Airbus

A318/A319/A320/A321 _(non-enhanced-technology)
Differences to non-enhanced-technology Revision: 1JAN2010

ATA 31
Author: PoL
For Training Purposes Only
E LTT 2007
Indicating/Recording Systems

31−32 Centralized Fault Display System (CDFS)

31−38 Up & Down Data Loading System Acquisition/Interface & Equipment
31−00 Airman/e-Logbook

Line and Base Maintenance

Level 3

A318-21E_31B_L3/D-NEN
Training Manual

For training purposes and internal use only.

E Copyright by Lufthansa Technical Training (LTT).
LTT is the owner of all rights to training documents and
training software.
Any use outside the training measures, especially
reproduction and/or copying of training documents and
software − also extracts there of − in any format at all
(photocopying, using electronic systems or with the aid
of other methods) is prohibited.
Passing on training material and training software to
third parties for the purpose of reproduction and/or
copying is prohibited without the express written
consent of LTT.
Copyright endorsements, trademarks or brands may
not be removed.
A tape or video recording of training courses or similar
services is only permissible with the written consent of
LTT.
In other respects, legal requirements, especially under
copyright and criminal law, apply.

Lufthansa Technical Training

Dept HAM US
Lufthansa Base Hamburg
Weg beim Jäger 193
22335 Hamburg
Germany

Tel: +49 (0)40 5070 2520

Fax: +49 (0)40 5070 4746
E-Mail: Customer-Service@LTT.DLH.DE

www.Lufthansa-Technical-Training.com
Revision Identification:
S The date given in the column ”Revision” on the face of S Dates and author’s ID, which may be given at the base S The LTT production process ensures that the Training
this cover is binding for the complete Training Manual. of the individual pages, are for information about the Manual contains a complete set of all necessary pages
latest revision of that page(s) only. in the latest finalized revision.
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
GENERAL
31−00

ATA 31 INDICATING/RECORDING SYSTEMS

FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 01|ATA DOC Page 1

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

31−32 CENTRALIZED FAULT DISPLAY INTERFACE (CFDIU)

CFDS PRESENTATION
CFDIU ACARS
The CFDIU (Centralized Fault Display Interface Unit) receives failure The ACARS (Aircraft Communication Addressing and Reporting System) is
messages from the aircraft systems. used to exchange data between the aircraft and a ground station via a radio
It memorizes and manages them. Information is available in various reports. VHF link.
The CFDIU consists of two distinct channels:
S a NORMAL CHANNEL which ensures all the functions.
S a BACKUP CHANNEL (optionally) which permits restricted operation when
the normal channel is faulty.

BITE
The BITE (Built In Test Equipment) is a function incorporated in the computers
which detects, localizes and memorizes failures.
All systems including a BITE are connected to the CFDIU.

ECAM
The ECAM monitors the aircraft systems. The warning information is delivered
to the Centralized Fault Display System.
FWC (Flight Warning Computer).
Only the primary and the independent failure information is sent to the CFDS.

MCDU
The MCDU (Multipurpose Control and Display Unit) is a display unit and a
keyboard used by the CFDS to display and interrogate BITE‘s and to initiate
FOR TRAINING PURPOSES ONLY!

system tests.
The 2nd MCDU is also connected to the CFDS.
You can only use the CFDS on one MCDU at a time.
PRINTER
The PRINTER is used for printing information automatically or on request.

FRA US/T-5 PoL Mar 8, 2010 02|INTTRO|L1 Page 2

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CENTRALIZED FAULT
DISPLAY INTERFACE
UNIT (CFDIU)

FLIGHT
WARNING
COMPUTER
(FWC 1 & 2)
AIR TRAFFIC
FOR TRAINING PURPOSES ONLY!

SERVICE UNIT
(ATSU)

Figure 1 CFDS Overview

FRA US/T-5 PoL Mar 8, 2010 02|INTTRO|L1 Page 3
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

SYSTEM BITE PHILOSOPHY

BITE
Most aircraft system computers are equipped with a BITE (Built−In Test
Equipment). The BITE, which is an electronic device (hard + soft), monitors
permanently the system operation. When a failure is detected, it is stored in the
BITE memory and is transmitted to the CFDIU (Centralized Fault Display
Interface Unit). Memorization of the 64 previous legs report is done by most of
the BITEs.

MEMORIZATION
Memorization of failures is different when the aircraft is on ground or in flight.
The full BITE functions and memorization operate in flight.
On ground, the memorization is done only in the BITEs. The BITEs are
provided with flight and ground memory zones.

CFDIU
The CFDIU centralizes all information concerning aircraft system failures.
Reading or printing of all the failure information is done in the cockpit.
The CFDS (Centralized Fault Display System = CFDIU + BITEs) functions are
accessed through the MCDUs.

CFDS MODES
Two CFDS modes are available: NORMAL and MENU modes. The MENU
MODE is available only on ground.
NORMAL MODE
In this mode, the CFDIU scans all the connected system outputs and
FOR TRAINING PURPOSES ONLY!

memorizes the failure messages in order to generate the CURRENT (LAST)

LEG REPORT and the CURRENT (LAST) LEG ECAM REPORT. In flight the
CFDS always operates in the normal mode.

MENU MODE
In this mode, the CFDIU dialogues with one computer at a time in order to read
the contents of its BITE memory and to initiate various tests. This mode can
only be selected on ground and interrupts the normal mode of operation.

FRA US/T-5 PoL Mar 8, 2010 03|BITE Phil|L2 Page 4

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 2 BITE Philosophy

FRA US/T-5 PoL Mar 8, 2010 03|BITE Phil|L2 Page 5
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

SYSTEM BITE PHILOSOPHY CONTINUED

REPORTS
LAST/CURRENT LEG REPORT POST FLIGHT REPORT
A CURRENT LEG REPORT is elaborated during the flight. After the flight, its The PFR (Post Flight Report) is the sum of the LAST LEG REPORT and of the
title becomes LAST LEG REPORT. The purpose of this item is to present the LAST LEG ECAM REPORT. The PFR can only be printed on ground. The list
failure messages, concerning all systems, occurred during the last/current of ECAM WARNING MESSAGES and FAULT MESSAGES with the
flight. Each message contains the test of the failure, the ATA reference and the associated time, flight phase and ATA reference allow the maintenance crew to
flight phase and time at which the failure occurred. A function correlates the make a correlation for easier trouble−shooting.
”SOURCE” failure message with the ”resulting” failure messages. Beginning of PFR recording:
SOURCE: Name of system affected by a failure. S if flight number inserted prior to first engine start:
IDENTIFIER: Name of system affected by an external failure, which is − first engine start + 3 minutes.
correlated with the ”SOURCE” failure.
S if not:
The CFDIU capacity for failure messages memorization is up to 40 lines.
− aircraft speed > 80 knots.
LAST/CURRENT LEG ECAM REPORT End of PFR recording:
A CURRENT LEG ECAM REPORT is elaborated during the flight. After the S Aircraft speed < 80 knots + 30 seconds.
flight, its title becomes LAST LEG ECAM REPORT. The purpose of this item is
to present the warning messages displayed on the upper ECAM display unit
during the last/current flight. These are primary or independent warnings. Each
message contains the ECAM warning, the ATA reference and the flight phase
and time at which the warning was triggered. When several identical and
consecutive warnings are transmitted, the CFDIU memorizes the first
occurrence only and carries on counting with a maximum of 8. The occurrence
counter is displayed between brackets at the end of the message. The CFDIU
capacity for warning messages memorization is up to 40 lines.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 04|Reports|L2 Page 6

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

0832/1001

0935 06 23−00 CIDS 1

0855 05 30−31−34 PHC 6DA2 PHC 2

0855 05 30−11−51 R WAI VALVE TEMPCTL
FOR TRAINING PURPOSES ONLY!

0920 05 27−51−00 SFCC2 OR FLP PCU SFCC2 AFS

VALVE BLOCK CFDS
0935 06 23−73−34 DIRECTOR CIDS 1
0940 06 34−51−33 AFS: DME 1 AFS

Figure 3 Reports Presentation

FRA US/T-5 PoL Mar 8, 2010 04|Reports|L2 Page 7
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

SYSTEM BITE PHILOSOPHY CFDS MODES PRESENTATION

Two CFDS modes are available. NORMAL MODE is always active except on
Internal/External Failures
ground when MENU MODE is selected.
Each BITE (Built−In Test Equipment) can make the difference between an
S NORMAL MODE
internal and an external failure.
In this mode, the CFDIU scans all the connected system outputs and
Let us suppose that an angle of attack sensor failure has been detected and
memorizes the failure messages in order to generate the current (last) leg
that systems A, B and C are affected by this failure.
report and the current (last) leg ECAM report. In flight the CFDS always
The AIR DATA system will transmit an INTERNAL FAILURE (= SOURCE on operates in normal mode.
the POST FLIGHT REPORT).
S MENU MODE
Systems A, B and C will transmit EXTERNAL FAILURE (= IDENTIFIERS on
In this mode, the CFDIU dialogues with one computer at a time in order to
the POST FLIGHT REPORT).
read the contents of its BITE memory and initiate various tests (SYSTEM
Memorization REPORT/TEST).
Memorization of failures is different when the aircraft is on ground or in flight. This mode can only be selected on ground and interrupts the normal mode
of operation.
The full BITE functions and memorization operate in flight.
On ground, the memorization is done only in the BITEs.
The BITEs are provided with flight and ground memory zones.
Failure Gravity
The failures are classified according to their importance.
Class 1 failures are the most serious ones and require an immediate
maintenance action subject to the minimum equipment list.
Class 2 failures may have consequences if a second failure occurs.
A maintenance action is necessary at the next adequate opportunity.
Class 3 failures can be left uncorrected until the next scheduled maintenance
check.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 05|SYS BITE|L2 Page 8

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

AIR DATA REFERENCE

PART OF ADIRU
FOR TRAINING PURPOSES ONLY!

