2019-16-01: Turbine section

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2019-16-01 International Aero Engines AG: Amendment 39-19704; Docket No. FAA-2019-0274; Product Identifier 2019-NE-07-AD. (a) Effective Date This AD is effective September 19, 2019. (b) Affected ADs None. (c) Applicability This AD applies to all International Aero Engines AG (IAE) V2525-D5 and V2528-D5 model turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine section. (e) Unsafe Condition This AD was prompted by reports of a cracked turbine exhaust case (TEC). The FAA is issuing this AD to prevent failure of the TEC. The unsafe condition, if not addressed, could result in engine separation and loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) At the next engine shop visit, but not later than 4,000 flight cycles (FCs) after the effective date of this AD, perform an eddy current inspection (ECI) and high sensitivity fluorescent penetrant inspection (FPI) of the TEC front and rear mount stiffener rails for cracking indications as follows: (i) Perform an ECI using the Accomplishment Instructions, Part I--For Engines Installed on Aircraft, paragraphs 2 through 19 inclusive, or Part II--For Engines Not Installed on Aircraft, paragraphs 2 through 18 inclusive, of IAE Non-Modification Service Bulletin (NMSB) V2500-ENG-72-0694, Revision No. 2, dated July 2, 2018 (``IAE NMSB V2500-ENG-72-0694''). (ii) If a rejectable indication was found during the ECI, perform a local high sensitivity FPI to confirm a crack. [[Page 41623]] (iii) If a rejectable indication was found during the ECI, but no crack(s) were confirmed using the local high sensitivity FPI, then clean, blend and repeat the ECI in the local area of the part. Use the Accomplishment Instructions, Part I--For Engines Installed on Aircraft, paragraph 20.A.(3), or Part II--For Engines Not Installed on Aircraft, paragraph 19.A.(3), of IAE NMSB V2500-ENG-72- 0694 to perform the cleaning and blending. Use the Accomplishment Instructions, Part I--For Engines Installed on Aircraft, paragraphs 2 through 19 inclusive, or Part II--For Engines Not Installed on Aircraft, paragraphs 2 through 18 inclusive, of IAE NMSB V2500-ENG- 72-0694 to perform the repeat ECI. (iv) If a rejectable indication was again found during the repeat ECI, then repeat the local high sensitivity FPI inspection in the local area of the part. If the local high sensitivity FPI does not confirm a crack, follow the instructions in the Accomplishment Instructions, Part I--For Engines Installed on Aircraft, paragraph 20.A.(5)(a), or Part II--For Engines Not Installed on Aircraft, paragraph 19.A.(5)(a), of IAE NMSB V2500-ENG-72-0694. (2) If no cracks were found, within 2,000 FCs since the last inspection, and thereafter, repeat the inspections of paragraphs (g)(1)(i) through (iv) of this AD. (3) If a crack was confirmed during the FPI and visual inspection required by paragraphs (g)(1)(ii) or (iv), before further flight, remove the part from service and replace with a part eligible for installation. (h) Credit for Previous Actions You may take credit for the inspections required by paragraph (g)(1) of this AD if you performed these inspections before the effective date of this AD, using IAE NMSB V2500-ENG-72-0694, Revision No. 1, dated February 7, 2018; or IAE NMSB V2500-ENG-72- 0694, Original Issue, dated January 5, 2018. (i) No Reporting RequirementNo reporting requirement contained within the NMSB referenced in paragraph (g) of this AD is required by this AD. (j) Definition For 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 case 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. (k) Special Flight Permit A special flight permit is not permitted if the crack indication extends past the mount stiffener rail or if there is evidence of an FPI indication on the outer diameter of the case. (l) Alternative Methods of Compliance (AMOCs) (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 (m) of this AD. You may email your request to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (m) Related Information For more information about this AD, contact Martin Adler, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; phone: 781-238-7157; fax: 781-238-7199; email: [email protected]. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicableto do the actions required by this AD, unless the AD specifies otherwise. (i) International Aero Engines Non-Modification Service Bulletin V2500-ENG-72-0694, Revision No. 2, dated July 2, 2018. (ii) [Reserved] (3) For International Aero Engines service information identified in this AD, contact International Aero Engines AG, 400 Main Street, East Hartford, CT, 06118; phone: 800-565-0140; email: [email protected]; internet: http://fleetcare.pw.utc.com. (4) You may view this referenced service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA, 01803. For information on the availability of this material at the FAA, call 781-238-7759. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.