Airworthiness Directive · Amendment 39-23086 · Turbine engine compressor section
CFM International, S.A. Engines
This AD applies to CFM International, S.A. (CFM) Model LEAP-1B21, LEAP-1B23, LEAP-1B25, LEAP-1B27, LEAP-1B28, LEAP-1B28B1, LEAP-1B28B2, LEAP-1B28B2C, LEAP-1B28B3, LEAP-1B28BBJ1, and LEAP-1B28BBJ2 engines.
The FAA is superseding Airworthiness Directive (AD) 2023-23-12 for all CFM International, S.A. (CFM) Model LEAP-1B21, LEAP-1B23, LEAP- 1B25, LEAP-1B27, LEAP-1B28, LEAP-1B28B1, LEAP-1B28B2, LEAP-1B28B2C, LEAP-1B28B3, LEAP-1B28BBJ1, and LEAP-1B28BBJ2 engines. AD 2023-23-12 required replacing certain high-pressure turbine (HPT) rotor stage 1 disks and a certain compressor rotor stages 6-10 spool. Since the FAA issued AD 2023-23-12, the manufacturer has identified additional parts that were manufactured from material suspected to have reduced material properties due to iron inclusion, which prompted this AD. This AD retains the requirements to replace certain HPT rotor stage 1 disks and a certain compressor rotor stages 6-10 spool. This AD also expands the applicability to include additional affected HPT rotor stage 1 disks that were manufactured from the same material suspected to have reduced material properties due to iron inclusion. The FAA is issuing this AD to address the unsafe condition on these products.
(1) For engines with an installed HPT rotor stage 1 disk having a part number (P/N) and serial number (S/N) identified in Compliance, paragraph 3.E., Tables 1 through 2, of CFM Service Bulletin (SB) LEAP-1B-72-00-0392-01A-930A-D, Issue 002, dated September 5, 2023 (CFM SB LEAP-1B-72-00-0392-01A-930A-D, Issue 002): At the next piece-part exposure of the HPT rotor stage 1 disk, or before exceeding the applicable cycles since new (CSN) threshold identified in Compliance, paragraph 3.E., Tables 1 through 2, of CFM SB LEAP-1B-72-00-0392-01A-930A-D, Issue 002, whichever occurs first after January 16, 2024 (the effective date of AD 2023-23-12); or if the applicable CSN threshold has been exceeded as of January 16, 2024 (the effective date of AD 2023-23-12), within 50 flight cycles (FCs) from January 16, 2024 (the effective date of AD 2023-23-12); remove the HPT rotor stage 1 disk from service and replace with a part eligible for installation.
(2) For engines with an installed compressor rotor stages 6-10 spool having a P/N and S/N identified in Compliance, paragraph 3.E., Table 3, of CFM SB LEAP-1B-72-00-0392-01A-930A-D, Issue 002: At the next piece-part exposure of the compressor rotor stages 6-10 spool, or before exceeding the applicable CSN threshold identified in Compliance, paragraph 3.E., Table 3, of CFM SB LEAP-1B-72-00-0392-01A-930A-D, Issue 002, whichever occurs first after January 16, 2024 (the effective date of AD 2023-23-12); or if the applicable CSN threshold has been exceeded as of January 16, 2024 (the effective date of AD 2023-23-12), within 50 FCs from January 16, 2024 (the effective date of AD 2023-23-12); remove the compressor rotor stages 6-10 spool from service and replace with a part eligible for installation.
For engines with an installed HPT rotor stage 1 disk having a P/N and S/N identified in Compliance, paragraph 3.E., Table 1, of CFM SB LEAP-1B-72-00-0402-01A-930A-D, Issue 001, dated January 23, 2024 (CFM SB LEAP-1B-72-00-0402-01A-930A-D, Issue 001): At the next piece-part exposure of the HPT rotor stage 1 disk, or before exceeding the applicable CSN threshold identified in Compliance, paragraph 3.E., Table 1, of CFM SB LEAP-1B-72-00-0402-01A-930A-D, Issue 001, whichever occurs first after the effective date of this AD; or if the applicable CSN threshold has been exceeded as of the effective date of this AD, within 50 FCs from the effective date of this AD; remove the HPT rotor stage 1 disk from service and replace with a part eligible for installation.
For the purpose of this AD, a “part eligible for installation” is an HPT rotor stage 1 disk or compressor rotor stages 6-10 spool that does not have a P/N and S/N identified in Compliance, paragraph 3.E., Tables 1 through 3, of CFM SB LEAP-1B-72-00-0392-01A-930A-D, Issue 002; or Compliance, paragraph 3.E., Table 1, of CFM SB LEAP-1B-72-00-0402-01A-930A-D, Issue 001.
After the effective date of this AD, do not install an HPT rotor stage 1 disk or compressor rotor stages 6-10 spool that has a P/N and S/N identified in Compliance, paragraph 3.E., Tables 1 through 3, of CFM SB LEAP-1B-72-00-0392-01A-930A-D, Issue 002; or Compliance, paragraph 3.E., Table 1, of CFM SB LEAP-1B-72-00-0402-01A-930A-D, Issue 001, on any engine.
This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed prior to January 16, 2024 (the effective date of AD 2023-23-12) by following the Accomplishment Instructions specified in CFM SB LEAP-1B-72-00-0392-01A-930A-D, Issue 001, dated March 7, 2023.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
