SECTION
3
CESSNA
EMERGENCY PROCEDURES MODEL
2088
(675
SHP)
ELECTRICAL POWER SUPPLY SYSTEM
MALFUNCTIONS
(Continued)
LOSS OF ELECTRICAL POWER
The design of the electrical power system, due to the self-exciting
feature of the generator and the multiple protected busing system,
minimizes the possibility of a complete electrical power loss. However,
a fault to ground (airframe) on the generator or battery cables can be
identified by one or more of the following: illumination of the
GENERATOR OFF annunciator, sudden dimming of lights, contactor
chattering, circuit breaker tripping, or arcing noises. The voltlammeter
provides further information concerning the location of the fault, or the
system affected by the fault. In the event of the above indication, the
portion of the system containing the fault should be isolated. The
battery should be disconnected first by turning the battery switch to the
OFF position. Then, following the checklist procedures for Generator
Failure should result in restoration of electrical power to the distribution
buses. The voltlammeter should be monitored to assure that ground
fault currents have been shut off and the capacity of the remaining
power
source(s) is not exceeded.
PARTIAL AVIONICS POWER FAILURE
Avionics power is supplied to the 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 feeder cable failure, both
avionics buses can be connected to the remaining feeder by closing the
guarded avionics bus tie switch. If a ground fault has occurred on one
feeder, it will be necessary to verify the avionics power
switchlbreaker
associated with the affected feeder is off 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.
Nonessential avionics equipment should be turned off.
(Continued Next Page)
1
3-42 U.S.
Revision 23
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