Airworthiness Directive · Amendment 39-21269 · Turbine section
General Electric Company Turbofan Engines
Superseded. A later AD replaced this one: AD 2021-26-22. Comply with the one in force.
This AD applies to General Electric Company (GE) CF6-80A, CF6-80A1, CF6-80A2, CF6-80A3, CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-80C2B1, CF6-80C2B1F, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, CF6-80C2D1F, CF6-80C2L1F, and CF6-80C2K1F model turbofan engines with high-pressure turbine (HPT) disks with serial numbers listed in Tables 1 and 2 of Appendix A in GE CF6-80C2 Service Bulletin (SB) 72-1562 R04, dated May 29, 2019; and Table 1 of Appendix A in GE CF6-80A SB 72-0869 R02, dated May 29, 2019.
The FAA is superseding Airworthiness Directive (AD) 2018-15-04 for certain General Electric Company (GE) CF6-80A, CF6-80A1, CF6-80A2, CF6-80A3, CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-80C2B1, CF6-80C2B1F, CF6-80C2B2, CF6-80C2B2F, CF6- 80C2B4, CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6, CF6-80C2B6F, CF6- 80C2B6FA, CF6-80C2B7F, CF6-80C2D1F, CF6-80C2L1F, and CF6-80C2K1F model turbofan engines. AD 2018-15-04 required ultrasonic inspection (UI) of high-pressure turbine (HPT) stage 1 and stage 2 disks. This AD retains the required inspections while expanding the population of affected HPT disks. This AD was prompted by an uncontained failure of an HPT stage 2 disk and the manufacturer's determination to expand the population of affected HPT disks. The FAA is issuing this AD to address the unsafe condition on these products.
(1) After the effective date of this AD, perform an ultrasonic inspection (UI) for cracks in HPT stage 1 and stage 2 disks on the CF6-80C2 turbofan engine at each piece-part exposure using the Accomplishment Instructions, paragraph 3.A.(2), of GE CF6-80C2 SB 72-1562 R04, dated May 29, 2019.
(2) After the effective date of this AD, perform a UI for cracks in HPT stage 2 disks on the CF6-80A turbofan engine at each piece-part exposure using the Accomplishment Instructions, paragraph 3.A.(2), of GE CF6-80A SB 72-0869 R02, dated May 29, 2019.
(3) If any disk fails the inspection required by paragraphs (g)(1) and (2) of this AD, replace the disk before further flight.
The reporting requirements specified in the Accomplishment Instructions, paragraphs 3.A.(2)(c) and 3.A.(2)(f), of GE CF6-80C2 SB 72-1562 R04, dated May 29, 2019, are not required by this AD.
For the purpose of this AD, “piece-part exposure” of the HPT stage 1 or stage 2 disk is the separation of that HPT disk from its mating rotor parts within the HPT rotor module (thermal shield and HPT stage 1 and stage 2 disk, respectively).
