Airworthiness directives › 2025-04-13
AD 2025-04-13 Airworthiness Directives; Pratt & Whitney Engines
Models named: PW1519G, PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A engines with an installed high-pressure compressor (HPC) 7th-stage axial rotor having part number (P/N) 30G5307.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) At the next piece-part exposure after the effective date of this AD and thereafter at each piece-part exposure, except as required by paragraph (g)(2) and (4) of this AD, perform an angled ultrasonic inspection (AUSI) of the affected HPC 7th-stage axial rotor for cracks in accordance with paragraphs (g)(1)(i) or (ii) of this AD, as applicable. (i) For Model PW1500G engines: Step 7 of the Accomplishment Instructions of PW Alert Service Bulletin (ASB) PW1000G-A-72-00-0210-00A-930A-D, Issue No: 002, dated May 22, 2024 (PW1000G-A-72-00-0210-00A-930A-D, Issue No: 002), or step 5.B of the Accomplishment Instructions of PW ASB PW1000G-A-72-00-0211-00A-930A-D, Issue No: 002, dated August 1, 2024. (ii) For Model PW1900G engines: Step 7 of the Accomplishment Instructions of PW ASB PW1000G-A-72-00-0157-00B-930A-D, Issue No: 002, dated May 22, 2024 (PW1000G-A-72-00-0157-00B-930A-D, Issue No: 002), or step 5.B of the Accomplishment Instructions of PW ASB PW1000G-A-72-00-0158-00B-930A-D, Issue No: 002, dated August 1, 2024. (2) For engines with an installed HPC 7th-stage axial rotor with a serial number listed in Table 1 of PW1000G-A-72-00-0210-00A-930A-D, Issue No: 002, or Table 1 of PW1000G-A-72-00-0157-00B-930A-D, Issue No: 002, that have not had an AUSI performed prior to the effective date of this AD, at the next HPC engine shop visit after the effective date of this AD, not to exceed 10,000 part cycles since new, or within 100 flight cycles (FCs) after the effective date of this AD, whichever occurs later, and thereafter at each piece-part exposure: perform an AUSI of the HPC 7th-stage axial rotor for cracks in accordance with paragraphs (g)(1)(i) or (ii) of this AD, as applicable. (3) If any crack indication is found during any inspection required by paragraphs (g)(1) or (2) of this AD, before further flight, remove the HPC 7th-stage axial rotor from service and replace with a part eligible for installation. (4) If an HPC 7th-stage axial rotor has accumulated 100 FCs or less since the last AUSI, reinspection is not required until the next shop visit provided that the part was not damaged during removal from the engine.
Unsafe condition
This AD was prompted by an analysis of an event involving an International Aero Engines, LLC Model PW1127GA-JM engine, which experienced an HPC 7th-stage integrally bladed rotor separation that resulted in an aborted takeoff. The FAA is issuing this AD to prevent failure of the HPC 7th-stage axial rotor. The unsafe condition, if not addressed, could result in uncontained HPC 7th-stage axial rotor failure, release of high-energy debris, damage to the engine, damage to the airplane, and possible loss of the airplane.
Affected ADs
None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1