AD 2007-21-02 Airworthiness Directives; Raytheon Aircraft Company Models 58P and 58TC Airplanes

Makes named: raytheon. Models named: 58P, 58TC. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Models 58P and 58TC airplanes, with the following serial numbers: TJ-177, TJ-178, TJ-180, TJ-211, TJ-213, TJ-247, TJ-284, TJ-285, TJ-289, TJ-290, TJ-314, TJ-322, TJ-367, TJ-368, TJ-370, TJ-371, TJ-425, TJ-426, TJ-433, TJ-442, and TK-33, that are certificated in any category. These airplanes were used as lead airplanes by the United States Forest Service for firefighting missions.

To address this problem, you must do the following:   Actions Compliance Procedures (1) Insert the Raytheon Model 58P/58PA and Model 58TC/58TCA POH/AFM Supplement, part number (P/N) 102-590000-67, issued January 2005, into the Limitations Section of pilot's operating handbook (POH)/airplane flight manual (AFM) (P/N 102-590000-41 or 106-590000-5). The POH/AFM Supplement limits the structural fatigue life of the airframe (wing, fuselage, empennage, and associated structure) to 4,500 hours TIS Upon the accumulation of 4,500 hours TIS on the airframe (wing, fuselage, empennage, or associated structure) or before further flight after November 15, 2007 (the effective date of this AD), whichever occurs later, unless already done Any person holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may modify the POH/AFM as specified in paragraph (e)(1) of this AD. Make an entry into the aircraft records showing compliance with this portion of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (2) Do not operate any Models 58P and 58TC airplanes (with any serial number noted in paragraph (c) of this AD) upon the accumulation of 4,500 hours TIS on the airframe (wing, fuselage, empennage, or associated structure) or before further flight, whichever occurs later As of November 15, 2007 (the effective date of this AD) Not Applicable. Note 1: 14 CFR 43.10 requires anyone who removes a life-limited part from an airplane to ensure that the part is controlled using one of the methods in paragraph (c) of the regulation. This includes a recordkeeping system, tag or record attached to part, non-permanent marking, permanent marking, segregation, mutilation, or other methods. This AD establishes the structural life limit of the affected airplanes. Anyone removing the life-limited airframe (wing, fuselage, empennage, and associated structure) from one of the affected airplanes is obligated by 14 CFR 43.10 to control the part once it is removed. Note 2: Although aircraft used in public operations are generally exempt from compliance with the Federal Aviation Regulations, the safety implications of the structural fatigue life (4,500 hours TIS) of the airframe are serious. Therefore, we strongly recommend operators of public-use-only aircraft comply with the structural fatigue life (4,500 hours TIS) of the airframe. Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Steve Potter, Aerospace Engineer, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4124; fax: (316) 946-4107. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (g) You may obtain the service information referenced in this AD from Hawker Beechcraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140. To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at http://dms.dot.gov . The docket number is FAA-2005-21175; Directorate Identifier 2005-CE-24-AD. Issued in Kansas City, Missouri, on October 3, 2007. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-19888 Filed 10-10-07; 8:45 am] BILLING CODE 4910-13-P

This AD is the result of the FAA's analysis and determination that the operational history and usage of the affected airplanes requires a reduction in the structural life limit to 4,500 hours time-in-service (TIS) for the airframe (wing, fuselage, empennage, and associated structure). The actions specified in this AD are intended to prevent structural failure of the airframe (wing, fuselage, empennage, or associated structure) based on the operational history and usage of the affected airplanes. Such failure could lead to loss of control.