Airworthiness Directive · Amendment 39-17407 · Landing gear
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2023-12-19. Comply with the one in force.
This AD applies to Airbus Model A330-201, -202, -203, -223, -243, -223F, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; Model A340-211, -212, -213, -311, -312, and -313 airplanes; and Model A340-541 and Model A340-642 airplanes; certificated in any category; all manufacturer serial numbers.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 airplanes and Model A340- 642 airplanes. This AD was prompted by reports of cracks in the bogie pivot pin caused by material heating due to friction between the bogie pivot pin and bush, leading to chrome detachment and chrome dragging on the bogie pivot pin. This AD requires repetitive detailed inspections for degradation of the bogie pivot pins and for any cracks and damage of the pivot pin bushes of the main and central landing gear; a magnetic particle inspection of the affected bogie pivot pins for corrosion and base metal cracks; and repairing or replacing bogie pivot pins and pivot pin bushes, if necessary. We are issuing this AD to detect and correct cracks and damage to the main and central landing gear, which could result in the collapse of the landing gear and adversely affect the airplane's continued safe flight and landing.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 26 months after the effective date of this AD or 26 months after the first flight of the airplane, whichever occurs later, but no earlier than 12 months after the first flight of the airplane: Do a detailed inspection for degradation (i.e., loss of chromium plate, loose chromium, sharp edges) of the bogie pivot pins and for any cracks and damage of the pivot pin bushes of the main landing gear, and, as applicable, the central landing gear, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Repeat the inspection thereafter at intervals not to exceed 26 months. Accomplishment of an overhaul of the landing gear does not substitute the accomplishment of the inspection as required by this paragraph.
(1) Airbus Mandatory Service Bulletin A330-32-3240, Revision 02, including Appendices 01 and 02, dated December 2, 2011 (for Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes).
(2) Airbus Mandatory Service Bulletin A340-32-4281, Revision 01, including Appendices 01 and 02, dated December 2, 2011 (for Model A340-200 series airplanes and Model A340-300 series airplanes).
(3) Airbus Mandatory Service Bulletin A340-32-5096, Revision 01, including Appendices 01 and 02, dated December 2, 2011 (for Model A340-541 airplanes and Model A340-642 airplanes).
If, during any inspection required by paragraph (g) of this AD, any pivot pin bush is found cracked or damaged: Before further flight, repair or replace the pivot pin bush with a new or serviceable pivot pin bush, in accordance with the Accomplishment Instructions of the applicable service bulletin specified paragraph (h)(1), (h)(2), or (h)(3) of this AD.
(1) Airbus Mandatory Service Bulletin A330-32-3240, Revision 02, including Appendices 01 and 02, dated December 2, 2011 (for Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes).
(2) Airbus Mandatory Service Bulletin A340-32-4281, Revision 01, including Appendices 01 and 02, dated December 2, 2011 (for Model A340-200 series airplanes and Model A340-300 series airplanes).
(3) Airbus Mandatory Service Bulletin A340-32-5096, Revision 01, including Appendices 01 and 02, dated December 2, 2011 (for Model A340-541 airplanes and Model A340-642 airplanes).
If, during any inspection required by paragraph (g) of this AD, degraded chrome plating on any bogie pivot pin is found: Before further flight, do a non-destructive test (magnetic particle inspection) of the affected bogie pivot pin for corrosion and base metal cracks, in accordance with the Accomplishment Instructions of the applicable service bulletin specified paragraph (i)(1), (i)(2), or (i)(3) of this AD.
(1) Airbus Mandatory Service Bulletin A330-32-3240, Revision 02, including Appendices 01 and 02, dated December 2, 2011 (for Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes).
(2) Airbus Mandatory Service Bulletin A340-32-4281, Revision 01, including Appendices 01 and 02, dated December 2, 2011 (for Model A340-200 series airplanes and Model A340-300 series airplanes).
(3) Airbus Mandatory Service Bulletin A340-32-5096, Revision 01, including Appendices 01 and 02, dated December 2, 2011 (for Model A340-541 airplanes and Model A340-642 airplanes).
If, during the non-destructive test (magnetic particle inspection) specified in paragraph (i) of this AD, the bogie pivot pin is found corroded or the base metal is found cracked: Before further flight, repair or replace the bogie pin with a new or serviceable bogie pin, in accordance with the Accomplishment Instructions of the applicable service bulletin specified paragraph (j)(1), (j)(2), or (j)(3) of this AD.
(1) Airbus Mandatory Service Bulletin A330-32-3240, Revision 02, including Appendices 01 and 02, dated December 2, 2011 (for Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes).
(2) Airbus Mandatory Service Bulletin A340-32-4281, Revision 01, including Appendices 01 and 02, dated December 2, 2011 (for Model A340-200 series airplanes and Model A340-300 series airplanes).
(3) Airbus Mandatory Service Bulletin A340-32-5096, Revision 01, including Appendices 01 and 02, dated December 2, 2011 (for Model A340-541 airplanes and Model A340-642 airplanes).
Accomplishment of the corrective actions required by paragraphs (h) and (j) of this AD does not terminate the repetitive inspections required by paragraph (g) of this AD.
Submit a one-time report of the findings (both positive and negative) of the inspections required by paragraphs (g) and (i) of this AD to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France, ATTN: SDC32 Technical Data and Documentation Services; fax (+33) 5 61 93 28 06; email sb.reporting@airbus.com; at the applicable time specified in paragraph (l)(1) or (l)(2) of this AD. The report must include the inspection results and a description of any discrepancies found.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 90 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 90 days after the effective date of this AD.
