Airworthiness Directive · Amendment 39-18321 · Fuselage
Airbus Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers.
(1) Airbus Model A330-201, -202, -203, -223, -223F, -243, and -243F airplanes.
(2) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(3) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-200 and A340-300 series airplanes. This AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). This AD requires repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and reinstallation or installation of reinforcing clamps on certain strut ends. We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts, making the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane.
For the purpose of this AD, a Societé Anonyme de Recherche Mécanique Appliquée (SARMA) strut is a strut on which the diameter of the strut end is less than 43 millimeters. All other struts are Technical Airborne Components Industries (TAC) struts.
At the applicable time specified in paragraph (i) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of all TAC strut ends of the THS support located at frame (FR) 91 in the tail cone, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. Repeat the inspection thereafter at intervals not to exceed 42 months or 20,000 flight hours, whichever occurs first. For airplanes on which Airbus Modification 203493 or 203834 has been embodied in production, or Airbus Service Bulletin A330-53-3204 or Airbus Service Bulletin A340-53-4199, as applicable, has been embodied in service, remove the clamp from each strut end before accomplishing the inspections required by this paragraph.
Do the inspections required by paragraphs (h) and (k) of this AD at the applicable times specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD.
(1) For Model A330 series airplanes having manufacturer serial numbers 012 through 209 inclusive, and Model A340 series airplanes having manufacturer serial numbers 002 through 210 inclusive: Within 6 months after the effective date of this AD.
(2) For Model A330 series airplanes having manufacturer serial numbers 211 through 422 inclusive, and Model A340 series airplanes having manufacturer serial numbers 212 through 447 inclusive: Within 24 months after the effective date of this AD.
(3) For Model A330 series airplanes having manufacturer serial numbers 423 and subsequent, and Model A340 series airplanes having manufacturer serial numbers 450 through 955 inclusive: Within 36 months after the effective date of this AD or since the first flight of the airplane, whichever occurs later.
(1) If, during any inspection required by paragraph (h) of this AD, no cracks are found: Before further flight, reinstall or install, as applicable, reinforcing clamps on the strut ends, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable.
(2) If, during any inspection required by paragraph (h) of this AD, any crack is found: Before further flight, replace any affected strut with a new or serviceable TAC strut and install reinforcing clamps on the strut end, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable.
At the applicable time specified in paragraph (i) of this AD, do an HFEC inspection for cracking of all SARMA strut ends of the THS support located at FR 91 in the tail cone, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. Repeat the inspection thereafter at intervals not to exceed 12 months.
If any crack is found on a strut end during the inspection required by paragraph (k) of this AD: Before further flight, replace any affected SARMA strut with a new or serviceable TAC strut and install reinforcing clamps on the strut end, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable.
Replacement of THS struts on an airplane does not constitute terminating action for the repetitive inspections required by this AD.
Although Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; and Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; specify to submit certain information to the manufacturer, this AD does not include that requirement.
