ELECTRICAL POWER - GENERAL - DESCRIPTION AND OPERATION
______________________________________________________
1. _______
General
(Ref. Fig. 001)
A. Generation
Two Integrated Drive Generators (IDG) normally supply the aircraft
electrical power in flight ; each engine drives one generator.
The APU drives a third, auxiliary, generator (APU GEN) which can replace
either main generator (GEN 1 or GEN 2).
The generators supply the distribution network with alternating current.
Two Transformer Rectifiers (TR) supply, in normal configuration, the
distribution network with direct current. In the event of major failure,
a constant-speed hydraulic motor drives an emergency generator (CSM/G) to
supply the systems required for aircraft control.
On the ground, an electrical Ground Power Unit (GPU) can supply the
aircraft. The APU GEN can also be an independant power source.
B. General Arrangement of the Distribution Network
In normal flight configuration, each IDG supplies its own distribution
network via its Line Contactor (GLC). The two IDGs are never electrically
coupled.
The distribution network 1 consists of:
- the Alternating Current Bus 1 (AC BUS 1),
- the Alternating Current Essential Bus (AC ESS BUS),
- the Alternating Current Sheddable Essential Bus (AC SHED ESS BUS).
The distribution network 2 corresponds to the Alternating Current Bus 2
(AC BUS 2).
The TR 1 powered from the AC BUS 1 supplies through its contactor:
- the Direct Current Bus 1 (DC BUS 1),
- the Direct Current Battery Bus (DC BAT BUS),
- the Direct Current Essential Bus (DC ESS BUS),
- the Direct Current Sheddable Essential Bus (DC SHED ESS BUS).
Two batteries are associated with the DC BAT BUS.
The TR 2 powered from the AC BUS 2 supplies the Direct Current Bus 2 (DC
BUS 2) through its contactor.
In case of loss of the TR 1 or the TR 2, a third Essential Transformer
Rectifier (ESS TR) powered from the AC BUS 1, supplies through its
contactor:
- the DC ESS BUS,
- the DC SHED ESS BUS.
In certain failure configurations, the AC ESS BUS and the AC SHED ESS BUS
plus, via the ESS TR, the DC ESS BUS and the DC SHED ESS BUS can be
supplied by:
- the AC BUS 2 if the AC BUS 1 is lost,
- the CSM/G more especially in emergency configuration or smoke emergency
configuration.
Two sheddable AC and DC busbars are powered respectively by the GLC 2 and
the TR 2 and controlled by two contactors. These AC busbars are
automatically shedded in the single generator configuration and the DC
busbars in the single generator and single TR configurations.
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2. __________________
Component Location
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A. Main Component Location
(Ref. Fig. 002, 003)
------------------------------------------------------------------------------FIN
|
FUNCTIONAL DESIGNATION
| PANEL|ZONE|ACCESS |
ATA
|
|
|
| DOOR |
REF.
------------------------------------------------------------------------------1PE
TR-ESS
125 812
24-34-51
3XB
STAT INV
126 822
24-28-51
1XE
CONTROL UNIT-CSM/G
125 812
24-24-34
8XE
CSM/G
148 734
24-24-51
20XG
RCPT-EXT PWR
120 121AL
24-41-51
24XG
GAPCU
92VU 122
24-41-00
8XS
GEN-APU
310
24-23-51
1XU1
GCU-1
91VU 121 811
24-22-34
1XU2
GCU-2
91VU 121 811
24-22-34
4000XU
IDG
430
24-21-51
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3. __________________
System Description
A. AC Generation and Distribution
(Ref. Fig. 004)
(1) Generation
(a) Main generator and APU GEN drive:
- Each main generator is driven by an engine HP compressor via an
accessory gearbox and an integrated hydromechanical speed
regulator which transforms the engine variable speed into
constant speed for the generator.
In the event of mechanical failure, the IDG pushbutton switch
protected by a guard and located on the ELEC panel on the
overhead panel, serves to disconnect the IDG.
The disconnection mechanism can be reset on the ground only
with the engine shut down.
- The APU directly drives the APU GEN at constant speed. This
maintains the generator frequency constant.
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Electrical Power - General Schematic
Figure 001
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Electrical Power - Component Location
Figure 002
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Control and Indicating - Component Location
Figure 003
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AC Generation and Distribution - Schematic
Figure 004
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(b) Main Generator, APU GEN, Generator Control Unit (GCU) and Ground
and Auxiliary Power Control Unit (GAPCU).
Each generator is controlled, via a GCU and via the GAPCU for the
APU generator, by a GEN pushbutton switch located on the ELEC
panel on the overhead panel.
The leading particulars of the generator are:
- nominal power: 90 KVA at the POR,
- voltage: 115 V/200 V, three-phase, 400 Hz.
The main functions of the GCU and GAPCU are:
- to regulate the generator voltage by the field current,
- to protect the network and the generator by control of the
associated GLC and the generator field current,
- to provide BITE information to the Centralized Fault Display
System (CFDS),
- to control the warnings associated with the corresponding
channel.
