Summary
This document proposes the supersedure of an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-215-1A10 and CL-215-6B11 series airplanes, that currently requires repetitive inspections to detect cracking on certain wing-to-fuselage frame angles; and repair, if necessary. This action would decrease the compliance time for the initial inspection to detect cracking on certain wing-to-fuselage frame angles and would decrease the interval between repetitive inspections. This proposal is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by the proposed AD are intended to detect and correct cracking in the wing-to-fuselage frame angles, which could result in reduced structural integrity of the airframe.