Document ID: chunk:federal_register_of_legislation:F2006B01981:body:0
Version: federal_register_of_legislation:F2006B01981
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/91 Frames 43 and 44 Pressure Floor Connection 2/98

            Applicability: Model A320 with MSN 005 through 008, 010 through 014, and 016 through 043, without Modification 20941 or Service Bulletin A320-53-1015 incorporated.

             Requirement: 1. Inspect bolts and fittings of the frame to pressure floor connection at frames 43 and 44 in accordance with Airbus Industrie Service Bulletin A320-53-1083 revision 2.

2.    If bolts are found cracked and/or missing and/or fittings are cracked, apply the corresponding inspection program and corrective actions in accordance with the instructions given in Service Bulletins A320-53-1083 revision 2 and A320-53- 1015.

3.    If no crack is detected on the frames and bolts, repeat the inspection as defined in Requirement 1 of this Directive.

            Note: DGAC AD 97-316-110 (B) refers.

 Compliance: 1. Before the accumulation of 20,000 flights.

             2.    At the thresholds and intervals specified in the Requirement 2 documents.

            3.    At intervals not to exceed 5,100 flights after initial inspection. This airworthiness directive becomes effective on 29 January 1998.
            Background: During a full scale fatigue test, a bolt at frame 43, which connects the frame segment with the pressure floor, sheared off. A crack developed after further simulated flights.