Summary
This document proposes the supersedure of an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires an initial inspection of fastener holes on certain outer frames of the fuselage to detect fatigue cracking, and modification of the area by cold expanding the holes and installing oversized fasteners. This action would revise the applicability to include additional airplanes; require a high frequency eddy current inspection to detect fatigue cracking in the frames and frame feet at fuselage frames FR37 through FR41; and follow-on actions. This proposal also provides for an optional terminating action for the follow-on 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 prevent fatigue cracking of the fuselage frames and frame feet, and consequent reduced structural integrity of the fuselage.