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normal electrical power and ADG deployment.
When the ADG unit is fully extended, the two-blade propeller is unlocked and rotates
in the airstream. Once the ADG voltage and frequency are within normal limits, the
AUTO DEPLOY CONTROL Unit energizes the appropriate transfer contactors, and
allows the ADG to provide power to the AC ESS BUS and to hydraulic pump 3B via
the ADG BUS.
Airplanes 5301 to 5407
On airplanes 5301 to 5407, the ADG AUTO DEPLOY CONTROL Unit deploys the
ADG by sending an electrical signal to fire the squib cartridge in the ADG uplock
mechanism.
Airplane 5408 and Subsequent
On airplanes 5408 and subsequent, the ADG AUTO DEPLOY CONTROL Unit sends
a signal to release the solenoid of the ADG uplock mechanism.
ADG Manual Deploy Handle and ADG AUTO DEPLOY CONTROL Panel
Figure 7-13
ADG PWR TXFR
OVERRIDE
UNIT
ADG AUTO DEPLOY
CONTROL
LAMP
TEST
P604_07_041
ELECTRICAL
7-18 For Training Purposes Only
Jan 04
P I LOT T R A I N I N G GU I D E
PWR TXFR OVERRIDE
With the ADG deployed, it may be possible to restore normal AC electrical power by
resetting an engine-driven generator or by using the APU generator. If AC electrical
power is restored, the PWR TXFR OVERRIDE switch (see Figure 7-13) should be
selected to reset the three transfer contactors and regain normal AC distribution. This
returns the AC ESS BUS to AC BUS 1 and the 3B hydraulic pump to normal
operation.
The ADG Manual Deploy Handle must be stowed to allow the
transfer contactors to reset.
ADG LAMP / UNIT Switch
The ADG Auto Deploy Control Unit may be tested using the two-position ADG
LAMP / UNIT switch located on the ADG AUTO DEPLOY CONTROL Panel.
Selecting the switch to the UNIT position tests the continuity of the uplock circuit, the
three transfer contactors, and the ADG AUTO DEPLOY CONTROL Unit internal
logic circuitry. Both engine generators must be operating and AC BUS 1 and AC BUS
2 must be powered to ensure a proper test.
Selecting the switch to the LAMP position checks the serviceability of the green TEST
lamp only.
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.
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.
NOTE
NOTE
ELECTRICAL
For Training Purposes Only
May 03
7-19
P I LOT T R A I N I N G GU I D E
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.
ADG Operation
Figure 7-14
AC ELECTRICAL
UTIL BUS 1
BUS 2
GEN
2
GEN
1
APU
BUS 1
UTIL BUS 2
GEN
ESS BUS
P604_07_037
4
115
400
KVA
V
HZ
4
115
400
KVA
V
HZ
0
0
0
KVA
V
HZ
AC ELECTRICAL
UTIL BUS 1
BUS 2
GEN
2
GEN
1
APU
BUS 1
UTIL BUS 2
GEN
0
0
0
KVA
V
HZ
0
0
0
KVA
V
HZ
0
0
0
KVA
V
HZ
AC ELECTRICAL
UTIL BUS 1
BUS 2
GEN
2
GEN
1
APU
BUS 1
UTIL BUS 2
GEN
0
0
0
KVA
V
HZ
0
0
0
KVA
V
HZ
9
113
400
KVA
V
HZ
AUTO
XFER
FAIL
SHED SHED
ADG
ESS BUS
115
400
V
HZ
ADG 115
400
V
HZ
ESS BUS
AC ELECTRICAL
UTIL BUS 1
BUS 2
GEN
2
GEN
1
APU
BUS 1
UTIL BUS 2
GEN
0
0
0
KVA
V
HZ
0
0
0
KVA
V
HZ
10
113
400
KVA
V
　
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