Partial Avionics Power Failure - Textron Cessna Grand Caravan Ex 208B Pilot's Operating Handbook And Faa Approved Airplane Flight Manual

CESSNA
MODEL 208B 867 SHP
GARMIN G1000
ELECTRICAL
MALFUNCTIONS

PARTIAL AVIONICS POWER FAILURE

Avionics power is supplied to No. 1 and No. 2 avionics buses from the
power distribution bus in the engine compartment through separate
protected feeder cables. In the event of a single feeder cable failure,
both avionics buses can be connected to the remaining feeder by
setting the AVIONICS BUS TIE switch to the ON position. If a ground
fault has occurred on one feeder, it will be necessary to verify the
AVIONICS No.1 or No. 2 switch, associated with the faulted feeder, is in
the OFF position before the AVIONICS BUS TIE switch will restore
power to both avionics buses. The maximum avionics load with one
feeder should be limited to 30 amperes, the maximum crosstie load is
limited to 20 amps. All nonessential avionics equipment should be
turned off.
FAA APPROVED
208BPHCUS-00
EMERGENCY PROCEDURES
POWER
(Continued)
SECTION 3
SUPPLY SYSTEM
U.S.
3-57