AMC E 525 Continued rotation

(1)Continued rotation can be either due to windmilling or due to mechanical effects such as clutch drag in the case of a multi-engined rotorcraft. Compliance with this specification may be established by test or analysis and should take into account the conditions imposed on the Engine by a typical aircraft installation.

(2)The conditions imposed on the Engine after in flight shutdown and their maximum duration should include consideration of all expected aircraft applications for the Engine, e.g. rotorcraft, turbopropeller, subsonic aircraft and supersonic aircraft.

(3)Conditions that should be considered and addressed, if determined to be applicable, should include, but are not limited to, those identified below: Complete loss of Engine oil, Rotor unbalance resulting from blade loss and subsequent rotor damage. Consideration should be given to extended periods of continued rotation under these conditions in conjunction with the assumed flight envelope with one Engine shut down, including, where applicable, supersonic and supersonic to subsonic transition flight conditions.

(4)The conditions imposed at the Engine-to-aircraft interface as a result of the rotor unbalance and rotational speed associated with continued rotation of an Engine following an Engine blade loss and subsequent rotor damage should be determined by analysis or test or both by the applicant as required by CS-E 520(c)(2), covering the entire flight envelope, and be provided in the installation documents required by CS-E 20.

[Amdt. No.: E/1]