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S Push the upper part of the hatch fully outward to squeeze the seal.
S Release the shootbolt latch lever under the handle
S Push the inner handle up and outward to fully engage the shootbolts.
S Close the inner handle cover
Vol. 1 06--70--8
DOORS
Emergency Exits Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Emergency Doors EICAS Indications <1001, 2224>
Figure 06---70---5
L (FWR or AFT) EMER DOOR or
R (FWR or AFT) EMER DOOR caution (amber)
Indicates that the respective overwing
emergency exit is unsafe.
Primary Page
Doors Page
Vol. 1 07--00--1
ELECTRICAL
Table of Contents REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
CHAPTER 7 --- ELECTRICAL
Page
TABLE OF CONTENTS 07--00--1
Table of Contents 7--00--1
INTRODUCTION 07--10--1
Introduction 7--10--1
AC ELECTRICAL SYSTEM 07--20--1
AC Electrical System 07--20--1
Integrated Drive Generator (IDG) 07--20--1
APU Generator 07--20--1
AC Distribution 07--20--1
AC Loads Distribution 07--20--10
Air Driven Generator (ADG) 07--20--10
Systems Circuit Breakers 07--20--12
DC ELECTRICAL SYSTEM 07--30--1
DC Electrical System 07--30--1
Transformer Rectifier Units (TRU) 07--30--1
Batteries 07--30--1
DC Distribution 07--30--1
DC Loads Distribution 07--30--9
Systems Circuit Breakers 07--30--11
CIRCUIT BREAKER PANELS 07--40--1
Circuit Breaker Panels 07--40--1
ATA Numbering and Circuit Breaker Location 07--40--4
LIST OF ILLUSTRATIONS
INTRODUCTION
Figure 07--10--1 Electrical System -- Introduction 07--10--2
AC ELECTRICAL SYSTEM
Figure 07--20--1 AC System Distribution 07--20--3
Figure 07--20--2 AC Electrical System 07--20--4
Figure 07--20--3 AC Electrical System Synoptic Page 07--20--5
Figure 07--20--4 AC Electrical System -- EICAS Indications (Generators) 07--20--8
Figure 07--20--5 AC Electrical System -- EICAS Indications (Busses) 07--20--9
Figure 07--20--6 Air Driven Generator (ADG) 07--20--11
Vol. 1 07--00--2
ELECTRICAL
Table of Contents REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
DC ELECTRICAL SYSTEM
Figure 07--30--1 DC Electrical System -- Schematic 07--30--3
Figure 07--30--2 Electrical Power Overhead Panel 07--30--4
Figure 07--30--3 DC Electrical Page Tru Voltage 07--30--5
Figure 07--30--4 DC Electrical Page Service Configuration 07--30--6
Figure 07--30--5 EICAS Primary Display
Auxiliary Power Unit/Main Battery Off 07--30--7
Figure 07--30--6 Transformer Rectifire Unit Fail -- Status Page 07--30--8
CIRCUIT BREAKER PANELS
Figure 07--40--1 Panel Overview 07--40--2
Figure 07--40--2 Circuit Breaker Panel 1 (Reference Only) 07--40--3
Vol. 1 07--10--1
ELECTRICAL
Introduction Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
1. INTRODUCTION
The aircraft AC electrical power is provided by two engine-driven generation systems. Each
system includes an integrated drive generator (IDG) and a generator control unit (GCU). An
auxiliary power unit (APU) generator is also available as a back AC power source to replace
either or both IDGs.
In the event of total AC power loss, emergency AC power is available from an in-flight
air-driven generator (ADG). The ADG assembly is stowed in a compartment on the right
side of the nose section.
DC power is supplied by four transformer rectifier units (TRU) which rectifies AC input power
into DC output power. An AC power center (ACPC) and two DC power centers (DCPCs) are
used for connecting AC and DC power to the appropriate buses, depending on system
configuration and health. The following is a list of all the aircraft electrical system buses:
AC BUSSES DC BUSSES
DC BUS 1
DC BUS 2
AC BUS 1 DC ESSENTIAL BUS
AC BUS 2 DC SERVICE BUS
AC ESSENTIAL BUS DC BATTERY BUS
AC SERVICE BUS DC EMERGENCY BUS
ADG BUS DC UTILITY BUS
MAIN BATTERY DIRECT BUS
APU BATTERY DIRECT BUS
A main battery and an APU battery, with battery chargers, are installed in the aircraft
electrical power system. Power for starting the APU is provided by the APU battery.
On the ground, the aircraft can receive external AC power through a receptacle located on
the forward right side of the fuselage.
The electrical power panel in the flight compartment, and the external service panel on the
right forward fuselage, contain the AC system control switches. The switches are used for
manual and automatic control of the electrical power generating system and external power
operation.
Electrical system warnings and cautions are displayed on the EICAS primary page. Status
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