AD 2000-02-13 Airworthiness Directives; de Havilland Model DHC-8-100, -200, and -300 Series Airplanes

Models named: DHC-8-100, -200, -300 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model DHC-8-100, -200, and -300 series airplanes, certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To prevent positioning of the power levers below the flight idle stop during flight, which could cause engine overspeed, possible engine damage or failure, and consequent reduced controllability of the airplane, accomplish the following: (a) Within 30 days after the effective date of this AD, install a placard in a prominent location on the instrument panel of the cockpit that states: “Positioning of the power levers below the flight idle stop during flight is prohibited. Such positioning may lead to loss of airplane control, or may result in an engine overspeed condition and consequent loss of engine power.” (b) Within 2 years after the effective date of this AD, install a system that would prevent positioning the power levers below the flight idle stop during flight, in accordance with a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Following accomplishment of that installation, the placard required by paragraph (a) of this AD may be removed. (c) In the event that the system required by paragraph (b) of this AD malfunctions, or if the use of an override (if installed) is necessary, the airplane may be operated for three days to a location where required maintenance/repair can be performed, provided the system required by paragraph (b) of this AD has been properly deactivated and placarded for flightcrew awareness, in accordance with the FAA-approved Master Minimum Equipment List (MMEL). (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) This amendment becomes effective on March 1, 2000. Issued in Renton, Washington, on January 20, 2000. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 00-1772 Filed 1-21-00; 11:20 am] BILLING CODE 4910-13-P