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and advisory messages are displayed on the EICAS status page. General views of the
electrical systems are displayed on the EICAS, AC and DC synoptic pages. Access to the
AC and DC synoptic page is through the EICAS control panel (ECP). One push of the
ELEC key on the ECP will display the AC synoptic page. Pushing the ELEC key a second
time will display the DC synoptic page.
Vol. 1 07--10--2
ELECTRICAL
Introduction REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Electrical System --- Introduction
Figure 07---10---1
AC EXTERNAL
POWER ADG
CIRCUIT
BREAKER
PANELS
ACPC
DCPC
MAIN
BATTERY
APU GENERATOR
IDG 2
IDG 1
APU BATTERY
Vol. 1 07--10--3
ELECTRICAL
Introduction REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Electrical System --- Control Panels <1205>
Figure 07---10---2
Electrical Power Panel
Overhead Panel
A
External Service Panel
A B Right Forward Fuselage
B
Vol. 1 07--10--4
ELECTRICAL
Introduction REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 07--20--1
ELECTRICAL
AC Electrical System REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. AC ELECTRICAL SYSTEM
AC power for the aircraft electrical systems is provided by two engine-driven, integrated
drive generators (IDGs) which power all AC buses during normal operations. An APU
generator provides a backup AC power source, in flight, if an IDG is inoperative or when the
aircraft is on the ground with the engines off. If all AC power is lost in flight, emergency AC
power is provided automatically by a deployable air-driven generator (ADG). The AC
distribution system is controlled by the respective IDG and APU generator control units
(GCUs). Each generator is monitored by the GCUs for voltage, frequency and kilovolt amps
(kVA) for display on the EICAS and for system fault protective shutdowns.
A. Integrated Drive Generator (IDG)
Each IDG consists of a constant speed drive (CSD) and a generator. The CSD
hydro--mechanically, converts the variable input speed from the engine accessory
gearbox to a constant output speed to the generator to produce a constant frequency.
An oil cooler cools the oil used by the IDG.
Each IDG has a disconnect switchlight (on the electrical panel) to manually decouple
the IDG from the engine gearbox in the event of a CSD low oil pressure or high oil
temperature. The IDG will automatically disconnect if a severe over temperature or
overtorque condition occurs. Once disconnected, either manually or automatically, the
IDG cannot be reconnected in flight. It can only be reset on the ground, with the engine
shutdown.
Voltage and frequency regulation and fault protection is incorporated into each
generator control unit (GCU). The GCU also protects the electrical system from
overcurrent and differential current faults. In the event of a malfunction, the GCU will
automatically disconnect the faulty generator from the respective AC buses. The
generator may be reset when the malfunction is corrected or no longer exists, by
selecting the generator switch to the OFF/RESET position then back to ON.
B. APU Generator
The APU generator is driven, directly by the APU gearbox, at a constant speed to
maintain a constant frequency output. A GCU, identical to the IDG GCU, provides the
same regulation and protection functions as the IDG GCUs.
C. AC Distribution
AC power from IDG 1 and IDG 2 is distributed to the AC buses via GCU controlled
switches in the AC power center (ACPC). There is a priority control of AC power
distribution. During normal operations, IDG 1 powers AC bus 1 and IDG 2 powers AC
bus 2. Failure of an IDG generator, for any reason other than a fault on its associated
bus, will automatically transfer the load from the failed IDG to the remaining operative
IDG. The APU generator can then be used to replace the failed IDG to power the
respective AC bus.
Vol. 1 07--20--2
ELECTRICAL
AC Electrical System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
On the ground, if the aircraft is being powered with external AC power and either the
APU or an IDG is brought on line, the external power will be automatically disconnected
and the respective APU or IDG generator will power all the AC buses. When external
power is not available, the APU generator provides electrical power to the AC buses
and bleed air to start the aircraft engines. If an IDG is powering its respective AC bus
and the APU generator is powering the other AC bus, when the remaining IDG is
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