Cessna T188C - Page 192

MODEL 188 & T188 SERIES SERVICE MANUAL
n. Make a magneto switch
ground-out and continuity
3. Examine the exterior
of hoses for evidence
check and connect magneto
switch wires.
of leakage
or wetness.
4.
Hoses found
leaking should
be replaced.
WARNING 5. After pressure testing fuel hoses, allow suf-
ficient time for excess fuel to drain overboard from
Be sure magneto switch is in OFF position the engine manifold before attempting an engine start.
when connecting switch wires
to magnetos.
6. Refer to paragraph 11-14
for detailed inspec-
tion procedures for flexible hoses.
o. Service engine with proper grade and quantity of
engine oil. Refer to
Section 2 if engine is new, new-
11A-19. REPLACEMENT.
Refer to Section 11.
ly overhauled or has been in storage.
p. Make sure all switches
are in the OFF position
11A-20. ENGINE BAFFLES.
Refer to Section 11.
and connect battery cables.
q. Inspect engine installation
for security, correct
11A-21. ENGINE MOUNT.
(See figure 11A-1.)
routing of controls, lines, hoses and electrical wir- The engine-mount is comprised of sections of tubing
ing, proper
safetying
and tightness
of all components.
welded
together and reinforced
with welded
gussets.
r. Install engine cowling in accordance with para- The purpose of the mount is to support the engine and
graph 11A-3. attach it to the airframe. Each engine-mount pad has
s. Clean and install air
filter.
a small hole for a locating
pin which serves as a lo-
t. Perform
an engine run-up
and make
final adjust-
eating dowel
for the engine
shock mounts.
Beginning
ments
on engine controls,
with Aircraft
Serial 18801825, a swing
engine mount
designed
to provide access
to the rear
of engine is
11A-16.
PIVOTING ENGINE FOR
MAINTENANCE. installed.
The mount hinges on the
right side with
Access
to the engine
components and
accessories on
the overcenter
arm supporting
the left
lower mount
the back
of the
engine
may be gained
by
swinging
the
leg.
engine forward
and downward,
pivoting
about the
lower
engine
mount bolts
at the
lugs protruding
11A-22.
REMOVAL
AND INSTALLATION.
through
the firewall. Attach
a suitable
hoist to the
a. Remove
engine in accordance
with
paragraph
hoisting
Lug
on top of the
engine
and take-up
engine
11A- 10.
weight with the
hoist.
b. Remove bolts
from upper and lower mount-to-
fuselage structure
and carefully
remove
engine-
NOTE
mount.
c. Reverse
the preceding
steps for reinstallation.
The working space
needed will
determine
Torque
bolts to 160-190
lb-in.
Reinstall engine
in
just
how many
items will have
to be dis-
accordance
with paragraph
11A-15.
connected before the engine can be pivoted
away
from the
firewall.
A very small
11A-23.
PREPARATIONS
FOR SWING
MOUNT
space may
require that
only a few items
USAGE.
(Refer to figure
11A-1, sheet
2.)
be disconnected
or unclamped.
A larger
a.
Disconnect
the
following
items:
working space
will require
most of the
1. Propeller
control at
governor, at
oil pan
items listed in paragraph 11A-10
to be bracket
(remove 2 bolts securing
bracket to oil pan)
disconnected.
Always
be sure that
lines,
and at
attachment
to intake manifold.
hoses, electrical
wires and
controls are
2. Main fuel
line clamps from
the engine mount
not stretched
or
broken.
Cap
or plug all
leg.
disconnected
lines, hoses
and fittings.
3. Vapor
return line.
4. Intake induction air hose (disconnect or
After disconnecting and/or unclamping items to per- remove).
mit swinging the engine down as much as needed, re- 5. Wiring clamps (as required).
move the
bolts from the engine mount upper
attach- 6. If optional
hydraulic pump is installed,
re-
ment points and
loosen the pivot bolts at the bottom
move the bolts securing
pump to engine and allow
of the engine
mount. Slowly lower
the hoist, watch-
pump to hang free of
engine.
ing
for any additional
items that
may need to be
dis- b.
Remove LH
upper and lower
firewall mount
connected
or unfastened.
The induction airbox
will
bolts.
have
to be removed
for maximum
access on aircraft
c.
Loosen nuts
on RH upper and
lower firewall
prior to serial number
18800833.
mount bolts.
11A-17. FLEXIBLE
FLUID HOSES.
NOTE
11A-18.
PRESSURE
TEST.
Engine
will
sag approximately
1/4" when
a. After each
50 hours
of engine operation,
all
disengaged from
firewall
lug.
flexible fluid hoses in the engine compartment should
be pressure tested as
follows:
d. Safety swing arm
(16) to overcenter position
1.
Place mixture
control
in the
idle cut-off
posi-
using
pin (14).
tion.
2. Operate the auxiliary fuel pump in the high
position.
11A-8