Engine — High Pressure Turbine Rotor Stage 1 Blade — Inspection
- Published
- Effective
- Deadline
- Replaces
- 2022-0009
AI-generated summary of the official EASA document. Verify against the PDF before acting.
What to do
Operators must perform initial and repetitive borescope inspections of the specified high pressure turbine rotor stage 1 blades according to the thresholds and intervals defined for their engine group. Inspections must begin based on accumulated critical departures as of 2 February 2022, with corrective actions required if discrepancies are found. Inspection results must be reported to CFM within 30 days if cracks or other issues are detected.
Summary
EASA Airworthiness Directive 2022-0009R1 is an updated safety directive addressing inspection requirements for high pressure turbine rotor stage 1 blades on CFM International LEAP-1A engines installed on certain Airbus A319, A320, and A321 aircraft. The directive mandates repetitive borescope inspections of specific turbine blades to detect cracks and prevent potential in-flight engine failures. It applies to multiple LEAP-1A engine variants and specifies affected part numbers for inspection.
What changed
This revision of EASA AD 2022-0009 reduces the number of affected part numbers requiring inspection by excluding high pressure turbine stator stage 1 nozzles from additional inspection requirements. It also updates the related CFM Service Bulletin to Issue 003 and clarifies inspection intervals and thresholds based on engine groups and accumulated critical departures.
Why it matters
This directive is critical for aviation maintenance and operations teams to prevent engine failures caused by cracked turbine blades, particularly for engines operating extensively in the Middle East and North Africa regions. Compliance ensures continued airworthiness and safety of affected aircraft, reducing the risk of in-flight shutdowns and maintaining regulatory compliance with EASA requirements.
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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