AGUSTA Experience on Damage Tolerance Evaluation of Helicopter Components
Abstract
Within the fatigue evaluation of the EH101, Agusta has carried out a specific program of flaw tolerance evaluation of the primary loading path. The program is close to completion and this paper provides a summary of the most relevant results. For composite components, damage size was increased considering both manufacturing discrepancies greater than the minimum quality standard and impact damages clearly detectable during visual inspections. The favorable data achieved are based on the no growth' concept. The metal parts of the main rotor head were evaluated by enhanced safe life method and fail safe capability. The slow crack growth approach was instead applied for the Rear Fuselage End Fittings, which connect the Tail Unit. All these evidences can be used in addition to the comprehensive safe life evaluation of the aircraft to improve the maintenance and the repair actions. Based on this experience, application of flaw tolerance criteria will be carried out on the new helicopters in development phase.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 2000
- Accession Number
- ADP010640
Entities
People
- Luigi Candiani
- Ugo Mariani