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TECHNICAL TRAINING MANUAL

T1+T2 (IAE V2500) (Lvl 2&3)

RECORDING SYSTEMS

RECORDING SYSTEMS Recording System Component Location (2).................... 2

UP & DOWN DATA LOADING SYSTEM

Up & Down Data Loading System Presentation (2).............. 8 Up & Down Data Loading System Utilization (2)............... 12

DIGITAL FLIGHT DATA RECORDING SYSTEM (DFDRS)

DFDRS Description/Operation (3)........................... 16 FDIMU Interfaces (3)..................................... 18

A/C INTEGRATED DATA SYSTEM (AIDS-SFIM)

Print Report STD Header Description (3)..................... 20 Individual Print Report Description (3)....................... 26 AIDS Programming (3)................................... 54

A/C INTEGRATED DATA SYS (AIDS-TELEDYNE) (option)

Print Report STD Header Description (3)..................... 60 Individual Print Report Description (3)....................... 66 AIDS Description/Operation (3)............................ 96

T1+T2 (IAE V2500) (Lvl 2&3) TABLE OF CONTENTS Feb 01, 2011

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SYSTEM OVERVIEW

T1+T2 (IAE V2500) (Lvl 2&3) RECORDING SYSTEM COMPONENT LOCATION (2) Feb 01, 2011

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RECORDING SYSTEM COMPONENT LOCATION (2)

COMPONENT LOCATION

The DFDRS and AIDS computers are in the aft avionics rack. About the QAR/DAR, there are several vendors of optical disk storage media. The recorder is then called Optical QAR/DAR (OQAR/ODAR). There is also a version from Teledyne that includes a GSM module for data transmission called WQAR (Wireless GroundLink QAR). The FDIMU computer is in the aft avionics rack. The SSFDR is installed immediately above the Cockpit Voice Recorder (CVR), in an unpressurized area of the rear fuselage. The SSFDR stores the data of the last 25 hours collected by the FDIU. The SSFDR stores these data in a solid state memory which is in a crash-and-fire-protected housing. The linear accelerometer is near the A/C center of gravity. It sends the accelerations in the 3 axes (pitch, roll and yaw) to the DFDRS.

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COMPONENT LOCATION

T1+T2 (IAE V2500) (Lvl 2&3) RECORDING SYSTEM COMPONENT LOCATION (2) Feb 01, 2011

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COMPONENT LOCATION

T1+T2 (IAE V2500) (Lvl 2&3) RECORDING SYSTEM COMPONENT LOCATION (2) Feb 01, 2011

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GENERAL

T1+T2 (IAE V2500) (Lvl 2&3) UP & DOWN DATA LOADING SYSTEM PRESENTATION (2) Feb 01, 2011

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UP & DOWN DATA LOADING SYSTEM PRESENTATION (2)

UP LOADING

The aircraft system computers use the loading system to update their data base, for example the Flight Management and Guidance Computer (FMGC) or to modify parts of their operational S/W, for example the Air Traffic Service Unit (ATSU). The Up loading is automatically done from a 3.5 inch disk, via an internal logic specific to each computer. The installation of Portable Data Loader (PDL) connectors enables ARINC 615A data loading of the ATSU. Power supply plug is installed to enable data loader power supply.

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 Data Management Unit (DMU) part of the Flight Data Interface and Management Unit (FDIMU). Down loading is done automatically through an internal logic specific to each computer.

T1+T2 (IAE V2500) (Lvl 2&3) UP & DOWN DATA LOADING SYSTEM PRESENTATION (2) Feb 01, 2011

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UP & DOWN DATA LOADING SYSTEM UTILIZATION (2)

GENERAL

The Multipurpose Disk Drive Unit (MDDU) has two functions: uploading and downloading. According to the operation to do, the disk, which is used, has to contain specific information (e.g. configuration file). Before doing an up data loading operation, refer to the relevant procedure for the related system in the Aircraft Maintenance Manual (AMM).

NOTE: Up loading procedure will only be illustrated, down loading is similar.

UP LOADING PROCEDURE

When you have selected the disk related to the computer to be loaded from the disks in the storage box, you have to select the computer by means of the Data Loading Selector (DLS). The MDDU READY message is shown on the MDDU window: the system is in the standby state. After selecting Flight Management and Guidance Computer (FMGC) 2 on the DLS, you have to open the MDDU door, insert the disk in the data loader disk drive and close the MDDU door. When the disk is inserted in the disk drive, the READY message is shown: this message acknowledges disk insertion. The MDDU processes the specific information contained in the disk, contacts the computer to be loaded and shows the WAIT RESPONSE message until the computer is ready to receive the data. This message stays permanently displayed when:

• the computer is not power supplied or is out of order,
• the DLS is set to the wrong computer,
• the configuration file is not correct,
• the Landing Gear Control and Interface Unit (LGCIU) 1 is not powered. As soon as a dialog is established between the computer to be loaded and the data loader, the TRANSFert IN PROGress message is displayed and the data is transferred to the computer.

