AMC 22.561(b)(2) Emergency Landing Conditions

• ED Decision 2008/008/R found in: Sailplane Rule Book - Part-SAO Part-SFCL CS-22 (Nov 2022)

AMC 22.561(b)(2) Emergency Landing Conditions ED Decision 2008/008/R Compliance with [CS 22.561(b)(2)](#_DxCrossRefBm2056272171) 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)](#_DxCrossRefBm2056272171) should represent the maximum weight derived from [CS 22.25(a)(2)](#_DxCrossRefBm2056272040) 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)](#_DxCrossRefBm2056272171). References: (1) Sperber, M. Restraint Systems in Gliders under Biomechanical Aspects. Technical Soaring Vol. 19 No 2. ISSN #0744-8996 (1995) [Amdt 22/1]