[Correction] Fuselage — Pressure Panel Longitudinal Beams — Inspection / Repair / Modification
- Published
- Effective
- Deadline
- Replaces
- 2016-0206
AI-generated summary of the official EASA document. Verify against the PDF before acting.
What to do
Affected operators must perform special detailed inspections around the pressure panel fasteners before exceeding 30,000 flight cycles and at intervals not exceeding 18,000 flight cycles thereafter. If cracks are detected, repairs must be completed before the next flight. Additionally, pressure panel modifications must be carried out according to Airbus SB A320-53-1263 Revision 05 or SB A320-53-1240 Revision 01, with compliance effective from 2 April 2024.
Summary
EASA Airworthiness Directive 2024-0077 is a regulatory document addressing inspection, repair, and modification requirements for the pressure panel longitudinal beams on Airbus A318, A319, A320, and A321 aircraft. It targets all manufacturer serial numbers except those with Airbus modification 151574 embodied in production. The directive aims to ensure structural integrity by mandating inspections and corrective actions related to fatigue cracks found around fasteners connecting the pressure panel to the flexible bracket at fuselage frame 36.
What changed
EASA AD 2024-0077 supersedes the previous AD 2016-0206 and introduces updated requirements based on revised Airbus Service Bulletin A320-53-1263 Revision 05, correcting prior countersunk information errors. It retains existing inspection and repair mandates while requiring modifications to affected holes in the pressure panel and provides credit for actions performed under earlier revisions of the service bulletin. Additionally, typographical errors and the effective date in the appendix have been corrected.
Why it matters
This directive is critical for aviation professionals as it addresses a potential unsafe condition that could compromise the structural integrity of Airbus A320 family aircraft. Operators and maintenance organizations must comply to prevent fatigue-related cracks from progressing, which could lead to serious safety risks. Ensuring adherence to the updated inspection and modification procedures helps maintain airworthiness and regulatory compliance.
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