1. Date of download: 6/20/2016 Copyright © ASME. All rights reserved. From: Analysis of the Reliability of a Jet Engine Compressor Rotor Blade Containing a Fatigue Crack J. Appl. Mech. 2016;83(4):041004-041004-9. doi:10.1115/1.4032376 (a) View of the compressor rotor blade and (b) magnified view of blade tangs that are held by a pin. The dashed circle indicates the location of the fatigue crack. Figure Legend:

2. Date of download: 6/20/2016 Copyright © ASME. All rights reserved. From: Analysis of the Reliability of a Jet Engine Compressor Rotor Blade Containing a Fatigue Crack J. Appl. Mech. 2016;83(4):041004-041004-9. doi:10.1115/1.4032376 (a) ECI response versus inspection time and (b) ECI response versus crack length Figure Legend:

3. Date of download: 6/20/2016 Copyright © ASME. All rights reserved. From: Analysis of the Reliability of a Jet Engine Compressor Rotor Blade Containing a Fatigue Crack J. Appl. Mech. 2016;83(4):041004-041004-9. doi:10.1115/1.4032376 (a) Posterior mean ECI response and 90% credible bounds with detection threshold and posterior noise mean, and (b) posterior mean POD and 95% lower credible bound Figure Legend:

4. Date of download: 6/20/2016 Copyright © ASME. All rights reserved. From: Analysis of the Reliability of a Jet Engine Compressor Rotor Blade Containing a Fatigue Crack J. Appl. Mech. 2016;83(4):041004-041004-9. doi:10.1115/1.4032376 The mesh for coarse global model and refined submodel. Stress intensity factor has been obtained from the refined submodel. Figure Legend:

5. Date of download: 6/20/2016 Copyright © ASME. All rights reserved. From: Analysis of the Reliability of a Jet Engine Compressor Rotor Blade Containing a Fatigue Crack J. Appl. Mech. 2016;83(4):041004-041004-9. doi:10.1115/1.4032376 The surface of stress intensity factor obtained from the submodel Figure Legend:

6. Date of download: 6/20/2016 Copyright © ASME. All rights reserved. From: Analysis of the Reliability of a Jet Engine Compressor Rotor Blade Containing a Fatigue Crack J. Appl. Mech. 2016;83(4):041004-041004-9. doi:10.1115/1.4032376 Fishbone diagram shows the sources of variability for fatigue growth Figure Legend:

7. Date of download: 6/20/2016 Copyright © ASME. All rights reserved. From: Analysis of the Reliability of a Jet Engine Compressor Rotor Blade Containing a Fatigue Crack J. Appl. Mech. 2016;83(4):041004-041004-9. doi:10.1115/1.4032376 (a) Sensitivity index of a 0 versus N, (b) sensitivity index of m versus N, (c) sensitivity index of C versus N, and (d) sensitivity index of Δσ versus N Figure Legend:

8. Date of download: 6/20/2016 Copyright © ASME. All rights reserved. From: Analysis of the Reliability of a Jet Engine Compressor Rotor Blade Containing a Fatigue Crack J. Appl. Mech. 2016;83(4):041004-041004-9. doi:10.1115/1.4032376 Bayesian network for fatigue crack growth analysis Figure Legend:

9. Date of download: 6/20/2016 Copyright © ASME. All rights reserved. From: Analysis of the Reliability of a Jet Engine Compressor Rotor Blade Containing a Fatigue Crack J. Appl. Mech. 2016;83(4):041004-041004-9. doi:10.1115/1.4032376 Reliability index calculated from both the DBN model and MCS Figure Legend:

10. Date of download: 6/20/2016 Copyright © ASME. All rights reserved. From: Analysis of the Reliability of a Jet Engine Compressor Rotor Blade Containing a Fatigue Crack J. Appl. Mech. 2016;83(4):041004-041004-9. doi:10.1115/1.4032376 Calibrated (a) Δσ and (b) m Figure Legend:

11. Date of download: 6/20/2016 Copyright © ASME. All rights reserved. From: Analysis of the Reliability of a Jet Engine Compressor Rotor Blade Containing a Fatigue Crack J. Appl. Mech. 2016;83(4):041004-041004-9. doi:10.1115/1.4032376 Comparison between before and after the calibration Figure Legend: