R **ON A/C 401-499,
R R R R R R R C. Automatic Periodic Test As soon as the GAPCU is supplied (Aircraft on ground and engines shut down) it will automatically perform the test (GAPCU and GCUs) and will store the failure (if any). Moreover, the GAPCU will activate the BITE Message discrete. This information is provided to the SDACs to be written on the ECAM status page.
R **ON A/C 001-049, 051-060, 101-101, 401-499,
6. BITE Test_________
R **ON A/C 001-049, 051-060, 101-101,
A. Description
The GPCU is a type 1 system. The GPCU performs the following functions: - communication with the CFDS, - communication with up to three generator control units, - detection of any failure affecting the external power channel, - identification of the Line Replaceable Unit (LRU) responsible for the external power channel failure, - memorization of the information pertaining to the failure in a Non Volatile Memory (NVM).
B. Conditions of Power-up Test Initialisation
(1) How long must the computer be de-energized: - no time requirement.
(2) A/C configuration: - A/C on ground, engines stopped, APU stopped and ground power unit connected to the A/C.
C. Progress of Power-up Test
(1) Duration: - 35 ms.
(2) Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded): - none.
D. Results of power-up Test
(1) Test passed: - ELEC panel: . green AVAIL legend of EXT PWR pushbutton switch on.
(2) Test failed: - ELEC panel: . AVAIL legend of EXT PWR pushbutton switch not illuminated.
NOTE : The GPCU is energized as soon as the Ground Power Unit (GPU)____ is connected to the A/C or the batteries are in AUTO position without any other alternative AC power.
NOTE : In case of GPU voltage and frequency malfunction the AVAIL____ legend of the EXT PWR pushbutton switch is also not illuminated. Consequently, before removing the GPCU, check if the GPU is not operating.
R **ON A/C 401-499,
R R R R R R R R R R R R A. Description The GAPCU is a type 1 system. The GAPCU performs the following functions: - communication with the CFDS, - communication with up to the four generator control units, - detection of any failure affecting the external power channel and/or the APU Ancillary generator, - identification of the Line Replaceable Unit (LRU) responsible for the external power channel failure, - memorization of the information pertaining to the failure in a Non Volatile Memory (NVM).
R B. Not Applicable
R C. Not Applicable
R D. Not Applicable
R (3) Communication with the CFDIU
R
R (Ref. Fig. 008)
R The GAPCU is connected to the CFDIU via separate ARINC 429 links.
R The GAPCU transmits data to and receives data from the CFDIU
R The GAPCU communicates with the CFDIU in either of the two modes:
R normal or interactive mode.
R (a) Normal mode
R
R The normal mode starts after the GAPCU has completed all its
R power up and initialization routines. This normal mode runs
R continuously, unless one of the following conditions occurs:
R - initiation of interactive mode,
R - GAPCU failure (BITE bypass),
R - loss of GAPCU power.
R
R During the normal mode operation, the GAPCU provides the
R following communications with the CFDIU
R - reception of BITE commands and parametric data,
R - transmission of the equipment identification data,
R - transmission of system fault data.
R
R For each fault, the GAPCU transmits a message in English language
R to the CFDS. The message is encoded in ISO5 alphabet.
R The dialogue principle is the same as for all the other type 1
R systems in communication with the CFDIU.
R Refer to chapter 31-32-00 for more detailed data.
R EPGS main menu on MCDU
R Figure 007A
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R BITE Communication - Block Diagram
R Figure 008
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R (b) Interactive mode 中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320飛機維護(hù)手冊 AMM ELECTRICAL POWER 電源2(74)
