Airworthiness Directive · Amendment 39-23038 · Turbine section
General Electric Company Engines
This AD applies to General Electric Company (GE) Model CF34-10E2A1, CF34-10E5, CF34-10E5A1, CF34-10E6, CF34-10E6A1, CF34-10E7, and CF34-10E7-B engines with an installed high-pressure turbine (HPT) shroud/low-pressure turbine (LPT) nozzle assembly having part number (P/N) 2205M38G01, 2205M38G02, 2205M38G03, 2205M38G04, or 2205M38G05.
The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) Model CF34-10E2A1, CF34-10E5, CF34- 10E5A1, CF34-10E6, CF34-10E6A1, CF34-10E7, and CF34-10E7-B engines with certain part-numbered high-pressure turbine (HPT) shroud/low pressure turbine (LPT) nozzle assemblies installed. This AD was prompted by a report of failed retention features of the inner and outer support air ducts (commonly referred to as spoolies) discovered during engine disassembly. This AD requires a visual inspection of the combustion case for wear and gouges, repair if necessary, and rework of the affected HPT shroud/LPT nozzle assemblies to add a positive retention of the support air duct. The FAA is issuing this AD to address the unsafe condition on these products.
(1) At the next engine shop visit after the effective date of this AD, do a visual inspection of the combustion case inner shell surface for wear and gouges in accordance with paragraphs 3.A.(1) and (2) of the Accomplishment Instructions in GE CF34-10E Service Bulletin (SB) 72-0351 R01, dated July 17, 2019 (GE CF34-10E SB 72-0351 R01).
(i) If any wear or gouges are found during any inspection required by paragraph (g)(1) of this AD, before further flight, repair the combustion case in accordance with Table 1 of GE CF34-10E SB 72-0351 R01.
(ii) If any wear or gouges exceed the maximum repairable limit in accordance with Table 1 of GE CF34-10E SB 72-0351 R01, before further flight, remove the combustion case from service.
(2) At the next engine shop visit after the effective date of this AD, rework the affected HPT shroud/LPT nozzle assembly, in accordance with paragraph 3.B. of the Accomplishment Instructions of GE CF34-10E SB 72-0351 R01.
For the purpose of this AD, an “engine shop visit” is defined as when the HPT shroud/LPT nozzle assembly or the HPT rotor disk is removed from the engine.
