2400G01T00 AV - Electrical Power Generation System

2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
C-27J
ELECTRICAL POWER
GENERATION SYSTEM
Sep 2010 – Rev 0
© 2011 Alenia
This document contains Proprietary Information of Alenia Aeronautica. Disclosure to
others, use or copying without express written authorization of Alenia Aeronautica is
strictly prohibited
Electrical Power Generation System
PERFORMANCE: Describe the Electrical Power Generation System
ENABLING OBJECTIVE:
Describe hazards, safety requirements and sys features
Describe AC/DC system components and architecture
Describe AC/DC distribution and components location.
Describe and locate the systems controls and indicators.
State the systems ACAWS messages and describe the associated crew response actions.
Describe the principles of operation of the systems
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Hazards
High Voltage (115/200 V AC 400 Hz)
Battery Corrosive Fluid
Use and/or disclosure is governed by the Statement on the title page of this document
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Safety Precautions



Prepare Aircraft to be safe prior to apply electrical power
Connect static ground wire of external supply cart
Caution of high voltage when the system is supplied
Use and/or disclosure is governed by the Statement on the title page of this document
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Safety Precautions

Switch-off electrical power before
removing connectors and components

Avoid skin/eyes contact with
battery fluid
Use and/or disclosure is governed by the Statement on the title page of this document
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Primary Generators
AC GENERATOR 2 (RH)
AC GENERATOR 1 (LH)
Use and/or disclosure is governed by the Statement on the title page of this document
The Primary Generators and the APU Generator are identical. Each generator, brushless
type, is rated to deliver continuous 60 KVA at its POR over a load Power Factor (PF) range
from 0.75 lagging to unity, with any input speed between 11,790 to 12,210 rpm corresponding
to a frequency range of 393 to 407 Hz.
Each generator can be overloaded at 75 KVA for 5 minutes rating.
Each generator is an oil cooled machine which shares oil with the engine gearbox. The
generator oil cooling circuitry includes an integral oil scavenging system.
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APU Electrical Generator Location
APU GENERATOR
APU BAY
Use and/or disclosure is governed by the Statement on the title page of this document
APU generator, having identical characteristics of the main generator, is directly driven by the
APU machine.
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Electrical System Features

Electrical power generation and distribution





115/200 V AC 3-phase 400 Hz
26 V AC 400 Hz
28 V DC (provided by Transformer Rectifier
Units)
8 V DC (control panels power and lighting)
Provision of emergency power by batteries

24 V 40 Ah nickel cadmium
Use and/or disclosure is governed by the Statement on the title page of this document
The electrical generation system of the aircraft supplies two different types of electrical power:
AC power supply and DC power supply.
The 115/200 VAC power supply is obtained from two 3-phase generators driven at constant
speed by the propeller accessory gear box (GMAD - Gearbox Mounted Accessory Drive) and
one more 3-phase generator driven at constant speed by the Auxiliary Power Unit.
Each generator has a capacity of 50/60 KVA at a frequency of 400Hz
The DC electrical power generation is normally provided by two 28 V dc Transformer
Rectifier Units (TRU 1 and TRU 2) which supply the DC main
buses (DC BUS 1 and DC BUS 2). A third TRU (STBY TRU) is used as an alternative source
in the event of failure of one primary TRU.
In addition, two 40 Ah batteries are provided: the emergency battery (EMER BAT) and the
APU start battery (APU START BAT).
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AC Power Generation Components
AUTO
TRANSFORMER
115V AC BUS1
AUTO
TRANSFORMER
26V AC BUS 2
26V AC BUS 1
AC BUS TIE
1
CONTACTOR
AC BUS TIE
2
CONTACTOR
115V AC BUS2
BUS POWER
CONTROL UNIT
APU GENERATOR
CONTROL UNIT
GENERATOR
CONTROL UNIT
GENERATOR
CONTACTOR
AC GEN 1
(LH ENGINE)
AC EXT PWR
CONTACTOR
GENERATOR
CONTROL UNIT
GENERATOR
CONTACTOR
GENERATOR
CONTACTOR
APU GEN
AC GEN 2
(RH ENGINE)
AC EXT WR
Use and/or disclosure is governed by the Statement on the title page of this document
The AC generation primary is provided with two AC Bus Generator Contactors that connect
the AC BUSSES N° 1 & 2.
The 26 VAC is provided by two AUTOTRANSFORMERS connected to AC BUS1 & 2.
The MAIN Autotransformer characteristics are:
Nominal continuous power
100VA
Frequency
400  20Hz
Input Voltage
115VAC  10%
Output Voltage under max continuous power with PF 1
26VAC  2%
The autotransformers are cooled by natural convention.
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DC Power Generation Components
Emergency
Battery
HOT APU
BAT BUS
HOT EMER
BAT BUS
DC EMERGENCY
BUS
POWER DISTRIBUTION
UNIT
(PDU)
28 V DC BUS 1
TRANSFORMER
RECTIFIER UNIT 1
(TRU 1)
APU
Battery
DC ESSENTIAL
BUS
28 V DC BUS 2
TRANSFORMER
RECTIFIER UNIT 2
(TRU 2)
STANDBY
TRU
DC EXT PWR
AC STANDBY TRU
CONTACTOR 1
AC STANDBY TRU
CONTACTOR 2
115V AC BUS
1
115V AC BUS 2
Use and/or disclosure is governed by the Statement on the title page of this document
The DC is generated by 2 TRUs (Transformer Rectifier Unit) connected to 115 VAC BUS 1
and 2 and by a Stand-By TRU that can be connected either to 115 VAC BUS 1 (through AC
STANDBY TRU CONTACTOR 1) or to 115 VAC BUS 2 (through AC STANDBY TRU
CONTACTOR 2). The DC power generated from each TRU is provided to a PDU that provide
for distribution to the DC busses.
In addition, two 40 Ah batteries are provided: emergency battery (EMER BAT) and APU start
battery (APU START BAT). The first one is used as back-up power for the ESSEN BUS, the
other is mainly used to start-up the APU.
The DC network is controlled and supplied by the PDU which receives also DC from DC
EXTERNAL POWER.
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GCUs and BPCU Location
FLIGHT
BPCU
GCU 2
FLIGHT
COCKPIT
TOP VIEW
GCU 1
Use and/or disclosure is governed by the Statement on the title page of this document
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TRU Location
FLIGHT
FLIGHT
COCKPIT
TOP VIEW
GCU
APU
TRU 2
TRU 1
Use and/or disclosure is governed by the Statement on the title page of this document
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Battery Compartment
EMERGENCY BATTERY
APU BATTERY
CARGO
FLOOR
Use and/or disclosure is governed by the Statement on the title page of this document
A battery compartment is located, underfloor, in the forward cargo bay. Two nickel cadmium
batteries (35,2 kg each one) are located in a bay between the frames 7 - 9. One battery is used
to provide electrical power to emergency loads in case of Transformer Rectifier Unit's failure
and the other one is shared between the Auxiliary Power Unit starting and emergency power
supply systems. The batteries installation is designed to permit an easy replacement opening the
bay door, hinged on the cargo floor, and using the related handle. The installation is designed
so that no corrosive fluid, coming from battery in case of overtemperature or overpressure
condition, may damage surrounding aircraft structure or adjacent essential equipment.
