Cessna T188C - Page 195

MODEL 188 & T188 SERIES SERVICE MANUAL
11A-24. SWING
MOUNT ATTACHMENT
TO FIRE-
NOTE
WALL. (See
figure
11A-1, sheet
2.)
a. Remove pin
(14) attaching
swing arm (16)
to
Teledyne
Contnental Motors
recommends
overcenter position.
that the spin-on
filter be
inspected. Refer
b.
Align engine
mount
holes
to firewall
lugs using
to Continental
Aircraft
Engine Service
bullet-shaped
drift
pin
(15).
Bulletin
M74-2,
dated
16 January
1974.
CAUTION
Before installing
oil filter (6) lightly lubricate
filter
gasket (8)
with a thin coating
of Dow Corning
Care
must be exercised
when swinging
the
Compound,
DC-4, apply
by brushing
or wiping hubri-
engine
back to firewall
or damage
may
cant
on to base
gasket.
result.
e. Install
spin-on filter,
(6), on the
stud and torque
to 18-20 lb-ft or 3/4 to 1 full turn after gasket makes
c. Lift
the
lower
engine
mount
leg onto
the
firewall
contact.
lug using
screwdriver
to
assist.
f. Safety
wire
filter to
adapter.
d. Install
LH upper
and lower
firewall
bolts.
g. Install
all parts
removed
for access
and service
Torque
bolts
to value specified
in
paragraph
11A-
the engine
with
the proper
grade and
quantity of
en-
22"c".
gine oil.
One additional
quart of oil is
required each
e. Torque RH upper and
lower firewall bolts to
time the filter element
is changed.
value
specified
in paragraph
l1A-22"c".
h.
Start engine
and check
for proper
oil pressure.
f. Connect items which were disconnected or re- Check for oil leakage after warming up the engine.
moved
in step "a" of
paragraph 11A-23.
Ensure all
i. Again
check for oil
leakage after engine
has been
connections
are correctly
made,
secured,
and free
run at
high power
setting
(preferably
a flight
around
from
binding.
the field).
j. Check to make sure filter can has not been mak-
11A-25. ENGINE SHOCK-MOUNT PADS. (See ing contact with any adjacent parts due to engine
figure
11A-1.)
The bonded
rubber
and metal
shock-
torque.
mounts
are designed
to reduce transmission
of engine
k. While
engine is still
warm, recheck
filter (6), to
vibrations
to the airframe.
The
rubber
pads should
assure
proper tightness.
be wiped clean with a clean dry cloth.
11A-32.
ENGINE
FUEL
SYSTEM.
NOTE
11A-33 DESCRIPTION. The fuel injection system
Do
not clean the rubber pads and
dampener is a low
pressure system of injecting
fuel into the
assembly with any tpye of
cleaning solvent.
intake valve port of each cylinder.
It is a multi-
nozzle, continuous-flow type which controls fuel flow
Inspect the
metal parts
for cracks and excessive
to match engine
airflow. Any
change in throttle
posi-
wear due to aging and
deterioration. Inspect the
ton, engine speed, or a
combination of both, causes
rubber pads for
separation between the pad and
changes in fuel flow
in the correct relation to engine
metal backing,
swelling, cracking or a
pronounced airflow. A
manual mixture control and a
fuel flow
set of the pad.
Install new
parts for all parts
that
indicator are provided
for leaning
at any combination
show evidence
of wear or damage.
of
altitude and power
setting. The
fuel flow indicator
is calibrated
in gallons
per hour and indicates
approxi-
11A-26. ENGINE
OIL SYSTEM.
mately
the gallons
of fuel consumed
per hour.
The
continuous-flow
system
uses a typical
rotary vane fuel
11A-27. DESCRIPTION.
(Refer
to Section 11.)
pump.
There are
no running parts
in this system
ex-
cept for the engine-driven fuel pump.
11A-28. TROUBLE SHOOTING. (Refer to Section 11.)
NOTE
11A-29. FULL-FLOW OIL FILTER. 18803474 & ON
(See
figure 11A-2.)
Throughout the aircraft fuel
system, from
the
fuel tank/cells
to the
engine-driven
fuel
11A-30.
DESCRIPTION.
An external
oil filter
may
pump, use
RAS-4 (Snap-On
Tools Corp.,
be installed on
the engine. The
filter and filter
Kenosha,
Wisconsin), MIL-T-5544
(Thread
adapter replace
the regular engine oil pressure
Compound,
Antiseize, Graphite-Petrolatum)
screen.
The filter
is a throw-away
type spin-on
or equivalent,
as a thread lubricant
or to
filter which
has an internal
bypass valve.
seal
a leaking connection.
Apply
sparingly
to male
fittings only,
omitting
the first two
11A-31.
REMOVAL AND
INSTALLATION.
(See
threads.
Always
ensure that a
compound,
figure
11A-2.
)
the
residue
from a previously
used compound
a.
Remove
engine cowling
in accordance
with para-
or any other
foreign
material
cannot enter
the
graph
11A-3.
system.
Throughout
the
fuel injection
system,
b. Remove
safety wire (7)
from filter, (6).
from the
engine-driven
pump through the
dis-
c. Unscrew
filter
from adapter,
(3).
charge
nozzles,
use only
a fuel soluble
lubri-
cant, such as
engine lubricating
oil,
on fitting
threads.
Do not use any
other form
of thread
compound on the injection system fittings.
11A-11