Cessna T188C - Page 372

MODEL 188
& T188 SERIES
SERVICE
MANUAL
17-47A. CRACKS IN CORRUGATED ELEVATOR AND RUDDER SKINS (Continued from page 17-10)
1. It is permissible to stop
drill crack(s) that originate at
the trailing edge of the control
surface provided the
crack
is not more
than 2 inches
in length.
2. Stop
drill crack
using a #30 (.128
inch) drill.
3.
A crack may
only be
stop drilled
once.
NOTE:
A crack that passes through
a trailing edge rivet and
does not extend to the trailing
edge of the
skin may be
stop dilled
at both ends
of the crack.
4. Any control
surface that
has a crack
that progresses
past a stop drilled
hole shall
be repaired. Refer
to
paragraphs 17-47,
-48, and -49
as applicable for repair
information.
5. A control
surface that
has any of the
following conditions
shall have
a repair made as
soon as practicable:
A. A crack that is longer than 2 inches.
B.
A crack that does not
originate from the trailing
edge or a trailing
edge rivet.
C.
Cracks in more
than six trailing edge
rivet locations
per skin.
Refer to paragraphs
17-47, -48,
and -49 as applicable
for repair information.
6. Affected
control surfaces
with corrugated
skins and
having a stop
drilled crack
that does not extend
past
the stop drilled hole, may remain in service without additional repair.
I17-10B
Temporary Revision
Number 3
7 January 2000