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Electrical Control Panel Location
AC SOURCE MONITORING
OVERHEAD PANEL
Use and/or disclosure is governed by the Statement on the title page of this document
The electrical System Control Panel (202VE) located on the overhead panel, provides for
control and monitoring of the AC and DC electrical power system.
The AC phase rotary switch labeled PHASE, is connected in series to the source rotary switch
and enables the phase A-B or C to be tested and displayed.
The AC source rotary switch labeled AC SOURCE is a rotary switch with five positions which
have the function to display the % load and frequency of all AC sources.
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Electrical Control Panel Location
DC SOURCE
MONITORING
OVERHEAD
PANEL
Use and/or disclosure is governed by the Statement on the title page of this document
The DC source rotary switch labeled DC SOURCE is a rotary switch with seven positions
which have the function to display the voltage and current of all DC sources.
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Electrical Control Panel Location
ELECTRICAL
DISTRIBUTION
CONTROL AND
MONITORING
OVERHEAD
PANEL
Use and/or disclosure is governed by the Statement on the title page of this document
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Generator Pushbutton-Indicators
FAULT
FAULT
FAULT
OFF
OFF
OFF
Use and/or disclosure is governed by the Statement on the title page of this document
Three generator pushbutton-indicators labelled GEN 1, GEN 2 and APU provide manual
control of generator 1, generator 2 and APU generator. They also provide a status indication of
the generators.
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Generator Pushbutton-Indicators
FAULT
OFF
THE ASSOCIATED GENERATOR IS
DISCONNECTED FROM THE AC BUS
RELEASED
FAULT
OFF
ASSOCIATED GENERATOR
IS CONNECTED TO THE AC BUS
AND UNDER GCU CONTROL
PUSHED-IN
(NORMAL CONDITION)
GEN 1 FAULT
FAULT
GEN 2 FAULT
OFF
APU GEN FAULT
IF FAILURE IS
DETECTED
ACAWS
THE ASSOCIATED GENERATOR
IS AUTOMATICALLY DISCONNECTED
FROM THE AC BUS.
THE FAULT LEGEND ILLUMINATION
CONFIRM THE DISCONNECTION
Use and/or disclosure is governed by the Statement on the title page of this document
The pushbutton-indicator has two captions named FAULT and OFF.
In normal operation with the pushbutton pressed and the captions unlit, the associated
generator is under automatic control of the associated GCU. As generator output power reaches
its normal value, the associated generator contactor is automatically closed by the GCU.
The yellow FAULT caption illuminates when the relevant GCU detects a failure condition of
the associated generator.
This failure condition is also monitored by a dedicated ACAWS caution message GEN 1
FAULT, GEN 2 FAULT and APU GEN FAULT.
When released, the yellow OFF caption illuminates and the associated generator is
disconnected from AC BUS.
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External AC Power
Pushbutton-Indicator
AVAIL
ON
AVAIL
PUSHBUTTON RELEASED
AND EXT PWR NOT CONNECTED
PUSHBUTTON RELEASED
AND EXT PWR CONNECTED
ON
NO FAILURE CONDITION
OF EXTERNAL AC POWER
AVAIL
ON
PUSHBUTTON PUSHED-IN
AND EXT PWR CONNECTED
BPCU IS READY TO
CLOSE THE AC EPC
AND BOTH AC BTC
Use and/or disclosure is governed by the Statement on the title page of this document
This pushbutton is labeled AC EXT and is located on the electrical control panel. The
pushbutton-indicator has two captions named AVAIL and ON. The green AVAIL caption
illuminates when no failure conditions of external AC power quality are detected by BPCU.
The green ON caption illuminates when the pushbutton is pressed, therefore the BPCU is ready
to close the AC EPC and both AC BTCs.
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AC Bus 1 Tie & AC Bus 2 Tie
Pushbutton-Indicators
OFF
OFF
Use and/or disclosure is governed by the Statement on the title page of this document
Two AC Bus Tie pushbutton-indicators labelled TIE provide manual control of the AC Bus Tie
Contactors (BTCs).
The pushbutton-indicator is identified by a flow bar at the upper half side and a caption OFF at
the lower half side. When the pushbuttons are pressed (normal condition), the bus-tie system is
in stand-by operation and the BPCU provides the automatic control of the AC BTCs.
When released, the yellow OFF caption illuminates and the AC BTC is manually opened.
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AC Bus 1 Tie & AC Bus 2 Tie
Pushbutton-Indicators
AC BTC IS MANUALLY OPEN
OFF
RELEASED
BUS-TIE SYSTEM IS IN
STANDBY OPERATION AND THE
BPCU PROVIDES AUTOMATIC
CONTROL OF THE BTC
OFF
PUSHED-IN
(NORMAL CONDITION)
IN CASE OF ANY AC BUS FAILURE
THE BPCU CLOSES THE BTC
OFF
THE OPERATION IS ANNOUNCED
BY THE GREEN BAR ILLUMINATED
PUSHED-IN
(NORMAL CONDITION)
Use and/or disclosure is governed by the Statement on the title page of this document
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AC Bus 1 & Bus 2 Indicators
BUS
OFF
BUS
OFF
WHEN THE ASSOCIATED AC BUS
IS NOT SUPPLIED
AC BUS 1 OFF
BUS
OFF
AC BUS 2 OFF
ACAWS
Use and/or disclosure is governed by the Statement on the title page of this document
Two yellow indicators (labeled BUS OFF), come on when the associated AC BUS is not
supplied. This condition is controlled by the AC BUS 1 OFF and AC BUS 2 OFF relays. These
are supplied respectively by AC BUS 1 through AC BUS 1 OFF circuit breaker and AC BUS 2
through AC BUS 2 OFF circuit breaker.
This failure is monitored by a dedicated ACAWS caution message AC BUS 1 OFF and AC
BUS 2 OFF.
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TRU Pushbutton-Indicators
FAULT
OFF
PDU OPENS THE ASSOCIATED
TRU CONTACTOR
DISCONNECTING THE TRU
FROM DC BUS
RELEASED
FAULT
OFF
TRU IS UNDER AUTOMATIC
CONTROL OF THE PDU
PUSHED-IN
(NORMAL CONDITION)
FAILURE DETECTED
FAULT
TRU 1 FAULT
OFF
FAULT
FAULT
TRU 2 FAULT
OFF
OFF
ACAWS
Use and/or disclosure is governed by the Statement on the title page of this document
Two TRU pushbutton-indicators labeled TRU 1 and TRU 2 provide manual control of the
TRUs. They also provide a status indication of the TRUs.
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Standby TRU Pushbutton-Indicator
FAILURE DETECTED
FAULT
ON
STANDBY TRU IS READY TO
REPLACETRU
THE IS
FAILED
TRU
STANDBY
DISABLED
IN CASE OF LOSS OF BOTH TRUs
PUSHED-IN
RELEASED
(NORMAL CONDITION)
STBY TRU FAULT
ACAWS
IF THE STAND-BY TRU SELECTOR
IS POSITIONED ON LH OR RH POSITION
AND TRU 1 OR TRU 2
PUSHBUTTON IS SELECTED TO OFF
Use and/or disclosure is governed by the Statement on the title page of this document
The yellow ON caption illuminates when the pushbutton is pressed, therefore the standby TRU
is ready to replace the failed TRU or supply both DC buses in case of loss of both TRUs if the
standby TRU selector is positioned on LH or RH position and TRU 1 and/or TRU 2 pushbutton
is selected OFF.
