AD 2006-18-06 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes

Models named: A318, A319, A320, A321. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category; having a manufacturer serial number as identified in Airbus All Operators Telex (AOT) A320-54A1015, dated December 14, 2005 (referred to after this paragraph as “the AOT”).

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Revise Limitations (f) Within 10 days after the effective date of this AD, revise the Limitations section of the Airbus A318/319/320/321 Airplane Flight Manual (AFM) to include the following statement. This may be done by inserting a copy of this AD into the AFM. “In case of flight in severe turbulence, strictly adhere to reduced speeds as defined in Aircraft Flight Manual 4.03.00 P 03.” Note 1: When a statement identical to that specified in paragraph (f) of this AD has been included in the general revisions of the AFM, and the general revisions have been inserted into the AFM, the copy of this AD may be removed from the Limitations section of the AFM unless it has already been removed as specified in paragraph (g) or (h) of this AD. Hardness Test (g) Within the compliance time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable: Perform a one-time hardness test to determine the hardness of ribs 8 and 9 of the left- and right-hand engine pylons, in accordance with the instructions of the AOT. If no discrepant rib is found installed on the airplane, the statement specified in paragraph (f) of this AD may be removed from the Limitations section of the AFM. (1) For airplanes equipped with CFM engines: Within 6 months after the effective date of this AD. (2) For airplanes equipped with IAE engines: Within 9 months after the effective date of this AD. Note 2: The AOT refers to Airbus Repair Instruction 546 12081, Issue B, dated January 3, 2006, as an additional source of service information for accomplishing the actions specified by the AOT. Corrective Actions (h) For any discrepant rib found during the hardness test specified by paragraph (g) of this AD: Within the compliance time specified in paragraph (h)(1) or (h)(2) of this AD, as applicable, perform applicable corrective actions in accordance with the instructions of the AOT. When corrective actions have been applied to all discrepant ribs found on the airplane, the statement specified in paragraph (f) of this AD may be removed from the Limitations section of the AFM for that airplane. (1) For airplanes equipped with CFM engines: Within 14 days after accomplishing the hardness test required by paragraph (g) of this AD. (2) For airplanes equipped with IAE engines: Within 28 days after accomplishing the hardness test required by paragraph (g) of this AD. No Reporting Requirement (i) Although the AOT referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (k) European Aviation Safety Agency airworthiness directive 2006-0136, dated May 22, 2006, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus All Operators Telex A320-54A1015, dated December 14, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the 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 23, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-14623 Filed 9-5-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report that certain stainless steel ribs installed in the engine pylon may not have been heat-treated during manufacture, which could result in significantly reduced structural integrity of the pylon. We are issuing this AD to detect and correct reduced structural integrity of the engine pylon, which could lead to separation of the engine from the airplane.