Airworthiness Directive · Amendment 39-11725 · Airbus Model A300 B2, A300-B2K, A300 B4-2C, A300 B4-100, and A300 B4-200 Series Airplanes
Airbus Model A300 B2, A300-B2K, A300 B4-2C, A300 B4-100, and A300 B4-200 Series Airplanes
All Model A300 B2, A300 B2K, A300 B2-200, A300 B4-2C, A300 B4-100, and A300 B4-200 series airplanes, certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (h) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B2, A300 B2K, A300 B2-200, A300 B4, A300 B4-100, and A300 B4-200 series airplanes, that currently requires certain structural inspections and modifications. This amendment requires that those inspections be accomplished on additional airplanes. This action also requires new repetitive inspections for airplanes in certain configurations at revised thresholds and intervals. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct corrosion and cracking of the wings and fuselage, which could result in reduced structural integrity of the airplane.
To detect and correct corrosion and cracking of the wings and fuselage, which could result in reduced structural integrity of the airplane, accomplish the following:
(a) Accomplish the inspections and modifications contained in the Airbus service bulletins listed below prior to or at the thresholds identified in each of those service bulletins, or within 1,000 landings or 12 months after April 13, 1992 (the effective date of AD 92-02-09, amendment 39-8145), whichever occurs later, except as provided in paragraph (d) of this AD for the service bulletin identified in paragraph (a)(8) of this AD. Required inspections shall be repeated thereafter at intervals not to exceed those specified in the corresponding service bulletin for the inspection. After April 13, 1992, the actions shall only be accomplished in accordance with the latest revision of the service bulletins specified.
(1) Airbus Service Bulletin A300-53-103, Revision 4, dated June 30, 1983; or Revision 5, dated February 23, 1994;
(2) Airbus Service Bulletin A300-53-126, Revision 7, dated November 11, 1990; or Revision 8, dated September 18, 1991;
(3) Airbus Service Bulletin A300-53-146, Revision 7, dated April 26, 1991;
Note 2: Airbus Service Bulletin A300-53-146 provides for a compliance threshold of within 5 years after the date of issuance of French airworthiness directive 90-222-116(B), issued on December 12, 1990, the accomplishment of which is required by AD 85-07-09, amendment 39-5033.
(4) For Configuration 1 airplanes identified in Airbus Service Bulletin A300-53-0162, Revision 6, dated March 20, 1996: Airbus Service Bulletin A300-53-162, Revision 4, dated November 12, 1990; Revision 5, dated March 17, 1994; or Revision 6, dated March 20, 1996. After the effective date of this new AD, only Revision 6 of the service bulletin shall be used;
(5) Airbus Service Bulletin A300-53-196, Revision 1, dated November 12, 1990; as amended by Service Bulletin Change Notice 1.A., dated February 4, 1991, or Revision 2, dated March 17, 1994;
Note 3: Airbus Service Bulletin A300-53-196 provides for a compliance threshold of within 6,000 landings after accomplishment of Airbus Service Bulletin A300-53-194, accomplishment of which is required by AD 87-04-12, amendment 39-5536.
(6) Airbus Service Bulletin A300-53-225, Revision 2, dated May 30, 1990;
(7) Airbus Service Bulletin A300-53-226, Revision 4, dated November 12, 1990; or Revision 5, dated September 7, 1991;
Note 4: Airbus Service Bulletin A300-53-226 provides for a compliance threshold of within 5 years after the issuance of French airworthiness directive 90-222-116(B), issued on December 12, 1990; but not later than 20 years after first delivery; the accomplishment of which is required by AD 90-03-08, amendment 39-6481.
(8) For Configuration 1 and 2 airplanes identified in Airbus Service Bulletin A300-53-0278, Revision 2, dated November 10, 1995: Airbus Service Bulletin A300-53-278, dated November 12, 1990; or Revision 1, dated March 17, 1994;
(9) Airbus Service Bulletin A300-54-045, Revision 4, dated January 31, 1990; or Revision 6, dated February 25, 1994;
(10) Airbus Service Bulletin A300-54-060, Revision 2, dated September 7, 1988, and Change Notice 2.A., dated February 13, 1990; or Revision 3, dated February 25, 1994;
(11) Airbus Service Bulletin A300-54-063, Revision 1, dated April 22, 1987, and Change Notice 1.A., dated February 13, 1990; or Revision 2, dated February 25, 1994;
(12) Airbus Service Bulletin A300-54-066, Revision 1, dated February 15, 1989, and Change Notice 1.A., dated February 13, 1990; or Revision 2, dated February 25, 1994.