The yellow FAULT caption illuminates when the standby TRU has failed. This failure is
monitored by a dedicated ACAWS caution message STBY TRU FAULT.
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Standby TRU Source Rotary Selector
CONNECTS AC BUS 21 TO THE STANDBY
TRU AND ALLOWS
THE
STANBY TRU TO
STANDBY
TRU
REPLACE
THE FAILED TRU 21
NOT OPERATIVE
TRU 1
2 PUSHBUTTON SELECTED OFF
AND
STBY TRU PUSHBUTTON SELECTED ON
Use and/or disclosure is governed by the Statement on the title page of this document
The function of this rotary selector is to enable the pilots to select the AC power source to be
used by standby TRU.
This selector has three positions: OFF, LH and RH which have the following functions:
- OFF: normal position with standby TRU not operative,
- LH: connects the AC BUS 1 to the standby TRU and it allows the standby TRU to replace
the failed TRU 1 if the TRU 1 pushbutton is selected OFF and STBY TRU pushbutton is
pressed (ON light lit).
- RH: connects the AC BUS 2 to the standby TRU and it allows the standby TRU to replace
the failed TRU 2 if the TRU 2 pushbutton is selected OFF and STBY TRU pushbutton is
pressed (ON light lit).
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DC Bus Tie Pushbutton-Indicator
OFF
DC BTC IS
MANUALLY OPENED
RELEASED
PDU PROVIDES AUTOMATIC
CONTROL OF THE DC BTC
OFF
PUSHED-IN
(NORMAL CONDITION)
OFF
BUS TIE CLOSED
OFF
BUS TIE OPEN
Use and/or disclosure is governed by the Statement on the title page of this document
This pushbutton-indicator labelled TIE provides manual control of the DC bus tie contactor.
The pushbutton-indicator is identified by a green flow bar and a caption named OFF. When the
pushbutton is pressed (normal condition), the DC Bus Tie Contactor (BTC) is under automatic
control of the PDU.
When released, the yellow OFF caption illuminates and the DC BTC is manually open.
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DC 1 Bus Tie and DC 2 Bus Tie
Indicators
DC BUS 12 IS TIED TO THE STANDBY TRU
Use and/or disclosure is governed by the Statement on the title page of this document
Two flow bars labelled TIE, illuminate green when the respective DC BUS is connected to the
standby TRU through the DC standby TRU contactors, controlled by the PDU.
The left flow bar indicates that the DC BUS 1 is supplied by the STANDBY TRU (TRU 1
failed or not operative) while the right flow bar indicates that the DC BUS 2 is supplied by the
STANDBY TRU (TRU 2 failed or not operative).
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DC Bus 1 & Bus 2 Indicators
BUS
OFF
WHEN ASSOCIATED DC BUS
IS NOT SUPPLIED
BUS
OFF
DC BUS 1 OFF
DC BUS 2 OFF
ACAWS
Use and/or disclosure is governed by the Statement on the title page of this document
Two yellow indicators (labeled BUS OFF), come on when the associated DC BUS is not
supplied. This condition is controlled by the DC BUS 1 OFF and DC BUS 2 OFF relays. These
are supplied respectively by DC BUS 1 through DC BUS 1 CNT circuit breaker and DC BUS 2
through DC BUS 2 CNT circuit breaker. This failure is monitored by a dedicated ACAWS
caution message DC BUS 1 OFF and DC BUS 2 OFF.
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DC Emer/Essen Bus Tie
Pushbutton-Indicator
RELEASED
(NORMAL CONDITION)
CLOSED
OPEN
PDU PROVIDES AUTOMATIC
CONTROL OF EMMER/ESSEN BUS TIE
Use and/or disclosure is governed by the Statement on the title page of this document
This pushbutton-indicator labeled TIE provides manual control of the emergency bus tie
contactor. The pushbutton-indicator is guarded and has a flow bar indicator.
When the guard is raised and the pushbutton is pressed (emergency condition) the emergency
bus tie contactor is forced to close and the DC EMER BUS and DC ESSEN BUS are
interconnected.
This pushbutton is used to recover the corresponding battery charge operation, when a fault
(short circuit) on one of the DC buses occurs. This is necessary due to the failed bus being
automatically isolated, causing loss of the battery charge line.
This pushbutton is also used to discharge the batteries at the same rate when the total loss of
primary and APU generators occurs and the DC EMER BUS and DC ESSEN BUS are the only
buses available.
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DC Emer/Essen Bus Tie
Pushbutton-Indicator
PUSHED-IN
(EMERGENCY CONDITION)
CLOSED
EMERGENCY BUS TIE CONTACTOR IS
FORCED TO CLOSE AND DC EMER BUS
AND ESSEN BUS ARE INTERCONNECTED
Use and/or disclosure is governed by the Statement on the title page of this document
This pushbutton-indicator labeled TIE provides manual control of the emergency bus tie
contactor. The pushbutton-indicator is guarded and has a flow bar indicator.
When the guard is raised and the pushbutton is pressed (emergency condition) the emergency
bus tie contactor is forced to close and the DC EMER BUS and DC ESSEN BUS are
interconnected.
This pushbutton is used to recover the corresponding battery charge operation, when a fault
(short circuit) on one of the DC buses occurs. This is necessary due to the failed bus being
automatically isolated, causing loss of the battery charge line.
This pushbutton is also used to discharge the batteries at the same rate when the total loss of
primary and APU generators occurs and the DC EMER BUS and DC ESSEN BUS are the only
buses available.
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Battery Charge
Pushbutton-Indicators
FAULT
FAULT
OFF
OFF
ASSOCIATED BATTERY BUS
XFR CONTACTOR IS UNDER
AUTOMATIC CONTROL OF THE PDU
PUSHED-IN
(NORMAL CONDITION)
FAULT
OFF
WHEN THE DC BUS IS SUPPLIED,
BATTERY CHARGE IS INTERRUPTED
RELEASED
FAULT
OFF
PDU OPENS THE ASSOCIATED BATTERY
BUS XFR CONTACTORS
IF FAILURE IS
DETECTED
Use and/or disclosure is governed by the Statement on the title page of this document
Two battery charge pushbutton-indicators labeled CHARGE provide manual control of
batteries bus XFR 2 contactors by isolating the batteries from their charge circuits in the event
of a failure. They also provide the indication of the battery fault during the charge.
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Battery Charge/Discharge Indicators
BATTERYIS
IS
BATTERY
DISCHARGING
CHARGING
Use and/or disclosure is governed by the Statement on the title page of this document
The battery charge/discharge operation in indicated by two green arrows located on the upper
part of EPGS control panel.
Their function is to clearly indicate the battery current direction, whereas upon which arrow is
illuminated is possible to check if the battery is charging or discharging.
