AD 2001-16-07 Airworthiness Directives; Boeing Model 747-400 and 767 Series Airplanes Equipped With General Electric CF6-80C2 Series Engines

Models named: 747-400, 767 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 747-400 and 767 series airplanes, certificated in any category, equipped with General Electric CF6-80C2 series engines; as listed in Boeing Service Bulletin 747-71-2285 or 767-71-0088, both dated October 8, 1998. 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 (c) 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 failure of the core cowl latches during an engine fire, and consequent in-flight separation of an engine core cowl and its strut fire barrier from the airplane, accomplish the following: Modification (a) Within 36 months after the effective date of this AD: Modify the left- and right-hand core cowl assemblies of the engines per the Accomplishment Instructions of Boeing Service Bulletin 747-71-2285 (for Model 747-400 series airplanes) or 767-71-0088 (for Model 767 series airplanes), both dated October 8, 1998. Note 2: The Boeing service bulletins reference ROHR Service Bulletin TBC/80C2-NAC-71-028, dated August 1, 1998, as an additional source of service information for accomplishment of the modification. Spares (b) As of 6 months after the effective date of this AD, no one may install an aluminum core cowl assembly, part number 224-2301-513 (left-hand) or 224-2302-539 (right-hand), on any airplane. Alternative Methods of Compliance (c) 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, Seattle Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA Principal Operations Inspector or Principal Maintenance Inspector, as applicable, who may add comments and then send the request and any comments to the Manager, Seattle ACO. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. Special Flight Permits (d) 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. Incorporation by Reference (e) The actions shall be done in accordance with Boeing Service Bulletin 747-71-2285, dated October 8, 1998; or Boeing Service Bulletin 767-71-0088, dated October 8, 1998; as applicable. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Effective Date (f) This amendment becomes effective on September 24, 2001. Issued in Renton, Washington, on August 10, 2001. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-20698 Filed 8-17-01; 8:45 am] BILLING CODE 4910-13-P