98-10-11: Accessory Gearbox

98-10-11 CFM International: Amendment 39-10523. Docket No. 97-ANE-54-AD. Supersedes telegraphic AD T97-25-51. Applicability: CFM International (CFMI) CFM56-3, -3B, and -3C series turbofan engines, having any of the engine serial numbers (ESNs) identified in Table 1 of CFMI CFM56-3/-3B/-3C Service Bulletin (SB) No. 72-863, Revision 1, dated November 18, 1997, Table 1 of CFMI CFM56-3/-3B/-3C SB No. 72-867, dated November 28, 1997, or Table 1 of CFMI CFM56-3/-3B/-3C SB No. 72-873, Revision 1, dated February 5, 1998; CFM56-5 series turbofan engines, having any of the ESNs identified in Table 1 of CFMI CFM56-5 SB No. 72-523, Revision 1, dated January 30, 1998; CFM56-5B series turbofan engines, having any of the ESNs identified in Table 1 of CFMI CFM56-5B SB No. 72-211, Revision 1, dated January 29, 1998; and CFM56-5C series turbofan engines, having any of the ESNs identified in Table 1 of CFMI CFM56-5C SB No. 72-350, Revision 1, dated January 30, 1998. These engines are installed on but not limited to Boeing 737 series, and Airbus Industrie A319, A320, A321, and A340 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 (i) 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 inflight engine shutdowns due to an accessory gearbox (AGB) starter gearshaft, transfer gearbox (TGB) input bevel gear, TGB output bevel gear, AGB gearshaft cluster spur assembly or AGB intermediate gear assembly failure, accomplish the following: (a) For twin engine aircraft that are equipped with both engines identified by ESN in Table 1 of the applicable SB noted in the Applicability paragraph of this AD, prior to further flight, accomplish the following: (1) Remove one of the engines, and replace with an engine not identified by ESN in Table 1 of the applicable SB noted in the Applicability paragraph of this AD; or (2) On one of the engines, accomplish the following as applicable: (i) For CFM56-3, -3B, and -3C series engines: (A) Replace the AGB starter gearshaft with a serviceable part, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-3/-3B/-3C SB No. 72-863, Revision 1, dated November 18, 1997, (B) Replace the TGB assembly with a serviceable part, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-3/-3B/-3C SB No. 72-865, dated November 18, 1997; or, replace the TGB input bevel gear and/or output bevel gear, as applicable, with a serviceable part in accordance with CFMI CFM56-3/-3B/-3C SB No. 72-867, dated November 28, 1997, (C) Replace the AGB intermediate gear assembly with a serviceable part, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-3/-3B/-3C SB No. 72-873, Revision 1, dated February 5, 1998. (ii) For CFM56-5 series engines, replace the gearshaft cluster spur assembly with a serviceable part, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-5 SB No. 72-523, Revision 1, dated January 30, 1998. (iii) For CFM56-5B series engines, replace the gearshaft cluster spur assembly with a serviceable part, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-5B SB No. 72-211, Revision 1, dated January 29, 1998. (b) For four engine aircraft that are equipped with morethan one engine identified by ESN in Table 1 of CFMI CFM56-5C SB No. 72-350, Revision 1, dated January 30, 1998, prior to further flight, accomplish the following: (1) Remove at least all but one affected engine from the aircraft, and replace with serviceable engines not identified by ESN in Table 1 of CFMI CFM56-5C SB No. 72-350, Revision 1, dated January 30, 1998; or (2) Replace the gearshaft cluster spur assembly with a serviceable part, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-5C SB No. 72-350, Revision 1, dated January 30, 1998, on at least all but one affected engine. (c) For CFM56-3, -3B, and -3C series engines identified by ESN in Table 1 of CFMI CFM56-3/-3B/-3C SB No. 72-863, Revision 1, dated November 18, 1997, or CFMI CFM56-3/-3B/-3C SB No. 72-867, dated November 28, 1997, prior to further flight, and thereafter once per calendar day, perform checks of the AGB/TGB magnetic chip detector in accordance with CFMI CFM56-3/-3B/-3C Alert Service Bulletin (ASB) No. 72-A861, Revision 3, dated December 3, 1997. If magnetic particles are found to be abnormal in accordance with CFMI CFM56-3/-3B/-3C ASB No. 72-A861, Revision 3, dated December 3, 1997, prior to further flight, accomplish the following as applicable: (1) For engines identified by ESN in Table 1 of CFMI CFM56-3/-3B/-3C SB No. 72-863, Revision 1, dated November 18, 1997, remove the AGB starter gearshaft, and replace with a serviceable part, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-3/-3B/-3C SB No. 72-863, Revision 1, dated November 18, 1997. (2) For engines identified