS MENUS PRESENTATION
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INTERACTIVE MODE
The SYSTEM REPORT/TEST function of the ground menu enables access tothe 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.
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CMS MENUS PRESENTATION / INTERACTIVE MODE
CMS MENUS PRESENTATION
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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.
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CMS MENUS PRESENTATION / COMPLEMENTARY FUNCTIONS
MENU NORMAL MODE D/O
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January03/05MENU NORMALMODED /O
GENERAL
This is the Multipurpose Control & Display Unit (MCDU) menu page whichpresents 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.
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MENU NORMAL MODE D/O / GENERAL
MENU NORMAL MODE D/O
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POST FLIGHT REPORT
The POST FLIGHT REPORT displays the Electronic Centralized AircraftMonitoring (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 numberof 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 (
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MENU NORMAL MODE D/O / POST FLIGHT REPORT
MENU NORMAL MODE D/O
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POST FLIGHT REPORT PRINT
All the information presented on the POST FLIGHT REPORT on differentMCDU 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.
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MENU NORMAL MODE D/O / POST FLIGHT REPORT PRINT
MENU NORMAL MODE D/O
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PREVIOUS FLIGHT REPORTS
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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 (
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MENU NORMAL MODE D/O / AVIONICS STATUS
MENU NORMAL MODE D/O
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CLASS 3 REPORT
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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.
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MENU NORMAL MODE D/O / CLASS 3 REPORT
MENU NORMAL MODE D/O
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COMPLEMENTARY FUNCTIONS
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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.
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MENU NORMAL MODE D/O / COMPLEMENTARY FUNCTIONS
MENU INTERACTIVE MODE D/O
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GENERAL
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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 thatfunction.
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MENU INTERACTIVE MODE D/O / GENERAL
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SPECIFIC DATA
The purpose of this item is to display specific information in order to
help the trouble shooting.
f l f ifi d i i h h
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MENU INTERACTIVE MODE D/O / GENERAL
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 typesof SPECIFIC DATA exist in a system, they must be displayed on a
sub-menu page accessible from line key 6R.
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This Page Intentionally Left Blank
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MENU INTERACTIVE MODE D/O / TYPE 1 SYSTEM TYPICAL MENU
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MENU INTERACTIVE MODE D/O / TYPE 1 SYSTEM EXAMPLE MENU
MENU INTERACTIVE MODE D/O
A340-500/600 TECHNICAL TRAINING MANUAL
TYPE 2 SYSTEM TYPICAL MENU
Unlike the Type 1 Systems there is no Menu Mode for the Type 2 Systems
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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 modeMenu).
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.
TESTThe 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.
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MENU INTERACTIVE MODE D/O / TYPE 2 SYSTEM TYPICAL MENU
MENU INTERACTIVE MODE D/O
A340-500/600 TECHNICAL TRAINING MANUAL
TYPE 2 SYSTEM EXAMPLE MENU
To describe the contents of the different items of a type 2 system, we have
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yp y ,
chosen the Battery Charge Limiter 1(BCL 1) , part of the DC ELECTRICALGENERATION 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 faultmessage 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 arepermanently 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.
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MENU INTERACTIVE MODE D/O / TYPE 2 SYSTEM EXAMPLE MENU
MENU INTERACTIVE MODE D/O
A340-500/600 TECHNICAL TRAINING MANUAL
TYPE 3 SYSTEM TYPICAL MENU
This is a typical type 3 system menu. The menu is fully generated by the active
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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 MENUTo 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.
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MENU INTERACTIVE MODE D/O / TYPE 3 SYSTEM EXAMPLE MENU
MENU SERVICING D/O
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GENERAL
This function provides reports with different parameters, which have to be
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periodically checked, and which may induce servicing actions. The servicingreport 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).
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MENU SERVICING D/O / GENERAL
MENU SERVICING D/O
A340-500/600 TECHNICAL TRAINING MANUAL
REPORT
The report is available either in flight or on ground.
The ser icing report is composed of the different items listed in the table as:
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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.
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MENU SERVICING D/O / REPORT
MENU SERVICING D/O
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REPORT (CONTINUED)
COUPON MODE
The purpose of this is to present to the user only items needing action
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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.
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MENU SERVICING D/O / REPORT (CONTINUED)
MENU SERVICING D/O
A340-500/600 TECHNICAL TRAINING MANUAL
REPORT (CONTINUED)
MCDU PRESENTATION
The servicing report, which is displayed on MCDU is complete and
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e se v c g epo , w c s d sp ayed o C U s co p e e a d
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.
