Airworthiness Directive · Amendment 39-18378 · Wings
Airbus Airplanes
This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) through (c)(4) of this AD, all manufacturer serial numbers.
(1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(2) Airbus Model A300 B4-605R and B4-622R airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
(4) Airbus Model A300 C4-605R Variant F airplanes.
We are superseding Airworthiness Directive (AD) 98-20-27 for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 98-20-27 required repetitive inspections to detect fatigue cracking of the wing top skin at the front spar joint; and a follow-on eddy current inspection and repair, if necessary. This new AD reduces the inspection compliance time and intervals, and expands the inspection area of the wing top skin at the front spar joint. This AD was prompted by reports of cracking of the wing top skin in an area not required for inspection by AD 98-20-27. We are issuing this AD to detect and correct fatigue cracking of the wing top skin at the front spar joint; such fatigue cracking could result in reduced structural integrity of the airplane.
This paragraph restates the requirements of paragraph (a) of AD 98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), with revised service information. Prior to the accumulation of 22,000 total flight cycles, or within 2,000 flight cycles after October 29, 1998 (the effective date of AD 98-20-27), whichever occurs later: Perform a detailed visual inspection to detect fatigue cracking of the wing top skin at the front spar joint, in accordance with Airbus Service Bulletin A300-57-6045, Revision 1, dated August 3, 1994, including Appendix 1, Revision 1, dated August 3, 1994; Airbus Service Bulletin A300-57-6045, Revision 02, dated April 21, 1998, including Appendix 1, Revision 02, dated April 21, 1998; or Airbus Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013. Repeat the detailed visual inspection thereafter at intervals not to exceed 8,000 flight cycles.
This paragraph restates the requirements of paragraph (b) of AD 98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), with revised service information. If any cracking is suspected or detected during any inspection required by paragraph (g) of this AD: Prior to further flight, perform an eddy current inspection to confirm the findings of the visual inspection, in accordance with Airbus Service Bulletin A300-57-6045, Revision 1, dated August 3, 1994, including Appendix 1, Revision 1, dated August 3, 1994; Airbus Service Bulletin A300-57-6045, Revision 02, dated April 21, 1998, including Appendix 1, Revision 02, dated April 21, 1998; or Airbus Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013. If any cracking is detected during any eddy current inspection, 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 (or its delegated agent).
At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD: Do a detailed inspection of the wing top skin between ribs 1 and 7 for cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013. Accomplishment of the initial inspection required by this paragraph terminates the requirements of paragraph (g) of this AD.
(1) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; and Model A300 C4-605R Variant F airplanes: At the later of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
(i) Before the accumulation of 17,100 total flight cycles or 38,400 total flight hours, whichever occurs first.
(ii) Within 1,000 flight cycles or 2,200 flight hours, whichever occurs first after the effective date of this AD.
(2) For Model A300 F4-605R and F4-622R airplanes: At the later of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
(i) Before the accumulation of 22,000 total flight cycles or 49,500 total flight hours, whichever occurs first.
(ii) Within 1,300 flight cycles or 2,800 flight hours, whichever occurs first after the effective date of this AD.
Repeat the inspection required by paragraph (i) of this AD thereafter at the applicable time and intervals specified in paragraphs (j)(1) and (j)(2) of this AD.
(1) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; and Model A300 C4-605R Variant F airplanes: Repeat the inspection at the applicable time specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD.
(i) For airplanes that have an average flight time (AFT) that is equal to or more than one and one-half hours: Repeat the inspection at intervals not to exceed 5,100 flight cycles or 11,000 flight hours, whichever occurs first.
(ii) For airplanes that have an AFT that is less than one and one-half hours: Repeat the inspection at intervals not to exceed 5,500 flight cycles or 8,300 flight hours, whichever occurs first.
(2) For Model A300 F4-605R and F4-622R airplanes: Repeat the inspection at the applicable time specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD.
(i) For airplanes that have an AFT that is equal to or more than one and one-half hours: Repeat the inspection at intervals not to exceed 6,500 flight cycles or 14,100 flight hours, whichever occurs first.
(ii) For airplanes that have an AFT that is less than one and one-half hours: Repeat the inspection at intervals not to exceed 7,000 flight cycles or 10,600 flight hours, whichever occurs first.
(1) If any crack in the top skin in the area forward of the front spar attachment is found during any inspection required by paragraph (i) or (j) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(2) If any crack or sign of a crack is found in the top skin at or aft of the spar attachment during any inspection required by paragraph (i) or (j) of this AD: Before further flight, do an eddy current inspection of the cracks or of the signs of cracking to confirm the findings of the detailed inspection, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013. If there is any crack at or aft of the spar attachment, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; EASA; or Airbus's EASA DOA.
Accomplishment of any repair required by paragraph (k) this AD does not constitute terminating action for the repetitive inspections required by paragraph (j) of this AD.
Although Airbus Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
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.