Each GCU and the GAPCU include a BITE and self monitoring system
which:
- analyzes most of the faults that affect the channel,
- memorizes the corresponding data in a non-volatile memory.
In addition the lower ECAM display unit receives the electrical
parameters and warnings dealing with the channel concerned.
(c) CSM/G drive
In emergency conditions, a hydraulic motor speed-controlled by a
servo-valve speed regulator drives the CSM/G. The regulator uses
the oil flow from the Blue Hydraulic system to maintain the CSM/G
at a constant speed.
In normal conditions, an electric pump supplies the Blue
hydraulic system. In emergency conditions, the Ram Air Turbine
(RAT) supplies the Blue system.
(d) CSM/G and CSM/G control unit
Loss of the AC BUS 1 and AC BUS 2 automatically controls the RAT
and the CSM/G.
The MAN ON guarded pushbutton switch located on the EMER ELEC PWR
panel on the cockpit overhead panel serves to manually control
the RAT and the CSM/G. This control is redundant with the
automatic RAT deployment.
The CSM/G control unit enables full control of the CSM/G.
The leading particulars of the CSM/G are:
- Nominal Power: 5 KVA at POR
- Voltage: 115/200 VAC, three-phase, 400 Hz.
The main functions of the control unit are:
- to control the servo-valve excitation for speed regulation,
- to regulate the generator voltage by the field current,
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- to protect the network and the generator by control of the
associated GLC and the generator field current.
The EMER GEN TEST guarded pushbutton switch on the EMER ELEC PWR
panel allows to test the CSM/G on the ground, with the Blue
electric pump running.
(e) Static inverter
The static inverter, with a 1000 VA nominal power, transforms the
direct current from the battery 1 into a single phase, 115 V 400
Hz, alternating current.
The static inverter is automatically activated if AC BUS 1 and AC
BUS 2 are lost and the CSM/G is unavailable.
For maintenance purposes, the static inverter delivers FAULT
indication to the Centralized Fault Display System (CFDS) through
the two Battery Charge Limiters (BCL).
(2) Transfer Circuit
The transfer circuit enables supply of either AC electrical network
or both from one of the four power sources (GEN 1, GEN 2, APU GEN,
EXT PWR) via the Bus Transfer Contactors (BTC). BTC control is
entirely automatic and depends on the availability of these sources
and the correct condition of each network. The BTC 1 closes, if no
interlock condition exists on the GCU 1:
- when the GEN 1 is not available, in order to supply the network 1
from another power source (GEN 2 APU GEN or EXT PWR),
- to supply the network 2 from the GEN 1, if the GEN 2, APU GEN and
EXT PWR are not available.
The BTC 2 control is symmetrical to BTC 1.
The GCU 1 or GCU 2 enables closure of the BTC 1 or BTC 2 if no
overcurrent condition and no GLC welded failure occurred (Ref:
24-22-00).
The networks 1 and 2 are supplied in priority order:
- by the corresponding generator,
- by the ground power unit,
- by the APU GEN,
- or by the other generator.
NOTE : Locking of the two BTCs and isolation of the two channels is
____
possible by action on the BUS TIE pushbutton switch; this
control is located on the ELEC panel on the cockpit overhead
panel.
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(3) Distribution
The alternating current distribution network comprises three
independent parts.
The network 1 mainly comprises the AC BUS 1, the AC ESS BUS and the
AC SHED ESS BUS which are three-phase, 115 V/400 Hz busses.
The AC BUS 1 supplies the essential busses in series.
The AC BUS 1 and the AC ESS BUS also deliver 26 V/400 Hz power supply
through their 115/26 V transformer.
In the event of AC BUS 1 loss, AC ESS BUS and the AC SHED ESS BUS can
be manually restored by the transfer of power supply directly from
the AC BUS 2. It is possible to perform the transfer by action on the
AC ESS FEED pushbutton switch on the ELEC panel, after illumination
of the FAULT legend.
In the event of AC BUS 1 and AC BUS 2 loss (emergency configuration),
the AC ESS BUS and AC SHED ESS BUS are restored on the CSM/G when the
RAT hydraulic power is available.
During RAT deployment or when the following two conditions are both
met:
- main landing gear compressed,
- and A/C speed below 100 Knots,
AC ESS BUS and AC STAT INV BUS are supplied by battery 1 via the
static inverter.
The network 2 includes the AC BUS 2 which is a three-phase, 115
VAC/400 Hz bus.
It also delivers 26 VAC/400 Hz power supply through a 115/26 VAC
transformer.
NOTE : To carry out ground service operations (Ref. Para. C.), the
____
external power receptacle provides independent and direct
supply to a part of the network 2.
B. DC Generation and Distribution
(Ref. Fig. 005)
(1) DC Power Sources
The power sources of direct current are:
- three identical transformer rectifiers and two identical batteries.
In normal configuration, the two normal TRs (TR 1 and TR 2) and
possibly the batteries supply direct current.
