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ensure a proper test.
Selecting the switch to the LAMP position checks the serviceability of the green TEST lamp
only.
ELECTRICAL
Description
Vol. 2 07−10−17
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AIR-DRIVEN GENERATOR (ADG) (CONT'D)
ADG Manual Deploy Handle
In the event of an auto-deploy failure, the ADG can be manually deployed using the ADG
manual deploy handle located on the lower center pedestal. Pulling the handle manually
releases the uplock that allows the ADG to deploy. In addition, the emergency AC transfer
contactor and emergency DC transfer contactor are energized immediately.
In the event the ADG fails, operating the ADG manual deploy handle enables the DC ESS BUS
to be supplied by the BATT BUS through the emergency DC transfer contactor.
NOTE
If the ADG is not operating properly and the airplane is on battery
power only, then all electrical power may be lost after 30 minutes.
Hydraulic pump 3B will be inoperative when on battery power.
Manual deployment of the ADG handle is also required for landing when the ADG is the only
source of AC electrical power. This ensures that the DC ESS BUS remains powered by the
BATT BUS throughout the landing rollout, when the ADG is no longer capable of generating AC
power.
ELECTRICAL
Description
Vol. 2 07−10−18
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AIR-DRIVEN GENERATOR (ADG) (CONT'D)
ADG Operation
Figure 07−10−14
DC ELECTRICAL POWER SYSTEM
Description
Four transformer-rectifier units (TRUs), two NiCad batteries and an external DC power receptacle
supply direct current (DC) power to the DC buses. The TRUs carry the majority of the DC electrical
loads, and the batteries provide emergency power in-flight and allow the APU to be started on the
ground.
ELECTRICAL
Description
Vol. 2 07−10−19
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
DC ELECTRICAL POWER SYSTEM (CONT'D)
DC power is distributed to the DC buses directly from the TRUs or batteries, and from various
contactors which provide alternate sources of power.
Electrical power is supplied to the buses through the circuit breaker panels.
DC System Schematic
Figure 07−10−15
Monitoring of system status is done using the EICAS DC electrical synoptic page. The aircraft DC
bus system consists of the following nine buses:
• DC BUS 1
• DC BUS 2
• DC ESS (Essential) BUS
• DC EMER (Emergency) BUS
• BATT (Battery) BUS
• DC UTIL (Utility) BUS 1
• DC UTIL (Utility) BUS 2
ELECTRICAL
Description
Vol. 2 07−10−20
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
DC ELECTRICAL POWER SYSTEM (CONT'D)
• MAIN BATTERY DIRECT BUS
• APU BATTERY DIRECT BUS
EICAS DC Electrical Synoptic Page
Figure 07−10−16
Components and Operation
Transformer-Rectifier Units (TRUs)
The normal sources of 28-volt DC electrical power for the DC system are the four TRUs. Each
TRU converts 115-volt AC to 28-volt DC and supplies it to its respective DC buses. Each TRU is
rated at 100 amps.
The four TRUs are identified as:
• TRU 1
• TRU 2
• ESS (Essential) TRU 1
• ESS (Essential) TRU 2
The TRUs supply the following buses:
• TRU 1 normally supplies DC BUS 1 and DC UTIL BUS 1
• TRU 2 normally supplies DC BUS 2 and DC UTIL BUS 2
• ESS TRU 1 normally supplies DC ESS BUS and DC BATT BUS
• ESS TRU 2 normally supplies DC ESS BUS and DC BATT BUS
ELECTRICAL
Description
Vol. 2 07−10−21
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
DC ELECTRICAL POWER SYSTEM (CONT'D)
TRU Power Distribution System
The TRU power distribution system supplies the following buses:
DC BUS 1 and DC BUS 2
DC BUS 1 is supplied by TRU 1 and DC BUS 2 is supplied by TRU 2. If either TRU fails, both
buses can be supplied by either TRU by selecting the MAIN BUS TIE switch/light on the
ELECTRICAL POWER panel.
DC ESS BUS
The DC ESS BUS powers equipment essential for safe flight and, therefore, may be supplied
by numerous DC sources to ensure redundancy of its power supply. Normally, ESS TRU 1 and
ESS TRU 2 power the DC ESS BUS. In the event of a single ESS TRU failure, either ESS
TRU is capable of sustaining the DC ESS BUS load. Should both ESS TRUs fail with the
aircraft in flight, the APU BATT DIR BUS, through the DC ESS solid-state contactor, will power
　
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