Airworthiness Directive · Amendment 39-18024 · Landing gear
Airbus Airplanes
This AD applies to Airbus 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; certificated in any category; all manufacturer serial numbers.
We are superseding Airworthiness Directive (AD) 2012-06-19 for certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340- 200 and -300 series airplanes. AD 2012-06-19 required repetitive inspections of the main fitting and sliding tube of the nose landing gear (NLG) for defects, damage, and cracks; and corrective actions if necessary. This new AD requires an inspection of the part number and serial number of the NLG main fitting and NLG sliding tube; for affected parts, this new AD requires a magnetic particle inspection (MPI) for cracks, and flap peening and replacement if necessary. This new AD also requires, for certain parts, additional inspections for damage and cracking. This new AD also adds airplanes to the applicability. This AD was prompted by reports of a cracked main fitting and sliding tube during NLG overhaul. We are issuing this AD to detect and correct cracks, defects, or damage of the main fitting or sliding tube, which could result in consequent NLG collapse.
This paragraph restates the requirements of paragraph (g) of AD 2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), with revised service information. For Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and -313 airplanes; if fitted with the NLG identified in table 1 to paragraph (g) of this AD: Within 900 flight hours after April 30, 2012 (the effective date of AD 2012-06-19), do a detailed inspection of the NLG main fitting and sliding tube for any cracks, defects, and damage of the paint or surface protection, including paint removal and cracking of the surface treatment. Before further flight after doing the detailed inspection of the NLG, remove the labels, paint, surface protection coatings, and cadmium from the NLG main fitting; do a detailed inspection for any damage to the surface that will impair the magnetic particle inspection (MPI); and, if any defects are found, before further flight, remove any defects by polishing. Do all actions specified in this paragraph in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(1) or (g)(2) of this AD.
(1) For Model A330 airplanes: Airbus Mandatory Service Bulletin A330-32-3233, dated October 22, 2009; or Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014.
(2) For Model A340 airplanes: Airbus Mandatory Service Bulletin A340-32-4275, dated October 22, 2009; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013.
| Part No. | Serial No. |
|---|---|
| D23285200 | B2 |
| D23285101-7 | B58 |
| D23285101-10 | B75 |
| D23581100-1 | B124 |
| D23581100-1 | B159 |
| D23581100-7 | B386 |
| D23581100-7 | B398 |
| D23581100-7 | B400 |
| D23581100-7 | B403 |
This paragraph restates the requirements of paragraph (h) of AD 2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), with revised service information. Before further flight after doing the actions required in paragraph (g) of this AD: Do an MPI for cracking of the NLG main fitting and sliding tube, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(1) or (g)(2) of this AD.
(1) If no crack is detected during the MPI required by the introductory text of paragraph (h) of this AD: Before further flight, flap peen the inspected area where the paint and cadmium has been removed, and replace the protective coatings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(1) or (g)(2) of this AD.
(2) If any crack is detected during the MPI required by the introductory text of paragraph (h) of this AD: Before further flight, replace the damaged part with a new or serviceable part, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(1) or (g)(2) of this AD.
Within 1,000 flight hours after the effective date of this AD, identify the part number and serial number of the NLG main fitting and NLG sliding tube, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable. A review of airplane maintenance records is acceptable in lieu of this identification if the part number and the serial number of the NLG main fitting and NLG sliding tube can be conclusively determined from that review.
If, during the identification required by paragraph (i) of this AD, it is determined any NLG main fitting or NLG sliding tube is installed and the fitting or tube has a part number and serial number listed in Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable: Within 1,000 flight hours after the effective date of this AD, do an MPI for cracks of the affected parts, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable. Accomplishing the MPI required by this paragraph terminates the inspections required by paragraphs (g) and (h) of this AD.
(1) If any crack is detected during the MPI required by the introductory text of paragraph (j) of this AD: Before further flight, replace any cracked part (NLG main fitting and NLG sliding tube) with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable.
(2) If no crack is detected during the MPI required by the introductory text of paragraph (j) of this AD: Before further flight, do a flap peening to introduce compressive residual stress and corrosion protection, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable.
Within 900 flight hours after doing the flap peening required by paragraph (j)(2) of this AD, do a detailed inspection for damage to paint, damage to the sealant around the labels, damage to the cadmium or base metal, and for cracking of the affected parts, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable. Repeat the inspection thereafter at intervals not to exceed 900 flight hours.
(1) If any damage to the paint, damage to the sealant around the labels, or damage to the cadmium or base metal, is detected during any detailed inspection required by the introductory text of paragraph (k) of this AD; Before further flight, do an MPI for cracking of the affected parts, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable.
(2) If any cracking is detected during any inspection required by the introductory text of paragraph (k) or paragraph (k)(1) of this AD: Before further flight, replace any cracked part with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable.
Replacement of a part as required by paragraph (j)(1) or (k)(2) of this AD is terminating action for the repetitive detailed inspections required by paragraph (k) of this AD for that part, provided that the part number and serial number of the replacement part is not listed in Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable.
As of the effective date of this AD, installation of an NLG main fitting or NLG sliding tube having a part number and serial number listed in Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable; is allowed, provided that the NLG main fitting and NLG sliding tube have not accumulated more than 900 flight hours since the most recent inspection accomplished in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable.
