Engine — High Pressure Turbine Nozzle Assembly and Stator Stationary Seal — Inspection
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AI-generated summary of the official EASA document. Verify against the PDF before acting.
What to do
Operators of affected LEAP-1A engines must inspect the stage 2 high pressure turbine nozzle assembly and stator stationary seal honeycomb within the most restrictive compliance time specified in the referenced CFM Service Bulletin or during the next engine shop visit, whichever occurs first after 21 July 2022. If any discrepancies are found during inspection, corrective actions must be completed before the next flight or before releasing the engine to service. Alternative methods of compliance may be approved upon request.
Summary
EASA Airworthiness Directive 2022-0139 is an official regulatory document addressing the inspection of the high pressure turbine nozzle assembly and stator stationary seal on CFM International LEAP-1A engines. This directive applies specifically to various LEAP-1A engine models installed on Airbus A319, A320, and A321 aircraft. It mandates a one-time inspection to detect potential damage caused by non-synchronous vibrations that could affect engine safety and performance.
What changed
EASA Airworthiness Directive 2022-0139 introduces a new mandatory inspection requirement for the honeycomb of the stage 2 high pressure turbine nozzle assembly and the high pressure turbine stator stationary seal on affected LEAP-1A engines. It requires operators to perform inspections within specified compliance times or during the next engine shop visit and to carry out corrective actions if discrepancies are found. This AD does not supersede any previous directives.
Why it matters
This directive is critical for aviation professionals because it addresses a potential unsafe condition that could lead to thermal degradation and reduced fatigue life of key turbine components. Operators and maintenance organizations must comply to ensure continued airworthiness and prevent in-flight engine failures. Compliance helps maintain engine reliability and safety, reducing the risk of costly repairs and operational disruptions.
More for CFM International LEAP-1A
All 21- EASA SIB 2025-06R1Potential Risk Management Issue after Engine Load Reduction Device ActivationOct 1, 2026
- EASA AD 2025-0171R2Engine – High Pressure Turbine Rotor Stage 1 Blade – InspectionJul 3, 2026
- EASA PAD 26-006Engine — Full Authority Digital Electronic Control Software — ReplacementJan 16, 2026
- EASA AD 2025-0246Engine — Non-Synchronous Vibration During Engine Operation — Monitoring / ReplacementOct 30, 2025
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