AD 2016-11-05 Airworthiness Directives; Airbus Airplanes

Models named: A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, B4-622R, A300 F4-605R, A300 C4-605R Variant F. Read the applicability below — it usually turns on serial or part numbers too.

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 airplanes; and Model A300 C4-605R Variant F airplanes; certificated in any category; all manufacturer serial numbers.

Comply with this AD within the compliance times specified, unless already done.

This paragraph restates the requirements of paragraphs (a), (b), (c), (d), (e), and (f) of AD 99-16-01 with revised service information and reduced thresholds and repetitive intervals, for Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes; manufacturer serial numbers (MSNs) 252 through 553 inclusive; except those airplanes on which Airbus Modification 07601 has been accomplished prior to delivery. (1) Perform a high frequency eddy current (HFEC) rototest inspection to detect cracks in certain bolt holes where the main landing gear (MLG) forward pick-up fitting and MLG rib 5 aft are attached to the rear spar, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994; or Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011, may be used for the actions required by this paragraph. (i) For airplanes that have accumulated 17,300 total landings or less as of November 9, 1995 (the effective date of AD 95-20-02, Amendment 39-9380 (60 FR 52618, October 10, 1995)) (“AD 95-20-02”): Inspect prior to the accumulation of 17,300 total landings, or within 1,500 landings after November 9, 1995, whichever occurs later. (ii) For airplanes that have accumulated 17,301 or more total landings, but less than 19,300 total landings as of November 9, 1995 (the effective date of AD 95-20-02): Inspect within 1,500 landings after November 9, 1995. (iii) For airplanes that have accumulated 19,300 or more total landings as of November 9, 1995 (the effective date of AD 95-20-02): Inspect within 750 landings after November 9, 1995 (the effective date of AD 95-20-02). (2) If no crack is found during the inspection required by paragraph (g)(1) of this AD, repeat that inspection thereafter at the time specified in either paragraph (g)(2)(i) or (g)(2)(ii) of this AD, as applicable. (i) For airplanes on which Airbus Modification 07716 (as specified in Airbus Service Bulletin A300-57-6020) has not been accomplished: Inspect at the time specified in paragraph (g)(2)(i)(A) or (g)(2)(i)(B) of this AD, as applicable. (A) For airplanes having MSNs 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 13,000 landings, until the inspection required by paragraph (g)(4)(ii)(A)( 1 ) of this AD has been accomplished. (B) For airplanes having MSNs 252 through 464 inclusive: Repeat the inspection at intervals not to exceed 8,400 landings, until the inspection required by paragraph (g)(4)(ii)(A)( 2 ) of this AD has been accomplished. (ii) For airplanes on which Airbus Modification 07716 has been accomplished: Inspect at the time specified in either paragraph (g)(2)(ii)(A) or (g)(2)(ii)(B) of this AD, as applicable. (A) For airplanes having MSNs 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 11,800 landings, until the inspection required by paragraph (g)(4)(i)(B) of this AD has been accomplished. (B) For airplanes having MSNs 252 through 464 inclusive: Repeat the inspection within 10,700 landings following the initial inspection required by paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 7,500 landings, until the inspection required by paragraph (g)(4)(ii)(B)( 2 ) has been accomplished. (3) If any crack is found during the inspection required by either paragraph (g)(1) or (g)(2) of this AD, prior to further flight, accomplish the requirements of either paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as applicable. (i) For airplanes on which Airbus Modification 07716 has not been accomplished: Oversize the bolt hole by 1/32 inch and repeat the HFEC inspection required by paragraph (g)(1) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994. After accomplishing the oversizing and HFEC inspection, repeat the inspection, as required by paragraph (g)(2) of this AD, at the applicable schedule specified in that paragraph, until the inspection required by paragraph (g)(4)(ii)(B)( 1 ) or (g)(4)(ii)(B)( 2 ) of this AD has been accomplished. (A) If no cracking is detected, install the second oversize bolt in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994. (B) If any cracking is detected, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. (ii) For airplanes on which Airbus Modification 07716 has been accomplished: Repair in accordance with a method approved by the Manager, International Branch, ANM-116. After repair, repeat the inspections as required by paragraph (g)(2) of this AD at the applicable schedule specified in that paragraph, until the inspection required by paragraph (g)(4)(ii)(B)( 1 ) or (g)(4)(ii)(B)( 2 ) of this AD has been accomplished. (4) Perform an ultrasonic inspection to detect cracks in certain bolt holes where the MLG forward pick-up fitting and MLG rib 5 aft are attached to the rear spar, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, Revision 03, dated November 19, 1997; or Revision 04, including Appendix 1, dated February 24, 2011; at the time specified in paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as applicable. