AD 2011-20-03

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

For rudders identified in table 1 or table 2 of this AD: Do the actions specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, and paragraphs (g)(3) and (g)(4) of this AD, at the time specified. Do the actions in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-55-2049 (for Model A310 series airplanes) or A300-55-6048 (for Model A300-600 series airplanes), both dated March 16, 2010.

(1) For rudders identified in table 1 of this AD: Within 8 months after the effective date of this AD, perform a vacuum loss inspection in the “area 1” location defined in Airbus Mandatory Service Bulletin A310-55-2049 or A300-55-6048, both dated March 16, 2010, as applicable, to detect defects, including de-bonding.

(2) For rudders identified in table 2 of this AD: Within 24 months after the effective date of this AD, perform a vacuum loss inspection in the “area 1” location defined in Airbus Mandatory Service Bulletin A310-55-2049 or A300-55-6048, both dated March 16, 2010, as applicable, to detect defects, including de-bonding.

(3) Within 24 months after the effective date of this AD: Do an elasticity laminate checker inspection to detect defects, including de-bonding, in the trailing edge location.

(4) Repeat the inspection required by paragraph (g)(3) of this AD two times at intervals not to exceed 4,500 flight cycles, but not fewer than 4,000 flight cycles from the most recent inspection.

(h) For rudders identified in table 3 of this AD: Do the actions specified in paragraphs (h)(1) and (h)(2) of this AD at the time specified. Do the actions in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-55-2049 (for Model A310 series airplanes) or A300-55-6048 (for Model A300-600 series airplanes), both dated March 16, 2010.

(1) Within 4,500 flight cycles after the effective date of this AD, but not fewer than 4,000 flight cycles from the most recent elasticity laminate checker inspection: Do an elasticity laminate checker inspection to detect defects, including de-bonding, in the trailing edge location.

(2) Repeat the inspection required by paragraph (h)(1) of this AD one time within 4,500 flight cycles, but not fewer than 4,000 flight cycles from the last inspection.

(i) If any defect is found during any inspection required by paragraphs (g) and (h) of this AD, before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or the European Aviation Safety Agency (EASA) (or its delegated agent).

(j) If no defect is found during the inspections required by paragraphs (g)(1) and (g)(2) of this AD, before further flight, restore the vacuum loss holes with the temporary restoration with self adhesive tape, temporary restoration with resin, or permanent restoration with resin and surface protection. Do the applicable actions specified in paragraph (j)(1) or (j)(2) of this AD.

(1) For airplanes on which a temporary restoration with self-adhesive disks or tapes is done, within 4 months after doing the restoration, do a detailed inspection for loose or missing self-adhesive disks or tapes and repeat the inspection thereafter at intervals not to exceed 4 months until the permanent restoration is done, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-55-2049 (for Model A310 series airplanes) or A300-55-6048 (for Model A300-600 series airplanes), both dated March 16, 2010. If any loose or missing self-adhesive disks or tapes are found during any inspection required by this AD, before further flight, close the holes, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-55-2049 or A300-55-6048, both dated March 16, 2010, as applicable. Do the permanent restoration within 4,500 flight cycles after doing the temporary restoration, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-55-2049 or A300-55-6048, both dated March 16, 2010, as applicable.

(2) For airplanes on which a temporary restoration with resin is done: Within 4,500 flight cycles after doing the temporary restoration do the permanent restoration, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-55-2049 (for Model A310 series airplanes) or A300-55-6048 (for Model A300-600 series airplanes), both dated March 16, 2010.

At the applicable time specified in paragraph (k)(1) or (k)(2) of this AD: Report the results of each inspection required by paragraphs (g) and (h) of this AD, including no findings, to Airbus, as specified in Airbus Mandatory Service Bulletin A310-55-2049 (for Model A310 series airplanes) or A300-55-6048 (for Model A300-600 series airplanes), both dated March 16, 2010.

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

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

For rudders identified in table 4 of this AD: Within 8 months after the effective date of this AD, replace the affected rudder with a serviceable unit, in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or the EASA (or its delegated agent).

As of the effective date of this AD, no person may install any rudder identified in table 1, 2, or 3 of this AD on any airplane, unless the rudder has been inspected and all applicable corrective actions have been done in accordance with paragraphs (g), (h), and (i) of this AD, as applicable.

(n) As of the effective date of this AD, no person may install any rudder identified in table 4 of this AD on any airplane.

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