Document ID: chunk:federal_register_of_legislation:F2006L01297:body:0:p3
Version: federal_register_of_legislation:F2006L01297
Segment Type: other
Provision Reference: 
Character Range: 5458–7505

already accomplished, within 300 hours time in service after 8 June 2006, unless accomplished within the last 4,700 hours time in service.

                  a. Within 5,000 hours time in service after the initial inspection.

                     (i) Within 5,000 hours time in service after the Requirement 1.a. inspection, and thereafter at intervals not to exceed 5,000 hours time in service.

                     (ii) Within 7,500 hours time in service after the Requirement 1.a. inspection, and thereafter at intervals not to exceed 7,500 hours time in service.

                  b. Within 5,000 hours time in service after the initial inspection, and thereafter at intervals not to exceed 5,000 hours time in service.

                2. Unless already accomplished, within 1,500 hours time in service after 8 June 2006, unless accomplished within the last 3,500 hours time in service.

                3. Unless already accomplished, within 3,000 hours time in service after 8 June 2006, unless accomplished within the last 4,500 hours time in service.  Repetitively inspect thereafter at intervals not to exceed 7,500 hours time in service.

                4. Unless already accomplished, within 3,000 hours time in service after 8 June 2006, unless accomplished within the last 7,000 hours time in service.  Repetitively inspect thereafter at intervals not to exceed 10,000 hours time in service.

                5. Unless already accomplished, within 3,000 hours time in service after accumulating 25,000 hours time in service.  Repetitive inspections must be performed at the intervals required by Requirements 1 through 4.

                6. As specified in Requirement 6.
             This Airworthiness Directive becomes effective on 8 June 2006.
Background:  The FAA requires certain actions to prevent loss of structural integrity of the aircraft, due to longitudinal cracks in the stringer or beltframe at the beltframe attach points.

David Villiers
Delegate of the Civil Aviation Safety Authority

11 April 2006