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PIPER AIRCRAFT CORPORATION
SECTION 4
PA-28R-201T, CHEROKEE TURBO ARROW III
NORMAL PROCEDURES
4.43 STALLS
The
stall characteristics
of
the
Cherokee
Turbo
Arrow
III are conventional.
An
approaching
stall
is
indicated
by
a stall warning
horn
which
is
activated
between five
and
ten
knots above stall speed.
Mild
airframe
buffeting and
gentle pitching may also precede
the
stall.
The
gross weight stalling speed of
the
Cherokee Turbo Arrow
III with power off and
full flaps
is
56
KIAS. With
the
flaps
up
this
speed is
increased
7
KTS. Loss
of altitude
during
stalls can
be
as great as
500
feet, depending on
configuration
and power.
NOTE
The stall
warning
system
is inoperative
with
the
master
switch
"OFF."
During
preflight,
the
stall
warning system should
be
checked
by
turning the
master switch "ON,"
lifting
the
detector
and checking
to
determine if
the
horn is
actuated.
'lhe
master switch should be returned
to the
"OFF"
position after
the
check
is
complete.
4.45 TURBULENT AIR OPERATION
In
keeping with good operating practice used in all aircraft, it
is
recommended
that
when
turbulent
air
is
encountered
or expected,
the
airspeed
be
reduced
to
maneuvering
speed
to
reduce
the
structural
loads
caused by gusts and
to
allow
for inadvertent
speed
build-ups
which may occur as a
result
of
the turbulence
or of
distractions
caused
by
the
conditions.
4.47 LANDING GEAR
This
airplane
is equipped
with an airspeed
-
power
sensing
system
(back-up
gear extender)
which
extends
the
landing gear under low airspeed
-
power conditions*
even
though the
pilot may not have
selected gear
down. This
system will also prevent retraction
of
the
landing gear
by
normal means
when
the
airspeed
-
power
values
are
below
a predetermined
minimum.
To
override
this
system or
to
hold
the
emergency
gear lever in
the
"OVERRIDE ENGAGED"
position without
maintaining
manual pressure on
the
emergency gear lever, pull
the
lever
full
up and push
the
lock
pin
in.
To release
the
override, pull
lever
up and
then
release.
For
normal
operation,
the
pilot should extend and
retract
the
gear with
the
gear selector switch
located on
the
instrument
panel,
just
as he would
if
the
back-up gear extender system were not
installed.
The pilot should
become familiar
with
the
function
and significance
of
the
landing gear position
indicators and warning
lights.
The red gear warning
light
on
the
instrument
panel and
the
horn operate simultaneously
in flight
when
the throttle
is reduced
to
where
the
manifold pressure is approximately
14
inches
of mercury or
below,
and
the
gear selector switch is not in
the
"DOWN" position. This
warning
will
also occur
during flight
when
the
back-up
gear extended
system
has
lowered
the landing
gear and
the
gear selector switch is
not
in
the
"DOWN" position and
the
manifold pressure is
reduced
below approximately
14 inches of mercury.
ISSUED: DECEMBER
20,
1976
REPORT:
VB-800
4-19
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