Bombardier-Challenger_00-Electrical电气

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canadair
chatienQer
OPERATING MANUAL
SECTION 7
ELECTRICAL
TABLE OF CONTENTS
Subject
SUPPLY
General
Power Generating Systems
DC Static Conversion System
Secondary DC Power System
External Power System
AC Power
No. 1 and No. 2 Generators
Transfer and Bus Tie
APU and External Power
AC Metering
DC Power
Internal DC Power
External DC Power
DC Metering
DISTRIBUTION
Page
1
2
3
Figure
Number
LIST OF ILLUSTRATIONS
Title Pajge
1 Electrical System - Basic Configuration
2 Electrical System Control Panels
3 Primary AC Control
4 Auxiliary AC Control
5 Main DC Control
6 Essential AC Power and ADG Control
7 External Power and Battery Control
8 AC and DC Metering
5
6
7
8
9
10
11
12
7 - CONTENTS
Page 1
Oct 03/83
chanenper
OPERATING MANUAL
Figure
Number Title Page
| 9 Main AC No. 1 and DC No. 1 Circuit Breaker Panel (6 Sheets) 13
| 10 Battery Bus - Left Circuit Breaker Panel 19
| 11 Main AC No. 2 and DC No. 2 Circuit Breaker Panel (2 Sheets) 20
| 12 Battery Bus - Right Circuit Breaker Panel (2 Sheets) 22
13 AC Essential Bus Circuit Breaker Panel (3 Sheets) 24
14 DC Essential Bus Circuit Breaker Panel (3 Sheets) 27
I 15 Aft Electrical Distribution Box Circuit Breaker Panel {2 Sheets) 30
7 - CONTENTS
Page 2
Oct 03/83
canaaair
chauenQer
OPERATING MANUAL
SECTION 7
ELECTRICAL
1. SUPPLY
A. General
The electrical power system consists of generating and static conversion
systems, and secondary and external power systems*
| (1) Power Generating Systems
There are three power generating systems:
( Primary ac power is provided by two integrated drive generators,
GEN 1 and GEN 2. Both generators provide 115/200 volts ac, 400
Hz, 3 phase, with a maximum power rating of 30 kVA.
I - Auxiliary ac power is provided by the auxiliary power unit (APU).
The generator output is 115/200 volts ac, 400 Hz, 3 phase, with a
maximum power rating of 30 kVA.
I - Emergency ac power is provided by an air-driven generator (ADG).
The generator provides 115/200 volts, 400 Hz, 3 phase, with a
maximum power rating of 15 kVA at 160 knots.
| (2) DC Static Conversion System
The primary and essential ac supplies are fed to three transformer
rectifier units (TRU) which produce unregulated 28-volt dc supplies.
(3) Secondary DC Power System
A nickel-cadmium battery provides secondary and emergency dc power.
(4) External Power System
| The aircraft can be supplied from an external source through ac and dc
receptacles on the lower fuselage.
B. AC Power (Figures 1, 2, 3 and 4)
(1) No. 1 and No. 2 Generators
Each generator normally supplies its own distribution system. GEN 1
supplies power to the ac main bus No. 1 which feeds the ac essential
I bus, TRU 1 and the ac utility bus No. 1. The AC essential bus
supplies the essential loads and TRU 3.
SECTION 7
Page 1
Oct 03/83
canadair
OPERATING MANUAL
GEN 2 supplies ac main bus No. 2 which feeds the main No. 2 loads,
TRU 2, ac utility bus No. 2 and the battery charger.
Transfer and Bus Tie (Figures 1, 2, 5 and 6)
If either primary generator fails, the associated bus is transferred
automatically to the other generator and both ac utility busses are
isolated. The GEN OFF light comes on but the MAIN BUS OFF light
remains out to indicate that the bus is tied to another supply. To
restore the services of the ac utility busses, the APU generator must
be brought on line.
Under bus tie conditions, if an overload occurs in the bus tie, the
generator control circuit de-energizes the transfer contactors and the
FAIL and MAIN BUS OFF lights come on. When the AUTO OFF/FAIL
switch/light is pressed, the automatic transfer circuit is inhibited,
the AUTO OFF light comes on and the FAIL light goes out.
