AD 2005-25-04 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ, -135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes

Models named: EMB-135BJ, -135ER, -35KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all EMBRAER Model EMB-135BJ, -135ER, -35KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP 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. Records Review (f) Within 5 days after the effective date of this AD: Review the airplane maintenance records to determine whether any vibration from the tail section or rudder pedals was reported within 120 flight hours or 100 flight cycles before the effective date of this AD. Inspection (g) At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD: Do a detailed inspection of the skin, attachment fittings, and control rods of rudder II to detect cracks, loose parts, wear, or damage. Inspect in accordance with the Accomplishment Instructions of EMBRAER Alert Service Bulletin 145LEG-55-A010, dated August 26, 2005 (for Model EMB-135BJ airplanes); or 145-55-A036, Revision 01, dated September 5, 2005 (for all other airplanes). Do all related investigative/corrective actions before further flight by doing all applicable actions specified in the service bulletin; except as required by paragraph (i) of this AD. Repeat the inspection at intervals not to exceed 2,500 flight hours, except as required by paragraph (h) of this AD. (1) If any vibration was reported during the time period specified in paragraph (f) of this AD, inspect within 2 days after the records review. (2) If no vibration was reported during the time period specified in paragraph (f) of this AD, except as required by paragraph (h) of this AD, inspect before the later of: (i) 2,500 total accumulated flight hours. (ii) 600 flight hours or 500 flight cycles, whichever occurs first, after the effective date of this AD. 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 a mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” (h) If any vibration from the tail section or rudder pedals is reported after the effective date of this AD, do the inspection specified in paragraph (g) of this AD before the next flight. Repeat the inspection thereafter at intervals not to exceed 2,500 flight hours. Note 2: EMBRAER Alert Service Bulletin 145LEG-55-A010, dated August 26, 2005, and 145-55-A036, Revision 01, dated September 5, 2005; refer to EMBRAER Service Bulletins 145LEG-55-0008, Revision 01, dated January 14, 2005, 145LEG-55-0009, dated June 21, 2004, and 145-55-0034, Revision 01, dated January 14, 2005, as additional sources of service information for installing washers in the rudder II hinge fittings and control rod assembly. Exceptions to Service Bulletin Specifications (i) Where EMBRAER Alert Service Bulletins 145LEG-55-A010 and 145-55-A036 specify to contact EMBRAER for repair instructions, operators must perform the repair before further flight using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Departmento de Aviacao Civil (or its delegated agent). (j) Although EMBRAER Alert Service Bulletins 145LEG-55-A010 and 145-55-A036 recommend sending a report of the inspection results to the manufacturer, this AD does not require a report. Credit for Prior Accomplishment of Earlier Service Bulletin (k) For Model -135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes: Accomplishment of the inspection and applicable related investigative/corrective actions before the effective date of this AD, in accordance with EMBRAER Alert Service Bulletin 145-55-A036, dated August 20, 2005, is acceptable for compliance with the corresponding requirements of this AD. Alternative Methods of Compliance (AMOCs) (l)(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 (m) Brazilian emergency airworthiness directive 2005-09-02R1, dated November 3, 2005, also addresses the subject of this AD. Material Incorporated by Reference (n) You must use EMBRAER Alert Service Bulletin 145LEG-55-A010, dated August 26, 2005; or EMBRAER Alert Service Bulletin 145-55-A036, Revision 01, dated September 5, 2005; as applicable, 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 these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil, 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 November 2, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-23656 Filed 12-7-05; 8:45 am] BILLING CODE 4910-13-U

This AD results from reports of rudder vibration due to wear. We are issuing this AD to prevent failure of multiple hinge fittings, which could result in severe vibration, and to prevent failure of the rudder control rods, which could result in jamming of the rudder II; and possible structural failure and reduced controllability of the airplane.