In the event of loss of one or both TR, part of the DC network is
transferred to the ESS TR.
(a) TR
Each TR transforms the three-phase alternating current into
direct current (28VDC).
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DC Generation and Distribution - Schematic
Figure 005
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1
_
TR1 and TR2
Upon energization, the two normal TRs operate and supply the
DC network via a contactor controlled by the internal TR
logic.
In case of failure, the TR sends a FAULT signal to the CFDS
for maintenance purposes.
2
_
Essential TR
Upon energization, the essential TR operates and supplies the
DC network via a contactor.
To reset the TR push the TR RST pushbutton switch 15PU located
on the relay box 103VU.In addition,the TR sends its electrical
parameters to the lower ECAM display unit.
In addition, the TR sends its electrical parameters to the
lower ECAM display unit.
(b) Batteries
Each of the two batteries has a nominal 23 AH capacity and a 24
VDC voltage. The main functions of the batteries are:
- to start the APU in flight and on the ground,
- to supply the essential network in some configurations.
A BCL controls each battery contactor when the BAT pushbutton
switch is in the AUTO configuration.
In addition, each BCL includes a BITE and a self monitoring
system which analyzes internal and peripherical fault
information. Initiation of the test is possible via the CFDS or
at each power up on ground.
Each BCL delivers electrical parameters and warnings concerning
each battery to the lower ECAM display unit.
(2) Distribution
The direct current distribution network is divided into two parts.
The network 1 comprises the DC BUS 1, the DC BAT BUS, the DC ESS BUS
and the DC SHED ESS BUS. The TR 1 supplies the network 1.
The network 2 comprises the DC BUS 2. The TR 2 supplies the network
2.
In the event of TR 1 loss, the TR 2 automatically restores supply to
the DC BUS 1 and the DC BAT BUS. The DC ESS BUS and the DC SHED ESS
BUS are automatically transferred to the ESS TR.
The AC BUS 1 supplies the ESS TR.
The TR 2 loss leads to the symmetrical recovery of the DC BUS 2 from
the TR 1 and the same transfer for the DC ESS BUS and the DC SHED ESS
BUS.
In the event of TR 1 and TR 2 loss (DC BUS 1 and 2 loss), the DC ESS
BUS and the DC SHED ESS BUS are supplied from the ESS TR.
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In case of loss of AC BUS 1 and AC BUS 2 (emergency configuration),
DC ESS BUS and DC SHED ESS BUS are recovered by the CSM/G (via the
ESS TR) when the RAT hydraulic generation is available.
During RAT deployment or when the following two conditions are both
met:
- main landing gear compressed,
- and A/C speed below 100 Knots,
DC ESS BUS only is supplied by battery 2.
NOTE : The external power receptacle directly energizes the TR 2
____
which can independently supply a part of the DC normal
network. (Ground service configuration).
C. Power Supply Via the External Power Receptacle
(Ref. Fig. 004)
(1) AC External Power Control Supply
An external power receptacle located in front of the nose landing
gear well enables power supply of the aircraft network. This is
performed by means of the three-phase, 400 Hz, 115/200 V ground power
unit.
External power supply is controlled from the ELEC panel on the
cockpit overhead panel and via the GAPCU.
The GAPCU includes a BITE and a self monitoring system which analyzes
most of the faults which may affect the channel. The system memorizes
the corresponding information in a non-volatile memory.
This memory also memorizes the fault information from each main GCU.
Finally, the GAPCU delivers all fault information to the CFDS.
The test is initialized:
- either on the ground by the CFDS,
- or automatically at each power-up.
(2) Ground Service Bus Control
(Ref. Fig. 003)
It is possible to supply a part of the aircraft electrical network as
follows, directly from the external power receptacle, to carry out
ground service operations :
- supply of part of the AC network (AC SVCE busses),
- supply of part of the DC network (DC SVCE busses), without
energization of the whole aircraft electrical network.
The MAINT BUS switch located on the panel 2000VU controls the supply
of the ground service network.
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4. __________________________________________________________________________
Controls and Indications Related to Electrical Generation and Distribution
(Ref. Fig. 003)
Controls and indications related to electrical generation and distribution
are on:
- the ELEC control panels,
- the ECAM display units,
- the forward entryway circuit breaker panel (2000VU),
- the CFDS.
A. MAINT BUS Switch
(Ref. Fig. 003)
This switch is located on the panel 2000VU. It controls power supply of
the AC and DC ground/flight network.
ON: This network is supplied in priority as follows:
- by the aircraft network if it is energized,
- or by the electrical ground power unit, via the external power
receptacle.
OFF: This network is supplied by the main electrical network.
B. Central Warning System
(Ref. Fig. 006)
The block diagram of the electrical generation appears on the lower ECAM
display unit (Ref. 24-27-00).
C. Centralized Fault Display System (CFDS)
Line maintenance of the electronic systems is based on the use of the
CFDS.
The purpose of the CFDS is to give to maintenance technicians a central
maintenance aid. The CFDS enables intervention at system or subsystem
level from the Multipurpose Control and Display Units (MCDUs) located in
the cockpit.
