Airworthiness Directive · Amendment 39-18158 · Landing gear
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2016-14-08. Comply with the one in force.
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 (MSNs), equipped with basic (201252 series) main landing gear (MLG), or growth (201490 series) MLG.
(2) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes, all MSNs, equipped with basic (201252 series) MLG or growth (201490 series) MLG.
We are superseding Airworthiness Directive (AD) 2014-09-05, for certain Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2014-09-05 required repetitive inspections of certain sidestay upper cardan pins of the main landing gear (MLG) and associated nuts and retainer assemblies, and pin replacement if necessary. This AD was prompted by a determination that a previously optional measurement is necessary to address the identified unsafe condition. This new AD continues to require a detailed inspection for visible chrome of each affected MLG sidestay upper cardan pin, associated nuts, and retainer assembly, and pin replacement if needed, and adds new requirements for measuring cardan pin clearance dimensions (gap check), doing corrective actions, and reporting all findings. We are issuing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing gear collapse and consequent damage to the airplane and injury to occupants.
This paragraph restates the requirements of paragraph (g) of AD 2014-09-05, Amendment 39-17840 (79 FR 23909, April 29, 2014), with no changes.
(1) For airplanes identified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD on which the affected MLG has exceeded 8 years since first overhaul, as of May 14, 2014 (the effective date of AD 2014-09-05, Amendment 39-17840 (79 FR 23909, April 29, 2014), except those MLG that have had a second overhaul: Within 30 days after May 14, 2014, accomplish a detailed inspection for visible chrome of each affected MLG sidestay upper cardan pin, and associated nut and retainer assembly, in accordance with the instructions of Airbus Alert Operators Transmission (AOT) A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices).
(i) Airplanes equipped with any MLG sidestay upper cardan pin subassembly part number (P/N) 201267202 (on 201252 series MLG).
(ii) Airplanes equipped with any MLG sidestay upper cardan pin subassembly P/N 201483202 (on 201490 series MLG).
(2) If, during any inspection required by paragraph (g)(1) of this AD, no pin chrome is visible inboard of the wing rear spar fitting lug, repeat the detailed inspection for visible chrome specified in paragraph (g)(1) of this AD thereafter at intervals not to exceed 10 days.
(3) If, during any inspection required by paragraphs (g)(1) or (g)(2) of this AD, a pin chrome is visible inboard of the wing rear spar fitting lug, before further flight, replace the affected cardan pin assembly, in accordance with the instructions of Airbus AOT A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). Replacement of the affected cardan pin assembly terminates the repetitive inspections required by paragraph (g)(2) of this AD.
Note 1 to paragraph (g) of this AD: MLG sidestay upper cardan pin subassembly P/N 201267202 (found in Airbus Illustrated Parts Catalogue (IPC) as item 32-11-18-01) includes the cardan pin P/N 201267600. MLG sidestay upper cardan pin subassembly P/N 201483202 (found in Airbus IPC as item 32-11-18-01) includes the cardan pin P/N 201483600.
For airplanes identified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD on which the affected MLG has exceeded 8 years since first overhaul, as of May 14, 2014 (the effective date of AD 2014-09-05, Amendment 39-17840 (79 FR 23909, April 29, 2014), except those MLG that have had a second overhaul: Within 4 months after the effective date of this AD: Measure the cardan pin clearance dimensions (gap check) and do the applicable corrective action specified in paragraph (h)(1) or (h)(2) of this AD. Measuring the gap check and doing the applicable corrective action specified in paragraph (h)(1) or (h)(2) of this AD, as applicable, terminates the inspections required by paragraphs (g)(1) and (g)(2) of this AD for that sidestay upper cardan pin, nut, and retainer only. The measurement must be done in accordance with Airbus AOT A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices).
(1) If the total clearance dimension (gap check result) is equal to or greater than 1.5 mm, before further flight, replace the cardan pin assembly, in accordance with Airbus AOT A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices).
(2) If the total clearance dimension (gap check) is less than 1.5 mm but greater than 0.6 mm, do the actions specified in paragraphs (h)(2)(i) or (h)(2)(ii) of this AD.
(i) Do the actions specified in paragraphs (h)(2)(i)(A) and (h)(2)(i)(B) of this AD.
(A) Within 30 days after accomplishing the gap check, send the information (Appendix 2 proforma, photographs, and the movement traceability sheet) specified in paragraph 4.2.3, “Findings,” of Airbus AOT A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices), to Airbus at the address specified in Appendix 2 (the issue date is not specified on this appendix) of Airbus AOT A32L003-14, dated March 10, 2014.
(B) Within 30 days after accomplishing the gap check, repair 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). If approved by the DOA, the approval must include the DOA-authorized signature.
(ii) Within 30 days after accomplishing the gap check, replace the cardan pin assembly, in accordance with Airbus AOT A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices).
For airplanes on which a gap check specified in paragraph (h) of this AD has been done: Except as required by paragraph (h)(2)(i) of this AD, at the applicable time specified in paragraphs (i)(1) and (i)(2) of this AD, report all findings (including no findings) to Airbus, in accordance with Airbus AOT A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3, (the issue date is not specified on the appendices).
(1) If the gap check was done on or after the effective date of this AD: Submit the report within 30 days after the gap check.
(2) If the gap check was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
