Document ID: chunk:federal_register_of_legislation:F2006B04833:body:0:p2
Version: federal_register_of_legislation:F2006B04833
Segment Type: other
Provision Reference: 
Character Range: 2644–5113

50 hours time in service after 1 February 1996, whichever occurs later. Re-inspect at intervals not to exceed 100 hours time in service.

2.        Inspect in accordance with Requirement 2 before 500 hours aircraft time in service or 50 hours time in service after 1 February 1996, whichever occurs later. Re-inspect at intervals not to exceed 100 hours time in service.

3.        Inspect in accordance with Requirement 3 before further flight if no fluid is found in the tube as a result of Requirement 1.

           For CA25 aircraft with serial number greater than CA25010 and CA25N aircraft S/N CA25003 and S/N CA25N020 and above:

               1. Action in accordance with Requirement 1 before 1000 hours aircraft time in service or 100 hours time in service after 1 February 1996, whichever occurs later. Re-inspect at intervals not to exceed 200 hours time in service.

2.        Inspect in accordance with Requirement 2 before 1000 hours aircraft time in service or 100 hours time in service after 1 February 1996, whichever occurs later. Re-inspect at intervals not to exceed 200 hours time in service.

3.        Inspect in accordance with Requirement 3 before further flight if no fluid is found in the tube as a result of Requirement 1.

           Background: A CA22 Skyfox aircraft registered to the Australian Ultralight Federation experienced on inflight failure of the wing lift strut mount cross tube. The aircraft had previously been involved a landing accident and repaired. Failure occurred at a time well below the retirement life. The area of the failure is subject to a combination of tensile and bending stress.

               A once off dye penetrant inspection of the wing lift strut mount cross tube was required by the initial issue of this Directive. The laboratory examination of the failed tube has indicated that failure resulted from fatigue initiating at the toe of the weld. The examination also indicated that there was no evidence of crack initiation from the earlier accident.

               This amendment sets a threshold for inspection and requires repeat visual inspections to be made. The dye penetrant inspection is made conditional on the findings of the visual inspections. The two aircraft groups reflect a production change which introduced a stronger wing lift strut mount cross tube.

               This Directive does not remove the life limitation of the wing lift strut mount cross tube in AD/CA25/1 Amdt 1.