-
Tests failed: display unit black or diagonal line
NOTE : It is recommended to do a C/B reset with engines running.
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(2) Computer DMC
(a) Conditions of power-up tests initialization
-How long the computer must be de-energized: > 1 s.
-A/C configuration: whatever the A/C configuration on ground.
(b) Progress of power-up tests
-Duration: 4 s.
-Cockpit repercussions directly linked to power-up test accomplishment (some of other repercussions may occur depending on the A/C configuration, but these can be disregarded): -ECAM warning EIS DMC 1 or 2 or 3 FAULT Diagonal line on the three associated display units
(c) Results of power-up tests (cockpit repercussions, if any, in case of tests pass/tests failed).
-
Tests pass:
-ECAM warning
warning disappears
Appropriate images on the display units
-
Tests failed: -ECAM warning EIS DMC 1 or 2 or 3 FAULT Diagonal line on the three associated display units
R 1EFF : 001-049, 051-060, 101-101, 1 31-60-00Page A19 1 1 Config-1 May 01/05 1 1 1CES 1 ELECTRONIC INSTRUMENT SYSTEM (EIS) - DESCRIPTION AND OPERATION
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1. General
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A. Architecture
(1) Philosophy The Electronic Instrument System (EIS) architecture is designed to cope with requirements in regard to:
-REDUNDANCY (2 PFDs, 2 NDs, 1 EWD, 1 SD, 3 DMCs),
-SEGREGATION (4 types of symbologies, PFD, ND, EWD and SD),
-RECONFIGURATION capabilities for minimization of operational consequences and maximization of A/C availability in case of any EIS component failure.
B. Description (Ref. Fig. 001) The Electronic Instrument System (EIS) is an avionics system connected with most of the aircraft systems to carry out the two following main display functions:
(1) EFIS display function The Electronic Flight Instrument System display function is shared in two, one for CAPT and one for F/O. Each crew member has at his disposal two displays presenting the whole FLIGHT information (for safe flight and navigation): the PFD and the ND.
(a)
The two Primary Flight Displays (CAPT and F/O PFDs), presented on the outer display units (DUs) installed in front of each crew member, provide the whole short term flight information for the A/C control, mainly including A/C Attitude, Airspeeds, Altitudes, Heading and AFS annoncements. (For further details, Ref. to 31-64-00).
(b)
The two Navigation Displays (CAPT and F/O NDs), presented on the inner display units (DUs) installed in front of each crew member, indicate the medium term flight information necessary to locate the A/C with respect to navigation aids, map data and Flight Management System flight plans. The NDs provide also the weather radar (WXR) information. The NDs provide this information according to the modes selectable by the crew members. (For further details, Ref. to 31-65-00).
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EIS - Component Location in the cockpit
Figure 001
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(2) ECAM display function (For further details, Ref. to 31-66-00, 31-67-00). The Electronic Centralized Aircraft Monitoring display function is unique for both crew members. The ECAM display function presents the whole AIRCRAFT information via two displays: the EWD and the SD.
(a)
The Engine/Warning Display (EWD), presented on the upper display unit (DU) installed on the center instrument panel, presents the short term A/C information composed by engine primary indications, wing configuration information and warning/caution messages in case of any failure. (For further details, Ref. to 31-66-00).
(b)
The System Display (SD), presented on the lower display unit (DU) installed on the center instrument panel, presents A/C status messages and A/C system synoptic diagrams according to A/C configuration (flight phase or warning). Many pages are available corresponding to the various A/C systems. (For further details, Ref. to 31-67-00).
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