If power is lost from ac main bus No. 1, the essential transfer
contactor automatically transfers the ac essential bus to ac main bus
No. 2.
If all ac power is lost, the ADG is deployed automatically. If
automatic deployment fails, the ADG can be deployed manually by
operating the manual deploy handle located on the centre pedestal.
When the ADG comes on line, the ADG ac emergency transfer contactor
transfers the ac essential bus to the ADG bus and also connects the
dc essential bus to the battery bus.
APU and External Power (Figures 1, 2 and 7)
The APU and external ac power can supply any ac bus through the AP/EP
contactor and line and transfer contactors.
When external power is connected to the aircraft the AVAIL light comes
on. When the GPWR switch is set to on, the external contactor
energizes. The AVAIL light goes out, the IN USE light comes on and
the external power is connected to the ac main busses. When the APU
is running and on line, it overrides the external supply and supplies
power to the main busses.
AC Metering (Figure 8)
All sources of ac power are monitored on the metering section of the
power management panel.
SECTION 7
Page 2
Oct 03/83
canadair
chaiienc/er
OPERATING MANUAL
DC Power
(1) Internal DC Power
When ac power is available from the ac busses, the transformer
rectifier units supply dc power to dc bus No. 1, dc bus No. 2, and the
dc essential bus. Two other busses, dc utility bus No. 1 and dc
utility bus No. 2, are supplied by dc bus No. 1 and dc bus No. 2
respectively under normal operating conditions. Power to the battery
bus from the battery direct bus is fed via a battery contactor
controlled by a battery bus power sensing relay. Normally this relay
is energized and the battery bus is isolated except when a bus tie
operation is carried out. Each bus, except the utilities, has an
associated light which is out when the bus has power.
If either dc bus No. 1 or No. 2 loses power, it can be supplied from
the other bus by pressing the appropriate BUS TIE CLOSED switch/light
on the power management panel. When the bus is tied, the BUS TIE
CLOSED light comes on. If the dc essential bus loses power because of
TRU 3 failure, it can be supplied from either dc bus No. 1 or No. 2 by
pressing the appropriate BUS TIE CLOSED switch/light. For any of the
described tie conditions, the battery bus receives power.
If a complete power failure occurs, an emergency transfer takes place
and power is fed from the battery direct bus via the battery
contactor. The contactor is energized via the BATTERY MASTER switch
and de-energized battery bus power sensing relay. The dc essential
bus receives power from the battery bus via an emergency dc transfer
contactor. The BATT BUS OFF light goes out and the CHARGE light comes
on, indicating that the battery is on load.
The battery direct bus supplies refuel/defuel facilities, passenger
doors, control circuits for the battery, boarding lights and service
lights.
(2) External DC Power
External dc power is connected to the aircraft through an external
receptacle located adjacent to the battery compartment. It energizes
an external dc contactor and supplies the battery direct bus.
(3) DC Metering
A rotary switch on the power management panel permits all sources of
dc power to be monitored on the metering section.
SECTION 7
Page 3
Oct 03/83
canaaatr
cftanentjer
OPERATING MANUAL
2. DISTRIBUTION
| Primary ac power from the integrated drive generators (GEN 1 and GEN 2) or from
the APU generator and external ac power are supplied to ac main bus No. 1 and
ac main bus No. 2 through the main electrical distribution panel. The ac
essential bus is normally supplied from ac main bus No. 1 but transfer
facilities permit the ac essential bus to be fed from ac main bus No. 2 or, in
an emergency, from the ADG bus.
Primary dc power to dc bus No. 1 and dc bus No. 2 is obtained from primary ac
I power by transformer rectifier units (TRUs). The dc essential bus is supplied
from the essential TRU. Battery and external dc power are fed to the battery
| bus through the aft electrical distribution box and the battery direct bus.
The electrical power is distributed through the following circuit breaker
panels:
I - CBP-A is located on the forward bulkhead behind the pilot's position and is
divided into two sections. One section contains ac main bus No. 1, dc bus
No. 1, and dc utility bus No. 1 circuit breakers. The other section
contains battery bus circuit breakers (refer to Figures 9 and 10).
| - CBP-B is located on the forward bulkhead behind the copilot1s position and
divided into two sections. One section contains ac main bus No. 2, dc bus
No. 2, dc utility bus No. 2 and ac utility bus No. 2 circuit breakers. The
other section contains battery bus circuit breakers (refer to Figures 11
and 12).
