Health and usage monitoring systems (HUMS) use vibration-based Condition Indicators (CI) to assess the health of helicopter powertrain components. A fault is detected when a CI exceeds its threshold value. The effectiveness of fault detection can be judged on the basis of assessing the condition of actual components from fleet aircraft. The Bell 412 HUMS-equipped helicopter is chosen for such an evaluation. A sample of 20 aircraft included 12 aircraft with confirmed transmission and gearbox faults (detected by CIs) and eight aircraft with no known faults. The associated CI data is classified into "healthy" and "faulted" populations based on actual condition and these populations are compared against their CI thresholds to quantify the probability of false alarm and the probability of missed detection. Receiver Operator Characteristic analysis is used to optimize thresholds. Based on the results of the analysis, shortcomings in the classification method are identified for slow-moving CI trends. Recommendations for improving classification using time-dependent receiver-operator characteristic methods are put forth. Finally, lessons learned regarding OEM-operator communication are presented.


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    Titel :

    Health Monitoring Survey of Bell 412EP Transmissions


    Beteiligte:

    Kongress:

    American Helicopter Society International''s Annual Forum & Technology Display ; 2016 ; West Palm Beach, FL, United States


    Erscheinungsdatum :

    2016-05-17


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    ACOUSTIC BEAMFORMING FOR HEALTH MONITORING OF HELICOPTER TRANSMISSIONS

    Hood, A. A. / Pines, D. / American Helicopter Society | British Library Conference Proceedings | 2002


    Structural Health Monitoring for Bell 407 Tail Boom

    Purekar, A. / Choi, Y.T. / Wereley, N. et al. | British Library Conference Proceedings | 2009



    Transmissions

    Online Contents | 1996


    Transmissions

    Online Contents | 1996