AMC 22.561(b)(2) Emergency Landing Conditions
ED Decision 2008/008/R
Compliance with CS
22.561(b)(2) can be shown
either by static tests or by analysis using methods validated by previous
static test evidence from structures of similar design. The analysis should,
at minimum, show that ultimate material strength properties and stability
limits, such as buckling of the canopy sill, are not exceeded. The weight used
when showing compliance to CS 22.561(b)(2) should represent the maximum weight
derived from CS 22.25(a)(2) as
far as these weights contribute to the loading of the safety cell.
For conventional
(semi-reclined) seating configurations it is sufficient to demonstrate, that
the main part of the cockpit, extending at least from the front control pedals
(adjusted to the intermediate longitudinal position) to the rearmost headrest
mounting or the wing attachment section whichever is further aft, including
the harness attachments (ref. 1), meets the requirements of CS
22.561(b).
References:
(1) Sperber,
M.
Restraint Systems in
Gliders under Biomechanical Aspects.
Technical Soaring Vol. 19 No 2. ISSN #0744-8996 (1995)
[Amdt 22/1]
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