Product Certification Consultations and Publications

Clarification on the limited validity of equation (A-22) and (A-22a) proposed by DO-229(A,B,C,D) for the ionospheric pierce point location computation and provision of a formula which does not have that limitation.

Determination of an Unsafe Condition for Risk of Rotorcraft Engine In-Flight Shut-Down (IFSD) and Power Loss

Usable Fuel Capacity Marking

Fire protection of flight controls, engine mounts, and other flight structure (Applicable to Boeing 737-7 / -8 / -9)

Fan blade loss - effects at aircraft level - Applicable to Airbus A-320 Neo (equipped with CFN LEAP-1A engines)

Rotor Drive System - Gearbox TBO Development

Wing Leading Edge Slats (Applicable to Boeing 737-7 / -8 / -9)

Deviate from RTCA/DO-229D 2.2.3.3.1 and provide the deviations relative to the first approach leg instead of the FAF.

Deviates from RTCA DO-283A Appendix H section H.2.7 by alerting 15 seconds instead of the minimum 30 seconds before the required vertical path change.

Deviates from RTCA DO-283A Appendix H section H.2.4.4.3 by using a different vertical guidance compatible of the vertical constraints.

Deviates from RTCA DO-283A Appendix C section C.2.2 by using a different algorithm to determine position from multiple (more than two) DME, and secured with reasonableness checks.

Deviate from RTCA DO-283A Appendix C section C.2.1 by using a different weighting-algorithm to select or exclude VOR stations, and secured with reasonableness checks.