Figure 4 Internal/External Failures & Failure Gravity

FRA US/T-5 PoL Mar 8, 2010 05|SYS BITE|L2 Page 9
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

SYSTEM BITE TYPES INTERFACE

Type 1 Systems Type 3 Systems
Most Systems are type 1 systems. These systems can memorize failures Type 3 Systems are simple systems linked to the CFDS by only two discrete
occurred in the last 64 flight legs. signals.
Type 1 systems are connected to the CFDIU (Centralized Fault Display Type 3 systems cannot memorize failure messages.
Interface Unit) via an ARINC 429 input bus and an ARINC 429 output bus. The discrete input permits to initiate the test or reset.
S SINGLE COMPUTER The discrete output indicates if the system is OK or not.
The first configuration in TYPE 1 is a single computer. Example: TRU (Transformer Rectifier Unit)
Example: VHF 1 Transceiver
S MULTI COMPUTER
The second configuration in TYPE 1 includes several computers in the
same aircraft system.
One computer concentrates the maintenance data of the other computers.
Example: FMGC (Flight Management and Guidance Computers) and FAC
(Flight Augmentation Computer) with
FMGC1 as A
FMGC2 as B
FAC as C
S DUPLICATED SYSTEM
A duplicated system includes two different subsystems in the same
computer.
Example: ADIRU (Air Data and Inertial Reference Unit) with
ADR as subsystem 1
IR as subsystem 2
FOR TRAINING PURPOSES ONLY!

Type 2 Systems
Type 2 Systems memorize only failures from the last flight leg.
The discrete signal is provided to initiate the test of the system.
Example: AEVC (Avionics Equipment Ventilation Computer)

FRA US/T-5 PoL Mar 8, 2010 06|BITE Types|L3 Page 10

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 5 System Types

FRA US/T-5 PoL Mar 8, 2010 06|BITE Types|L3 Page 11
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CLASS 1 FAILURE PRESENTATION

Class 1 failures have an operational consequence on the flight.
You can display the class 1 failures on the MCDU (Multipurpose Control and
Display Unit):
S In the LAST (or CURRENT) LEG REPORT
S In the LAST (or CURRENT) LEG ECAM REPORT.
These faults are also indicated to the crew in flight:
S by the ECAM system (upper and/or lower DU (Display Unit)).
S by local warning in the cockpit.
Refer to the MMEL (Master Minimum Equipment List):
S ”GO“,
S ”GO IF”,
S ”NO GO”.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 07|Class1|L1 Page 12

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

MCDU IN FLIGHT
FOR TRAINING PURPOSES ONLY!

Figure 6 Class 1 Failure Indication and Annunciation

FRA US/T-5 PoL Mar 8, 2010 07|Class1|L1 Page 13
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CLASS 2 FAILURE PRESENTATION

Class 2 failures have no immediate operational consequence and can be
displayed on request on the ECAM STATUS page after Engine shut down.
You can display the class 2 failures on the MCDU (Multipurpose Control and
Display Unit):
S In the LAST (or CURRENT) LEG REPORT
S In the LAST (or CURRENT) LEG ECAM REPORT.
Refer to the MMEL: ”GO” without condition.
Example: CIDS Director 1 Fault (Cabin Intercommunication Data System).
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 08|Class2|L2 Page 14

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

MCDU IN FLIGHT
FOR TRAINING PURPOSES ONLY!

MAINTENANCE
CIDS 1

Indication after
Engine Shut down

Figure 7 Class 2 Failure Presentation

FRA US/T-5 PoL Mar 8, 2010 08|Class2|L2 Page 15
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CLASS 3 FAILURE PRESENTATION

Class 3 failures have no operational consequence.
All aircraft systems remain available.
You can display the name of the systems affected by at least a class 3 failure
in the AVIONICS STATUS.
The Class 3 failures can be left uncorrected until the next scheduled
maintenance check. (At least before 400 hours or a A check).
Do not refer to the MMEL.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 09|Class3|L2 Page 16

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

MCDU ON GROUND
FOR TRAINING PURPOSES ONLY!

Figure 8 Class 3 Failure Presentation

FRA US/T-5 PoL Mar 8, 2010 09|Class3|L2 Page 17
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

SYNTHESIS SYSTEM DESCRIPTION AND FAILURE CLASSES OVERVIEW

AVIONICS STATUS displays on ground the title of the systems currently Must be entered into the Log−book.
affected by any failure class. Compatible to content of MMEL (Master Minimum Equipment List)
Class 1 and 2 failures are displayed in the LAST LEG REPORT and in the Normally a “GO“-Item without condition (C-Item).
LAST LEG ECAM REPORT.
Exceptional cases require immediate maintenance action under certain
Only Class 1 & 2 Faults are shown on the PFR. condition.
CFDS SYSTEM TYPES Class 3
TYPE 1 BITE Not indicated to the crew. CFDS access on ground only.
Access with ARINC Input and ARINC Output buses. Can wait until next A−check (every 400 hours).
Menu−mode access from MCDU. ECAM WARNING LEVELS
TYPE 2 BITE LEVEL 3 RED WARNINGS
Access with Discrete Input and ARINC Output bus. RED WARNINGS with Master Warning Light, Continuous Repetitive Chime or
Pseudo menu−mode access from MCDU. specific sound and ECAM message.
Immediate crew action:
TYPE 3 (No System-BITE available)
S Aircraft in dangerous configuration
System−access with Discrete Input and Output wires.
S Limits exceeded
Only Test/Reset functions available.
S Flight safety directly involved.
SYSTEM FAILURE CLASSES
LEVEL 2 AMBER CAUTIONS
Class 1 AMBER WARNINGS with Master Caution Light, Single Chime and
With operational consequences on actual flight. Indicated to the crew as: ECAM−message.
warnings, cautions, local lights, and sounds, ECAM−messages, instrument Immediate crew attention:
flags.
S Aircraft in abnormal situation
FOR TRAINING PURPOSES ONLY!

They must be entered into the Log−book.

S Flight safety not directly involved
They require immediate maintenance action.
LEVEL 1 AMBER MESSAGES
Class 2
S No Master Caution Light.
With no operational consequences on actual flight.
S No aural warning.
Indicated to the crew as:
S ECAM−message only.
S In−flight:
− depending on FWC software, on the STATUS page only. Advisory
S After engine shutdown: Advisory−reminder in Engine/Warning Display (EWD), pulsing parameter in
System Display (SD) Should be monitored from the crew.
− by pulsing STS reminder.

FRA US/T-5 PoL Mar 8, 2010 10|Synthesis|L2 Page 18

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 9 Failure Classification Synthesis

FRA US/T-5 PoL Mar 8, 2010 10|Synthesis|L2 Page 19
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

MULTIPURPOSE CONTROL AND DISPLAY UNIT DESCRIPTION

MCDU GENERAL
The MCDU menu annunciator illuminates white when a system
There are several different versions of MCDUs installed in the A320 family. The
connected to the MCDU request the display.
older ones are equipped with CRTs (Cathode Ray Tubes) the new generation
have LCDs (Liquid Crystal Displays).
The CRT contains 14 lines, each having 24 characters.
The brightness knobs enable the brightness of the display to be The top line is used as title line and the bottom one, is the scratchpad.
adjusted. Two character size can be used, as well as various colours: white, cyan,
green, amber.
By pressing the MCDU menu key, the MCDU menu page is displayed, Various symbols <, >, *, →, ↑, ↓ can be displayed to indicate special
and any one of the systems connected to the MCDU can be selected. functions.
The green colour indicates the system already in dialogue with the NOTE: The MCDU is part of the Auto Flight System (AFS).
MCDU. The other systems are displayed in white.
For more details refer to ATA 22−82.
A multiple page display is indicated by an arrow in the right upper corner
of the screen. In this case the key with the right arrow (or “NEXT PAGE“
depending on MCDU version) must be used to give access to the
various pages of the display.

Some systems like the Flight Management System or Aircraft Integrated

Data System contain too many data for a single page.
In this instances, vertical scroll keys can be used to scroll display, up or
down.
The scroll keys can be used as long as these arrows are displayed.
NOTE: The vertical scroll keys are not used for any CFDS menu.
FOR TRAINING PURPOSES ONLY!

Twelve line select keys, six on the left and six on the right, give access
to a page or a function.
The line select keys permit access to a page or a function when these
symbols appear (>, <, *).
They are identified as 1L to 6L on the left, and 1R to 6R on the right.

