-
The FDIMS can transmit reports to the Aircraft Communication Addressing and Reporting System (ACARS) and to the printer in the cockpit.
-Via the MCDUs in the cockpit, it is possible to control the FDIMS and to see system-reports.
-A PCMCIA-Interface is integrated in the FDIMU to upload application-software and to download AIDS-reports with a notebook-computer.
-It is also possible to load the application-software of the FDIU- and DMU-part via a Portable Data Loader (PDL) or a Multipurpose Disk Drive Unit (MDDU)(if installed) in the cockpit.
-The power supply operates from the 115VAC 400Hz single-phase power of the A/C.
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System Block Diagram Figure 002A
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R System Block Diagram Figure 002B
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DFDRS Interconnection Schematic 1/2
Figure 003
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DFDRS Interconnection Schematic 1/2
Figure 003A
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DFDRS Interconnection Schematic 2/2
Figure 004
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A. DFDRS Function: The FDIU-part collects all critical flight-parameters from various A/C-systems and sends it to the DFDR. The FDIU-part converts the flight parameters and sends them in serial digital format to the DFDR. These flight-parameters are stored to the DFDR and to the QAR (if installed) in data-frame cycles. At the same time the FDIU-part sends an audio signal encoded in GMT-information to the Cockpit Voice Recorder (CVR).
The three-axis Linear Accelerometer (LA) is installed between Frame 42 and 45 under a floor panel of the passenger compartment (center of gravity of the A/C). The LA generates acceleration data in analog format. The analog information from the LA is sent to the System Data Acquisition Computer (SDAC). The SDAC converts this information to a digital format and sends it to the FDIU-part via an ARINC-429 data-bus. The FDIU-part sends this acceleration data to the DFDR together with the other flight-parameters. On each flight the FDIU-part makes an integrity check of the acceleration-parameters.
The status of the DFDR and the status of the FDIU-part (failure/no failure) is monitored by the SDACs. If a failure occurs, it is shown on the ECAM display.
For maintenance and test of the DFDRS, the FDIU-part is connected with the Centralized Fault Display Interface Unit (CFDIU) of the Centralized Fault Display System (CFDS).
B. AIDS Function (Ref. 31-36-00)
C. System Architecture (Ref. Fig. 002A) The basic DFDRS Components are:
-
A Flight Data Interface Management Unit (FDIMU) (FDIU-Part)
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A Digital Flight Data Recorder (DFDR)
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A Linear Accelerometer (LA)
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A Control Panel (CTL PNL)
-An Event Marker Button (EVENT).
The minimum equipment of a basic DFDRS (FDIMU, DFDR, LA, CTL PNL and
EVENT) must be installed on each aircraft. This is to meet the
requirement of the authorities for recording of mandatory parameters.
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(Ref. Fig. 002B)
The FDIU is connected to different aircraft systems. DATA (parameters) are received in discrete and digital form. The FDIU collects these parameters and converts them for internal processing. A standardized set of flight critical parameters are transmitted in serialized digital form to the DFDR. These parameters are stored on the recorder in data frame cycles. The FDIU generates aircraft data and sends them to the ARINC 429 output bus. A separate linear accelerometer is installed to provide the FDIU with acceleration data appearing in the center of gravity. The SDAC digitizes the analog signal of the LA and sends it to the FDIU via ARINC 429 bus. The EVENT Button and the Override Button of power interlock are located on the CTL PNL's.
A. Not Applicable
B. Not Applicable
C. System Architecture
(Ref. Fig. 002B)
**ON A/C 151-158, 201-209,
(Ref. Fig. 003A, 004A)
**ON A/C 151-199, 201-210,
The basic DFDRS Components are:
-
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