AD 2010-18-07 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes

Models named: A318-111, -112, -121, -122, A320-111, -211, -212, -214, -231, -232. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Airbus Model A318-111, -112, -121, and -122 airplanes; A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Actions (g) Within 30 days after the effective date of this AD, inspect the left-hand (LH) and right-hand (RH) elevators to determine if the first twelve digits of the part number on the elevator are identified in Table 1 or Table 2 of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55A1040, dated January 11, 2010; and do the actions required by paragraphs (g)(1) and (g)(2) of this AD, as applicable. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the elevators can be conclusively identified from that review. (1) If any part number is identified in Table 1 of this AD: Within 30 days after the effective date of this AD, do the applicable determination specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD and compare it to the threshold for the next due inspection, as specified in Airbus ALI Task 552007-01-1 or 552007-01-3, which is defined in Airbus A318/A319/A320/A321 ALI AI/SE-M4/95A.0252/96, Issue 09, dated November 2006; or Issue 10, dated October 2009. Table 1—Elevator Part Number Part name First twelve digits of part number only LH Elevator D55280001000. RH Elevator D55280001001. (i) For elevators on which Airbus Service Bulletin A320-55-1024 has been done: If adequate records exist, determine the elapsed (calendar) time since the date of the first flight of the first airplane on which the elevator is installed after the actions in Airbus Service Bulletin A320-55-1024 were done on the elevator. (ii) For elevators on which Airbus Service Bulletin A320-55-1024 has not been done: If adequate records exist, determine the elapsed (calendar) time since the date of the first flight of the first airplane on which the elevator is installed. (2) If any part number is identified in Table 2 of this AD: Within 30 days after the effective date of this AD, if adequate records exist, determine the elapsed (calendar) time since the date of the first flight of the first airplane on which the elevator is installed and compare it to the threshold for the next due inspection, as specified in Airbus ALI Task 552007-01-2 or 552007-01-4, which is defined in Airbus A318/A319/A320/A321 ALI AI/SE-M4/95A.0252/96, Issue 09, dated November 2006; or Issue 10, dated October 2009. Table 2—Elevator Part Number Part name First twelve digits of part number only LH Elevator D55280001002, D55280001004, D55280001008, D55280001010, or D55280001012. RH Elevator D55280001003, D55280001005, D55280001009, D55280001011 or D55280001013. (h) If the elapsed time, determined as required by paragraph (g)(1) of this AD, has exceeded the ALI threshold for the next due inspection, as specified in Airbus ALI Task 552007-01-1 or 552007-01-3; or if unable to determine the elapsed time: Within 30 days after the effective date of this AD, perform a special detailed inspection for damage, including cracking, of the top and bottom skin panels of the affected elevators, in accordance with Airbus ALI Task 552007-01-1 or 552007-01-3, which is defined in Airbus A318/A319/A320/A321 ALI AI/SE-M4/95A.0252/96, Issue 09, dated November 2006; or Issue 10, dated October 2009. If any damage or cracking is found, 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 (EASA) (or its delegated agent). (i) If the elapsed time, determined as required by paragraph (g)(1) of this AD, has not exceeded the ALI threshold for the next due inspection, as specified in Airbus ALI Task 552007-01-1 or 552007-01-3: Before reaching that threshold, or within 30 days after the effective date of this AD, whichever occurs later; perform a special detailed inspection for damage, including cracking, of the top and bottom skin panels of the affected elevators in accordance with Airbus ALI Task 552007-01-1 or 552007-01-3, which is defined in Airbus A318/A319/A320/A321 ALI AI/SE-M4/95A.0252/96, Issue 09, dated November 2006; or Issue 10, dated October 2009. If any damage or cracking is found before further flight repair using a method approved by either the Manager, International Branch, or EASA (or its delegated agent). (j) If the elapsed time, determined as required by paragraph (g)(2) of this AD, has exceeded the ALI threshold for the next due inspection, as specified in Airbus ALI Task 552007-01-2 or 552007-01-4; or if unable to determine the elapsed time: Within 30 days after the effective date of this AD, perform a special detailed inspection for damage, including cracking, of the top and bottom skin panels of the affected elevators, in accordance with Airbus ALI Task 552007-01-2 or 552007-01-4, which is defined in Airbus A318/A319/A320/A321 ALI AI/SE-M4/95A.0252/96, Issue 09, dated November 2006; or Issue 10, dated October 2009. If any damage or cracking is found before further flight, repair using a method approved by either the Manager, International Branch, or the EASA (or its delegated agent). (k) If the elapsed time, determined as required by paragraph (g)(2) of this AD has not exceeded the ALI threshold for the next due inspection, as specified in Airbus ALI Task 