Engine – Forward Outer Seal, High-Pressure Compressor Stages 6-10 Compressor Rotor Spools and High-Pressure Turbine Rotor Stage 1 Disks – Replacement
Superseded. Comply with 2025-0243, which replaces this document.
- Published
- Effective
- Replaces
- 2023-0108
AI-generated summary of the official EASA document. Verify against the PDF before acting.
What to do
Operators must replace all affected parts on Group 1 engines within the compliance times specified in the service bulletins or within 50 engine cycles after 10 December 2024, whichever is later. From the effective date, no affected parts may be installed on any engine. Compliance with the replacement instructions in the referenced CFM service bulletins is mandatory.
Summary
EASA Airworthiness Directive 2024-0225 is an airworthiness directive addressing certain CFM International LEAP-1A engine models installed on Airbus A319, A320, and A321 aircraft. It mandates the replacement of forward outer seals, high-pressure compressor stages 6-10 compressor rotor spools, and high-pressure turbine rotor stage 1 disks that are affected by manufacturing defects. The directive aims to ensure continued airworthiness and prevent potential engine part failures.
What changed
This directive supersedes EASA AD 2023-0108 and expands the scope by identifying additional affected parts requiring replacement. It incorporates new service bulletin instructions from CFM International for the replacement of these newly identified parts and prohibits the installation of any affected parts from the effective date.
Why it matters
The directive addresses a critical safety concern where iron inclusions in certain engine parts may reduce mechanical properties and lead to premature failure. For operators, maintenance, repair, and overhaul organizations, and compliance teams, this means ensuring affected parts are replaced promptly to prevent engine damage and maintain aircraft safety and regulatory compliance.
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
Get the next one by email
New ADs and bulletins for CFM International LEAP-1A and International LEAP-1C, summarized like this page, every Monday.