Empennage Structure — Vertical Stabilizer Top End Cap Assembly Cracking
- Published
- Effective
- Replaces
- 2024-03
AI-generated summary of the official EASA document. Verify against the PDF before acting.
What to do
Operators must perform a one-time detailed visual inspection of the vertical stabilizer top end cap assembly within 10 hours air time after 16 July 2025. If cracks are found, the part must be replaced before further flight. Recurring inspections must be conducted every 25 hours air time until the affected part is replaced with the new machined assembly within 12 months of the effective date.
Summary
Canadian Airworthiness Directive CF-2025-32 addresses cracking in the vertical stabilizer top end cap assembly on Bell Textron Canada Limited Model 505 helicopters with specific serial numbers. This directive mandates inspections and replacement of affected parts to ensure structural integrity and flight safety. It applies to helicopters equipped with part number SLS-030-701-125 and introduces a new machined top end cap assembly part number SLS-704-701-101.
What changed
CF-2025-32 supersedes emergency AD CF-2024-03 by limiting the applicability due to the introduction of a new one-piece machined vertical stabilizer top end cap assembly. It requires replacement of the older top end cap assembly part number SLS-030-701-125 with the new part number SLS-704-701-101 when cracks are found or after 12 months from the effective date.
Why it matters
This directive is critical for aviation professionals because cracks in the vertical stabilizer top end cap assembly can lead to the loss of the NAV/VOR/GS antenna and tuning weight, potentially damaging the tail rotor and causing loss of directional control. Operators and maintenance teams must comply to prevent in-flight component failure and ensure continued airworthiness of affected Bell 505 helicopters.
More for Bell 505 (Jet Ranger X)
All 19- EASA AD CF-2026-12Levelling and Weighing — Aft Moveable Ballast Box Assembly Door Hinge FailureMar 4, 2026
- EASA AD CF-2026-01Tail Rotor - Incorrect Tailcone Assembly Part Number Identification PlateJan 20, 2026
- EASA AD CF-2025-62Fuselage — Tailboom — Elongated Holes and Gaps on Tailcone AssemblyDec 5, 2025
- EASA AD CF-2025-35Levelling and Weighing — Aft Moveable Ballast Box Assembly Door Hinge FailureJul 9, 2025
- EASA AD CF-2025-34
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