I - CBP-C is located in the flight compartment on the pilot's left console and
contains the ac essential bus and ADG bus circuit breakers (refer to
Figure 13).
| - CBP-D is located in the flight compartment on the copilot's right console
and contains the dc essential bus circuit breakers (refer to Figure 14).
| The aft electrical distribution box is located in the battery compartment and
contains the battery direct bus circuit breakers (refer to Figure 15).
SECTION 7
Page 4
Oct 03/83
canadair
chaHencjer
OPERATING MANUAL
Electrical System - Basic Configuration
Figure 1 SECTION 7
Page 5
Apr 4/83
canadair
chanenqer
OPERATING MANUAL
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Electrical System Control Panels
Figure 2
SECTION 7
Page 6
May 28/82
canaetair
ctiaiiencjer
OPERATING MANUAL
ON
OFF/RESET
TEST
ON - OFF/RESET - TEST SWITCH
Three-position generator control switch with the following functions:
ON - supplies power to ac busses.
OFF - removes auxiliary power from the ac busses.
RESET - reselects generator after a fault.
TEST - checks voltage and frequency of the generator off -load.
MAIN
BUS 1
OFF
t> MAIN BUS 1 OFF LIGHT
Amber MAIN BUS 1 OFF light
comes on when main bus No.1 is not
connected to any generator.
AUTO OFF SWITCH /LIGHTS
When pressed, the automatic bus tie operation is disabled and
the associated amber AUTO OFF light comes on
FAIL LIGHTS
Associated amber FAIL light comes on if a bus tie overcurrent or
generator overcurrent condition exists.
MAIN BUS 2 OFF LIGHT
Amber MAIN BUS 2 OFF light
comes on when main bus No. 2 is not
connected to any generator.
Primary AC Control SECTION 7
Figure 3 Page 7
May 28/82
canadair
chaiiencjer
OPERATING MANUAL
APU KVA LOAD METER
Indicates kVA toad on the APU generator.
• ^
ON - OFF/RESET - TEST SWITCH
Three-position generator control switch with the
following functions:
ON — supplies power to ac busses.
OFF — removes auxiliary power from the ac busses.
RESET — reselects generator after a fault.
TEST — checks voltage and frequency of the
generator off-load.
BUS 1
ON
OFF/RESET
TEST
BUS 2
GEN LIGHT OFF
Amber GEN OFF light comes on when the generator
is off line for any of the following reasons:
— Generator frequency out of tolerance.
— Generator voltage out of tolerance.
— No output from the generator.
If APU is shut down, the APU GEN OFF light goes
out.
OVLD LIGHT
If the generator output current exceeds 100 A for
more than 2 seconds, the overload monitoring circuit
in the GCU operates and the amber OVLD light
comes on.
Auxiliary AC Control
Figure 4
SECTION 7
Page 8
May 28/82
canadair
chauencjer
OPERATING MANUAL
MAIN BUS 1 OFF LIGHT
Amber MAIN BUS 1 OFF light comes on if
power is lost from the main dc bus No. 1 due
to failure of TRU 1 or ac bus No. 1. Power is
supplied from main dc bus No. 2 when both
BUS TIE CLOSED switch/lights are pressed.
ESS BUS OFF LIGHT
Amber ESS BUS OFF light comes on if power
is lost from the dc essential bus due to the
failure of TRU 3 or ac essential bus. Power is
restored to the dc essential bus by pressing
either BUS TIE CLOSED switch/light or, in
emergency conditions, by deploying ADG.
MAIN BUS 2 OFF LIGHT
A/nb#* MAIN BUS 2 OFF light comes on "rf
is tost from the main dc bus No. 2 due
to tariure of TRU 2 or ac bus No. 2. Power is
from main dc bus No. 1 when both
BUS TIE CLOSED switch/lights are pressed.
BUS TIE CLOSED SWITCH/LIGHT
When pressed, dc bus No. 1 supplies the
battery bus and/or the dc essential bus. The
amber BUS TIE CLOSED light comes on and
the dc utility bus No. 1 is disconnected.
BUS Ti

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