Airworthiness Directive · Amendment 39-18354 · Wings
Airbus Airplanes
This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 22418 has been embodied in production.
We are superseding Airworthiness Directive (AD) 2004-14-09 for certain Airbus Model A320-211, -212, and -231 airplanes. AD 2004-14-09 required repetitive inspections for fatigue cracking of the lower surface panel on the wing center box, and repair if necessary; and modification of the lower surface panel on the wing center box, which constitutes terminating action for the repetitive inspections. This new AD retains the requirements of AD 2004-14-09, reduces the compliance times for the repetitive inspections, and requires an additional repair for certain airplanes. This AD was prompted by a determination that, based on the average flight duration, the average weight of fuel at landing is higher than that defined for the analysis of the fatigue-related tasks; and that shot peening might have been improperly done on the chromic acid anodizing (CAA) protection, which would adversely affect fatigue crack protection. We are issuing this AD to detect and correct fatigue cracking of the lower surface panel on the wing center box, which could result in reduced structural integrity of the airplane.
This paragraph restates the requirements of paragraph (a) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. Except as provided by paragraph (k) of this AD: Prior to the accumulation of 20,000 total flight cycles, or within 60 days after November 27, 1998 (the effective date of AD 98-22-05, Amendment 39-10851 (63 FR 56542, October 22, 1998)), whichever occurs later, perform a high frequency eddy current (HFEC) inspection to detect fatigue cracking of the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002. Repeat the HFEC inspection thereafter at intervals not to exceed 7,500 flight cycles until the actions required by paragraph (i) of this AD are accomplished.
This paragraph restates the requirements of paragraph (b) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. Except as provided by paragraph (j) of this AD, if any cracking is detected during any inspection required by paragraph (g) of this AD: Prior to further flight, repair in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002. Accomplishment of the repair constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD for the repaired area only.
This paragraph restates the requirements of paragraph (c) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with new terminating action provided. Prior to the accumulation of 25,000 total flight cycles, or within 60 days after November 27, 1998 (the effective date of AD 98-22-05, Amendment 39-10851 (63 FR 56542, October 22, 1998)), whichever occurs later: Perform an HFEC inspection to detect fatigue cracking of the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002. Accomplishment of the initial inspection required by paragraph (p) of this AD constitutes terminating action for the inspection requirements of this paragraph.
(1) If no cracking is detected: Prior to further flight, modify the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997; or Revision 05, dated April 30, 2002. Accomplishment of the modification constitutes terminating action for the requirements of paragraph (g) of this AD.
(2) Except as provided by paragraph (j) of this AD: If any cracking is detected, prior to further flight, repair in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, or Revision 03, dated April 30, 2002; and modify any uncracked area, in accordance with Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997, or Revision 05, dated April 30, 2002. Accomplishment of the repair of cracked area(s) and modification of uncracked area(s) constitutes terminating action for the requirements of paragraph (g) of this AD.
This paragraph restates the requirements of paragraph (d) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with revised repair instructions. If any cracking is detected during any inspection required by paragraph (h) or (i)(2) of this AD, and the applicable service bulletin specifies to contact Airbus for an appropriate action: Prior to further flight, repair using a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). After the effective date of this AD only repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA.
This paragraph restates the provision of paragraph (e) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. The actions required by paragraph (g) of this AD are not required to be accomplished if the requirements of paragraph (i) of this AD are accomplished at the time specified in paragraph (g) of this AD.
This paragraph restates the requirements of paragraph (f) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with terminating action provided. For airplanes on which neither the inspection required by paragraph (g) of this AD nor the modification required by paragraph (i)(1) of this AD has been done before August 13, 2004 (the effective date of AD 2004-14-09): Perform an HFEC inspection to detect fatigue cracking of the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002; at the later of the times specified in paragraphs (l)(1) and (l)(2) of this AD. Accomplishment of the inspection required by this paragraph terminates the requirements of paragraph (g) of this AD. Accomplishment of the initial inspection required by paragraph (p) of this AD terminates the inspection requirements of this paragraph.
(1) Prior to the accumulation of 13,200 total flight cycles or 39,700 total flight hours, whichever is first.
