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AC Utility Buses
AC UTILITY BUS 1 and 2 receive power from AC BUS 1 and 2 respectively. The AC
utility buses supply AC power to nonessential cabin equipment.
Utility Bus Shedding
During single-generator operation in flight, AC UTILITY BUS 1 and 2 are
automatically load shed to reduce the electrical load on the remaining generator.
During ground operations, AC UTILITY BUS 1 and 2 are load shed when a single
generator (or external AC power only) is supplying AC power and the flaps are not
retracted.
Load shedding of AC UTILITY BUS 1 and 2 is indicated by the appearance of AC
UTIL 1(2) OFF status EICAS messages and the SHED icons on the AC Electrical
Synoptic page (see Figure 7-11).
AC Utility Bus Shedding
Figure 7-11
P604_07_036
AC ELECTRICAL
UTIL BUS 1
BUS 2
GEN
2
GEN
1
APU
BUS 1
UTIL BUS 2
GEN
ESS BUS
0
0
0
KVA
V
HZ
0
0
0
KVA
V
HZ
7
113
401
KVA
V
HZ
AUTO
XFER
FAIL
SHED SHED
AC UTIL 2 OFF
AC UTIL 1 OFF
EICAS SECONDARY
DISPLAY
ELECTRICAL
For Training Purposes Only
Jan 04
7-15
P I LOT T R A I N I N G GU I D E
Air-Driven Generator (ADG)
Description
The ADG provides 115-volt, 400-Hz, 15-kVA power to the AC ESS BUS and 3B
hydraulic pump, in the event of a complete loss of AC power in flight. The ADG is
located in the forward right fuselage beside the nose gear and is deployed
automatically or manually. Once deployed, the ADG can only be restowed when the
aircraft is on the ground (see Figure 7-12).
Air-Driven Generator (Wet ADG Shown)
Figure 7-12
ADG Ground
Safety Lockpin
UPLOCK ASSEMBLY
Auto Release
( Squib Cartridge
Solenoid)
Wet ADG - /
Dry ADG -
P604_07_003
Manual
Release
Ejection
Jack
Assembly
Manual
Restowable
Pump Assembly
Air-Driven
Generator
Assembly
Ejection
Jack
Assembly
Manual
Retraction
Pump
Assembly
AIR - DRIVEN DRY GENERATOR
(Aircraft 5408 and subsequent)
AIR - DRIVEN WET GENERATOR
(Aircraft 5301 to 5407)
Air-Driven
Generator
Assembly
ELECTRICAL
7-16 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Components and Operation
Air-Driven Generator
The ADG consists of an AC generator mounted on a pivoted support leg and a
variable-pitch two-bladed propeller that turns in the airstream. There are two versions
of the ADG.
Airplanes 5301 to 5407
On airplanes 5301 to 5407, constant speed of the generator is achieved by
hydraulically controlling the propeller pitch angle. This ADG is commonly referred to
as the “wet ADG”. Wet ADG operation is airspeed-limited (refer to the Airplane
Flight Manual Limitations).
On landing with the wet ADG deployed, use gentle deceleration
to prevent the ADG from swinging forward and contacting the
fuselage.
Airplane 5408 and Subsequent
On airplanes 5408 and subsequent, the constant speed of the ADG is achieved by
using a counterweight system to control the propeller pitch angle. This ADG is
commonly referred to as the “dry ADG”.
ADG Generator Control Unit
The ADG generator is controlled and monitored by the ADG generator control unit
(GCU). The ADG GCU provides the following functions:
• monitors and controls ADG voltage output
• protects against overvoltage, overfrequency and underfrequency to the ADG BUS
• provides a signal to the ADG Auto Deploy Control Unit to energize the HYD
PUMP 3B Transfer Contactor, Emergency AC Transfer Contactor, and Emergency
DC Transfer Contactor when the ADG voltage and frequency are within limits
NOTE
ELECTRICAL
For Training Purposes Only
May 03
7-17
P I LOT T R A I N I N G GU I D E
ADG AUTO DEPLOY CONTROL Unit
Located on the lower center pedestal, the ADG AUTO DEPLOY CONTROL Unit
controls the automatic deployment of the ADG.
Automatic deployment of the ADG occurs when:
• both AC BUS 1 and AC BUS 2 become unpowered
• the aircraft is in flight
Another ADG deployment prerequisite is that one of the three main generators must
be on line prior to both AC main buses going off (this prevents the ADG from
deploying during ground maintenance tests with external power being connected and
disconnected with the aircraft on jacks.
The red EMER PWR ONLY warning EICAS message appears to indicate loss of all
　
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