FRA US/T-5 PoL Mar 8, 2010 11|MCDU|L2 Page 20

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

MCDU LCD Version MCDU CRT Version

->
< LAST LEG REPORT

< LAST LEG ECAM REPORT

< PREVIOUS LEGS REPORT

< AVIONICS STATUS

< SYSTEM REPORT TEST

POST FLT
* SEND REP PRINT *
FOR TRAINING PURPOSES ONLY!

Figure 10 MCDU LCD & CRT Version

FRA US/T-5 PoL Mar 8, 2010 11|MCDU|L2 Page 21
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDS REPORTS TROUBLESHOOTING

General
On ground, all the functions are available.
In flight, only CURRENT LEG REPORT and CURRENT LEG ECAM REPORT
are available.
Note that the CFDS menu comprises two pages on ground.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 12|Reports1|L2 Page 22

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDS ->
< CURRENT LEG REPORT
< CURRENT LEG ECAM REPORT
FOR TRAINING PURPOSES ONLY!

Figure 11 CFDS Menus on Ground and in Flight

FRA US/T-5 PoL Mar 8, 2010 12|Reports1|L2 Page 23
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
LAST LEG REPORT
The LAST LEG REPORT displays failure information delivered by the BITE‘s of
the aircraft systems.
It can store up to 20 failures occurred during the last leg.
When a key is pressed where a prompt is displayed beside the “GMT“
indication a page is displayed showing the “SOURCE/IDENTIFIERS“.
The Last Leg Report displays the internal failures (class 1 and 2) only.
On the ground, the title of this item is ”LAST LEG REPORT”. In the flight, it is
”CURRENT LEG REPORT”.
When the report is displayed on several pages, an arrow appears on the top
right−hand corner. The NEXT PAGE or arrow key permits to see the following
pages.
If you select the NEXT PAGE or arrow key on the last page, you come back to
the first page.
When you select the PRINT line key, the complete LAST LEG REPORT is
printed, even if it contains several pages.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 12|Reports1|L2 Page 24

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 12 Last Leg Report

FRA US/T-5 PoL Mar 8, 2010 12|Reports1|L2 Page 25
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
LAST LEG ECAM REPORT
The LAST LEG ECAM REPORT displays the list of ECAM warning messages
sent to the CFDIU by the flight warning computers.
It can store up to 20 warnings occurred during the last leg.
On ground, the title of this item is ”LAST LEG ECAM REPORT”, in flight it is
”CURRENT LEG ECAM REPORT”.
DOCUMENTARY DATA appears on the print report:
S the A/C identification
S the city pair
S the flight number
S date and GMT (UTC).
All the reports are printed.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 12|Reports1|L2 Page 26

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 13 Last Leg ECAM Report

FRA US/T-5 PoL Mar 8, 2010 12|Reports1|L2 Page 27
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
PREVIOUS LEGS REPORT
At each new flight leg, the content of the LAST LEG REPORT is transferred
into the PREVIOUS LEGS REPORT.
This report can store up to 200 failures over the last 63 flight legs.
Each failure message contains the same data as the LAST LEG REPORT:
i.e.: NO FAC 1 DATA
FEB 23 13 12
22−00−00
It also contains a flight leg counter relative to the previous flight.
−XX is the number of flight legs before the last flight leg:
i.e.: 01 (previous leg).
The PREVIOUS LEGS REPORT is displayed only on ground.
(INTM) means that the failure has occurred intermittently.
When you make a print of the PREVIOUS LEGS REPORT, only the displayed
page is printed.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 12|Reports1|L2 Page 28

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 14 Previous Legs Report

FRA US/T-5 PoL Mar 8, 2010 12|Reports1|L2 Page 29
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDS REPORTS (AV STS) TROUBLESHOOTING

AVIONICS STATUS
The AVIONICS STATUS presents the list of systems which are currently
affected by a failure.
This function is only available on ground.
The information presented is permanently updated.
The message contains the name of the systems presently affected by a failure,
i.e. VHF 3, or a NO X DATA message when the related system X bus is not
active, i.e. NO ILS 2 DATA.
The AVIONICS STATUS also indicates the class 3 failures.
(Class 3 ) means that the system is affected by at least one class 3 failure.
Note that there could also be class 1 or 2 failures.
When you make a print, all the AVIONICS STATUS report is printed even if it
contains several pages.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 13|AV STS|L2 Page 30

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 15 Avionics Status

FRA US/T-5 PoL Mar 8, 2010 13|AV STS|L2 Page 31
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDS REPORTS (SYS REP/TEST) PRESENTATION

SYSTEM REPORT/TEST LAST LEG REPORT
This function presents the internal and external failure messages concerning
General
this system that appeared during the last flight. These failure messages contain
The SYSTEM REPORT/TEST function is available on the ground only. the name of the failed Line Replaceable Unit (LRU) associated with the time at
It enables a dialogue between the CFDS and one system computer. which the failure occurred and the ATA reference.
The SYSTEM REPORT/TEST menu presents the list of all the systems
PREVIOUS LEGS REPORT
connected to the Centralized Fault Display Interface Unit, in ATA chapter order.
This function presents the internal and external failure messages concerning
An example for each system type is available:
this system that appeared during the previous 64 flights.
S in L/G for type 1 systems
The failure messages contain the name of the failed LRU associated with the
S in AIR COND for type 2 systems time and date at which the failure occurred, the flight number (−00 to −63) and
S in ELEC for type 3 systems the ATA reference.
SYSTEM REPORT/TEST−BSCU A (Type 1 system) LRU IDENTIFICATION
Type 1 systems are the most common systems. This function presents the Part Number (PN) of the system LRUs. On certain
The menu they present depends on the system itself. In the MENU mode, the systems also the partnumber of the software will be indicated.
menu is transmitted by the system itself. You talk directly with the system.
The menu includes three basic functions:
S the LAST LEG REPORT
S the PREVIOUS LEGS REPORT
S the LRU IDENTIFICATION
and optional functions, depending on the system, for example:
S TROUBLE SHOOTING DATA
S CLASS 3 FAULTS
FOR TRAINING PURPOSES ONLY!

S TEST
S GROUND SCANNING and many more.

FRA US/T-5 PoL Mar 8, 2010 14|SYS REP/TST|L2 Page 32

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 16 System Report/Test

FRA US/T-5 PoL Mar 8, 2010 14|SYS REP/TST|L2 Page 33
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDS REPORTS (MENU TYPES) PRESENTATION

SYSTEM REPORT/TEST−BSCU SYS1 (Type 1 system)
TROUBLE SHOOTING DATA
This item presents complementary information concerning the failures for
trouble shooting at level 3 (engineering maintenance). These messages
contain data constituting a snapshot of the system environment at the moment
of the failure or contain parameters internal to the computer (Aircraft
configuration, valve positions,...). This information is presented on MCDU in
hexadecimal language. When required, the TSM (Trouble Shooting Manual)
gives the interpretation of the message.

CLASS 3 faults
This item presents class 3 failure messages concerning this system that
appeared during previous flights. These failure messages contain the name of
the equipment affected by a class 3 fault associated with the time, the date, the
flight number and the ATA reference.

TEST
This item initiates system tests and shows the test results on the MCDU. The
CFDIU transmits the code of the line key (TEST) to the system. The system
BITE executes its test and may display a wait message to the CFDIU when the
test lasts for a long time. At the end of the test, the BITE transmits the test
results to the CFDIU for display.

GROUND SCANNING
This item presents the internal and external failures concerning this system and
which are present when the request is made (on ground only). This report is
FOR TRAINING PURPOSES ONLY!

established by forcing the operation of the BITE in system normal mode (same
BITE operation as in flight).

FRA US/T-5 PoL Mar 8, 2010 15|Type 1 Menu|L2 Page 34

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 17 System Report/Test - BSCU SYS1 (Type 1 System)

FRA US/T-5 PoL Mar 8, 2010 15|Type 1 Menu|L2 Page 35
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
SYSTEM REPORT/TEST−AEVC (Type 2 System)
Type 2 systems present a menu with one basic function, the LAST LEG
REPORT and optional functions depending on the system. Unlike Type 1
systems, Type 2 systems do not have a Menu Mode. These functions are
presented on the MCDU by the CFDIU: you are in PSEUDO−MENU mode.
You do not talk directly to the system. The system permanently transmits its
data on the system bus, and the CFDIU reads them, except for the test. The
menu includes one basic function:
S the LAST LEG REPORT,
and optional functions depending on the system, for example here
S TEST,
S CLASS 3 FAULTS.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 15|Type 1 Menu|L2 Page 36

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 18 System Report/Test−AEVC (Type 2 System)

FRA US/T-5 PoL Mar 8, 2010 15|Type 1 Menu|L2 Page 37
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
SYSTEM REPORT/TEST−GCU EMER (Type 3 system)
Type 3 systems present only one function on their menu. Type 3 systems have
no MENU mode. The available functions are shown by the CFDIU. The only
possible functions are TEST or RESET. When you make a test or a reset, the
CFDIU initiates the test or the reset, receives the result and shows it on the
MCDU.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 15|Type 1 Menu|L2 Page 38

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 19 System Report/Test−GCU EMER (Type 3 System)

FRA US/T-5 PoL Mar 8, 2010 15|Type 1 Menu|L2 Page 39
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDS REPORTS (PFR) INTRODUCTION

