| Number |
2026-0049 |
| Issued by |
 Europe |
| Issue date |
2026-03-11 |
| Effective date |
2026-03-25 |
| EASA approval number |
|
| ATA Chapter |
72 |
Approval Holder
/ Type Designation |
-
CFM INTERNATIONAL
-
LEAP-1A/-1C
-
LEAP-1A23
-
LEAP-1A24
-
LEAP-1A24E1
-
LEAP-1A26
-
LEAP-1A26CJ
-
LEAP-1A26E1
-
LEAP-1A29
-
LEAP-1A29CJ
-
LEAP-1A30
-
LEAP-1A32
-
LEAP-1A33
-
LEAP-1A33B2
-
LEAP-1A35A
|
| Revision |
Not applicable
|
| Correction |
Not applicable
|
| Supersedure |
This AD supersedes EASA AD 2018-0216 dated 08 October 2018.
|
| Publication(s) and related information |
CFM SB LEAP-1A-73-00-0050-01A-930A-D Issue 001 dated 03 January 2024.
CFM SB LEAP-1A-73-00-0051-01A-930A-D Issue 001 dated 04 July 2022, Issue 002 dated 03 January 2024, or Issue 003 dated 01 August 2024.
CFM SB LEAP-1A-73-00-0042-01A-930A-D Issue 001 dated 22 July 2020, Issue 002 dated 04 July 2022, or Issue 003 dated 11 July 2024.
The use of later approved revisions of the above-mentioned documents is acceptable for compliance with the requirements of this AD.
|
| PAD number |
26-006 |
| Remarks |
1.
If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.
2. This AD was posted on 16 January 2026 as PAD 26-006 for consultation until 13 February 2026. The Comment Response Document can be found in the EASA Safety Publications Tool, in the compressed (zipped) file attached to the record for this AD.
3. Enquiries regarding this AD should be referred to the EASA Safety Information Section, Certification Directorate. E-mail: ADs[at]easa.europa.eu.
4. Information about any failures, malfunctions, defects or other occurrences, which may be similar to the unsafe condition addressed by this AD, and which may occur, or have occurred on a product, part or appliance not affected by this AD, can be reported to the EU aviation safety reporting system. This may include reporting on the same or similar components, other than those covered by the design to which this AD applies, if the same unsafe condition can exist or may develop on an aircraft with those components installed. Such components may be installed under an FAA Parts Manufacturer Approval (PMA), Supplemental Type Certificate (STC) or other modification.
|