(2) Prior to the accumulation of 20,000 total flight cycles, or within 3,500 flight cycles after August 13, 2004 (the effective date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004)), whichever is later.
This paragraph restates the requirements of paragraph (g) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. If no cracking is detected during the inspection required by paragraph (g) or (l) of this AD: Repeat the inspection required by paragraph (l) of this AD at the applicable time specified in paragraph (m)(1) or (m)(2) of this AD. Accomplishment of the modification required by paragraph (i)(1) of this AD terminates the requirements of this paragraph.
(1) For airplanes on which the inspections required by paragraph (g) of this AD have been initiated before August 13, 2004 (the effective date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004)): Do the next inspection within 5,700 flight cycles after accomplishment of the last inspection, or within 1,800 flight cycles after August 13, 2004, whichever is later. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles.
(2) For airplanes on which no inspection required by paragraph (g) of this AD has been done before August 13, 2004 (the effective date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004)): Do the next inspection within 5,700 flight cycles after accomplishment of the inspection required by paragraph (l) of this AD. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles.
This paragraph restates the requirements of paragraph (h) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with revised repair instructions. If any cracking is detected during any inspection required by paragraph (l) or (m) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, or Revision 03, dated April 30, 2002; and modify any uncracked area, in accordance with Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997, or Revision 05, dated April 30, 2002. Where Airbus Service Bulletin A320-57-1082 specifies to contact Airbus for an appropriate repair action: Prior to further flight, repair using a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the DGAC (or its delegated agent)); or EASA; or Airbus's EASA DOA. After the effective date of this AD only repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Accomplishment of the repair of cracked area(s) and modification of uncracked area(s) constitutes terminating action for the requirements of paragraphs (g) through (n) of this AD.
For airplanes on which the actions specified in Airbus Service Bulletin A320-57-1043 have not been accomplished, and on which a repair has been accomplished, as specified in the service information identified in paragraph (o)(1), (o)(2), (o)(3), or (o)(4) of this AD: Within 30 days after the effective date of this AD, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the EASA; or Airbus's EASA DOA.
(1) Airbus Service Bulletin A320-57-1082, dated October 31, 1996.
(2) Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997.
(3) Airbus Service Bulletin A320-57-1082, Revision 02, dated July 26, 1999.
(4) Airbus Service Bulletin A320-57-1082, Revision 03, dated April 30, 2002.
At the applicable time specified in paragraphs (p)(1) and (p)(2) of this AD: Do an HFEC inspection for cracking of the lower surface panel on the WCB, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1082, Revision 04, dated December 5, 2013. Repeat the inspection of the lower surface panel on the WCB thereafter at intervals not to exceed 7,200 flight cycles or 14,400 flight hours, whichever occurs first. Accomplishment of the initial inspection required by this paragraph terminates the inspections required by paragraphs (g), (i), and (l) of this AD.
(1) For airplanes on which the actions specified in Airbus Service Bulletin A320-57-1043 have not been done: At the later of the times specified in paragraphs (p)(1)(i) and (p)(1)(ii) of this AD.
(i) Before the accumulation of 20,700 flight cycles or 41,400 flight hours, whichever occurs first since first flight of the airplane.
(ii) Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first after doing the most recent inspection as specified in the service information specified in paragraph (o)(1), (o)(2), (o)(3), or (o)(4) of this AD.
(2) For airplanes on which the actions specified in Airbus Service Bulletin A320-57-1043 have been done: At the latest of the times specified in paragraphs (p)(2)(i), (p)(2)(ii), and (p)(2)(iii) of this AD.
(i) Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first since doing the actions specified in Airbus Service Bulletin A320-57-1043.
(ii) Within 3,750 flight cycles or 7,500 flight hours, whichever occurs first after July 31, 2012 (as described in Airbus Service Bulletin A320-57-1082, Revision 04, dated December 5, 2013).
(iii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first after the effective date of this AD.
If any crack is found during any inspection required by paragraph (p) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the EASA; or Airbus's EASA DOA.
Modification of an airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1043, Revision 06, dated December 5, 2013, constitutes terminating action for the actions required by paragraph (p) of this AD.
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
