Airworthiness Directive · Amendment 39-18912 · Fuselage
Airbus Airplanes
This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, manufacturer serial numbers (S/Ns) 0001 through 0123 inclusive, except those that have embodied Airbus Modifications 21780 and 21781 in production.
We are superseding Airworthiness Directive (AD) 98-13-14, for certain Airbus Model A320-211, -212, and -231 airplanes. AD 98-13-14 required repetitive inspections of certain fastener holes of the aft fuselage, and corrective action if necessary. This new AD continues to require the actions in AD 98-13-14, with revised inspection compliance times. This AD was prompted by identification of cracks in the fastener holes of the former junction of the aft fuselage, which occurred during a fatigue test; and a determination that certain compliance times specified in AD 98-13-14 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 98-13-14, with additional methods of approving repairs. For Model A320 series airplanes, as listed in Airbus Service Bulletins A320-53-1089 and A320-53-1090, both dated November 22, 1995: Prior to the accumulation of 20,000 total flight cycles, or within 500 flight cycles after July 30, 1998 (the effective date of AD 98-13-14), whichever occurs later, perform a rotating probe inspection for fatigue cracking of the fastener holes and/or the adjacent tooling hole, as applicable, of the right- and left-hand former junctions at FR 68, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, dated November 22, 1995. Accomplishing an inspection required by paragraph (h) of this AD terminates the actions required by this paragraph.
(1) If no crack is detected, accomplish either paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) Repeat the inspection thereafter at intervals not to exceed 20,000 flight cycles; or
(ii) Prior to further flight following the accomplishment of the inspection required by paragraph (g) of this AD, cold work the fastener holes and/or the adjacent tooling hole of the right- and left-hand former junctions at FR 68, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1090, dated November 22, 1995. Accomplishment of this cold working constitutes terminating action for the repetitive inspections required by paragraph (g)(1)(i) of this AD.
(2) If any crack is detected, prior to further flight, repair in accordance with 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).
Within the compliance time specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, whichever occurs latest: Accomplish a special detailed rototest inspection for fatigue cracking of the frame junction holes and the adjacent tooling hole, as applicable, of the right- and left-hand former junctions at FR 68, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, Revision 04, dated June 1, 2016. Repeat the inspection thereafter at intervals not to exceed 3,800 flight cycles or 7,600 flight hours, whichever occurs first, until a repair required by paragraph (i) of this AD is done or a modification specified in paragraph (j) of this AD is done. Accomplishing an inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD.
(1) Within 28,700 flight cycles or 57,400 flight hours since airplane first flight, whichever occurs first.
(2) Within 3,800 flight cycles or 7,600 flight hours, whichever occurs first, since the most recent inspection done as specified in the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089.
(3) Within 3,800 flight cycles or 7,600 flight hours after the effective date of this AD, whichever occurs first, without exceeding 20,000 flight cycles since the most recent inspection done as specified in the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089.
If any crack is detected during any inspection required by paragraph (h) of this AD: Before further flight, repair, including doing all applicable related investigative actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, Revision 04, dated June 1, 2016. Do all applicable related investigative actions before further flight. Repair of an airplane in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, Revision 04, dated June 1, 2016, constitutes terminating action for the repetitive inspections required by paragraph (h) of this AD.
Modification of an airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1090, Revision 02, dated December 22, 1998, constitutes terminating action for the repetitive inspections required by paragraphs (g) and (h) of this AD, provided the modification is accomplished before further flight after accomplishing an inspection required by paragraph (h) of this AD and no cracks were detected.
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
