Cessna 188 Series Service Manual 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