PFR (POST FLIGHT REPORT)
The POST FLIGHT REPORT is the sum of the LAST LEG REPORT and of the
LAST LEG ECAM REPORT.
It is only available on the printer.
S “ECAM WARNING MESSAGES“ or “ECAM WARNING/MAINT. STATUS
MESSAGES MESSAGES“ display the LAST LEG ECAM REPORT.
S FAILURE MESSAGES display the LAST LEG REPORT.
S DB/N indicates if and which a PFR filter database is active.
You can send this report to the ACARS.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 16|PFR|L1 Page 40

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

A/C ID DATE GMT FLTN CITY PAIR A/C ID DATE GMT FLTN CITY PAIR
D-AIRB 28MAY 18:00 LH021 EDDH EDDF D-AIRB 28MAY 18:00 LH021 EDDH EDDF

+−−−−−−−−−−−−−−−−−−−−+ +−−−−−−−−−−−−−−−−−−−−+
! MAINTENANCE ! DB/N ! MAINTENANCE !
! POST FLIGHT REPORT ! A320FAM03 ! POST FLIGHT REPORT !
+−−−−−−−−−−−−−−−−−−−−+ +−−−−−−−−−−−−−−−−−−−−+

A/C ID DATE GMT FLTN CITY PAIR A/C ID DATE GMT FLTN CITY PAIR
D-AIRB 28MAY 16:20 LH021 EDDH EDDF D-AIRB 28MAY 16:20 LH021 EDDH EDDF

ECAM WARNING MESSAGES WARNING/MAINT.STATUS MESSAGES

−−−−−−−−−−−−−−−−−−−−−−−−−−−−−—— −−−−−−−−−−−−−−−−−−−−−−−−−−−−−——
GMT PH ATA GMT PH ATA
1641 06 31−00 RECORDER DFDR FAULT 1641 06 31−00 RECORDER DFDR FAULT
1702 06 36−00 AIR BLEED 1702 06 36−00 AIR BLEED
1713 07 22−00 AUTO FLT AP OFF 1713 07 22−00 AUTO FLT AP OFF

FAILURE MESSAGES FAILURE MESSAGES

−−−−−−−−−−−−−−−−—- −−−−−−−−−−−−−−−−—-
GMT PH ATA SOURCE / IDENT. GMT PH ATA SOURCE / IDENT.
1633 06 52−22−00 DOOR BTL CIDS1 1633 06 52−22−00 DOOR BTL CIDS1
1641 06 31−33−34 DFDR FDIU 1641 06 31−33−34 DFDR FDIU
FOR TRAINING PURPOSES ONLY!

1649 06 34−41−11 WXR ANTENNA (11SQ) RADAR 1 1649 06 34−41−11 WXR ANTENNA (11SQ) RADAR 1
1702 06 36−11−34 BMC 1 BMC 1 1702 06 36−11−34 BMC 1 BMC 1
1713 06 22−83−34 AFS:FMGC1 AFS 1713 06 22−83−34 AFS:FMGC1 AFS

Version 1 Version 2

Figure 20 Post Flight Report

FRA US/T-5 PoL Mar 8, 2010 16|PFR|L1 Page 41
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

GMT/DATE INITIALIZATION OPERATION

The GMT/DATE INITialization function is available only in case of clock failure
plus CFDIU power interrupt.
The Centralized Fault Display System permits to reinitialize the time and the
date on the multipurpose control and display unit.
GMT (UTC) and date are entered using the scratchpad.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 17|GMT/DATE|L3 Page 42

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

12 34
FOR TRAINING PURPOSES ONLY!

Figure 21 GMT/Date Initialization

FRA US/T-5 PoL Mar 8, 2010 17|GMT/DATE|L3 Page 43
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

ACARS/ PRINT PROGRAM OPERATION

An ACARS/PRINT PROGRAM function is available. The AVIONICS DATA function enables to send and/or print system pages
It enables programming of the CFDS reports transmission to the ACARS and available in the SYSTEM REPORT/TEST menu.
to the printer. The printing or/and sending is not automatic; you must select the print line key
The functions written in green are delivered by the ACARS or the CFDIU. displayed in the system page.
They cannot be modified by the flight crew. NOTE: In the system pages, the PRINT message cannot be modified.
The functions written in blue can be changed manually. But when you print and send the system pages, the ”PRINT
If you select one of these functions, you will switch the YES message to NO ALSO SEND” message appears in the scratchpad. The ALL
and vice versa. reports which are printed manually are also send automatically
via ACARS.
The REAL TIME FAILURES provide, in real time, all the internal failure
messages delivered by the systems or created by the CFDIU (CURRENT LEG Functions delivered by the ACARS:
REPORT DATA). When the CFDIU has not received any programming from the ACARS, the
When the associated SEND is on YES, this data is automatically transmitted to YES or NO message is replaced by a blank.
the ACARS, in real time.
The REAL TIME WARNINGS function provides, in real time, warning
messages, sent by the Flight Warning Computers (CURRENT LEG ECAM
REPORT DATA).
When the associated SEND is on YES, the report is automatically transmitted
in real time, to the ACARS.
The POST FLIGHT REPORT is the sum of the LAST LEG REPORT and of
the LAST LEG ECAM REPORT.
When the associated SEND is on YES, the POST FLIGHT REPORT will be
automatically transmitted to the ACARS at the end of the flight (transition from
flight phase 9 to 10).
The PRINT function associated to
FOR TRAINING PURPOSES ONLY!

S the POST FLIGHT REPORT

S the REAL TIME FAILURES
S the REAL TIME WARNINGS
permits an automatic print of the report.
The POST FLIGHT REPORT will be printed automatically at transition from
flight phase 9 to 10 (Second engine shutdown).
Upon power on, the last selected programmed functions are still present.
At the initialization, the manual programming functions present the last
configuration in vigor.

FRA US/T-5 PoL Mar 8, 2010 18|ACARS/PRINT PRG|L3 Page 44

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 22 ACARS/Print Program

FRA US/T-5 PoL Mar 8, 2010 18|ACARS/PRINT PRG|L3 Page 45
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDS PFR FILTER PROGRAM-MAINTENANCE PRACTICES

PFR FILTER PROGRAM
The purpose of this function is to improve the operational use of the PFR,
CURRENT/LAST LEG ECAM REPORT and LAST LEG REPORT, by filtering
all the spurious or unjustified failures/messages. It concerns the PFR printed at
the end of the flight as well as the real−time failure and warning information
transmitted by the ATSU.
FILTER ACTIVATED
The filter database is activated after correct uploading. It can be deactivated
then activated again through the second page of the main maintenance menu
by pushing line key 4L then 2L. This database is adapted from SIL (Service
Information Letter) 0028 under diskette form. It must be periodically updated.

PRINT FILTER CONTENT

Action on line key 3R starts the printing of the maintenance filter database.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 19|PFR Filter|L3 Page 46

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 23 PFR Filter Program − Filter Activated & Print Filter Content
FRA US/T-5 PoL Mar 8, 2010 19|PFR Filter|L3 Page 47
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

PFR FILTERING FUNCTION MAINTENANCE PRACTICES

PURPOSE
The purpose of the filtering function is to reduce the number of spurious
maintenance messages. So the filtered PFR (Post Flight Report) contains only
the messages needing a maintenance action.

FILTER DATA BASE CUSTOMIZATION AND LOADING

Using the feedback data from the airlines or the data from laboratory or flight
tests, Airbus establishes, keeps up to date and transmits to the airlines a
document called SIL (Service Information Letter) 00−028. SIL 00−028 consists
of a ”spurious maintenance messages data base”. This is an envelope data
base, including the spurious messages concerning every possible PN (Part
Number) from every vendor. The airline is responsible for customizing this
envelope data base to its fleet configuration using a compatible personal
computer and dedicated software. The customized maintenance filter data
base is first stored on a floppy disk, and then uploaded into the CFDIU
(Centralized Fault Display Interface Unit) by means of the data loader.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 20|Filter Upload|L3 Page 48

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

SIL: Service Information

Letter

DB/N
A320FAM03
FOR TRAINING PURPOSES ONLY!

