Airworthiness Directive · Amendment 39-18369 · Fuselage
Airbus Airplanes
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, all manufacturer serial numbers.
(1) Airbus Model A300 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.
We are superseding Airworthiness Directive (AD) 2004-20-14, for all Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes. AD 2004-20-14 required repetitive inspections to detect cracking of the splice fitting at fuselage frame (FR) 47 between stringers 24 and 26 (left- and right-hand sides), and corrective actions if necessary. This new AD reduces the inspection compliance time and repetitive inspection intervals, and adds Airbus Model A300 C4-605R Variant F airplanes to the applicability. This AD was prompted by a determination that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of cracks in the splice fitting at fuselage FR 47. We are issuing this AD to detect and correct cracking of the splice fitting at fuselage FR 47; such cracking could result in reduced structural integrity of the airplane.
This paragraph restates the requirements of paragraph (a) of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), with new service information. For airplanes defined in Airbus Service Bulletin A300-53-0350, Revision 02, dated November 12, 2002: Do a high frequency eddy current (HFEC) inspection to detect cracking of the splice fitting at fuselage FR 47 between stringers 24 and 26 (left- and right-hand sides), at the applicable times specified in paragraph (g)(1) or (g)(2) of this AD. Repeat the inspection thereafter at the earlier of the flight-cycle/flight-hour intervals specified in the applicable column in Table 2 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002. Do the inspections in accordance with Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002; or Revision 03, excluding Appendix 01, dated July 26, 2007. As of the effective date of this AD, use only Airbus Service Bulletin A300-53-0350, Revision 03, excluding Appendix 01, dated July 26, 2007.
(1) For airplanes that have accumulated 20,000 or more total flight cycles as of November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do the initial inspection at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) At the earlier of the flight-cycle/flight-hour intervals after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002.
(ii) Within 750 flight cycles or 1,500 flight hours after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), whichever is first.
(2) For airplanes that have accumulated fewer than 20,000 total flight cycles as of November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do the initial inspection at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) At the earlier of the flight-cycle/flight-hour intervals after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002.
(ii) Within 1,800 flight cycles or 3,000 flight hours after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), whichever is first.
This paragraph restates the requirements of paragraph (b) of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), with new service information. For airplanes defined in Airbus Service Bulletin A300-53-6123, Revision 02, dated November 12, 2002: Do the HFEC inspection required by paragraph (g) of this AD at the applicable times specified in paragraph (h)(1) or (h)(2) of this AD. Repeat the inspection thereafter at the earlier of the flight-cycle/flight-hour intervals specified in the applicable column in Table 2 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002. Do the inspections in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002; or Revision 06, dated September 28, 2011. Accomplishment of the actions required by paragraph (j) of this AD terminates the requirements of this paragraph.
(1) For airplanes that have accumulated 10,000 or more total flight cycles as of November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do the initial inspection within 750 flight cycles or 1,900 flight hours after November 17, 2004, whichever is first.
(2) For airplanes that have accumulated fewer than 10,000 total flight cycles as of November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do the initial inspection at the later of the times specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) At the earlier of the flight-cycle/flight-hour intervals after November 17, 2004 (the effective date of AD 2004-2-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002.
(ii) Within 1,500 flight cycles or 3,800 flight hours after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), whichever is first.
This paragraph restates the requirements of paragraph (c) of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), with revised repair instructions. Repair any cracking found during any inspection required by paragraphs (g) and (h) this AD before further flight, in accordance with Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002; or Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002; as applicable. Where Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002; or Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002; specifies to contact Airbus in case of certain crack findings, this AD requires that a repair be accomplished before further flight using a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
For airplanes identified in paragraphs (c)(2) through (c)(5) of this AD: At the applicable time specified in paragraph (j)(1) or (j)(2) of this AD, remove the fasteners and accomplish an HFEC rotating probe inspection for cracking of the splice fitting between stringer 24 and 26, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 06, dated September 28, 2011. Repeat the inspection thereafter at the applicable intervals specified in paragraphs (k)(1) through (k)(4) of this AD. If no cracking is found: Before further flight after each inspection, install new fasteners, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 06, dated September 28, 2011. Accomplishment of the initial inspection required by this paragraph terminates the requirements of paragraph (h) of this AD for that airplane.
(1) For airplanes on which Airbus Modification 5890 or the actions specified in Airbus Service Bulletin A300-53-6131 have not been done: At the applicable time specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD.
(i) For airplanes that have an average flight time (AFT) that is more than 1.5 hours: At the later of the times specified in paragraphs (j)(1)(i)(A) and (j)(1)(i)(B) of this AD.
(A) Before the accumulation of 2,500 total flight cycles or 5,500 total flight hours, whichever occurs first.
(B) Within 800 flight cycles or 1,750 flight hours, whichever occurs first after the effective date of this AD.
