Airworthiness Directive · Amendment 39-14993 · Airbus Model A330 Airplanes
Airbus Model A330 Airplanes
Superseded. A later AD replaced this one: AD 2014-16-25. Comply with the one in force.
This AD applies to Airbus Model A330-201, -202, -203, -223, -243, -301, -321, -322, -323, -341, -342, and -343 airplanes, certificated in any category; except those on which Airbus Modification 49202 has been incorporated in production.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A330-300 airplanes. That AD currently requires reinforcement of the structure of the center fuselage by installing external stiffeners (butt straps) at frame (FR) 53.3 on the fuselage skin between left-hand (LH) and right-hand (RH) stringer (STR) 13, and related investigative and corrective actions. This new AD requires additional reinforcement of the structure of the center fuselage by installing external stiffeners (butt straps) at frame FR53.3 on the fuselage skin between LH and RH STR13, and related investigative and other specified actions. This AD also adds airplanes to the applicability. This AD results from cracking found at the circumferential joint of FR53.3. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For Airbus Model A330-301, -321, -322, -323, -341, -342, and -343 airplanes, except those on which Airbus Modification 41652S11819 has been incorporated in production: At the later of the times in paragraphs (f)(1) and (f)(2) of this AD, install the butt straps at FR53.3 on the fuselage skin between left-hand (LH) and right-hand (RH) stringer (STR) 13, and do all related investigative and corrective actions before further flight. Except as provided by paragraph (g) of this AD, do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3127, Revision 01, dated November 21, 2003.
(1) Before the accumulation of 14,700 total flight cycles or 51,400 total flight hours, whichever occurs earlier.
(2) Within 6 months after October 19, 2005 (the effective date of AD 2005-20-07).
For Airbus Model A330-301, -321, -322, -323, -341, -342, and -343 airplanes, except those on which Airbus Modification 41652S11819 has been incorporated in production: If any crack is detected during the related investigative actions (rototest) required by paragraph (f) of this AD, before further flight, repair the crack according to a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the DGAC (or its delegated agent); or the EASA (or its delegated agent).
For Airbus Model A330-201, -202, -203, -223, -243, -301, -321, -322, -323, -341, -342, and -343 airplanes, on which Airbus Modification 41652S11819 has been incorporated in production or in accordance with paragraph (f) of this AD, except those airplanes on which Airbus Modification 49202 has been incorporated in production: At the later of the times in paragraphs (h)(1) and (h)(2) of this AD, install the butt straps at FR53.3 on the fuselage skin between LH and RH STR13; and do all related investigative and other specified actions before further flight, as applicable. Do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3143, Revision 01, including Appendix 01, dated June 29, 2006; except if any crack is detected during a related investigative action (rototest), before further flight, repair the crack using a method approved by the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
(1) Before the accumulation of 17,600 total flight cycles or 61,600 total flight hours, whichever occurs earlier.
(2) Within 6 months after the effective date of this AD.
(i) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A330-53-3143, including Appendix 01, dated December 24, 2004, are acceptable for compliance with the corresponding requirements of paragraph (h) of this AD.
