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PIPER
AIRCRAFT CORPORATION
SECTION
7
PA-28R-201T,
CHEROKEE
TURBO
ARROW IH
DESCRIPTION
AND
OPERATION
WARNING
Avoid
ejecting
objects out of
the
pilot storm window which could
possibly enter or obstruct
the
holes in
the
mast.
The
emergency
gear lever, used for emergency
extension
of
the
gear, manually
releases hydraulic
pressure
to
permit
the
gear
to
free-fall with spring assistance on
the
nose gear. The lever must be
held
in
the
downward
position
for emergency extension.
This same lever, when placed in
the
raised position,
can be
used
to
override
the
system,
and gear position is
then
controlled
by
the
selector switch regardless of
airspeed/power
combinations.
The emergency
gear lever is provided
with
a locking
device
which may
be
used
to
lock
the
override lever in
the
up position.
The lock
is
located
on
the
right side panel of
the
console
below
the
level
of
the
manual
override
lever.
To lock
the
override lever
in
the
up
position, raise
the
override
lever
to the
full up position and push
the
pin in.
A
yellow warning
light located below
the
gear selector
switch
(Figure 7-3) flashes
to
warn
the
pilot
that the
automatic gear
lowering
system
is disabled.
The
lock is
spring-loaded
to the
off position
to
aid
disengagement.
To
disengage
the
lock
raise
the
override
lever
and
release.
The lever
will return
to
its
normal position and
the
yellow flashing
light
will extinguish.
The lever
must
also be locked
in
the
raised
(up)
position when gear-up stalls are practiced.
Gear
down
and locked positions are
indicated
by
three
green lights located
below
the
selector, and a
red
"Warning
Gear
Unsafe"
light is
located
at
the top
of
the
panel.
An
all
lights
out condition
indicates
the
gear is up. The landing gear should not
be
retracted above a speed of 107
KIAS
and should not
be
extended
above a speed of 129
KIAS.
The
main
landing
gear uses
6.00
x
6
wheels.
The
main gear
incorporate brake drums
and
Cleveland
single
disc
hydraulic
brake
assemblies.
The
nose
wheel
carries a 5.00 x 5 four ply
tire
and
the
main gear use
6.00
x
6
six ply
tires.
All
three tires
are
tube type.
A
micro-switch
in
the
throttle
quadrant activates a warning horn and red "Warning Gear
Unsafe"
light
under
the
following conditions:
(a)
Gear up and power reduced
below
approximately
14 inches of manifold pressure.
(b)
Gear extended
by
back-up
gear extender system but gear selector switch "UP," power reduced
below
approximately
14 inches of manifold pressure.
(c)
Gear selector switch "UP" while on
the
ground and
throttle
in retarded position.
The gear warning horn emits a 90 cycle per minute beeping sound in contrast
to
the
stall warning horn
which
emits a continuous
sound.
The nose gear is steerable
through
a
30 degree
arc each side of center
through the
use of
the
rudder
pedals. As
the
nose wheel retracts,
the
steering linkage disengages
to
reduce rudder pedal
loads
in flight. The
nose
wheel
is
equipped
with a hydraulic
shimmy
dampener to
reduce nose wheel shimmy.
A
bungee
assembly is also included
to
reduce ground steering effort and
to dampen
shocks and
bumps during
taxiing.
The oleo struts are of
the
air-oil
type,
with normal extension being 2.75
±
.25
inches for
the
nose gear
and 2.25
±
.25
inches for
the
main gear
under
normal static load
(empty
weight of airplane
plus
full fuel
and oil).
The standard
brake
system includes
toe
brakes on
the
left and right set of rudder pedals and a hand
brake located below and
near
the
center
of
the
instrument
panel.
The toe brakes
and
the hand brake have
individual brake
cylinders,
but all cylinders
use
a common reservoir. The
parking
brake is incorporated
in
the
lever brake and is operated
by
pulling
back
on
the
lever and
depressing the
knob attached
to the
top
of
the handle.
To
release
the
parking
brake,
pull back on
the
brake lever;
then
allow
the
handle
to
swing
forward.
ISSUED: DECEMBER
20,
1976
REPORT: VB-800
7-7
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