2006-04-11 Airbus: Amendment 39-14492. Docket No. FAA-2006-23935; Directorate Identifier 2005-NM-060-AD.
Effective Date
(a) This AD becomes effective March 8, 2006.
Affected ADs
(b) This AD supersedes AD 2004-07-15.
Applicability
(c) 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.
Unsafe Condition
(d) This AD results from manufacturer analysis of the fatigue and damage tolerance of the area surrounding certain mounting holes of the main landing gear (MLG). The FAA is 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.
Compliance
(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Restatement of Requirements of AD 2004-07-15
Repetitive Inspections and Corrective Actions
(f) 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).
Optional Terminating Action
(g) 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).
Repetitive Inspections for Airplanes Not Previously Inspected Per Paragraph (f)
(h) 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.
Repetitive Inspections for Airplanes Previously Inspected Per Paragraph (f)
(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.
Existing Repair
(j) 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).
New Requirements of This AD
Initial and Repetitive Inspections
(k) 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 inthe 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; orRevision 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.
New Repair
(l) If any crack is detected during any inspection requiredby 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).
No Reporting Requirement
(m) 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.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, International Branch, ANM-116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office.
Related Information
(o) French airworthiness directive F-2004-166, dated October 13, 2004, also addresses the subject of this AD.
Material Incorporated by Reference
(p) You must use the service information specified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise.
Table 1.--All Material Incorporated by Reference
Airbus service bulletin
Revision level
Date
A320 57 1100, including Appendix 01
Original
July 28, 1997.
A320 57 1100, including Appendices 01 and 02
03
January 16, 2003.
A320 57 1101
Original
July 24, 1997.
A320 57 1101
02
October 25, 2001.
A320 57 1101
03
July 30, 2003.
A320 57 1101
04
November 22, 2004.
The optional terminating action specified in paragraph (g) of this AD should be done in accordance with the service bulletins specified in Table 2 of this AD.
Table 2.--Optional Service Bulletins
Airbus service bulletin
Revision level
Date
A320 57 1100, including Appendix 01
Original
July 28, 1997.
A320 57 1100, including Appendices 01 and 02
03
January 16, 2003.
(1) The Director of the Federal Register approved the incorporation by reference of the service bulletins specified in Table 3 of this AD, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Table 3.--New Material Incorporated by Reference
Airbus service bulletin
Revision level
Date
A320 57 1100, including Appendix 01
Original
July 28, 1997.
A320 57 1100, including Appendices 01 and 02
03
January 16, 2003.
A320 57 1101
03
July 30, 2003.
A320 57 1101
04
November 22, 2004.
(2) The incorporation by reference of Airbus Service Bulletin A320-57-1101, Revision 02, dated October 25, 2001, was approved previously by the Director of the Federal Register as of April 21, 2004 (69 FR 17906, April 6, 2004).
(3) The incorporation by reference of Airbus Service Bulletin A320-57-1101, dated July 24, 1997, was approved previously by the Director of the Federal Register as of December 18, 1998 (63FR 66753, December 3, 1998).
(4) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html .