Airworthiness Directive · Amendment 39-18638 · Wings
Airbus Airplanes
This AD applies to Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; and Model A300 B4-605R airplanes; certificated in any category; except airplanes on which Airbus Modification 6661 has been embodied during production.
We are superseding Airworthiness Directive (AD) 90-11-05 for certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4- 203 airplanes and Model A300 B4-600 series airplanes. AD 90-11-05 required repetitive detailed inspections for cracking in the aft hinge brackets of the outer shroud box that is located in the outer wing box, and related investigative and corrective actions if necessary. This new AD changes certain compliance times and adds airplanes to the applicability. This AD was prompted by reports of cracks in the aft hinge brackets of the outer shroud box that is located in the outer wing box, which were found during routine maintenance checks, and our subsequent determination that a change in inspection compliance times is needed. We are issuing this AD to detect and correct cracking of the aft hinge brackets of the outer shroud box; such cracking could affect the structural integrity of the airplane.
At the applicable compliance time specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Do a detailed inspection for cracks and fractures of the hinge brackets of the forward and aft outer shroud boxes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0142, Revision 04, dated March 30, 2011; or Airbus Service Bulletin A300-57-6010, Revision 05, dated February 21, 2011; as applicable. Repeat the inspection thereafter at the applicable interval specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0142, Revision 04, dated March 30, 2011; or Airbus Service Bulletin A300-57-6010, Revision 05, dated February 21, 2011; as applicable. Doing the replacement specified in paragraph (j) of this AD terminates the repetitive inspections required by this paragraph.
(1) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-2C, and B4-203 airplanes: Do the inspection at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 2,000 flight hours, whichever occurs first.
(i) Before the accumulation of 5,000 flight cycles or 10,400 flight hours since first flight, whichever occurs first.
(ii) Within 100 flight cycles after the effective date of this AD.
(2) For Model A300 B2-1C, B2-203, and B2K-3C airplanes: Do the inspection at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 1,000 flight hours, whichever occurs first.
(i) Before the accumulation of 5,000 flight cycles or 5,400 flight hours since first flight, whichever occurs first.
(ii) Within 100 flight cycles after the effective date of this AD.
(3) For Model A300 B4-103 airplanes: Do the inspection at the later of the times specified in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 1,300 flight hours, whichever occurs first.
(i) Before the accumulation of 5,000 flight cycles or 6,600 flight hours since first flight, whichever occurs first.
(ii) Within 100 flight cycles after the effective date of this AD.
If any crack or fracture is found during any inspection required by paragraph (g) of this AD: Before further flight, replace the damaged hinge bracket with a new bracket, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-143, Revision 2, dated July 10, 1989; or Airbus A300-57-6011, Revision 2, dated July 10, 1989; as applicable.
If any crack or fracture is found during any inspection required by paragraph (g) of this AD: Before further flight, do a general visual inspection for secondary damage (e.g., cracks, wear damage, pitting, and gouging) in the areas specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0142, Revision 04, dated March 30, 2011; or Airbus Service Bulletin A300-57-6010, Revision 05, dated February 21, 2011; as applicable. If any damage is found, 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).
(1) The inner shroud-box forward attachments and the attachment brackets at the inboard end.
(2) The inner and outer shroud-box structure, adjacent to the fractured bracket.
(3) The top skin of the inboard flap.
(1) Replacement of the hinge bracket, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-143, Revision 2, dated July 10, 1989 (for Model A300 series airplanes); or Airbus Service Bulletin A300-57-6011, Revision 2, dated July 10, 1989; as applicable; terminates the inspection requirements of paragraph (g) of this AD (for Model A300 B4-600 series airplanes).
(2) Replacement of a hinge bracket before the effective date of this AD terminates the repetitive inspections required by paragraph (g) of this AD, provided that after the hinge bracket replacement, but before further flight after the effective date of this AD, a one-time detailed inspection of the forward and aft outer shroud box has been done with no cracking found, in accordance with paragraph (g) of this AD. The replacement must be done in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
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.
