Summary
This document proposes the supersedure of an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires modification of the rear spar web of the wing, cold expansion of certain attachment holes for the forward pintle fitting and certain holes at the actuating cylinder anchorage of the main landing gear (MLG), repetitive inspections for fatigue cracking in certain areas of the rear spar of the wing, and corrective action if necessary. That AD also provides for optional terminating action for the requirements of the AD. This proposed AD would revise the threshold and repetitive intervals for the inspection. The actions specified by the proposed AD are intended to detect and correct fatigue cracking, which may lead to reduced structural integrity of the wing and the MLG. This action is intended to address the identified unsafe condition.