AD 2006-13-15 Airworthiness Directives; Mitsubishi Heavy Industries MU-2B Series Airplanes

This AD affects the following airplane models and serial numbers that are certificated in any category:   Model Serial Nos. MU-2B-10 101 through 120 (Except 102, 114, 115, and 118). MU-2B-15 114, 115, and 118. MU-2B-20 102, and 121 through 238. MU-2B-25 239 through 318 (Except 313), and 313SA. MU-2B-26 319 through 347 (Except 321), and 349SA. MU-2B-26A 321SA, 348SA, and 350SA through 394SA (Except 365SA). MU-2B-30 502 through 547. MU-2B-35 548 through 654 (Except 652), and 652SA. MU-2B-36 501, and 655 through 696 (Except 661). MU-2B-36A 661SA, and 697SA through 730SA (Except 700SA). MU-2B-40 365SA. MU-2B-60 700SA.

To address this problem, you must do the following, unless already done:   Actions Compliance Procedures (1) Remove each wing attach barrel nut, bolt, and retainer and do a visual inspection for cracks, corrosion, and fractures Within the next 200 hours time-in-service or 12 months after August 11, 2006 (the effective detailed date of this AD), whichever occurs first, unless already done Follow Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57-004A, dated March 10, 2006, as applicable. (2) If any signs of cracks, corrosion, or fractures are found on any wing attach barrel nut during the inspection required in paragraph (e)(1) of this AD, replace that wing attach barrel nut, bolt, and retainer with new parts and install to the correct torque value Before further flight after the inspection required in paragraph (e)(1) of this AD, unless already done Follow Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57-004A, dated March 10, 2006, as applicable, and the appropriate maintenance manual. (3) If no signs of cracks, corrosion, or fractures are found during the inspection required in paragraph (e)(1) of this AD, you may reuse the wing attach barrel nuts and bolts if they have been inspected and are free of deformation and irregularities in the threads and meet the minimum breakaway torque requirement. Reinstall inspected parts to the correct torque value. If the wing attach barrel nuts and bolts are not free of deformation and irregularities in the threads or do not meet the minimum breakaway torque requirement, install new parts to the correct torque value Before further flight after the inspection required in paragraph (e)(1) of this AD, unless already done Follow Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57-004A, dated March 10, 2006, as applicable, and the appropriate maintenance manual. 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 alternative methods of compliance for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (g) Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletins JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57-004A, dated March 10, 2006, pertain to the subject of this AD. Material Incorporated by Reference (h) You must do the actions required by this AD following Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletins referenced as JCAB T.C.: No. 241, dated July 14, 2004, and FAA T.C.: No. 103/57-004A, pages 1 and 4 dated March 10, 2006, pages 2, 3, 5, 6, and 7 dated August 2, 2004. 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 Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 95001; telephone: (972) 934-5480; fax: (972) 934-5488, or Turbine Aircraft Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 75001; telephone: (972) 248-3108; facsimile: (972) 248-3321. 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-2006-23578; Directorate Identifier 2006-CE-01-AD. Issued in Kansas City, Missouri, on June 19, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-5653 Filed 6-28-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from a recent safety evaluation that used a data-driven approach to evaluate the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was to identify unsafe conditions that exist or could develop on the affected type design airplanes. The actions specified in this AD are intended to detect and correct cracks, corrosion, fractures, and incorrect torque values in the wing attach barrel nuts, which could result in failure of the wing attach barrel nuts and/or associated wing attachment hardware. This failure could lead to in-flight separation of the outer wing from the center wing section and result in loss of controlled flight.