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97-19-14
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Turbine Blade / Shaft Category
- Engine Applicability: Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -17, and -17R turbofan engines, installed on but not limited to Boeing 737 and 727 series aircraft, and McDonnell Douglas DC-9 series aircraft. 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 aircraft resulting from engine debris following a low pressure turbine (LPT) blade, shaft, or hub failure, accomplish the following: (a) For engines that do not contain fan exhaust inner front duct segment assemblies that are installed in accordance with PW Alert Service Bulletin (ASB) No. 6039, Revision 3, dated October 15, 1993, or earlier revisions of PW ASB No. 6039, and either PW honeycomb third stage outer airseal Part Number (P/N) 801931, 802097, 797594, or 798279; or Pyromet Industries, Inc., honeycomb third stage outer airseal P/N PI9336; or McClain International, Inc., honeycomb third stage outer airseal P/N M2433; or a turbine case shield assembly installed in accordance with PW ASB No. 6039, Revision 3, dated October 15, 1993, or earlier revisions of PW ASB No. 6039; or a third stage blade set that has third stage turbine blades that were installed in accordance with PW SB No. 5331, dated October 27, 1982, accomplish the following: (1) Conduct initial and repetitive inspections on installed third and fourth stage LPT blade sets, and remove and replace with serviceable blade sets, as necessary, in accordance with Part 1 of the Accomplishment Instructions of PW ASB No. A5913, Revision 6, dated October 15, 1993; or PW ASB No. A5913, Revision 5, dated August 10, 1992; or PW ASB No. A5913, Revision 4, dated February 20, 1992, as follows: (i) Initially inspect the blade shroud crossnotches of the third stage LPT blade set when specified in paragraphs (a)(1)(i)(A) or (a)(1)(i)(B) of this AD, whichever occurs later. Engines that contain a third stage blade set that have third stage turbine blades that were installed per the requirements specified in PW Service Bulletin (SB) No. 5331, dated October 27, 1982, do not require the third stage blade set inspection. (A) Inspect within 6,000 cycles or 6,000 hours time in service, whichever occurs first, since new, since the last blade shroud crossnotch inspection specified in Section 72-53-12 of PW JT8D Engine Manual P/N 481672, or since last blade shroud crossnotch repair that was accomplished per the requirements specified in Section 72-53-12 of PW JT8D Engine Manual P/N 481672; or (B) Inspect within 1,000 cycles or 1,000 hours time in service since November 14, 1994, whichever occurs first. (ii) Initially inspect the blade shroud crossnotches of the fourth stage LPT blade set when specified in paragraph (a)(1)(ii)(A) or (a)(1)(ii)(B) of this AD, whichever occurs later. Engines that contain fan exhaust inner front duct segment assemblies that were installed per the requirements of PW ASB No. 6039, Revision 3, dated October 15, 1993, or earlier revisions of PW ASB No. 6039, do not require the fourth stage blade set inspection. (A) Inspect within 6,000 cycles or 6,000 hours time in service, whichever occurs first, since new, since the last blade shroud crossnotch inspection specified in Section 72-53-13 of PW JT8D Engine Manual P/N 481672, or since last blade shroud crossnotch repair that was accomplished per the requirements specified in Section 72-53-13 of PW JT8D Engine Manual P/N 481672; or (B) Inspect within 1,000 cycles or 1,000 hours time in service since November 14, 1994, whichever occurs first. (iii) Thereafter, inspect the third and fourth stage LPT blade sets in accordance with the procedures and intervals specified in PW ASB No. A5913, Revision 6, dated October 15, 1993; (2) At the next shop visit after the effective date of this AD, install the improved inner front fan exhaust duct and associated hardware in accordance with Part A of the Accomplishment Instructions of PW ASB A6110, Revision 1, dated October 15, 1993, as follows: (i) For engines that have a 4th stage LPT hub installed with a serial number listed in PW ASB A6274, Table A, dated November 7, 1996, or Revision 1, dated December 9, 1996, install the improved inner front fan exhaust duct before December 31, 1998, or 8,000 hours time in service since November 14, 1994, or 7,000 cycles in service since November 14, 1994, whichever occurs first. (ii) For engines that do not have a 4th stage LPT hub installed with a serial number listed in PW ASB A6274, Table A, dated November 7, 1996, or Revision 1, dated December 9, 1996, install the improved inner front fan exhaust duct before December 31, 1999, or 8,000 hours time in service since November 14, 1994, or 7,000 cycles in service since November 14, 1994, whichever occurs latest. (3) At the next access to the third stage turbine air sealing ring, install the improved third stage turbine air sealing ring and associated hardware in accordance with Part B of the Accomplishment Instructions of PW ASB A6110, Revision 1, dated October 15, 1993. The installation of the improved third stage turbine air sealing ring must occur no later than December 31, 1999, or 8,000 hours time in service since November 14, 1994, or 7,000 cycles in service since November 14, 1994, whichever occurs latest. Note 2: Third stage turbine outer air seal, P/N M2533, is an acceptable alternative to PW P/N 811962 for compliance with this paragraph. (4) At the next shop visit after the effective date of this AD, install the improved No. 6 bearing scavenge pump bracket bushing in accordance with the Accomplishment Instructions of PW ASB No. A6131, dated August 24, 1993, or Revision 1, dated May 16, 1995, or Revision 2, dated July 28, 1997. The installation of the improved No. 6 bearing scavenge pump bracket bushing must be accomplished no later than December 31, 1999, or 8,000 hours time in service since November 14, 1994, or 7,000 cycles since November 14, 1994, whichever occurs latest. (5) Accomplishment of the installations required by paragraphs (a)(2), (a)(3), and (a)(4) of this AD constitutes terminating action to the repetitive inspections required by paragraph (a)(1) of this AD. (b) For engines that do contain fan exhaust inner front duct segment assemblies that are installed in accordance with PW ASB No. 6039, Revision 3, dated October 15, 1993, or earlier revisions of PW ASB No. 6039, and either PW honeycomb third stage outer airseal P/N 801931, 802097, 797594, or 798279; or Pyromet Industries, Inc., honeycomb third stage outer airseal P/N PI9336; or McClain International, Inc., honeycomb third stage outer airseal P/N M2433; or a turbine case shield assembly installed in accordance with PW ASB No. 6039, Revision 3, dated October 15, 1993, or earlier revisions of PW ASB No. 6039; or a third stage blade set that has third stage turbine blades that were installed in accordance with PW SB No. 5331, dated October 27, 1982, perform the installations required by paragraphs (a)(2), (a)(3), and (a)(4) of this AD, at the times specified in those respective paragraphs. (c) For the purpose 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 that is capable of compliance with the instructions of this AD, regardless of other planned maintenance, except for field maintenance type activities performed at this maintenance facility in lieu of performing them on-wing or at another peripheral facility. (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. Operators shall forward their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 3: Information concerning the existence of approved alternative method of compliance with this AD, if any, may be obtained from the Engine Certification Office. (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 aircraft 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. A5913.......... 1-12
6.............. October
15, 1993. Total pages: 23. ASB
No. A6274.......... 1-23
Original....... November
7, 1996. Total pages: 62. This incorporation by reference of PW ASB No. A5913, Revision 6, dated October 15, 1993; and PW ASB No. A6110, Revision 1, dated October 15, 1993; was previously approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of November 14, 1994 (59 FR 51842, October 13, 1994). 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 Assistant Chief 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 October 24, 1997. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7175, fax (781) 238-7199.
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