Airworthiness Directive · Amendment 39-18242 · Wings
Airbus Airplanes
This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, and B4-622R airplanes, Model A300 F4-605R and F4-622R airplanes, and Model A300 C4-605R Variant F airplanes, certificated in any category, except those on which Airbus Modification 8608 is incorporated in production.
We are superseding Airworthiness Directive (AD) 98-18-02 for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R variant F airplanes (collectively called A300-600 series airplanes). AD 98-18-02 required inspections to detect cracks in the center spar sealing angles adjacent to the pylon rear attachment and in the adjacent butt strap and skin panel, and correction of discrepancies. This new AD continues to require inspections for cracks. This new AD also requires a modification by cold expansion of the center spar sealing angles, replacement of both sealing angles and cold expansion of the attachment holes if necessary, and post-repair repetitive inspections and corrective actions if necessary. This AD was prompted by reports of cracking in the vertical web of the center spar sealing angles of the wing, and subsequent analyses that showed that the inspection threshold and interval specified in AD 98-18-02 must be reduced to allow timely detection of cracks on the sealing angles of the center spar, adjacent to rib 8. We are issuing this AD to prevent crack formation in the sealing angles, which could rupture the sealing angle and lead to subsequent crack formation in the bottom skin of the wing, and result in reduced structural integrity of the center spar section of the wing.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For all airplanes, at the applicable time specified in paragraph (h) of this AD, accomplish the actions specified in paragraphs (g)(1) and (g)(2) of this AD concurrently. Repeat the inspection required by paragraph (g)(1) of this AD thereafter at intervals not to exceed the values as specified in the “Repeat Interval” column in Table 1 or Table 2 of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011, as applicable to the airplane configuration and utilization; except as required by paragraph (k) of this AD.
(1) Do a high frequency eddy current (HFEC) inspection of the center spar sealing angles adjacent to the pylon rear attachment fitting for cracks, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011.
(2) Unless already done: Modify the airplane by cold expansion of the center spar sealing angles outboard of rib 8, adjacent to the pylon rear attachment fitting, including doing the eddy current inspections for cracks of the bolt holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6033, Revision 02, dated September 19, 2011.
At the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD, except as required by paragraph (k) of this AD, do the actions required by paragraph (g) of this AD.
(1) At the applicable compliance time specified in Table 1 and Table 2 in the “Threshold Inspection,” column in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011.
(2) At the applicable compliance time specified in Table 1 and Table 2 in the “Grace Period,” column in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011.
If, during any inspection required by paragraph (g), (g)(1), or (g)(2) of this AD, any crack is found: Before further flight, repair the crack by replacing both of the forward and aft sealing angles with new sealing angles and cold expansion of the attachment holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011. The corrective actions, as required by this paragraph, do not constitute as a terminating action for the repetitive inspections specified in paragraph (g)(1) of this AD.
For airplanes on which the modification specified in Airbus Repair Drawing R571504040 has been done: Within 3 months after the effective date of this AD, or before further flight after doing the modification, whichever occurs later, contact 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) for repetitive post-repair inspections and corrective actions, and do those actions.
(1) Where Note 01 and Note 02 of paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011, specify to contact Airbus for inspection requirements, this AD requires, at the applicable compliance time specified in Table 1 and Table 2 in the “Grace Period,” column in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011, inspecting using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(2) Where Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011, specifies a compliance time in Table 1 and Table 2 in the “Grace Period,” column in paragraph 1.E., “Compliance,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(3) Where Table 1 and Table 2 in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011, specify a choice between flight cycles or flight hours, this AD requires a compliance time within the specified flight cycles or flight hours, whichever occurs first.
(4) Where Table 1 and Table 2 in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011, specify compliance times in the “Threshold Inspection” column for pre-modification 8609, those compliance times are flight cycles or flight hours since first flight of the airplane.
(5) Where Table 1 and Table 2 in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011, specify compliance times in the “Threshold Inspection” column for any post modification or repair, this AD requires compliance within the applicable compliance time specified in the “Threshold Inspection” column of Table 1 and Table 2 in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-57-6027, Revision 07, dated June 6, 2011. Those compliance times are flight cycles or flight hours since accomplishing the modification or repair.
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.
