AD 2005-20-37 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, -135KE, -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, -135KE, -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. Part Number Verification (f) Within 600 flight hours or 180 days after the effective date of this AD, whichever occurs first, inspect the left and right MLG to determine whether cardan assembly part number (P/N) 2309-2041-003 is installed. A review of airplane maintenance records is acceptable in lieu of this inspection if the P/N of the cardan assembly can be conclusively determined from that review. If cardan P/N 2309-2041-003 is not installed in the MLG, no further action is required for that MLG, except as provided by paragraph (j) of this AD. If cardan P/N 2309-2041-003 is installed in the MLG, continue with paragraph (g) of this AD. Inspection (g) Within 600 flight hours or 180 days after the effective date of this AD, whichever occurs first, perform a detailed inspection for surface bruising of the MLG trailing arms and integrity of the MLG pivot axle sealant; in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 145-32-0091, Change 01, dated July 1, 2004. If no sign of sealant failure or bruising of the trailing arm is found, repeat the inspection thereafter at intervals not to exceed 5,500 flight hours or 24 months, whichever occurs first, until paragraph (h) of this AD has been accomplished. 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 mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” Corrective/Terminating Actions (h) If any sign of sealant failure or bruising of either trailing arm surface is found during any inspection required by paragraph (g) of this AD, prior to further flight, do paragraphs (h)(1), (h)(2), and (h)(3) of this AD. Do the actions in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 145-32-0091, Change 01, dated July 1, 2004. Accomplishment of paragraph (h) of this AD for any MLG ends the repetitive inspections required by paragraph (g) for that MLG. (1) Repair any bruising of the trailing arm surface. (2) Replace the MLG cardan with a new, improved cardan having P/N 2309-2041-401. (3) Perform a detailed inspection for corrosion of the internal surface of the trailing arm pivot axle. (i) If no corrosion is found, prior to further flight, apply protective paint and corrosion inhibitors. (ii) If corrosion is found, prior to further flight, replace the pivot axle with a new pivot axle and apply corrosion inhibitors. Note 2: EMBRAER Service Bulletin 145-32-0091, Change 01, dated July 1, 2004, refers to Embraer Liebherr Equipamentos do Brasil S.A. (ELEB) Service Bulletin 2309-2002-32-04, Revision 01, dated May 24, 2004, as an additional source of service information for the inspection and repair of the MLG components. The ELEB service bulletin is included within the EMBRAER service bulletin. Actions Accomplished According to Previous Issue of Service Bulletin (i) Actions accomplished before the effective date of this AD according to EMBRAER Service Bulletin 145-32-0091, dated February 19, 2004, are considered acceptable for compliance with the corresponding actions specified in this AD. Parts Installation (j) As of the effective date of this AD, no person may install an MLG having a cardan assembly, part number 2309-2041-003, on any affected airplane, unless the requirements of paragraphs (g) and (h) of this AD, as applicable, have been accomplished. Alternative Methods of Compliance (AMOCs) (k)(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 (l) Brazilian airworthiness directive 2004-08-02, dated September 3, 2004, also addresses the subject of this AD. Material Incorporated by Reference (m) You must use EMBRAER Service Bulletin 145-32-0091, Change 01, dated July 1, 2004, 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 Empresa Brasileira de Aeronautica S.A. (EMBRAER), PO 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 September 28, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-20066 Filed 10-11-05; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by a report of a fractured axle of the trailing arm of the main landing gear (MLG) due to corrosion of the axle. We are issuing this AD to prevent a broken trailing arm and consequent failure of the MLG, which could lead to loss of control and damage to the airplane during takeoff or landing.