{"data":{"id":"us/14-cfr-33.62","jurisdiction":"us","citation":"14 CFR 33.62","heading":"Stress analysis.","body":"A stress analysis must be performed on each turbine engine showing the design safety margin of each turbine engine rotor, spacer, and rotor shaft.","path":["Title 14—Aeronautics and Space","CHAPTER I—FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION","SUBCHAPTER C—AIRCRAFT","PART 33—AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES","Subpart E—Design and Construction; Turbine Aircraft Engines"],"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":"d3bb71fed7fe1262a81cbcb0adf38fe00198007c5d7f3a62a8592c017c2f0819","source_id":"us-cfr","stale":true,"prev":"us/14-cfr-33.61","next":"us/14-cfr-33.63"},"notice":"GroundRules: Original legal text. Not legal advice."}