{"data":{"id":"us/14-cfr-25.371","jurisdiction":"us","citation":"14 CFR 25.371","heading":"Gyroscopic loads.","body":"The structure supporting any engine or auxiliary power unit must be designed for the loads, including gyroscopic loads, arising from the conditions specified in §§ 25.331, 25.341, 25.349, 25.351, 25.473, 25.479, and 25.481, with the engine or auxiliary power unit at the maximum rotating speed appropriate to the condition. For the purposes of compliance with this paragraph, the pitch maneuver in § 25.331(c)(1) must be carried out until the positive limit maneuvering load factor (point A2 in § 25.333(b)) is reached.","path":["Title 14—Aeronautics and Space","CHAPTER I—FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION","SUBCHAPTER C—AIRCRAFT","PART 25—AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES","Subpart C—Structure"],"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":"d959908fd532588c70e09cef05ad84cc6732a278a358e7b09943141ca62cb73a","source_id":"us-cfr","stale":true,"prev":"us/14-cfr-25.367","next":"us/14-cfr-25.373"},"notice":"GroundRules: Original legal text. Not legal advice."}