The 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 EFIS 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:
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EIS - Functional description
Figure 007
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(a) The two PFDs present the following short term data:
-attitude angles: Pitch, Roll, Heading,
-airspeed indications: computed Airspeed and various manoeuvring or limit speeds,
-altitude, vertical speed,
-trajectory deviations (ILS),
-automatic flight mode announcement,
-TCAS alert.
(For further details, Ref. to 31-64-00).
(b) The two NDs present the following long term data:
-radio navigation (VOR, DME, ILS, MLS, ADF),
-flight management paths,
-weather radar mapping,
-TCAS report.
-GPS status.
(For further details, Ref. to 31-65-00).
All the EFIS data are basically displayed but some may be
activated by pin programming.
(2) ECAM display function The ECAM display function is unique for both crew members (For further details, Ref. to 31-50-00). The ECAM display function presents the whole aircraft information via two displays: the EWD and the SD. (Ref. Fig. 008)
(a) The EWD presents the following data:
-engines primary indications,
-slats/flaps positions,
-warning/memo messages related to the main systems of the aircraft. (For further details, Ref. to 31-66-00).
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ECAM Display - EWD and SD
Figure 008
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(b) The SD presents the synoptic diagrams of the following systems:
-Engine secondary parameters . . . . . . ENGINE
-Air Bleed . . . . . . . . . . . . . . . AIR BLEED
-Cabin pressurization. . . . . . . . . . CAB PRESS
-Electrical power supply (AC/DC) . . . . ELEC
-Hydraulic power . . . . . . . . . . . . HYD
-Fuel. . . . . . . . . . . . . . . . . . FUEL
-APU . . . . . . . . . . . . . . . . . . APU
-Air conditioning. . . . . . . . . . . . COND
-Doors and oxygen. . . . . . . . . . . . DOOR/OXY
-Landing gear, wheels, brakes. . . . . . WHEEL
-Flight controls . . . . . . . . . . . . F/CTL
-Cruise phase parameters . . . . . . . . CRUISE
-Operational status. . . . . . . . . . . STATUS
These data are presented on different system pages which are displayed either:
-manually (manual mode),
- or automatically on system warning,
- or automatically after parameter drift (advisory mode),
- or automatically according to the flight phase.
(For further details, Ref. to 31-67-00).
B. Component Description
(1)
General The EIS display functions are performed by the 3 DMCs and the 6 DUs. The DMCs receive data from different avionics systems in the aircraft, decode them and process them in such a way so that the externally connected full color DUs in the cockpit can use them to generate symbols and pictures on their screens.
(2)
DMC description (Ref. Fig. 009) (For further details, Ref. to 31-63-00). The 3 DMCs are identical and interchangeable. The DMCs are teleloaded to perform the EFIS function or the ECAM function.
(a) Power supply The DMCs are supplied from various buses (115VAC from NORMAL and EMERGENCY A/C network) to ensure that at least one DMC remain available in case of emergency configuration. The DMCs also receive 28VDC for A629 switching purpose.
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DMC - Internal block diagram
Figure 009
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