AD 2017-05-01

Within 4 months after the effective date of this AD, verify whether the Airbus modifications specified in table 1 to paragraphs (g), (h), and (i) of this AD, as applicable to airplane model, have been embodied on the airplane, in accordance with the Accomplishment Instructions of the applicable Airbus service bulletin specified in table 1 to paragraphs (g), (h), and (i) of this AD. A review of the airplane maintenance records is acceptable to accomplish the verification required by this paragraph, provided those records can be used to conclusively determine whether the modifications have been embodied.

If, during the verification required by paragraph (g) of this AD, it is determined that any modification has not been embodied, do the applicable actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD.

(1) If it is determined that any Airbus modification, specified in the applicable Airbus Service Bulletin, identified in “Set 1A” of table 1 to paragraphs (g), (h), and (i) of this AD is not embodied: Within the applicable compliance time specified in the applicable Airbus Service Bulletin identified in “Set 1A” of table 1 to paragraphs (g), (h), and (i) of this AD, or within 4 months after the effective date of this AD, whichever occurs later, do the applicable actions specified in paragraphs (h)(1)(i) through (h)(1)(xi) of this AD, except as required by paragraph (i) of this AD. Do all applicable related investigative and corrective actions before further flight.

(i) For airplanes on which Airbus Service Bulletin A300-53-0239, Revision 02, dated March 6, 2000, has not been embodied: Modify the longitudinal junction and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0239, Revision 02, dated March 6, 2000.

(ii) For airplanes on which Airbus Service Bulletin A300-53-247, Revision 2, dated July 20, 1990, has not been embodied: Modify the fuselage upper door frame structure by doing eddy current inspections for cracks of the structure specified in Airbus Service Bulletin A300-53-247, Revision 2, dated July 20, 1990, and a structural modification or repair, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-247, Revision 2, dated July 20, 1990.

(iii) For airplanes on which Airbus Service Bulletin A300-53-0271, Revision 05, dated June 21, 2013, has not been embodied: Modify the fuselage frame, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0271, Revision 05, dated June 21, 2013.

(iv) For airplanes on which Airbus Service Bulletin A300-53-0366, dated April 7, 2005, has not been embodied: Modify the fuselage frame, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0366, dated April 7, 2005.

(v) For airplanes on which Airbus Service Bulletin A300-53-0368, dated April 7, 2005, has not been embodied: Modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0366, dated April 7, 2005.

(vi) For airplanes on which Airbus Service Bulletin A300-53-0369, Revision 03, dated September 1, 2010, has not been embodied: Modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0369, Revision 03, dated September 1, 2010.

(vii) For airplanes on which Airbus Service Bulletin A300-53-0375, Revision 01, dated June 24, 2013, has not been embodied: Modify the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0375, Revision 01, dated June 24, 2013.

(viii) For airplanes on which Airbus Service Bulletin A300-53-0393, dated September 27, 2013, has not been embodied: Modify the fuselage frame, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0393, dated September 27, 2013.

(ix) For airplanes on which Airbus Service Bulletin A300-57-0203, Revision 04, dated February 18, 2015, has not been embodied: Modify the outer wing, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0203, Revision 04, dated February 18, 2015.

(x) For airplanes on which Airbus Service Bulletin A300-57-0258, dated September 30, 2014, has not been embodied: Modify the wing structure and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0258, dated September 30, 2014.

(xi) For airplanes on which Airbus Service Bulletin A300-57-0259, dated September 30, 2014, has not been embodied: Modify the wing structure, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0259, dated September 30, 2014.

(2) If it is determined that Airbus Service Bulletin A300-53-0374, Revision 04 dated July 5, 2013 (mod 12794) has not been embodied: Within the compliance time specified in paragraphs (h)(2)(i), (h)(2)(ii), (h)(2)(iii), and (h)(2)(iv) of this AD, as applicable, modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0374, Revision 04, dated July 5, 2013, except as required by paragraph (i) of this AD.

(i) For Model A300 B2 and A300 B4-100 airplanes, fuselage frame (FR) 55: Within 31,300 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later.

(ii) For Model A300 B2 and A300 B4-100 airplanes, FR 58: Within 49,700 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later.

(iii) For Model A300 B4-200 airplanes, FR 55: Within 33,600 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later.

(iv) For Model A300 B4-200 airplanes, FR 58: Within 55,800 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later.

(3) If it is determined that Airbus Service Bulletin A300-53-0373, Revision 03, dated September 1, 2010 (mod 12796) has not been embodied: Within the compliance time specified in paragraphs (h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of this AD, as applicable, modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0373, Revision 03, dated September 1, 2010, except as required by paragraph (i) of this AD.

(i) For Model A300 B2 airplanes: Within 42,700 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later.

(ii) For Model A300 B4-100 airplanes: Within 41,700 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later.

(iii) For Model A300 B4-200 airplanes: Within 47,900 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later.

Where any service information identified in table 1 to paragraphs (g), (h), and (i) of this AD specifies to contact the manufacturer for instructions or solutions, 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).

Accomplishing the modification required by paragraph (h)(1)(iii) of this AD terminates the modification required by paragraph (i) of AD 2004-23-20 for that airplane only.