AD/A320/52 - Rear Fuselage Skin Lap Joints

Airworthiness Directive - AD/A320/52 - Rear Fuselage Skin Lap Joints Airworthiness Directive - AD/A320/52 - Rear Fuselage Skin Lap Joints CASA Airworthiness Directive Jurisdiction:Commonwealth of Australia;CorporateName:Civil Aviation Safety Authority; Issue 5/1995,Aircraft above 5700 kg,Airbus Industrie A319, A320 and A321 Series Aeroplanes,Rear Fuselage Skin Lap Joints,52 DellaCa, Donna 2 0 2022-10-28T00:29:00Z 2022-10-28T00:29:00Z 1 245 1402 Office of Parliamentary Counsel 11 3 1644 16.0000 2006-09-22T00:00:00Z Toolkit http://www.activepdf.com 2022-10-28T00:00:00Z 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/A320/52   Rear Fuselage Skin Lap Joints   5/95 Applicability:   A320 series aircraft, serial numbers in Airbus Industrie Service Bulletin (SB) A320- 53-1057, without Modification 21905K2008 incorporated.   Requirement:   Inspect, using detailed visual or eddy current method, the upper rivet row of the longitudinal lap joints between:-   Frame 48 and Frame 64 next to stringer 6 LH and RH Frame 60 and Frame 64 next to stringer 32 LH Frame 59 and Frame 64 next to stringer 32 RH Frame 58 and Frame 64 next to stringer 41 RH Inspect in accordance with Airbus Industrie SB A320-53- 1057.   Note: The inspection of stringer 32 RH lap joint is only applicable to aircraft SN 003, 004, 045 to 051, 056 and 057 which do not have the additional rear cargo door installed (modification number 20029).   Compliance:   Initially inspect before 20 000 flights.   Re-inspect at intervals not to exceed:   4 000 flights, if last inspected visually; or,   ii.    12 000 flights, if last inspected by eddy current.   Note: Modification in accordance with Airbus Industrie SB A320-53-1056, after the inspection area has been shown to be crack free, cancels the inspection requirements of this AD.   Background:   Cracks have been found in the longitudinal lap joints of the fatigue test specimen at 76000 flights. Inspections around NAS1097-5 rivets installed in upper skins which are less than 1.8 mm thick are required to prevent multi-site damage causing loss of pressurisation.