ATA 31 - INDICATING RECORDING SYSTEM

• Six Cathode Ray Tube (CRT) display units (DU)/Liquid Crystal Displays (LCD’s) are installed, all interchangeable

• 80 VU is our main avionic rack in avionic compartment, 49VU in the cockpit (OVHD

panel)

• Centralized Fault Data Interface Unit (CFDIU), Flight Data Interface Unit (FDIU), Flight Management and Guidance Computers (FMGC)(ARINC 429)(CFDIU provide back up UTC to MCDU)

• The Centralized Fault Display System (CFDS) is a MAN/MACHINE INTERFACE for maintenance purpose. (CFDIU have 2 channels normal and standby).

You can only use the CFDS on one MCDU at a time.

• Memorization of the 64 previous legs (Type 1 computers) report is done by most of the

BITEs.

• Two CFDS modes are available: NORMAL and MENU modes.

The MENU MODE is available only on ground.

• Class 1 failures are the most serious ones and require an immediate maintenance action subject to the Minimum Equipment List (MEL). (Class 2-10 days delay)

• Class 2 failures don’t require immediate attention, can be displayed in flight (ECAM STS Page) or on ground through MCDU → PFR / Last Leg ECAM Report

TRICK – Trip FWC 2 C/B to make Class 2 Faults disappear from ECAM STS Page

• Class 3 failures can be left uncorrected until the next scheduled maintenancecheck.

Class 3 failures can been displayed on ground only through MCDU -> Avionics status report

• Most systems are type 1 systems.

These systems can memorize failures, which occurred in the last 64 flight legs.

(2 ways communication with CFDIU on ARINC 429)

• Type 2 systems memorize only failures from the last flight leg.

• Type 3 systems cannot memorize failure messages. (TRU)

• The CFDIU capacity for warning messages memorization is up to 40 lines.

• CFDIU back-up channel communicates only with MCDU 1 and MCDU 3

• Clock has 2 sources of elec power:

- DC ESS BUS

- DC HOT BATT BUS

• ECAM (Electronic Centralized Aircraft Monitoring) is composed of:

- EWD (Engine / Warning Display) – Upper ECAM Display

- SD (System Display) - Lower ECAM Display

- 2 SDAC (System Data Acquisition Concentrator)

- 2 FWC (Flight Warning Computer)

- 3 DMC (Data Management Computer)

• Post Flight Report (PFR) can be printed on ground only.

PFR is generated by FWC after city pairing

• PFR is composed by:

- Last Leg Report (Class 1 and 2 faults)

- Last Leg ECAM Report (Messages generated and shown by ECAM during last flight)

• The LAST LEG ECAM REPORT shows the list of Electronic Centralized Aircraft Monitoring (ECAM) warning messages sent to the Centralized Fault Display Interface Unit (CFDIU) by the Flight Warning Computers (FWC).

• FDIMU (ENHANCED): FDIU + DMU

• FDIMU is used for digital/discrete signals and data collection from A/C systems.

It converts those data to a recordable format and send them to DFDR.

• The DFDR (Digital Flight Data Recorder) stores data, which the FDIU (Flight Data Interface Unit) has collected during the last 25 hours in a crash and fire protected housing.

• The QAR (Quick Access Recorder) stores the same data as the DFDR for on ground performance, maintenance or condition monitoring tasks.

• The SSFDR (Solid State Flight Data Recorder) is automatically supplied when the aircraft is in flight with engines running or not. The SSFDR is automatically supplied when the aircraft is on ground with one or both engines running.

The SSFDR continues to run up to five minutes after 2nd engine shutdown. Five minutes after the second engine shutdown, the SSFDR supply is automatically cut off.

• The ECP (ECAM Control Panel) outputs discrete for the CLeaR, ReCalL, StaTuS and

EMERgency CANCel keys wired to the FWCs, and for the ALL key wired to the DMCs.

• MASTER WARNING light flashes red for any red warning

• The Flight Warning Computers (FWC) monitor the aircraft systems. These computers are the heart of the ECAM system. Each FWC generates all warning messages to be displayed and supplies the attention getters. It also computes the flight phases and provides aural warnings.

• DMC they can simultaneously drive 3 DU (two Electronic Flight Instrument System (EFIS) and one ECAM).

• Failure of DMC 1+3:

The ECAM system page can temporarily be displayed instead of the engine/warning (EWD) image by manual page call.

• Loss of aural warnings:

Loss of text messages on E/W display.

Loss of attention getters:

The DMC receives no data from the FWCs and displays the following message: “FWS FWC 1 + 2 FAULT”.

• The Electronic Flight Instrument System (EFIS) are displayed on 4 identical Display Units (DU) and controlled through the EFIS control panels and the lighting/ loudspeaker control panels.

• The Electronic Centralized Aircraft Monitoring (ECAM) pages are displayed on 2 identical DU and controlled through the ECAM Control Panel (ECP).

• Primary Flight Display (PFD) image has priority over the Navigation Display (ND)

• One among SDAC, FWC, DMC and DU may be inoperative for dispatch. DMC 2 cannot drive the CAPT PFD and ND. DMC 3 drives any of the six DU. DMC 3 is a hot spare awaiting the failure of DMC 1 or 2 and can be switched to take over the DU linked to the failed DMC.

• DMC 1,2,3 are identical and interchangeable

• Flight phases are computed by FWC (Flight Warning Computer)

• PFD has priority over ND, if PFD’s DU fail the PFD will be displayed over ND’s DU.

• MASTER WARNING AND MASTER CAUTION have 2 lines of light bulbs inside each pushbutton, FWC 1 powers the upper row of lights on the CAPT side while FWC 2 powers the lower row of lights on FO side.

• AIDS is designed to monitor, store, display and print a/c system parameters. Core computers are DMUs.

• Acronyms:

- AIDS (Aircraft Integrated Data System)

- ATSU (Air Traffic Service Unit)

- FMGC (Flight Management and Guidance Computer)

- EVMU (Engine Vibration Monitoring Unit)

- DMC (Display Management Computer)

- ECAM (Electronic Centralized Aircraft Monitoring)

- SDAC (System Data Acquisition Concentrator)

- CFDS (Centralized Fault Display System)

- CFDIU (Centralized Fault Display Interface Unit)

- DU (Display Unit)

- FWC (Flight Warning Computer)

- ECP (ECAM Control Panel)