DESCRIPTION
General 07−10−1
EPGDS Components 07−10−2
EPGDS Architecture 07−10−3
AC System 07−10−4
AC System Distribution 07−10−7
Electrical Panel 07−10−8
Electrical Management System 07−10−9
AC System EICAS Messages 07−10−13
AC System Synoptic 07−10−15
AC BUS Feed System 07−10−16
EXT AC Power 07−10−22
DC System 07−10−23
DC System Distribution 07−10−24
Electrical Panel 07−10−25
DC System EICAS Messages 07−10−26
DC System Synoptic 07−10−28
DC BUS Feed System 07−10−29
External DC Power 07−10−34
RAT GEN FEED 07−10−35
RAT Pilot Activated Test 07−10−37
Emergency DC Power 07−10−38
DC Power Emergency Override 07−10−39
EICAS Philosophy 07−10−41
EMS CIRCUIT PROTECTION
Cockpit Circuit Breaker Panel (CCBP) 07−20−1
EMS CDU 07−20−2
System Key 07−20−2
Next Page Key 07−20−2
Previous Page Key 07−20−2
Elec System Key 07−20−3
ELECTRICAL
TABLE OF CONTENTS
CHAPTER 7
07−00−1
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
07−00−1
Page
TABLE OF CONTENTS
EMS CIRCUIT PROTECTION
Bus Key 07−20−4
AC BUS 1 07−20−4
AC BUS 2 07−20−5
AC BUS 3 07−20−6
AC BUS 4 07−20−7
AC ESS BUS 07−20−8
DC EMER BUS 07−20−9
DC BUS 1 07−20−10
DC BUS 2 07−20−17
DC ESS BUS 07−20−24
BATT BUS 07−20−30
AV BATT BUS 07−20−37
APU BATT BUS 07−20−38
CNTL Key 07−20−39
Test Key 07−20−40
FIRE TEST 07−20−41
STALL TEST 07−20−42
AURAL WARNING TEST 07−20−43
LAMP TEST 07−20−44
RAT TEST 07−20−45
EMER CONT 07−20−46
ELECTRICAL
TABLE OF CONTENTS
Flight Crew Operating Manual Rev 3, Apr 25, 2005
CSP 700−5000−6
Volume 2
07−00−2
Page
GENERAL
The airplane electrical power generation and distribution system (EPGDS) consist of four 40 KVA,
enginedriven
variable frequency generators (VFG) and one constant frequency 40/45 KVA APU
generator. Control and protection of the generators are provided by five identical generator control
units (GCU). Distribution systems furnish power to the following busses through the AC power center
(ACPC) and the cockpit circuit breaker panel (CCBP).
· AC bus 1, 2, 3 and 4 (ACPC).
· AC bus 1A, 2A, 3A, essential bus (CCBP).
A ram air turbine (RAT) deployable during flight, supplies 115−volt, 400−Hz, 3−phase AC power
9 KVA for emergency use (when all other AC sources have been lost) to supply AC power to the AC
essential bus. Mounted on the RAT is a hydraulic pump which powers hydraulic system #3.
For other load devices requiring DC power, 115–volt AC power is converted to 28–volt DC power by
four 150 Amp transformerrectifier
units (TRU). 28–volt DC power is distributed through the DC
power center (DCPC) and the secondary power distribution assemblies (SPDA) on the following
busses:
· DC bus 1 and 2
· DC essential bus
· Battery bus
· DC Emergency bus
The 25–ampere hour, 24–volt DC avionics battery provides power to the following:
· Stored energy to selected electronic equipment during normal ground operations.
· During flight in an emergency (loss of all generators) to the flight essential DC loads.
The 42 ampere hour, 25.2 volt DC APU battery provides power to the following:
· Stored energy for starting the APU during both ground and flight operations.
· During flight in an emergency (loss of all generators) to the flight essential DC loads.
The following busses are connected directly to the battery terminals:
· Avionics battery direct bus
· APU battery direct bus
Battery chargers and battery heaters, powered by the main AC buses, maintain the main and APU
batteries in a charged and warm condition.
An Electrical Control Panel, located in the cockpit, provides control of all generators, external AC and
DC power and battery master.
An Electrical Management System (EMS), located in the cockpit, controls and displays the status of
　
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