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AD 2025-02148

Published 2025-02-04 · 2 models · 27 US-registered tails affected · Federal Register

Airworthiness Directives; Airbus SAS Airplanes Federal Register ↗

Abstract

The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a full-scale fatigue test that found cracks on the main landing gear (MLG) bay rear skin panel at the stringer run-out at Frame 46 and Stringer 32 on the left-hand and right-hand sides. This AD requires repetitive special detailed inspections (SDIs) of the affected area for cracking and applicable corrective actions, 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.

Applicability · by US fleet size

Federal Register text

Verbatim; the Federal Register publication is the legally binding document. Cite: 90 FR 8866. View on Federal Register ↗

[Federal Register Volume 90, Number 22 (Tuesday, February 4, 2025)] [Rules and Regulations] [Pages 8866-8868] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 2025-02148]

[[Page 8866]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2327; Project Identifier MCAI-2024-00233-T; Amendment 39-22926; AD 2025-01-02] RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a full-scale fatigue test that found cracks on the main landing gear (MLG) bay rear skin panel at the stringer run-out at Frame 46 and Stringer 32 on the left-hand and right-hand sides. This AD requires repetitive special detailed inspections (SDIs) of the affected area for cracking and applicable corrective actions, 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.

DATES: This AD is effective March 11, 2025. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 11, 2025.