AD 2011-08-12

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Do the actions required by paragraphs (g)(1) through (g)(8) of this AD, in accordance with the Instructions of Airbus All Operators Telex (AOT) A330-55A3040 or A340-55A4036, both Revision 02, both dated September 30, 2009, as applicable.

(1) In the reinforced location of the rudder: Within 1,800 flight hours after the rudder has accumulated 13,000 total flight cycles since first installation, or within 1,800 flight hours after the effective date of this AD, whichever is later, do a vacuum loss inspection to detect defects, including de-bonding between the skin and honeycomb core of the rudder.

(2) In the trailing edge location of the rudder: Within 21 months after the rudder has accumulated 13,000 total flight cycles since first installation, or within 21 months after the effective date of this AD, whichever is later, do an elasticity laminate checker inspection to detect defects, including de-bonding between the skin and honeycomb core of the rudder. If no defects are found, repeat the inspection two times at intervals not to exceed 4,500 flight cycles, but not fewer than 4,000 flight cycles from the most recent inspection.

(3) In locations other than those identified in paragraphs (g)(1) and (g)(2) of this AD (e.g., lower rib, upper edge, leading edge, and other locations): Within 1,800 flight hours after the rudder has accumulated 13,000 total flight cycles since first installation, or within 1,800 flight hours after the effective date of this AD, whichever is later, do an elasticity laminate checker inspection to detect defects, including de-bonding between the skin and honeycomb core of the rudder. Repeat the inspection thereafter at intervals not to exceed 1,800 flight hours.

(4) If no defects are found during any inspection required by paragraph (g)(3) of this AD: Within 21 months after the rudder has accumulated 13,000 total flight cycles since first installation, or within 21 months after the effective date of this AD, whichever is later, do a vacuum loss inspection on the other locations (e.g., lower rib, upper edge, leading edge, and other locations) to detect defects, including de-bonding between the skin and honeycomb core of the rudder.

(5) Accomplishment of the inspection required by paragraph (g)(4) of this AD terminates the initial and repetitive inspections required by paragraph (g)(3) of this AD.

(6) If any defect is found during any inspection required by this AD, before further flight, repair using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency Airworthiness (EASA) (or its delegated agent).

(7) If no defects are found during any inspection required by paragraphs (g)(1) and (g)(4) of this AD, before further flight, restore the vacuum loss holes by doing a temporary restoration with self-adhesive patches, a temporary restoration with resin, or a permanent restoration. Do the applicable actions specified in paragraph (g)(7)(i) or (g)(7)(ii) of this AD.

(i) For airplanes on which a temporary restoration with patch is done: Within 900 flight hours after the restoration, do a detailed inspection for defects of the restored area and repeat the inspection thereafter at intervals not to exceed 900 flight hours until the permanent restoration is done. Do the permanent restoration within 21 months after the temporary restoration.

(ii) For airplanes on which a temporary restoration with resin is done: Within 21 months after doing the temporary restoration, do the permanent restoration.

(8) If any defect is found during any initial inspection required by paragraphs (g)(1), (g)(3), and (g)(4) of this AD, at the applicable time in paragraph (g)(8)(i) or (g)(8)(ii) of this AD: Report the inspection results to Airbus SAS, SEER1/SEER2/SEER3, Customer Services, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 (0) 5 61 93 28 73; or e-mail to region1.StructureRepairSupport@airbus.com, region2.StructureRepairSupport@airbus.com, or region3.StructureRepairSupport@airbus.com.

(i) Inspections done before the effective date of this AD: Within 30 days after the effective date of this AD.

(ii) Inspections done on or after the effective date of this AD: Within 30 days after accomplishment of the inspection.

Actions accomplished before the effective date of this AD in accordance with the service information identified in table 2 of this AD, are considered acceptable for compliance with the corresponding actions specified in paragraphs (g)(1) through (g)(5) and paragraph (g)(7) of this AD for only the areas inspected. For all areas, the repetitive inspections required by this AD remain applicable.

(i) For rudders on which temporary vacuum loss hole restoration with resin or permanent vacuum loss hole restoration has been done, as required by paragraph (g)(7) of this AD, in accordance with the applicable AOT in table 2 of this AD before the effective date of this AD: Within 21 months after the restoration date, or within 3 months after the effective date of this AD, whichever occurs later, do an ultrasonic inspection for defects, including debonding of the reinforced area, in accordance with the Instructions of Airbus AOT A330-55A3040 or A340-55A4036, both Revision 02, both dated September 30, 2009, as applicable. If any defect is found, before further flight, repair using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA (or its delegated agent).

(j) As of the effective date of this AD, no person may install any rudder identified in table 1 of this AD on any airplane, unless the rudder has been inspected and all applicable corrective actions have been done in accordance with paragraph (g) or (i) of this AD, as applicable.

Note 1: This AD differs from the MCAI and/or service information as follows: No differences.