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HZ
AUTO
XFER
FAIL
SHED SHED
ADG 115
400
V
HZ
ESS BUS
1. NORMAL OPERATION 2. EMER PWR ONLY – ADG DEPLOYED
3. APU GEN SELECTED ON 4. PWR TXFR OVERRIDE PRESSED
ELECTRICAL
7-20 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
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 inflight
and allow the APU to be started on the ground.
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 7-15
APU
BATT
EXT
DC
TRU 1 TRU 2 ESS TRU 2 ESS TRU 1
APU
BATT
CHGR
FROM
ADG
DC TIE
RELAY 1
DC TIE
RELAY 2
DC ESS
SOLID-STATE
CONTACTOR
APU BATT
SOLID-STATE
CONTACTOR
EXTERNAL
DC
CONTACTOR
EMERGENCY
DC TX
CONTACTOR
MAIN
BATT
MAIN BATT
SOLID STATE
CONTACTOR
MAIN
BATT
CHGR
P604_07_005
NOTE: This schematic only displays DC power sources.
Disregard the positions of all contactors and ties.
DC UTILITY
BUS 2
DC UTILITY
BUS 1
DC BUS 1
DC BUS 2
DC
ESS BUS
BATT BUS
EMERGENCY
BUS
APU BATT
DIR BUS
MAIN BATT
DIR BUS
AC BUS 1 AC BUS 2
AC
ESS BUS
ELECTRICAL
For Training Purposes Only
May 03
7-21
P I LOT T R A I N I N G GU I D E
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
• MAIN BATTERY DIRECT BUS
• APU BATTERY DIRECT BUS
EICAS DC Electrical Synoptic Page
Figure 7-16
P604_07_038
DC ELECTRICAL
TRU 1
BUS 1
BUS 2
UTIL BUS 1
UTIL BUS 2
EMER BUS
APU BATT
DIR BUS
MAIN BATT
DIR BUS
AC BUS 1 AC BUS 2 AC ESS BUS
TIE
ESS BUS
BATT BUS
28 V
8 A
TRU 2
28 V
13 A
ESS
TRU 2
28 V
24 A
ESS
TRU 1
28 V
24 A
MAIN
BATT
26 V
0 A
APU
BATT
27 V
0 A
EXT
DC
28 V
19 A
DC BUS 1
DC BUS 2
DC UTIL (Utility) BUS 1
DC UTIL (Utility) BUS 2
DC ESS (Essential) BUS
BATT (Battery) BUS
APU BATTERY
DIRECT BUS
MAIN BATTERY
DIRECT BUS
DC EMER (Emergency) BUS
ELECTRICAL
7-22 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
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
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 (see Figure 7-17).
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 the DC ESS BUS.
　
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