2000-16-12: High Pressure Compressor Rotor Stage 3-9 Spools

2000-16-12 General Electric Company: Amendment 39-11868 Docket 2000-NE-31-AD. Applicability \n\tThis airworthiness directive is applicable to General Electric Company (GE) CF6-45, -50, -80A, -80C2, and -80E1 turbofan engines with high pressure compressor rotor stage 3-9 spools with the following part numbers (P/N's). These engines are installed on, but not limited to, Airbus A300, A310, and A330 series, Boeing 747 and 767 series, and McDonnell Douglas DC-10 and MD-11 series airplanes. \n\n\nEngine Model\n\n\n\nHPCR 3-9 Spool P/N\nCF6-45/50 Series Engines\n9136M89G02, 9136M89G08, 9136M89G19, 9273M14G01,\n9136M89G03, 9136M89G09, 9136M89G21, 9331M29G01,\n9136M89G06, 9136M89G17, 9136M89G22, 9253M85G01,\n9136M89G07, 9136M89G18, 9136M89G27, 9253M85G02\nCF6-80A Series Engines\n9136M89G10, 9136M89G22,\n9136M89G11, 9136M89G27\n9136M89G20, \n9136M89G21, \nCF6-80C2 Series Engines\n1333M66G01, 1781M52P01, 1854M95P03, 1854M95P07,\n1333M66G03, 1781M53G01, 1854M95P04, 9380M28P05\n1333M66G07, 1854M95P01, 1854M95P05, \n1333M66G09, 1854M95P02, 1854M95P06, \nCF6-80E1 Series Engines\n1669M22G01,\n1669M22G03,\n1782M22G01,\n1782M22G02\n\n\tNote 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 (j) 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.\n\nCompliance\n\tCompliance with this AD is required as indicated below, unless already done.\n\tTo detect cracks which can cause separation of the HPCR stage 3-9 spool and result in an uncontained engine failure, perform the following inspections:\n\nCF6-45/50 Series Engines\n\t(a)\tFor HPCR stages 3-9 spools installed in CF6-45/50 series engines that have not been inspected in accordance with AD 99-24-15, do the following:\n\n\nNumber of Cycles-Since-New (CSN)\nAction\nBy the earliest of\n(1)\tMore than 7,000 CSN but fewer than 10,500 CSN after the effective date of this AD.\nEddy current and ultrasonic inspect bores for cracks in accordance with ASB 72-A1108, Revision 3, dated November 12, 1999.\n(i)\tWithin the next 1,000 cycles-in-service (CIS) after the effective date of this AD, OR\n\n(ii)\tAt the next engine shop visit (ESV) after the effective date of the AD, OR\n\n(iii)\tBefore July 29, 2001.\n(2)\t10,500 or more CSN, after the effective date of this AD, on HPCR 3-9 spools P/N 9136M89G02, 9136M89G03, 9136M89G06, 9136M89G07, 9136M89G08, 9136M89G09, 9136M89G17, 9136M89G18, 9273M14G01, 9331M29G01, 9253M85G01, 9253M85G02.\nEddy current and ultrasonic inspect bores for cracks in accordance with ASB 72-A1108, Revision 3, dated November 12, 1999.\n(i)\tWithin the next 500 CIS after the effective date of this AD, OR\n\n(ii)\tAt the next ESV after the effective date of the AD, OR\n\n(iii)\tBefore May 31, 2001.\n(3)\t10,500 or more CSN, after the effective date of this AD, on HPCR 3-9 spools P/N 9136M89G19, 9136M89G21, 9136M89G22, 9136M89G27\nReplace with a serviceable HPCR 3-9 spool.\n(i)\tWithin the next 500 CIS after the effective date of this AD, OR\n\n(ii)\tAt the next ESV after the effective date of the AD, OR\n\n(iii)\tBefore May 31, 2001.\n\n\t(b)\tRemove any HPCR 3-9 spool from service that equals or exceeds the reject criteria established by ASB 72-A1108, Revision 3, dated November 12, 1999; and replace it with a serviceable spool before further flight.\n\nCF6-80A Series Engines\n\t(c)\tFor HPCR stages 3-9 spools installed in CF6-80A series engines that have not been inspected inaccordance with AD 99-24-15, do the following:\n\n\nNumber of Cycles-Since-New (CSN)\nAction\nBy the earliest of\n(1)\tMore than 7,000 CSN but fewer than 10,500 CSN, after the effective date of this AD.\nEddy current and ultrasonic inspect bores for cracks in accordance with ASB 72-A0678, Revision 3, dated November 12, 1999.\n(i)\tWithin the next 1,000 CIS after the effective date of this AD, OR\n\n(ii)\tAt the next ESV after the effective date of the AD, OR\n\n(iii)\tBefore July 29, 2001.\n(2)\t10,500 or more CSN, after the effective date of this AD, on HPCR 3-9 spools P/N 9136M89G10, 9136M89G11.\nEddy current and ultrasonic inspect bores for cracks in accordance with ASB 72-A0678, Revision 3, dated November 12, 1999.\n(i)\tWithin the next 500 CIS after the effective date of this AD, OR\n\n(ii)\tAt the next ESV after the effective date of the AD, OR\n\n(iii)\tBefore May 31, 2001.\n(3)\t10,500 or more CSN, after the effective date of this AD, on HPCR 3-9 spools P/N 9136M89G20, 9136M89G21, 9136M89G22, 9136M89G27\nReplace with a serviceable HPCR 3-9 spool.\n(i)\tWithin the next 500 CIS after the effective date of this AD, OR\n\n(ii)\tAt the next ESV after the effective date of the AD, or\n\n(iii)\tBefore May 31, 2001.