Cessna T188C - Page 186

MODEL
188 & T188
SERIES SERVICE
MANUAL
11A-1. ENGINE COWLING.
11A-5. REPAIR.
(Refer to Section 11).
11A-2. DESCRIPTION.
(Refer
to Section 11).
11A-6. ENGINE.
11A-3. REMOVAL AND INSTALLATION. 11A-7. DESCRIPTION. The fuel-injected engine is
an air-cooled,
horizontally-opposed,
direct-drive,
NOTE
six-cylinder
Continental 10-520 series
engine. The
cylinders,
numbered
from
rear
to front,
are stagger-
On aircraft
serials 18801375 THRU 18801750
ed to permit
a separate throw on the crankshaft
for
when
the new solid rubber forward
engine each
connecting rod. The right rear
cylinder is
shock mounts are installed, refer to Cessna number 1 and the cylinders on the right side are
Single-Engine Service Letter SE75-4, dated identified by odd numbers 1, 3 and 5. The left rear
January 31, 1975.
cylinder is number 2 and the
cylinders on the left
side
are identified
as numbers 2,
4 and 6. For
repair
a. (ALL AIRCRAFT). Unfasten the quick-release and overhaul of the engine, accessories and propeller,
fasteners
along aft end and sides to
remove upper refer to
the applicable publication issued
by the manu-
cowling section.
facturer of these items. These
publications are avail-
b. (THRU AIRCRAFT SERIAL
18800832).
able from the Cessna
Supply Division.
Remove plate
at aft end
of lower cowling
section
and disconnect air intake boot at airbox. 11A-7A. TIME BETWEEN OVERHAUL (TBO). Tele-
c. (BEGINNING WITH AIRCRAFT SERIAL dyne Continental Motors recommends engine overhaul
18800833). Remove plate at
aft end of lower cowling
at 1200 hours operating time for
the IO-520-D series
section, disconnect alternate air rod assembly at engines employed in spraying or dusting operations.
alternate air door arm ball joint, loosen clamp Refer to Continental Aircraft Engine Service Bulletin
securing
hose to adapter, slide hose
from adapter M81-22,
and to any superseding bulletins,
revisions
flange and disconnect landing
light wires at quick or
supplements thereto, for further
recommendations.
disconnects. At the time of overhaul, engine accessories should be
d. (ALL AIRCRAFT). Unfasten the quick-release overhauled. Refer to Section 13 for propeller and
fasteners along
aft end and carefully
remove lower governor
overhaul periods.
cowling
section.
e.
Reverse the preceding steps for
reinstallation. 11A-7B.
OVERSPEED LIMITATIONS.
The engine
Ensure the
vertical baffle
seals are folded
forward
must not be operated
above specified
maximum
con-
and the side
baffle seals
are folded
upward.
tinuous
RPM.
However,
should
inadvertent
over-
speed occur, refer to Continental Aircraft Engine
11A-4. CLEANING AND
INSPECTION. Refer to
Service Bulletin M75-16,
and to any superseding
Section 11.
bulletins, revisions
or supplements thereto,
for
further recommendations.
11A-8.
ENGINE
DATA.
Aircraft
A188 AGwagon,
A188
AGwagon
A, A188A
Agwagon B,
A188B
AGwagon
C, A188B
AGtruck
Model (Continental)
1O-520-D
BHP Maximum
for Take-Off
300
(5 Minutes)
at RPM
2850
BHP
Maximum
Except
Take-Off
285
RPM (Max.
Continuous)
2700
Static RPM
2800 RPM
(Refer to
paragraph
11-10 for
details)
Model
A188B (Controllable
pitch )
Number
of Cylinders
6-Horizontally
Opposed
Displacement
520 Cubic
Inches
Bore
5. 25 Inches
Stroke
4. 00
Inches
Compression
Ratio
8.5:1
11A-2 Revision 1