Propeller Overspeed; Emergency Landing Gear Extension; Spin Recovery - Piper SARATOGA II HP PA-32R-301 Pilot Operating Handbook

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SECTION3
EMERGENCY PROCEDURES
PA-32R-301, SARATOGA ll HP
3.29 PROPELLER OVERSPEED
Propeller overspeed is caused by a malfunction in the propeller
governor or low oil pressure which allows the propeller blades to rotate to
full low pitch.
If
propeller overspeed should occur, retard the throttle and check the
oil pressure. The propeller control should be moved to full DECREASE
rpm and then set if any control is available. Airspeed should be reduced and
throttle used to maintain below 2700 RPM.
3.31 EMERGENCY LANDING GEAR EXTENSION
Prior to proceeding with an emergency gear extension, check to insure
that the battery master and alternator switches are ON and that the circuit
breakers have not opened. If it is daytime, the day/night dimmer switch should
be in the day position. Check the landing gear indicators for faulty bulbs by
depressing the annunciator press to test..
NOTE
Refer to Par. 4.39 for differences when
emergency extension procedure is performed for
training purposes.
If
the landing gear does not check down and locked, reduce the airspeed
to below 90 KIAS. Move the landing gear selector to the DOWN position. If
I
the landing gear still does not check down and locked, PULL the landing gear
pump circuit breaker and PULL the emergency extend knob while fish tailing
the airplane.
Under normal conditions, the above procedure, will require approximately 10
seconds for the gear to extend and lock down.
If
all electrical power has been lost, the landing gear must be extended
using the above procedure. The gear position indicator lights will not
illuminate.
3.33 SPIN RECOVERY
Intentional spins are prohibited in this airplane. If a spin is
inadvertently entered, immediately apply full rudder opposite to the
direction of rotation. Move the 2ontrol wheel full forward while neutralizing
the ailerons. Move the throttle to IDLE. When the rotation stops, neutralize
the rudder and ease back on the control wheel as required to smoothly
regain a level flight attitude.
REPORT: VB-1669
3-16
ISSUED:
JUNE
30, 1997
REVISED: JANUARY 9, 2001

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