Airworthiness Directive · Amendment 39-22107 · Turbine engine compressor section
CFM International, S.A. Turbofan Engines
This AD applies to CFM International, S.A. LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A model turbofan engines with an installed:
(1) High-pressure turbine (HPT) rotor stage 1 disk (HPT stage 1 disk) with part number (P/N) and serial number (S/N) identified in Table 1 to paragraph (g)(1) of this AD; or,
(2) Stages 6-10 compressor rotor spool with P/N 2468M20G03 and S/N GWN1141P.
The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A (LEAP-1A) model turbofan engines. This AD was prompted by a manufacturer investigation that revealed that certain high-pressure turbine (HPT) rotor stage 1 disks (HPT stage 1 disks) and a stages 6-10 compressor rotor spool were manufactured from material suspected to contain iron inclusion. This AD requires the replacement of certain HPT stage 1 disks and a stages 6-10 compressor rotor spool. The FAA is issuing this AD to address the unsafe condition on these products.
(1) At the next engine shop visit or before exceeding the cycles since new (CSN) threshold in Table 1 to paragraph (g)(1), whichever occurs first after the effective date of this AD, or if the CSN threshold in Table 1 to paragraph (g)(1) has been exceeded as of this AD's effective date, within 50 flight cycles (FCs) from the effective date of this AD, remove the HPT stage 1 disk with P/N and S/N identified in Table 1 to paragraph (g)(1) of this AD from service and replace with an HPT stage 1 disk eligible for installation.
(2) At the next engine shop visit or before exceeding 7,290 CSN, whichever occurs first after the effective date of this AD, or if 7,290 CSN has been exceeded as of this AD's effective date, within 50 FCs from the effective date of this AD, remove the stages 6-10 compressor rotor spool with P/N 2468M20G03 and S/N GWN1141P from service and replace with a stages 6-10 compressor rotor spool eligible for installation.
(1) For the purpose of this AD, an “HPT stage 1 disk eligible for installation” is any HPT stage 1 disk that does not have a P/N and S/N identified in Table 1 to paragraph (g)(1) of this AD.
(2) For the purpose of this AD, a “stages 6-10 compressor rotor spool eligible for installation” is any stages 6-10 compressor rotor spool that does not have P/N 2468M20G03 and S/N GWN1141P.
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.
