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Volume 2
07−10−36
RAT PILOT ACTIVATED TEST
The pilot activated test is initiated by the pilot during preflight
after AC power has been applied to the
airplane. It takes approximately 5 seconds to complete the test. The test is activated through the
EMS CDU on the ground only.
RAT TEST:
Press the RAT TEST activation button
to initiate test. Test duration is
approximately 5 seconds.
GF0710_052
TEST CONTROL 2/2
RAT TEST OFF
The pilot activated test checks the following:
· The RAT line contactor,
· the 147 KIAS discrete signal from the MADCs
· the RAT GCU,
· the RAT deploy handle status signal,
· AC bus 4 status signal,
· the RAT GEN push button annunciator status,
· the RAT generator heater.
A failed test results in a RAT GEN FAIL caution message being posted on the EICAS status page.
ELECTRICAL
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
07−10−37
EMERGENCY DC POWER
In the event of loss of all AC power , or the airplane speed is 147 knots or less with the RAT
deployed, a “BATTERY EMER PWR ON” EICAS message will be displayed. This message will be
displayed when the airplane is operating on emergency battery power only.
If the RAT is deployed and speed is less than 147 knots, it will automatically shed its electrical output
giving priority to hydraulics.
NOTE
Battery emergency power is available for a minimum of 15 minutes.
GF0710_053
AC BUS 1
V
KVA
GEN
1
GEN
2
AC BUS 2
V
KVA
GEN
3
AC BUS 3
V
KVA
V
KVA
GEN
4
AC BUS 4
AC ESS BUS
GEN
V
KVA
0
0
0 HZ
APU
AC ELECTRICAL
0
0
0
0
0
0
0
0
0
0
V
HZ
BATTERY EMER PWR ON
AC BUS 2
FEEDER
DC BUS 1
AC BUS 3
FEEDER
DC BUS 2
TRU 2
AC BUS 1
FEEDER
AC ESS
BUS
V
A
0
0
ESS
TRU 1
DC EMER
BUS
V
A
26
24
−10°C
AV
BATT
V
A
24
24
20 °C
APU
BATT
DC ELECTRICAL
V
A
0
0
ESS
TRU 2
V
A
0
0
TRU 1
V
A
0
0
BATT BUS
APU BATT
DIR BUS
AV BATT
DIR BUS
DC ESS
BUS
180
170
160
150
140
130
120
110
147
8
6
RAT GEN
ELECTRICAL
Flight Crew Operating Manual Rev 3, Apr 25, 2005
CSP 700−5000−6
Volume 2
07−10−38
DC POWER EMERGENCY OVERRIDE
In the event of loss of all DC power control (black cockpit), selecting the DC POWER EMERGENCY
OVERRIDE switch (located on the pedestal), to OVERRIDE, will allow ESS TRU1 and 2 to bypass
the DCPC and power the SPDAs directly. All components normally powered by tenable ESS TRU 1
and ESS TRU 2 to power the BATT BUS and DC ESS BUS SPDAs.
ELECT DC PWR EMER OVRD
Switch
Used in the event of a total loss of
DC power control, to connect ESS TRU 1
and ESS TRU 2 directly to the SPDAs to
power the components normally powered
the BATT BUS and DC ESS BUS are
powered directly by the ESS TRU 1
BUS are powered by TRUS and are
powering their respective SPDAs.
GF0710_054a
OVRD − SPDAs normally powered by
NORM − BATT BUS and DC ESS
by the BATT BUS and DC ESS BUS.
and ESS TRU 2.
ELECTRICAL
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
07−10−39
DC POWER EMERGENCY OVERRIDE (CONT'D)
Expected results when loss of DC
power control occurs. Results
may vary depending on degree of
failure.
NOTE
Expected flow lines while
performing the DC Override Test.
GF0710_055
AC BUS 2
FEEDER
DC BUS 1
AC BUS 3
FEEDER
DC BUS 2
TRU 2
AC BUS 1
FEEDER
AC ESS
BUS
V
A
0
0
ESS
TRU 1
DC EMER
BUS
V
A
26
24
−10°C
AV
BATT
V
A
24
24
20 °C
APU
BATT
DC ELECTRICAL
V
A
0
0
ESS
TRU 2
V
A
0
0
TRU 1
V
A
0
0
　
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