Summary
This document proposes the supersedure of an existing amendment, 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 continue to require the same inspections. This proposal is prompted by an adverse comment received in response to the existing amendment. 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.