AD 2010-16-13 Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F airplanes (Collectively Called A300-600 series airplanes); and A310 Series Airplanes

Models named: A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, C4-605R Variant F, A310-203. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes; certificated in any category; equipped with carbon fiber reinforced plastic rudders having part numbers and serial numbers listed in Table 1 of this AD. Table 1—Rudder Information Rudder part No. Affected rudder Serial No. Core density 24kg/m 3 A554-71500-016-91 HF-1017 Yes. A554-71500-016-91 HF-1020 No. A554-71500-016-91 HF-1059 No. A554-71500-016-91 HF-1061 No. A554-71500-016-91 HF-1064 No. A554-71500-014-00 HF-1087 Yes. A554-71500-014-00 HF-1119 Yes. A554-71500-016-00 HF-1189 Yes. A554-71500-016-00 HF-1203 Yes. A554-71500-016-00 HF-1266 Yes. A554-71500-026-00 TS-1405 No. A554-71710-000-00 TS-2001 No. A554-71710-000-00 TS-2004 No. A554-71710-000-00 TS-2007 No. A554-71710-000-00 TS-2009 No. A554-71710-000-00 TS-2011 No. A554-71710-000-00 TS-2012 No. A554-71710-000-00 TS-2013 No. A554-71710-000-00 TS-2014 No. A554-71710-000-00 TS-2016 No. A554-71710-000-00 TS-2017 No. A554-71710-000-00 TS-2018 No. A554-71710-000-00 TS-2020 No. A554-71710-000-00 TS-2021 No. A554-71710-000-00 TS-2022 No. A554-71710-000-00 TS-2024 No. A554-71710-000-00 TS-2025 No. A554-71710-000-00 TS-2026 No. A554-71710-000-00 TS-2028 No. A554-71710-000-00 TS-2029 No. A554-71710-002-00 TS-2031 No. A554-71710-002-00 TS-2032 No. A554-71710-002-00 TS-2035 No. A554-71710-002-00 TS-2040 No. A554-71710-002-00 TS-2041 No. A554-71710-002-00 TS-2044 No. A554-71710-002-00 TS-2046 No. A554-71710-004-00 TS-2050 No. A554-71710-004-00 TS-2056 No. A554-71710-004-00 TS-2058 No. A554-71710-004-00 TS-2060 No. A554-71710-004-00 TS-2062 No. A554-71710-004-00 TS-2065 No. A554-71710-004-00 TS-2066 No. A554-71710-004-00 TS-2074 No. A554-71710-004-00 TS-2075 No. A554-71710-004-00 TS-2076 No. A554-71710-004-00 TS-2079 No.

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. Table 2—Credit Service Information Airbus AOT— Revision— Dated— A300-55A6047 Original May 11, 2009. A300-55A6047 01 July 8, 2009. A310-55A2048 Original May 11, 2009. A310-55A2048 01 July 8, 2009. (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. FAA AD Differences Note 3: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (m) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. Related Information (n) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2010-0002, dated January 5, 2010; Airbus AOT A310-55A2048, Revision 02, dated October 12, 2009; and Airbus AOT A300-55A6047, Revision 02, dated October 12, 2009; for related information. Material Incorporated by Reference (o) You must use Airbus All Operators Telex A300-55A6047, Revision 02, dated October 12, 2009; or Airbus All Operators Telex A310-55A2048, Revision 02, dated October 12, 2009; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (The document number, revision level, and date appear only on page 1 of the AOTs; no other page of these documents contains this information) (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet: http://www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on July 28, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-19327 Filed 8-12-10; 8:45 am] BILLING CODE 4910-13-P