Piper ARCHER II - Pitot-Static System

SECTION
7
PIPER
AIRCRAFT
CORPORATION
DESCRIPTION
&
OPERATION
PA-28-181,
ARCHER
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
lines
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
lines
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
pitot
head
is
located
on
the
electrical
switch
panel
to
the
left
of
the
right
contro!
wheel.
To
prevent
bugs
and
water
from
entering
the
pitot
and
static
pressure
holes,
a
cover
should
be
placed
over
the
pitot
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-1120
ISSUED:
JULY
2,
1979
7-16