AD 2004-13-08 Airworthiness Directives; Short Brothers Model SD3-60 Series Airplanes

Models named: SD3-60 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model SD3-60 series airplanes, certificated in any category.

Required as indicated, unless accomplished previously. To prevent the loss of the balance weight for the elevator trim tab, which could result in incorrect trim during takeoff and landing, and reduced controllability of the airplane, accomplish the following: Service Bulletin Reference (a) The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003. Initial Inspection (b) Within 2 months after the effective date of this AD: Do a dye penetrant inspection for cracking in the welded joints of the balance weight brackets for the left and right elevator trim tabs, in accordance with the service bulletin. Investigative and Corrective Actions if No Cracking Is Found (c) If no cracking is found during the inspection required by paragraph (b) of this AD, do the actions required by paragraphs (c)(1) and (c)(2) of this AD at the applicable compliance times. (1) Repeat the inspection required by paragraph (b) of this AD at intervals not to exceed 4,800 flight hours until the bracket is replaced per paragraph (c)(2) or (d) of this AD. (2) Prior to the accumulation of 28,800 total flight hours, or within 6 months after the effective date of this AD, whichever occurs later: Replace any bracket that has not been replaced per paragraph (d) of this AD with a new bracket or with a serviceable bracket that has been inspected in accordance with paragraph (b) of this AD. Replace in accordance with the service bulletin. Replacement of the brackets constitutes terminating action for the repetitive inspections required by paragraph (c)(1) of this AD. Corrective Actions if Any Cracking Is Found (d) If any cracking is found during any inspection required by paragraph (b) or (c) of this AD: Before further flight, accomplish the applicable action in paragraph (d)(1) or (d)(2) of this AD in accordance with the service bulletin. (1) For airplanes that have accumulated less than 28,800 flight hours and on which all cracking on brackets is less than 0.25 inch in length: Repair the affected bracket in accordance with Part B of the service bulletin (including the additional dye penetrant inspection of the repaired welded joint) and repeat the inspection required by paragraph (b) of this AD at intervals not to exceed 4,800 flight hours; or replace the bracket in accordance with paragraph (d)(2) of this AD. Replacement of the bracket constitutes terminating action for the repetitive inspections. (2) For any airplane on which any cracking on a bracket is 0.25 inch in length or greater, and for any airplane that has accumulated 28,800 flight hours or more on which any cracking of any length is found on a bracket: Replace the affected bracket with a new bracket or with a serviceable bracket that has been inspected in accordance with paragraph (b) of this AD. Replacement of the bracket constitutes terminating action for the repetitive inspections required by paragraph (d)(1) of this AD. Refitting (e) Before further flight following any inspection per paragraphs (b) or (c) of this AD; or before further flight following repair or replacement of a bracket per paragraphs (c)(2) or (d) of this AD: Refit the balance weights, covers, and trim tabs, in accordance with the service bulletin. Where the service bulletin specifies to contact the manufacturer for disposition of certain conditions while refitting, obtain further disposition instructions from the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Civil Aviation Authority (CAA) (or its delegated agent). Parts Installation (f) As of the effective date of this AD, no person may install on any airplane a balance weight bracket unless the welded joint has been inspected in accordance with paragraph (b) of this AD. Alternative Methods of Compliance (g) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (h) Unless otherwise specified in this AD the actions shall be done in accordance with Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Short Brothers, Airworthiness & Engineering Quality, P.O. Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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. Note 1: The subject of this AD is addressed in British airworthiness directive 009-06-2003. Effective Date (i) This amendment becomes effective on August 3, 2004. Issued in Renton, Washington, on June 16, 2004. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-14321 Filed 6-28-04; 8:45 am] BILLING CODE 4910-13-P