Airworthiness directives › 2025-21-03
AD 2025-21-03 Airworthiness Directives; CFM International, S.A. Engines
Applicability*9
This AD applies to CFM International, S.A. Model (CFM) 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 engines with an installed high-pressure turbine (HPT) rotor stage 1 blade, having part number (P/N) 2747M92P01, P/N 2553M91G03, P/N 2553M91G05, P/N 2553M91G06, P/N 2553M91G07, or P/N 2553M91G08 and that has accumulated more than 1,100 South Asia takeoffs.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) Group 1 Engines: Borescope Inspection (BSI) of HPT Rotor Stage 1 Blades For Group 1 engines with an affected HPT rotor stage 1 blade installed: (i) Within 100 flight cycles (FCs) after accumulating 1,100 South Asia takeoffs on the HPT rotor stage 1 blade, before the HPT rotor stage 1 blade accumulates 2,500 cycles since new (CSN), or within 100 FCs after the effective date of this AD, whichever occurs later, perform an initial BSI of the HPT rotor stage 1 blades in accordance with the Accomplishment Instructions, paragraph 5.E.(1)(c), of CFM Service Bulletin LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00, dated July 30, 2025 (CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00). (ii) Thereafter, at intervals not to exceed 150 FCs since the last BSI, perform a repetitive BSI of the HPT rotor stage 1 blades in accordance with the Accomplishment Instructions, paragraph 5.E.(1)(c), of CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00. (2) Group 2 Engines: BSI of HPT Rotor Stage 1 Blades For Group 2 engines with an affected HPT rotor stage 1 blade installed: (i) Within 100 FCs after accumulating 1,100 South Asia takeoffs on the HPT rotor stage 1 blade, before the HPT rotor stage 1 blade accumulates 5,100 CSN, or within 100 FCs after the effective date of this AD, whichever occurs later, perform an initial BSI of the HPT rotor stage 1 blades in accordance with the Accomplishment Instructions, paragraph 5.E.(1)(c), of CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00. (ii) Thereafter, at intervals not to exceed 300 FCs since the last BSI, perform a repetitive BSI of the HPT rotor stage 1 blades in accordance with the Accomplishment Instructions, paragraph 5.E.(1)(c), of CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00. (3) BSI Results Disposition for Group 1 and Group 2 Engines Based on the results of the BSI required by paragraphs (g)(1) or (2) of this AD, as applicable, either re-inspect or replace, as applicable, the HPT rotor stage 1 blades set using the criteria, compliance times, and procedures as described in the Accomplishment Instructions, paragraph 5.E.(1)(e), of CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00. (4) Conditional Inspection of the Sister Engine for Group 1 and Group 2 Engines (i) Based on the BSI results disposition required by paragraph (g)(3) of this AD, if re-inspection or replacement of the HPT rotor stage 1 is required, within 50 FCs based on the criteria, compliance times, and procedures described in the Accomplishment Instructions, paragraph 5.E.(1)(e), of CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00, then perform the actions required in paragraph (g)(4)(ii) of this AD. (ii) Within 5 FCs after performing the inspection required by paragraph (g)(1) or (2) of this AD, as applicable, either inspect or replace the HPT rotor stage 1 blades on the sister engine using the procedures and compliance times in the Accomplishment Instructions, paragraph 5.E.(1)(f), of CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00. Where CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00, specifies to remove the engine, this AD requires replacement of the HPT rotor stage 1 blades.
Unsafe condition
This AD was prompted by reports of two in-flight shutdowns due to cracks in the HPT rotor stage 1 blades. The FAA is issuing this AD to prevent failure of the HPT rotor stage 1 blades. The unsafe condition, if not addressed, could result in failure of the engine, in-flight shutdown, loss of thrust control, and consequent loss of control of the airplane.
Affected ADs
None.
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