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Collins/Honeywell Recommendations for C63c TSO Appendix

Collins/Honeywell Recommendations for C63c TSO Appendix Describing Turbulence Minimum Operational Performance. Flight Test (Add to the AC not the TSO). Purpose of flight test should be end to end demonstration of turbulence detection system

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Collins/Honeywell Recommendations for C63c TSO Appendix

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  1. Collins/Honeywell Recommendations for C63c TSO Appendix Describing Turbulence Minimum Operational Performance • Flight Test (Add to the AC not the TSO) • Purpose of flight test should be end to end demonstration of turbulence detection system • Allows a subjective evaluation of system in a flight environment • Verify detections and absence of nuisance detections • No turbulence penetration requirement. System is advisory only. Similar to weather radar precipitation advisory.

  2. Collins/Honeywell Recommendations for C63c TSO Appendix Describing Turbulence Minimum Operational Performance • Analysis • Assume good correlation between variance of vertical and horizontal winds within detection resolution interval. • Use analysis to determine statistical performance of spectral width estimators • Statistical assumptions of wind field similar to Doviac and Zrnic • Could be analytical or Monte Carlo. • Consider estimator variance as function of signal to noise ratio and spectral width magnitude. • Determine statistical impact of “one-size-fits-all” weight tables (need FAA help/concurrence)

  3. Collins/Honeywell Recommendations for C63c TSO Appendix Describing Turbulence Minimum Operational Performance • Simulation • Purpose is to validate “must detect” and “must not detect” scenarios • Choose limited number of scenarios: • Select Cases with good correlation between vertical and horizontal winds • One case with “must detect” spectral width, moderate reflectivity • One case with “must not detect” spectral width, moderate reflectivity • Low reflectivity case with large spectral width • If MOPS requirements are specified in g’s, must have method specified for obtaining g’s from spectral width • one-size-fits-all weight and aircraft type • Truth model (outputs simulated in situ g’s) uses same airspeed, altitude, weight and aircraft type as algorithm under test, i.e. hazard tables are validated via analysis and this analysis is not repeated in simulation. • ADWRS and Turbulence Data Sets need no validation beyond existing NASA work.

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