Cessna 152 - Page 53

CESSNA
MODEL
152
SECTION4
NORMAL
PROCEDURES
The
carburetor
heat
control
knob
should
be
pushed
full
in
during
all
ground
operations
unless
heat
is
absolutely
necessary.
When
the
knob
is
pulled
out
to
the
heat
position,
air
entering
the
engine
is
not
filtered.
Taxiing
over
loose
gravel
or
cinders
should
be
done
at
low
engine
speed
to
a.void
abrasion
and
stone
damage
to
the
propeller
tips.
The
nose
wheel
is
designed
to
automatically
center
straight
a.head
when
the
nose
strut
is
fully
extended.
In
the
event
the
nose
strut
is
over-
inflated
and
the
airplane
is
loaded
to
a
rearward
center
of
gravity
position,
it
may
be
necessary
to
partially
compress
the
strut
to
permit
steering.
This
can
be
accomplished
prior
to
taxiing
by
depressing
the
airplane
nose
(by
hand)
or
during
ta.xi
by
sharply
applying
brakes.
·
BEFORE TAKEOFF
WARM-UP
Most
of
the
warm-up
will
have
been
conducted
during
ta.xi,
and
additional
warm-up
before
takeoff
should
be
restricted
to
the
checklist
procedures.
Since
the
engine
is
closely
cowled
for
efficient
in-flight
cooling,
precautions
should
be
taken
to
avoid
overheating
on
the
ground.
MAGNETO CHECK
The
magneto
check
should
be
ma.de
at
1700
RPM
as
follows.
Move
ignition
switch
first
to
R
position
and
note
RPM.
Next
move
switch
back
to
BOTH
to
clear
the
other
set
of
plugs.
Then
move
switch
to
the
L
position,
note
RPM
and
return
the
switch
to
the
BOTH
position.
RPM
drop
should
not
exceed
125
RPM
on
either
magneto
or
show
greater
than
50
RPM
differen-
tial
between
magnetos.
If
there
is
a
doubt
concerning
operation
of
the
ignition
system,
RPM
checks
at
higher
engine
speeds
will
usually
confirm
whether
a
deficiency
exists.
An
absence
of
RPM
drop
may
be
an
indication
of
faulty
grounding
of
one
side
of
the
ignition
system
or
should
be
ca.use
for
suspicion
that
the
magneto
timing
is
set
in
advance
of
the
setting
specified.
ALTERNATOR CHECK
Prior
to
flights
where
verification
of
proper
alternator
and
alternator
control
unit
operation
is
essential
(such
as
night
or
instrument
flights),
a
positive
verification
can
be
made
by
loading
the
electrical
system
momentarily
(3
to
5
seconds)
with
the
landing
light,
or
by
operating
the
wing
flaps
during
the
engine
runup
(1700 RPM).
The
ammeter
will
remain
1
July
1978
4-13