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Battery Switch
EMER BUS AND ESSEN BUS
ARE SUPPLIED ONLY
FROM THE RESPECTIVE BATTERIES
(XFR2 CONTACTORS CLOSED
XFR1 CONTACTORS OPEN)
“OVRD” POSITION
“ON” POSITION
“OFF” POSITION
PDU CONTROL
IS BY PASSED
BATTERIES ARE
CONNECTED TO THE
EMER BUS AND
ESSEN BUS
BATTERIES ARE
DISCONNECTED FROM
THE EMER BUS AND
ESSEN BUS
Use and/or disclosure is governed by the Statement on the title page of this document
This switch labelled BATT has three positions: ON, OFF and OVRD. The switch is guarded
between the ON and OVRD positions. When set to ON, (normal position) and guarded down
the batteries are connected to the EMER BUS and ESSEN BUS respectively.
Each emergency battery and APU start battery is automatically disconnected from the
respective bus when the system detects a fault in that battery.
When set to OFF, the batteries are disconnected from the EMER BUS and ESSEN BUS.
When the switch is set to OVRD the normal PDU control is by-passed forcing the EMER BUS
and ESSEN BUS to be supplied only from the respective batteries.
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AC Phase Rotary Selector
ENABLES PHASE VOLTAGE
TESTING
OF A - B - C
Use and/or disclosure is governed by the Statement on the title page of this document
This rotary selector, labelled PHASE, is connected in series to the source and enables the A, B
or C phase of the voltage tested by the voltmeter to be selected.
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AC Source Rotary Selector
ENABLES AC POWER SOURCE
SELECTION
Use and/or disclosure is governed by the Statement on the title page of this document
This selector, labeled AC SOURCE, is a rotary selector with five positions: OFF, GEN 1, GEN
2, APU and EXT which have the following functions:
- OFF: no indications on the voltmeter, ammeter and frequency meter,
- GEN 1: allows to display the voltage, % load and frequency of the generator 1 output,
- GEN 2: allows to display the voltage, % load and frequency of the generator 2 output,
- APU: allows to display the voltage, % load and frequency of the APU generator output,
- EXT: allows to display the voltage, % load and frequency of the external AC power
source.
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AC Source Rotary Selector
NO INDICATIONS ON THE
VOLMETER, AMMETER, AND FREQUENCYMETER
SELECTS DISPLAY OF THE VOLTAGE,
% LOAD AND FREQUENCY OF THE
GENERATOR 1 OUTPUT
SELECTS DISPLAY OF THE VOLTAGE,
% LOAD AND FREQUENCY OF THE
APU GENERATOR OUTPUT
SELECTS DISPLAY OF THE VOLTAGE,
% LOAD AND FREQUENCY OF THE
GENERATOR 2 OUTPUT
SELECTS DISPLAY OF THE VOLTAGE,
% LOAD AND FREQUENCY OF THE
EXTERNAL AC POWER SOURCE
Use and/or disclosure is governed by the Statement on the title page of this document
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AC Digital Displays
AC FREQUENCY
AC VOLTAGE
AC BUS
% OF LOAD
Use and/or disclosure is governed by the Statement on the title page of this document
The AC measuring system provides Voltage, Load and Frequency indication of each AC power
source by means of digital voltmeter, ammeter and frequencymeter under a multi-position
selector control.
The three AC instruments are installed on the upper side of the EPGS control panel, located on
the overhead panel in the flight deck compartment.
The voltage, load and frequency indication signals for the three generators are provided by the
corresponding GCUs whereas the voltage, load and frequency indications for the external
power are provided by the BPCU.
One display labelled V, % and Hz provide respectively the indications of AC voltage, AC bus
loading in percent and AC frequency with green digital 7-segment readout up to 3 digits for
each indication.
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DC Source Rotary Selector
NO INDICATION ON THE VOLMETER
AND AMMETER DISPLAYS
Use and/or disclosure is governed by the Statement on the title page of this document
This selector, labeled DC SOURCE, is a rotary selector with seven positions: OFF, TRU 1,
TRU 2, STBY TRU, APU BATT, EMER BATT and EXT which have the following functions:
- OFF: no indications on the voltmeter and ammeter,
- TRU 1: allows to display the voltage and current of the TRU 1 output,
- TRU 2: allows to display the voltage and current of the TRU 2 output,
- STBY TRU: allows to display the voltage and current of the standby TRU output,
- APU BATT: allows to display the voltage and current of the APU start battery output,
- EMER BATT: allows to display the voltage and current of the emergency battery output,
- EXT: allows to display the voltage and current of the external DC power source.
37
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
DC Source Rotary Selector
ENABLES THE READOUT OF TRU 1
VOLTAGE AND CURRENT OUTPUTS
ON THE RELEVANT DISPLAY
Use and/or disclosure is governed by the Statement on the title page of this document
38
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
DC Source Rotary Selector
ENABLES THE READOUT OF TRU 2
VOLTAGE AND CURRENT OUTPUTS
ON THE RELEVANT DISPLAY
Use and/or disclosure is governed by the Statement on the title page of this document
39
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
DC Source Rotary Selector
ENABLES THE READOUT OF STANDBY
TRU VOLTAGE AND CURRENT
OUTPUTS ON THE RELEVANT DISPLAY
Use and/or disclosure is governed by the Statement on the title page of this document
40
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
DC Source Rotary Selector
ENABLES THE READOUT OF APU
BATTERY VOLTAGE AND CURRENT
OUTPUTS ON THE RELEVANT DISPLAY
Use and/or disclosure is governed by the Statement on the title page of this document
41
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
DC Source Rotary Selector
ENABLES THE READOUT OF EMER
BATTERY VOLTAGE AND CURRENT
OUTPUTS ON THE RELEVANT DISPLAY
Use and/or disclosure is governed by the Statement on the title page of this document
42
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
DC Source Rotary Selector
ENABLES THE READOUT OF
EXTERNAL POWER VOLTAGE AND
CURRENT OUTPUTS ON THE
RELEVANT DISPLAY
Use and/or disclosure is governed by the Statement on the title page of this document
43
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
DC Digital Displays
DC
VOLTAGE
DC
CURRENT
Use and/or disclosure is governed by the Statement on the title page of this document
Two displays labelled V and A provide respectively the indications of voltage and current by
green digital 7-segmentreadout (up to 3 digits). The PDU also provides a signal that identifies
the charging current with respect to the discharging current, to allow "current measurements"
of the battery, when APU BATT or EMER BATT is selected. This signal is used to show a +
or - indication in front of the current display and to drive the battery charge/discharge arrows.
44
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Circuit Breakers Panels
Overhead Panel Location
271VE
Use and/or disclosure is governed by the Statement on the title page of this document
45
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Circuit Breakers Panels
Rear Panels Location
UPPER
MID
COPILOT
SEAT
REAR PANELS
LOWER
Use and/or disclosure is governed by the Statement on the title page of this document
46
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
AC External Socket Location
Use and/or disclosure is governed by the Statement on the title page of this document
The external receptacle is located on the aft end of the left landing gear fairing. The receptacle
allows an external power source to be connected to the aircraft while it is on the ground.
47
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
AC External Socket Indicators
EXT AC
NOT CONNECTED
EXT AC
CONNECTED
AND NOT IN USE
EXT AC
CONNECTED
AND IN USE
Use and/or disclosure is governed by the Statement on the title page of this document
Two advisory light are installed inside the external receptacle just above the socket and used
to aware the ground mechanics about the electrical power condition.
When the AC external power is connected and good quality is detected by the BPCU, both
green lights illuminate whereas one extinguishes whenever the AC EXT pushbutton is
depressed.
