AD 2006-24-03

To prevent incorrect operation or jamming of the nose wheel steering (NWS), which could cause reduced controllability of the airplane on the ground, accomplish the following:

(a) For airplanes that were not modified in production by Airbus Modification 51381: Do the inspection specified in either paragraph (a)(1) or (a)(2) of this AD, in accordance with the required service bulletin identified in Table 1 of this AD, as applicable. The required compliance time is specified in paragraph (b) of this AD.

(1) Inspect for discrepancies of the grease by sending it to a laboratory for analysis, and do a detailed inspection for discrepancies of the gear teeth of the radial variable differential transducer (RVDT) driving ring and the gears in the RVDT gearboxes. If there are no discrepancies (such as metallic particles in the grease, abnormal wear of the gear teeth, or missing rubber sealant at the mating face between the main fitting and the RVDT gearbox), repeat the inspection as specified in paragraph (c) of this AD. If there is any discrepancy, do the inspection in paragraph (a)(2) of this AD within 3 months after the inspection specified in paragraph (a)(1) of this AD.

(2) Do a detailed inspection for damage of the chrome on the bearing surface of the nose landing gear (NLG) main fitting barrel under the NWS rotating sleeve. If there is no damage (such as flaking, corrosion, or blistering), repeat the inspection as specified in paragraph (c) of this AD. If there is any damage, before further flight, do the corrective action in paragraph (e) of this AD.

Note 1: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”

(b) For airplanes identified in paragraph (a) of this AD: Do the initial inspection specified in paragraph (a) of this AD at the latest of the following times:

(1) Within 60 months after the date that the new NLG was installed on the airplane.

(2) Within 60 months after the last major NLG overhaul accomplished before the effective date of this AD.

(3) Within 700 flight hours after the effective date of this AD.

(c) For airplanes identified in paragraph (a) of this AD: Repeat either inspection specified in paragraph (a)(1) or (a)(2) of this AD at intervals not to exceed the applicable interval specified in paragraph (c)(1) or (c)(2) of this AD, until the requirements of paragraph (g) of this AD are done.

(1) If the most recent inspection was the inspection specified in paragraph (a)(1) of this AD, then the next inspection must be done within 8 months.

(2) If the most recent inspection was the inspection specified in paragraph (a)(2) of this AD, then the next inspection must be done within 18 months.

(d) For airplanes modified in production by Airbus Modification 51381: Perform a detailed inspection for damage of the chrome on the bearing surface of the NLG main fitting barrel under the NWS rotating sleeve. Do the inspection at the later of the times specified in paragraphs (d)(1) and (d)(2) of this AD in accordance with the applicable required Airbus service bulletin identified in Table 1 of this AD. Repeat the inspection thereafter at intervals not to exceed 18 months, until the requirements of paragraph (g) of this AD have been done.

(1) Within 60 months after the date that the new NLG was installed on the airplane.

(2) Within 60 months after the last major NLG overhaul accomplished before the effective date of this AD.

(e) For all airplanes: If any damage or discrepancy is found during any inspection required by this AD, do the corrective action before further flight in accordance with the applicable required Airbus service bulletin identified in Table 1 of this AD, with the following exceptions:

(1) If discrepancies are found during any inspection specified in paragraph (a)(1) of this AD, the inspection in paragraph (a)(2) of this AD is required within 3 months.

(2) Where the service bulletin recommends contacting Messier-Dowty for appropriate action. Repair before further flight in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; the Direction Gonorale de l'Aviation Civile (or its delegated agent); or the European Aviation Safety Agency (or its delegated agent).

Note 2: Airbus Service Bulletins A330-32-3134 and A340-32-4172, both Revision 04, both dated April 3, 2006, refer to Messier-Dowty Special Inspection Service Bulletins D23285-32-037, Revision 2, dated May 23, 2002; and D23285-32-044, dated January 12, 2004; as additional sources of service information for the inspections.

(f) Actions done before the effective date of this AD in accordance with an applicable Approved Revision Level of the service bulletin identified in Table 1 of this AD are acceptable for compliance with the corresponding requirements of paragraphs (a), (d), and (e) of this AD.

(g) For all airplanes: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, modify the NLG as specified in Table 2 of this AD, as applicable.

(1) For NLGs overhauled before the effective date of this AD: At the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD:

(i) Within 60 months since the NLG was overhauled or 180 months since the NLG was new, whichever occurs first.

(ii) Within 6 months after the effective date of this AD.

(2) For NLGs not overhauled before the effective date of this AD: Within 120 months since the NLG was new, or within 6 months after the effective date of this AD, whichever occurs later.

(h) Accomplishment of both NLG modifications specified in paragraph (g) of this AD terminates the repetitive inspection requirements of this AD.

Note 3: Airbus Service Bulletins A330-32-3164 and A340-32-4204 refer to Messier-Dowty Service Bulletin D23285-32-042, dated June 19, 2003, as an additional source of service information for the modification.

Note 4: Airbus Service Bulletins A330-32-3192 and A340-32-4227 refer to Messier-Dowty Service Bulletin D23581-32-047, dated December 1, 2005, as an additional source of service information for the modification.

(i) Certain service bulletins specify to submit a report to the manufacturer. This AD does not require a report, unless the grease analysis required by paragraph (a)(1) of this AD is done at a lab chosen by the operator, which requires the results to be evaluated by Messier-Dowty.

(j)(1) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, is authorized to approve alternative methods of compliance for this AD.

(2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office.

Note 5: The subject of this AD is addressed in French airworthiness directives F-2005-209 and F-2005-210, both dated December 21, 2005.

(k) Unless otherwise specified in this AD, the actions must be done in accordance with the applicable service bulletins identified in Table 3 of this AD. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of this service information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. To inspect copies of this service information, go to the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.