Document ID: chunk:federal_register_of_legislation:F2008L00624:body:0:p2
Version: federal_register_of_legislation:F2008L00624
Segment Type: other
Provision Reference: 
Character Range: 2735–4289

flight hours if no cracking is detected; or,

             At the latest, upon accumulation of 8,810 flight hours on helicopters that have logged less than 8,800 flight hours, and thereafter at intervals not to exceed 10 flight hours if no cracking is detected.

             For Requirement 2.a:

             Repeat the inspection at intervals not to exceed 50 flight hours, and following embodiment of an approved skin repair, resume the Requirement 1 inspection at intervals not to exceed 10 flight hours.

             For Requirement 3:

             Within 300 flight hours or 6 months after 25 February 2008, whichever occurs first, on helicopters that have logged 8,800 or more flight hours; or,

             Within 300 flight hours or 6 months, whichever occurs first after accumulating 8,800 flight hours, on helicopters that have logged 8,800 or more flight hours.
             This Airworthiness Directive becomes effective on 25 February 2008.
Background:  Cracking was discovered in fuselage frame 5295 on an AS 332 L helicopter.  The helicopter was fitted with a frame 5295 comprising plates and angles assembled by riveting that corresponds to the original definition of that frame i.e. before embodiment of MOD 0722907.  The crack in frame 5295 was detected subsequent to a daily check, during which the presence of cracks were detected in the outer skin and in the butt strap where the rail of the MGB sliding cowling is attached on frame 5295.

David Villiers
Delegate of the Civil Aviation Safety Authority

22 February 2008