Document ID: chunk:federal_register_of_legislation:F2006B08272:body:0
Version: federal_register_of_legislation:F2006B08272
Segment Type: other
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 Cessna 340 Series Aeroplanes

AD/CESSNA340/27 Wing Front Spar Lower Attachment Fittings 6/89

 Applicability: All models.

             Requirement: 1. Remove the fairing between the wing and carry-thru and gain access to the wing front spar lower attachment fittings P/N 0822550.

2.    Visually inspect the upper and lower edges of the lug of each wing fitting, looking for cracks as shown in the figure below.

3.    From inside the wheel well, visually inspect each visible wing fitting for cracks and surface pitting in the area shown in the figure.

            Note: It is not necessary to remove the primer for any of the above inspections.

                     Wing Fitting Showing Typical Cracking

                     Note: Fitting Shown removed from aircraft for clarity

            Compliance: Before exceeding 5000 hours component time in service or before the issue of the next Maintenance Release after 15 June 1989, whichever is the later. Thereafter, reinspect at each scheduled inspection for issue of a new Maintenance Release.

            Background:  Fatigue cracking has been discovered in the wing fitting from an Australian-registered Cessna 310R with 6500 hours time in service. No abnormality could be found in the fitting or the aircraft's history. Since then stress corrosion cracking has been found in a similar wing fitting in a Cessna 402C with 6400 hours time in service.

            There is insufficient evidence to regard either of these as isolated occurrences: either or both may be expected to occur at a later time elsewhere in the fleet of Cessna twins which use the same generic wing fitting. A simple repetitive visual inspection has therefore been introduced.