Airworthiness Directive · Amendment 39-18380 · Wings
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2018-02-12. Comply with the one in force.
This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, manufacturer serial numbers 0002 through 0104 inclusive.
We are superseding Airworthiness Directive (AD) 96-18-06 for certain Airbus Model A320-211 and -231 airplanes. AD 96-18-06 required visual inspections to detect cracks of the pressurized floor fittings at frame 36, and renewal of the zone protective finish or replacement of fittings with new fittings if necessary. Since we issued AD 96-18- 06, an extended service goal analysis by the manufacturer revealed that the compliance times and repetitive inspection intervals should be reduced to meet the design service goal. This AD retains the requirements of AD 96-18-06, with reduced compliance times and repetitive inspection intervals. This AD also adds Model A320-212 airplanes to the applicability. We are issuing this AD to detect and correct fatigue cracking in the pressurized floor fittings at frame 36, which could result in failure of a floor fitting and subsequent depressurization of the fuselage.
This paragraph restates the requirements of paragraph (a) of AD 96-18-06, Amendment 39-9730 (61 FR 46703, September 5, 1996), with revised service information for Airbus Model A320-211 and -231 airplanes. Prior to the accumulation of 16,000 total landings, or within 6 months after October 10, 1996 (the effective date of AD 96-18-06), whichever occurs later, perform a visual inspection to detect cracks of the 6 fittings of the pressurized floor at frame 36 under the lower surface panel, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph. Accomplishment of the initial inspection required by paragraph (i) of this AD terminates the actions required by this paragraph.
(1) If no cracking is found, prior to further flight, renew the zone protective finish, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph. Repeat the visual inspection thereafter at intervals not to exceed 12,000 landings.
(2) If only 1 of the 6 fittings is found to be cracked and that crack is less than or equal to 0.59 inch (15 mm) in length, prior to further flight, replace the cracked fitting with a new fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. Thereafter, prior to the accumulation of 500 landings following accomplishment of this replacement, replace the remaining 5 fittings with new fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph.
(3) If only 1 of the 6 fittings is found to be cracked, and that crack is greater than 0.59 inch (15 mm) in length, prior to further flight, replace all six fittings with new fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph.
(4) If 2 or more fittings are found to be cracked, prior to further flight, replace all 6 fittings with new fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph.
This paragraph restates the provisions of paragraph (b) of AD 96-18-06, Amendment 39-9730 (61 FR 46703, September 5, 1996), with revised service information for Airbus Model A320-211 and -231 airplanes. Replacement of all 6 fittings with new fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013; constitutes terminating action for the inspection requirements of paragraph (g) of this AD.
(1) At the latest of the times in paragraph (i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this AD: Do a detailed inspection of the pressurized floor fittings at frame 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. Repeat the inspection thereafter, at intervals not to exceed 9,300 flight cycles or 18,600 flight hours, whichever occurs first. Accomplishment of the initial inspection required by this paragraph terminates the actions required by paragraph (g) of this AD.
(i) Prior to the accumulation of 20,900 total flight cycles or 41,800 total flight hours, whichever occurs first.
(ii) Prior to the accumulation of 9,300 flight cycles or 18,600 flight cycles since the most recent inspection required by paragraph (g) or (i) of this AD, whichever occurs first.
(iii) At the earlier of the times specified in paragraph (i)(1)(iii)(A) and (i)(1)(iii)(B) of this AD.
(A) Prior to the accumulation of 1,250 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first.
(B) Prior to the accumulation of 12,000 flight cycles since the most recent inspection required by paragraph (g) or (i) of this AD.
(2) If any crack is found during any inspection required by paragraph (i)(1) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
Modification (replacement of aluminum fittings with titanium fittings) of the pressurized floor fittings at frame 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1029, Revision 02, dated June 16, 1999, is terminating action for the repetitive inspections required by paragraphs (g) and (i) 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
