CESSNA
MODEL 172N
SECTION 3
EMERGENCY PROCEDURES
NOTE
In an emergency on airplanes not equipped with an
alternate static source, cabin pressure can be supplied to
the static pressure instruments by breaking the glass in
the face of the rate-of-climb indicator.
With the alternate static source on, adjust indicated airspeed slightly
during climb or approach according to the alternate static source airspeed
calibration table in Section
5,
appropriate to vent/window(s) configura
tion, causing the airplane to be flown at the normal operating speeds.
Maximum airspeed and altimeter variation from normal is
4
knots and
30 feet over the normal operating range with the window(s) closed. With
window(s) open, larger variations occur near stall speed. However,
maximum altimeter variation remains within
50
feet of normal.
SPINS
Should an inadvertent spin occur, the following recovery procedure
should be used:
1.
RETARD THROTTLE TO IDLE POSITION.
2.
PLACE AILERONS IN NEUTRAL POSITION.
3.
APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIREC
TION OF ROTATION.
4.
JUST AFTER THE RUDDER REACHES THE STOP, 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.
5.
HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS.
Premature relaxation of the control inputs may extend the recov
ery.
6.
AS ROTATION STOPS, NEUTRALIZE RUDDER, AND MAKE A
SMOOTH RECOVERY FROM THE RESULTING DIVE.
NOTE
If disorientation precludes a visual determination of the
direction of rotation, the symbolic airplane in the turn
coordinator may be referred to for this information.
For additional information on spins and spin recovery, see the discus
sion under SPINS in Normal Procedures (Section 4).
1
July 1979
3-15