From the MCDUs it is possible:
- to read the maintenance information,
- to initiate various tests.
The electrical components connected to the CFDS are:
- the GAPCU,
- the BCLs,
- the emergency GCU,
- the TRs.
The GAPCU and BCLs can memorize fault codes and communicate with the
CFDIU via ARINC 429 buses.
The emergency GCU and the three TRs are connected to the CFDIU by a
discrete link: it is thus possible to know only the status of these
systems (OK or faulty) during SYSTEM REPORT/TEST sequence.
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Lower ECAM Display Unit - ELEC Page
Figure 006 (SHEET 1)
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Lower ECAM Display Unit - ELEC Page
Figure 006 (SHEET 2)
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ELECTRICAL POWER - GENERAL - ADJUSTMENT/TEST
____________________________________________
TASK 24-00-00-710-003
Integrity Test of the Electrical Power
1. __________________
Reason for the Job
To ensure aircraft safety after maintenance work on the wiring.
2. ______________________
Job Set-up Information
A. Referenced Information
------------------------------------------------------------------------------REFERENCE
DESIGNATION
------------------------------------------------------------------------------24-41-00-861-002
24-41-00-862-002
31-32-00-860-004
31-60-00-860-001
31-60-00-860-002
Energize the Aircraft Electrical Circuits from the
External Power
De-energize the Aircraft Electrical Circuits Supplied
from the External Power
Procedure to Get Access to the SYSTEM
REPORT/TEST/ELEC Page
EIS Start Procedure
EIS Stop Procedure
3. __________
Job Set-up
Subtask 24-00-00-860-056
A. Aircraft Configuration
(1) Energize the aircraft electrical circuits
(Ref. TASK 24-41-00-861-002).
(2) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
(Ref. TASK 31-60-00-860-001).
(3) On the ECAM control panel, push the ELEC key (on the lower ECAM DU,
the ELEC page comes into view).
(4) On the MCDU, get the system REPORT/TEST/ELEC page (Ref. TASK 31-3200-860-004).
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Subtask 24-00-00-865-061
B. Make sure that this(these) circuit breaker(s) is(are) closed:
------------------------------------------------------------------------------PANEL DESIGNATION
IDENT. LOCATION
------------------------------------------------------------------------------49VU SDAC/1 AND 2/28VDC/ESS BUS
12WV
F05
106VU DC BUS/1 AND 2/MONG
68WV
C03
122VU ELEC/GALY & CAB/GND/FLT/LOGIC
7XA
S24
122VU ELEC/BUS/2XP/CTL
17XN2
V27
122VU ELEC/AC/BUS1/CTL
17XN1
V25
122VU ELEC/CNTOR/DC/BUS/TIE1
9PC
W25
122VU ELEC/EXT PWR/LT CLT/NOT IN/USE
6XG
X30
122VU ELEC/TR2/MONG
3PU2
X26
122VU ELEC/TR1/MONG
3PU1
X25
123VU TR1/SPLY
2PU1
AB10
123VU TR2/214XP/SPLY
2PU2
AB04
123VU AC ESS/BUS ON/BUS 1
1XC
AC12
123VU AC ESS/BUS ON/BUS 2
2XC
AC01
124VU TR2/CNTOR/SPLY
4PU2
BC01
125VU TR1/CNTOR/SPLY
4PU1
CF01
4. Procedure
_________
Subtask 24-00-00-710-050
A. Energization of the Aircraft with the Batteries 1 and 2
------------------------------------------------------------------------------ACTION
RESULT
-------------------------------------------------------------------------------
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1. On the ELEC control panel 35VU:
- push the AC ESS FEED, BUS TIE
and GALLEY pushbutton switches
- release the EXT POWER
pushbutton switch
- push the BAT 1 and BAT 2
pushbutton switches.
On the ELEC control panel 35VU:
- the AVAIL legend of the EXT POWER
pushbutton switch comes on
- the battery voltmeters must show a
voltage of 28 volts.
2. On the EMER ELEC PWR section of
the panel 21VU:
- open the guard, push and hold
the EMER GEN TEST pushbutton
switch.
Wait until the PFD and the upper ECAM
DU images come into view.
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------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------3. On the ECAM control panel:
On the upper ECAM DU, on the ELEC page:
- push and hold the ELEC key.
- the STAT INV indications come into
view (115V, 400Hz)
- the BAT indications come into view
(28V, 20A) (values are given for
information).
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4. Release the ELEC key of the ECAM
control panel and the EMER GEN
TEST pushbutton switch of the
EMER ELEC PWR section of the
panel 21VU.
Subtask 24-00-00-710-051
B. Ground Service Configuration
------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------1. On the control panel 2000VU:
- set the MAINT BUS switch to ON
In the right avionics compartment:
- the TR2 operates.
2. On the panel 122VU:
- open then close the circuit
breaker 6XG.
In the right avionics compartment
- the TR2 does not operate.
