| Number |
F-2005-170R1 |
| Issued by |
 Europe |
| Issue date |
2006-07-11 |
| Effective date |
2006-07-31 |
| EASA approval number |
2005-6353R1 |
| ATA Chapter |
62, 65 |
Approval Holder
/ Type Designation |
-
AIRBUS HELICOPTERS
-
SA/AS 365 / EC 155
-
AS 365 N2
-
AS 365 N3
-
SA 365 C1
-
SA 365 C2
-
SA 365 C3
-
SA 365 N
-
SA 365 N1
|
| Revision |
Not applicable
|
| Correction |
Not applicable
|
| Supersedure |
The results of the examinations and analyses have shown that the rate of growth of the crack is very slow and that the TBO for these assemblies is sufficient for the crack to be detected before it becomes critical. Consequently, DGAC France AD F-2005-170 is cancelled by EASA 2005-6353R1.
|
| Publication(s) and related information |
|
| Remarks |
Comments regarding this AD should be referred to the Safety Information Section, Certification Directorate, EASA;
E-mail:
ADs [at] easa.europa [dot] eu
|
