AD 2006-22-08 Airworthiness Directives; Air Tractor, Inc. Models AT-602, AT-802, and AT-802A Airplanes

Models named: AT-602, AT-802, AT-802A. Read the applicability below — it usually turns on serial or part numbers too.

This AD affects all Models AT-602, AT-802, and AT-802A airplanes, all serial numbers, that are certificated in any category.

To address this problem, you must do the following:   Actions Compliance Procedures (1) Visually inspect the engine mount for any cracks Initially inspect upon accumulating 4,000 hours time-in-service (TIS) or within the next 100 hours TIS after December 1, 2006 (the effective date of this AD), whichever occurs later, unless already done. Thereafter, repetitively inspect every 300 hours TIS Follow Snow Engineering Co. Service Letter #253, dated December 12, 2005. (2) If you find any crack damage, do one of the following: (i) Obtain an FAA-approved repair scheme and incorporate this repair scheme; or (ii) Replace the engine mount with a new engine mount. Before further flight after any inspection required by paragraph (e)(1) of this AD where crack damage is found. If you repair the cracked engine mount, then continue to reinspect at intervals not to exceed 300 hours TIS, unless the repair scheme states differently. If you replace the engine mount, then initially inspect upon accumulating 4,000 hours TIS and repetitively at intervals not to exceed 300 hours TIS thereafter For obtaining a repair scheme: Follow Snow Engineering Co. Service Letter #253, dated December 12, 2005. For the replacement: The maintenance manual includes instructions for the replacement. (3) Report any cracks that you find to the FAA at the address specified in paragraph (f) of this AD. Include in your report: (i) Airplane serial number; (ii) Airplane and engine mount hours TIS; (iii) Crack location(s) and size(s); (iv) Corrective action taken; and (v) Point of contact name and telephone number. Within the next 10 days after you find the cracks or within the next 10 days after December 1, 2006 (the effective date of this AD), whichever occurs later The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act and assigned OMB Control Number 2120-0056. Alternative Methods of Compliance (AMOCs) (f) The Manager, Fort Worth Airplane Certification Office, FAA, Attn: Andrew McAnaul, Aerospace Engineer, ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308-3365; facsimile: (210) 308-3370, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (g) You must do the actions required by this AD following the instructions in Snow Engineering Co. Service Letter #253, dated December 12, 2005. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564-5616; facsimile: (940) 564-5612. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2006-24228; Directorate Identifier 2006-CE-22-AD. Issued in Kansas City, Missouri, on October 13, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-17828 Filed 10-26-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of cracked engine mounts. We are issuing this AD to detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane.