Airworthiness Directive · Amendment 39-21352 · Turbine section
General Electric Company Turbofan Engines
(1) This AD applies to all General Electric Company (GE) GEnx-1B64/P2, GEnx-1B67/P2, GEnx-1B70/75/P2, GEnx-1B70/P2, GEnx-1B70C/P2, GEnx-1B74/75/P2, GEnx-1B76/P2, and GEnx-1B76A/P2 model turbofan engines that have a high-pressure turbine (HPT) rotor stage 2 disk, part number (P/N) 2383M86P02, and a serial number (S/N) listed in paragraph 4, Appendix—A, Table 1, Table 2, or Table 3, of GE GEnx-1B Service Bulletin (SB) 72-0463 R01, dated January 6, 2020, installed.
(2) This AD applies to all GE GEnx-2B67/P model turbofan engines that have a HPT rotor stage 2 disk, P/N 2383M86P02, and a S/N listed in paragraph 4, Appendix—A, Table 1, Table 2, or Table 3, of GE GEnx-2B SB 72-0402 R01, dated January 8, 2020, installed.
The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) GEnx-1B64/P2, GEnx-1B67/P2, GEnx-1B70/75/ P2, GEnx-1B70/P2, GEnx-1B70C/P2, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx- 1B76A/P2, and GEnx-2B67/P model turbofan engines with a certain high- pressure turbine (HPT) rotor stage 2 disk installed. This AD was prompted by a report of the potential for undetected subsurface anomalies formed during the manufacturing process that could result in uncontained failure of the HPT rotor stage 2 disk. This AD requires an immersion ultrasonic inspection (USI) of the HPT rotor stage 2 disk and, depending on the results of the inspection, replacement of the HPT rotor stage 2 disk with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
(1) For affected GE GEnx-1B engines, at the next engine shop visit after the effective date of this AD, or before the HPT rotor stage 2 disk has accumulated 6,500 cycles since new (CSN), whichever occurs first, perform an immersion ultrasonic inspection (USI) of the HPT rotor stage 2 disk using paragraph 3.B.(1) of GE GEnx-1B SB 72-0463 R01, dated January 6, 2020.
(2) If, during the USI required by paragraph (g)(1) of this AD, a rejectable indication is found, before further flight, remove the HPT rotor stage 2 disk from service and replace it with a part eligible for installation.
(3) For affected GE GEnx-2B engines, at the next engine shop visit after the effective date of this AD, or before the HPT rotor stage 2 disk has accumulated 6,500 CSN, whichever occurs first, perform an immersion USI of the HPT rotor stage 2 disk using paragraph 3.B.(1) of GE GEnx-2B SB 72-0402 R01, dated January 8, 2020.
(4) If, during the USI required by paragraph (g)(3) of this AD, a rejectable indication is found, before further flight, remove the HPT rotor stage 2 disk from service and replace it with a part eligible for installation.
(1) For the purpose of this AD, an “engine shop visit” is when a major engine flange is separated for purposes other than the removal of the fan for transportation.
(2) For the purposes of this AD, a “part eligible for installation” is:
(i) An HPT rotor stage 2 disk that does not have an S/N listed in paragraph 4, Appendix—A, Table 1, Table 2, or Table 3, of GE GEnx-1B SB 72-0463 R01, dated January 6, 2020, or GE GEnx-2B SB 72-0402 R01, dated January 8, 2020; or,
(ii) An HPT rotor stage 2 disk that has successfully passed the immersion USI required by paragraph (g)(1) or (3) of this AD, or passed the immersion USI using GE GEnx-1B SB 72-0463 R00, dated November 20, 2019, or GE GEnx-2B SB 72-0402 R00, dated November 20, 2019, before the effective date of this AD.
You may take credit for the immersion USI of the HPT rotor stage 2 disk required by paragraph (g)(1) or (3) of this AD if you performed this inspection before the effective date of this AD using GE GEnx-1B SB 72-0463 R00, dated November 20, 2019, or GE GEnx-2B SB 72-0402 R00, dated November 20, 2019.
