Main Rotor — Pitch Link Assembly Clevis Fracture
- Published
- Effective
- Replaces
- 2021-26
AI-generated summary of the official EASA document. Verify against the PDF before acting.
What to do
Operators must verify service records and perform initial inspections within 50 flight hours or 60 days from 17 December 2024, whichever occurs first. Components exceeding new life limits must be replaced before further flight. Repetitive detailed inspections of the pitch link clevises are required every 50 hours or 60 days, and universal bearings every 150 hours or 12 months, with corrective actions taken as needed. Parts must be re-identified and properly greased according to the Bell Alert Service Bulletin 430-22-61.
Summary
Canadian Airworthiness Directive CF-2024-40 addresses the risk of fracture in the main rotor pitch link assembly clevis on Bell Textron Canada Limited model 430 helicopters, serial numbers 49001 through 49129. This directive mandates inspections, life limit reductions, and replacement requirements for the main rotor pitch link clevis, universal bearings, and universal to pitch link bolts to prevent loss of control. It updates previous safety measures following fatal accidents linked to fatigue failures of these components.
What changed
CF-2024-40 supersedes AD CF-2021-26 and introduces reduced airworthiness life limits for the main rotor pitch link clevises, universal bearings, and universal to pitch link bolts as specified in Bell's revised Airworthiness Limitations Schedule. It mandates initial and repetitive detailed inspections, re-identification of parts, and replacement of components exceeding new life limits. The directive also incorporates requirements from Bell Alert Service Bulletin 430-22-61.
Why it matters
This directive is critical for operators and maintenance organizations to prevent catastrophic failures caused by fatigue cracks in key rotor components. Compliance ensures continued airworthiness and safety of Bell 430 helicopters by addressing wear, corrosion, and damage before failure occurs. It also provides clear inspection intervals and life limits, aiding maintenance planning and regulatory compliance.
More for Bell 430
All 10- EASA AD 2015-0226R8Equipment / Furnishings — Hoist — Test / ReplacementJul 16, 2025
- EASA AD CF-2010-29R2Hydraulic Power — Servo Actuator Piston Rod — Corrosion and CrackingJul 26, 2022
- EASA AD CF-2021-26Main Rotor — Pitch Link Assembly Clevis FractureJul 29, 2021
- EASA AD 2021-0148Equipment & Furnishings — Emergency Flotation System — Rotorcraft Flight Manual (Supplement)Jun 21, 2021
- EASA AD 2020-0039Fire Protection — Hand-held Fire Extinguishers — Replacement
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