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/A320/79
Amdt 2
Fuselage Frame 68 10/98
Applicability: All model A320 aircraft without Airbus Industrie modifications 21780 and 21781 or Airbus Industrie Service Bulletin A320-53-1090.
Requirement: 1. Inspect frame 68 between stringers 4 and 5 in accordance with instructions of Airbus Industrie Service Bulletin A320-53-1089.
2. In the case of no crack findings, repeat the Requirement 1 inspection, or modify the frame in accordance with the instructions of Airbus Industrie Service Bulletin A320-53-1090.
3. In the case of crack findings, repair in accordance with the instructions of Airbus Industrie A320-53-1089 Revision 1.
Note 1: Total accomplishment of Service Bulletin A320-53-1090 cancels the requirements of this Directive; and, no further inspection is required for areas repaired in accordance with the instructions of Service Bulletin A320-53-1089 Revision 1.
Note 2: DGAC AD 96-298-093(B) R2 refers.
Compliance: 1. Before the accumulation of 20,000 flight cycles.
2. Repeat at intervals not to exceed 20,000 flight cycles.
3. Before further flight after inspection.
This amendment becomes effective on 10 September 1998.
Background: This Directive was raised as a result of cracking found in the fatigue test specimen, which could occur on an in-service aircraft and adversely affect the structural integrity. Amendment 1 clarified the applicability and included modification status information.
Amendment 2 is issued in response to a new revision of the related DGAC AD which introduces additional information in the cases of crack and no crack findings and expands applicability to all aircraft.
Amendment 1 of this Airworthiness Directive became effective on 24 April 1997.
The original issue of this Airworthiness Directive became effective on 27 March 1997.