48
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
DC External Socket Indicators
EXT DC
NOT CONNECTED
EXT DC
CONNECTED
AND NOT IN USE
EXT DC
CONNECTED
AND IN USE
Use and/or disclosure is governed by the Statement on the title page of this document
Two advisory light are installed inside the external receptacle just above the socket and used
to aware the ground mechanics about the electrical power condition.
When the DC external power is connected and good quality is detected by the PDU, both green
lights illuminate whereas one extinguishes whenever the EXT DC pushbutton is depressed.
49
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Electrical External Power
Enable Switch (In Flight)
WHEN THE AIRCRAFT IS ON THE JACKS THE
EXTERNAL POWER IS DISABLED
THE EXTERNAL POWER CAN BE ENABLED
WITH THE SWITCH IN FLIGHT POSITION
ELECTRICAL RACK
Use and/or disclosure is governed by the Statement on the title page of this document
The external power is normally used to supply the aircraft network for maintenance duties.
The PSEU (Proximity Switch Electronic Unit) provides a logic to disable the external
connection if the landing gear shock absorbers are extended (i.e. aircraft is on the jacks).
In this configuration to enable the external power, a dedicated switch is installed in the cockpit
just above the electrical rack, the use of which by-passes the PSEU logic permitting the use of
external power.
50
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Start-Up
EMERGENCY
BATTERY
M
HOT EMER BAT BUS
EMER
BUS
XFR2
CNTOR
APU START
BATTERY
APU STARTER
APU START
CNTOR
APU BAT STR
CNTOR
HOT APU BAT BUS
APU STARTING BUS
ESSEN BUS
XFR 2
CNTOR
DC EMER BUS
DC ESSEN BUS
EMER BUS
TIE CNTOR
EMER
BUS
XFR1
CNTOR
APU TRU STR
CNTOR
ESSEN BUS
XFR 1
CNTOR
DC BUS TIE
CNTOR
DC BUS 1
TRU 1
CNTOR
DC BUS 2
DC STBY TRU
CNTOR 1
DC STBY TRU
CNTOR 2
TRU 2
CNTOR
STBY
TRU
TRU 1
AC STBY TRU
CNTOR 1
26VAC BUS1
TRU 2
AC STBY TRU
CNTOR 2
26VAC BUS2
AC BUS 2
AC BUS1
AC BUS TIE1
CNTOR
GEN 1
CNTOR
DC EXT PWR
CNTOR
AC
GEN 1
AC EXT PWR
CNTOR
APU GEN
CNTOR
APU
GEN
50/60
kVA
DC EXT PWR
AC BUS TIE2
CNTOR
50/60
kVA
AC EXT PWR
GEN 2
CNTOR
50/60
kVA
AC
GEN 2
Use and/or disclosure is governed by the Statement on the title page of this document
AT Start –Up (If no AC/DC external power is connected)
The Emergency Battery supplies the Hot Emergency BUS and the EMERGENCY BUS via the
EMER BUS XFR 2 Contactor;
The APU Start Battery supplies the Hot APU Battery BUS and the ESSENTIAL BUS via the
ESSEN BUS XFR 2 Contactor.
51
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Start-Up (Ext Power Not Connected)
FAULT
FAULT
OFF
OFF
BUS
OFF
FAULT
AVAIL
ON
ON
R
R =RELEASED
BUS
OFF
R
OFF
FAULT
FAULT
OFF
OFF
BUS
OFF
FAULT
OFF
BUS
OFF
OFF
OFF
R
AVAIL
FAULT
FAULT
ON
OFF
OFF
Use and/or disclosure is governed by the Statement on the title page of this document
AT Start –Up the BUS OFF indications (AC-DC) and the FAULT caption on GENs p/b
Switches are displayed.
52
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
APU available (Generators OFF)
EMERGENCY
BATTERY
M
HOT EMER BAT BUS
EMER
BUS
XFR2
CNTOR
APU START
BATTERY
APU STARTER
APU START
CNTOR
APU BAT STR
CNTOR
HOT APU BAT BUS
APU STARTING BUS
ESSEN BUS
XFR 2
CNTOR
DC EMER BUS
DC ESSEN BUS
EMER BUS
TIE CNTOR
EMER
BUS
XFR1
CNTOR
APU TRU STR
CNTOR
ESSEN BUS
XFR 1
CNTOR
DC BUS TIE
CNTOR
DC BUS 1
TRU 1
CNTOR
DC BUS 2
DC STBY TRU
CNTOR 1
DC STBY TRU
CNTOR 2
TRU 2
CNTOR
STBY
TRU
TRU 1
AC STBY TRU
CNTOR 1
26VAC BUS1
TRU 2
AC STBY TRU
CNTOR 2
26VAC BUS2
AC BUS 2
AC BUS1
GEN 1
CNTOR
AC
GEN 1
AC BUS TIE1
CNTOR
DC EXT PWR
CNTOR
50/60
kVA
AC EXT PWR
CNTOR
APU GEN
CNTOR
APU
GEN
OFF
DC EXT PWR
AC BUS TIE2
CNTOR
50/60
kVA
AC EXT PWR
GEN 2
CNTOR
OFF
50/60
kVA
AC
GEN 2
Use and/or disclosure is governed by the Statement on the title page of this document
If a fault is detected on two channels (GEN 1 & 2), the associated GCUs open the respective
GC: this condition is indicated by the illumination of the FAULT amber light on the
corresponding GEN pb switches and on the ACAWS.
The APU GCU closes the APU GEN Contactor (if P/b is pressed) and the BPCU, energizes the
two BTCs (1 & 2) connecting the AC BUS1 and 2 to the APU generator, and indicating the
bus-tie condition by the illumination of the flow bar on the BTC pb switches.
53
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Ground Config. (APU available)
FAULT
FAULT
OFF
OFF
BUS
OFF
BUS
OFF
FAULT
AVAIL
ON
ON
R
R
OFF
R =RELEASED
FAULT
FAULT
OFF
OFF
BUS
OFF
FAULT
OFF
BUS
OFF
OFF
OFF
R
AVAIL
FAULT
FAULT
ON
OFF
OFF
Use and/or disclosure is governed by the Statement on the title page of this document
In Ground Configuration (AC Ext Connected and Available), releasing the GENs p/b (OFF),
pressing the AC EXT switch (AVAIL and ON lit) the AC BUSES are supplied through the AC
BUS TIE Contactors (Flow bar lit on both AC BUS tie Contactor switches).
54
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
APU available (Generator 2 ON)
EMERGENCY
BATTERY
M
HOT EMER BAT BUS
EMER
BUS
XFR2
CNTOR
APU START
BATTERY
APU STARTER
APU START
CNTOR
APU BAT STR
CNTOR
HOT APU BAT BUS
APU STARTING BUS
ESSEN BUS
XFR 2
CNTOR
DC EMER BUS
DC ESSEN BUS
EMER BUS
TIE CNTOR
EMER
BUS
XFR1
CNTOR
APU TRU STR
CNTOR
ESSEN BUS
XFR 1
CNTOR
DC BUS TIE
CNTOR
DC BUS 1
TRU 1
CNTOR
DC BUS 2
DC STBY TRU
CNTOR 1
DC STBY TRU
CNTOR 2
TRU 2
CNTOR
STBY
TRU
TRU 1
AC STBY TRU
CNTOR 1
26VAC BUS1
TRU 2
AC STBY TRU
CNTOR 2
26VAC BUS2
AC BUS 2
AC BUS1
GEN 1
CNTOR
AC
GEN 1
AC BUS TIE1
CNTOR
DC EXT PWR
CNTOR
50/60
kVA
AC EXT PWR
CNTOR
APU GEN
CNTOR
APU
GEN
OFF
DC EXT PWR
AC BUS TIE2
CNTOR
50/60
kVA
AC EXT PWR
GEN 2
CNTOR
ON
50/60
kVA
AC
GEN 2
Use and/or disclosure is governed by the Statement on the title page of this document
If a fault is detected on two channels (GEN 1 & 2), the associated GCUs open the respective
GC: this condition is indicated by the illumination of the FAULT amber light on the
corresponding GEN pb switches and on the ACAWS.
