CESSNA AIRCRAFT
COMPANY
SINGLE ENGINE
STRUCTURAL REPA
IR MANUAL
(4) Any control surface that has a crack that progresses past a stop drilled hole shall be repaired or
replaced.
(5) A control surfa
ce that has any of the following conditions shall have a repair made as soon as
practical:
(a) A crack that is longer than 2 inches.
(b) A crack that doe
s not originate from the trailing edge or a trailing edge rivet.
(c) Cracks in more than six trailing edge rivet locations per skin.
(6) Affected control surfaces with corrugated skins and having a stop drilled crack that does not
extend past th
e stop drilled hole, may remain in service without additional repair.
(7) Refer to Figure 802 as applicable for repair information.
51-75-00 Page 808
© Cessna Aircraft Company Jun 1/2005
To Next Page
Loading...
