2020-09-03: Turbine Engine Compressor Section

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): \n\n2020-09-03 International Aero Engines AG: Amendment 39-21117; Docket No. FAA-2019-0832; Project Identifier 2019-NE-28-AD. \n\n(a) Effective Date \n\n\n\tThis AD is effective May 29, 2020. \n\n(b) Affected ADs \n\n\n\tNone. \n\n(c) Applicability \n\n\n\tThis AD applies to International Aero Engines AG (IAE) V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528- D5, V2530-A5, V2531-E5, and V2533-A5 model turbofan engines with diffuser case assembly, serial number PGGUBB8267, PGGUBB8271, PGGUA95825, PGGUA95827, or PGGUBB8264, installed.(d) Subject \n\n\n\tJoint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. \n\n(e) Unsafe Condition \n\n\n\tThis AD was prompted by a report of a manufacturing quality escape that could impact the life of the diffuser case assembly. The FAA is issuing this AD to prevent failure of the diffuser case assembly. The unsafe condition, if not addressed, could result in the uncontained release of the diffuser case assembly, damage to the engine, and damage to the airplane. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) Required Action \n\n\n\tAt the next engine shop visit after the effective date of the AD or before accumulating 10,000 cycles since new, whichever occurs first, remove the affected diffuser case assembly from service and replace with a part eligible for installation. \n\tNote to paragraph (g): IAE Non-Modification Service Bulletin (NMSB) V2500-ENG-72-0707, dated July 1, 2019, contains guidance for replacing the diffuser case assembly. \n\n(h) Definition \n\n\n\tFor the purpose of this AD, an ''engine shop visit'' is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. \n\n(i) Alternative Methods of Compliance (AMOCs) \n\n\n\t(1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j) of this AD. You may email your request to: ANE-AD-AMOC@faa.gov. \n\t(2) Before using any approvedAMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. \n\n(j) Related Information \n\n\n\tFor more information about this AD, contact Nicholas Paine, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7116; fax: 781-238-7199; email: nicholas.j.paine@faa.gov. \n\n(k) Material Incorporate by Reference \n\n\n\tNone. \n\n\n\tIssued on April 20, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2020-08703 Filed 4-23-20; 8:45 am) \n\tBILLING CODE 4910-13-P