CS 27.337 Limit
manoeuvring load factor
ED Decision 2003/15/RM
The rotorcraft must be designed for:
(a) A limit manoeuvring load factor ranging from a positive limit of 3.5 to a negative limit of – 1.0; or
(b) Any positive limit manoeuvring load factor not less than 2.0 and any negative limit manoeuvring load factor of not less than – 0.5 for which:
(1) The probability of being exceeded is shown by analysis and flight tests to be extremely remote; and
(2) The selected values are appropriate to each weight condition between the design maximum and design minimum weights.
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