Engine - Turbine Compressor Discharge Pressure Bolted Joint - Inspection
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AI-generated summary of the official EASA document. Verify against the PDF before acting.
What to do
Affected operators must perform initial and repetitive inspections of the CDP bolted joint as specified, and if damage is found, conduct piece part inspections of key engine components. The CDP bolted joint must be reassembled using the specified 11C4888P01 torque wrench as a terminating action. Compliance with this directive is required by March 21, 2022.
Summary
The Federal Aviation Administration (FAA) Airworthiness Directive 2022-03-16 addresses certain General Electric Company GEnx-1B and GEnx-2B model turbofan engines. It mandates inspections of the compressor discharge pressure (CDP) bolted joint due to findings of sheared CDP bolts during engine shop visits, which could cause damage to critical engine components. The directive also requires reassembly of the CDP bolted joint using a specified torque wrench to ensure safety.
What changed
This new airworthiness directive introduces initial and repetitive inspections of the CDP bolted joint on affected GE GEnx-1B and GEnx-2B engines. Depending on inspection results, it requires piece part inspections of the stages 6-10 compressor rotor spool, CDP seal, and high-pressure turbine rotor stage 1 disk. As a terminating action, it mandates reassembly of the CDP bolted joint using the updated 11C4888P01 torque wrench to prevent over-torque conditions.
Why it matters
This directive is critical for aviation professionals as it addresses a safety risk caused by sheared CDP bolts that can damage vital engine components, potentially leading to engine failure. Operators and maintenance organizations must comply to maintain engine airworthiness and avoid costly repairs or operational disruptions. The directive ensures consistent use of proper torque tools, reducing the risk of bolt fractures during assembly.
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- EASA AD US-2024-25-07Engine - Stages 6-10 Compressor Rotor Spools - InspectionJan 14, 2025
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