Subtask 24-00-00-710-052
C. Loss of the Busbars 1XP and 2XP
------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------1. On the ELEC control panel 35VU:
- push the EXT POWER pushbutton
switch.
On the ELEC control panel 35VU:
- the AVAIL legend of the EXT POWER
pushbutton switch goes off.
2. On the panel 122VU:
- open the circuit breaker 17XN1.
On the lower ECAM DU, on the ELEC page:
- the AC1 busbar indication comes on
amber
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------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------- the DC2 busbar energizes the DC BAT
busbar
- the ESS TR busbar energizes the DC
ESS busbar.
On the upper ECAM DU:
- the AC BUS1 FAULT warning comes into
view.
3. On the panel 122VU:
- close the circuit breaker
17XN1.
On the lower ECAM DU, on the ELEC page:
- the AC1 busbar indication becomes
green
- the DC1 busbar energizes the DC BAT
busbar
- the ESS TR busbar energizes the DC
ESS busbar.
On the upper ECAM DU:
- the AC BUS1 FAULT warning goes out of
view.
4. On the panel 123VU:
- open then close the circuit
breaker 1XC.
On the lower ECAM DU, on the ELEC page:
- the DC1 busbar energizes the DC ESS
busbar.
5. On the panel 122VU:
- open the circuit breaker 17XN2.
On the lower ECAM DU, on the ELEC page:
- the AC2 busbar indication comes on
amber.
On the upper ECAM DU:
- the AC BUS2 FAULT warning comes into
view.
6. On the panel 122VU:
- close the circuit breaker
17XN2.
On the lower ECAM DU, on the ELEC page:
- the AC2 busbar indication becomes
green.
On the upper ECAM DU:
- the AC BUS2 FAULT warning goes out of
view.
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Subtask 24-00-00-710-053
D. Transfer Logic of the Busbar 4XP
------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------1. On the panel 123VU:
- open the circuit breaker 1XC.
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On the lower ECAM DU, on the ELEC page:
- the AC ESS busbar indication comes on
amber
- the SHED indication comes into view
under the AC ESS busbar indication.
On the lower ECAM DU:
- the AC ESS BUS FAULT and
AC ESS FEED .... ALTN warnings come
into view.
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On the ELEC control panel 35VU:
- the FAULT legend of the AC ESS FEED
pushbutton switch comes on.
2. On the ELEC control panel 35VU:
- release the AC ESS FEED
pushbutton switch.
On the ELEC control panel 35VU:
- the FAULT legend of the AC ESS FEED
pusbutton switch goes off and the
ALTN legend comes on.
On the lower ECAM DU, on the ELEC page:
- the AC ESS busbar indication becomes
green
- the SHED indication goes out of view.
On the upper ECAM DU:
- the AC ESS BUS FAULT and
AC ESS FEED .... ALTN warnings go out
of view.
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3. On the panel 123VU:
- open the circuit breaker 2XC.
On the ELEC control panel 35VU:
- the FAULT legend of the AC ESS FEED
pushbutton switch comes on and the
ALTN legend stays on.
On the lower ECAM DU, on the ELEC page:
- the AC ESS busbar indication becomes
amber
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------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------- the SHED indication comes into view
under the AC ESS busbar indication.
On the upper ECAM DU:
- the AC ESS BUS FAULT warning comes
into view.
4. On the panel 123VU:
- close the circuit breaker 2XC.
On the ELEC control panel 35VU:
- the FAULT legend of the AC ESS FEED
pushbutton switch goes off and the
ALTN legend stays on.
On the lower ECAM DU, on the ELEC page:
- the AC ESS busbar indication becomes
green
- the SHED indication goes out of view.
On the upper ECAM DU:
- the AC ESS BUS FAULT warning goes out
of view.
5. On the panel 123VU:
- close the circuit breaker 1XC.
No change.
6. On the ELEC control panel 35VU:
- push the AC ESS FEED pushbutton
switch.
On the ELEC control panel 35VU:
- the ALTN legend of the AC ESS FEED
pushbutton switch goes off.
On the lower ECAM DU, on the ELEC page:
- the line between the AC2 and the AC
ESS busbar indications goes out of
view
- the line between the AC1 and the AC
ESS busbar indications comes into
view.
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Subtask 24-00-00-710-054
E. Loss of the Electrical Network with the BUS TIE Pushbutton Switch
------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------1. On the ELEC control panel 35VU:
- release the BUS TIE pushbutton
switch.
On the ELEC control panel 35VU:
- the OFF legend of the BUS TIE
pushbutton switch comes on.
On the lower ECAM DU, on the ELEC page:
- total loss of the electrical network.
2. On the ELEC control panel 35VU:
- push the BUS TIE pushbutton
switch.
On the ELEC control panel 35VU:
- the OFF legend of the BUS TIE
pushbutton switch goes off.
On the lower ECAM DU, on the ELEC page:
- the electrical network is energized
again.
Subtask 24-00-00-710-055
F. Galley Shedding Logic
------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------1. On the panel 122VU:
- open the circuit breaker 7XA.
