Document ID: chunk:federal_register_of_legislation:F2008L01943:body:0:p2
Version: federal_register_of_legislation:F2008L01943
Segment Type: other
Provision Reference: 
Character Range: 2938–5314

to S/N4,420.637.
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.

                 Terminating Action

              Modification of the engine by installing P/N 881.831 spare part kit, which includes hydraulic valve tappet P/N 854.095, constitutes terminating action for the requirements of this AD.

              Note 2:  EASA 2006-0316 R1 dated 13 March 2008 refers. This AD supersedes EASA AD 2006-316-E.
Compliance:      1. Before further flight after the effective date of this AD, unless previously accomplished.

                 2. Remains unchanged as detailed in the original issue of this AD as: Within 5 hours operation after 20 October 2006 (the effective date of the original issue of this AD but not later than 1 March 2007 and thereafter at every oil change.

              Note 3:  Previous accomplishment with Requirement 2 of the original issue of this AD is considered acceptable to showing compliance with this AD.

                 3. Before further flight.

                 4. From the effective date of this AD.
              This Amendment becomes effective on 3 July 2008.

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.

             The manufacturer has introduced a new hydraulic tappet which does not require the inspections detailed in this AD.  For that reason this amendment limits the requirements to those engines not fitted with P/N 854.095 hydraulic tappets.

James Coyne
Delegate of the Civil Aviation Safety Authority

22 May 2008