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MENU SERVICING D/O / REPORT (CONTINUED)
MENU SERVICING D/O
A340-500/600 TECHNICAL TRAINING MANUAL
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.Y l th t ti t i i t th i t th ATSU i
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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.
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MENU SERVICING D/O / PROGRAMMING
MENU SERVICING D/O
A340-500/600 TECHNICAL TRAINING MANUAL
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 toautomatically trigger a coupon if they are exceeded. The airline can also add
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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.
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MENU SERVICING D/O / THRESHOLD AND TEXT INSERTIONS
MENU AVIONICS CONFIGURATION D/O
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GENERAL
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 theCentral Maintenance Computer 1 (CMC1).
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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 REPORTThis 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.
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MENU AVIONICS CONFIGURATION D/O / EQUIPMENT CONFIGURATION REPORT
MENU AVIONICS CONFIGURATION D/O
A340-500/600 TECHNICAL TRAINING MANUAL
EQUIPMENT CONFIGURATION REPORT CONTD
They are displayed on the MCDU or they can be printed.
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MENU AVIONICS CONFIGURATION D/O / EQUIPMENT CONFIGURATION REPORT CONTD
MENU AVIONICS CONFIGURATION D/O
A340-500/600 TECHNICAL TRAINING MANUAL
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. Theycontain databases necessary for the operation of some computers.
Th di k tt fi ti t i fi t d fi d b th i li i i
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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.
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MENU AVIONICS CONFIGURATION D/O / DISKETTE CONFIGURATION REPORT
MENU AVIONICS CONFIGURATION D/O
A340-500/600 TECHNICAL TRAINING MANUAL
DISKETTE CONFIGURATION REPORT CONTD
Pushing the line key adjacent to Avionics Configuration Reports gives you
access to the different MCDU screens as presented in the following example.
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MENU AVIONICS CONFIGURATION D/O / DISKETTE CONFIGURATION REPORT CONTD
MENU AVIONICS CONFIGURATION D/O
A340-500/600 TECHNICAL TRAINING MANUAL
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.
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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 inthe Equipment Configuration Report.
The configuration change report can be printed through the MCDU.
The screens and reports are presented as an example.
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MENU AVIONICS CONFIGURATION D/O / CONFIGURATION CHANGE
MENU AVIONICS CONFIGURATION D/O
A340-500/600 TECHNICAL TRAINING MANUAL
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 dataloader.
Non programmed printouts, dumps or transmissions to the ground have to be
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made manually.
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MENU AVIONICS CONFIGURATION D/O / PROGRAMMING
MESSAGE D/O
A340-500/600 TECHNICAL TRAINING MANUAL
January03/05MESSAGED /O
GENERAL
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
R l bl U it (LRU) E h i li it d t i f 48
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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.
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MESSAGE D/O / GENERAL
MESSAGE D/O
A340-500/600 TECHNICAL TRAINING MANUAL
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
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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 itpossible 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.
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MESSAGE D/O / MESSAGE CATEGORIES
MESSAGE D/O
A340-500/600 TECHNICAL TRAINING MANUAL
MESSAGE CATEGORIES (CONTINUED)
CATEGORY 3
Wiring is only indicated when the conclusion of the BITE analysis isa 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
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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 supplymust 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.
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MESSAGE D/O / MESSAGE CATEGORIES (CONTINUED)
MESSAGE D/O
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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.
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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).
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MESSAGE D/O / MESSAGE CONSTRUCTION
MESSAGE D/O
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MESSAGE HANDLING
Each Central Maintenance System message is covered by the TSM and is an
entry point to trouble shooting.
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MESSAGE D/O / MESSAGE HANDLING
MESSAGE PROCESSING D/O
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January03/05MESSAGEPROCESSINGD /O
GENERAL PARAMETERS
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
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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 ACMSwarnings, 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 take-off 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.
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MESSAGE PROCESSING D/O / GENERAL PARAMETERS
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MESSAGE PROCESSING D/O / CENTRAL MAINTENANCE COMPUTER /TYPE 1 SYSTEM
MESSAGE PROCESSING D/O
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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.
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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 memorizedby 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.
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MESSAGE PROCESSING D/O / CENTRAL MAINTENANCE COMPUTER/TYPE 2 SYSTEM
MESSAGE PROCESSING D/O
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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
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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 toprocess 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.
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MESSAGE PROCESSING D/O / CENTRAL MAINTENANCE COMPUTER/TYPE 3 SYSTEM
MESSAGE PROCESSING D/O
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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.
D i 1 it i t ll th f lt ith th ATA h t
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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 th