Airworthiness directives › 2015-13-07
AD 2015-13-07 Airworthiness Directives; Airbus Airplanes
Models named: A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, B4-622R, A300 F4-605R, F4-622R, A300 C4-605R Variant F. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes; certificated in any category; on which Airbus Modification 6146 has not been installed.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraphs (a), (b), (c), (d), and (e) of AD 98-13-23, Amendment 39-10614 (63 FR 34576, June 25, 1998), with revised service information. (1) Prior to the accumulation of 18,000 total landings, or within 2,000 landings after July 30, 1998 (the effective date of AD 98-13-23, Amendment 39-10614 (63 FR 34576, June 25, 1998), whichever occurs later: Perform a visual and eddy current inspection to detect cracks and/or corrosion of Areas 1 and 2 of the lower horizontal stabilizer cutout longeron, in accordance with Airbus Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; or the Accomplishment Instructions of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012. As of the effective date of this AD, use only Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, to do the actions required by this paragraph. (2) At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: Perform a visual and an eddy current inspection to detect cracks and corrosion of Area 3 of the lower horizontal stabilizer cutout longeron, in accordance with Airbus Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; or the Accomplishment Instructions of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012. As of the effective date of this AD, use only Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, to do the actions required by this paragraph. (i) Prior to the accumulation of 24,000 total landings, but not before the accumulation of 18,000 total landings; or (ii) Prior to the accumulation of 2,000 landings after July 30, 1998 (the effective date of AD 98-13-23, Amendment 39-10614 (63 FR 34576, June 25, 1998)). (3) If no cracking is detected during any inspection required by paragraph (g)(1) or (g)(2) of this AD: Before further flight, cold work and ream the vacated fastener holes, in accordance with Airbus Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; or the Accomplishment Instructions of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012; and perform the requirements of paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as applicable. As of the effective date of this AD, use only Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, to do the actions required by this paragraph. (i) For airplanes on which no cracking is found in Area 1 or 2: Repeat the inspections required by paragraph (g)(1) of this AD thereafter at intervals not to exceed 6,000 flight cycles. (ii) For airplanes on which no cracking is found in Area 3: Perform the various follow-on actions in accordance with Airbus Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; or the Accomplishment Instructions of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012. (The follow-on actions include installing a new corner fitting, installing a new longeron, and performing a cold working procedure.) After accomplishment of these follow-on actions, no further action is required by this AD. After the effective date of this AD, use only Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, to do the actions required by this paragraph. (4) If any cracking is detected during any inspection required by paragraph (g)(1) or (g)(2) of this AD, perform the requirements of paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as applicable. (i) If any cracking is found in Area 1 or 3 that is within the limits specified in Airbus Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; or Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012: Before further flight, repair in accordance with Airbus Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; or the Accomplishment Instructions of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012. As of the effective date of this AD, use only Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, to do the actions required by this paragraph. (ii) If any cracking is found in Area 2, or if any cracking is found in any area and that cracking is beyond the limits described in Airbus Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; or Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA), or Airbus's EASA Design Organization Approval (DOA). (5) If any corrosion is detected during any inspection required by paragraph (g) of this AD, prior to further flight, repair the corrosion, in accordance with Airbus Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; or the Accomplishment Instructions of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012. As of the effective date of this AD, use only Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, to do the actions required by this paragraph.
Unsafe condition
This AD was prompted by reports of cracking found at the lower corner of the horizontal stabilizer cutout longeron during a full scale fatigue test, and a determination that the risk of cracking is higher than initially determined. We are issuing this AD to prevent cracking of the lower horizontal stabilizer cutout longeron, the corner fitting, the skin strap, and the outer skin, which could result in reduced structural integrity of the horizontal-stabilizer cutout longeron.
Affected ADs
This AD replaces AD 98-13-23, Amendment 39-10614 (63 FR 34576, June 25, 1998).
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