AD 2005-19-02 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-110P1 and EMB-110P2 Airplanes

Models named: EMB-110P1, EMB-110P2. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all EMBRAER Model EMB-110P1 and EMB-110P2 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. Service Bulletin Reference (f) The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of EMBRAER Service Bulletin 110-32-0088, Revision 03, dated February 11, 2004. Inspections and Related Investigative/Corrective Actions (g) Within 150 flight hours or 4 months after the effective date of this AD, whichever is first: Perform the evaluation inspection for corrosion or cracking of the NLG rotating cylinder assembly, by doing all the actions in accordance with Part II, paragraph 2.3.1.1., “Evaluation Inspection,” of the service bulletin. Depending on the results of the inspections, perform the applicable action specified in paragraph (g)(1), (g)(2), (g)(3), or (g)(4) of this AD. (1) If no corrosion or cracking is found: Perform the bench detailed inspection of the rotating cylinder assembly required by paragraph (h) of this AD at the time specified in paragraph (h) of this AD. (2) If only light corrosion is found: Repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 150 flight hours or 4 months, whichever occurs first, until the requirements specified in paragraph (h) or (i) of this AD are accomplished. (3) If severe corrosion is found: Before further flight, perform the bench detailed inspection of the rotating cylinder assembly required by paragraph (h) of this AD for evidence of further corrosion or cracking. Note 1: The criteria for determining light or severe corrosion are included in EMBRAER Service Bulletin 110-32-0088, Revision 03, dated February 11, 2004. The presence of oxidation is not considered to be corrosion. (4) If any cracking is found, before further flight: Replace the rotating cylinder assembly with a new part, in accordance with Part II of the service bulletin. Replacing the rotating cylinder assembly terminates the requirements of paragraphs (h) and (i) of this AD. Bench Inspections, Protection Procedures, and Corrective Actions (h) Within 600 flight hours or 12 months after the effective date of this AD, whichever occurs first: Perform the bench detailed inspection for corrosion or cracking of the NLG rotating cylinder assembly in accordance with Part II of the service bulletin. (1) If no corrosion or cracking is found during any inspection, before further flight: Perform all of the actions specified in Part II, paragraph 2.3.1.3., “Protection Procedure,” of the service bulletin. (2) If only light corrosion is found during any inspection, before further flight: Perform all of the actions specified in Part II, paragraph 2.3.1.3., “Protection Procedure,” of the service bulletin. Thereafter, repeat the inspection required by paragraph (g) of this AD at intervals not to exceed 600 flight hours or 9 months, whichever occurs first, until accomplishing paragraph (i) of this AD. (3) If any cracking or severe corrosion is found during any inspection, before further flight: Replace the rotating cylinder assembly with a new part in accordance with Part II of the service bulletin. Replacing the rotating cylinder assembly terminates the inspections required by paragraphs (g)(2) and (h)(2) of this AD. Replacement (i) If any NLG rotating cylinder assembly is found to have light corrosion during any inspection required by paragraph (g)(2) or (h)(2) of this AD, as applicable: Within 3,000 flight hours or 36 months after the effective date of this AD, whichever occurs first, replace the NLG rotating cylinder assembly with a new part, in accordance with Part II of the service bulletin. Replacing the rotating cylinder assembly terminates the inspections required by paragraphs (g)(2) and (h)(2) of this AD. Actions Accomplished Previously (j) Actions accomplished before the effective date of this AD in accordance with EMBRAER Service Bulletin 110-32-0088, Revision 01, dated September 1, 2003; or EMBRAER Service Bulletin 110-32-0088, Revision 02, dated October 30, 2003; are acceptable for compliance with the corresponding requirements of this AD. Reporting Not Required (k) Where the service bulletin states to report inspection results to EMBRAER, that action is not required by this AD. Alternative Methods of Compliance (AMOCs) (l) The Manager, International Branch, ANM-116, Transport Airplane Directorate, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (m) Brazilian airworthiness directive 2004-04-01R1, effective July 27, 2004, also addresses the subject of this AD. Material Incorporated by Reference (n) Unless otherwise specified in this AD, the actions must be done in accordance EMBRAER Service Bulletin 110-32-0088, Revision 03, dated February 11, 2004, which contains the following list of effective pages:   Page No. Revision level shown on page Date shown on page 1-8 03 February 11, 2004. 2-7, 9 01 September 1, 2003. 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), 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 September 6, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-18057 Filed 9-13-05; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of corrosion on the rotating cylinder assembly in the nose landing gear (NLG). We are issuing this AD to prevent cracks from emanating from corrosion pits in the NLG rotating cylinder assembly, which could result in failure of the NLG.