Airworthiness directives › 2015-12-05
AD 2015-12-05 Airworthiness Directives; Airbus Airplanes
Models named: A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, B4-203, A300 B4-601, B4-603, B4-620. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, all certified models, all serial numbers. (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes. (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (3) Airbus Model A300 B4-605R and B4-622R airplanes. (4) Airbus Model A300 F4-605R and F4-622R airplanes. (5) Airbus Model A300 C4-605R Variant F airplanes.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (f) of AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008), with revised service information. Unless already done, do the following actions. (1) Except as provided by paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), (g)(1)(iv), and (h) of this AD: At the threshold specified in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007 (for Model A300 series airplanes); Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007 (for Model A300-600 series airplanes); or Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model A300-600 series airplanes); as applicable; perform the inspection of the wing lower skin panel and associated internal support structure aft of the rear spar and inboard of rib 9 and apply applicable corrective measures in accordance with Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007 (for Model A300 series airplanes); Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007 (for Model A300-600 series airplanes); or Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model A300-600 series airplanes); as applicable. All applicable corrective measures must be done at the applicable times specified in paragraph 1.E.(2) and the Accomplishment Instructions of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007 (for Model A300 series airplanes); Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007 (for Model A300-600 series airplanes); or Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model A300-600 series airplanes); as applicable. Accomplishing the requirements of paragraph (h) of this AD terminates the requirements of this paragraph for Model A300-600 airplanes. (i) Where the tables in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007; and Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007; specify a grace period for doing the actions, this AD requires that the actions be done within the specified grace period relative to April 23, 2008 (the effective date of AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008)). (ii) Where the tables in paragraph 1.E.(2)(e), “Config 04,” of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007, specify an inspection interval but not an initial threshold, this AD requires that the actions be done within the specified interval after inspecting in accordance with Table 1A or 1B, as applicable, for Configuration 01 airplanes described in the Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007, and thereafter at the inspection interval specified in the tables in paragraph 1.E.(2)(e), “Config 04,” of Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007. (iii) Where the tables in paragraph 1.E.(2)(f), “Config 05,” of Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007, specify an inspection interval but not an initial threshold, this AD requires that the actions be done within the specified interval after inspecting in accordance with Table 1A, or 1B, as applicable, for Configuration 01 airplanes described in Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007, and thereafter at the inspection interval specified in the tables in paragraph 1.E.(2)(f), “Config 05,” of Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007. (iv) All crack lengths specified in Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007; and Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007, are considered “not to exceed” lengths. (2) Repeat the inspection at the intervals in, and according to the instructions defined in, Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007 (for Model A300 series airplanes); Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 2007 (for Model A300-600 series airplanes); or Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model A300-600 series airplanes); as applicable; except where Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007, specifies repetitive inspections for cracking if Airbus Service Bulletin A300-57-022 has not been embodied, this AD requires doing repetitive inspections for cracking if Airbus Service Bulletin A300-57-0222 (modification 11178H5410) has not been embodied. (3) Report to Airbus the first inspection results, whatever they may be, at the applicable time specified in paragraph (g)(3)(i) or (g)(3)(ii) of this AD. (i) If the inspection was done after April 23, 2008 (the effective date of AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008)), submit the report within 30 days after the inspection. (ii) If the inspection was accomplished prior to April 23, 2008 (the effective date of AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008)), submit the report within 30 days after April 23, 2008.
Unsafe condition
This AD was prompted by a report that information from an analysis and a fleet survey shows a need for reduced compliance times and intervals. We are issuing this AD to detect and correct cracking, which could lead to reduced structural integrity of the airplane.
Affected ADs
This AD replaces AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008).
Read the original on the Federal Register →
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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