{"data":{"id":"us/14-cfr-27.337","jurisdiction":"us","citation":"14 CFR 27.337","heading":"Limit maneuvering load factor.","body":"The rotorcraft must be designed for—\n(a) A limit maneuvering load factor ranging from a positive limit of 3.5 to a negative limit of −1.0; or\n(b) Any positive limit maneuvering load factor not less than 2.0 and any negative limit maneuvering load factor of not less than −0.5 for which—\n(1) The probability of being exceeded is shown by analysis and flight tests to be extremely remote; and\n(2) The selected values are appropriate to each weight condition between the design maximum and design minimum weights.","path":["Title 14—Aeronautics and Space","CHAPTER I—FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION","SUBCHAPTER C—AIRCRAFT","PART 27—AIRWORTHINESS STANDARDS: NORMAL CATEGORY ROTORCRAFT","Subpart C—Strength Requirements"],"source_url":"https://www.ecfr.gov/api/versioner/v1/full/2026-08-25/title-14.xml","current_through":"2026-08-25","vintage":"","retrieved_at":"2026-08-27T02:24:20Z","sha256":"83048ecee23562b30411a071c066943c9e29762b1b5ae45e0a20262e1c8a428a","source_id":"us-cfr","stale":true,"prev":"us/14-cfr-27.321","next":"us/14-cfr-27.339"},"notice":"GroundRules: Original legal text. Not legal advice."}