SECTION
II
CHEROKEE
"ARROW"
pressure
is
maintained above most vapor forming
conditions
while
fuel
inlet
pressure
is
low enough to allow
use
of
a diaphragm
pump.
The
servo
system
feature
also
checks
vapor lock and
associated
starting
problems.
The
servo
regulator meters fuel flow proportionally with air-
flow and maintains the mixtures
as
manually
set
for
all
engine
speeds.
The
fuel
flow
divider
receives
metered fuel and
dis-
tributes fuel
to
each
cylinder fuel nozzle.
The
fuel flow portion of
the
manifold
pressure
fuel flow
gauge
is
connected to the flow divider and monitors fuel pres-
sure.
This
instrument converts fuel
pressure
to an
indication
of
fuel flow in
gallons
per hour and percentage of rated horsepower.
The
alternate
air
source
of
the induction
system
contains
a
door
that
functions automatically
and/or
manually.
If
the
primary
source
is
obstructed, the door will open automatically.
It
may
be
opened manually by moving
the
selector
on the right
side
of the
quadrant.
The
primary source should always
be
used for take-off.
STRUCTURES
All
structures
are of aluminum alloy construction and
are
designed
to
ultimate load
factors
well
in
excess
of normal re-
quirements. All
exterior
surfaces
are
primed with
etching
primer
and painted with
acrylic
lacquer.
The
wings
are
attached
to
each
side
of the
fuselage
by in-
serting the
butt
ends
of the
respective
main
spars
into a
spar
box
carry-through,
an
integral
part of
the
fuselage
structure,
thus
providing in
effect
a continuous main
spar
which
splices
at
each
side
of the
fuselage.
There
are
also
fore and aft
attachments
at
the rear
spar
and
at
an auxiliary front
spar.
The wing airfoil
section
is
a laminar flow type,
NACA6~-
415 with the maximum
thickness
about
40%
aft
of
the
leading
edge.
This
permits
the
main
spar
carry-through
structure
to
be
located under
the
rear
seat
providing unobstructed
cabin
floor
space
ahead of the rear
seat.
6
690203
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