# Proposed AD FAA-2005-21175: Raytheon Aircraft Company Models 58P and 58TC Airplanes

- Type: Proposed airworthiness directive (not in force)
- Status: Became AD 2007-21-02
- Products: Raytheon
- Product type: Aircraft
- Action: Notice of proposed rulemaking (NPRM).
- Published: November 22, 2005, 70 FR 70555
- Comments due: January 23, 2006
- Became: [AD 2007-21-02](https://openairdocs.org/ad/2007-21-02)
- Docket: FAA-2005-21175 (https://www.regulations.gov/docket/FAA-2005-21175, where comments are filed)
- Project: 2005-CE-24-AD
- FR document: 05-23055
- Official PDF: https://openairdocs.org/files/sha256/43/fc/43fc44d19e8ffa78ec51268b60599adf16c038cba4dc52d352863662cba4d965 (from https://www.govinfo.gov/content/pkg/FR-2005-11-22/pdf/05-23055.pdf)
- Federal Register: https://www.federalregister.gov/documents/2005/11/22/05-23055/airworthiness-directives-raytheon-aircraft-company-models-58p-and-58tc-airplanes
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/56118717956464DE862570C1006A2099.0001
- Page: https://openairdocs.org/proposed/FAA-2005-21175

## Summary

The FAA proposes to adopt a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) Models 58P and 58TC airplanes used as a lead airplane by the United States Forest Service. This proposed AD would require you to insert a new supplement into the Limitations Section of the Pilot's Operating Handbook and Airplane Flight Manual (POH/AFM) that establishes new limits for the structural life of the airframe (wing, fuselage, empennage, or associated structure); and dispose of the life-limited airframe following 14 CFR 43.10 when the limit of the structural life of the airframe is reached. This proposed AD results from Raytheon issuing a POH/AFM supplement that establishes the structural life limit of 4,500 hours time-in- service (TIS) for the airframe (wing, fuselage, empennage, and associated structure) for any Models 58P and 58TC airplanes used as a lead airplane by the United States Forest Service; and FAA's determination that the structural life limit isnecessary. We are issuing this proposed AD to prevent cumulative fatigue damage and fatigue cracking damage that would sufficiently reduce residual strength of the airframe and result in failure. Failure of the airframe (wing, fuselage, empennage, or associated structure) could lead to loss of control of the airplane.

## Notices in this docket

- Nov 22, 2005: Notice of proposed rulemaking (NPRM). (first notice), FR document 05-23055, comments due Jan 23, 2006 (https://www.federalregister.gov/documents/2005/11/22/05-23055/airworthiness-directives-raytheon-aircraft-company-models-58p-and-58tc-airplanes)

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.