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LAST LEG REPORT is identified in the PREVIOUS
LEGS REPORT under the LEG -00.
"ON GROUND" PHASE
On ground, the system BITEs ensure:
- detection (Type 1/2/3 systems) and memorization
in their ground memory (Type 1/2 systems) of
internal faults only,
- transmission to the CFDIU of internal faults
for monitoring and establishment of the
AVIONICS STATUS.
All CFDS functions (e.g. PFR printing) are available
on request through the Multipurpose Control and Display
Units (MCDUs).
TMUCFDY02-T01 LEVEL 2
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TMUCFDY02-P01 LEVEL 2
CFDS: CFDS PHASES
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SELF EXAMINATION
When is the LAST LEG REPORT transfered to the
PREVIOUS LEGS REPORT?
A - At first engine start + 3 minutes.
B - At touch down.
C - After touch down when the aircraft speed
has been below 80 knots for 30 seconds.
When is the leg number incremented?
A - At ground/flight transition.
B - At flight/ground transition.
C - Both.
TMUCFDY02 LEVEL 2
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31 - INDICATING/RECORDING SYSTEMS
31-32-00 CFDS: CFDIU FUNCTIONS
CONTENTS:
Main Functions : Memory
Main Functions : Management
Main Functions : Correlation
Main Functions : Monitoring
Main Functions : Detection
Interfaces : Clock
Interfaces : FAC
Interfaces : FDIU
Interfaces : FWC
Interfaces : DMU
Interfaces : DMC
Interfaces : ATSU
Interfaces : EVMU
Abnormal Operation : Clock Backup
Abnormal Operation : Backup Mode
Abnormal Operation : CFDIU Failure
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CFDS: CFDIU FUNCTIONS
MAIN FUNCTIONS
MEMORY
The CFDIU stores the failure messages and the ECAM
warning messages in a Non Volatile Memory.
MANAGEMENT
The CFDIU manages failure information and adds data
such as GMT, DATE, ATA chapter, LEG, FLIGHT PHASE to
elaborate reports.
CORRELATION
If a computer internal failure is detected, the CFDIU
achieves a correlation function that means it isolates
or ignores the malfunctions of systems relating to
this failure.
Example : "ADC FAILURE" causes "NO DATA FROM ADC" in
other computers.
The CFDS will present only the initial failure in the
last leg report.
The function "IDENT" will then present the systems
affected by this failure.
MONITORING
The CFDIU scans permanently all input buses in order
to detect a transmitted failure message.
The CFDIU detects intermittent operation of the systems
and adds (INTM) to the failure message.
DETECTION
The CFDIU can detect the nature of the failure by
reading the ARINC words.
Nature of failures :
- Internal Ex : "SDAC FAULT"
- External Ex : "FWC 1: NO DATA FROM ADIRU1"
- Intermittent (INTM) added
- Class 3 (CLASS 3) added.
INTERFACES
CLOCK
The CFDIU permanently receives the GMT and the date
from the aircraft clock and then sends these two
parameters to all type 1 systems.
The GMT and date are used by the system BITEs as well
as the CFDIU for the various maintenance reports.
FAC (Flight Augmentation Computer)
The CFDIU receives the flight number and city pair
from the Flight Augmentation Computer. The city pair
(FROM/TO airport) is sent to the Air Traffic Service
Unit (ATSU) and to the Data Management Unit (DMU).
The CFDIU counts the number (maximum 8) of identical
and consecutive ECAM warning messages and records in
the "LAST LEG ECAM REPORT".
FDIU (Flight Recorders - DFDR)
The CFDIU receives the aircraft identification from
the Flight Data Interface Unit and sends this parameter
to all type 1 systems.
The CFDIU is used as an interface between the Flight
Data Interface Unit (FDIU) and the Flight Warning
Computer (FWC) to send some FDIU class 2 failures to
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