AD 2006-07-13 Airworthiness Directives; Airbus Model A310 Airplanes, Model A300 B4-600 Series Airplanes, Model A300 B4-600R Series Airplanes, Model A300 F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes

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

This AD applies to Airbus Model A310 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes; certificated in any category; equipped with a carbon fiber reinforced plastic (CFRP) rudder having any series of part number (P/N) A55471500; except for those airplanes on which Airbus Modification 8827 has been incorporated in production.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspections and Corrective Actions (f) Within 500 flight cycles or 120 days after the effective date of this AD, whichever occurs first: Do the actions specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD, in accordance with paragraph 4.2.2 of Airbus All Operators Telex (AOT) A310-55A2043 (for Model A310 airplanes) or AOT A300-55A6042 (for Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes), both dated March 2, 2006, as applicable. (1) Do a general visual inspection of the drainage at the lower edge of the rudder spar to determine if the aft edges of the leading edge butt strap at rib 0 are clean. If any aft edge side of the leading edge butt strap at rib 0 is not clean, before further flight, restore the drainage to the correct condition. Note 1: For the purposes of this AD, a general visual inspection is: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.” Note 2: AOT A310-55A2043 refers to Chapter 55-42-11 of the Airbus A310 Structural Repair Manual (SRM) as an additional source of service information for restoring the drainage to the correct condition. AOT A300-55A6042 refers to Chapter 55-42-11 of the Airbus A300-600 SRM as an additional source of service information for restoring the drainage to the correct condition. (2) Do a general visual inspection of the rear spar of the rudder external surfaces below the rudder actuators for the presence of hydraulic fluid. If any hydraulic fluid is found, before further flight, clean the contaminated rudder external surfaces. Note 3: AOT A310-55A2043 refers to Chapter 51-78-20 of the Airbus A310 SRM as an additional source of service information for cleaning hydraulic fluids from the rudder external surfaces. AOT A300-55A6042 refers to Chapter 51-78-20 of the Airbus A300-600 SRM as an additional source of service information for cleaning hydraulic fluids from the rudder external surfaces. (3) Clean the inner surface of the rudder panels and do a manual tap test inspection, or an automatic tap test inspection using Woodpecker tool WP632, at the inner side of the rudder panels for any disbonding in the inspection areas defined in Airbus Technical Disposition 943.0046/06, dated March 2, 2006. If any disbond area is found during a manual tap test inspection, as an option, an automatic tap test inspection using Woodpecker tool WP632 may be accomplished before further flight to verify the finding. If any disbond area crosses the perimeter of any inspection zone defined in Airbus Technical Disposition 943.0046/06, before further flight, repeat the tap test inspection in the applicable area outside of the defined inspection zone to obtain the size of the entire disbond area. (i) If one disbond area per panel with a diameter of less than 130mm is found during the inspection required by paragraph (f)(3) of this AD: Within 6 months, do a temporary or permanent repair of the disbond area using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Chapter 55-41-12 of the Airbus A310 SRM is one approved method for accomplishing the temporary or permanent repair on Model A310 airplanes. Chapter 55-41-12 of the Airbus A300-600 SRM is one approved method for accomplishing the temporary or permanent repair on Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes. If a temporary repair is accomplished, within 1,500 flight cycles after accomplishing the temporary repair, do a permanent repair of the disbond area in accordance with this paragraph. (ii) If one disbond area per panel with a diameter of 130mm or greater, but less than 200mm, is found during the inspection required by paragraph (f)(3) of this AD: Before further flight after the inspection, do a temporary or permanent repair of the disbond area using a method approved by the Manager, International Branch, ANM-116, FAA. Chapter 55-41-12 of the Airbus A310 SRM is one approved method for accomplishing the temporary or permanent repair on Model A310 airplanes. Chapter 55-41-12 of the Airbus A300-600 SRM is one approved method for accomplishing the temporary or permanent repair on Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes. If a temporary repair is accomplished, within 1,500 flight cycles after accomplishing the temporary repair, do a permanent repair of the disbond area in accordance with this paragraph. (iii) If one disbond area per panel with a diameter of 200mm or greater is found during the inspection required by paragraph (f)(3) of this AD: Before further flight after the inspection, repair the disbond area using a method approved by the Manager, International Branch, ANM-116, FAA. (iv) If more than one disbond area of any diameter is found on a single panel during the inspection required by paragraph (f)(3) of this AD: Before further flight, repair the disbond areas using a method approved by the Manager, International Branch, ANM-116, FAA. Reporting Requirement (g) At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, submit a report of all findings (both positive and negative) of the inspection required by paragraph (f)(3) of this AD to M. Xavier Jolivet, Dept. SEE83; fax +33(0) 5 61-93-36-14; e-mail Xavier.Jolivet@airbus.com, and to Thomas Stafford, International Branch, ANM-116, FAA; fax (425) 227-1149; e-mail Thomas.Stafford@faa.gov. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. 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 contained in this AD and has assigned OMB Control Number 2120-0056. (1) If the inspection is accomplished after the effective date of this AD: Submit the report within 10 days after the inspection. (2) If the inspection was accomplished before the effective date of this AD: Submit the report within 10 days after the effective date of this AD. Parts Installation (h) As of the effective date of this AD, no person may install a CFRP rudder, any series of P/N A55471500, on any airplane, unless the CFRP rudder has been inspected and any applicable corrective action has been accomplished in accordance with paragraphs (f)(2) and (f)(3) of this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM-116, 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 (j) The European Aviation Safety Agency's airworthiness directive 2006-0066, dated March 24, 2006, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use Airbus All Operators Telex A310-55A2043, dated March 2, 2006, or Airbus All Operators Telex A300-55A6042, dated March 2, 2006, as applicable; and Airbus Technical Disposition 943.0046/06, dated March 2, 2006; to perform the actions that are required by this AD, unless the AD specifies otherwise. (Only page 1 of Airbus All Operators Telex A310-55A2043 and Airbus All Operators Telex A300-55A6042 contains the document number and date of the document; no other page of the document contains this information.) 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. Issued in Renton, Washington, on March 24, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-3119 Filed 3-28-06; 12:45 pm] BILLING CODE 4910-13-P

This AD results from two separate findings of inner skin disbonding discovered while undergoing unrelated repair and maintenance procedures. We are issuing this AD to detect discrepancies of the rudder, which could result in reduced structural integrity of the rudder.