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AD 2024-14936

Published 2024-07-09 · 1 model · 2 US-registered tails affected · Federal Register

Airworthiness Directives; Pratt & Whitney Engines Federal Register ↗

Abstract

The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) Model PW2037, PW2037M, and PW2040 engines with a certain high-pressure turbine (HPT) 2nd stage blade assembly installed. This AD was prompted by an in-flight shutdown (IFSD) caused by the fracture of HPT 2nd stage turbine hub assembly lugs, which resulted in blade liberation and a titanium fire in the high-pressure compressor (HPC). This AD requires a visual inspection of the HPT 2nd stage blade assemblies for missing contact marks, a dimensional shadowgraph inspection of the HPT 2nd stage blade assemblies for blade root profile dimensional deviations, and an eddy current inspection (ECI) of the HPT 2nd stage turbine hub assembly for conforming slot flatness. This AD also requires removal from service and replacement of any HPT 2nd stage turbine hub assembly or HPT 2nd stage blade assembly that does not pass any inspection. The FAA is issuing this AD to address the unsafe condition on these products.

Applicability · by US fleet size

Federal Register text

Verbatim; the Federal Register publication is the legally binding document. Cite: 89 FR 56198. View on Federal Register ↗

[Federal Register Volume 89, Number 131 (Tuesday, July 9, 2024)] [Rules and Regulations] [Pages 56198-56203] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 2024-14936]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-1640; Project Identifier AD-2022-00283-E; Amendment 39-22768; AD 2024-12-04] RIN 2120-AA64

Airworthiness Directives; Pratt & Whitney Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) Model PW2037, PW2037M, and PW2040 engines with a certain high-pressure turbine (HPT) 2nd stage blade assembly installed. This AD was prompted by an in-flight shutdown (IFSD) caused by the fracture of HPT 2nd stage turbine hub assembly lugs, which resulted in blade liberation and a titanium fire in the high-pressure compressor (HPC). This AD requires a visual inspection of the HPT 2nd stage blade assemblies for missing contact marks, a dimensional shadowgraph inspection of the HPT 2nd stage blade assemblies for blade root profile dimensional deviations, and an eddy current inspection (ECI) of the HPT 2nd stage turbine hub assembly for conforming slot flatness. This AD also requires removal from service and replacement of any HPT 2nd stage turbine hub assembly or HPT 2nd stage blade assembly that does not pass any inspection. The FAA is issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective August 13, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 13, 2024.