Airworthiness Directive · Amendment 39-22279 · Turbine engine combustion section
GE Aviation Czech s.r.o. (Type Certificate Previously Held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Turboprop Engines
This AD applies to GE Aviation Czech s.r.o. (GEAC) M601D-11, M601E-11, M601E-11A, M601E-11AS, M601E-11S, M601F, H75-100, H75-200, H80, H80-100, H80-200, H85-100, and H85-200 model turboprop engines installed on single-engine airplanes, with an installed combustion chamber outer liner having part numbers (P/Ns) M601-229.3, M601-229.3A, M601-229.3B, M601-229.31A, or M601-229.31B.
The FAA is adopting a new airworthiness directive (AD) for certain GE Aviation Czech s.r.o. (GEAC) M601D-11, M601E-11, M601E-11A, M601E-11AS, M601E-11S, M601F, H75-100, H75-200, H80, H80-100, H80-200, H85-100, and H85-200 model turboprop engines. This AD was prompted by reports of cracks in dilution tube weld areas of the combustion chamber outer liner. This AD requires initial and repetitive borescope inspections (BSIs) of the dilution tube weld areas of the combustion chamber outer liner and, depending on the results of the inspections, replacement of the combustion chamber outer liner with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
(1) At the next 300-hour (Type 3) engine inspection, or within 25 flight hours (FHs) after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 300 FHs, perform a borescope inspection (BSI) of the dilution tube weld areas of the combustion chamber outer liner in accordance with the Accomplishment Instructions, paragraph 2.1 of GEAC Alert Service Bulletin (ASB) ASB-H75-72-40-00-0056 [01], ASB-M601E-72-40-00-0113 [01], ASB-H80-72-40-00-0099 [01], ASB-M601D-72-40-00-0081 [01], ASB-M601F-72-40-00-0064 [01], ASB-M601Z-72-40-00-0063 [01], and ASB-H85-72-40-00-0045 [01] (single document; formatted as service bulletin identifier [revision number]), dated February 16, 2022 (the ASB).
(2) If a crack is detected during any BSI required by paragraph (g)(1) of this AD, before further flight, perform the applicable corrective actions in accordance with the Accomplishment Instructions, paragraph 2.1, Table 1 of the ASB.
Replacing the affected combustion chamber outer liner with a combustion chamber outer liner that does not have P/N M601-229.3, M601-229.3A, M601-229.3B, M601-229.31A, or M601-229.31B, constitutes a terminating action for the repetitive inspections required by paragraph (g)(1) of this AD.
(1) After the effective date of this AD, it is permissible to install an engine, having an affected combustion chamber outer liner installed, on a single-engine airplane, provided that prior to operation, the BSI required by paragraph (g)(1) of this AD is performed and, depending on the findings, the applicable corrective actions are performed as required by paragraph (g)(2) of this AD.
(2) After the effective date of this AD, it is permissible to install an affected combustion chamber outer liner on the engine of a single-engine airplane, provided that it is a part eligible for installation, as defined in paragraph (j) of this AD, and provided that prior to operation, the BSI required by paragraph (g)(1) of this AD is performed and, depending on the findings, the applicable corrective actions are performed as required by paragraph (g)(2) of this AD.
For the purpose of this AD, a “part eligible for installation” is an affected combustion chamber outer liner, which was not previously installed on an engine, or an affected combustion chamber outer liner that, before installation, has passed an inspection (no defects found) in accordance with the Accomplishment Instructions, paragraphs 2.2 and 2.3 of the ASB, or a combustion chamber outer liner that does not have P/Ns M601-229.3, M601-229.3A, M601-229.3B, M601-229.31A, or M601-229.31B.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
