CS 25.362 Engine failure
loads
ED Decision 2009/017/R
(See AMC 25.362.)
(a) For
engine mounts, pylons and adjacent supporting airframe structure, an ultimate
loading condition must be considered that combines 1g flight loads with the
most critical transient dynamic loads and vibrations, as determined by dynamic
analysis, resulting from failure of a blade, shaft, bearing or bearing
support, or bird strike event.
Any permanent deformation from
these ultimate load conditions should not prevent continued safe flight and
landing.
(b) The
ultimate loads developed from the conditions specified in paragraph (a) are to
be:
(1) multiplied
by a factor of 1.0 when applied to engine mounts and pylons; and
(2) multiplied
by a factor of 1.25 when applied to adjacent supporting airframe structure.
[Amdt 25/8]