99-22-14: High Pressure Turbine Shaft

99-22-14 PRATT & WHITNEY: Amendment 39-11392. Docket 92-ANE-15. Supersedes AD 93-23-10, Amendment 39-8746. Issued October 21, 1999. Applicability: Pratt & Whitney (PW) Model JT8D-209, -217, -217A, -217C, and -219 turbofan engines, installed on but not limited to McDonnell Douglas MD-80 series airplanes. NOTE 1: This airworthiness directive (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: Required as indicated, unless accomplished previously. To prevent damage to the airplane resulting from uncontained engine debris following a high pressure turbine (HPT) shaft fracture or a low pressure turbine (LPT) blade failure, accomplish the following: (a) For PW Model JT8D-217C and -219 engines, install improved HPT containment hardware at the next shop visit after the effective date of this AD, but no later than December 31, 2004, in accordance with PW JT8D Alert Service Bulletin (ASB) No. A6346, dated September 10, 1998, or Revision 1, dated April 23, 1999. (b) For PW Model JT8D-209, -217, -217A, -217C and -219 engines, install improved LPT-to-turbine exhaust case bolts and nuts at the next shop visit after the effective date of this AD but no later than December 31, 2004, in accordance with paragraph 2.A.(1) and 2.B.(1) of PW Service Bulletin (SB) No. 6149, January 19, 1994, or Revision 1, dated August 27, 1998. (c) For the purpose of this AD, an engine shop visit is defined as engine maintenance that entails the separation of the J and K flanges. (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 shall submit their requests 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 method of compliance with this AD, if any, may be obtained from the ECO. (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) The actions required by this AD shall be done in accordance with the following PW service documents: Document No. Pages Revision Date ASB No. A6346 1,2 1 April 23, 1999 3 Original September 10, 1998 4 1 April 23, 1999 5,6 Original September 10, 1998 7-25 1 April 23, 1999 Total pages: 25 ASB No. A6346 1-23 Original September 10, 1998 Total pages: 23 SB No. 6149 1-3 1 August 27, 1998 4-10 Original January 19, 1994 Total pages: 10 SB No. 6149 1-10 Original January 19, 1994 Total pages: 10 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, Publications Department, Supervisor Technical Publications Distribution, M/S 132-30, 400 Main St., East Hartford, CT 06108; telephone (860) 565-8770, 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. (g) This amendment becomes effective on December 28, 1999.