Figure 24 Purpose & Filter Data Base Customization and Loading

FRA US/T-5 PoL Mar 8, 2010 20|Filter Upload|L3 Page 49
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

PFR FUNCTION (INDICATION) OPERATION

FILTER DATA BASE IDENTIFICATION
Each filter is identified by a 15−character data base number. The data base
number is written on the filtered PFR and can be displayed on the MCDU.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 21|DB Ident|L3 Page 50

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 25 Filter Data Base Identification

FRA US/T-5 PoL Mar 8, 2010 21|DB Ident|L3 Page 51
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

POST FLIGHT REPORT FILTERING FUNCTION (EXAMPLE)

EXAMPLES
These examples show a PFR not filtered, the maintenance filter data base and
the PFR filtered.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 22|Filter Example|L3 Page 52

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 26 Examples
FRA US/T-5 PoL Mar 8, 2010 22|Filter Example|L3 Page 53
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

BACKUP MODE (OPTION) OPERATION

BACKUP MODE GENERAL S If the fault in the CFDIU normal channel is not serious (interface board),
The BACKUP MODE function is only displayed in case of CFDIU main channel automatic switching is not performed, so as not to lose the other CFDS
failure. functions for the systems not affected by the fault.
It enables access to the functions of the backup channel. However, the CFDS may add a BACKUP MODE item in its menu, on the
ground only, enabling manual switching to the back−up channel on the
In flight, no function is available.
MCDU. This switching gives the operator access to the systems affected by
On ground, the only function possible is SYSTEM REPORT/ TEST. the fault in the normal channel. When the switching has been performed by
This function is available for the main systems only. the operator, the CFDIU is placed in the previous configuration (automatic
switching).
CFDS BACKUP MODES
Note: Only the MCDU1 or 3 is connected to the CFDIU back−up channel
First Back−up Mode and can alone be used in BACKUP MODE.
The CFDIU consists of two distinct channels: normal channel and back−up After switching to the back−up channel (automatic or manual), return to the
channel. normal channel is not possible using the MCDU. The return can only be
In normal operation, the normal channel of the CFDIU ensures all maintenance performed after a CFDIU power cutoff longer than 1 second.
functions and the back−up channel is not energized. A CFDIU fault is indicated by a class 2 warning to the ECAM.
In the event of a CFDIU normal channel fault: Second CFDS Back−up Mode: the test Plugs
S If this fault is serious (power supply board or micro): In the event of total CFDIU failure (normal and back−up channels), it is still
it is automatically and immediately switched to the CFDIU back−up channel. possible to read the maintenance information sent by certain systems by
In addition, the back−up channel is power supplied on the ground only means of two test plugs located in the avionics compartment, on either side of
(ground/flight discrete). When the CFDS item is selected in the MCDU rack 80VU.
MENU, the CFDS BACKUP MODE page is directly displayed on the MCDU.
In flight: No functions are possible (not supplied).
On the ground: The only function possible is the SYSTEM REPORT/TEST
function, for the aircraft main systems only.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 23|Backup Mode|L3 Page 54

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

STEP 1 STEP 2

CFDS SYSTEM REPORT

BACK UP MODE TEST
< SYSTEM REPORT TEST < CPC 1 AFS >
< AC GEN SFCC 1 >
Gives direct access
to the 26 systems < EFCS 1 SFCC 2 >
connected to the < EFCS 2 LGCIU 1 >
CFDIU backup card
< FDIU ECAM 1 >
< RETURN < RETURN ECAM 2 >

 
STEP 3 STEP 4
SYSTEM REPORT SYSTEM REPORT
TEST TEST
< ADR 1 IR 1 > < FADEC 1B
FOR TRAINING PURPOSES ONLY!

< ADR 2 IR 2 > < FADEC 2B

< BSCU A EIS 1 >
< FADEC 1A EIS 2 >
 
< FADEC 2A EIU 1 >
< RETURN EIU 2 > < RETURN

Figure 27 Backup Mode (OPTION)

FRA US/T-5 PoL Mar 8, 2010 23|Backup Mode|L3 Page 55
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

PASSWORD CHANGE (OPTION) OPERATION

CFDS Password Settings
The purpose of this function is to enable customized access to REPORTS
PROGRAMMING and PFR FILTER PROGRAM pages through a password.
Two modes can be used:
S transparent mode: free acess
S password mode: access through a password
The operator can exit the transparent mode to use the password mode and
vice versa.
S the transparent mode is active at component delivery.
S the password is made up of the character minimum and eight characters
maximum. The ninth character becomes the eighth character.
S password XXXXXXXX is dedicated to the transparent mode.
S when changing the password:
− OK means ”password corrected and accepted”
− ERROR means ”not OK”
S The three fields LAST PASSWORD, NEW PASSWORD and CONFIRM
PASSWORD must be correctly filled in (i.e. three OK indications) to validate
the new password.
When the password entered cannot be validated, the ERROR message is
displayed in the scratchpad.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 23|Backup Mode|L3 Page 56

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDS CFDS

< LAST LEG REPORT

< LAST LEG ECAM REPORT

 
< PREVIOUS LEGS REPORT < ACARS/PRINT PROGRAM
< AVIONICS STATUS < PFR FILTER PROGRAM
< SYSTEM REPORT/TEST < PASSWORD CHANGE
< RETURN

EXAMPLE FOR PASSWORD ENTRY

PASSWORD CHANGE ENTER PASSWORD

< LAST PASSWORD

FOR TRAINING PURPOSES ONLY!

< NEW PASSWORD

< CONFIRM PASSWORD

ENTER >
< RETURN < RETURN

Figure 28 PASSWORD SETTINGS (OPTION)

FRA US/T-5 PoL Mar 8, 2010 23|Backup Mode|L3 Page 57
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDS PHASES FUNCTIONAL OPERATION

GROUND/FLIGHT TRANSITION ON GROUND PHASE
Transition to flight (Event 1) is defined at the soonest or at the latest depending On ground, the system BITEs ensure:
on whether the flight number has been entered by the crew before take−off or S detection (Type 1/2/3 systems) and memorization in their ground memory
not: (Type 1/2 systems) of internal faults only,
S at the soonest: First engine start + 3 minutes if flight number entered prior S transmission to the CFDIU of internal faults for monitoring and
to first engine start. establishment of the AVIONICS STATUS.
S at the latest: Aircraft speed > 80 knots if flight number not entered prior to All CFDS (Centralized Fault Display System) functions (e.g. PFR printing) are
first engine start. available on request through the MCDUs.
At event ”1”, the leg number is incremented.
IN FLIGHT PHASE
From event 1 until aircraft speed has been below 80 knots for 30 seconds, type
1 and 3 systems are considered in flight.
NOTE: Type 2 systems are only considered in flight from 30 seconds
after lift off up to touch down.
In flight, the system BITE (Built−In Test Equipment)ensures:
S detection (Type 1/2/3 systems) and memorization in their flight memory
(Type 1/2 systems only, as type 3 system BITEs do not have any memory)
of internal and external faults,
S transmission to the CFDIU (Centralized Fault Display Interface Unit) of
internal and external faults for memorization and establishment of the
CURRENT LEG REPORT.
This in flight phase corresponds to the PFR (Post Flight Report) recording time
(Beginning and end of fault and ECAM (Electronic Centralized Aircraft
Monitoring) warning message memorization in the CFDIU.
FOR TRAINING PURPOSES ONLY!

FLIGHT/GROUND TRANSITION
Transition to ground occurs when, after touch down, the aircraft speed has
been below 80 knots for 30 seconds. At this time, the CURRENT LEG
REPORT is renamed under the title LAST LEG REPORT and is stored in the
PREVIOUS LEGS REPORT.
NOTE: As the leg has not changed, the content of the LAST LEG
REPORT is identified in the PREVIOUS LEGS REPORT under
the LEG −00.

FRA US/T-5 PoL Mar 8, 2010 24|Phases|L2 Page 58

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

PFR START: PFR END:

1st ENGINE START < 80KTS
+ 180 SECONDS +30 S
“1“

TYPE 2 SYSTEMS
FOR TRAINING PURPOSES ONLY!

FOR TYPE 3 SYSTEMS TEST INHIBITION ONLY (NO MEMORY)

TYPE 1 SYSTEMS

Figure 29 Ground/Flight Transition

FRA US/T-5 PoL Mar 8, 2010 24|Phases|L2 Page 59
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDIU FUNCTIONS
MAIN FUNCTIONS INTERFACES
Memory Clock
The CFDIU stores the failure messages and the ECAM warning messages in a The CFDIU permanently receives the GMT (UTC) and the date from the
non volatile memory. aircraft clock and then sends these two parameters to all type 1 systems.
The GMT and date are used by the system BITE’s as well as the CFDIU for
Management
the various maintenance reports.
The CFDIU manages failure information and adds data such as GMT, DATE,
LEG, FLIGHT PHASE to elaborate reports. FAC (Flight Augmentation Computer)
The CFDIU receives the flight number and city pair from the FAC.
Correlation
The city pair (FROM/TO airports) is sent to the MU (Management Unit) of the
If a computer internal failure is detected, the CFDIU achieves a correlation
ACARS (Aircraft Communication Addressing and Reporting System) and to the
function that means it isolates or ignores the malfunctions of systems relating
DMU (Data Management Unit) of the AIDS (Aircraft Integrated Data System).
to this failure.
Example: ”ADC FAILURE” causes ”NO DATA FROM ADC” in other FDIU (Flight Data Interface Unit, part of Flight Recorder System)
computers. The CFDIU receives the aircraft identification from the Flight Data Interface
The CFDS will present only the initial failure in the last leg report. Unit and sends this parameter to all type 1 systems.
The function ”IDENT” will then present the systems affected by this failure. The CFDIU is used as an interface between the FDIU and the FWC (Flight
Warning Computer) to send some FDIU class 2 failures to the FWC in order to
Monitoring constitute the maintenance status.
The CFDIU scans permanently all input buses in order to detect a transmitted
failure message. FWC (Flight Warning Computer, part of ECAM)
The CFDIU detects intermittent operation of the systems and adds (INTM) to The CFDIU receives the flight phases and ECAM warnings from the FWC.
the failure message. The ECAM warnings are used by the CFDIU to generate the LAST or
CURRENT LEG ECAM REPORT.
Detection
Only PRIMARY failures, INDEPENDENT failures and CLASS 2 failure
FOR TRAINING PURPOSES ONLY!

