12.5.4 Detailed Description
The Electrical Power Generation and Distribution System (EPGDS) (Figure 12.5-13) has an
Electrical Power Control Unit (EPCU) to control, monitor and distribute DC power to the
aeroplane’s electrical buses. The EPCU automatically re configures the EPGDS for power
source and bus failures, by the closing and opening of bus ties contactors. Contactor control is
determined by automatic functions during the operation of the aeroplane. Manual inputs are
achieved through the selection of switches in the flight deck that may be vetoed by the EPCU.
12.5.5 AC/DC Power Monitor System
System parameters are monitored in the flight deck on the Electronic System Indicating Displays
(ESID). Select the SYS (System) position on the appropriate Multi Function Display (MFD) rotary
switch on the ESID control panel to give electrical system indications.
12.5.6 DC System
The DC electrical schematic is shown in Figure 12.5-14.
The DC generation system has the following sources:
• Main, Auxiliary, and Standby Batteries
• Two Starter/Generators
• Two Transformer Rectifiers Units (TRU)
• DC External
• APU Starter/Generator (Optional)
The power sources supply power to the following buses in order of priority:
•Battery
• Left and Right Essential
• Left and Right Main
• Left and Right Secondary
DC Electrical Medical Outlet
A 24 VDC, 35 A electrical outlet for medical purposes is installed on the inboard face of the G1
galley.
Dash8 - Q400 - Electrical
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