Airworthiness Directive · Amendment 39-18370 · Wings
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2018-13-08. 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 (MSN) 0001 through 0155 inclusive.
We are superseding Airworthiness Directive (AD) 98-18-26, for certain Airbus Model A320 series airplanes. AD 98-18-26 required repetitive inspections to detect fatigue cracking of the front spar vertical stringers on the wings; and repair, if necessary. This new AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame 36, a rototest inspection for cracking of the fastener holes of the front spar vertical stringers on frame 36, and repair if necessary. This AD was prompted by reports that indicate new repetitive inspections having new thresholds and intervals are needed and that additional work is needed to accomplish the inspections on airplanes on which a previous modification has been accomplished. We are issuing this AD to detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airframe.
Within the applicable compliance times specified in paragraphs (h)(1) through (h)(4) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame 36, and do a rototest inspection for cracking of the fastener holes of the front spar vertical stringers on frame 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1178, Revision 01, dated May 28, 2014, including Appendix 01, dated May 28, 2014. Repeat the inspections thereafter at the compliance times specified in paragraphs (g)(1) and (g)(2) of this AD.
(1) For Configuration 1 airplanes identified in paragraph (h)(1) of this AD: At intervals not to exceed 8,800 flight cycles or 17,700 flight hours, whichever occurs first.
(2) For Configuration 2, 3, and 4 airplanes identified in paragraphs (h)(2) through (h)(4) of this AD: At intervals not to exceed 24,900 flight cycles or 49,800 flight hours, whichever occurs first.
Do the initial inspections required by paragraph (g) of this AD within the applicable compliance times specified in paragraphs (h)(1) through (h)(4) of this AD.
(1) For Configuration 1 airplanes, having MSNs 0001 through MSN 0079 inclusive, on which the modification specified by Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997, has not been accomplished: Inspect at the later of the times specified by paragraphs (h)(1)(i) through (h)(1)(iii) of this AD.
(i) Inspect at the later of the times specified by paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of this AD.
(A) Prior to the accumulation of 24,000 flight cycles or 48,000 flight hours, whichever occurs first since airplane first flight.
(B) Within 60 days after the effective date of this AD.
(ii) Inspect within 8,800 flight cycles or 17,700 flight hours, whichever occurs first, since the last inspection specified in Airbus Service Bulletin A320-57-1016 was accomplished.
(iii) Inspect within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD, without exceeding 14,000 flight cycles after the last inspection specified in Airbus Service Bulletin A320-57-1016 was accomplished.
(2) For Configuration 2 airplanes, having MSNs 0001 through 0079 inclusive, on which the actions specified by Airbus Service Bulletin A320-57-1016, have not been done prior to accomplishing the actions specified by Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997: Inspect at the later of the times specified by paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Within 8,800 flight cycles or 17,700 flight hours, whichever occurs first, since the modification specified in Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated December 6, 1995, was accomplished.
(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.
(3) For Configuration 3 airplanes, having MSNs 0001 through 0079 inclusive, on which the actions specified by Airbus Service Bulletin A320-57-1016, have been done prior to accomplishing the actions specified by Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997: Inspect at the later of the times specified by paragraphs (h)(3)(i) and (h)(3)(ii) of this AD.
(i) Within 24,900 flight cycles or 49,800 flight hours, whichever occurs first, since the modification specified in Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997, was accomplished.
(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.
(4) For Configuration 4 airplanes, having MSNs 0080 through 0155 inclusive: Inspect at the later of the times specified in paragraphs (h)(4)(i) or (h)(4)(ii) of this AD.
(i) Prior to the accumulation of 54,300 flight cycles or 108,600 flight hours, whichever occurs first since airplane first flight.
(ii) Within 60 days after the effective date of this AD.
If any crack is detected during any inspection required by paragraph (g) 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).
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
