Airworthiness Directive · Amendment 39-19418 · Wings
Airbus SAS Airplanes
Superseded. A later AD replaced this one: AD 2019-12-04. Comply with the one in force.
This AD applies to Airbus SAS Model A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 C4-605R Variant F, and A300 F4-605R airplanes, certificated in any category, all manufacturer serial numbers, except airplanes on which Airbus Modification 12171 or 12249 has been embodied in production, or on which Airbus Service Bulletin A300-57-6069 has been embodied in service.
We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 B4-600R series airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R airplanes. This AD was prompted by reports of cracking on a certain frame (FR) angle fitting. This AD requires, depending on airplane configuration, a modification of certain angle fitting attachment holes; repetitive inspections for cracking of certain holes of the internal lower angle fitting web, certain holes of the internal lower angle fitting horizontal splicing, the aft bottom panel, and a certain junction area; and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
For the purposes of this AD, the definitions in paragraphs (g)(1) through (g)(6) apply.
(1) Group 1 airplanes are those airplanes on which Airbus Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, has not been incorporated as of the effective date of this AD.
(2) Group 2 airplanes are those airplanes on which Airbus Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, has been incorporated as of the effective date of this AD.
(3) The average flight time (AFT) for the inspection threshold is defined as the flight hours (FH) divided by the flight cycles (FC), counted from the first flight of the airplane.
(4) The AFT for the inspection interval is defined as the FH divided by the FC, counted from the date of the last inspection required by paragraph (i), (j), (k), or (l) of this AD, as applicable.
(5) For airplanes on which Airbus modification 10155 has been embodied, the thresholds for the inspections required by paragraphs (i), (j), and (k) of this AD are counted from the first flight of the airplane.
(6) For airplanes on which Airbus modification 10155 has not been embodied, the thresholds for the inspections required by paragraphs (i), (j), and (k) of this AD are counted since the date on which Airbus Service Bulletin A300-57-6050 was embodied on the airplane.
For all airplanes on which Airbus modification 10155 has not been embodied: Before exceeding 15,100 FC or 38,900 FH, whichever occurs first after first flight of the airplane; or within the “grace periods” defined in paragraph 1.B.(4), “Accomplishment Timescale,” of Airbus Service Bulletin A300-57-6050, Revision 3, dated May 31, 2001; whichever occurs later, modify the angle fitting attachment holes of the wing center box by cold expansion, including doing a rotating probe inspection for cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6050, Revision 3, dated May 31, 2001. Where paragraph 1.B.(4), “Accomplishment Timescale,” of Airbus Service Bulletin A300-57-6050, Revision 3, dated May 31, 2001, specifies “grace periods” relative to the receipt of the service bulletin, count the “grace periods” from December 19, 2005 (the effective date of AD 2005-23-08 (70 FR 69056, November 14, 2005)). If any crack is found during any inspection: Before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
For Group 1 airplanes: Before exceeding the applicable threshold specified in figure 1 to paragraph (i) of this AD, or within 12 months after the effective date of this AD, whichever occurs later, do a high frequency eddy current (HFEC) rotating probe inspection for cracking of holes H, I, K, L M, N, U, V, W, X, and Y of the internal lower angle fitting web (left-hand and right-hand sides), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, Revision 8, dated July 4, 2017. Repeat the inspection thereafter at intervals not to exceed those specified in figure 1 to paragraph (i) of this AD.
For Group 1 airplanes: Before exceeding the applicable threshold specified in figure 2 to paragraph (j) of this AD, or within 12 months after the effective date of this AD, whichever occurs later, do an HFEC rotating probe inspection for cracking of holes A, B, C, D, E, F, G, P, Q, S, and T (adjacent to hole G) of the internal lower angle fitting horizontal splicing (left-hand and right-hand sides), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 7, dated March 26, 2018. Repeat the inspection thereafter at intervals not to exceed those specified in figure 2 to paragraph (j) of this AD.
For Group 1 airplanes: Before exceeding the applicable thresholds specified in figure 3 to paragraph (k) of this AD, or within 12 months after the effective date of this AD, whichever occurs later, do an ultrasonic inspection for cracking of the aft bottom panel, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, Revision 7, dated March 26, 2018. Repeat the inspection thereafter at intervals not to exceed those specified in figure 3 to paragraph (k) of this AD.
For Group 2 airplanes: Before exceeding the applicable thresholds specified in figure 4 to paragraph (l) of this AD, do ultrasonic and radiographic inspections for cracking of the FR47/Rib 1 junction area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6119, Revision 00, dated April 25, 2016. Repeat the inspections thereafter at intervals not to exceed those specified in figure 4 to paragraph (l) of this AD. Count the threshold compliance times from the date on which Airbus Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, was embodied on the airplane.
If, during any inspection required by paragraph (i), (j), (k), or (l) of this AD, any crack is found: Before further flight, accomplish all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of the service information specified in paragraphs (m)(1) through (m)(3) of this AD, as applicable. Where the service information specified in paragraphs (m)(1) through (m)(3) of this AD specifies to contact Airbus for instructions, before further flight, obtain instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA and accomplish those instructions accordingly. If approved by the DOA, the approval must include the DOA-authorized signature.
(1) If the inspection was done as specified in paragraph (i) of this AD: Airbus Service Bulletin A300-57-6049, Revision 8, dated July 4, 2017.
(2) If the inspection was done as specified in paragraph (j) or (k) of this AD: Airbus Service Bulletin A300-57-6086, Revision 7, dated March 26, 2018.
(3) If the inspection was done as specified in paragraph (l) of this AD: Airbus Service Bulletin A300-57-6119, Revision 00, dated April 25, 2016.
At the applicable time specified in paragraph (n)(1) or (n)(2) of this AD: Report the results of the inspections required by paragraphs (i), (j), (k), and (l) of this AD to Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/), or submit the results to Airbus in accordance with the instructions of the applicable service information specified in paragraphs (i), (j), (k), or (l) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of flight cycles and flight hours on the airplane.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
Accomplishment of the action required by paragraph (h) of this AD and the initial inspections required by paragraphs (i) and (j), and (k) of this AD terminates all requirements of AD 2014-20-18.
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.