On the lower ECAM DU, on the ELEC page:
- the GALLEY SHED indication comes into
view.
2. On the panel 122VU:
- close the circuit breaker 7XA.
On the lower ECAM DU, on the ELEC page:
- the GALLEY SHED indication goes out
of view.
3. On the ELEC control panel 35VU:
- release the GALLEY pushbutton
switch.
On the lower ECAM DU, on the ELEC page:
- the GALLEY SHED indication comes into
view.
4. On the ELEC control panel 35VU:
- push the GALLEY pushbutton
switch.
On the lower ECAM DU, on the ELEC page:
- the GALLEY SHED indication goes out
of view.
EFF :
ALL
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Page 507
May 01/03
Subtask 24-00-00-710-056
G. Transfer Logic of the DC Electrical Network
NOTE : This test is for the system 1. For the other system(s), use the
____
indications between parentheses.
------------------------------------------------------------------------------ACTION
RESULT
-------------------------------------------------------------------------------
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1. On the panel 122VU:
- open the circuit breaker 3PU1
(3PU2).
On the lower ECAM DU, on the ELEC page:
- no change.
2. On the panel 125VU (124VU):
- open the circuit breaker 4PU1
(4PU2).
On the lower ECAM DU, on the ELEC page:
- the TR1 (2) stops to energize the DC1
(2) busbar
- the DC1 (2) busbar indication stays
amber for 5 seconds
- the TR1 (2) parameters are 30V, 0A
- the DC2 (1) busbar energizes the DC1
(2) busbar through the DC BAT busbar
- the ESS TR energizes the DC ESS
busbar.
On the upper ECAM DU:
- the TR1 (2) warning comes into view.
3. On the panels 122VU and 125VU
(122VU, 124VU):
- close the circuit breakers 3PU1
(2) and 4PU1 (2).
No change.
4. On the MCDU, on the ELEC page:
- push the line key adjacent to
the TR1 (2) indication.
On the MCDU:
- the TR1 (2) pages comes into view.
- push the line key adjacent to
the RESET indication.
On the MCDU:
- the NO FAULT indication comes into
view.
On the lower ECAM DU, on the ELEC page:
- the TR1 (2) energizes the DC1 (2)
busbar
- the ESS TR continues to energize the
DC ESS busbar.
EFF :
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Page 508
May 01/07
------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------On the upper ECAM DU:
- the TR1 (2) FAULT warning goes out of
view.
5. On the panel 125VU:
- open then close the circuit
breaker 1XC.
On the lower ECAM DU, on the ELEC page:
- the DC1 busbar energizes the DC ESS
busbar.
6. On the panel 123VU:
- open the circuit breaker 2PU1
(2).
On the lower ECAM DU, on the ELEC page:
- the TR1 (2) stops to energize the DC1
(2) busbar
- the DC1 (2) busbar indication stays
amber for 5 seconds
- the TR1 (2) parameters are 0V, 0A
- the DC2 (1) busbar energizes the DC1
(2) busbar through the DC BAT busbar
- the ESS TR energizes the DC ESS
busbar.
On the upper ECAM DU:
- the TR1 (2) FAULT warning comes into
view.
7. On the panel 123VU:
- close the circuit breaker 2PU1
(2).
On the lower ECAM DU, on the ELEC page:
- the TR1 (2) parameters are 30V, 0A.
8. On the MCDU, on the ELEC page:
- push the line key adjacent to
the TR1 (2) indication.
On the MCDU:
- the TR1 (2) page comes into view.
- push the line key adjacent to
the RESET indication.
On the MCDU:
- the NO FAULT indication comes into
view.
On the SD, on the ELEC page:
- the TR1 (2) energizes the DC1 (2)
busbar
- the ESS TR continues to energize the
DC ESS busbar.
On the upper ECAM DU:
- the TR1 (2) FAULT warning goes out of
view.
EFF :
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Page 509
May 01/03
------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------9. On the panel 125VU:
On the lower ECAM DU, on the ELEC page:
- open then close the circuit
- the DC1 busbar energizes the DC ESS
breaker 1XC.
busbar.
10. On the panel 122VU:
- open the circuit breaker 9PC.
On the lower ECAM DU, on the ELEC page:
- the DC2 busbar energizes the DC BAT
busbar (the DC1 busbar stops to
energize the DC BAT busbar)
- the ESS TR energizes the DC ESS
busbar.
11. On the control panel 122VU:
- close the circuit breaker 9PC.
On the lower ECAM DU, on the ELEC page:
- the DC1 busbar energizes the DC BAT
busbar
- the ESS TR energizes the DC ESS
busbar.
12. On the panel 125VU:
- open then close the circuit
breaker 1XC.
On the lower ECAM DU, on the ELEC page:
- the DC1 busbar energizes the DC ESS
busbar.
Subtask 24-00-00-710-057
H. Test of the DC EMER CONFIG Warning
------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------1. On the panels 106VU and 49VU:
- open the circuit breakers 68WV
and 12WV.
