Fuselage — Tailboom — Elongated Holes and Gaps on Tailcone Assembly
- Published
- Effective
AI-generated summary of the official EASA document. Verify against the PDF before acting.
What to do
Operators must replace tailcone assemblies before exceeding the new reduced life limits within 60 days of the directive's effective date, 12 December 2025. They must perform initial inspections for gaps prior to 1750 hours air time or within 25 hours if already above 1725 hours, followed by recurring inspections at specified intervals. Any findings of gaps, cracks, or loose fasteners require contacting Bell Product Support Engineering for repair before further flight.
Summary
Canadian Airworthiness Directive CF-2025-62 addresses manufacturing quality issues in Bell Textron Canada Limited model 505 helicopters, specifically affecting tailcone assemblies with elongated holes and gaps. The directive mandates inspections and a reduced airworthiness life limit for tailcone assemblies part number SLS-030-600-XYZ, applicable to serial numbers 65011 and subsequent. It aims to prevent potential tailboom skin fractures that could lead to loss of helicopter control.
What changed
CF-2025-62 introduces a mandatory reduction in the airworthiness life limit of the affected tailcone assemblies and requires initial and repetitive inspections for gaps, cracks, and loose or missing fasteners as detailed in Bell Alert Service Bulletin 505-24-41 Revision A. It also formalizes inspection intervals and corrective actions to address the identified manufacturing defects.
Why it matters
This directive is critical for operators and maintenance organizations to ensure the structural integrity of the tailboom assembly on Bell 505 helicopters. Failure to comply could result in undetected cracks leading to tailboom separation and potential loss of control, posing serious safety risks. Compliance teams must update maintenance planning and inspection schedules accordingly to meet regulatory requirements.
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- EASA AD CF-2025-32Empennage Structure — Vertical Stabilizer Top End Cap Assembly CrackingJul 7, 2025
- EASA AD CF-2025-34
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