Cessna 188 Series Service Manual 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