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011, may be used for the actions in this paragraph. (i) For airplanes not inspected prior to September 1, 1999 (the effective date of AD 99-16-01), as specified in Airbus Service Bulletin A300-57-6017, dated November 22, 1993; or Revision 01, including Appendix 1, dated July 25, 1994: Inspect at the time specified in paragraph (g)(4)(i)(A), (g)(4)(i)(B), or (g)(4)(i)(C) of this AD, as applicable. Accomplishment of this inspection terminates the requirements of paragraph (g)(1) of this AD. (A) For airplanes that have accumulated 17,300 total landings or fewer as of the effective date of this AD: Inspect prior to the accumulation of 17,300 total landings, or within 1,500 landings after September 1, 1999 (the effective date of AD 99-16-01), whichever occurs later. (B) For airplanes that have accumulated 17,301 total landings or more but fewer than 19,300 total landings as of September 1, 1999 (the effective date of AD 99-16-01): Inspect within 1,500 landings after September 1, 1999 (the effective date of AD 99-16-01). (C) For airplanes that have accumulated 19,300 total landings or more as of September 1, 1999 (the effective date of AD 99-16-01): Inspect within 750 landings after September 1, 1999 (the effective date of AD 99-16-01). (ii) For airplanes on which an HFEC inspection was performed prior to September 1, 1999 (the effective date of AD 99-16-01), in accordance with the requirements of paragraph (g)(1) of this AD, or in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, dated November 22, 1993: Inspect at the time specified in paragraph (g)(4)(ii)(A) or (g)(4)(ii)(B) of this AD, as applicable. (A) If no cracking was detected during any HFEC inspection accomplished prior to September 1, 1999 (the effective date of AD 99-16-01), and if Airbus Modification 07716 has not been accomplished: Inspect at the time specified in paragraph (g)(4)(ii)(A)( 1 ) or (g)(4)(ii)(A)( 2 ) of this AD, as applicable. ( 1 ) For airplanes having MSNs 465 through 553 inclusive: Inspect within 13,000 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 8,900 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(2)(i)(A) of this AD. ( 2 ) For airplanes having MSNs 252 through 464 inclusive: Inspect within 8,400 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 5,500 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(2)(i)(B) of this AD. (B) If any cracking was detected during any HFEC inspection performed prior to the effective date of this AD, regardless of the method of repair, or if Airbus Modification 07716 has been accomplished: Inspect at the time specified in paragraph (g)(4)(ii)(B)( 1 ) or (g)(4)(ii)(B)( 2 ) of this AD, as applicable. ( 1 ) For airplanes having MSNs 465 through 553 inclusive: Inspect within 11,800 landings after the most recent HFEC inspection, and thereafter at intervals not to exceed 8,200 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as applicable. ( 2 ) For airplanes having MSNs 252 through 464 inclusive: Inspect within 10,700 landings after the initial inspection in accordance with paragraph (g)(1) of this AD, or within 7,500 landings after the most recent HFEC inspection, whichever occurs later, and thereafter at intervals not to exceed 4,900 landings. Accomplishment of this inspection constitutes terminating action for the repetitive inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as applicable. (5) If no cracking is detected during the ultrasonic inspection required by paragraph (g)(4)(i) of this AD, repeat that inspection thereafter at the time specified in paragraph (g)(5)(i) or (g)(5)(ii) of this AD, as applicable, until the initial ultrasonic inspection required by paragraph (h) of this AD is done. (i) For airplanes having MSNs 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 8,900 landings. (ii) For airplanes having MSNs 232 through 464 inclusive: Repeat the inspection at intervals not to exceed 5,500 landings. (6) If any cracking is detected during any inspection performed in accordance with the requirements of paragraph (g)(4) or (g)(5) of this AD: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the Direction Générale de l'Aviation Civile (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Note 1 to paragraph (g) of this AD: Airbus Service Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 25, 1994; and Airbus Service Bulletin A300-57-6017, Revision 04, including Appendix 1, dated February 24, 2011; also reference Airbus Service Bulletin A300-57-6020, dated November 22, 1993, as an additional source of service information for installation of oversize studs in the bolt holes.

This AD was prompted by the results of a full-scale fatigue test when cracking was found on the rear spar of the wing, and the subsequent determination that the risk of such cracking is higher than initially determined. We are issuing this AD to detect and correct cracking of the rear spar of the wing, which could result in reduced structural integrity of the airplane.

This AD replaces AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999) (“AD 99-16-01”).