Airworthiness directives › 2012-01-05
AD 2012-01-05 Airworthiness Directives; Airbus Airplanes
Models named: A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, B4-203, A300 B4-601, B4-603, B4-620, B4-622. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD; except airplanes on which Airbus Modification 11912 or 11932 has been installed. (1) Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes. (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R airplanes.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Required actions
This paragraph restates the requirements of paragraph (g) of AD 2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010). 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 (g)(1) or (g)(2) of this AD. After April 12, 2000 (the effective date of AD 2000-05-07, Amendment 39-11616 (65 FR 12077, March 8, 2000)), the service bulletins listed in table 2 of this AD must be used to accomplish the actions required by this paragraph. 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. Table 1—Revision 01 of Service Bulletins for Paragraph ( g ) of This AD Model— Airbus Service Bulletin— Revision— Dated— A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R and F4-605R airplanes A300-57-6087 01 March 11, 1998. A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes A300-57-0234 01 March 11, 1998. Table 2—Other Revisions of Service Bulletins for Paragraph ( g ) of This AD Model— Airbus Service Bulletin— Revision— Dated— A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R airplanes A300-57A6087 02, including Appendix 01 June 24, 1999. 03, including Appendix 01 May 19, 2000. 04, including Appendix 01 February 19, 2002. 05, including Appendix 01 March 10, 2008. A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes A300-57A0234 02 June 24, 1999. 03, including Appendix 01 September 2, 1999. 04, including Appendix 01 May 19, 2000. 05, including Appendix 01 February 19, 2002. (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 (63 FR 5224, February 2, 1998)): 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 (the effective date of AD 98-03-06, Amendment 39-10298 (63 FR 5224, February 2, 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. (3) 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.”
Unsafe condition
This AD was prompted by new cases of cracks discovered during scheduled maintenance checks. We are issuing this AD to prevent cracking of the Gear Rib 5 right-hand and left-hand attachment fitting at the lower flanges of the main landing gear (MLG), which could result in failed bolts penetrating through the rear spar and into a fuel tank, consequent fuel loss, and reduced structural integrity of the airplane.
Affected ADs
This AD supersedes AD 2010-23-26, Amendment 39-16516 (75 FR 74610, December 1, 2010).
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1