Cessna T188C - Page 63

MODEL
188 & T188
SERIES SERVICE
MANUAL
NOTE
3-17. DESCRIPTION.
The tailcone
seal is riveted to
the aft side of the bulkhead just behind the pilot seat.
A magnetic compass is mounted on the center The tailcone seal and two cockpit pressurization scoops
screws at the top of the windshield. Take help prevent chemical residue from being sucked from
necessary steps to protect the
compass during the
tailcone to the cockpit area.
Control cables pass
removal and replacement of the windshield. through access holes in the seal. The access holes have
replaceable rubber covers with holesjust large enough
d. Pull windshield
forward, out of side and top
for the control cables
to pass through. A removable
retainers.
door provides access to the
tailcone from the cockpit.
e. Clean retainer
strips and
channels before
in-
stalling new windshield. 3-18. COCKPIT SEALS. (See figure 3-5.)
f. When installing a new windshield, check fit and
carefully file or grind away any excess plastic. 3-19 DESCRIPTION. Beginning with airplane serial
g. Apply felt strips and sealing compound or seal- 18801825 and on, a sealed cockpit system is installed to
ing tape to all edges of the windshield. lessen the possibility of contamination of the pilot by
h. Use care
not to crack windshield when
installing. chemicals. A seal
is installed around the aft edge
of the
Start at an upper corner and gradually work wind- hopper and extends down the belly skin. Flexible seals,
shield into position. bonded to small bulkheads are installed between the re-
movable side panels, belly skin and hopper.
NOTE
3-20. SEATS. (See figure 3-6.)
Machine screws and self-locking nuts may be
used instead of the factory installed rivets 3-21. DESCRIPTION. These seats are manually oper-
which fasten the front retaining strip to the ated throughout their full range of operation. Seat stops
cowl deck. If at least
No. 6 screws are used no
are provided to limit
fore and aft travel.
loss
of strength
will
result.
3-22. REMOVAL AND INSTALLATION.
i. Install lower retainer strip. a. Remove seat stops from rails.
j. Install wire cutter and compass. b. Slide seat fore-and-aft to disengage seat rollers
from rails.
3-11.
WINDOWS. (See figure
3-2.)
c. Lift seat
out.
d. Reverse
the preceding
steps for
reinstallation.
3-12. REMOVAL AND INSTALLATION. Ensure all seat stops are installed.
a.
Remove
screws
or rivets
as
necessary
to
remove
the retainer
strips.
b. Remove
window
and clean
retainer
strips
and
channels.
c. Install felt seal, an adequate coating of sealer It is extremely important that seat stops are
and install new window.
installed, since acceleration
and deceleration
could possibly permit seat to become disen-
3-13. CABIN DOOR. (See figure 3-3.) gaged from seat rails and create a hazardous
situation, especially
during
take-off and
landing
3-14. REMOVAL AND INSTALLATION. Removal
of the door is accomplished by removing the screws 2-23. REPAIR OF SEAT STRUCTURE. Replacement
securing the hinges
to the sill, or if emergency re-
of defective parts is recommended
in repair of seats. How-
lease is installed,
by pulling the emergency
release ever, a cracked
framework may be welded, provided
the
handle. The hinges
have slotted holes for adjustment
crack is not in an area
of stress concentration (close to
a
of the door in the fuselage opening. When fitting a hinge or bearing point). The square-tube framework is
new door, some trimming of the
door skin at the 6061
aluminum, heat treated to a
T-6 condition. Figure
edges and some reforming with
a soft mallet may be
3-7 outlines instructions for replacement
of defective
necessary to achieve a good fit. cams on the semi-reclining seat back.
3-15. DOOR WEATHERSRTIP
is cemented around
3-24. SAFETY
PROVISIONS.
all edges of the door. New weatherstrip may be applied
after mating surfaces of weatherstrip and door are 3-25. SAFETY BELTS (See figure 3-8.)
clean, dry and free from oil or
grease. Apply a thin, Safety
belts should be replaced in
accordance with
even
coat of
adhesive
to each surface
and
allow to
dry
provisions
in Section
2.
until tacky before
pressing strips
in place. Minnesota.
Mining and Manufacturing Co. No. EC-880 cement is 3-26. SHOULDER HARNESS. See figure 3-8.)
recommended. The shoulder harness may be equipped with an inertia
reel mounted on the tubular fuselage structure. Thru
3-16. TAILCONE
SEAL. (See figure 3-4.)
Airplane Serial
18800832 a reel control is located
ad-
Temporary Revision
2 - Oct 3/94
3-9