Engine — High Pressure Turbine Rotor Stage 1 Blade — Inspection
Superseded. Comply with 2025-0171R2, which replaces this document.
- Published
- Effective
AI-generated summary of the official EASA document. Verify against the PDF before acting.
What to do
Affected operators and maintenance teams should review the inspection requirements outlined in the directive and schedule inspections of the high pressure turbine rotor stage 1 blades accordingly. They must comply with any specified inspection intervals and document the findings as part of the aircraft's maintenance records. Immediate action is required upon the directive's issuance, but no specific compliance deadline is provided in the document.
Summary
The document titled 'Engine — High Pressure Turbine Rotor Stage 1 Blade — Inspection' is a regulatory directive concerning the inspection requirements for the high pressure turbine rotor stage 1 blades on CFM INTERNATIONAL LEAP-1A and LEAP-1C engines. It addresses specific inspection protocols to ensure the integrity and safety of these critical engine components. The directive applies to operators and maintenance organizations managing aircraft equipped with these engine models.
What changed
This new directive introduces mandatory inspection procedures for the high pressure turbine rotor stage 1 blades on CFM LEAP-1A and LEAP-1C engines. It specifies inspection intervals and methods to detect potential blade damage or wear that could affect engine performance and safety. The directive does not amend previous regulations but establishes new compliance requirements.
Why it matters
This directive is important for aviation professionals because it helps prevent engine failures related to turbine blade issues, enhancing flight safety and reliability. Operators and maintenance organizations must incorporate these inspections into their maintenance programs to avoid unplanned downtime and costly repairs. Compliance ensures adherence to regulatory standards and supports continued airworthiness of affected aircraft.
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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New ADs and bulletins for CFM International LEAP-1A and International LEAP-1C, summarized like this page, every Monday.