by ESN in Table 1 of CFMI CFM56-3/-3B/-3C SB No. 72-867, dated November 28, 1997, remove the TGB assembly and replace with a serviceable part, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-3/-3B/-3C SB No. 72-865, dated November 18, 1997; or, remove the TGB input bevel gear and/or TGB output bevel gear, as applicable, and replace with serviceable parts, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-3/-3B/-3C SB No. 72-867, dated November 28, 1997. (d) For CFM56-3, -3B, and -3C series engines identified by ESN in Table 1 of CFMI CFM56-3/-3B/-3C SB No. 72-863, Revision 1, dated November 18, 1997, remove the AGB starter gearshaft within 30 days after the effective date of this AD, and replace with a serviceable part, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-3/-3B/-3C SB No. 72-863, Revision 1, dated November 18, 1997. Installation of a serviceable AGB starter gearshaft, as defined in paragraph (h) of this AD, and compliance with paragraph (e) of this AD, if applicable, constitutes terminating action to the daily AGB/TGB magnetic chip detector checks required by paragraph (c) of this AD. (e) For CFM56-3, -3B, and -3C series engines identified by ESN in Table 1 of CFMI CFM56-3/-3B/-3C SB No. 72-867, dated November 28, 1997, remove the TGB assembly in accordance withCFMI CFM56-3/-3B/-3C SB No. 72-865, dated November 18, 1997; or, remove the TGB input bevel gear and/or output bevel gear, as applicable, within 30 days after the effective date of this AD, and replace with serviceable parts, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-3/-3B/-3C SB No. 72-867, dated November 28, 1997. Installation of a serviceable TGB assembly, or TGB input bevel gear and/or TGB output bevel gear, as defined in paragraph (h) of this AD, and compliance with paragraph (d) of this AD if applicable, constitutes terminating action to the daily AGB/TGB magnetic chip detector checks required by paragraph (c) of this AD. (f) For CFM56-3, -3B, and -3C series engines identified by ESN in Table 1 of CFMI CFM56-3/-3B/-3C SB No. 72-873, Revision 1, dated February 5, 1998, remove the AGB intermediate gear assembly within 30 days after the effective date of this AD, and replace with a serviceable part, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-3/-3B/-3C SB No. 72-873, Revision 1, dated February 5, 1998. (g) For CFM56-5, -5B, and -5C series engines identified by ESN in Table 1 of CFMI CFM56-5 SB No. 72-523, Revision 1, dated January 30, 1998, CFMI CFM56-5B SB No. 72-211, Revision 1, dated January 29, 1998, or CFMI CFM56-5C SB No. 72-350, Revision 1, dated January 30, 1998, remove the gearshaft cluster spur assembly within 30 days after the effective date of this AD, and replace with a serviceable part, as defined in paragraph (h) of this AD, in accordance with CFMI CFM56-5 SB No. 72-523, Revision 1, dated January 30, 1998, CFMI CFM56-5B SB No. 72-211, Revision 1, dated January 29, 1998, or CFMI CFM56-5C SB No. 72-350, Revision 1, dated January 30, 1998, as applicable. (h) For the purposes of this AD, a serviceable part is defined as an AGB starter gearshaft, Part Number (P/N) 335-302-503-0, a TGB assembly, P/N 335-300-012-0, a TGB input bevel gear, P/N 335-321-008-0, a TGB output bevel gear, P/N 335-322-405-0, AGB gearshaft cluster spur assembly, P/N 335-302-503-0, or an AGB intermediate gear assembly, P/N 335-303-202-0, not identified by part serial number in Table 1 of the applicable SB noted in the Applicability Section of this AD. (i) An alternative method of compliance or adjustment of the initial compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (j) The actions required by this AD shall be accomplished in accordance with the following CFMI service documents: Document No. Page Revision Date CFM56-3/-3B/-3C ASB No. 72-A8611-10 3 December 3, 1997 Total Pages: 10. CFM56-3/-3B/-3C SB No. 72-863 1-39 1 November 18, 1997 Total Pages: 39. CFM56-3/-3B/-3C SB No. 72-865 1-8 Original November 18, 1997 Total Pages: 8. CFM56-3/-3B/-3C SB No. 72-867 1-11 Original November 28, 1997 Total Pages: 11. CFM56-3/-3B/-3C SB No. 72-873 1-21 1 February 5, 1998 Total Pages: 21. CFM56-5 SB No. 72-523 1-33 1 January 30, 1998 Total Pages: 33. CFM56-5B SB No. 72-211 1-28 1 January 29, 1998 Total Pages: 28. CFM56-5C SB No. 72-350 1-28 1 January 30, 1998 Total Pages: 28. 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 CFM International, Technical Publications Department, 1 Neumann Way, Cincinnati, OH 45215; telephone (513) 552-2981, fax (513) 552-2816. 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. (k) This amendment supersedes telegraphic AD T97-25-51, issued December 4, 1997. (l) This amendment becomes effective on June 3, 1998.