Main Electrical Power Supply of FWS Components Figure 030
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-FWC1
-ECAM control panel
-SDAC1
NOTE : In emergency configuration, the ADIRU3 is also supplied from the AC
____ ESS bus as soon as the ATT/HDG or the AIR DATA selector switch is set to CAPT/3.
NOTE : The recovery time after the occurrence of a real emergency
____ configuration (for instance due to both engine shutdown) is short since the static inverter takes over the supply of the AC ESS bus bar within less than 1 sec. until the RAT driven generator is able to ensure the supply of this bar in its turn.
NOTE : If cooling air is lost, the grey background areas disappear from the
____ PFDs and the WX image from the NDs. If the DU internal temperature exceeds a given threshold, the DU is automatically cut off. This applies to any DU, EFIS or ECAM.
6. Bite Description
________________
A. General This paragraph describes the Built-In Test Equipment (BITE) system of the Flight Warning System (FWS). The FWS is a type 1 system, i.e. data interchanges between the FWS and the Centralized Fault Display System (CFDS) for maintenance purposes are performed by means of ARINC 429 High Speed (HS) buses. The BITE essentially detects internal and external FWS faults, stores them in memories under certain conditions and reports them to the maintenance system.
B. Operation/ Control and Indicating The interrogation of the FWS is achieved through the interactive function by means of the Multipurpose Control and Display Unit (MCDU). This function is described below. Selection of the ECAM main menu enables access to the following functions:
-LAST LEG REPORT
-PREVIOUS LEGS REPORT
-LRU IDENTIFICATION
-GROUND SCANNING
-CLASS 3 FAULTS
-SYSTEM CONFIGURATION
(Ref. Fig. 031)
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ECAM-1 Page Figure 031
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(1) LAST LEG REPORT (Ref. Fig. 032) The purpose of this item is to present the list of class 1 and 2 internal and external faults detected by the FWS during the last flight. These faults are presented with the failed LRU, the associated source of detection (SDACs, FWCs, ECAM control panel) and the ATA reference.
NOTE : If several faults are detected, the total number of faults is
____
mentioned.
(2)
PREVIOUS LEGS REPORT (Ref. Fig. 033) The purpose of this item is to present the list of class 1 and 2 internal and external faults detected by the FWS during the last 63 flights (except the last flight). The list contains the leg number to identify the concerned flight, the date and the time of the fault detection, the ATA reference and the fault message.
(3)
LRU IDENTIFICATION (Ref. Fig. 034) The purpose of this item is to present the Part Number (P/N) of the FWS components (FWCs, SDACs, ECAM control panel).
NOTE : For A/C equipped with the OEB DATABASE (OEB reminder) option:
____ in addition to the P/N identification, the OEB data base version and the associated checksum are given for each FWC.
(4)
GROUND SCANNING (Ref. Fig. 035) The purpose of this item is to present the internal and external faults that are applicable when the request is made and on the ground only. The date and the time of the scanning are mentioned. They are followed by the test of failures and the associated ATA reference.
(5)
CLASS 3 FAULTS (Ref. Fig. 036) The purpose of this item is to present only the class 3 internal and external faults which are detected by the FWS (SDACs, FWCs, ECAM control panel) during the last flight. For each fault, the text of the fault, the date and the ATA reference are given.
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ECAM-1/LAST LEG REPORT Figure 032
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ECAM-1/PREVIOUS LEGS REPORT Figure 033
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ECAM-1/LRU IDENTIFICATION Figure 034 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320飞机维护手册 AMM 指示/记录系统 5(151)
