Airworthiness Directive · Amendment 39-22971 · Turbine engine compressor section
Pratt & Whitney Engines
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.
The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G- 3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A engines with a certain high-pressure compressor (HPC) 7th-stage axial rotor installed. This AD was prompted by an analysis of an event involving an International Aero Engines, LLC (IAE LLC) Model PW1127GA-JM engine, which experienced an HPC 7th-stage integrally bladed rotor (IBR-7) separation that resulted in an aborted takeoff. This AD requires performing initial and repetitive angled ultrasonic inspections (AUSI) of certain HPC 7th-stage axial rotors for cracks and replacing the HPC 7th-stage axial rotors if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
(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.
For the purpose of this AD:
(1) “Model PW1500G” engines are PW Model PW1519G, PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3, PW1525G, and PW1525G-3 engines.
(2) “Model PW1900G” engines are PW Model PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A engines.
(3) A “part eligible for installation” is any of the following:
(i) An HPC 7th-stage axial rotor, P/N 30G5307, that has passed the AUSI required by paragraphs (g)(1) or (2) of this AD.
(ii) An HPC 7th-stage axial rotor, P/N 30G5307, that has a Certificate of Conformance that shows compliance with NDIP-1281.
(iii) An HPC 7th-stage axial rotor that has a later approved P/N.
(iv) A new zero-time HPC 7th-stage axial rotor, P/N 30G5307, that has passed an AUSI at new part production.
Note 1 to paragraph (h)(3)(iv): Parts that have been inspected at new part production are identified in the original manufacturing record for the part and may be obtained using PW's Vital Statistics Logbook look up tool.
(4) A “piece-part exposure” is when the HPC 7th-stage axial rotor is disassembled from the rotor assembly.
(5) An “HPC engine shop visit” is when the HPC rotor assembly is removed from the HPC module.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
