Airworthiness directives › 2020-22-06
AD 2020-22-06 Airworthiness Directives; Airbus SAS Airplanes
Models named: A319-111, -112, -113, -114, -115, -131, -132, -133, A320-211, -212. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; and Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2020-0040R1, dated June 16, 2020 (“EASA AD 2020-0040R1”).
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
For Airbus SAS Model A320-111, -211, -212, and -231 series airplanes on which Airbus Modification 21346 has not been done: This paragraph restates the requirements of paragraph (f) of AD 2004-25-02, with no changes. At the applicable time specified in paragraph (g)(1) or (2) of this AD: Do a detailed inspection to find cracking on the outboard flanges around the fastener holes of frames 38 through 41, between stringers 12 and 21, using Airbus Service Bulletin A320-53-1032, Revision 02, dated December 5, 2001. (1) For airplanes on which the inspection specified in Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998; or Airbus Service Bulletin A320-53-1032, Revision 02, dated December 5, 2001; has been done as of February 10, 2005 (the effective date of AD 2004-25-02): Do the next inspection within 4,900 flight cycles after accomplishment of the last inspection, or within 1,100 flight cycles after February 10, 2005, whichever is later. (2) For airplanes on which no inspection specified in Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998; or Airbus Service Bulletin A320-53-1032, Revision 02, dated December 5, 2001; has been done as of February 10, 2005 (the effective date of AD 2004-25-02): Do the inspection at the earlier of the times specified in paragraphs (g)(2)(i) and (ii) of this AD. (i) Before the accumulation of 30,000 total flight cycles. (ii) Before the accumulation of 24,800 total flight cycles, or within 3,500 flight cycles after February 10, 2005 (the effective date of AD 2004-25-02), whichever is later.
Unsafe condition
This AD was prompted by a report that, during full scale tests to support the Model A320 structure extended service goal (ESG) exercise, several cracks were found on both sides of the overwing emergency exit door cut-outs at fuselage section 15. The FAA is issuing this AD to address fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane.
Affected ADs
This AD replaces AD 99-01-19, Amendment 39-10987 (64 FR 1114, January 8, 1999) (“AD 99-01-19”); and AD 2004-25-02, Amendment 39-13889 (70 FR 1184, January 6, 2005) (“AD 2004-25-02”).
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