The CFDIU can detect the nature of the failure by reading the ARINC words. messages (Maintenance status) are received.
Nature of failures:
DMU (Data Management Unit, part of AIDS)
S Internal Example: ”SDAC FAULT”
The CFDIU is used as an interface between the DMU and the FWC to send
S External Example: ”FWC1: NO DATA FROM ADIRU1”
some DMU class 2 failures.
S Intermittent (INTM) added
DMU class 2 failures are used for the maintenance status on the ECAM.
S Class 3 ( CLASS 3) added
S Messages requiring more investigation with the help of the trouble−shooting
manual Example: ”CHECK EIU 1”

FRA US/T-5 PoL Mar 8, 2010 25|CFDIU Functions|L3 Page 60

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CLASS 2 FLIGHT
FAILURES PHASES

ECAM
WARNINGS
FOR TRAINING PURPOSES ONLY!

Figure 30 CFDIU Functions

FRA US/T-5 PoL Mar 8, 2010 25|CFDIU Functions|L3 Page 61
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
INTERFACES BACKUP Mode
In BACKUP Mode, only the main computers are available and only the
DMC (Display Management Computer, part of EIS)
”SYSTEM REPORT/TEST ” function is available.
The CFDIU receives the Engine Serial Number from the DMC and sends this
In the event of main channel failure:
parameter to the EVMU (Engine Vibration Monitoring Unit).
S If this failure is serious (Power Supply or Microprocessor) the backup
MU (Management Unit of ACARS) channel takes over.
The ACARS Management Unit receives the city pair from the FAC through the Only ”BACKUP MODE” is displayed on the CFDS menu.
CFDIU. No function is available in flight.
EVMU (Engine Vibration Monitoring Unit) S If this failure is minor, the item ”BACKUP MODE” is added to the CFDS
menu.
The EVMU receives the Engine serial number from the DMC through the
CFDIU. This enables the access to the backup channel.
The DMC receives it from the ECU (Engine Control Unit). The main channel remains available.

ABNORMAL OPERATION
Clock Back Up
If the aircraft clock fails, the CFDIU takes over and its internal clock sends
GMT (UTC) and DATE on the output bus to all type 1 systems.
Upon power−on after A/C clock failure, the item ”GMT/DATE INIT” is added to
the CFDS Menu.
This option enables GMT and date initialization.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 25|CFDIU Functions|L3 Page 62

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CLASS 2 FLIGHT
FAILURES PHASES

ECAM
WARNINGS
FOR TRAINING PURPOSES ONLY!

Figure 31 CFDIU Functions

FRA US/T-5 PoL Mar 8, 2010 25|CFDIU Functions|L3 Page 63
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDIU TEST MENU PRESENTATION

Menu Mode of the CFDIU GROUND SCANNING function
The menu mode of the CFDIU comprises the following four functions: The purpose of this function is to present the internal or external faults on the
S LAST LEG REPORT ground, whether these faults are already present in flight or not.
S LRU IDENTIFICATION These faults are detected through monitoring activated on manual selection of
the function.
S POWER UP TEST RESULT
Handling of faults:
S GROUND SCANNING.
S Activation
LAST LEG REPORT function − After manual selection of the function, the CFDIU monitors the internal
The purpose of this function is to memorize the internal or external faults in and external faults.
flight, whether these faults are already present on the ground or not. − The ATA reference and the time at which the fault is detected are
In the general case, these faults are detected through permanent monitoring associated with each fault message.
and in some cases, through the power−up test. S Presentation capacity
The ATA reference, the time at which the failure occurred and the flight phase Presentation capacity is 5 failures while new faults delete the oldest ones.
during which it occurred are associated with each fault message.
S The presentation of this function is identical to that of the LAST LEG
Memorization capacity is 5 faults, while new faults delete the oldest ones. REPORT.
LRU identification function S During function progress the CFDIU presents the message: IN PROGRESS
(50 SEC) and a RETURN/STOP key is presented to enable function
The purpose of this function is to display the computer part number and
interruption and return to CFDIU BITE menu.
database number.
S Criteria of monitoring
POWER−UP TEST RESULT function − Monitoring is activated on function selection for the following systems:
The purpose of this function is to present the CFDIU internal components FAC 1, FDIU, DMC 1, AMU, CIDS 1, MCDU, PRINTER, CLOCK, CFDIU
detected faulty during the last Power−Up Test. and FWCs.
The ATA reference 31−32−34 is associated with each fault message. Description of faults
In the event of fault, the following messages are displayed:
FOR TRAINING PURPOSES ONLY!

Monitoring and associated message are identical to the case of the LAST LEG
S CFDIU I/0 ARINC 1 (or 2 or 3) for fault of multiplexor 1, 2 or 3 REPORT.
S CFDIU I/0 DISCRETE 1 (or 2) for fault of discrete inputs/outputs 1 or 2 NOTE: This manually activated monitoring does not entail acquisition of
S CFDIU BITE MEMORY for fault in NVM monitored parameters by the CFDIU.
S CFDIU for any other fault of the channel

FRA US/T-5 PoL Mar 8, 2010 26|SYS/Test Menu|L2 Page 64

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

SYSTEM REPORT / TEST

< ECAM 1 CFDIU >
< ECAM 2 EIS 1 >
< FDIU EIS 2 >
CFDIU
EIS 3 >
< LAST LEG REPORT
DMU >
< LRU IDENTIFICATION
< RETURN < GROUND SCANNING
< POWER UP TEST RESULT

< RETURN

CFDS
LRU IDENTIFICATION
FOR TRAINING PURPOSES ONLY!

P/N: B401ACM507
If there is no filter,
DB/N: A320FAM03 „A320FAM03“ is replaced by „SPACE“

< RETURN PRINT >

Figure 32 CFDS System Report/Test Menu

FRA US/T-5 PoL Mar 8, 2010 26|SYS/Test Menu|L2 Page 65
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

CFDS COMPONENT LOCATION

MCDU 1 3CA 1
MCDU 2 3CA 2

PRINTER
FOR TRAINING PURPOSES ONLY!

Figure 33 Components Location (1)

FRA US/T-5 PoL Mar 8, 2010 27|COMP LOC|L1 Page 66
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

STA977/FR24A

STA808/FR20

ACCESS DOOR 824 AFT ELECTRONICS RACK 80VU

FOR TRAINING PURPOSES ONLY!

Figure 34 Components Location (2)

FRA US/T-5 PoL Mar 8, 2010 27|COMP LOC|L1 Page 67
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

TROUBLE SHOOTING PROCEDURE WITH CFDS

COCKPIT EFFECT
After a malfunction, the crew reports the cockpit effect in the log book.
The fault symptoms, relative to the cockpit effect, can be as follows:
S a WARNING/MALFUNCTION + CFDS (Centralized Fault Display System)
FAULT message (with possible associated warnings and system
IDENTIFIERS).
S a WARNING/MALFUNCTION alone.
S a CFDS FAULT message alone.

PFR
For the class 1 and 2 failures of CFDS monitored systems, the PFR (Post
Flight Report) permits an access to the concerned list of faults in Airn@v. For
this purpose, it gives the following information: ECAM (Electronic Centralized
Aircraft Monitoring) WARNING message (if it exists), FAULT message with its
SOURCE, ATA reference and IDENTIFIERS list.
When the PFR print is not available, this information can be retrieved through
the MCDU (in Normal mode or Menu mode). SIL (Service Information Letter)
00−028, made of ”spurious maintenance messages”, and the maintenance
knowledge let the airlines create a specific data base to filter the messages to
be displayed on the PFR.
Once loaded into the CFDIU (Centralized Fault Display Interface Unit), this
maintenance filter data base can be activated through the MCDU.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 28|TS Procedure|L2 Page 68

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

1440/16
34
FOR TRAINING PURPOSES ONLY!

Figure 35 Cockpit Effect & PFR

FRA US/T-5 PoL Mar 8, 2010 28|TS Procedure|L2 Page 69
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32

TROUBLE SHOOTING PROCESS

AIRN@V ENTRY
The CFDS report information gives a direct access to the fault isolation
procedure task numbers through Airn@v. You have to select the
Troubleshooting documentation to get access to the fault symptoms, which are
the association of a warning/malfunction and/or CFDS fault message. The fault
symptoms are divided into the five following sections:
S ECAM,
S EFIS (Electronic Flight Instrument System),
S LOCAL warning,
S Crew & Maintenance Observation and,
S CFDS.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 29|TS Airnav|L2 Page 70

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 36 Trouble Shooting Process − AIRN@V Entry

FRA US/T-5 PoL Mar 8, 2010 29|TS Airnav|L2 Page 71
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
ECAM WARNING SELECTION
To find the reported problem (ELEC BCL 1 FAULT in this example), you have
to select ECAM Warning and enter the name of the ECAM WARNING
MESSAGE, which appears on the PFR (or on the ECAM Display Unit). You
can also enter the ATA chapter to have a list of Warnings/malfunctions, and
then you select the related ECAM warning message.
NOTE: If required, additional Warnings/malfunctions must be selected.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 29|TS Airnav|L2 Page 72

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 37 Trouble Shooting Process − ECAM Warning Selection

FRA US/T-5 PoL Mar 8, 2010 29|TS Airnav|L2 Page 73
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
TROUBLE SHOOTING PROCESS
CORRELATION
A Warning/malfunction with its correlated CFDS fault could have several
associated fault isolation procedure tasks according to the systems, which
have detected the fault. The PFR gives a SOURCE item, which must be
compared with the SOURCE item of the CFDS Fault messages list in Airn@v.
By selecting the appropriate fault message, the Airn@v system gives the right
access to the fault isolation procedure.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 29|TS Airnav|L2 Page 74

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 38 Trouble Shooting Process − Correlation

FRA US/T-5 PoL Mar 8, 2010 29|TS Airnav|L2 Page 75
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FAULT ISOLATION PROCEDURE
The related fault isolation procedure task in Airn@v (TASK number
24−30−00−810−805) has a presentation of possible causes and the fault
confirmation (for example by an operational test, power−up test or GROUND
SCANNING). It also gives the fault isolation procedure including LRU (Line
Replaceable Unit) removal/installation, wiring check, etc.... In addition, the
procedure gives access to the useful aircraft documentation references
knowing that all manuals contained in AirN@v are interconnected by
hyperlinks, and all the schematics can be found and printed easily.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 29|TS Airnav|L2 Page 76

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
CENTRALIZED FAULT DISPLAY
INTERFACE (CFDIU) 31−32
FOR TRAINING PURPOSES ONLY!

