Airworthiness Directive · Amendment 39-18086 · Wings
Airbus Airplanes
This AD applies to the Airbus airplanes specified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, all manufacturer serial numbers.
(1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes.
(2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 F4-605R airplanes.
(5) Model A300 C4-605R Variant F airplanes.
We are superseding Airworthiness Directive (AD) 95-24-04 for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F airplanes. AD 95-24-04 required inspections to detect cracks at the aft spar web of the wings, and repair if necessary. This new AD reduces certain compliance times, and expands the applicability. This AD was prompted by a determination that the inspection threshold and interval must be reduced to allow timely detection of cracks and accomplishment of applicable repairs, because of cracking in the rear spar web of the wings between certain ribs due to fatigue-related high shear stress. We are issuing this AD to detect and correct fatigue-related cracking, which could result in reduced structural integrity of the wing.
This paragraph restates the requirements of paragraph (a) of AD 95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with no changes. For Model A300 B2 series airplanes: Prior to the accumulation of 18,000 total flight cycles, or within 1,400 flight cycles after December 27, 1995 (the effective date of AD 95-24-04), whichever occurs later, perform a high frequency eddy current (HFEC) inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles.
This paragraph restates the requirements of paragraph (b) of AD 95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with no changes. For Model A300 B4-103 and B4-2C airplanes: Prior to the accumulation of 19,000 total flight cycles, or within 1,400 flight cycles after December 27, 1995 (the effective date of AD 95-24-04), whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 6,000 flight cycles.
This paragraph restates the requirements of paragraph (c) of AD 95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with no changes. For Model A300 B4-200 airplanes: Prior to the accumulation of 17,000 total flight cycles, or within 1,400 flight cycles after December 27, 1995 (the effective date of AD 95-24-04), whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles.
This paragraph restates the requirements of paragraph (d) of AD 95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with no changes. For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R airplanes: Prior to the accumulation of 21,600 flight cycles, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-6059, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles. Accomplishment of the initial inspection required by paragraph (l) of this AD terminates the requirements of this paragraph.
This paragraph restates the requirements of paragraph (e) of AD 95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with new actions and with specific delegation approval language in paragraph (k)(2) of this AD.
(1) Before the effective date of this AD, if any crack is detected during any inspection required by paragraphs (g) through (j) of this AD: Prior to further flight, repair the crack, in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994; or Airbus Service Bulletin A300-57-6059, dated August 12, 1994; as applicable; or in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA.
(2) As of the effective date of this AD, if any crack is detected during any inspection required by paragraphs (g) through (j) of this AD: Before further flight, repair the crack, in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994; or Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011; as applicable; except if Airbus Service Bulletin A300-57-0213, dated August 12, 1994; or Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011; specifies to contact Airbus for an approved repair, before further flight, repair the crack using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the European Aviation Safety Agency (EASA); or Airbus's EASA design organization approval (DOA).
For airplanes identified in paragraphs (c)(2) through (c)(5) of this AD: At the later of the times specified in paragraphs (l)(1) and (l)(2) of this AD, perform an HFEC inspection to detect cracks of the aft face of the wing rear spar web in the area adjacent to the build slot, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011. Repeat the inspection thereafter at the applicable time specified in Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011, except as specified in paragraph (m) of this AD. Accomplishment of the initial inspection required by this paragraph terminates the requirements of paragraph (j) of this AD.
(1) At the earlier of the applicable times specified in the “Threshold Inspection” column in table 1 through table 4 of paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011. Where Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011, specifies “(FH)” and “(FC)” in the “Threshold Inspection” columns, this AD specifies “total flight hours” and “total flight cycles.” The inspection threshold for airplanes on which Airbus Modification 11130 (Airbus Service Bulletin A300-57-6063) has been done is determined from the point of embodiment of Airbus Modification 11130, and is not based on total flight cycles.
(2) At the earlier of the applicable times specified in the “Grace Period” column in table 1 through table 4 of paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011. Where Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011, specifies “(FH)” and “(FC)” in the “Grace Period” columns, this AD specifies “flight hours” and “flight cycles.” Where Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011, specifies a grace period, this AD requires compliance within the specified time after the effective date of this AD.
The repetitive inspection required by paragraph (l) of this AD must be accomplished at the earlier of the applicable times specified in the “Repeat Interval” column of table 1 through table 4 of Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011. Where Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011, specifies “(FC)” and “(FH)” in the “Repeat Interval” columns, this AD specifies “flight hours” and “flight cycles.”
If any crack is detected during any inspection required by paragraph (l) of this AD: Before further flight, repair the crack, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011. Where Airbus Service Bulletin A300-57-6059, Revision 04, dated February 22, 2011, specifies to contact Airbus for an approved repair: Before further flight, repair the crack using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the EASA; or Airbus's EASA DOA. Repair of any cracking, as required by this paragraph, does not terminate the repetitive inspections required by paragraph (l) of 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.