The APU GCU closes the APU GEN Contactor (if P/b is pressed) and the BPCU, energizes the
two BTCs (1 & 2) connecting the AC BUS1 and 2 to the APU generator, and indicating the
bus-tie condition by the illumination of the flow bar on the BTC pb switches.
55
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Start-Up Engine Generator
EMERGENCY
BATTERY
M
HOT EMER BAT BUS
EMER
BUS
XFR2
CNTOR
APU START
BATTERY
APU STARTER
APU START
CNTOR
APU BAT STR
CNTOR
HOT APU BAT BUS
APU STARTING BUS
ESSEN BUS
XFR 2
CNTOR
DC ESSEN BUS
DC EMER BUS
EMER BUS
TIE CNTOR
EMER
BUS
XFR1
CNTOR
APU TRU STR
CNTOR
ESSEN BUS
XFR 1
CNTOR
DC BUS TIE
CNTOR
DC BUS 1
DC BUS 2
TRU 1 CNTOR
DC STBY TRU
CNTOR 1
TRU 2
CNTOR
DC STBY TRU
CNTOR 2
STBY
TRU
TRU 1
AC STBY TRU
CNTOR 1
26VAC BUS1
TRU 2
AC STBY TRU
CNTOR 2
26VAC BUS2
AC BUS 2
AC BUS1
AC BUS TIE1
CNTOR
GEN 1
CNTOR
DC EXT PWR
CNTOR
AC
GEN 1
AC EXT PWR
CNTOR
APU GEN
CNTOR
APU
GEN
50/60
kVA
DC EXT PWR
AC BUS TIE2
CNTOR
50/60
kVA
AC EXT PWR
GEN 2
CNTOR
50/60
kVA
AC
GEN 2
Use and/or disclosure is governed by the Statement on the title page of this document
Battery switch set in ON position
AT Start –Up (If no AC/DC external power is connected)
The Emergency Battery supplies the Hot Emergency BUS and the EMERGENCY BUS via
the EMER BUS XFR 2 Contactor;
The APU Start Battery supplies the Hot APU Battery BUS and the ESSENTIAL BUS via
the ESSEN BUS XFR 2 Contactor.
56
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Start-Up Engine Generator
EMERGENCY
BATTERY
M
HOT EMER BAT BUS
EMER
BUS
XFR2
CNTOR
APU START
BATTERY
APU STARTER
APU START
CNTOR
APU BAT STR
CNTOR
HOT APU BAT BUS
APU STARTING BUS
ESSEN BUS
XFR 2
CNTOR
DC ESSEN BUS
DC EMER BUS
EMER BUS
TIE CNTOR
EMER
BUS
XFR1
CNTOR
APU TRU STR
CNTOR
ESSEN BUS
XFR 1
CNTOR
DC BUS TIE
CNTOR
DC BUS 1
DC BUS 2
TRU 1 CNTOR
DC STBY TRU
CNTOR 1
TRU 2
CNTOR
DC STBY TRU
CNTOR 2
STBY
TRU
TRU 1
AC STBY TRU
CNTOR 1
26VAC BUS1
TRU 2
AC STBY TRU
CNTOR 2
26VAC BUS2
AC BUS 2
AC BUS1
AC BUS TIE1
CNTOR
GEN 1
CNTOR
DC EXT PWR
CNTOR
AC
GEN 1
AC EXT PWR
CNTOR
APU GEN
CNTOR
APU
GEN
50/60
kVA
DC EXT PWR
AC BUS TIE2
CNTOR
50/60
kVA
AC EXT PWR
GEN 2
CNTOR
50/60
kVA
AC
GEN 2
Use and/or disclosure is governed by the Statement on the title page of this document
Battery switch set in ON position
AT Start –Up (If no AC/DC external power is connected)
The Emergency Battery supplies the Hot Emergency BUS and the EMERGENCY BUS via
the EMER BUS XFR 2 Contactor;
The APU Start Battery supplies the Hot APU Battery BUS and the ESSENTIAL BUS via
the ESSEN BUS XFR 2 Contactor.
57
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Normal Operation
FAULT
FAULT
OFF
OFF
BUS
OFF
FAULT
AVAIL
ON
ON
R
R =RELEASED
BUS
OFF
R
OFF
FAULT
FAULT
OFF
OFF
BUS
OFF
FAULT
OFF
BUS
OFF
OFF
OFF
R
AVAIL
FAULT
FAULT
ON
OFF
OFF
Use and/or disclosure is governed by the Statement on the title page of this document
If APU Gen switch is released the caption OFF illuminates.
58
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Short Circuit on DC BUS 1
EMERGENCY
BATTERY
M
HOT EMER BAT BUS
EMER
BUS
XFR2
CNTOR
APU START
BATTERY
APU STARTER
APU START
CNTOR
APU BAT STR
CNTOR
HOT APU BAT BUS
APU STARTING BUS
ESSEN BUS
XFR 2
CNTOR
DC EMER BUS
OPEN
DC ESSEN BUS
EMER BUS
TIE CNTOR
EMER
BUS
XFR1
CNTOR
APU TRU STR
CNTOR
ESSEN BUS
XFR 1
CNTOR
DC BUS TIE
CNTOR
DC BUS 1
OPEN
DC BUS 2
DC STBY TRU
CNTOR 1
TRU 1
CNTOR
DC STBY TRU
CNTOR 2
TRU 2
CNTOR
STBY
TRU
TRU 1
AC STBY TRU
CNTOR 1
26VAC BUS1
TRU 2
AC STBY TRU
CNTOR 2
26VAC BUS2
AC BUS 2
AC BUS1
AC BUS TIE1
CNTOR
GEN 1
CNTOR
DC EXT PWR
CNTOR
AC
GEN 1
AC EXT PWR
CNTOR
APU GEN
CNTOR
APU
GEN
50/60
kVA
DC EXT PWR
AC BUS TIE2
CNTOR
50/60
kVA
AC EXT PWR
GEN 2
CNTOR
50/60
kVA
AC
GEN 2
Use and/or disclosure is governed by the Statement on the title page of this document
In case of Short circuit on DC BUS 1, the TRU 1 contactor and Emer Bus XFR1 Contactor
open; the DC EMER BUS can be supplied DC ESSEN BUS by manually pressing EMER
BUS TIE Contactor switch.