NOTE: The disk should not be extracted while TRANSF IN PROG message is shown as damage to the disk could result. When the data transfer is terminated and no anomalies are detected, the TRANSF COMPLETE message is shown to inform the operator that the transfer is successfully completed. You have to deselect the computer by means of the DLS. If more than one disk for the up loading is necessary , the EJECT DISK and INSERT NEXT DISK message are displayed one after the other on the MDDU when the next disk needs to be inserted. This disk must contain a configuration file identical to the previous one and its order in the sequence must be up loaded on the same computer. When you have ejected the disk from the disk drive, you have to set the ON/OFF switch on the DLS to OFF. Check on one of the MCDUs that the software (S/W) reference shown on the Line Replaceable Unit (LRU) IDENTIFICATION page of the concerned computer agrees with the S/W reference of the disk used for the up loading.

DOWN LOADING PROCEDURE

If there is no disk inserted in the data loader disk drive, the system is in the standby state and does not communicate with any onboard computers. The MDDU READY message is shown on the MDDU window: the system is in standby state. The MDDU is activated by inserting the disk containing a configuration file defining the label of the computer concerned by a down loading operation: the READY message is shown on the MDDU window. Supposing that the disk inserted is configured to dialog with the Data Management Unit (DMU), the operator can down load the reports by pushing the SELector ConTroL key on the DLS when Aircraft Integrated Data System (AIDS) is shown. After the computer has acknowledged the request, it sorts 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 window. Then, the computer downloads its information: the TRANSF IN PROG message

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is shown throughout the transfer. When the data transfer is terminated and no anomalies are detected, the TRANSF COMPLETE message is shown to tell the operator that the transfer is successfully completed.

ABNORMAL OPERATION

Other messages shown on the MDDU window tell the operator of the transfer status:

• TRANSFER FAILURE: If the MDDU has to stop data transfer (up or down loading) for any reason, this message is shown.
• UNIT FAIL: The MDDU shows this message if a hardware (H/W) failure is detected during the self-test. In this case, the MDDU stops all operations.
• DISK ERROR: If the MDDU cannot read or write data on the disk (incorrect formatting, write-protected, disk damaged, etc), it will interrupt the operations and send this message.

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DFDRS DESCRIPTION/OPERATION (3)

FDIMU

The Flight Data Interface and Management Unit (FDIMU) combines two functions which operate independently from each other: the Flight Data Interface Unit (FDIU) and the Data Management Unit (DMU). An internal data-bus connects the two parts. The FDIU-part receives discrete and digital parameters and processes them. The functions of the FDIU-part are:

• conversion,
• comparison,
• check and Built-In Test Equipment (BITE). The FDIU-part converts the input parameters into a numerical format for:
• the Digital Flight Data Recorder (DFDR),
• the optional Quick Access Recorder (QAR). -the Digital AIDS Recorder (DAR) The FDIU-part compares the data that it sends with the data recorded by the DFDR. The recorded data is transmitted back to the FDIU-part through the playback data bus. For PCMCIA recording function, data transmission from the FDIMU part to DMU part is given through an internal ARINC 429 data bus. The FDIU-part checks the integrity of the mandatory parameters during the flight. After the flight, engines shutdown, only the Linear Accelerometer (LA) signal check is done. The FDIU-part includes BITE and monitoring functions.

DFDR

The DFDR stores data, which the FDIU-part has collected during the last 25 hours. The data is recorded in data frames. Each frame contains data received during one second. The DFDR includes BITE functions. The DFDR status signal is sent to the Centralized Fault Display Interface Unit (CFDIU) through the FDIU-part and to the Electronic Centralized Aircraft Monitoring (ECAM) through the System Data Acquisition Concentrators

(SDACs). The DFDR energization is controlled through the power interlock circuit. The underwater locator beacon installed on the front face of the DFDR gives the location of the recorder if the aircraft is immersed in water following an accident. The underwater locator beacon has a battery, which is activated by both fresh and salt water.

QAR (OPTIONAL)

The QAR stores the same data as the DFDR for on ground performance, maintenance or condition monitoring tasks. The data frames stored in the QAR are identical to the DFDR data frames. The QAR includes BITE functions. The QAR status signals (QAR MEDIA LOW, QAR FAIL) are sent to the lamps on its front face and to the CFDIU through the FDIU-part. The QAR energization is controlled through the power interlock circuit. If installed, the DAR records data in a formatted optical disk.

LINEAR ACCELEROMETER

The task of the LA is to measure the acceleration of the aircraft in all three axes. The range of measurement is:

• vertical axis (Z): -3 to +6 g,
• longitudinal axis (X): -1 to +1 g,
• lateral axis (Y): -1 to +1 g. The LA generates an analog signal, which is sent to the SDACs. This signal is digitalized and sent to the FDIU-part through an ARINC 429 bus.

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