Airworthiness Directive · Amendment 39-18280 · Fuselage
Airbus Airplanes
This AD applies to all airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(2) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes.
We are superseding Airworthiness Directive (AD) 2013-02-10 for all Airbus Model A330-200 Freighter series airplanes; Model A330-200 and -300 series airplanes; and Model A340-200 and -300 series airplanes. AD 2013-02-10 required an inspection of the rods to determine the manufacturer; and for affected parts, an inspection for any cracking of the rods, and related investigative and corrective actions if necessary. This AD revises the affected airplanes of a certain paragraph of AD 2013-02-10 due to the discovery of an error. We are issuing this AD to detect and correct cracking of the rods, which could result in rupture of rods that attach the belly fairing to the airframe, leading to separation of the belly fairing from the airframe, and consequent damage to airplane structure and airplane systems.
This paragraph restates the requirements of paragraph (g) of AD 2013-02-10, Amendment 39-17331 (78 FR 7257, February 1, 2013), with revised affected airplanes. For Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and -313 airplanes, having manufacturer serial numbers (MSN) 0002 to 1113 inclusive, except MSNs 0996, 1039, 1054, 1059, 1105, 1107, 1108, and 1112: Within 72 months after March 8, 2013 (the effective date of AD 2013-02-10), accomplish the actions in paragraphs (g)(1) and (g)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3186, Revision 01, dated April 7, 2011 (for Model A330 airplanes); or A340-53-4185, Revision 01, dated April 7, 2011 (for Model A340 airplanes).
(1) Do a detailed inspection of the 21 rods of the belly fairing identified in Airbus Service Bulletin A330-53-3186, Revision 01, dated April 7, 2011 (for Model A330 airplanes); or A340-53-4185, Revision 01, dated April 7, 2011 (for Model A340 airplanes); for rod manufacturer identification. A review of airplane maintenance records is acceptable in lieu of this inspection if the manufacturer of the rods can be conclusively determined from that review.
(2) If the rod manufacturer is found to be Technical Airborne Components Industries (TAC), or if the manufacturer cannot be identified, do a high frequency eddy current (HFEC) inspection for cracking of the crimped end of the rod body and, if any crack is found, before further flight, do all applicable related investigative and corrective actions.
This paragraph restates the requirements of paragraph (h) of AD 2013-02-10, Amendment 39-17331 (78 FR 7257, February 1, 2013), with no changes. As of March 8, 2013 (the effective date of AD 2013-02-10), no person may install any affected TAC rod, as identified in Airbus Service Bulletin A330-53-3186, Revision 01, dated April 7, 2011; or A340-53-4185, Revision 01, dated April 7, 2011; as applicable; on any airplane unless the rod has passed (found to have no cracking) the inspection as required by paragraph (g)(2) of this AD.
This paragraph restates the credit provided by paragraph (i) of AD 2013-02-10, Amendment 39-17331 (78 FR 7257, February 1, 2013), with no changes. This paragraph provides credit for the inspections and corrective actions required by paragraph (g) of this AD, if those actions were performed before March 8, 2013 (the effective date of AD 2013-02-10), using Airbus Service Bulletin A330-53-3186, dated January 17, 2011 (for Model A330 airplanes); or A340-53-4185, dated January 17, 2011 (for Model A340 airplanes); which are not incorporated by reference in this AD.