552007-01-2 or 552007-01-4: Before reaching that threshold, or within 30 days after the effective date of this AD, whichever occurs later; perform a special detailed inspection for damage, including cracking, of the top and bottom skin panels of the affected elevators, in accordance with Airbus ALI Task 552007-01-2 or 552007-01-4, which is defined in Airbus ALI AI/SE-M4/95A.0252/96, Issue 09, dated November 2006; or Issue 10, dated October 2009. If any damage or cracking is found before further flight, repair using a method approved by either the Manager, International Branch, or EASA (or its delegated agent). (l) Accomplishment of the inspection and corrective actions required by paragraph (h), (i), (j), and (k) of this AD does not constitute terminating action for the repetitive inspections of Airbus ALI Task 552007, as defined in Airbus A318/A319/A320/A321 ALI AI/SE-M4/95A.0252/96, Issue 09 dated November 2006; or Issue 10, dated October 2009. (m) As of the effective date of this AD, no person may install, on any airplane, any elevator having a part number identified in Table 1 or 2 of this AD, unless the actions required by paragraphs (g)(1) and (g)(2), of this AD, as applicable, have been done and the inspections and corrective actions required by paragraphs (h), (i), (j), and (k) of this AD have been done. (n) As of the effective date of this AD, track all interchangeable damage tolerant part movements between airplanes, in accordance with the specific statement in the Section Rules for Compliance Demonstration, either in paragraph F., “Transferable Parts,” of the Airbus A318/A319/A320/A321 ALI AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or in sub-paragraph 10., “Interchangeable parts policy,” of Chapter 1.11, “General Rules,” of Airbus A318/A319/A320/A321 ALI AI/SE-M4/95A.0252/96, Issue 09, dated November 2006; or Issue 10, dated October 2009. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: Although the MCAI or service information specifies to perform corrective actions using the instructions defined in Airbus ALI AI/SE-M4/95A.0252/96, Issue 09, dated November 2006; or Issue 10, dated October 2009; if any affected elevators are found, such corrective actions are not identified in the ALI tasks. Therefore, this AD requires that you perform all corrective actions before further flight using a method approved by either the Manager, International Branch, ANM 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Other FAA AD Provisions (o) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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: Tim Dulin, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2141; 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 (p) Refer to MCAI EASA Airworthiness Directive 2010-0091, dated May 19, 2010; Airbus Service Bulletin A320-55A1040, dated January 11, 2010; and Airbus A318/A319/A320/A321 ALI AI/SE-M4/95A.0252/96, Issue 09, dated November 2006; and Issue 10, dated October 2009; for related information. Material Incorporated by Reference (q) You must use the applicable service information specified in Table 3 of this AD to do the actions required by this AD, unless the AD specifies otherwise. Table 3—Material Incorporated by Reference Document Issue Date Airbus A318/A319/A320/A321 Airworthiness Limitations Items AI/SE-M4/95A.0252/96 09 November 2006. Airbus A318/A319/A320/A321 Airworthiness Limitations Items AI/SE-M4/95A.0252/96 10 October 2009. Airbus Service Bulletin A320-55A1040 Original January 11, 2010. Airbus A318/A319/A320/A321 ALI AI/SE-M4/95A.0252/96, Issue 09, contains the following effective pages:   Page title/description Page number(s) Issue No. Date shown on page(s) List of Effective Pages: ALI Title Page None shown 09 November 2006. Record of Revisions 1-ROR through 3-ROR 9 November 2006. Summary of Changes 1-SOC through 2-SOC 9 November 2006. List of Effective Pages 1-LEP 9 November 2006. Table of Contents 1-TOC 9 November 2006. Section 1—Introduction 1—7 9 November 2006. Section 2—Airworthiness Limitation Items (ALI) 1—61 09 November 2006. Airbus A318/A319/A320/A321 ALI AI/SE-M4/95A.0252/96, Issue 10 contains the following effective pages:   Page title/description Page number(s) Issue No. Date shown on page(s) List of Effective Pages: ALI Title Page None shown 10 October 2009. Record of Revisions 1-ROR through 4-ROR None shown* October 2009. Table of Contents 1-TOC None shown* October 2009. Section 1—Introduction 1-INTRO through 8-INTRO None shown* October 2009. Section 2—Damage Tolerant Airworthiness Limitations List 1—85 None shown* October 2009. Appendix A—Summary of Changes 1-APXA through 9-APXA None shown* October 2009. Appendix B—Abbreviations 1-APXB through 2-APXB None shown* October 2009. Appendix C—Terms and Definitions 1-APXC None shown* October 2009. Appendix D—Reporting Form 1-APXD None shown* October 2009. Appendix E—Modifications List 1-APXE through 2-APXE None shown* October 2009. (*Only the title page of this document contains the issue level of the document.) (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, Airworthiness Office—EAS, 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 August 13, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-21023 Filed 8-24-10; 8:45 am] BILLING CODE 4910-13-P