EASA AD 2013-0084R1
Landing Gear - Main Landing Gear Lever Hinge Fitting - Inspection
Summary
EASA Airworthiness Directive 2013-0084R1 is an updated regulatory requirement addressing inspection and maintenance of the main landing gear lever hinge fittings on Piaggio P.180 Avanti and Avanti II aeroplanes, excluding those equipped with Magnaghi main landing gear. The directive mandates repetitive inspections to detect cracks caused by friction in the landing gear assembly, which could compromise structural integrity and aircraft control during takeoff or landing. It also introduces an optional modification to improve stress resistance and reduce inspection frequency for affected landing gear.
What Changed
This revision narrows the applicability by excluding aircraft fitted with Magnaghi main landing gear, which are not affected by the unsafe condition. It adds an optional modification for aircraft with SAFRAN Landing Systems main landing gear that, once implemented, terminates the need for repetitive inspections. Editorial updates were made to align with current AD writing standards without changing the core requirements.
Why It Matters
This directive is critical for operators and maintenance organizations to prevent potential structural failure of the main landing gear, which could lead to loss of control during critical phases of flight. Compliance ensures continued airworthiness and safety of Piaggio P.180 aircraft. The optional modification provides a cost-effective solution to reduce maintenance burden and inspection frequency, improving operational efficiency.
What To Do
Operators must perform initial and repetitive visual, detailed visual, and fluorescent penetrant inspections of the main landing gear lever hinge fittings within specified flight cycle thresholds or timeframes, starting from the original effective date of 19 April 2013. Any detected cracks require immediate replacement of the affected landing gear with a serviceable unit. Installation of modified landing gear or application of the approved modification terminates the inspection requirements. Compliance with these actions is mandatory within 200 flight cycles or 3 months after the original AD effective date, and before next flight after landing gear replacement.
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