Piper Malibu PA-46-310P Pilot Operating Handbook page 451

SECTION9
SUPPLEMENT 10
PIPER AIRCRAFT CORPORATION
PA-46-310P, MALIBU
SECTION 7 - DESCRIPTION AND OPERATION OF THE ICE
PROTECTION SYSTEM AND EQUIPMENT
For flight into known icing conditions (FIKI), a complete ice protection
system is required on the Malibu.
The complete ice protection system consists of the following com-
ponents: Pneumatic wing and empennage boots, wing ice detection light,
electrothermal propeller deice pads. electrothermal windshield panel, heated
lift detector(s), heated pitot head, dual alternators, dual vacuum pumps and
the alternate static source. Alternator and vacuum pump controls are
located on the main switch panel on the left side of the instrument panel.
Controls for the ice protection components are located to the right of the
control quadrant on the deice switch panel (Figure 7-1 ).
A single component or a combination of components may be installed.
However, the warning placard specified in Section 2 of this supplement is
required when the complete system is not installed. Such a placard is also
required if any component is inoperative.
The aircraft is designed to allow operation in the meteorological con-
ditions of the FAR 25 envelopes for continuous maximum and intermittent
maximum icing.
The airplane is not designed to operate for an indefinite
period of time in every icing condition encountered in nature.
Activation
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of the ice protection system prior to entering icing conditions and attempting
to minimize the length of the icing encounter will contribute significantly to
the ice flying capabilities of the airplane.
WING AND EMPENNAGE BOOTS
Pneumatic deice boots are installed on the leading edges of the wing,
the vertical stabilizer and the horizontal stabilizer. During normal operation,
when the surface deice system is turned off, the engine driven vacuum pump
applies a constant suction to the boots to provide smooth, streamlined
leading edges. The boots are inflated by a momentary ON type SURF
DEICE switch (Figure 7-1) located on the deice switch panel. Actuation of
the SURF DEICE switch activates a pressure regulator valve which energizes
three (tail, lower wing & upper wing) deice flow valves for approximately six
seconds. The boot solenoid valves are activated and air pressure is released
to the boots, sequentially inflating the surface deicers. A SURFACE DEICE
indicator light, located on the annunciator panel illuminates when the boots
inflate. When the cycle is complete, the deicer solenoid valves permit auto-
matic overboard exhaustion of pressurized air. Suction is then reapplied to
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the boots.
REPORT: VB-1200
9-96, 10 of 16
ISSUED: JULY 30, 1984
REVISED: OCTOBER 15, 1997