Airworthiness Directive · Amendment 39-19304 · Turbine engine compressor section
Engine Alliance Turbofan Engines
Superseded. A later AD replaced this one: AD 2019-03-04. Comply with the one in force.
This AD applies to Engine Alliance (EA) GP7270, GP7272, and GP7277 model turbofan engines with serial numbers (S/Ns) identified in Table 3 in Planning Information of Engine Alliance (EA) Alert Service Bulletin (ASB) EAGP7-A72-389, Revision No. 2, dated April 17, 2018.
We are adopting a new airworthiness directive (AD) for certain Engine Alliance (EA) GP7270, GP7272, and GP7277 turbofan engines. This AD requires a one-time eddy current inspection (ECI) of the engine fan hub blade slot bottom and blade slot front edge for cracks, a visual inspection of the engine fan hub for damage, and removal of parts if damage or defects are found that are outside serviceable limits. This AD was prompted by an uncontained failure of the engine fan hub. We are issuing this AD to address the unsafe condition on these products.
Within 120 days after the effective date of this AD:
(1) For engine fan hubs at the low-pressure compressor (LPC) module assembly level:
(i) Perform a visual inspection of the engine fan hub, in accordance with the Accomplishment Instructions, For Fan Hubs at LPC Module Assembly Level, paragraphs 1.A.(1), 1.A.(4), and 1.A.(6)(a), of EA ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018.
(ii) Perform an eddy current inspection (ECI) of the engine fan hub blade slot bottoms and front edges, in accordance with the Accomplishment Instructions, For Fan Hubs at LPC Module Assembly Level, paragraphs 2.A and 2.B, of EA ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018.
(2) For engine fan hubs at the piece part level:
(i) Perform a visual inspection of the engine fan hub, in accordance with the Accomplishment Instructions, For Fan Hubs at Piece Part Level, paragraphs 1.A.(1) and 1.A.(3), of EA ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018.
(ii) Perform an ECI of the engine fan hub blade slot bottoms and front edges, in accordance with the Accomplishment Instructions, For Fan Hubs at Piece Part Level, paragraphs 2.A and 2.B, of EA ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018.
(3) For engine fan hubs installed in an engine (on-wing or off-wing):
(i) Perform a visual inspection of the engine fan hub, in accordance with the Accomplishment Instructions, For Fan Hubs Installed in an Engine, paragraphs 1.C.(1), 1.C.(5), and 1.C.(7)(a), of EA ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018.
(ii) Perform an ECI of the engine fan hub blade slot bottoms and front edges, in accordance with the Accomplishment Instructions, For Fan Hubs Installed in an Engine, paragraphs 1.D.(1) and 1.D.(2), of EA ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018.
(4) If the engine fan hub visual inspection reveals defects or damage to the engine fan hub that are found outside the serviceable limits specified in Table 4 in the Accomplishment Instructions of EA ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018, remove the engine fan hub from service and replace with a part that is eligible for installation, prior to further flight.
(5) If the fan hub ECI results in a rejectable indication, per the Appendix, Added Data, of EA ASB EAGP7-A72-389, Revision No. 2, dated April 17, 2018, remove the hub from service and replace with a part that is eligible for installation, prior to further flight.