(ii) For airplanes that have an AFT that is equal to or less than 1.5 hours: At the later of the times specified in paragraphs (j)(1)(ii)(A) and (j)(1)(ii)(B) of this AD.
(A) Before the accumulation of 2,700 total flight cycles or 4,100 total flight hours, whichever occurs first.
(B) Within 800 flight cycles or 1,750 flight hours, whichever occurs first after the effective date of this AD.
(2) For airplanes that have accomplished Airbus Modification 5890 or have accomplished the actions specified in Airbus Service Bulletin A300-53-6131: At the applicable time specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD.
(i) For airplanes that have an AFT that is more than 1.5 hours: At the later of the times specified in paragraphs (j)(2)(i)(A) and (j)(2)(i)(B) of this AD.
(A) Before the accumulation of 6,800 total flight cycles or 14,700 total flight hours, whichever occurs first.
(B) Within 800 flight cycles or 1,750 flight hours, whichever occurs first after the effective date of this AD.
(ii) For airplanes that have an AFT that is equal to or less than 1.5 hours: At the later of the times specified in paragraphs (j)(2)(ii)(A) and (j)(2)(ii)(B) of this AD.
(A) Before the accumulation of 7,300 total flight cycles or 11,000 total flight hours, whichever occurs first.
(B) Within 800 flight cycles or 1,750 flight hours, whichever occurs first after the effective date of this AD.
For airplanes identified in paragraphs (c)(2) through (c)(5) of this AD: Repeat the inspection required by paragraph (j) of this AD at the applicable time specified in paragraphs (k)(1) through (k)(4) of this AD.
(1) For airplanes that have an AFT of more than 1.5 hours and meet the applicable conditions specified in paragraphs (k)(1)(i) through (k)(1)(iv) of this AD: Inspect at intervals not to exceed 2,000 flight cycles or 4,300 flight hours, whichever occurs first.
(i) Airplanes on which Airbus Modification 5890 has not been accomplished.
(ii) Airplanes on which the actions specified in Airbus Service Bulletin A300-53-6131 have not been accomplished.
(iii) Airplanes on which Airbus Modification 5890 has been accomplished and have splice part number (P/N) A53834139-202/-203 installed.
(iv) Airplanes on which the actions specified in Airbus Service Bulletin A300-53-6131 have been accomplished and have splice P/N A53834139-202/-203 installed.
(2) For airplanes that have an AFT that is equal to or less than 1.5 hours and meet the applicable conditions specified in paragraphs (k)(2)(i) through (k)(2)(iv) of this AD: Inspect at intervals not to exceed 2,100 flight cycles or 3,200 flight hours.
(i) Airplanes on which Airbus Modification 5890 has not been accomplished.
(ii) Airplanes on which the actions specified in Airbus Service Bulletin A300-53-6131 have not been accomplished.
(iii) Airplanes on which Airbus Modification 5890 has been accomplished and have splice P/N A53834139-202/-203 installed.
(iv) Airplanes on which the actions described in Airbus Service Bulletin A300-53-6131 have been accomplished and have splice P/N A53834139-202/-203 installed.
(3) For airplanes that have an AFT of more than 1.5 hours and meet the applicable conditions specified in paragraphs (k)(3)(i) and (k)(3)(ii) of this AD: Inspect at intervals not to exceed 1,600 flight cycles or 3,500 flight hours.
(i) Airplanes on which Airbus Modification 5890 has been accomplished and have splice P/N A53812635-200/-201/-202/-203 installed.
(ii) Airplanes on which the actions specified in Airbus Service Bulletin A300-53-6131 have been accomplished and have splice P/N A53812635-200-201/-202/-203 installed.
(4) For the airplanes that have an AFT that is equal to or less than 1.5 hours and meet the applicable conditions specified in paragraphs (k)(4)(i) and (k)(4)(ii) of this AD: Inspect at intervals not to exceed 1,700 flight cycles or 2,600 flight hours.
(i) Airplanes on which Airbus Modification 5890 has been accomplished and have splice P/N A53812635-200/-201/-202/-203 installed.
(ii) Airplanes on which the actions specified in Airbus Service Bulletin A300-53-6131 have been accomplished and have splice P/N A53812635-200/-201/-202/-203 installed.
If, during any inspection required by paragraph (j) or (k) of this AD, any crack is found: Before further flight, do the applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 06, dated September 28, 2011, except as provided by paragraph (m) of this AD.
If any crack is found during any inspection required by paragraph (j) or (k) of this AD and Airbus Service Bulletin A300-53-6123, Revision 06, dated September 28, 2011; or Airbus Service Bulletin A300-53-0350, Revision 03, dated July 26, 2007; specifies to contact Airbus: Before further flight, repair the crack using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA.
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.
