C. Make sure that this(these) circuit breaker(s) is(are) closed:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01 106VU CSM/G /EV/MAN/SPLY 6XE B04 106VU ESS TR/CNTOR/CTL 5PE C02
R 106VU ESS TR/SPLY 4PE C01
R 122VU ELEC/EMER GEN AUTO/2 9XE Z26 122VU ELEC/EMER GEN AUTO/1 11XE Z25
Subtask 24-30-00-710-050
D. Start one engine (Ref. TASK 71-00-00-710-003).
Subtask 24-30-00-869-052
E. On the Ecam Control Panel (ECP), get the HYD page and make sure on the System Display (SD) that the blue system pressure is 3000 psi.
4. Procedure
_________ Subtask 24-30-00-710-051
A. Do the CSM/G test with one normal TR failed:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the panel 21VU, on the EMER ELEC PWR section:
-lift the safety cover,
-push and hold the EMER GEN TEST pushbutton switch.
2. On the panel 21VU:
-release the EMER GEN TEST
pushbutton switch.
3. On the ECAM control panel:
-get the ELEC page.
4. On the panel 21VU:
-lower the safety cover.
5. Close-up
________
Subtask 24-30-00-710-052On the lower ECAM display unit:
-
the ELEC page comes into viewautomatically,
-
the green lines between the AC1 andthe AC ESS busbars and the DC1 and the DC ESS busbars go out of view,
-
the EMER GEN and ESS TR indications are shown in white. The related parameters are shown in green,
-
the green lines between the EMER GEN indication and the AC ESS busbar, the EMER GEN and the ESS TR indications, the ESS TR indication and the DC ESS busbar come into view,
-
the SHED indication comes into view below the AC ESS and DC ESS busbars.
On the lower ECAM display unit:
-the normal configuration comes into view (the emergency AC generator stops).
A. Stop the engine (Ref. TASK 71-00-00-710-028).
Subtask 24-30-00-860-051
B. Put the aircraft back to its initial configuration.
(1)
If the test duration is more than 30 seconds, on the panel 22VU, the FAULT light of the EXTRACT pushbutton switch comes on. If this occurs, release then push the EXTRACT pushbutton switch (the FAULT light goes off).
(2)
Do the EIS stop procedure
(Ref. TASK 31-60-00-860-002).
(3)
De-energize the aircraft electrical circuits
(Ref. TASK 24-41-00-862-002)
Subtask 24-30-00-410-050
C. Close Access
(1)
Close the access doors 812 and 822.
(2)
Remove the access platform(s).
DC MAIN GENERATION (TR) - DESCRIPTION AND OPERATION
___________________________________________________
1.
General
_______ The DC main generation is provided by the two Transformers Rectifiers 1 and 2 (TR1 and TR2). They are supplied with three phases 115 VAC/400 Hz voltage from the normal Alternating Current (AC) distribution network.
2.
Component Location
__________________
**ON A/C 001-049, 051-062, 101-105, 151-152, 201-205,
(Ref. Fig. 001)
R **ON A/C 063-099, 106-149, 153-199, 206-299, 301-399, 401-499,
(Ref. Fig. 001A)
**ON A/C ALL
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF.
-------------------------------------------------------------------------------1PU1 TR-1 126 822 24-32-51 1PU2 TR-2 126 822 24-32-51 5PU1 CNTOR-TR 1 120VU 212 831 24-32-55 5PU2 CNTOR-TR 2 120VU 212 831 24-32-55 14PU CNTOR-TR 2/AC SVCE BUS NORM SPLY 120VU 212 831 24-32-55 15PU P/BSW-TR RST 103VU 126 822 24-32-00
3. Component Description
_____________________
A. Transformer Rectifier
(1) Operation (Ref. Fig. 002, 003, 004) Each TR controls its contactor via an internal TR logic. This logic, which is intended to protect the Direct Current (DC) network and the TR, controls contactor opening in case of:
-no current flow to the DC BUS (minimum current detection),
-TR overheat (171/Deg.C).
To ensure these protections, each TR sends a fault signal to the
Centralized Fault Display System (CFDS) for maintenace purpose.
DC Main Generation (TR) - Component Location Figure 001 (SHEET 1) 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 ELECTRICAL POWER 电源2(29)
