Issued: -- | To: EASA | FRAN 2020-006 |
EASA and the FAA ensure that the design and sizing criteria and methods along with the manufacturing processes and in-production checks of engine rotor-grade critical parts made of a/ß titanium alloy, and in particular the titanium alloy Ti-6-4, are such that the risk of failure of these parts due to the cold dwell fatigue phenomenon is controlled. |
Issued: -- | To: FAA | FRAN 2020-007 |
EASA and the FAA ensure that the design and sizing criteria and methods along with the manufacturing processes and in-production checks of engine rotor-grade critical parts made of a/ß titanium alloy, and in particular the titanium alloy Ti-6-4, are such that the risk of failure of these parts due to the cold dwell fatigue phenomenon is controlled. |
Issued: -- | To: EASA | FRAN 2020-008 |
EASA and the FAA carry out a review of engine rotor-grade critical parts made of a/ß titanium alloy, and in particular the titanium alloy Ti-6-4, which undergo a manufacturing process likely to lead to the presence of intense macro-zones and for which the risk of failure due to a cold dwell fatigue phenomenon has not been sufficiently taken into account during the certification. EASA and the FAA will subsequently make sure, where appropriate, that an adapted in-service inspection programme is implemented to detect possible incipient cracks which might lead to the failure of the part. |
Issued: -- | To: FAA | FRAN 2020-009 |
EASA and the FAA carry out a review of engine rotor-grade critical parts made of a/ß titanium alloy, and in particular the titanium alloy Ti-6-4, which undergo a manufacturing process likely to lead to the presence of intense macro-zones and for which the risk of failure due to a cold dwell fatigue phenomenon has not been sufficiently taken into account during the certification. EASA and the FAA will subsequently make sure, where appropriate, that an adapted in-service inspection programme is implemented to detect possible incipient cracks which might lead to the failure of the part. |
Issued: 13-OCT-2017 | To: Engine Alliance GP7270 | AD 2017-21-51 |
This AD requires a one-time visual inspection of the GP7200 series engine fan hub, with the compliance time based on the number of accumulated flight cycles, and removal of the fan hub if damage or defects are found that are outside of serviceable limits. |
Issued: 09-NOV-2017 | To: Engine Alliance GP7270, GP7277 | AD 2017-23-03 |
supersedes AD 2017-21-51, clarifying the compliance requirements |
Issued: 22-JUN-2018 | To: Engine Alliance GP7270, GP7272, and GP7277 | AD 2018-11-16 |
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. |
Issued: 20-FEB-2019 | To: Engine Alliance GP7270, GP7277 | AD 2019-03-04 |
requires a visual inspection of the engine fan hub assembly for damage, a one-time eddy current inspection (ECI) of the fan hub blade slot bottom and blade slot front edge for cracks, and removal of parts if damage or defects are found. |
Issued: 20-AUG-2019 | To: Engine Alliance GP7270, GP7277 | AD 2019-16-04 |
supersedes AD 2019-03-04, adding replacement of the engine fan hub blade lock assembly for certain engines |
Issued: 24-SEP-2019 | To: Engine Alliance GP7270, GP7277 | AD 2019-18-08 |
supersedes AD 2019-16-04, reducing the compliance time for the initial ECI and requiring repetitive ECIs of the engine fan hub blade slot bottom and blade slot front edge for cracks. |