Airworthiness Directive · Amendment 39-19627 · Fuselage
Airbus SAS Airplanes
This AD applies to the Airbus SAS airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, manufacturer serial numbers 1175, 1180, 1287 through 1475 inclusive, 1478, 1480, 1483, and 1506.
(1) Model A330-223F and -243F airplanes.
(2) Model A330-201, -202, -203, -223, and -243 airplanes.
(3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
We are superseding Airworthiness Directive (AD) 2016-16-01, which applied to certain Airbus SAS Model A330-200 Freighter, -200, and -300 series airplanes. AD 2016-16-01 required an inspection of affected structural parts in the cargo and cabin compartments to determine if proper heat treatment has been done, and replacement or repair if necessary. This AD retains the requirements of AD 2016-16-01 and requires inspection of additional locations of the cabin compartment structure. This AD was prompted by a report of a manufacturing defect (i.e., improperly heat-treated materials) that affects the durability of affected parts in the cargo and cabin compartments. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (g) of AD 2016-16-01, with revised service information. Within 72 months since first flight of the airplane, do an eddy current inspection (i.e., conductivity measurement) of affected structural parts in the cargo compartment to determine if proper heat treatment has been done as identified in, and in accordance with, the Accomplishment Instructions of Airbus Service Bulletin A330-53-3227, dated August 18, 2015; or Airbus Service Bulletin A330-53-3227, Revision 02, dated July 25, 2018. As of the effective date of this AD, only Airbus Service Bulletin A330-53-3227, Revision 02, dated July 25, 2018, may be used.
This paragraph restates the requirements of paragraph (h) of AD 2016-16-01, with revised service information. If, during the inspection required by paragraph (g) of this AD, an affected structural part in the cargo compartment is identified to have a measured value greater than 26 megasiemens per meter (MS/m), or greater than 44.8% International Annealed Copper Standard (IACS), before further flight, replace the affected structural part with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3227, dated August 18, 2015; or Airbus Service Bulletin A330-53-3227, Revision 02, dated July 25, 2018. As of the effective date of this AD, only Airbus Service Bulletin A330-53-3227, Revision 02, dated July 25, 2018, may be used.
This paragraph restates the requirements of paragraph (i) of AD 2016-16-01, with revised service information. If, during the inspection required by paragraph (g) of this AD, an affected structural part in the cargo compartment is identified to have a measured value other than those specified in Figure A-GFAAA, Sheet 01, “Inspection Flowchart,” of Airbus Service Bulletin A330-53-3227, dated August 18, 2015; or Airbus Service Bulletin A330-53-3227, Revision 02, dated July 25, 2018; before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. As of the effective date of this AD, only Airbus Service Bulletin A330-53-3227, Revision 02, dated July 25, 2018, may be used to identify the measured value.
This paragraph restates the requirements of paragraph (j) of AD 2016-16-01, with revised service information. Within 72 months since first flight of the airplane, do an eddy current inspection of affected structural parts in the cabin compartment to determine if proper heat treatment has been done as identified in, and in accordance with, the Accomplishment Instructions of Airbus Service Bulletin A330-53-3228, dated August 18, 2015; or Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 2018, except as required by paragraph (n) of this AD. As of the effective date of this AD, only Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 2018, except as required by paragraph (n) of this AD, may be used.
This paragraph restates the requirements of paragraph (k) of AD 2016-16-01, with revised service information. If, during the inspection required by paragraph (j) of this AD, an affected structural part in the cabin compartment is identified to have a measured value greater than 26 MS/m or greater than 44.8% IACS, before further flight, replace the affected structural part with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3228, dated August 18, 2015; or Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 2018, except as required by paragraph (n) of this AD. As of the effective date of this AD, only Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 2018, except as required by paragraph (n) of this AD, may be used.
This paragraph restates the requirements of paragraph (l) of AD 2016-16-01, with revised service information and new alternative actions. If, during the inspection required by paragraph (j) of this AD, an affected structural part in the cabin compartment is identified to have a measured value other than those specified in Figure A-GFAAA, Sheet 01, “Inspection Flowchart,” of Airbus Service Bulletin A330-53-3228, dated August 18, 2015; or to have a measured value between 22 MS/m and 26 MS/m or between 37.9 and 44.8% IACS, as specified in Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 2018; before further flight, do the actions specified in paragraph (l)(1) or (l)(2) of this AD. As of the effective date of this AD, only Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 2018, may be used to identify the measured value.
(1) Repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(2) Do an eddy current inspection to verify the measurement, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 2018, except as required by paragraph (n) of this AD.
(i) If an affected structural part in the cabin compartment is identified to have a measured value between 22 MS/m and 26 MS/m or between 37.9 and 44.8% IACS, before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(ii) If an affected structural part in the cabin compartment is identified to have a measured value greater than 26 MS/m or greater than 44.8% IACS, before further flight, do the replacement specified in paragraph (k) of this AD.
For an airplane on which the cabin compartment structure was inspected and corrective actions were done before the effective date of this AD as specified in the Accomplishment Instructions of Airbus Service Bulletin A330-53-3228, dated August 18, 2015: Before exceeding 108 months since the airplane's first flight, do an eddy current conductivity test of the forward cabin overhead compartment, and do all applicable related investigative and corrective actions, in accordance with the applicable “additional work” task in the Accomplishment Instructions of Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 2018, except as required by paragraph (n) of this AD. Do all applicable related investigative and corrective actions before further flight. Where Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 2018, specifies to contact Airbus for appropriate action: Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (q)(2) of this AD.
Any required action specified in Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 2018, that cannot be accomplished as specified therein must be accomplished using a method approved in accordance with the procedures specified in paragraph (q)(1) of this AD.
Although Airbus Service Bulletin A330-53-3227, Revision 02, dated July 25, 2018; and Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 2018; specify to submit certain information to the manufacturer, and specify that action as “RC” (required for compliance), this AD does not include that requirement.
