Cessna T188C - Page 79

MODEL
188 &
T188
SERIES
SERVICE
MANUAL
4-11A. STUB
WING CATWALK. For repair
of cat- i. Tighten the
four bolts in the rear spar first.
then
walk,
SKI88-2A
is available.
tighten the four
bolts in the
front spar last.
4-12.
FIN.
(See
figure
4-3.)
NOTE
4-13.
DESCRIPTION.
The
fin is
primarily
of metal
Be sure
to
check
and reset
rudder
and ele-
construction
consisting
of two
main
spars
and
suitable
vator
travel.
If
any
stop bolts
were
removed
ribs
for attachment
of the
skin.
Skin
panels
are
rivet-
or
settings
disturbed,
the
system
will
have
ed
to the
ribs and
spars.
Hinge
brackets
are
attached
to be
rigged.
Refer
to applicable
sections
of
to the
rear spar
for
rudder
installation.
The rudder
this manual.
also
has
a removable
tip.
j.
Tighten deflector
cable to
15 to 20 pound-inches
4-14.
REMOVAL
AND
INSTALLATION.
The
fin
may
and
resafety.
be
removed
without
removing
the rudder.
However,
for
access
and
ease
of handling,
the
rudder
may
be
4-15.
REPAIR.
Repair
of the
fin should
be accom-
removed
if
desired,
following
procedures
outlined
in
plished
in accordance
with
the applicable
instructions
Section
10.
in
Section
17.
a.
Thru
18801374.
1.
Remove
stinger
and
disconnect
tail
navigation
4-16.
HORIZONTAL
STABILIZER.
(See
figure
4-4.)
light
lead and
flashing
beacon
lead,
if installed.
Dis-
connect
rudder
cables
if rudder
has not
been
removed.
4-17.
DESCRIPTION.
The horizontal
stabilizer
is
2.
Disconnect
deflector
cable
at
fitting on
fin.
primarily
of metal
construction,
consisting
of two
3.
Remove screws
attaching
dorsal
to fuselage.
main spars
and
suitable ribs
for attachment
of
the
4.
Remove
tail
fairing,
then remove
bolts
attach-
skin.
Stabilizer
tips
are of
thermo-formed
plastic.
ing fin
front
and rear
spars
to fuselage,
and
remove
A formed
metal
leading
edge
is riveted
to
the assem-
fin.
bly to
complete
the
structure.
The
elevator
trim tab
5. Reverse
the
preceding
steps
for
installation.
actuator
is
contained
within
the horizontal
stabilizer.
The
underside of
the stabilizer
contains a covered
NOTE
opening
which
provides
access-to
the
actuator.
Hinges
are located
on the rear
spar assembly
to support the
Be
sure
to
check
and
reset
rudder
and
eleva-
elevators.
tor travel.
If any
stop bolts were
removed
or
settings
disturbed,
the
system
will
have
4-18.
REMOVAL
AND
INSTALLATION.
to
be rigged.
Refer
to
applicable
sections
a. Remove
elevators
and
rudder
in
accordance
with
in this
manual.
procedures
outlined
in Sections
8
and 10.
b. Remove vertical fin in accordance with proce-
6. Tighten
deflector
cable
to 15
to 20 pound-
dures
outlined
in
paragraph
4-14.
inches
and resafety.
c.
Disconnect
elevator
trim
control
cables
at clevis
b. Beginning
with
188-1375.
and
turnbuckle
inside
tailcone,
remove
pulleys
which
1.
Remove
stinger
and disconnect
tail
naviga-
route
the aft
cables
into
horizontal
stabilizer,
and
tion
light
lead and
flashing
beacon
lead,
if installed.
pull
cables
out
of tailcone.
Disconnect
rudder
cables
if rudder
has
not been
re-
d.
Remove
bolts
securing
horizontal
stabilizer
to
moved.
tailcone.
2.
Disconnect
deflector
cable
at fitting
on
fin.
e. Remove
horizontal
stabilizer.
3. Remove
screws
attaching
dorsal
to fuselage.
f. Reverse
the
preceding
steps
for
installation.
4.
Remove
tail
fairing,
then
remove
horizontal
g.
Re-rigg
control
systems
as
necessary.
stabilizer
at.ach
bolts
and
lower
stabilizer
to
gain
h.
Check
operation
of tail
navigation
light
and
access
to the
fin attach
bolts.
flashing
beacon,
if installed.
5. Remove
bolts attaching
fin front
and rear
spars
to fuselage,
and
remove
fin.
4-19.
REPAIR.
Repair
of the
stabilizer
should
be
f. Installation
steps
are
as follows:
accomplished
in accordance
with
the
applicable
in-
g.
Adequately
support
the tailcone
at approximately
structions
in Section
17.
station
175.00
to a
height
sufficient
enough
to
raise
the tailwheel
above
ground
level.
4-20.
STABILIZER
ABRASION
BOOT.
h. Set the vertical
tail assembly
in place
and insert
the eight
attach bolts
thru the spars
and respective
NOTE
bulkheads.
An Accessory
Kit
(AK177-64)
is available
NOTE from the Cessna Supply Division for in-
stallation of abrasion boots on aircraft
Be sure to check the washer requirements, not so equipped.
assembly
sequence
of washers
and head
direction of bolts.
Revision
1
4-7