SECTION 7 PIPER AIRCRAFT CORPORATION
DESCRIPTION
& OPERATION PA-28-161, WARRIOR
II
7.21 PITOT-STATIC SYSTEM
The
system supplies both pitot and static pressure for the airspeed
indicator, altimeter,
and
the optional vertical speed indicator (Figure
7~17).
Pitot
and static pressure are picked up
by
a pitot head installed on the
bottom
of
the left wing and carried through pitot and static
Jines
within the
wing
and
fuselage to the gauges on the instrument panel.
An
alternate static source
is
available
as
optional equipment. The
control
valve
is
located below the left side of the instrument panel. When the
valve is set in the alternate position, the altimeter, vertical speed indicator
and
airspeed indicator will be using cabin air for static pressure. The storm
window and cabin vents must be closed and the cabin heater and defroster
must
be
on
during alternate static source operation. The altimeter error
is
less
than
50 feet unless otherwise placarded.
Both the pitot and static
Jines
can
be
drained through separate drain
valves located on the left lower side of the fuselage interior.
A heated pitot head, which alleviates problems with icing and heavy
rain, is available
as
optional equipment. The switch for the heated
pi
tot head
is located on the electrical switch panel to the left of the right control wheel.
To
prevent bugs and water from entering the pitot and static pressure
holes, a cover should be placed over the pi tot head. A partially or completely
blocked pitot head will give erratic or zero readings on the instruments.
NOTE
During the preflight, check
to
make sure the
pitot cover
is
removed.
REPORT:
VB-1180
7-18
ISSUED:
AUGUST
13,
1982
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