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- FAA-2025-02932
FAA-2025-02932
Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes
Resumo Rápido
- Número AD
- FAA-2025-02932
- Autoridade
- FAA
- Data de emissão
- 24/02/2025
- Data efetiva
- —
- Criticidade
- routine
Autoridade
Federal Aviation Administration (EUA)
Data de Publicação
24 de fevereiro de 2025
Data Efetiva
Não informada
Prazo de Cumprimento
Antes do próximo voo
Resumo da Diretiva
A FAA propõe substituir a Diretiva de Aeronavegabilidade (DA) 2023-26-05, que se aplica a certos aviões modelo PC-24 da Pilatus Aircraft Ltd. (Pilatus). A DA 2023-26-05 requer a substituição periódica de pernos roscados de titânio afetados, inspeção única do braço de contrapeso do leme e outros elementos da instalação do compensador de trim do leme quanto ao correto acoplamento, dano (riscos), trincas, deformação, acabamento de superfície e corrosão em quaisquer peças adjacentes e, conforme os achados, a realização de ações corretivas aplicáveis. Desde que a FAA emitiu a DA 2023-26-05, foi determinado que alguns lotes de pernos de titânio apresentavam variações na microestrutura que poderiam afetar as características de fadiga. Esta DA proposta exigiria a substituição de conjuntos de hastes de comando de trim do leme curtas afetados por conjuntos de hastes de comando de trim do leme em condições de aeronavegabilidade equipados com pernos roscados de aço, e proibiria a instalação de peças afetadas, conforme especificado em uma DA da Agência de Segurança da Aviação da União Europeia (EASA), que é proposta para incorporação por referência. A FAA está propondo esta DA para resolver a condição insegura destes produtos.
The FAA proposes to supersede Airworthiness Directive (AD) 2023-26-05, which applies to certain Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. AD 2023-26-05 requires periodic replacement of affected titanium threaded bolts, a one-time inspection of the rudder mass balance arm and other elements of the rudder trim tab installation for correct attachment, damage (gouges), cracks, deformation, surface finish, and corrosion on any surrounding parts and, depending on findings, the accomplishment of applicable corrective actions. Since the FAA issued AD 2023-26-05, it was determined that some batches of titanium bolts had variations in the microstructure that could affect the fatigue characteristics. This proposed AD would require replacing affected short rudder-trim control rod assemblies with serviceable rudder-trim control rod assemblies having threaded steel bolts and would prohibit the installation of affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference. The FAA is proposing this AD to address the unsafe condition on these products.Texto Completo da Diretiva
Expandir texto completo (Federal Register)Texto completo (Federal Register)
Document Headings Document headings vary by document type but may contain the following: • the agency or agencies that issued and signed a document • the number of the CFR title and the number of each part the document amends, proposes to amend, or is directly related to • the agency docket number / agency internal file number • the RIN which identifies each regulatory action listed in the Unified Agenda of Federal Regulatory and Deregulatory Actions See the Document Drafting Handbook for more details. Department of Transportation Federal Aviation Administration • 14 CFR Part 39 • [Docket No. FAA-2025-0208; Project Identifier MCAI-2024-00555-A] • RIN 2120-AA64 AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 2023-26-05, which applies to certain Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. AD 2023-26-05 requires periodic replacement of affected titanium threaded bolts, a one-time inspection of the rudder mass balance arm and other elements of the rudder trim tab installation for correct attachment, damage (gouges), cracks, deformation, surface finish, and corrosion on any surrounding parts and, depending on findings, the accomplishment of applicable corrective actions. Since the FAA issued AD 2023-26-05, it was determined that some batches of titanium bolts had variations in the microstructure that could affect the fatigue characteristics. This proposed AD would require replacing affected short rudder-trim control rod assemblies with serviceable rudder-trim control rod assemblies having threaded steel bolts and would prohibit the installation of affected parts, as ( printed page 10468) specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this NPRM by April 10, 2025. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493-2251. • Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA-2025-0208; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the mandatory continuing airworthiness information (MCAI), any comments received, and other information. The street address for Docket Operations is listed above. Material Incorporated by Reference: • For EASA material identified in this proposed AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email:ADs@easa.europa.eu; website: easa.europa.eu. You may find this material on the EASA website at ad.easa.europa.eu. It is also available at regulations.gov under Docket No. FAA-2025-0208. • You may view this material at the FAA…
Fonte: Federal Register (federalregister.gov). Texto original em inglês. Conteúdo sanitizado por segurança.
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