On the lower ECAM DU, on the ELEC page:
- the DC ESS busbar indication comes on
amber.
On the upper ECAM DU:
- the DC EMER CONFIG and EMER ELEC PWR
... MAN ON warnings come into view.
2. On the panels 106VU and 49VU:
- close the circuit breakers 68WV
and 12WV.
On the lower ECAM DU, on the ELEC page:
- the DC ESS busbar indication becomes
green.
On the upper ECAM DU:
- the DC EMER CONFIG and EMER ELEC PWR
... MAN ON warnings go out of view.
EFF :
ALL
24-00-00
AFL
Page 510
May 01/03
Subtask 24-00-00-710-058
J. Emergency Logic with the Batteries
------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------1. Make sure that the voltage of the
batteries 1 and 2 is more than
25.5V.
2. On the ELEC control panel 35VU:
- release then push the BAT1
pusbutton switch.
On the lower ECAM DU, on the ELEC page:
- the green line between the DC BAT
busbar and the BAT1 indications come
into view
- the load current is < 150A then
decreases
- the green line goes out of view when
the load current is < 4A.
3. On the ELEC control panel 35VU:
- release then push the BAT2
pushbutton switch.
On the lower ECAM DU, on the ELEC page:
- the green line between the DC BAT
busbar and the BAT2 indications comes
into view
- the load current is < 150A then
decreases
- the green line goes out of view when
the load current is < 4A.
4. On the ELEC control panel 35VU:
- release the BAT1 and BAT2
pusbutton switches.
On the ELEC control panel 35VU:
- the OFF legend of the BAT1 and BAT2
pushbutton switches comes on.
On the EMER ELEC PWR control
panel 21VU:
- push and hold the EMER GEN TEST
pushbutton switch.
On the ELEC control panel 35VU:
- release the BUS TIE pushbutton
switch.
On the lower ECAM DU:
- get the ELEC page and make sure
that it stays in view.
Total loss of the normal electrical
network.
On the lower ECAM DU:
EFF :
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Page 511
May 01/03
------------------------------------------------------------------------------ACTION
RESULT
------------------------------------------------------------------------------- the AC ESS and the DC ESS busbar
indications come on green
- the SHED indication comes into view
under the AC ESS and the DC ESS
busbar indications
- the STAT INV indication is shown
white
- the STAT INV parameters (115V, 400Hz)
are shown green.
5. On the ELEC control panel 35VU:
- push the BUS TIE pushbutton
switch
- push the BAT1 and BAT2
pushbutton switches.
On the EMER ELEC PWR control
panel 21VU:
- release the EMER GEN TEST
pushbutton switch.
The normal electrical network is
energized again.
On the ELEC control panel 35VU:
- the OFF legend of the BAT1 and BAT2
pushbutton switches goes off.
6. On the MCDU:
- push the line key adjacent to
the RETURN indication until the
CFDS menu page comes into view.
5. Close-up
________
Subtask 24-00-00-860-057
A. Put the Aircraft back to its initial Configuration
(1) Do the EIS stop procedure
(Ref. TASK 31-60-00-860-002).
(2) De-energize the aircraft electrical circuits
(Ref. TASK 24-41-00-862-002).
EFF :
ALL
24-00-00
AFL
Page 512
May 01/03
ELECTRICAL POWER - GENERAL - INSPECTION/CHECK
_____________________________________________
TASK 24-00-00-200-003
General - Inspection/Check of the Electrical Circuits and Equipment
WARNING : MAKE SURE THAT NO AC OR DC POWER IS CONNECTED TO THE AIRCRAFT
_______
ELECTRICAL CIRCUITS.
THERE IS A RISK OF ELECTROCUTION IF THE AC OR DC POWER STAYS
CONNECTED.
1. __________________
Reason for the Job
The inspection/check procedure of electrical circuit includes two different
operations:
- A fast inspection, which includes a visual examination of all visible
components without component removal.
- A detailed inspection during which components are removed. Thus you can
see the other components which are behind and do a detailed visual
inspection of all components of the system.
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2. ______________________
Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
------------------------------------------------------------------------------REFERENCE
QTY DESIGNATION
------------------------------------------------------------------------------No specific
No specific
No specific
access doors
warning notice
access platforms 1.8 m (5 ft. 11 in.)
B. Referenced Information
------------------------------------------------------------------------------REFERENCE
DESIGNATION
------------------------------------------------------------------------------71-13-00-010-040
71-13-00-410-040
Opening of the Fan Cowl Doors
Closing of the Fan Cowl Doors
EFF :
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Page 601
May 01/08
3. __________
Job Set-up
Subtask 24-00-00-860-055
A. Aircraft Maintenance Configuration
(1) In the cockpit, put a warning notice in position to tell persons not
to operate the pushbutton switches on the panels 35VU, 211VU and
115VU.
(2) Put a warning notice on the door 121AL to tell persons not to connect
the external power receptacle.
