SOLOY TURBINE PAC
SECTION 3
POHS CESSNA U/TU206G
EMERGENCY PROCEDURES
3-18
F.A.A. Approved
October 4, 2005
3. SIMULTANEOUSLY APPLY AND
HOLD
FULL RUDDER
OPPOSITE TO THE DIRECTION OF ROTATION AND MOVE
THE CONTROL WHEEL
BRISKLY
FORWARD FAR ENOUGH
TO BREAK THE STALL. Full down elevator may be required at
aft center of gravity loadings to assure optimum recoveries.
4. HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS.
Premature relaxation of the control inputs may extend the
recovery.
5. AS ROTATION STOPS, NEUTRALIZE RUDDER, AND MAKE A
SMOOTH RECOVERY FROM THE RESULTING DIVE.
NOTE
If disorientation precludes a visual determina-
tion of the direction of rotation, the symbolic
airplane in the turn coordinator or the needle of
the turn and bank indicator may be referred to
for this information.
ROUGH ENGINE OPERATION OR LOSS OF POWER
COMPRESSOR STALL
In the event of an engine compressor stall (noted by a bang or
popping noise and/or engine surging), slowly reduce power and, if it
continues, land as soon as practicable. If compressor stall is still
noted at flight idle power, shut down the engine and proceed with the
Engine Out landing procedure. If a flameout occurs, attempt one
restart to check for normal operation.
FUEL FILTER BYPASS
The fuel filter light on the instrument panel illuminates when the fuel filter
becomes clogged. Land as soon as practicable.
AUTO FEATHER SYSTEM FAILURE IN FLIGHT
In the event of a propeller auto feather system failure caused by a faulty
pressure switch or defective wiring (indicated by power surges, N
P
(Propeller) RPM oscillation and transmission pressure fluctuation) the
“AUTO
-FTHR ANN. LGHT” circuit breaker should be pulled to disable the
system. With this breaker pulled, the annunciator lights will be disabled
also. A landing should be made at the next suitable airport for repairs.
UNCONTROLLED
COPY
