EASA AD CF-2020-43
Landing Gear — Main Landing Gear Drag Strut — Longitudinal Cracking
Summary
Airworthiness Directive CF-2020-43 addresses longitudinal cracking in the main landing gear (MLG) drag strut assemblies, part number 46301-13, installed on De Havilland Aircraft of Canada Limited model DHC-8-400, DHC-8-401, and DHC-8-402 aeroplanes with serial numbers 4001, 4003, and subsequent. The directive mandates inspections and magnetic particle testing to detect cracks that could lead to landing gear failure. It also requires reporting inspection results to the manufacturer.
What Changed
This new Airworthiness Directive introduces mandatory verification, repetitive detailed visual inspections, and a one-time magnetic particle inspection of affected MLG drag strut assemblies. It prohibits installation of affected parts without completing these inspections and reporting requirements. The directive also specifies corrective actions including replacement of cracked parts before further flight.
Why It Matters
This directive is critical for aviation professionals to prevent potential failure of the main landing gear drag strut, which could cause asymmetric landing gear configuration and runway excursions. Operators and maintenance organizations must ensure compliance to maintain aircraft safety and airworthiness. The inspections and reporting requirements help identify and mitigate risks associated with previously overhauled parts that may have undetected cracks.
What To Do
Operators must verify within 30 days if affected MLG drag strut assemblies are installed. If installed, perform initial and repetitive detailed visual inspections every 80 flight hours and complete a magnetic particle inspection within 1600 flight hours or 12 months, whichever occurs first. Report inspection results to De Havilland Aircraft of Canada Limited within seven days after the magnetic particle inspection. Do not install affected parts without completing these requirements.
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