AD 2004-06-08 Airworthiness Directives; Bombardier Model DHC-8-401 and -402 Airplanes

Models named: DHC-8-401, -402. Read the applicability below — it usually turns on serial or part numbers too.

Model DHC-8-401 and -402 airplanes; certificated in any category; serial numbers 4005, 4006, 4008 through 4016 inclusive, and 4018 through 4058 inclusive.

Required as indicated, unless accomplished previously. To prevent a short circuit on the aileron/rudder trim control panel that could cause a runaway condition of the rudder trim actuator, which could result in reduced controllability of the airplane, accomplish the following: Modification, Inspection, and Corrective Action (a) Within 90 days after the effective date of this AD, do the actions in paragraphs (a)(1) and (a)(2) of this AD, per the Accomplishment Instructions of Bombardier Alert Service Bulletin A84-27-13, Revision “B,” dated January 12, 2002. (1) Modify the wiring of the rudder trim switch. (2) Before further flight after accomplishing the modification required by paragraph (a)(1) of this AD: Perform a one-time general visual inspection of all wiring on the back of the aileron/rudder trim control panel for chafing. Before further flight, replace any chafed wiring with new wiring. Note 1: For the purposes of this AD, a general visual inspection is defined as: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.” Previously Accomplished Actions (b) Modifications and inspections accomplished before the effective date of this AD per Bombardier Alert Service Bulletin A84-27-13, Revision “A,” dated January 9, 2002, are acceptable for compliance with the corresponding actions required by paragraph (a) of this AD. Parts Installation (c) As of the effective date of this AD, no person may install aileron/rudder trim control panel having part number 82410608-005 on any airplane, unless the control panel has been modified and inspected per the requirements of this AD. Alternative Methods of Compliance (d) In accordance with 14 CFR 39.19, the Manager, New York Aircraft Certification Office (ACO), FAA, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (e) Unless otherwise specified in this AD, the actions shall be done in accordance with Bombardier Alert Service Bulletin A84-27-13, Revision “B,” dated January 12, 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, Westbury, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 2: The subject of this AD is addressed in Canadian airworthiness directive CF-2002-15, dated February 20, 2002. Effective Date (f) This amendment becomes effective on April 29, 2004. Issued in Renton, Washington, on March 12, 2004. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-6501 Filed 3-24-04; 8:45 am] BILLING CODE 4910-13-P