EASA Regulations for Airbus A320neo

EASA AD US-2024-14-04

Turbine Engine Compressor Section - Low-Pressure Compressor 1st-Stage Integrally Bladed Rotor - Replacement

The Turbine Engine Compressor Section - Low-Pressure Compressor 1st-Stage Integrally Bladed Rotor - Replacement is a final rule airworthiness directive issued by the FAA affecting all International Aero Engines, LLC Model PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G1-JM, PW1127G1A-JM, PW1127G1B-JM, PW1127G-JM, PW1127GA-JM, PW1129G-JM, PW1130G-JM, PW1133G-JM, and PW1133GA-JM engines. It addresses an unsafe condition caused by fractures in the low-pressure compressor 1st-stage integrally bladed rotor (IBR-1) that led to an in-flight shutdown on an Airbus A320neo powered by these engines. The directive mandates removal and replacement of affected LPC key washers and IBR-1 parts and installation of inlet guide vane spacers to prevent recurrence.

Aug 15, 2024

Airworthiness DirectiveMaintenanceSafety MgmtInternational Aero Engines PW1100International Aero Engines PW1400Airbus A320neo

Engine - 1st-Stage Hubs and 2nd-Stage Hubs - Inspection / Replacement

The Federal Aviation Administration's Airworthiness Directive 2024-11-03 addresses certain International Aero Engines, AG Model V2500 engines installed on aircraft such as the Airbus A320neo and A321-231. This directive requires angled ultrasonic inspections and accelerated replacement of specific high-pressure turbine 1st-stage and 2nd-stage hubs due to a risk of failure caused by a nickel powdered metal anomaly. The AD aims to prevent unsafe conditions resulting from hub failures that could lead to engine shutdowns or uncontained engine debris.