Airworthiness Directive · Amendment 39-19436 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS Model A320-211 and Model A320-231 airplanes, certificated in any category, serial numbers 0029, 0045, 0046, 0049 through 0057 inclusive, 0059, 0064, and 0065.
We are superseding Airworthiness Directive (AD) 98-18-24, which applied to certain Airbus SAS Model A320 series airplanes. AD 98- 18-24 required repetitive inspections to detect cracking in the inner flange of a certain door frame, and corrective actions, if necessary. AD 98-18-24 also provided an optional terminating action for the repetitive inspections. This AD continues to require the repetitive inspections of the inner flange of a certain door frame, with reduced repetitive inspection intervals, and corrective action if necessary. This AD was prompted by a report of cracks on the inner flange of a certain door frame, and by the results of a full scale fatigue test that indicated the intervals for the repetitive inspections required by AD 98-18-24 must be reduced. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (a) of AD 98-18-24, with no changes. For Model A320 series airplanes on which Airbus Modification 21778 (reference Airbus Service Bulletin A320-53-1072, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996) has not been accomplished: Prior to the accumulation of 20,000 total flight cycles, or within 1 year after October 20, 1998 (the effective date of AD 98-18-24), whichever occurs later: Perform a rotating probe eddy current inspection to detect cracking around the edges of the gusset plate attachment holes of the inner flange of door frame 66, left and right, at stringer positions P18, P20, and P22, in accordance with Airbus Service Bulletin A320-53-1071, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996. If any crack is detected, prior to further flight, repair in accordance with a method approved by the Manager, International Section, Transport Standards Branch, FAA. Repeat the inspection thereafter at intervals not to exceed 20,000 flight cycles.
This paragraph restates the optional terminating action of paragraph (b) of AD 98-18-24, with no changes. Modification of the gusset plate attachment holes of the inner flange of door frame 66, left and right (Airbus Modification 21778), in accordance with Airbus Service Bulletin A320-53-1072, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996, constitutes terminating action for the repetitive inspection requirements of paragraph (g) of this AD.
At the applicable compliance time specified in figure 1 to paragraph (i) of this AD, do a rotating probe eddy current inspection to detect cracking around the edges of the gusset plate attachment holes of the inner flange of door frame 66, left and right, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017. Repeat the inspection thereafter at intervals not to exceed 10,900 flight cycles.
(1) If, during any inspection required by paragraph (i) of this AD, any crack is found on a gusset plate attachment hole: Before further flight, repair the affected attachment hole, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017, except as required by paragraph (n) of this AD.
(2) If, during any inspection required by paragraph (i) of this AD, any crack is found on any other hole of the gusset plate: Before further flight, contact the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA); for approved repair instructions and accomplish those instructions accordingly. If approved by the DOA, the approval must include the DOA-authorized signature.
(1) Repair of a gusset plate attachment hole area as required by paragraph (j)(1) of this AD terminates the repetitive inspections required by paragraph (i) of this AD for that attachment hole area on that airplane only.
(2) Repair of any other hole of the gusset plate, as required by paragraph (j)(2) of this AD, does not terminate the repetitive inspections required by paragraph (i) of this AD for that airplane, unless specified otherwise in the repair instructions provided by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus's EASA DOA.
(3) Accomplishing the initial inspection required by paragraph (i) of this AD terminates the inspections required by paragraph (g) of this AD.
Modification of the gusset plate attachment holes of the inner flange of door frame 66, left and right, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1072, Revision 02, dated May 5, 2016, terminates the repetitive inspections required by paragraph (i) of this AD for that airplane.
Report the results of the inspection required by paragraph (i) of this AD that are done on or after the effective date of this AD to Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/), or submit the results to Airbus in accordance with the instructions of Airbus Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017. Submit the report within 30 days after accomplishing the inspection required by paragraph (i) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. If operators have reported findings as part of obtaining any corrective actions approved by the EASA DOA, operators are not required to report those findings as specified in this paragraph.
Where Airbus Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017, specifies to contact Airbus for appropriate action, and specifies that action as “RC” (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (q)(2) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