\n\t\n\t(d)\tRemove any HPCR 3-9 spool from service that equals or exceeds the reject criteria established by ASB 72-A0678, Revision 3, dated November 12, 1999, and replace it with a serviceable spool before further flight.\n\nCF6-80C2 Series Engines\n\t(e)\tFor HPCR stages 3-9 spools installed in CF6-80C2 series engines that have not been inspected in accordance with both ASB 72-A0812, Revision 2, dated October 28, 1999; and ASB 72-A0848, Revision 5, dated August 3, 2000; or AD 99-24-15, do the following:\n\n\nNumber of Cycles-Since-New (CSN)\nAction\nBy the earliest of\n(1)\tMore than 7,000 CSN but fewer than 10,500 CSN, after the effective date of this AD.\nEddy current and ultrasonic inspect the bores and webs for cracks in accordance with ASB 72-A0812, Revision 2, dated October 28, 1999; and ASB 72-A0848, Revision 5, dated August 3, 2000.\n(i)\tWithin the next 1,000 CIS after the effective date of this AD, OR\n\n(ii)\tAt the next ESV after the effective date of the AD, OR\n\n(iii)\tBefore July 29, 2001.\n(2)\t10,500 or more CSN, after the effective date of this AD.\nReplace with a serviceable HPCR 3-9 spool.\n(i)\tWithin the next 500 CIS after the effective date of this AD, OR\n\n(ii)\tAt the next ESV after the effective date of the AD, OR\n\n(iii)\tBefore May 31, 2001.\n\n\t(f)\tRemove any HPCR 3-9 spool from service that equals or exceeds the reject criteria established by ASB 72-A0812, Revision 2, dated October 28, 1999; and ASB 72-A0848, Revision 5, dated August 3, 2000, and replace it with a serviceable spool before further flight.\n\nCF6-80E1 Series Engines\n\t(g)\tFor HPCR stages 3-9 spools installed in CF6-80E1 series engines that have not been inspected in accordance with both ASB 72-A0135, Revision 1, dated October 28, 1999; and ASB 72-A0126, Revision 3, dated August 3, 2000; or AD 99-24-15, do the following:\n\n\nNumber of Cycles-Since-New (CSN)\nAction\nBy the earliest of\n\t(1)\tMore than 7,000 CSN but fewer than 10,500 CSN, after the effective date of this AD.\nEddy current and ultrasonic inspect the bores and webs for cracks in accordance with ASB 72-A0126, Revision 3, dated August 3, 2000, and ASB 72-A0135, Revision 1, dated October 28, 1999.\n\t(i)\tWithin the next 1,000 CIS after the effective date of this AD,OR\n\t(ii)\tAt the next ESV after the effective date of the AD, OR\n\t(iii)\tBefore July 29, 2001.\n\t(2)\t10,500 or more CSN after the effective date of this AD.\nReplace with a serviceable HPCR 3-9 spool.\n\t(i)\tWithin the next 500 CIS after the effective date of this AD, OR\n\t(ii)\tAt the next ESV after the effective date of the AD, OR\n\t(iii)\tBefore May 31, 2001.\n\n\t(h)\tRemove any HPCR 3-9 spool from service before further flight that equals or exceeds the reject criteria established by ASB 72-A0135, revision 1, dated October 28, 1999; or ASB 72-A0126, revision 3, dated August 3, 2000, and replace it with a serviceable spool.\n\nDefinitions\n\t(i)\tFor the purpose of this AD, an ESV is defined as any time an engine is introduced into a shop for the separation of a major engine flange.\n\nAlternative Methods of Compliance\n\t(j)\tAn 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.\n\n\tNote 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the ECO.\n\nSpecial Flight Permits\n\t(k)\tSpecial 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 accomplished.\n\t(l)\tThe inspection shall be done in accordance with the following GE Alert Service Bulletins:\n\n\n\nDocument No.\nPages\nRevision\nDate\nGE CF6-50 ASB No. 72-A1108\n1-15\n3\nNovember 12, 1999\n\n\n\n\tTotal pages: 15\nGE CF6-80A ASB No. 72-A0678\n1-18\n3\nNovember 12, 1999\n\n\n\n\tTotal pages: 18\nGE CF6-80C2 ASB No. 72-A0812\n1-13\n2\nOctober 28, 1999\n\n\n\n\tTotal pages: 13\nGE CF6-80C2 ASB No. 72-A0848\n1-47\n5\nAugust 3, 2000\n\n\n\n\tTotal pages: 47\nGE CF6-80E1 ASB No. 72-A0126\n1-47\n3\nAugust 3, 2000\n\n\n\n\tTotal pages: 47\nGE CF6-80E1 ASB No. 72-A0135\n1-11\n1\nOctober 28, 1999\n\n\n\n\tTotal pages: 11\n\n\tThe incorporations by reference of ASB's No. CF6-50 72-A1108, Revision 3; CF6-80A 72-A0678, Revision 3; CF6-80C2 72-A0812, Revision 2; and CF6-80E1 72-A0135, Revision 1, were approved by the Director of the Federal Register on January 28, 2000 (64 FR 66554; November 29, 1999).The incorporations by reference of ASB's CF6-80C2 72-A0848, Revision 5; and CF6-80E1 72-A0126, Revision 3 were approved by the Director of the Federal Register on September 5, 2000 in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672-8400, fax (513) 672-8422. 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.\n\t(m)\tThis amendment becomes effective on September 5, 2000.