Airworthiness directives › 2019-16-01
AD 2019-16-01 Airworthiness Directives; International Aero Engines AG Turbofan Engines
Applicability*9
This AD applies to all International Aero Engines AG (IAE) V2525-D5 and V2528-D5 model turbofan engines.
Compliance
Comply with this AD within the compliance times specified, unless already done.
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. (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.
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.
Affected ADs
None.
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