AD 2011-19-04 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes

Models named: A318-111, -112, -121, -122, A319-111, -113, -114, -115, -131, -132. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A318-111, -112, -121, and -122 airplanes; Model 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; all manufacturer serial numbers.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009), With Reduced and Revised Compliance Times and Revised Service Information: (g) Unless already done, do the following actions. (1) At the applicable times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD: Inspect both the left-hand and right-hand inboard elevator servo-control rod eye-ends for cracking, in accordance with the instructions of Airbus All Operators Telex (AOT) A320-27A1186, Revision 04, dated April 3, 2009; or the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011. As of the effective date of this AD, use Airbus Mandatory Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011. (i) For airplanes that have accumulated 10,000 total flight cycles or more as of September 22, 2009 (the effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At the later of the times specified in paragraphs (g)(1)(i)(A) and (g)(1)(i)(B) of this AD. (A) Within 1,500 flight cycles after September 22, 2009. (B) Within 1,500 flight cycles after accumulating 10,000 total flight cycles since first flight of the airplane. (ii) For airplanes that have accumulated less than 10,000 total flight cycles as of September 22, 2009: At the later of the times specified in paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD. (A) Before the accumulation of 5,000 total flight cycles. (B) Within 20 months after the effective date of this AD but no later than before the accumulation of 11,500 total flight cycles. (2) At the applicable time specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: Inspect both the left-hand and right-hand outboard elevator servo-control rod eye-ends for cracking, in accordance with the instructions of Airbus AOT A320-27A1186, Revision 04, dated April 3, 2009; or the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011. As of the effective date of this AD, use Airbus Mandatory Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011. (i) For airplanes that have accumulated 10,000 total flight cycles or more as of September 22, 2009: At the later of the times specified in paragraphs (g)(2)(i)(A) and (g)(2)(i)(B) of this AD. (A) Within 3,000 flight cycles after September 22, 2009. (B) Within 3,000 flight cycles after accumulating 10,000 total flight cycles since first flight of the airplane. (ii) For airplanes that have accumulated less than 10,000 total flight cycles as of September 22, 2009: At the later of the times specified in paragraphs (g)(2)(ii)(A) and (g)(2)(ii)(B) of this AD. (A) Before the accumulation of 7,500 total flight cycles. (B) Within 40 months after the effective date of this AD but no later than before the accumulation of 13,000 total flight cycles. New Requirements of This AD: Repetitive Inspections and Corrective Action (h) Repeat the inspections of the left-hand and right-hand inboard and outboard elevator servo-control rod eye-ends for cracking as required by paragraphs (g)(1) and (g)(2) of this AD at the later of the times specified in paragraph (h)(1) or (h)(2) of this AD. Repeat the inspections thereafter at intervals not to exceed 5,000 flight cycles. (1) Within 5,000 flight cycles after the last inspection required by paragraph (g)(1) or (g)(2) of this AD as applicable. (2) Within 6 months after the effective date of this AD. (i) If any cracking is found during any inspection required by this AD, before further flight, accomplish all applicable corrective actions, in accordance with the Accomplishment Instructions and figures of Airbus Mandatory Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011. Parts Installation (j) As of the effective date of this AD, no person may install on any airplane an elevator servo-control rod eye-end unless it is new or has been inspected in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011, with no crack findings. Credit for Actions Accomplished in Accordance With Previous Service Information (k) Actions done before the effective date of this AD in accordance with the service information specified in table 1 of this AD are acceptable for compliance with the corresponding requirements of paragraphs (g)(1) and (g)(2) of this AD. Actions done before the effective date of this AD in accordance with the service information specified in table 2 of this AD are acceptable for compliance with the corresponding requirements of paragraph (h) of this AD. Table 1—Credit Service Information for Paragraph (g) of This AD Airbus AOT— Revision— Dated— A320-27A1186 Original June 23, 2008. A320-27A1186 01 August 11, 2008. A320-27A1186 02 March 30, 2009. A320-27A1186 03 April 1, 2009. A320-27A1186 04 April 3, 2009. Table 2—Credit Service Information for Paragraph (h) of This AD Airbus Service Bulletin— Revision— Dated— A320-27A1186 05 March 10, 2010. A320-27A1186 06 December 14, 2010. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (l) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to Attn: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1405; fax (425) 227-1149. Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov . Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009), are approved as AMOCs for the corresponding provisions of 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. Related Information (m) Refer to MCAI EASA Airworthiness Directive 2010-0046, dated March 19, 2010; and Airbus Mandatory Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011; for related information. Material Incorporated by Reference (n) You must use Airbus Mandatory Service Bulletin A320-27A1186, Revision 07, including Appendices 1, 2, 3, 4, 5, and 6, dated March 2, 2011, to do the actions required by this AD, unless the AD specifies otherwise. (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 September 7, 2011. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011-23468 Filed 9-15-11; 8:45 am] BILLING CODE 4910-13-P