AD 2017-13-05 Airworthiness Directives; Airbus Airplanes

Models named: A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes, all manufacturer serial numbers. (2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541, and -642 airplanes, all manufacturer serial numbers.

Comply with this AD within the compliance times specified, unless already done.

For airplanes other than those identified in figure 1 to paragraphs (g), (h), and (q) of this AD: If, during any flight, one of the “PRIM X PITCH FAULT” or “STAB CTL FAULT” messages is displayed on the ECAM associated with the “PITCH TRIM ACTR (1CS)” maintenance message, before further flight after each time the message is displayed on the ECAM, do the actions specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Do the applicable detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path; check the checkable shear pins (CSP), if installed; and do all applicable corrective actions; as specified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD. Do all applicable corrective actions before further flight. (i) For Model A330 series airplanes: Do the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-27-3102, Revision 09, dated March 29, 2016, except as required by paragraph (n)(1) of this AD. (ii) For Model A340-200 and -300 series airplanes: Do the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-27-4107, Revision 09, dated March 29, 2016, except as required by paragraph (n)(1) of this AD. (iii) For Model A340-500 and -600 series airplanes: Do the actions 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). Note 1 to paragraph (g)(1)(iii) of this AD: Guidance for the inspection of the ball-screw assembly can be found in Task 274000-B0002-1-C, Inspection of the ball-screw assembly for integrity of the primary and secondary load paths, of the Airbus A340 Airworthiness Limitations Section (ALS) Part 3—Certification Maintenance Requirements (CMR), Revision 03, dated October 19, 2015. (2) Lubricate the THSA ball-nut in accordance with the applicable service information specified in paragraph (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of this AD. (i) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of Airbus A330 ALS Part 4—System Equipment Maintenance Requirements (SEMR), Revision 05, dated October 19, 2015 (for Model A330 series airplanes). (ii) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of Airbus A340 ALS Part 4—System Equipment Maintenance Requirements (SEMR), Revision 04, dated October 19, 2015 (for Model A340-200 and -300 series airplanes). (iii) Task 274000-B0003-1-C, Lubrication of THS Actuator ball-screw nut, of Airbus A340 ALS Part 3—Certification Maintenance Requirements (CMR), Revision 03, dated October 19, 2015 (for Model A340-500 and -600 series airplanes). Figure 1 to Paragraphs ( g ), ( h ), and ( q ) of This AD—Definition of Airplane Groups Group Airplane models On which the following actions or modifications have been done Group 1 airplanes Airbus Model A330-200 and -300 series airplanes On which the actions specified in Airbus Service Bulletin A330-27-3137, dated March 20, 2007; or Revision 01, dated December 6, 2007; and Airbus Service Bulletin A330-92-3046, Revision 04, dated July 16, 2010; or Revision 05, dated November 7, 2011; or Revision 06, dated November 15, 2013; have been embodied in service.   Airbus Model A340-200 and -300 series airplanes On which the actions specified in Airbus Service Bulletin A340-27-4136, including Appendix 1, dated March 20, 2007; or Revision 01, including Appendix 1, dated December 6, 2007; and Airbus Service Bulletin A340-92-4056, Revision 03, dated July 16, 2010; have been embodied in service. Group 2 airplanes Airbus Model A330-200 and -300 series airplanes and Model A340-200 and -300 series airplanes On which Airbus Modifications 55780, 52269, and 56056 have been embodied in production.   Airbus Model A340-500 and -600 series airplanes On which Airbus Modifications 54882, 52191, and 56058 have been embodied in production. Group 3 airplanes Airbus Model A330-200 and -300 series airplanes On which Airbus Service Bulletin A330-27-3137, dated March 20, 2007; or Revision 01, dated December 6, 2007; has been embodied in service and Airbus Modifications 52269 and 56056 have been embodied in production.   Airbus Model A330-200 and -300 series airplanes On which Airbus Modification 55780 has been embodied in production and Airbus Service Bulletin A330-92-3046 Revision 04, dated July 16, 2010; or Revision 05, dated November 07, 2011; or Revision 06, dated November 15, 2013; has been embodied in service.   Airbus Model A340-200 and -300 series airplanes On which Airbus Service Bulletin A340-27-4136, including Appendix 1, dated March 20, 2007; or Revision 01, including Appendix 1, dated December 6, 2007; has been embodied in service and Airbus Modifications 52269 and 56056 have been embodied in production.   Airbus Model A340-200 and -300 series airplanes On which Airbus Modification 55780 has been embodied in production and Airbus Service Bulletin A340-92-4056, Revision 03, dated July 16, 2010, has been embodied in service.

This AD was prompted by the determination that a modification that automatically detects failure of the ball-screw assembly is necessary. We are issuing this AD to detect and correct wear on the trimmable horizontal stabilizer actuator (THSA), possibly resulting in damage to the ball-screw and fail-safe nut, which could jam the THSA and result in reduced control of the airplane.

This AD replaces AD 2013-13-16, Amendment 39-17504 (78 FR 47537, August 6, 2013) (“AD 2013-13-16”).