For AS 355 E, F, F1, and F2, versions:
For AS 355 E, F, F1, and F2, versions:
For AS 355 E, F, F1, and F2, versions:
At 1200 flight hours bearing time since new, thereafter at 1200 flight hours bearing time since new.
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Commonwealth legislation
Requires replacement of tail-rotor pitch-change plate bearings on Eurocopter AS 355 E/F/F1/F2 at 1,200 flight hours since new, and requires that any bearing transfers between AS 355 versions follow the manufacturer's Master Servicing Manual (Chapter 05.99, Page P8). Issued after cracks were found in some bearings, the directive places inspection, replacement and any transfer-compliance costs and associated downtime on aircraft operators and maintenance organisations and is administered by the Civil Aviation Safety Authority.
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Direct links to the current provisions in AD/AS 355/57 Amdt 1 - Tail Rotor Hub Pitch Change Bearings.
At 1200 flight hours bearing time since new, thereafter at 1200 flight hours bearing time since new.
If bearings are to be transferred from one AS 355 version to another, apply the transfer rules defined in Master Servicing Manual, Chapter 05.99, Page P8.
This Amendment becomes effective on 31 October 2002.
Background: This Airworthiness Directive is prompted by advice from the DGAC that cracks have been found in some tail rotor pitch change plate bearings, which can lead to malfunction of the plate and loss of control of the helicopter.
AD/AS 355/57 Amdt 1 (continued)
This Amendment has been issued to reflect compliance that is now relevant. The original is sue of this Directive became effective 7 March 2001.
View image in the official source
James Coyne
Delegate of the Civil Aviation Safety Authority 24 September 2002
View image in the official source
The above AD is notified in the Commonwealth of Australia Gazette on 9 October 2002.
Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.
At 1200 flight hours bearing time since new, thereafter at 1200 flight hours bearing time since new.
If bearings are to be transferred from one AS 355 version to another, apply the transfer rules defined in Master Servicing Manual, Chapter 05.99, Page P8.
This Amendment becomes effective on 31 October 2002.
Background: This Airworthiness Directive is prompted by advice from the DGAC that cracks have been found in some tail rotor pitch change plate bearings, which can lead to malfunction of the plate and loss of control of the helicopter.
AD/AS 355/57 Amdt 1 (continued)
This Amendment has been issued to reflect compliance that is now relevant. The original is sue of this Directive became effective 7 March 2001.
James Coyne
Delegate of the Civil Aviation Safety Authority 24 September 2002
The above AD is notified in the Commonwealth of Australia Gazette on 9 October 2002.