AD 2023-04-11
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric | Company | Airworthiness Directives; General Electric Company Turbofan Engines |
Unsafe Condition
Separation of the low-pressure turbine (LPT) rotor assembly, resulting in the LPT rotor assembly departing the rear of the engine.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect high-pressure turbine (HPT) and LPT rotor stage 1 and stage 2 blades, perform vibration surveys, use a lower life limit for affected LPT rotor stage 3 disks, and remove and replace the LPT rotor stage 3 disk with a redesigned disk. Revise the compliance time of the drawdown plan for the removal and replacement of the LPT rotor stage 3 disk. Prohibit the installation or reinstallation of certain LPT rotor stage 3 disks.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 flight hours after the effective date of this AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
General Electric Company CF6-45A, CF6-45A2, CF6-50A, CF6-50C, CF6-50CA, CF6-50C1, CF6-50C2, CF6-50C2B, CF6-50C2D, CF6-50E, CF6-50E1, CF6-50E2, and CF6-50E2B model turbofan engines, including engines marked as CF6-50C2-F and CF6-50C2-R, with an installed LPT rotor stage 3 disk having a part number listed in Table 1 of the AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.