AD 2006-12-13

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Perform a detailed inspection and a high-frequency eddy current (HFEC) inspection to detect cracks in Gear Rib 5 of the MLG attachment fittings at the lower flange, in accordance with the Accomplishment Instructions of any applicable service bulletin listed in Table 1 and Table 2 of this AD, at the time specified in paragraph (f)(1) or (f)(2) of this AD. After April 12, 2000 (the effective date of AD 2000-05-07), only the service bulletins listed in Table 2 of this AD may be used. Repeat the inspections thereafter at intervals not to exceed 1,500 flight cycles, until paragraph (h), (i), or (k) of this AD is accomplished.

(1) For airplanes that have accumulated 20,000 or more total flight cycles as of March 9, 1998 (the effective date of AD 98-03-06, amendment 39-10298): Inspect within 500 flight cycles after March 9, 1998.

(2) For airplanes that have accumulated less than 20,000 total flight cycles as of March 9, 1998: Inspect prior to the accumulation of 18,000 total flight cycles, or within 1,500 flight cycles after March 9, 1998, whichever occurs later.

Note 1: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”

Note 2: Accomplishment of the initial detailed and HFEC inspections in accordance with Airbus Service Bulletin A300-57A0234 or A300-57A6087, both dated August 5, 1997, as applicable, is considered acceptable for compliance with the initial inspections required by paragraph (f) of this AD.

If any crack is detected during any inspection required by paragraph (f) of this AD, prior to further flight, accomplish the requirements of paragraph (g)(1) or (g)(2) of this AD, as applicable.

(1) If a crack is detected at one hole only, and the crack does not extend out of the spotface of the hole, repair in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this AD.

(2) If a crack is detected at more than one hole, or if any crack at any hole extends out of the spotface of the hole, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or the European Aviation Safety Agency (EASA) (or its delegated agent).

Prior to the accumulation of 21,000 total flight cycles, or within 2 years after October 20, 1999 (the effective date of AD 99-19-26, amendment 39-11313), whichever occurs later: Modify Gear Rib 5 of the MLG attachment fittings at the lower flange in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 3 of this AD. After the effective date of this AD, only Revision 04 of Airbus Service Bulletin A300-57-6088, and Revisions 04 and 05 of Airbus Service Bulletin A300-57-0235 may be used. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirements of paragraphs (f) and (i) of this AD.

Note 3: Accomplishment of the modification required by paragraph (h) of this AD prior to April 12, 2000, in accordance with Airbus Service Bulletin A300-57-6088 or A300-57-0235, both dated August 5, 1998; as applicable; is acceptable for compliance with the requirements of that paragraph.

(i) For airplanes on which the modification specified in paragraph (h) or (k) of this AD has not been done as of the effective date of this AD, perform a detailed and an HFEC inspection to detect cracks of the lower flange of Gear Rib 5 of the MLG at holes 43, 47, 48, 49, 50, 52, and 54, in accordance with the applicable service bulletin listed in Table 4 of this AD. Perform the inspections at the applicable time specified in paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of this AD. Repeat the inspections thereafter at intervals not to exceed 700 flight cycles until the terminating modification required by paragraph (k) of this AD is accomplished. Accomplishment of the inspections per paragraph (i) of this AD, terminates the inspection requirements of paragraph (f) of this AD.

(1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; and Model C4-605R Variant F airplanes that have accumulated 18,000 or more total flight cycles as of the effective date of this AD: Within 700 flight cycles after the effective date of this AD.

(2) For Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes that have accumulated less than 18,000 total flight cycles as of the effective date of this AD: Prior to the accumulation of 18,000 total flight cycles, or within 700 flight cycles after the effective date of this AD, whichever occurs later.

(3) For Model A300 B4-2C, B4-103, and B4-203 airplanes that have accumulated less than 18,000 total flight cycles as of the effective date of this AD: Prior to the accumulation of 14,500 total flight cycles, or within 700 flight cycles after the effective date of this AD, whichever occurs later.

