2005-26-17: Elevators

2005-26-17 Airbus: Amendment 39-14438. Docket No. FAA-2005-21611; Directorate Identifier 2004-NM-234-AD. Effective Date (a) This AD becomes effective February 3, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, C4-605R Variant F, F4-605R, and F4-622R airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes; certificated in any category; equipped with carbon fiber elevators having part number (P/N) A55276055000 (left- hand side) or P/N A55276056000 (right-hand side), installed under Airbus Modification 04805. Unsafe Condition (d) This AD results from reports of debonded skins on the elevators. The FAA is issuing this AD to detect and correct debonding of the skins on the elevators, which could cause reduced structural integrity of an elevator and reduced controllability of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection for Serial Number, Repetitive Inspections, and Corrective Actions (f) Within 600 flight hours after the effective date of this AD, inspect to determine if the serial number (S/N) of the elevator is listed in Airbus All Operators Telex (AOT) A300-600-55A6032, dated June 23, 2004 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4- 622R, C4-605R Variant F, F4-605R, and F4-622R airplanes); or in Airbus AOT A310-55A2033, dated June 23, 2004 (for Model A310-203, - 204, -221, -222, -304, -322, -324, and -325 airplanes). (1) If the S/N does not match any S/N on either AOT S/N list, no further action is required by this paragraph. (2) If the S/N matches a S/N listed in an AOT, before further flight, do the actions listed in Table 1 of this AD, and any corrective action as applicable, in accordance with Airbus AOT A300- 600-55A6032,dated June 23, 2004; or Airbus AOT A310-55A2033, dated June 23, 2004; as applicable. Repeat the inspections at intervals not to exceed 600 flight hours. Do applicable corrective actions before further flight. Table 1.--Repetitive Inspections Do a Of the For any Detailed inspection Elevator upper and lower external skin surfaces Damage (i.e., breaks in the graphite fiber reinforced plastic (GFRP)/Tedlar film protection, debonded GFRP/Tedlar film protection, bulges, torn-out plies). Visual inspection with a low-angle light. Elevator upper and lower external skin surfaces Differences in the surface reflection. Tap-test inspection Upper and lower external skin surfaces of the honeycomb core panels in the elevator. Honeycomb core that has debonded from the carbon fiber reinforced plastic (CFRP). Note 1: For the purposes of this AD, a detailed inspection is "an intensive examination of a specific item, installation, or assembly to detect damage, failure,or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required." Repair Approval (g) Where the AOT says to contact the manufacturer for repair instructions, or an alternative inspection method: Before further flight, repair or do the alternative inspection method according to a method approved by either the Manager, International Branch, ANM- 116, FAA, Transport Airplane Directorate; or the Direction G n rale de l'Aviation Civile (DGAC) (or its delegated agent). Parts Installation (h) As of the effective date of this AD, no carbon fiber elevator having part number (P/N) A55276055000 (left-hand side) or P/N A55276056000 (right-hand side) may be installed on any airplane unless it is inspected according to paragraph (f) of this AD. No Reporting Required (i) Although the AOTs referenced in this AD specify to submit inspection reports to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM-116, 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 14 CFR 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) French airworthiness directive F-2004-131, dated August 4, 2004, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus All Operators Telex A300-600-55A6032, dated June 23, 2004; or Airbus All Operators Telex A310-55A2033, dated June 23, 2004; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. (The document number and date are only included on the first page of these documents.) The Director of the Federal Register approved the incorporation by reference of these documents 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.