(b) Accomplish the inspections and modifications contained in the Airbus service bulletins listed below prior to or at the thresholds identified in each of those service bulletins, or within 1,000 landings or 12 months after March 29, 1996 (the effective date of AD 96-08-08, amendment 39-9574), whichever occurs later. Required inspections shall be repeated thereafter at intervals not to exceed those specified in the corresponding service bulletin for the inspection.
(1) Airbus Service Bulletin A300-57-0194, Revision 2, including Appendix 1, dated August 19, 1993;
(2) Airbus Service Bulletin A300-57-166, Revision 3, including Appendix 1, dated July 12, 1993;
(3) Airbus Service Bulletin A300-57-0167, Revision 1, including Appendix 1, dated May 25, 1993;
(4) Airbus Service Bulletin A300-57-0168, Revision 3, including Appendix 1, dated November 22, 1993;
(5) Airbus Service Bulletin A300-57-0180, Revision 1, dated March 29, 1993;
(6) Airbus Service Bulletin A300-57-0185, Revision 1, including Appendix 1, dated March 8, 1993; and
(7) Airbus Service Bulletin A300-54-0084, dated April 21, 1994.
(c) For Configuration 2 airplanes identified in Airbus Service Bulletin A300-53-0162, Revision 6, dated March 20, 1996: Accomplish the inspections contained in Airbus Service Bulletin A300-53-0162, Revision 6, dated March 20, 1996, prior to or at the thresholds identified in the service bulletin; or within 1,000 landings or 12 months after the effective date of this AD, whichever occurs later. Required inspections shall be repeated thereafter at intervals not to exceed those specified in the service bulletin for the inspection.
(d) For Configuration 1 and 2 airplanes identified in Airbus Service Bulletin A300-53-0278, Revision 2, dated November 10, 1995: Accomplish the inspections contained in Airbus Service Bulletin A300-53-0278, Revision 2, dated November 10, 1995; at the time specified in paragraph (d)(1) or (d)(2) of this AD, as applicable. Repeat the inspections thereafter at intervals not to exceed 3,600 flight cycles. Accomplishment of the inspections required by this paragraph constitutes terminating action for the inspections required by paragraph (a)(8) of this AD.
(1) For airplanes that have not been inspected in accordance with paragraph (a) and (a)(8) of this AD prior to the effective date of this AD: Inspect at the time specified in paragraph (d)(1)(i) or (d)(1)(ii) of this AD, as applicable.
(i) For Configuration 1 airplanes: Prior to the accumulation of 18,300 total landings, or within 1,000 landings or 12 months after the effective date of this AD, whichever occurs later.
(ii) For Configuration 2 airplanes: At the earlier of the times specified in paragraphs (d)(1)(ii)(A) or (d)(1)(ii)(B) of this AD.
(A) At the time specified in paragraphs (a) and (a)(8) of this AD.
(B) Prior to the accumulation of 22,000 total landings, or within 1,000 landings or 12 months after the effective date of this AD, whichever occurs later.
(2) For airplanes that have been inspected in accordance with paragraph (a) and (a)(8) of this AD prior to the effective date of this AD: Perform the next inspection within 3,600 landings after accomplishing the last inspection, or within 1,000 landings or 12 months after the effective date of this AD, whichever occurs later.
(e) For Configuration 3 airplanes identified in Airbus Service Bulletin A300-53-0278, Revision 2, dated November 10, 1995: Accomplish the inspections contained in Airbus Service Bulletin A300-53-0278, Revision 2, dated November 10, 1995, prior to the accumulation of 26,000 total flight cycles; or within 1,000 landings or 12 months after the effective date of this AD, whichever occurs later. Repeat the inspections thereafter at intervals not to exceed 5,000 flight cycles.
Note 5: Accomplishment of the inspections specified in Airbus Service Bulletin A300-53-0278, Revision 2, dated November 10, 1995, is considered acceptable for compliance with the significant structural details (SSD) inspection 536206 of “Airbus Industrie A300 Supplemental Structural Inspection Document” (SSID), Revision 2, dated June 1994, required by AD 96-13-11, amendment 39-9679 (61 FR 35122, July 5, 1996).
(f) If any discrepant condition identified in any service bulletin referenced in this AD is found during any inspection required by this AD, prior to further flight, accomplish the corresponding corrective action specified in the service bulletin, except as specified in paragraph (g) of this AD.
(g) If any crack is found during any inspection required by this AD; and the applicable service bulletin specifies to contact Airbus for appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Generale de l'Aviation Civile (DGAC) (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference 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.
