# Proposed AD 2003-CE-51-AD: Raytheon Aircraft Company 65, 90, 99, 100, 200, and 1900 Series Airplanes, and Models 70 and 300 Airplanes

- Type: Proposed airworthiness directive (not in force)
- Status: Became AD 2004-23-02
- Products: Raytheon
- Product type: Aircraft
- Action: Notice of proposed rulemaking (NPRM).
- Published: March 18, 2004, 69 FR 12807
- Comments due: May 18, 2004
- Became: [AD 2004-23-02](https://openairdocs.org/ad/2004-23-02)
- Docket: 2003-CE-51-AD
- FR document: 04-6113
- Official PDF: https://openairdocs.org/files/sha256/40/5b/405b1e695d9e42911ac6befc111bccb0004f5682d06012deeb603c74acca96a0 (from https://www.govinfo.gov/content/pkg/FR-2004-03-18/pdf/04-6113.pdf)
- Federal Register: https://www.federalregister.gov/documents/2004/03/18/04-6113/airworthiness-directives-raytheon-aircraft-company-65-90-99-100-200-and-1900-series-airplanes-and
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4EC0F56BB63C5E4386256E5B005BE506.0001
- Page: https://openairdocs.org/proposed/2003-CE-51-AD

## Summary

The FAA proposes to supersede Airworthiness Directive (AD) 87-22-01 R1, which applies to certain Raytheon Aircraft Company (Raytheon) 65, 90, 99, 100, 200, and 1900 series airplanes, and Models 70 and 300 airplanes. AD 87-22-01 R1 currently requires you to repetitively inspect the nose landing gear (NLG) fork for cracks. If cracks are found that exceed certain limits, AD 87-22-01 R1 requires you to replace the NLG fork with a serviceable part or an improved NLG fork (Kit No. 101-8030-1 S or Kit No. 114-8015-1 S, as applicable). Installing an improved NLG fork kit is terminating action for the repetitive inspection requirements. This proposed AD is the result of FAA's current policy to disallow airplane operation when known cracks exist in primary structure. This proposed AD would retain the inspection requirements of AD 87-22-01 R1 and would require you to incorporate an improved NLG fork kit anytime a crack is found. We are issuing this proposed AD to detect and correct cracks in the NLG fork, which could result in reduced structural integrity and inability of the NLG fork to carry design limit and ultimate loads. The reduced residual strength may cause separation failure of the NLG fork, which could result in loss of control of the airplane during take off, landing, and taxi operations.

## Notices in this docket

- Mar 18, 2004: Notice of proposed rulemaking (NPRM). (first notice), FR document 04-6113, comments due May 18, 2004 (https://www.federalregister.gov/documents/2004/03/18/04-6113/airworthiness-directives-raytheon-aircraft-company-65-90-99-100-200-and-1900-series-airplanes-and)

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