AD 2004-03-14 Airworthiness Directives; Bombardier Model DHC-8-102, −103, −106, −201, −202, −301, −311, and −315 Series Airplanes

Model DHC-8-102, −103, −106, −201, −202, −301, −311, and −315 series airplanes; certificated in any category; as listed in Bombardier Service Bulletin 8-27-83, Revision ‘A’, dated May 29, 2002.

Required as indicated, unless accomplished previously. To find and fix damage and prevent subsequent failure of the rear spar fittings between the flex shaft of the flap secondary drive and the wing-to-fuselage structure, which could result in loss of the wing, accomplish the following: Repetitive Inspections/Corrective Action (a) For airplanes with rear spar fittings having part number (P/N) 85320053, 85322060, or 85334180: Within 12 months after March 16, 2004 (the effective date of AD 2004-03-14, amendment 39-13458), do a detailed inspection for discrepancies (chafing, wear damage, cracking) of the rear spar fittings located between the flex shaft of the flap secondary drive and the wing-to-fuselage structure. Do the inspection as defined in Parts III.A., III.B., and III.D. of the Accomplishment Instructions of Bombardier Service Bulletin 8-27-83, Revision ‘A’, dated May 29, 2002, except where the service bulletin specifies to report inspection findings, this AD does not require such reporting. Do the inspection per the service bulletin, and repeat the inspection thereafter at the applicable time specified in Part I.D. ‘Compliance’ of the service bulletin. Any applicable corrective action (high frequency eddy current inspection for cracking, blending out wear damage, replacement of rear spar fittings) must be done at the applicable time specified in Part I.D. ‘Compliance’ of the service bulletin. Note 1: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” Optional Terminating Modification (b) Modification of the flex shaft of the flap secondary drive per Part III.C. of the Accomplishment Instructions of Bombardier Service Bulletin 8-27-83, Revision ‘A’, dated May 29, 2002, terminates the repetitive inspections required by paragraph (a) of this AD. Actions Done per Previous Issue of Service Bulletins (c) Accomplishment of the inspections or the modification before the effective date of this AD in accordance with Bombardier Service Bulletin 8-27-83, dated October 19, 2001, is considered acceptable for compliance with the applicable actions specified in this AD. Alternative Methods of Compliance (d) In accordance with 14 CFR 39.19, the Manager, New York Aircraft Certification Office, FAA, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (e) Unless otherwise provided in this AD, the actions shall be done in accordance with Bombardier Service Bulletin 8-27-83, Revision ‘A’, dated May 29, 2002. 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 Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; at the FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New York; 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 2: The subject of this AD is addressed in Canadian airworthiness directive CF-2001-42, dated November 23, 2001. Effective Date (f) This amendment becomes effective on May 26, 2004. Issued in Renton, Washington, on April 23, 2004. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-10250 Filed 5-10-04; 8:45 am] BILLING CODE 4910-13-P