EASA AD 2013-0184R2
Fuselage — Frame 47 Splice Fitting Holes Between Stringers 24 and 26 — Inspection
Summary
EASA Airworthiness Directive 2013-0184R2 is a regulatory document addressing inspection requirements for the fuselage frame 47 splice fitting holes between stringers 24 and 26 on Airbus A300 and A300-600 aeroplanes. It mandates high frequency eddy current inspections to detect cracks that could compromise structural integrity. The directive applies to all manufacturer serial numbers of the specified Airbus models and includes detailed inspection thresholds and intervals.
What Changed
This revision adjusts the inspection intervals for Airbus A300-600 aeroplanes based on updated fatigue and damage tolerance analyses. It reduces the number of fastener holes requiring inspection and relaxes inspection intervals for aircraft equipped with reinforced splices. Editorial updates were also made to align with the latest AD writing standards without changing the substantive requirements.
Why It Matters
This directive is critical for maintaining the structural integrity of affected Airbus A300 series aircraft by preventing undetected crack development in a key fuselage splice area. Operators and maintenance organizations must comply to ensure continued airworthiness and avoid potential safety risks. The updated inspection intervals optimize maintenance efforts while ensuring timely detection of cracks.
What To Do
Operators must perform high frequency eddy current rotating probe inspections of the frame 47 splice fitting holes between stringers 24 and 26 within specified thresholds and at recurring intervals as defined in the directive. If cracks are found, corrective actions must be taken before the next flight. Compliance with the latest revision of the applicable Airbus Service Bulletins is required, and new fasteners must be installed after each inspection if no cracks are detected.
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