AD 2010-23-26

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 main landing gear (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 (g)(1) or (g)(2) of this AD. After April 12, 2000 (the effective date of AD 2000-05-07, Amendment 39-11616), 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 the actions specified in paragraph (i), (j), or (l) of this AD are 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 prior to April 12, 2000, 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 (g) of this AD.

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

(i) Except as required by paragraph (l) of this AD, 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 July 18, 2006 (the effective date of AD 2006-12-13), 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 (g) and (j) of this AD.

Note 3: Accomplishment of the modification required by paragraph (i) 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.

For airplanes on which the modification specified in paragraph (i) or (l) of this AD has not been done before July 18, 2006 (the effective date of AD 2006-12-13, Amendment 39-14639), 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 (j)(1), (j)(2), (j)(3), or (j)(4) of this AD. Repeat the inspections thereafter at intervals not to exceed 700 flight cycles until the terminating modification required by paragraph (l) of this AD is accomplished. Accomplishment of the inspections per paragraph (j) of this AD terminates the inspection requirements of paragraph (g) of this AD.

(1) For Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R airplanes that have accumulated 18,000 or more total flight cycles as of July 18, 2006: Within 700 flight cycles after July 18, 2006.

(2) For Model A300 B2-1C, B2K-3C, and B2-203 airplanes that have accumulated less than 18,000 total flight cycles as of July 18, 2006: Prior to the accumulation of 18,000 total flight cycles, or within 700 flight cycles after July 18, 2006, 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 July 18, 2006: Prior to the accumulation of 14,500 total flight cycles, or within 700 flight cycles after July 18, 2006, whichever occurs later.

(4) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R airplanes that have accumulated less than 18,000 total flight cycles as of July 18, 2006: Prior to the accumulation of 11,600 total flight cycles, or within 700 flight cycles after July 18, 2006, whichever occurs later.

If any crack is detected during any inspection required by paragraph (j) of this AD, prior to further flight, accomplish the requirements of paragraphs (k)(1) and (k)(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 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or A300-57A6087, Revision 04, including Appendix 01, dated February 19, 2002; or A300-57A6087, Revision 05, dated March 10, 2008 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R 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 (i) of this AD has not been accomplished before July 18, 2006: At the earlier of the times specified in paragraphs (l)(1) and (l)(2) of this AD, modify Gear Rib 5 of the MLG attachment fittings at the lower flange. Except as provided by paragraph (m) 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 (g) and (j) 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 July 18, 2006.

(m) Where the applicable service bulletin specified in paragraph (l) 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).

Actions accomplished before July 18, 2006, in accordance with the service bulletins listed in Table 6 of this AD, are considered acceptable for compliance with the corresponding action specified in paragraphs (g) through (m) of this AD.

Although the service bulletins identified in Tables 1, 2, 3, 4, 5, and 6 of this AD specify to submit certain information to the manufacturer, this AD does not include such a requirement.

Unless already done, do the following actions.

(1) At the applicable time specified in paragraph (p)(2) of this AD, perform a detailed inspection for cracking at the locations specified in paragraphs (p)(1)(i), (p)(1)(ii), and (p)(1)(iii) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, dated March 11, 2009; or Revision 04, dated September 9, 2009; or Airbus Mandatory Service Bulletin A300-57A6101, Revision 03, dated March 11, 2009; or Revision 04, dated September 9, 2009; as applicable.

(i) The bottom flange and vertical web in the area between the wing rear spar/gear rib 5 attachment and the forward reaction-rod pick-up lug.

(ii) On the inboard side, around the fastener holes at locations 43, 47 to 50, 52, and 54.

(iii) On the outboard side, the lower flange, the vertical web and around the fastener holes at locations 43, 47 to 50, 52 and 54.

(2) Do the inspection required by paragraph (p)(1) of this AD at the later of the times in paragraphs (p)(2)(i) and (p)(2)(ii) of this AD.

(i) Within 400 flight cycles after the accomplishment of the actions required by paragraph (i) or (l) of this AD, as applicable.

(ii) Within 400 flight cycles or 4 months after the effective date of this AD, whichever occurs first.

(3) If no cracking is detected during the inspection required by paragraph (p)(1) of this AD, before further flight, perform a fluorescent penetrant inspection (FPI) at holes location 47 and 54, in the right-hand and left-hand MLG rib 5 attachment fitting lower flange, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, dated March 11, 2009; or Revision 04, dated September 9, 2009; or Airbus Mandatory Service Bulletin A300-57A6101, Revision 03, dated March 11, 2009; or Revision 04, dated September 9, 2009; as applicable.

(4) Thereafter, at intervals not to exceed 400 flight cycles, repeat the detailed and FPI inspections, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, dated March 11, 2009; or Revision 04, dated September 9, 2009; or Airbus Mandatory Service Bulletin A300- 57A6101, Revision 03, dated March 11, 2009; or Revision 04, dated September 9, 2009; as applicable.

(5) If any crack is detected during any of the inspections required by paragraphs (p)(1), (p)(3), and (p)(4) of this AD, and Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, dated March 11, 2009; or Revision 04, dated September 9, 2009; or Airbus Mandatory Service Bulletin A300-57A6101, Revision 03, dated March 11, 2009; or Revision 04, dated September 9, 2009; recommends contacting Airbus for appropriate action: Before further flight, contact Airbus for a repair solution, and do the repair; or repair the cracking using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or EASA or its delegated agent.

(q) Spot-facing the sensitive holes on the bottom flange MLG ribs, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-57-0254, dated June 4, 2010, or Airbus Mandatory Service Bulletin A300-57-6110, dated June 7, 2010; as applicable; terminates the repetitive inspection requirements of paragraph (p)(4) of this AD.

Note 4: This AD differs from the MCAI and/or service information as follows: No differences.