Airworthiness Directive · Amendment 39-14492 · Airbus Model A321-100 Series Airplanes
Airbus Model A321-100 Series Airplanes
Superseded. A later AD replaced this one: AD 2006-04-11 R1. Comply with the one in force.
This AD applies to Airbus Model A321-111, -112, and -131 airplanes, certificated in any category; all manufacturer serial numbers (MSN), except MSN 364 and 365; and except for those airplanes that have received Airbus Modification 24977 in production.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A321-111, -112, and -131 series airplanes. That AD currently requires repetitive inspections to detect fatigue cracking in the area surrounding certain attachment holes of the forward pintle fittings of the main landing gear (MLG) and the actuating cylinder anchorage fittings on the inner rear spar; and repair, if necessary. The existing AD also provides for optional terminating action for the repetitive inspections. This AD adds inspections of three additional mounting holes and revises the thresholds for the currently required inspections. This AD results from manufacturer analysis of the fatigue and damage tolerance of the area surrounding certain mounting holes of the MLG. We are issuing this AD to detect and correct fatigue cracking on the inner rear spar of the wings, which could result in reduced structural integrity of the airplane.
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 20,000 total flight cycles, or within 120 days after December 18, 1998 (the effective date of AD 98-25-05, amendment 39-10928), whichever occurs later, perform an ultrasonic inspection to detect fatigue cracking in the area surrounding certain attachment holes of the forward pintle fittings of the MLG and the actuating cylinder anchorage fittings on the inner rear spar, in accordance with Airbus Service Bulletin A320-57-1101, dated July 24, 1997; or Revision 02, dated October 25, 2001.
(1) If no cracking is detected, prior to further flight, repair the sealant in the inspected areas and repeat the ultrasonic inspections thereafter at intervals not to exceed 7,700 flight cycles, until paragraph (g), (i), or (k) of this AD is accomplished.
(2) If any cracking is detected, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Generale de l'Aviation Civile (DGAC) (or its delegated agent).
Accomplishment of visual and eddy current inspections to detect cracking in the area surrounding certain attachment holes of the forward pintle fittings of the MLG and the actuating cylinder anchorage fittings on the inner rear spar; follow-on corrective actions, as applicable; and rework of the attachment holes; in accordance with Airbus Service Bulletin A320-57-1100, including Appendix 01, dated July 28, 1997; or Revision 03, including Appendices 01 and 02, dated January 16, 2003; constitutes terminating action for the repetitive inspection requirements of this AD. Actions accomplished in accordance with Airbus Service Bulletin A320-57-1100, Revision 01, including Appendices 01 and 02, dated June 4, 1999; or Revision 02, including Appendices 01 and 02, dated October 25, 2001; are considered acceptable for compliance with the optional terminating action specified in this paragraph. If any cracking is detected during accomplishment of any inspection described in the service bulletin, and the service bulletin specifies to contact Airbus for appropriate action: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent).
For airplanes on which the initial inspection required by paragraph (f) of this AD has not been accomplished as of April 21, 2004 (the effective date of AD 2004-07-15): Accomplish the inspection required by paragraph (f) of this AD, at the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 5,500 flight cycles or 10,200 flight hours, whichever occurs first, until paragraph (g) or (k) of this AD is accomplished. Accomplishment of this paragraph eliminates the need to accomplish repetitive inspections at the intervals required by paragraph (f)(1) of this AD.
(1) Prior to the accumulation of 20,000 total flight cycles.
(2) Prior to the accumulation of 37,300 total flight hours, or within 120 days after April 21, 2004, whichever occurs later.
(i) For airplanes on which the initial inspection required by paragraph (f) of this AD has been accomplished as of April 21, 2004, and no cracking was found: Do the next inspection at the earlier of the times specified in paragraphs (i)(1) and (i)(2) of this AD, and repeat the inspection thereafter at intervals not to exceed 5,500 flight cycles or 10,200 flight hours, whichever occurs first, until paragraph (g) or (k) of this AD is accomplished. Accomplishment of this paragraph terminates the repetitive inspections required by paragraph (f)(1) of this AD.
(1) Within 7,700 flight cycles since the most recent inspection.
(2) At the later of the times specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD:
(i) Within 5,500 flight cycles or 10,200 flight hours since the most recent inspection, whichever occurs first.
(ii) Within 120 days after April 21, 2004.
If any cracking is detected during any inspection required by paragraph (h) or (i) of this AD: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent).
Within the applicable compliance times specified by paragraph (k)(1), (k)(2), or (k)(3) of this AD, perform an ultrasonic inspection for cracking of the attachment holes of the MLG pintle fittings in the inner rear spar in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1101, Revision 03, dated July 30, 2003; or Revision 04, dated November 22, 2004. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 5,500 flight cycles or 10,200 flight hours, whichever occurs first, until paragraph (g) of this AD is accomplished. Accomplishment of this paragraph terminates the repetitive inspections required by paragraphs (f)(1), (h), and (i) of this AD.
(1) For airplanes that have never been inspected in accordance with Airbus Service Bulletin A320-57-1101, dated July 24, 1997; or Revision 02, dated October 25, 2001: Before the accumulation of 20,000 total flight cycles or 37,300 total flight hours, whichever occurs first; or within 120 days after the effective date of this AD; whichever occurs later.
(2) For airplanes previously inspected in accordance with Airbus Service Bulletin A320-57-1101, dated July 24, 1997; or Revision 02, dated October 25, 2001, that have accumulated less than 18,900 total flight cycles or 35,300 total flight hours as of the effective date of this AD: Within 5,500 flight cycles or 10,200 flight hours, whichever occurs first, after the previous inspection performed in accordance with Airbus Service Bulletin A320-57-1101, Revision 02, dated October 25, 2001; or within 120 days after the effective date of this AD; whichever occurs later.
(3) For airplanes previously inspected in accordance with Airbus Service Bulletin A320-57-1101, dated July 24, 1997; or Revision 02, dated October 25, 2001, that have accumulated 18,900 or more flight cycles or 35,300 or more flight hours as of the effective date of this AD: Before the accumulation of 24,400 total flight cycles or 45,600 total flight hours, whichever occurs first; or within 120 days after the effective date of this AD; whichever occurs later.
If any crack is detected during any inspection required by paragraph (k) of this AD: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent).
Although Airbus Service Bulletin A320-57-1101, Revision 02, dated October 25, 2001; and Revision 04, dated November 22, 2004; describe procedures for reporting inspection findings to Airbus, this AD does not require such a report.