Subtask 24-00-00-941-057
B. Get access to the Avionics Compartment
(1) Put the access platforms at the doors 811, 812 and 822 of the
electronics compartment and at the door 121AL which gives access to
the external power receptacle.
Subtask 24-00-00-010-051
C. Get Access
(1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040):
- FOR 1000EM1
437AL, 438AR
- FOR 1000EM2
447AL, 448AR
4. Procedure
_________
Subtask 24-00-00-210-065
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A. Fast Inspection
(1) Do a check of the general outer condition and attachment of these
components:
- Panels and their equipment
- Electrical connectors
- Rack-mounted system components
- Indicators
- Electrical bonding leads.
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EFF :
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Page 602
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(2) Check the condition of all wiring (for signs of ageing, alteration,
overheating, scaling and deformation which can cause a decrease of
wiring performance).
(3) Replace defective components.
Subtask 24-00-00-210-066
B. Detailed Inspection
(1) Open access doors and casings, remove or open panels and shields and,
if necessary, remove components which are in front of other
components, to gain access to wiring, plugs, electrical connections
and the different system components.
(2) Components
(a) Remove dust with a vacuum cleaner and clean other dirt if
necessary.
(b) Do a check of labels and their identification.
(c) Do a check of attachment and general condition of components.
(3) Wiring
(a) Do a check of identification sleeves or labels protective
coatings, insulation and protective fittings for correct
condition.
(b) Do a check of the condition of wiring (for signs of ageing,
alteration, overheating, scaling and deformation which can cause
a decrease of wiring performance).
(4) Electrical connectors
(a) Disconnect plugs, do a check of their physical and electrical
condition. Make sure that there are no signs of oxydation or
corrosion, replace defective components (seals, gaskets,
grommets, ferrules etc...).
(b) Do a check of the tightness of connections to all electrical
accessories, ground bonding leads, ground leads, busbars and
terminal bars.
(c) Do a check of tightness of non-safetied connectors.
EFF :
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Page 603
May 01/03
(d) Do a check of the condition of electrical connector protections
in the hydraulics compartment.
Subtask 24-00-00-020-053
C. Replacement of the Defective Components
(1) Replace defective components.
Subtask 24-00-00-420-053
D. Installation of the Removed Components
(1) Install removed components and put back all equipment in operating
condition.
5. Close-up
________
Subtask 24-00-00-410-057
A. Close the access doors 811, 812, 822, 121AL.
Subtask 24-00-00-410-058
B. Close Access
(1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040):
- FOR 1000EM1
437AL, 438AR
- FOR 1000EM2
447AL, 448AR
Subtask 24-00-00-942-054
C. Put the aircraft back to its initial configuration.
(1) Remove the warning notice(s).
(2) Remove the access platform(s).
EFF :
ALL
24-00-00
AFL
Page 604
May 01/03
TASK 24-00-00-200-004
Opening and Closing of all Circuit Breakers with Electrical Circuits
De-Energized
1. __________________
Reason for the Job
Refer to the MPD TASK: 240000-17
This task gives the procedure to do an opening and closing cycle of the
circuit breakers to:
- Have a better reliability
- Decrease the number of maintenance problems
- Decrease the effects of circuit breaker aging.
2. ______________________
Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
------------------------------------------------------------------------------REFERENCE
QTY DESIGNATION
------------------------------------------------------------------------------No specific
warning notice
B. Referenced Information
------------------------------------------------------------------------------REFERENCE
DESIGNATION
------------------------------------------------------------------------------24-41-00-862-002
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31-21-00-750-002
De-energize the Aircraft Electrical Circuits Supplied
from the External Power
Procedure to set the Clock
3. __________
Job Set-up
Subtask 24-00-00-860-058
A. Aircraft Maintenance Configuration
(1) In the cockpit, put a warning notice in position to tell persons not
to operate the pushbutton switches on the panels 35VU, 211VU and
115VU.
(2) Put a warning notice in position on the door 121AL to tell persons
not to connect the external power receptacle.
EFF :
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Page 605
May 01/08
(3) Make sure the aircraft electrical circuits are de-energized
(Ref. TASK 24-41-00-862-002).
4. Procedure
_________
Subtask 24-00-00-210-067
A. Opening and Closing of Circuit Breakers
NOTE : Open and close the circuit breakers with the aircraft electrical
____
circuit de-energized.
(1) Open and close each circuit breaker on these panels:
(a) In the cockpit:
- 49VU
- 121VU
- 122VU
- 123VU
- 124VU
- 125VU.
(b) In the avionics compartment:
- 105VU
- 106VU.
(c) In the cabin:
- 2000VU
- 2001VU.
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5. Close-up
________
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Subtask 24-00-00-750-050
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A. Adjustment of the Clock
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(1) Adjust the clock, if necessary (Ref. TASK 31-21-00-750-002).
Subtask 24-00-00-942-055
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B. Put the aircraft back to its initial configuration.
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(1) Make sure that the work area is clean and clear of tool(s) and other
items.
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(2) Remove the warning notice(s).
EFF :
ALL
24-00-00
AFL
Page 606
May 01/08