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APPRENDIX D: ELECTRICAL LOAD EFFECTS
Electrical Load Effects
The aircraft electrical load analysis must be checked to ensure the aircraft electrical system
is able to operate safely with the newly installed OASIS sytem. The electrical load analysis
must be checked for two conditions- the total aircraft load is less than the current
generating capability of the aircraft electrical source equipment (battery, generator,
alternator, etc.) and, the load on the bus used to power the OASIS is less than the
maximum load approved for that bus. These maximum load capabilities are provided in the
aircraft maintenance manuals.
Please note that the ASU provides the power for the DU and the MSU.
Update the aircraft electrical load analysis using the electrical load effects shown in Table
ITEM
MANUFACTURE
1
Aerosonic
2
Aerosonic
DESCRIPTION
PART NO.
DU
SLZ7365
ASU
SLZ7366
POWER REQUIRMENTS
28.0 Vdc
3.7 W Max
28.0 Vdc
17 W (1 DU, 1 MSU)
X W (2 DU, 1 MSU)
OASIS Installation Manual
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