Figure 39 Fault Isolation Procedure

FRA US/T-5 PoL Mar 8, 2010 29|TS Airnav|L2 Page 77
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
UP AND DOWN DATALOADING SYSTEM
ACQUISITION/INTERFACE & EQUIPMENT 31−38

31−38 UP AND DOWN DATA LOADING SYSTEM

SYSTEM DESCRIPTION
GENERAL
The data loading system is an interface between the aircraft computers and
ground data processing equipment used to update software (S/W) and
database or to retrieve aircraft system data. The data loading system includes:
S a DLS (Data Loading Selector) to select the desired computer to be loaded,
S a MDDU (Multipurpose Disk Drive Unit) to upload or download data,
S a stowage box with a 42 disk maximum capacity,
S a DLRB (Data Loading Routing Box) to route the input/output data between
the disk unit and the target computer.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 30|Data Load|L2 Page 78

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
UP AND DOWN DATALOADING SYSTEM
ACQUISITION/INTERFACE & EQUIPMENT 31−38

101 TD

POWR SPLY
FROM DLRB

103PP
103XP-B 28VDC
115 VAC BUS1
BUS1
FOR TRAINING PURPOSES ONLY!

102 TD
1 TD

Figure 40 Data Loading Component Location

FRA US/T-5 PoL Mar 8, 2010 30|Data Load|L2 Page 79
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
UP AND DOWN DATALOADING SYSTEM
ACQUISITION/INTERFACE & EQUIPMENT 31−38

UP & DOWN DATA LOADING SYSTEM INTERFACES

UP LOADING
The aircraft system computers use the loading system to update their data
base, for example the FMGC (Flight Management and Guidance Computer) or
to modify parts of their operational S/W, for example the ATSU (Air Traffic
Service Unit). The Up loading is automatically done from a 3.5 inch disk, via an
internal logic specific to each computer.
DOWN LOADING
The down loading system is used to down load, to a 3.5 inch disk, the data
recorded by some computers during aircraft operation, for example the DMU
(Data Management Unit) part of the FDIMU on enhanced aircraft (Flight Data
Interface and Management Unit).
Down loading is done automatically through an internal logic specific to each
computer.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 31|DL Interface|L3 Page 80

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
UP AND DOWN DATALOADING SYSTEM
ACQUISITION/INTERFACE & EQUIPMENT 31−38
FOR TRAINING PURPOSES ONLY!

DMC: DISPLAY MANAGEMENT COMPUTER FMGC: FLIGHT MANAGEMENT & GUIDANCE COMPUTER
FDIMU: FLIGHT DATA INTERFACE MANAGEMENT UNIT (DMU + FDIU) TCAS: TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM
DMU: DATA MANAGEMENT UNIT ATSU: AIR TRAFFIC SERVICE UNIT
FDIU: FLIGHT DATA INTERFACE UNIT CFDIU: CENTRALIZED FAULT DISPLAY INTERFACE UNIT

Figure 41 Up Loading & Down Loading Interfaces

FRA US/T-5 PoL Mar 8, 2010 31|DL Interface|L3 Page 81
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
UP AND DOWN DATALOADING SYSTEM
ACQUISITION/INTERFACE & EQUIPMENT 31−38

UP & DOWN DATA LOADING SYSTEM UTILIZATION

GENERAL file identical to the previous one and its order in the sequence must be up
The MDDU (Multipurpose Disk Drive Unit) has two functions: uploading and loaded on the same computer.
downloading. According to the operation to do, the disk, which is used, has to When you have ejected the disk from the disk drive, you have to set the
contain specific information (e.g. configuration file). Before doing an up data ON/OFF switch on the DLS to OFF. Check on one of the MCDUs that the
loading operation, refer to the relevant procedure for the related system in the software (S/W) reference shown on the LRU (Line Replaceable Unit)
AMM (Aircraft Maintenance Manual). IDENTIFICATION page of the concerned computer agrees with the S/W
NOTE: Up loading procedure will only be illustrated, down loading is similar. reference of the disk used for the up loading.

UP LOADING PROCEDURE DOWN LOADING PROCEDURE

When you have selected the disk related to the computer to be loaded from the If there is no disk inserted in the data loader disk drive, the system is in the
disks in the storage box, you have to select the computer by means of the DLS standby state and does not communicate with any onboard computers. The
(Data Loading Selector). The MDDU READY message is shown on the MDDU MDDU READY message is shown on the MDDU window: the system is in
window: the system is in the standby state. After selecting FMGC (Flight standby state. The MDDU is activated by inserting the disk containing a
Management and Guidance Computer) 2 on the DLS, you have to open the configuration file defining the label of the computer concerned by a down
MDDU door, insert the disk in the data loader disk drive and close the MDDU loading operation: the READY message is shown on the MDDU window.
door. When the disk is inserted in the disk drive, the READY message is Supposing that the disk inserted is configured to dialog with the DMU (Data
shown: this message acknowledges disk insertion. The MDDU processes the Management Unit), the operator can down load the reports by pushing the
specific information contained in the disk, contacts the computer to be loaded SELector ConTroL key on the DLS when AIDS (Aircraft Integrated Data
and shows the WAIT RESPONSE message until the computer is ready to System) is shown. After the computer has acknowledged the request, it sorts
receive the data. This message stays permanently displayed when: the data to be transferred into files and interrupts the wait phase established
with the MDDU: the WAIT RESPONSE message is shown on the MDDU
S the computer is not power supplied or is out of order,
window. Then, the computer downloads its information: the TRANSF IN PROG
S the DLS is set to the wrong computer, message is shown throughout the transfer. When the data transfer is
S the configuration file is not correct, terminated and no anomalies are detected, the TRANSF COMPLETE message
S the LGCIU (Landing Gear Control and Interface Unit) 1 is not powered. is shown to tell the operator that the transfer is successfully completed.
As soon as a dialog is established between the computer to be loaded and the ABNORMAL OPERATION
FOR TRAINING PURPOSES ONLY!

data loader, the TRANSFer IN PROGress message is displayed and the data
Other messages shown on the MDDU window tell the operator of the transfer
is transferred to the computer.
status:
NOTE: The disk should not be extracted while TRANSF IN PROG message is
S TRANSFER FAILURE: If the MDDU has to stop data transfer (up or down
shown as damage to the disk could result.
loading) for any reason, this message is shown.
When the data transfer is terminated and no anomalies are detected, the
S UNIT FAIL: The MDDU shows this message if a hardware (H/W) failure is
TRANSF COMPLETE message is shown to inform the operator that the
detected during the self−test. In this case, the MDDU stops all operations.
transfer is successfully completed.
S DISK ERROR: If the MDDU cannot read or write data on the disk (incorrect
If more than one disk for the up loading is necessary , the EJECT DISK and
formatting, write−protected, disk damaged, etc), it will interrupt the
INSERT NEXT DISK message are displayed one after the other on the MDDU
operations and send this message.
when the next disk needs to be inserted. This disk must contain a configuration

FRA US/T-5 PoL Mar 8, 2010 32|SYS OPS|L2 Page 82

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
UP AND DOWN DATALOADING SYSTEM
ACQUISITION/INTERFACE & EQUIPMENT 31−38
FOR TRAINING PURPOSES ONLY!

Figure 42 Data Loading System Operation

FRA US/T-5 PoL Mar 8, 2010 32|SYS OPS|L2 Page 83
Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
INDICATING/RECORDING
SYSTEMS-GENERAL 31−00

31−00 INDICATING/RECORDING SYSTEMS - GENERAL

AIRMAN (OPTIONAL) PRESENTATION
GENERAL
AIRMAN is a ground−based software dedicated to the identification and the
management of unscheduled maintenance.
AIRMAN receives and analyses the aircraft status information generated by the
Onboard Maintenance System (OMS) and also e−logbook data.
The information is automatically transmitted to the ground by the aircraft’s
communication system.
These information sources are synthesized, combined with Airbus’s and the
Airline’s own technical documentation and presented through a user−friendly
interface. Aircraft status information is sent to AIRMAN while the aircraft is both
in flight and on ground. Message analysis also takes place in real−time.
These capabilities maximize the time available for appropriate maintenance
actions to be determined and preparations to be made.
AIRMAN is capable of analyzing an aircraft’s fault history and consequently
identifying and prioritizing preventive maintenance actions.
The aircraft maintenance philosophy is based on the following steps:
S fault detection made by the computers BITEs,
S cockpit effects as flags on Display Units, and warning generated by the
Flight Warning System (FWS),
S centralization and correlation by the Onboard Maintenance System (OMS)
of BITE faults, cockpit effects and related maintenance procedures
generation of Post Flight Report (PFR)
FOR TRAINING PURPOSES ONLY!