59
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Ground Config. (AC Ext Pwr available)
EMERGENCY
BATTERY
M
HOT EMER BAT BUS
EMER
BUS
XFR2
CNTOR
APU START
BATTERY
APU STARTER
APU START
CNTOR
APU BAT STR
CNTOR
HOT APU BAT BUS
APU STARTING BUS
ESSEN BUS
XFR 2
CNTOR
DC EMER BUS
DC ESSEN BUS
EMER BUS
TIE CNTOR
EMER
BUS
XFR1
CNTOR
APU TRU STR
CNTOR
ESSEN BUS
XFR 1
CNTOR
DC BUS TIE
CNTOR
DC BUS 1
TRU 1
CNTOR
DC BUS 2
DC STBY TRU
CNTOR 1
DC STBY TRU
CNTOR 2
TRU 2
CNTOR
STBY
TRU
TRU 1
AC STBY TRU
CNTOR 1
26VAC BUS1
TRU 2
AC STBY TRU
CNTOR 2
26VAC BUS2
AC BUS 2
AC BUS1
AC BUS TIE1
CNTOR
GEN 1
CNTOR
DC EXT PWR
CNTOR
AC
GEN 1
AC EXT PWR
CNTOR
APU GEN
CNTOR
APU
GEN
50/60
kVA
DC EXT PWR
AC BUS TIE2
CNTOR
50/60
kVA
AC EXT PWR
GEN 2
CNTOR
50/60
kVA
AC
GEN 2
Use and/or disclosure is governed by the Statement on the title page of this document
If AC External Power is connected the AC Pwr contactor closes, and the AC BUSES 1&2
can be supplied through AC BUS TIE Contactors 1&2 (closed).
60
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
115 009 400 28.0
EMERGENCY
BATTERY
M
HOT EMER BAT BUS
EMER
BUS
XFR2
CNTOR
41
APU START
BATTERY
APU STARTER
APU START
CNTOR
APU BAT STR
CNTOR
HOT APU BAT BUS
APU STARTING BUS
ESSEN BUS
XFR 2
CNTOR
DC EMER BUS
DC ESSEN BUS
EMER BUS
TIE CNTOR
EMER
BUS
XFR1
CNTOR
Sep 2010 – Rev 0
APU TRU STR
CNTOR
ESSEN BUS
XFR 1
CNTOR
DC BUS TIE
CNTOR
DC BUS 1
TRU 1
CNTOR
DC BUS 2
DC STBY TRU
CNTOR 1
DC STBY TRU
CNTOR 2
TRU 2
CNTOR
STBY
TRU
TRU 1
AC STBY TRU
CNTOR 1
26VAC BUS1
TRU 2
AC STBY TRU
CNTOR 2
26VAC BUS2
AC BUS 2
AC BUS1
AC BUS TIE1
CNTOR
GEN 1
CNTOR
DC EXT PWR
CNTOR
AC
GEN 1
AC EXT PWR
CNTOR
APU GEN
CNTOR
APU
GEN
50/60
kVA
DC EXT PWR
AC BUS TIE2
CNTOR
50/60
kVA
AC EXT PWR
GEN 2
CNTOR
50/60
kVA
AC
GEN 2
Use and/or disclosure is governed by the Statement on the title page of this document
If AC External Power is connected the AC Pwr contactor closes, and the AC BUSES 1&2
can be supplied through AC BUS TIE Contactors 1&2 (closed).
61
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Ground Config. (AC Ext Pwr available)
FAULT
FAULT
OFF
OFF
BUS
OFF
BUS
OFF
FAULT
AVAIL
ON
ON
R
R =RELEASED
OFF
FAULT
FAULT
OFF
OFF
BUS
OFF
R
BUS
OFF
OFF
OFF
FAULT
AVAIL
OFF
ON
R
FAULT
OFF
R
FAULT
OFF
Use and/or disclosure is governed by the Statement on the title page of this document
In Ground Configuration (AC Ext Connected and Available), releasing the GENs p/b (OFF),
pressing the AC EXT switch (AVAIL and ON lit) the AC BUSES are supplied through the AC
BUS TIE Contactors (Flow bar lit on both AC BUS tie Contactor switches).
62
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Failure of Gen 2 (APU available)
EMERGENCY
BATTERY
M
HOT EMER BAT BUS
EMER
BUS
XFR 1
CNTOR
APU START
BATTERY
APU STARTER
APU START
CNTOR
APU BAT STR
CNTOR
HOT APU BAT BUS
APU STARTING BUS
ESSEN BUS
XFR 1
CNTOR
DC EMER BUS
DC ESSEN BUS
EMER BUS
TIE CNTOR
EMER
BUS
XFR 2
CNTOR
APU TRU STR
CNTOR
ESSEN BUS
XFR 2
CNTOR
DC BUS TIE
CNTOR
DC BUS 1
TRU 1
CNTOR
DC BUS 2
DC STBY TRU
CNTOR 1
DC STBY TRU
CNTOR 2
TRU 2
CNTOR
STBY
TRU
TRU 1
AC STBY TRU
CNTOR 1
26VAC BUS1
TRU 2
AC STBY TRU
CNTOR 2
26VAC BUS2
AC BUS 2
AC BUS1
AC BUS TIE1
CNTOR
GEN 1
CNTOR
DC EXT PWR
CNTOR
AC
GEN 1
AC EXT PWR
CNTOR
APU GEN
CNTOR
APU
GEN
50/60
kVA
DC EXT PWR
50/60
kVA
AC BUS TIE2
CNTOR
AVAILABLE
AC EXT PWR
GEN 2
CNTOR
FAIL 50/60
kVA
AC
GEN 2
Use and/or disclosure is governed by the Statement on the title page of this document
If a fault is detected on one channel (GEN 2), the associated GCU opens the respective Gen
Contactor: this condition is indicated by the illumination of the FAULT amber light on the
corresponding GEN 2 switch and on the ACAWS.
If in the above fault condition the APU generator is available, it takes the AC bus of the faulty
generator through the closing of the APU GC and one BTC (AC BTC 2 if the GEN2 fails).
63
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Failure of Gen 2 (APU available)
FAULT
FAULT
OFF
OFF
BUS
OFF
FAULT
AVAIL
ON
ON
R
R =RELEASED
Right generator fails.
BUS
OFF
R
Since the APU gen
operates as back-up,
the right side power
distribution is being
supplied via the BTC
OFF
FAULT
FAULT
OFF
OFF
GEN 2 FAULT
BUS
OFF
OFF
FAULT
OFF
BUS
OFF
OFF
R
AVAIL
FAULT
FAULT
ON
OFF
OFF
Use and/or disclosure is governed by the Statement on the title page of this document
If there is fault on Gen 2 the caption FAULT on GEN 2 p/b switch illuminates (switch pressed)
and the relevant ACAWS message is displayed; if APU is available the DC BUS 2 is supplied
by APU GEN by AC BUS TIE Contactor 2 closing (green flow illuminates on relevant switch).
64
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Failure of Gen 2 (APU available)
FAULT
FAULT
OFF
OFF
BUS
OFF
FAULT
AVAIL
ON
ON
R
R =RELEASED
BUS
OFF
R
OFF
FAULT
FAULT
OFF
OFF
BUS
OFF
OFF
FAULT
OFF
BUS
OFF
OFF
R
AVAIL
FAULT
ON
OFF
R
FAULT
OFF
Use and/or disclosure is governed by the Statement on the title page of this document
If Gen 2 switch is released the caption OFF illuminates.
