-115V AC-power from the ARINC-Connector-Card
-system test-signals
The test-connector enables the connection of portable
test-equipment and a data-loader to the FDIMU.
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**ON A/C 151-199, 201-210,
A. Data Management Unit (DMU) (Ref. Fig. 004A, 005A, 006A)
The DMU is a microprocessor-controlled unit with a module for collection and processing of digital parameters to monitor data by various aircraft systems. An expanded function is the creation of various A/C condition reports. This monitoring is to derive maintenance relevant data. The internal SAR stores the result of specific trigger conditions. The DMU-functional block diagram illustrates the internal connection of the functional modules of the DMU.
B. Hardware Layout of the DMU
(1)
Power Supply Board The power-suppy board converts aircraft power to operating power for the DMU. It also generates discretes discrete status and clock signals for the processors.
(2)
DMU Processor Board
The processor board consists of:
-a microprocessor 80386SXL and its support circuits
-Static RAM (SRAM), Nonvolatile SRAM (NVSRAM) and electrically programmable read-only memory (EEPROM)
-programmable interrupt controllers
-Serial interface AD232
(3)
The ARINC Board
The ARINC board consists of:
-two controller/arbitrator ARINC 429 gate arrays (CARGAS) and the interconnected ARINC receivers
-an input/output gate array (IOGA) and the interconnected input/output devices
-a logic analyzer interface
(4)
Not Applicable
(5)
Not Applicable
(6)
Not Applicable
(7)
Not Applicable
(8)
Not Applicable
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R DMU Interface Figure 006A
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R **ON A/C 106-149, 211-299, 301-399, 401-499,
C. General Functions of the FDIMU
(1) Identification of Location The design of the FDIMU allows its use in A/C with different input parameters and different tasks for data evaluation, if the appropriate programs are implemented. The unit is able to identify A/C type information on the internal FDIU-bus. Depending on the occurance of specific conditions or events, the FDIMU (DMU-part) has trigger predefined actions. As a result of specific trigger conditions AIDS reports may be generated or data may be recorded on the DAR (optional) or stored in the FDIMU internal Smart Access Recorder (SAR). Print reports can be either printed out on the cockpit printer or transmitted via ACARS (optional). SAR data is also retrieved via the Portable Data Loader (PDL). Functions which are specific to A/C type (CFMI or IAE engines) are indicated in the respective logic definition.
The A/C type coding, parameter 17.1.304.00, is shown below: Engine Type | Bit No. | 16 15 14 13 12 11 -------------------------------|----------------------------
For CFM 56-5 | 0 1 0 0 1 1
For IAE V2500 | 0 1 0 1 0 0
For P&W | 0 1 1 1 0 0
If the code for no programming is received, the FDIMU works according to the A/C type code from the last flight. If there is no coding from the last flight, the FDIMU works with the CFMI type code.
(2)
History Buffer A history buffer is provided for the history data required by the AIDS reports and the DAR and SAR. It is the responsibility of the sampling task, to control this buffer and manage the history buffering. The management of the history buffer is determined by the parameter sampling table. It is possible to program additional parameters for history buffering via Ground Support Equipment (GSE).
(3)
FDIMU Internal Parameter Internally the FDIMU processed-parameters are referred to as "Internal Parameters". All internal parameters are identified by a parameter number consisting of the EQ/SYS/LABEL/SDI. For the FDIMU applications up to 400 internal parameters can be created. In addition the parameter can be assigned with an alpha call-up code for identification through GSE programming.
R 1EFF : 106-149, 211-299, 301-399, 401-499, 1 31-36-00Page 63 1 1 Config-2 Aug 01/05 1 1 1CES 1 Internal parameters are provided for:
-FDIMU internal counter and timer
-Filtered Parameters
-Flags for certain flight conditions
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