Airworthiness Directive · Amendment 39-14332 · Airbus Model A320-111 Airplanes
Airbus Model A320-111 Airplanes
This AD applies to Airbus Model A320-111 airplanes, certificated in any category, having manufacturer serial number 002 through 021 inclusive.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A320-111 airplanes. The existing AD currently requires repetitive inspections for cracking in the front and rear faces and at the crown fittings of the upper stringers of the center wing box and applicable repairs. This new AD requires continuing the repetitive inspections at revised thresholds and intervals, and applicable repairs. This AD results from a manufacturer survey of airplanes affected by the existing inspection program that led to the consequent revision of the thresholds and intervals of the repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the upper stringers of the center wing box, which could lead to loss of structural integrity of the wing.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Prior to the accumulation of 6,500 total flight cycles or within 50 flight cycles after the effective date of this AD, whichever occurs later, except as provided by paragraph (g) of this AD, perform a detailed inspection for cracking in the front and rear faces and at the crown fittings of the upper stringers of the center wing box between frame (FR) 36 and FR42, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1030, Revision 03, dated August 28, 2002.
Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 5,500 flight cycles, in accordance with the service bulletin.
(2) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) or its delegated agent.
Airplanes that received an initial inspection prior to the effective date of this AD using any service information specified in paragraph (h) of this AD must receive the next inspection within 2,000 flight cycles after the effective date of this AD or 7,500 flight cycles since the last inspection, whichever occurs first; in accordance with paragraph (f) of this AD.
Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A320-57-1030, dated August 12, 1991; Revision 1, dated September 16, 1996; or Revision 02, dated February 20, 1998; are considered acceptable for compliance with the corresponding actions specified in paragraph (f) of this AD, except as provided by paragraph (g) of this AD.
(i) Although Airbus Service Bulletin A320-57-1030, Revision 03, dated August 28, 2002, describes procedures for reporting inspection findings to Airbus, this AD does not require such a report.
