AD 2010-16-13

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 with a honeycomb core density of 24 kg/m 3, as identified in Table 1 of this AD, do the actions required in paragraphs (g)(1) through (g)(10) of this AD, in accordance with Airbus All Operators Telex (AOT) A310-55A2048 or A300-55A6047, both Revision 02, both dated October 12, 2009, as applicable.

Note 1: Verification of the airplane serial numbers is not required.

(1) In the reinforced location: Within 8 months or 840 flight hours after the effective date of this AD, whichever occurs later, do a vacuum loss inspection to detect defects including de-bonding.

(2) In the trailing edge location: Within 24 months or 840 flight hours after the effective date of this AD, whichever occurs later, do an elasticity laminate checker inspection to detect defects including de-bonding.

(3) Repeat the inspection required by paragraph (g)(2) of this AD two times at intervals not to exceed 4,500 flight cycles, but not fewer than 4,000 flight cycles from the last inspection.

(4) In other locations (lower rib/upper edge/leading edge/other locations): Within 8 months or 840 flight hours after the effective date of this AD, whichever occurs later, do an elasticity laminate checker inspection to detect defects including de-bonding.

(5) Repeat the inspection required by paragraph (g)(4) of this AD at intervals not to exceed 8 months from the last inspection.

(6) Within 24 months or 840 flight hours after the effective date of this AD, whichever occurs later, do a vacuum loss inspection on the other locations (lower rib/upper edge/leading edge/other locations) to detect defects including de-bonding.

(7) Accomplishment of the inspection required by paragraph (g)(6) of this AD terminates the initial and repetitive inspections required by paragraphs (g)(4) and (g)(5) of this AD.

(8) If any defect is found during any inspection required by paragraph (g)(1), (g)(2), (g)(4), or (g)(6) of this AD, before further flight, contact Airbus for repair instructions and do the repair.

(9) If no defects are found during any inspection required by paragraphs (g)(1) and (g)(6) of this AD, before further flight, restore the vacuum loss holes with temporary restoration with self-adhesive patches, temporary restoration with resin, or permanent restoration with resin and surface protection, and repeat the inspection required by paragraph (g)(3) of this AD at intervals not to exceed 4,500 flight cycles until permanent restoration is completed.

(10) If any defect is found during any inspection required by paragraphs (g)(1), (g)(2), (g)(4), and (g)(6) of this AD, at the applicable time specified in paragraph (g)(10)(i) or (g)(10)(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.

(h) For rudders not having a honeycomb core density of 24 kg/m 3, as identified in Table 1 of this AD, do the actions required in paragraphs (h)(1) through (h)(10) of this AD, in accordance with Airbus AOT A310-55A2048 or AOT A300-55A6047, both Revision 02, both dated October 12, 2009, as applicable.

Note 2: Verification of the airplane serial numbers is not required.

(1) In the reinforced location: Within 8 months after the rudder has accumulated 13,000 flight cycles since first installation, or within 8 months after the effective date of this AD, or within 840 flight hours after the effective date of this AD; whichever occurs latest, do a vacuum loss inspection to detect defects including de-bonding.

(2) In the trailing edge location: Within 24 months after the rudder has accumulated 13,000 flight cycles since first installation, or within 24 months after the effective date of this AD, or within 840 flight hours after the effective date of this AD, whichever occurs latest, do an elasticity laminate checker inspection to detect defects including de-bonding.

(3) Repeat the inspection required by paragraph (h)(2) of this AD two times at intervals not to exceed 4,500 flight cycles, but not fewer than 4,000 flight cycles from the last inspection.

(4) In other locations (lower rib/upper edge/leading edge/other locations): Within 8 months after the rudder has accumulated 13,000 flight cycles since first installation, or within 8 months after the effective date of this AD, or within 840 flight hours after the effective date of this AD, whichever occurs latest; do an elasticity laminate checker inspection to detect defects including de-bonding.

(5) Repeat the inspection required by paragraph (h)(4) of this AD at intervals not to exceed 8 months from the last inspection.

(6) Within 24 months after the rudder has accumulated 13,000 flight cycles since first installation, or within 24 months after the effective date of this AD, or within 840 flight hours after the effective date of this AD, whichever occurs latest, do a vacuum loss inspection on the other locations (lower rib/upper edge/leading edge/other location) to detect defects including de-bonding.

(7) Accomplishment of the inspection required by paragraph (h)(6) of this AD terminates the initial and repetitive inspections required by paragraphs (h)(4) and (h)(5) of this AD.

(8) If any defect is found during any inspection required by paragraph (h)(1), (h)(2), (h)(4), or (h)(6) of this AD, before further flight, contact Airbus for repair instructions and do the repair.

(9) If no defects are found during the inspections required by paragraphs (h)(1) and (h)(6) of this AD, before further flight, restore the vacuum loss holes with the temporary restoration with self adhesive patches, temporary restoration with resin, or permanent restoration with resin and surface protection, and repeat the inspection required by paragraph (h)(3) of this AD at intervals not to exceed 4,500 flight cycles until permanent restoration is completed.

(10) If any defect is found during any inspection required by paragraphs (h)(1), (h)(2), (h)(4), and (h)(6) of this AD, at the applicable time specified in paragraph (h)(10)(i) or (h)(10)(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.

(i) Actions done before the effective date of this AD, in accordance with the service information listed in Table 2 of this AD, are acceptable for compliance with the requirements of paragraphs (g) and (h) of this AD for the areas inspected, for any rudder listed in Table 1 of this AD.

(j) Additional areas requiring inspection for all airplanes are defined in Airbus AOT A310-55A2048 or AOT A300-55A6047, both Revision 02, both dated October 12, 2009, as applicable. For these additional areas, do the actions required in paragraphs (g) and (h) of this AD, as applicable, at the times specified in those paragraphs. For all areas, do the repetitive inspections required by paragraphs (g) and (h) of this AD as applicable at the times specified in those paragraphs.

(k) For rudders on which temporary restoration with resin or permanent vacuum loss hole restoration has been done in accordance with the applicable service bulletin specified in Table 2 of this AD, as required in paragraph (g)(9) or (h)(9) of this AD, before the effective date of this AD: Within 4,500 flight cycles from the restoration date, do an ultrasonic inspection for defects, including debonding of the reinforced area, in accordance with Airbus AOT A310-55A2048 or AOT A300-55A6047, both Revision 02, both dated October 12, 2009, as applicable. If any defect is found, before further flight, contact Airbus for repair instructions and do the repair.

(l) After the effective date of this AD, no person may install any rudder listed 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 (h) of this AD.

Note 3: This AD differs from the MCAI and/or service information as follows: No differences.