(4) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes that have accumulated less than 18,000 total flight cycles as of the effective date of this AD: Prior to the accumulation of 11,600 total flight cycles, or within 700 flight cycles after the effective date of this AD, whichever occurs later.

If any crack is detected during any inspection required by paragraph (i) of this AD, prior to further flight, accomplish the requirements of paragraph (j)(1) and (j)(2) of this AD, as applicable.

(1) If a crack is detected at only one hole, and the crack does not extend out of the spotface of the hole, repair in accordance with Airbus Service Bulletin A300-57A0234, Revision 05, including Appendix 01, dated February 19, 2002 (for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or A300-57A6087, Revision 04, including Appendix 01, dated February 19, 2002 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R airplanes); as applicable.

(2) If a crack is detected at more than one hole, or if any crack at any hole extends out of the spotface of the hole, repair in accordance with a method approved by the Manager, International Branch, ANM-116, or the EASA (or its delegated agent).

For airplanes on which the terminating modification in paragraph (h) of this AD has not been accomplished before the effective date of this AD: At the earlier of the times specified in paragraphs (k)(1) and (k)(2) of this AD, modify Gear Rib 5 of the MLG attachment fittings at the lower flange. Except as provided by paragraph letter (l) of this AD, do the modification in accordance with the applicable service bulletin in Table 5 of this AD. This action terminates the repetitive inspections requirements of paragraphs (f) and (i) of this AD.

(1) Prior to the accumulation of 21,000 total flight cycles, or within 2 years after October 20, 1999, whichever is later.

(2) Within 16 months after the effective date of this AD.

(l) Where the applicable service bulletin in paragraph (k) of this AD specifies to contact Airbus for modification instructions; or if there is a previously installed repair at any of the affected fastener holes; or if a crack is found when accomplishing the modification: Prior to further flight, modify in accordance with a method approved by the Manager, International Branch, ANM-116, or the EASA (or its delegated agent).

Within 700 flight cycles after doing the modification in accordance with paragraph (h), (k), or (l) of this AD, or within 6 months after the effective date of this AD, whichever occurs later, except as provided by paragraph (o) of this AD: Do a detailed and an HFEC inspection for cracks at holes 47 and 54 in the lower flange of Gear Rib 5, and do all related investigative and corrective actions before further flight, by doing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A300-57A0246, including Appendix 01, dated May 20, 2005; or Airbus Service Bulletin A300-57A6101, including Appendix 01, dated May 20, 2005; as applicable. Where the applicable service bulletin specifies to contact Airbus for repair instructions: Prior to further flight, modify in accordance with a method approved by the Manager, International Branch, ANM-116, or the EASA (or its delegated agent). Repeat the inspection and related investigative and corrective actions thereafter at intervals not to exceed 700 flight cycles. If no crack is detected during the repeat inspection performed at or above 2,100 flight cycles after doing the modification in accordance with paragraph (h), (k), or (l) of this AD, then no further inspection is required. Except, at least one inspection is required after the accumulation of 2,100 flight cycles after installing the modification in accordance with paragraph (h) or (k) of this AD.

Actions accomplished before the effective date of this AD, per the service bulletins listed in Table 6 of this AD, are considered acceptable for compliance with the corresponding action specified in this AD.

(o)(1) Although Airbus Service Bulletins A300-57A0234, A300-57-0235, A300-57A6087, A300-57-6088, A300-57A0246, and A300-57A6101, specify to submit certain information to the manufacturer, this AD does not include such a requirement, except as provided by paragraph (o)(2) of this AD.

(2) Where Airbus Service Bulletins A300-57A0246 and A300-57A6101 specify to submit a report of positive and negative findings of the post-modification inspection required by paragraph (m) of this AD, within 30 days after the effective date of this AD, submit a report only of the positive findings of post-modification inspections to Airbus, Customer Service Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.