The CF-18 multi-role fighter entered service in the Canadian Forces (CF) in 1982. Since then, 138 of these aircraft have been delivered and are operating out of seven squadron located in Canada and in Europe. Each aircraft is equipped with a multi-channel data acquisition system which records a number of parameters including measured strains, engine data, and various flight incident data. The analysis of this recorded data has enabled the CF to very closely monitor aircraft usage and the rate at which each individual aircraft accumulates fatigue damage. Early in 1986, in-service analysis of CF-18 fleet usage indicated that the aircraft were being operated in a significantly different manner than assumed for design, and that severity of the usage approached or exceeded the spectrum used for certification testing. Furthermore, the CF-18s were accumulating fatigue at a higher rate than expected which lead to concern about the potential for the airframe to reach its required life expectancy to the year 2003. To ensure that the maximum economic life of the CF-18 fleet is achieved, the CF have implemented an aggressive Fatigue Life Management Programme (FLMP) and are proceeding with full scale Durability and Damage Tolerance Testing (DADTT) activities.
Durability and Damage Tolerance Testing and Fatigue Life Management: ACF-18 Experience
1991
16 pages
Report
No indication
English
Aircraft , Logistics Military Facilities & Supplies , Fatigue life , Fatigue(Mechanics) , Fighter aircraft , Airframes , Damage , Data acquisition , Engines , Flight , Management , Monitors , Parameters , Scale , Squadrons , Strain(Mechanics) , Damage assessment , Tolerances(Mechanics) , Failure(Mechanics) , Nondestructive testing , Data processing , Crack propagation , Airworthiness , Reprints , Foreign technology , Aircraft maintenance , CF-18 Aircraft , Economic life , Structural integrity , Canada
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