C. Main Components (For further details, Ref. to 31-63-00). To perform the EFIS and ECAM functions, the EIS includes two main types of equipment:
(1)
Display Management Computer (DMC) Three identical computers installed in the avionics compartment (DMC 1, DMC 2, DMC 3) are in charge to acquire data and parameters from various aircraft systems, to gather them on the A629 link to the display unit which generates the symbologies for the displays in the cockpit.
(2)
Display Unit (DU) Six identical display units receive dynamic parameters for the presentation of the whole flight and aircraft system information necessary to the crew. The DUs are called by the name of the display they present in normal operation i.e:
-
CAPT or F/O PFD,
-
CAPT or F/O ND,
-EWD,
-SD.
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D. Operation (Ref. Fig. 002)
(1)
Normal operation In normal operation, each DMC, with respect to sensor and computer inputs, acquires data/parameters through its ONSIDE sources to gather all necessary data in order for the display unit driven by the DMC to generate all graphic symbologies related to a particular image. The OFFSIDE sources and/or THIRD sources (if any) are redundancy information sources. In normal operation, the following DMC drives the following display units:
-
the DMC 1 drives the CAPT PFD DU, the CAPT ND DU, the EWD and the SD,
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the DMC 2 drives the F/O PFD DU and the F/O ND DU,
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the DMC 3 is a hot spare able to drive any of the six DUs.
(2)
Abnormal operation/reconfiguration In order to ensure the greatest availability of the displayed data, the fully redundancy architecture of the system enables three types of reconfiguration in case of any component failure:
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in case of single or multiple DU failures,
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in case of single or multiple DMC failures,
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in case of external (sensor/computer) information source failures. (For further details, Ref. to 31-68-00).
E. Test/Built-In Test Equipment (BITE)
(1) General The EIS computers include a self-test function i.e., a Built-In Test Equipment (BITE) and are connected to the CFDS maintenance system for centralization of the whole maintenance data. Each DMC carries out the BITE functions at once for itself and for its connected DUs. The BITE detects internal failures/input parameter failure, minimizes undetected failures and facilitates the maintenance. Reports are stored in a non volatile memory (NVM) inside the items of equipment and are sent to the Central Fault Display System (CFDS) permanently or during check. (For further details, Ref. to 31-69-00).
F. Teleloading function The EIS components may undergo a modification of their functional application software by the process of teleloading. Special wiring is provided for that purpose. The process is described in chap. 31.69.00
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EIS - Architecture
Figure 002
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G. EIS Sections
(Ref. Fig. 003)
(1) EIS breakdown Here after are listed all the EIS sections as well as a summary or their contents: 31-60-00-Electronic Instrument System (EIS)
-
The purpose of this document is to give a general description of the EIS (EIS components, display functions, reconfiguration capabilities...).
31-61-00-EIS Control and Supply
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The purpose of this document is to describe the control panels function linked to the display units, and its power supply arrangements
31-63-00-Display Management Computer (DMC)/LCD Display (LCD) control and interconnection
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The purpose of this document is to give the detailed description of the DMC and the DU hardware, the Inputs/Outputs of the DUs and the DMC/DU interconnection.
31-64-00-Primary Flight Display (PFD)
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The purpose of this document is to give the detailed description of
the PFDs, the display logics and the associated controls. 31-65-00-Navigation Display (ND)
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The purpose of this document is to give the detailed description of
the NDs, the logics and the associated controls. 31-66-00-Engine/Warning Display (EWD)
-
The purpose of this document is to give the detailed description of
the EWD, the logics and the associated controls. 31-67-00-System Display (SD)
-
The purpose of this document is to give the detailed description of
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