S fault event data reporting through the eLogbook (option)

S fault event data and reports transmission to AIRMAN for maintenance
support on ground

FRA US/T-5 PoL Mar 8, 2010 33|AIRMAN|L2 Page 84

Lufthansa Technical Training
INDICATING/RECORDING SYSTEMS A318/A319/A320/A321
INDICATING/RECORDING
SYSTEMS-GENERAL 31−00
FOR TRAINING PURPOSES ONLY!

Figure 43 Airman Overview (Option)

FRA US/T-5 PoL Mar 8, 2010 33|AIRMAN|L2 Page 85
Lufthansa Technical Training
INDICATING/RECORDING SYSTEM A318/A319/A320/A321
E-LOGBOOK
31

E-LOGBOOK (OPTION)
GENERAL
The eLogbook is the main communication means for aircraft operational staff. It
enables the flight crew and the technical staff to be aware of the aircraft status,
to enter aircraft defect and to report maintenance and servicing actions.
The eLogbook lets the flight crew:
S consult the Logbook status,
S accept / create a new flight,
S report aircraft defects,
S hand over to maintenance.
The maintenance staff uses the eLogbook to:
S consult the aircraft status,
S report aircraft defects,
S report corrective or scheduled maintenance actions,
S report servicing actions,
S build the Certificate of Release into Service (CRS) of the aircraft.
Finally the cabin crew can also use the eLogbook to:
S consult the aircraft status,
S inform the flight crew about regulatory cabin defects,
S report none regulatory cabin defects.
The eLogbook runs on a fully stand−alone laptop and is not connected to the
aircraft. The eLogbook is stowed in the cockpit by the flight crew.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 8, 2010 34|e−Logbook|L2 Page 86

Lufthansa Technical Training
INDICATING/RECORDING SYSTEM A318/A319/A320/A321
E-LOGBOOK
31
FOR TRAINING PURPOSES ONLY!

Figure 44 e-Logbook (OPTION)

FRA US/T-5 PoL Mar 8, 2010 34|e−Logbook|L2 Page 87
A318-21_31-32_L3

TABLE OF CONTENTS
ATA 31 INDICATING/RECORDING SYSTEMS 1 TROUBLE SHOOTING PROCEDURE WITH CFDS . . . 68
TROUBLE SHOOTING PROCESS . . . . . . . . . . . . . . . . . . 70
31−32 CENTRALIZED FAULT DISPLAY INTERFACE (CFDIU) 2 31−38 UP AND DOWN DATA LOADING SYSTEM . . . . . . . . . . 78
CFDS PRESENTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . 78
SYSTEM BITE PHILOSOPHY . . . . . . . . . . . . . . . . . . . . . . 4 UP & DOWN DATA LOADING SYSTEM INTERFACES 80
SYSTEM BITE PHILOSOPHY CONTINUED . . . . . . . . . 6 UP & DOWN DATA LOADING SYSTEM UTILIZATION 82
SYSTEM BITE PHILOSOPHY . . . . . . . . . . . . . . . . . . . . . . 8
31−00 INDICATING/RECORDING SYSTEMS - GENERAL . . . 84
CFDS MODES PRESENTATION . . . . . . . . . . . . . . . . . . . . 8
AIRMAN (OPTIONAL) PRESENTATION . . . . . . . . . . . . . 84
SYSTEM BITE TYPES INTERFACE . . . . . . . . . . . . . . . . . 10
E-LOGBOOK (OPTION) . . . . . . . . . . . . . . . . . . . . . . . . . . . 86
CLASS 1 FAILURE PRESENTATION . . . . . . . . . . . . . . . . 12
CLASS 2 FAILURE PRESENTATION . . . . . . . . . . . . . . . . 14
CLASS 3 FAILURE PRESENTATION . . . . . . . . . . . . . . . . 16
SYNTHESIS SYSTEM DESCRIPTION AND FAILURE
CLASSES OVERVIEW . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
MULTIPURPOSE CONTROL AND DISPLAY
UNIT DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
CFDS REPORTS TROUBLESHOOTING . . . . . . . . . . . . 22
CFDS REPORTS (AV STS) TROUBLESHOOTING . . . . 30
CFDS REPORTS (SYS REP/TEST) PRESENTATION . 32
CFDS REPORTS (MENU TYPES) PRESENTATION . . 34
CFDS REPORTS (PFR) INTRODUCTION . . . . . . . . . . . 40
GMT/DATE INITIALIZATION OPERATION . . . . . . . . . . . 42
ACARS/ PRINT PROGRAM OPERATION . . . . . . . . . . . . 44
CFDS PFR FILTER PROGRAM-MAINTENANCE
PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
PFR FILTERING FUNCTION MAINTENANCE
PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48
PFR FUNCTION (INDICATION) OPERATION . . . . . . . . 50
POST FLIGHT REPORT FILTERING FUNCTION
(EXAMPLE) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52
BACKUP MODE (OPTION) OPERATION . . . . . . . . . . . . 54
PASSWORD CHANGE (OPTION) OPERATION . . . . . . 56
CFDS PHASES FUNCTIONAL OPERATION . . . . . . . . . 58
CFDIU FUNCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60
CFDIU TEST MENU PRESENTATION . . . . . . . . . . . . . . 64
CFDS COMPONENT LOCATION . . . . . . . . . . . . . . . . . . . 66

Page i
A318-21_31-32_L3

TABLE OF CONTENTS

Page ii
A318-21_31-32_L3

TABLE OF FIGURES
Figure 1 CFDS Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 Figure 36 Trouble Shooting Process − AIRN@V Entry . . . . . . . . . . . . . . 71
Figure 2 BITE Philosophy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Figure 37 Trouble Shooting Process − ECAM Warning Selection . . . . . 73
Figure 3 Reports Presentation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 Figure 38 Trouble Shooting Process − Correlation . . . . . . . . . . . . . . . . . . 75
Figure 4 Internal/External Failures & Failure Gravity . . . . . . . . . . . . . . . . 9 Figure 39 Fault Isolation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 77
Figure 5 System Types . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 Figure 40 Data Loading Component Location . . . . . . . . . . . . . . . . . . . . . . 79
Figure 6 Class 1 Failure Indication and Annunciation . . . . . . . . . . . . . . . 13 Figure 41 Up Loading & Down Loading Interfaces . . . . . . . . . . . . . . . . . . 81
Figure 7 Class 2 Failure Presentation . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 Figure 42 Data Loading System Operation . . . . . . . . . . . . . . . . . . . . . . . . 83
Figure 8 Class 3 Failure Presentation . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 Figure 43 Airman Overview (Option) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85
Figure 9 Failure Classification Synthesis . . . . . . . . . . . . . . . . . . . . . . . . . . 19 Figure 44 e-Logbook (OPTION) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87
Figure 10 MCDU LCD & CRT Version . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
Figure 11 CFDS Menus on Ground and in Flight . . . . . . . . . . . . . . . . . . . 23
Figure 12 Last Leg Report . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
Figure 13 Last Leg ECAM Report . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
Figure 14 Previous Legs Report . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
Figure 15 Avionics Status . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
Figure 16 System Report/Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
Figure 17 System Report/Test - BSCU SYS1 (Type 1 System) . . . . . . . 35
Figure 18 System Report/Test−AEVC (Type 2 System) . . . . . . . . . . . . . 37
Figure 19 System Report/Test−GCU EMER (Type 3 System) . . . . . . . . 39
Figure 20 Post Flight Report . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
Figure 21 GMT/Date Initialization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
Figure 22 ACARS/Print Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45
Figure 23 PFR Filter Program − Filter Activated & Print Filter Content 47
Figure 24 Purpose & Filter Data Base Customization and Loading . . . 49
Figure 25 Filter Data Base Identification . . . . . . . . . . . . . . . . . . . . . . . . . . 51
Figure 26 Examples . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53
Figure 27 Backup Mode (OPTION) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55
Figure 28 PASSWORD SETTINGS (OPTION) . . . . . . . . . . . . . . . . . . . . 57
Figure 29 Ground/Flight Transition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59
Figure 30 CFDIU Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61
Figure 31 CFDIU Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63
Figure 32 CFDS System Report/Test Menu . . . . . . . . . . . . . . . . . . . . . . . 65
Figure 33 Components Location (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66
Figure 34 Components Location (2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 67
Figure 35 Cockpit Effect & PFR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69

Page i
A318-21_31-32_L3

TABLE OF FIGURES

Page ii
A318-21_31-32_L3

TABLE OF FIGURES

Page iii
A318-21_31-32_L3

TABLE OF FIGURES

Page iv