AD 2020-26-21 Requires A Rotating Probe Test Of All Fastener Holes Located In The Affected Area

The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes.

This AD was prompted by a report that during the assembly of a certain section of the fuselage, the gaps found on self-aligning nuts for eight fasteners were out of tolerance. This AD requires a rotating probe test of all fastener holes located in the affected area for any discrepancies, an eddy current inspection of the surrounding flange for any discrepancies, a detailed inspection of certain frames for any discrepancies, and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. This AD is effective February 3, 2021.

Supplementary Information: The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2020-0109, dated May 15, 2020 (EASA AD 2020-0109) (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for certain Airbus SAS Model A350-941 airplanes.

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus SAS Model A350-941 airplanes. The NPRM published in the Federal Register on August 4, 2020 (85 FR 47122). The NPRM was prompted by a report that during the assembly of the section 19 skin to frame (FR) 98 joint of the fuselage, the gaps found on self-aligning nuts for eight fasteners were out of tolerance. The NPRM proposed to require a rotating probe test of all fastener holes located in the affected area for any discrepancies, an eddy current inspection of the surrounding flange for any discrepancies, a detailed inspection of certain frames for any discrepancies, and corrective actions if necessary, as specified in an EASA AD.

The FAA is issuing this AD to address gaps that are out of tolerance, which could reduce the fatigue and damage tolerance properties of the affected area, and possibly affect the structural integrity of the rear cone of the fuselage. See the MCAI for additional background information.

FMI: www.regulations.gov