Beechcraft C-12C Operator And Technical Reference Manual page 902

TM 1-1510-218-10
2. BATT switch – OFF (monitor loadmeter).
IF LOADMETER STILL INDICATES ABOVE 100%:
3. Nonessential electrical equipment – off.
IF LOADMETER INDICATES 100% OR BELOW:
4. BATT switch – ON.
d. INVERTER Light Illuminated. Illumination of
the #1 or #2 INVERTER caution light indicates failure
of the affected inverter. When either inverter fails, the
total ac load is automatically switched to the remaining
inverter. When a #1 or #2 INVERTER light illuminates,
perform the following:
1. Affected INVERTER switch – OFF.
e. INST AC Light Illuminated. Illumination of
the INST AC warning light indicates that both 26-Vac
transformer circuits are inoperative.
power-indicating instruments, torque, and fuel flow will
be inoperative. Under these conditions, power must
be controlled by indications of the N
Perform the following:
1. N and TGT indications – Check.
1
2. Other engine instruments – Monitor.
f. Circuit Breaker Tripped.
breaker is for a nonessential item, do not reset in flight.
If the circuit breaker is for an essential item, the circuit
breaker may be reset once. If a bus feeder circuit
breaker (on the overhead circuit breaker panel) trips, a
short is indicated. Do not reset in flight. If a circuit
breaker trips, perform the following:
1. BUS FEEDER breaker tripped – Do not
reset.
2. Nonessential circuit – Do not reset.
3. Essential circuit – Reset once.
NOTE
Circuit breakers should not be reset more
than once until the cause of circuit
malfunction has been determined and
corrected. Do not reset dual-fed bus
feeder circuit breakers.
g. BATTERY CHARGE Light Illuminated.
the BATTERY CHARGE caution light illuminates
during normal flight, perform the following procedure.
9-12
The primary
Failure. If the AVIONICS MASTER POWER switch
fails to operate in the
following procedure.
and TGT gauges.
1
If the circuit
9-29. EMERGENCY DESCENT.
damage to the aircraft must be considered secondary
to getting the aircraft down. The following procedure
assumes the structural integrity of the aircraft and
smooth flight conditions.
doubt, limit speed as much as possible, reduce rate of
descent if necessary, and avoid high maneuvering
loads. For emergency descent, perform the following:
If
1. Loadmeter – Check and note indication.
2. BATT switch – OFF.
3. Loadmeter – Check.
indicates less than 2.5% change (one
needle width), turn BATT switch ON and
monitor for increasing load.
continues to increase, turn BATT switch
OFF.
NOTE
The battery may be turned back ON only
for gear and flap extension and approach
to landing. Battery may be usable after a
15 to 20-minute cool down period.
4. BATT switch (landing gear/flap extension
only) – ON.
h. AVIONICS MASTER
ON
NOTE
The avionics power relay is normally hot.
Pulling the AVIONICS MASTER CONTR
circuit breaker will remove power to the
relay, thus allowing electrical power to the
associated buses.
1. AVIONICS MASTER
breaker – Pull.
Emergency descent is a maximum effort in which
If structural integrity is in
1. POWER levers – IDLE.
2. PROP levers – HIGH RPM.
3. FLAPS – APPROACH.
4. GEAR – DN.
5. Airspeed – 181 KIAS maximum.
If loadmeter
If load
POWER Switch
position, perform the
CONTR circuit