65
2400G01T00_AV – ELECTRICAL POWER GENERATION SYSTEM
Sep 2010 – Rev 0
Failure of Gen 2 (APU not available)
Right generator fails.
FAULT
FAULT
OFF
OFF
BUS
OFF
FAULT
AVAIL
ON
ON
R
R =RELEASED
BUS
OFF
R
The right side power
distribution is being
supplied via the
BTC’s
OFF
FAULT
FAULT
OFF
OFF
GEN 2 FAULT
BUS
OFF
OFF
AVAIL
FAULT
OFF
BUS
OFF
OFF
R
ON
R
FAULT
FAULT
OFF
OFF
Use and/or disclosure is governed by the Statement on the title page of this document
If there is fault on Gen 2 the caption FAULT on GEN 2 p/b switch illuminates (switch pressed)
and the relevant ACAWS message is displayed; if APU is not available the AC BUS 2 is
supplied by GEN 1 by AC BUS TIE Contactors 1 & 2 closing (green flow illuminates on
relevant switches).
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Failure of Gen 2 (APU not available)
FAULT
FAULT
OFF
OFF
BUS
OFF
FAULT
AVAIL
ON
ON
R
R =RELEASED
BUS
OFF
R
OFF
FAULT
FAULT
OFF
OFF
BUS
OFF
AVAIL
FAULT
OFF
BUS
OFF
OFF
OFF
R
ON
R
FAULT
OFF
R
FAULT
OFF
Use and/or disclosure is governed by the Statement on the title page of this document
If Gen 2 switch is released the caption OFF illuminates.
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TESTING FACILITIES
Associated to Electrical Power System
Use and/or disclosure is governed by the Statement on the title page of this document
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Testing Facilities
 GCU BITE
 BPCU BITE
 PDU BITE
Use and/or disclosure is governed by the Statement on the title page of this document
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GCU BIT
Purpose of BIT
Initiation of BIT
Messages and Results
Use and/or disclosure is governed by the Statement on the title page of this document
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Purpose of BIT (GCU BIT)
 The GCU provides a Built in Test (BIT) to check its
main function.
 During the confidence check the unit tests the
following protection functions:
 Overvoltage protection
 Overfrequency protection
 Undervoltage protection
 Underfrequency protection
 Differential fault protection
 Generator diode failure
protection
 Overcurrent protection
 Open phase protection
Use and/or disclosure is governed by the Statement on the title page of this document
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Initiation of BIT (GCU BIT)
The Confidence Check can
be manually initiated by a
push-button, it must be
pressed (1,5 sec) and the
red lamp is switched on
Use and/or disclosure is governed by the Statement on the title page of this document
It can be done with aircraft on the ground and the relevant generator is not running.
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Messages and Results (GCU BIT)
 If the test is successful the red lump is
switched-off otherwise the lamp will flicker.
Use and/or disclosure is governed by the Statement on the title page of this document
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BPCU BIT
Purpose of BIT
Initiation of BIT
Messages and Results
Use and/or disclosure is governed by the Statement on the title page of this document
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Purpose of BIT (BPCU BIT)
The Unit checks the following protection function:
 External power overvoltage protection
 External power undervoltage protection
 External power undercurrent protection
 External power open phase protection
 External power overfrequency protection
 External power underfrequency protection
 External power phase sequence protection
Use and/or disclosure is governed by the Statement on the title page of this document
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Initiation of BIT (BPCU BIT)
The BIT is performed by
pressing , for about 1,5
seconds, the confidence
check push-button.
Use and/or disclosure is governed by the Statement on the title page of this document
It can be done with the aircraft on ground and the A/C EXT power is not connected.
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Messages and Results (BPCU BIT)
 Upon successful completion of test,
the red indicator will be off,
otherwise the lamp will flicker.
Use and/or disclosure is governed by the Statement on the title page of this document
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PDU BIT
Purpose of BIT
Initiation of BIT
Messages and Results
Use and/or disclosure is governed by the Statement on the title page of this document
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Purpose of BIT (PDU BIT)
The PDU is provided with a BIT, which permits
to check the internal protection circuits related
to the following aircraft electrical sources:
TRU1 and 2
STBY TRU
EXT PWR
EMER BATT
APU BATT
Use and/or disclosure is governed by the Statement on the title page of this document
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Initiation of BIT (PDU BIT)
 The test can be actuated only on the ground and
with no power to the main DC busses.
 When the “protection test” p/b is pressed, the
illuminate lights denote that the test is in progress.
Use and/or disclosure is governed by the Statement on the title page of this document
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Messages and Results (PDU BIT)
 Upon a successful test completion, the LEDS
will remain on, otherwise, if it is unsuccessful the
lights will be put off.
Use and/or disclosure is governed by the Statement on the title page of this document
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Any Questions on Testing
Facilities?
Use and/or disclosure is governed by the Statement on the title page of this document
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Avionic Systems ACAWS Messages
CAUTION
AC BUS 1 (2) OFF
ON CMDU 3
Respective AC BUS is not powered.
ON CMDU 3
APU BATTERY FAULT
APU battery fault detected.
ON CMDU 3
APU GEN FAULT
APU generator trips off line due to an
over or under voltage, over or under
frequency, or feeder fault.6UY
ON CMDU 3
DC BUS 1 (2) OFF
Respective DC bus is not powered.
Use and/or disclosure is governed by the Statement on the title page of this document
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Avionic Systems ACAWS Messages
CAUTION
RPS 1 (2) FAIL
ON CMDU 3
Respective Regulated Power Supply
failed.
ON CMDU 3
STBY TRU FAULT
Standby TRU fault detected.
ON CMDU 3
TRU 1 (2) FAULT
Respective TRU fault detected.
Use and/or disclosure is governed by the Statement on the title page of this document
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Avionic Systems ACAWS Messages
CAUTION
RPS 1 (2) FAIL
ON CMDU 3
Respective Regulated Power Supply
failed.
ON CMDU 3
STBY TRU FAULT
Standby TRU fault detected.
ON CMDU 3
TRU 1 (2) FAULT
Respective TRU fault detected.
Use and/or disclosure is governed by the Statement on the title page of this document
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Avionic Systems ACAWS Messages
CAUTION
DC EMER BUS OFF
ON CMDU 3
DC Emergency bus is off.
ON CMDU 3
DC ESS BUS OFF
DC Essential bus is off.
ON CMDU 3
EMER BATTERY FAULT
Fault detected in the emergency battery.
ON CMDU 3
GEN 1 (2) FAULT
Respective engine generator trips off
line due to an over or under voltage,
over or under frequency, or feeder fault.
Use and/or disclosure is governed by the Statement on the title page of this document
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Avionic Systems ACAWS Messages
ADVISORY
ON CMDU 3
AC BPCU COMM FAULT
AC Bus Power Control Unit has lost
communication with the MC.
Use and/or disclosure is governed by the Statement on the title page of this document
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Conclusions
Describe
hazards, safety requirements and sys features
Describe
AC/DC system components and architecture
Describe
AC/DC distribution and components location.
Describe
and locate the systems controls and indicators.
State
the systems ACAWS messages and describe the
associated crew response actions.
Describe
the principles of operation of the systems in normal
and emergency condition
Use and/or disclosure is governed by the Statement on the title page of this document
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Any Questions?
Use and/or disclosure is governed by the Statement on the title page of this document
89