Piper SENECA III - Page 205

PIPER
AIRCRAFT
CORPORATION
SECTION
7
PA-34-220T,
SENECA III
DESCRIPTION
&
OPERATION
An
optional
ground
clearance
energy saver
systern
ís
available
to
provide
direct
power
to
Comm
#f
without
turningon
the
master
switch.
An
internally
lit
pushbutton
switch,
located
on
the
instrument
panel,
provides
annunciation
for
engagement
of
t.he
system.
When the
button
is
engaged
direct
aircraft battery
power
is
applied
to
Comm
#1,
audio
amplifier
(speaker)
and
radio
accessories.
The
switch
must
be
turned
off
or
depletion
of
battery
could
result.
An
"Auxilary
Avionics Bus
Switch" is located
on
the
instrument
panel
to
the
right
of
the
copilot
control wheel
shaft.
The
switch
is provided
to
give
auxiliary
power
to
the
avionics
bus
in
the
event
of
a
radio
master
switch
circuit failure.
The
manifold
pressure
lines
have
drain
valves
located
behind
and below
the
dual
manifold
pressure
gauge
at
the
bottom
of
the
instrument panel.
This
allows
any
moisture
which
may
have
collected
from
condensation
to
be
pulled
into
the
engines.
This is
accomplished
by
depressing
the
two
valves
for
5
seconds
while
operating
the
engines
at
1000 RPM.
NOTE
Do
not
depress
the
valves
when
manifold
pressure
exceeds
25
inches
Hg.
ISSUED:
JANUÄRY
8,
1981
REPORT:
VB-1110
REVISEDF
AUGUST.9,
1982
7-27