AD 2002-21-17 Airworthiness Directives; Pratt & Whitney JT8D-200 Series Turbofan Engines

This airworthiness directive (AD) is applicable to Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 series turbofan engines that do not incorporate the fan exit guide vane case, part number (P/N) 805919 or 815377, and the improved durability and impact resistant fan duct assembly, P/N 805918-01. These engines are installed on, but not limited to McDonnell Douglas MD-80 and series airplanes. Note 1: This AD applies to each engine 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 engines 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.

Compliance with this AD is required as indicated, unless already done. To prevent the flange between the fan duct and the fan exit guide vane from separating due to a fan blade failure, which could result in damage to the airplane, do the following: Installation of Hardware (a) At the next shop visit after the effective date of this AD, install stops on the fan exit guide vane case in accordance with paragraphs 2.A. through 2.C.(1) of the Accomplishment Instructions of Pratt & Whitney (PW) service bulletin (SB) No. 6100, Revision 2, dated December 9, 1998. (b) Engines that have had stops installed using PW SB No. 6100, Revision 1 dated April 9, 1992, or original issue dated November 9, 1992, are considered to be in compliance with paragraph (a) of this AD. Definitions (c) For the purposes of this AD, a shop visit is defined as an engine removal, where engine maintenance entails separation of pairs of major mating engine flanges or the removal of a disk, hub, or spool at a maintenance facility regardless of other planned maintenance except as follows: (1) Engine removal for the purpose of performing field maintenance type activities at a maintenance facility in lieu of performing them on-wing is not a shop visit. (2) Separation of flanges of the combustion chamber and turbine fan duct assembly (split flanges) for the purpose of accessing non-rotating accessory hardware is not a shop visit. (3) Separation of flanges for the purpose of shipment without subsequent internal maintenance is not a shop visit. Alternative Methods of Compliance (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, Engine Certification Office (ECO). Operators must submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, ECO. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the ECO. Special Flight Permits (e) Special flight permits may be issued in accordance with §§ 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be done. Documents That Have Been Incorporated By Reference (f) The installations must be done in accordance with Pratt & Whitney (PW) Service Bulletin No. 6100, Revision 2, dated December 9, 1998. 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 Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-6600, fax (860) 565-4503. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC. Effective Date (g) This amendment becomes effective on November 29, 2002. Issued in Burlington, Massachusetts, on October 18, 2002. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 02-27183 Filed 10-24-02; 8:45 am] BILLING CODE 4910-13-P