Cessna 182 1978 - Cracks in Corrugated Aileron Skins

MODEL 182 & T182 SERIES SERVICE MANUAL
18-40A. CRACKS IN CORRUGATED AILERON SKINS (Continued from page 18-3)
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 drilled
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
18-40, -41, and -42
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
18-40, -41, and -42 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.
Temporary Revision Number 2
18-4A
7 January 2000