EASA AD 2018-0194
Engine — High Pressure Turbine Stage 1 Turbine Blades and Blade Damper — Replacement
Summary
EASA Airworthiness Directive 2018-0194 addresses the replacement of high pressure turbine stage 1 blades and blade dampers on Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 engines, commonly installed on Boeing 717 aircraft. The directive mandates inspection and replacement of affected turbine blade assemblies to prevent potential blade failure. It applies to all manufacturer serial numbers of these engine models.
What Changed
This new airworthiness directive introduces mandatory determination of flight cycles on affected turbine blade assemblies and requires replacement of these assemblies before exceeding 10,000 flight cycles or within specified shorter intervals. It also defines engine groups based on assembly condition and flight mission, specifying different compliance requirements accordingly. The directive incorporates instructions from Rolls-Royce Deutschland service bulletins for the replacement process.
Why It Matters
This directive is critical for aviation professionals because it addresses a safety risk involving sulphidation-induced cracking and failure of high pressure turbine blades, which could lead to engine in-flight shutdowns and reduced aircraft control. Operators and maintenance organizations must ensure compliance to maintain airworthiness and avoid unscheduled engine removals or incidents. Compliance teams need to track affected engines and assemblies to meet the directive's deadlines and avoid regulatory violations.
What To Do
Operators must determine the flight cycles of affected turbine blade assemblies within 30 days of the directive's effective date. Engines with affected assemblies must be removed from service and have the assemblies replaced before exceeding 10,000 flight cycles or within 50 flight cycles after the effective date, whichever is later. Engines previously inspected under a related service bulletin have a different compliance window of 1,500 flight cycles or 10 flight cycles after the effective date. Installation of only serviceable assemblies is permitted after modification.
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