2009-13-04: Engine controls

2009-13-04 Dornier Luftfahrt GmbH: Amendment 39-15943; Docket No. FAA-2009-0261; Directorate Identifier 2009-CE-017-AD. Effective Date (a) This airworthiness directive (AD) becomes effective July 24, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Models Dornier 228-100, Dornier 228-101, Dornier 228-200, Dornier 228-201, Dornier 228-202, and Dornier 228- 212 airplanes, all serial numbers, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 76: Engine Controls. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Excessive wear on a guide pin of a power lever has been detected during inspections. The total loss of the pin could cause loss of the flight idle stop and lead to inadvertent activation of the beta mode in flight. The inadvertent activation of beta mode in flight can result in loss of control of the airplane. For the reasons described above, thisnew EASA Airworthiness Directive (AD) introduces a repetitive detailed inspection of the guide pins of the power and condition levers and requires the replacement of the pins that exceed the allowable wear-limits. Actions and Compliance (f) Do the following actions per the instructions in RUAG Aerospace Defence Technology Dornier 228 Alert Service Bulletin ASB- 228-279, dated December 19, 2008: (1) Initial Inspection: Unless already done within the last 1,200 hours time-in-service (TIS) as of July 24, 2009 (the effective date of this AD), inspect upon accumulating 9,600 hours on the guide pins of the power and condition levers or within the next 100 hours TIS after July 24, 2009 (the effective date of this AD), whichever occurs later. (2) Repetitive Inspections: Inspect within 1,200 hours since the last inspection required by paragraph (f)(1) of this AD and thereafter at intervals not to exceed 1,200 hours TIS. (3) Replacement: Replace the guide pins as follows: (i) Before further flight, after any inspection required in paragraphs (f)(1) or (f)(2) of this AD, where any guide pin exceeds the acceptable wear-limits as defined in the service bulletin; and (ii) Prior to any required inspection, you may install new power and condition levers guide pins instead of doing the inspections required in this AD. You must then inspect or install new pins upon accumulating 9,600 hours TIS and follow the repetitive inspection intervals of this AD if replacement is not made. Note 1: If the hours TIS of the throttle box assembly is unknown, you may use the hours TIS of the airplane to determine the compliance time for the inspection. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; fax: (816) 329-4090. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, 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 and has assigned OMB Control Number 2120-0056. Related Information (h) Refer to MCAI EASA AD No.: 2009-0031, dated February 18, 2009; and RUAG Aerospace Defence Technology Dornier 228 Alert Service Bulletin ASB-228-279, dated December 19, 2008, for related information. Material Incorporated by Reference (i) You must use RUAG Aerospace Defence Technology Dornier 228 Alert Service Bulletin ASB-228-279, dated December 19, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact RUAG Aerospace Services GmbH, Dornier 228 Customer Support, P.O. Box 1253, 82231 Wessling, Federal Republic of Germany, telephone: +49 (0) 8153-30-2280; fax: +49 (0) 8153-30-3030; E-mail: custsupport.dorner228@ruag.com; Internet: http://www.ruag.com/. (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329-3768. (4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http:// www.archives.gov/federal_register/code_of_federal_regulations/ ibr_locations.html.