Airworthiness Directive · Amendment 39-18194 · Fuselage
Airbus Airplanes
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.
We are superseding Airworthiness Directive (AD) 98-13-23 for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 98-13-23 required inspections to detect corrosion and cracking of the lower horizontal stabilizer cutout longeron, the corner fitting, the skin strap, and the outer skin; and repair, if necessary. This new AD reduces the compliance times and repetitive intervals, and changes the inspection procedures. This AD was prompted by the 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.
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.
At the applicable times specified in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, except as provided by paragraphs (j)(1) and (j)(2) of this AD: Do the actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012. Repeat the inspections, thereafter, at the applicable intervals specified in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012. Doing the initial inspections required by paragraph (h) of this AD and applicable corrective actions required by paragraph (i) of this AD terminates the requirements of paragraph (g) of this AD.
(1) Do a general visual inspection for cracking and corrosion of the lower horizontal stabilizer cut-out longeron, the corner fitting, the skin strap, and the skin between frame (FR)87 and FR89 and between stringers (STGR)24 and STGR27, left- and right-hand sides.
(2) Do a high frequency eddy current (HFEC) inspection for cracking of the flanges of the lower corner fittings and the edges of the outer skin and the edges of the longeron, the skin strap, and the skin at the run-out of the corner fitting above the last eight fasteners.
(3) Do a rotating probe inspection for cracking of the fastener holes. If no cracking is found during the rotating probe inspection, before further flight, do a cold expansion of the fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012.
(1) If any corrosion is found during any inspection required by paragraph (h) of this AD, before further flight, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012.
(2) If any cracking is found during any inspection required by paragraph (h) of this AD, before further flight, repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, except where Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, specifies to contact Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA, or Airbus's EASA DOA.
(1) Where Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, specifies a grace period of 1950 flight cycles or 4100 flight hours, this AD specifies the grace period after the effective date of this AD.
(2) Where Airbus Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, specifies a compliance time “after receipt of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
