| Number |
2024-0175 |
| Issued by |
 Europe |
| Issue date |
2024-11-28 |
| Effective date |
2024-09-20 |
| EASA approval number |
|
| Contributor |
EASA Environment & Propulsion Systems Department |
| ATA Chapter |
72 |
Approval Holder
/ Type Designation |
|
| Revision |
Not applicable
|
| Correction |
This AD is republished to correct a typographical error in the 'Ref. Publication' section.
|
| Supersedure |
None
|
| Publication(s) and related information |
Airbus A318/A319/A320/A321 AMM dated 01 August 2024.
CFM ESM LEAP-1A ESM 72-41-00, Disassemble Engine Modular Section, Task LEAP-1A-72-41-00-03A-53AA-C issue 018-00, dated 07 December 2023.
CFM ESM LEAP-1A ESM 72-41-00, Assemble Engine Modular Section, Task LEAP-1A-72-41-00-03A-71AA-C issue 024-00, dated 07 December 2023.
CFM CMM 73-11-30 (CFM-TP.CM.056) at any revision.
The use of later approved revisions of the above-mentioned documents is acceptable for
compliance with the requirements of this AD. |
| Remarks |
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of
Compliance for this AD.
2. Based on the required actions and the compliance time, the original issue of this AD was posted on 06 September 2024 as Final AD with Request for Comments, postponing the public
consultation process until 04 October 2024. 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.
|
