Airworthiness Directive · Amendment 39-17840 · Landing gear
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2015-10-03. 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, A330-202, A330-203, A330-223, A330-243, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, A330-341, A330-342, and A330-343 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, A340-212, A340-213, A340-311, A340-312, and A340- 313 airplanes, all MSNs, equipped with basic (201252 series) MLG or growth (201490 series) MLG.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. This AD requires 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 also provides for an optional measurement of the cardan pin clearance dimensions (gap check) and corrective actions if necessary, which would terminate the repetitive inspections. This AD was prompted by a report of a sidestay upper cardan pin of the MLG migrating out of position. 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.
(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 the effective date of this AD, except those MLG that have had a second overhaul: Within 30 days after the effective date of this AD, 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, 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 need for 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.
Measuring the cardan pin clearance dimensions (gap check) and doing the applicable corrective action specified in paragraph (h)(1) or (h)(2) of this AD terminates the repetitive 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 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).
(1) If the total clearance dimension (gap check result) is equal to or greater than 1.5 mm, 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) and (h)(2)(ii) of this AD.
(i) 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, to Airbus at the address specified in Appendix 2 of Airbus AOT A32L003-14, dated March 10, 2014.
(ii) Repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or European Aviation Safety Agency (EASA) (or its delegated agent, or the Design Approval Holder with EASA's design organization approval, as applicable).
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
