2008-09-18: Wing strut attach fittings

2008-09-18 Taylorcraft, Inc.: Amendment 39-15499; Docket No. FAA- 2008-0177; Directorate Identifier 2007-CE-093-AD. Effective Date (a) This AD becomes effective on June 6, 2008. Affected ADs (b) None. Applicability (c) This AD applies to all serial numbers of Taylorcraft Models A, BC, BCS12-D, BCS, BC12-D1, BC-65, BCS12-D1, BCS-65, BC12D-85, BC12- 65 (Army L-2H), BCS12D-85, BCS12-65, BC12D-4-85, BC12-D, BCS12D-4- 85, (Army L-2G) BF, BFS, BF-60, BFS-60, BF-65, BFS-65, (Army L-2K) BF 12-65, BFS-65, BL, BLS, (Army L-2F) BL-65, BLS-65, (Army L-2J) BL12-65, BLS12-65, 19, F19, F21, F21A, F21B, F22, F22A, F22B, and F22C airplanes that are certificated in any category. Note: This AD applies to all Taylorcraft models listed above, including those models not listed in Taylorcraft Aviation, LLC Service Bulletin No. 2007-002, dated November 8, 2007. If there are any other differences between this AD and the above service bulletin, this AD takes precedence. Unsafe Condition (d) This AD results from data collected from an accident involving a Taylorcraft Model BF12-65 airplane. The wing separated from the airplane after the wing strut attach fitting failed due to corrosion. We are proposing this AD to detect and correct corrosion or cracks in the wing strut attach fittings. This condition, if not corrected, could result in failure of the wing strut attach fittings and lead to wing separation and loss of control. Compliance (e) To address this problem, you must do the following, unless already done: (1) Initially inspect the left and right wing lift strut attach fittings, part number (P/N) A-A11, for corrosion or cracking following Taylorcraft Aviation, LLC Service Bulletin No. 2007-002, dated November 8, 2007, using the following compliance times: (i) For airplanes that have never been equipped with floats or snow skis: Within the next 90 days after June 6, 2008 (the effective date of this AD). (ii) For airplanesequipped with or that have ever been equipped with floats or snow skis: Within the next 30 days after June 6, 2008 (the effective date of this AD). (2) If the airplane is equipped with floats or snow skis at the time of the initial inspection required by paragraph (e)(1) of this AD or at any time after the initial inspection required by paragraph (e)(1) of this AD, you must repeat the inspection required in paragraph (e)(1) of this AD as follows: If the following exists: Then: (i) The airplane is equipped with floats or snow skis at the time of the initial inspection required by paragraph (e)(1) of this AD. Inspect no later than 48 months following the initial inspection and repetitively inspect thereafter at intervals not to exceed 48 months. Continue these repetitive inspections until removal of floats or snow skis, at which time you must follow paragraph (e)(2)(ii) of this AD. (ii) You remove floats or snow skis at any time following the initial inspection requiredby paragraph (e)(1) of this AD. Inspect no later than 48 months following the last inspection. After the inspection following removal of floats or snow skis, no further inspections are required unless floats or snow skis are re-installed at a later date, at which time you must follow paragraph (e)(2)(iii) of this AD. (iii) You install floats or snow skis at any time since the initial inspection required by paragraph (e)(1) of this AD. Inspect no later than 48 months following the last inspection or before further flight after installation of floats or snow skis, whichever occurs later, and repetitively inspect thereafter at intervals not to exceed 48 months. Continue these repetitive inspections until removal of floats or snow skis, at which time you must follow paragraph (e)(2)(ii) of this AD. (3) If you find cracking or material loss due to corrosion during any of the inspections required in paragraph (e)(1) or (e)(2) of this AD, before further flight, do the following:(i) Contact Taylorcraft Aviation, LLC at 2124 North Central Avenue, Brownsville, Texas 78521; telephone: 956-986-0700 to obtain an FAA-approved repair scheme or replacement procedure; or refer to FAA Advisory Circular AC 43.13-1B CHG 1, dated September 27, 2001; and (ii) Repair or replace the left and/or right wing lift strut attach fitting(s), P/N A-A11. Alternative Methods of Compliance (AMOCs) (f) The Manager, Fort Worth Airplane Certification Office, 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: Andy McAnaul, Aerospace Engineer, SAT-MIDO-43, 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308-3365; fax: (210) 308-3370. 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. Material Incorporated byReference (g) You must use Taylorcraft Aviation, LLC Service Bulletin No. 2007-002, dated November 8, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Taylorcraft Aviation, LLC, 2124 North Central Avenue, Brownsville, Texas 78521; telephone: 956-986-0700. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202- 741-6030, or go to: http://www.archives.gov/federal_register/code_ of_federal_regulations/ibr_locations.html.