Piper SENECA III - Page 390

SECTION
9
PIPER AIRCRAFT
CORPORATION
SUPPI
EMENT
21
PA-34-220T,
SENECA
IH
m.
Press
Pitch
Modifier
switch
DN
then UP
-
the
lIST
light
remains
ofT
as
long
as
the
switch
is held.
n
Momentarily
press
the TEST
switch
-
HDG
and
ATT
lights remain
on
and the TEST
light
turns
off.
(2)
COMMAND TRlM
SYSTEM
-
To be performed
before
the
first
flight
of
each
day.
a.
Using
the
control
wheel trim switch,
verify
normal
trim
up
and down
operation.
b.
Press
and
hold
the
center
bar
on
the
control
wheel trim
switch.
Observe
that the
trim
system
does
not operate.
c.
Release
the
center
bar
on
the
control
wheel
trim switch.
Move
the
control
wheel
trim switch
fore
and aft.
Observe
that
the
trim
system
does
not
operate.
This
completes
the
test
sequences.
CAUTIONS
Any
failure
of the above
procedures
indicates
that
a
failure
exists
in
the
system
and the
system
shan
not
be
operated until the
failure has been
located
and
corrected.
Check the
elevator
trim
position
before
takeoff.
(3)
COMPASS
SYSTEM (NSD 360A)
(For
other
compass
systems,
refer
to
appropriate
manu-
facturer's
instructions)
a..
Check
slaving.switch
in
SLAVE
or
No.
I
or
No,
2position,
as
appropriate.
(Slaving
systems
with
R.M.L
output
provides
only
slave and
free
gyro
positions
)
b.
Rotate
card
to
center
slaving
meter
-
check
HDG
(
Heading)
displayed
with
magnetic
compass
heading.
c.
Perform
standard
VOR
receiver
check.
(b)
1N-FLlGHT
PROCEDURE
-
AUTOPILOT
(1) Rotate
heading bug
to
desired
heading,
(2)
Trim
aircraft
for
existing
flight
condition
(all
axes),
Engage
autopilot.
(3)
During
maneuvering
flight
-
control
aircraft
through
use
of
the
heading
bug
and
the
pitch
modifier
(HDG-ATT
modes)
REPORT:
VB-IIIe
ISSUED: FEBRUARY 10, 1984
I
9-140,
6
of
20