AD/Rotax/22 Camshaft Hydraulic Tappet Wear (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Rotax Piston Engines

AD/ROTAX/22 Camshaft Hydraulic Tappet Wear 13/2006 TX

Applicability:

BRP-Rotax GmbH & Co. KG; Bombardier-Rotax GmbH & Co. KG; Bombardier-Rotax GmbH:

Rotax 912 A series engines from serial number (S/N) 4,410.681 onwards; and

Rotax 912 F series engines from S/N 4,412.912 onwards; and

Rotax 912 S series engines from S/N 4,923.263 onwards; and

Rotax 914 F series engines from S/N 4,420.595 onwards; and

Any S/N engine on which the camshaft and/or the hydraulic valve tappets have been replaced (e.g. during engine repair or general overhaul) after 1 January 2006.

Requirement:

1.    Inspect the magnetic plug in accordance with BRP-Rotax ASB-912-051 or
ASB-914-034, both dated 13 October 2006, or later approved revision as is applicable.

2.    Repeat the inspection as detailed in Requirement 1 of this AD.

3.    If during the inspection detailed in Requirements 1 or 2 of this AD metal parts greater than 3mm are detected as detailed in Figure 1 and 2 of ASB-912-051 or ASB-914-034 both dated 13 October 2006, or later approved revision as is applicable, carry out investigation and rectification of the cause of the defect.

4.    Do not install an engine listed in the applicability section of this AD unless the magnetic plug has been inspected in accordance with the requirements detailed in Requirement 1 of this AD.

Note:  EASA AD 2006-0316-E dated 16 October 2006 refers.

Compliance:

1.    Before further flight after the effective date of this AD, unless previously accomplished.

2.    Within 5 hours operation after the effective date of this AD but not later than
1 March 2007 and thereafter at every oil change.

3.    Before further flight.

4.    From the effective date of this AD.

This Airworthiness Directive becomes effective on 20 October 2006.

Background:

Increased wear of the camshaft/hydraulic valve tappet can occur.  This may lead to improper engine operation, power loss or in-flight engine failure.

James Coyne
Delegate of the Civil Aviation Safety Authority

17 October 2006