AD 2010-23-17 Airworthiness Directives; Various Aircraft Equipped With Rotax Aircraft Engines 912 A Series Engines

Makes named: rotax. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all serial numbers (S/N) of the following aircraft, equipped with a Rotax Aircraft Engines 912 A series engine with a crankcase assembly S/N up to and including S/N 27811, certificated in any category: Type certificate holder Aircraft model Engine model Aeromot-Industria Mecanico Metalurgica ltda AMT-200 912 A2 Diamond Aircraft Industries HK 36 R “SUPER DIMONA” 912 A Diamond Aircraft Industries GmbH HK 36 TS HK 36 TC 912 A3 912 A3 Diamond Aircraft Industries Inc. DA20-A1 912 A3 HOAC-Austria DV 20 KATANA 912 A3 Iniziative Industriali Italiane S.p.A. Sky Arrow 650 TC 912 A2 SCHEIBE-Flugzeugbau GmbH SF 25C 912 A2 or 912 A3

Unless already done, do the following actions: (1) Within the next 50 hours time-in-service (TIS) after December 22, 2010 (the effective date of this AD), inspect the engine crankcase for cracks following Rotax Aircraft Engines Service Bulletin SB-912-029 R3, dated July 11, 2006. Repetitively thereafter do the inspection at each 100-hour, annual, or progressive inspection or within 110 hours TIS since last inspection, whichever occurs first. (2) If cracks in the engine crankcase are found during any inspection required by paragraph (f)(1) of this AD, before further flight, replace the crankcase following Rotax Aircraft Engines Service Bulletin SB-912-029 R3, dated July 11, 2006. (3) Installing a crankcase that has a S/N above 27811 terminates the inspection requirements of paragraph (f)(1) of this AD. Note 1: The service information is a combined service bulletin for both the 912 type (Service Bulletin SB-912-029 R3, dated July 11, 2006) and 914 type (Service Bulletin SB-914-018, Revision 3, dated July 11, 2006) engines. This AD does not reference Service Bulletin SB-914-018, Revision 3, dated July 11, 2006, because this AD does not apply to the 914 series engines. This unsafe condition for the 914 type engines is the subject of AD 2010-20-23. 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: Sarjapur Nagarajan, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4145; fax: (816) 329-4090; e-mail: sarjapur.nagarajan@faa.gov. 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, a federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. Special Flight Permit (h) We are limiting the special flight permits for this AD by the following conditions if the crankcase is cracked or there is evidence of oil leakage from the crankcase: (1) Perform a leak check as follows: (i) Clean the crankcase surface to remove any oil. (ii) Warm up the engine to a minimum oil temperature of 50 degrees C (120 degrees F). Information about warming up the engine can be found in the applicable line maintenance manual. (iii) Accelerate the engine to full throttle and stabilize at full throttle speed for a time period of 5 to 10 seconds. Information about performing a full throttle run can be found in the applicable line maintenance manual. (iv) Shutdown after running the engine at idle only long enough to prevent vapor locks in the cooling system and fuel system. (v) Inspect the crankcase for evidence of oil leakage. Oil wetting is permitted, but oil leakage of more than one drip in 3 minutes after engine shutdown is not allowed. (2) Check the crankcase mean pressure to confirm that it is 1.46 pounds-per-square inch gage (psig) (0.1 bar) or higher when checked at takeoff power to ensure proper return of oil from the crankcase to the oil tank. Information about checking crankcase mean pressure is available in the Lubrication System section of the applicable engine installation manual. (3) A ferry flight is not allowed if oil leakage exceeds one drip in 3 minutes or if crankcase mean pressure is below 1.46 psig. Related Information (i) Refer to MCAI EASA AD No.: 2007-0025, dated February 1, 2007, for related information. Material Incorporated by Reference (j) You must use Rotax Aircraft Engines Service Bulletin SB-912-029 R3, dated July 11, 2006, 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 BRP-Powertrain GMBH & Co KG, Welser Strasse 32, A-4623 Gunskirchen, Austria; phone: (+43) (0) 7246 601-0; fax: (+43) (0) 7246 6370; Internet: http://www.rotax.com. (3) You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-4148. (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. Issued in Kansas City, Missouri, on November 1, 2010. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-27980 Filed 11-16-10; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions: (1) Within the next 50 hours time-in-service (TIS) after December 22, 2010 (the effective date of this AD), inspect the engine crankcase for cracks following Rotax Aircraft Engines Service Bulletin SB-912-029 R3, dated July 11, 2006. Repetitively thereafter do the inspection at each 100-hour, annual, or progressive inspection or within 110 hours TIS since last inspection, whichever occurs first. (2) If cracks in the engine crankcase are found during any inspection required by paragraph (f)(1) of this AD, before further flight, replace the crankcase following Rotax Aircraft Engines Service Bulletin SB-912-029 R3, dated July 11, 2006. (3) Installing a crankcase that has a S/N above 27811 terminates the inspection requirements of paragraph (f)(1) of this AD. Note 1: The service information is a combined service bulletin for both the 912 type (Service Bulletin SB-912-029 R3, dated July 11, 2006) and 914 type (Service Bulletin SB-914-018, Revision 3, dated July 11, 2006) engines. This AD does not reference Service Bulletin SB-914-018, Revision 3, dated July 11, 2006, because this AD does not apply to the 914 series engines. This unsafe condition for the 914 type engines is the subject of AD 2010-20-23. 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: Sarjapur Nagarajan, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4145; fax: (816) 329-4090; e-mail: sarjapur.nagarajan@faa.gov. 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, a federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. Special Flight Permit (h) We are limiting the special flight permits for this AD by the following conditions if the crankcase is cracked or there is evidence of oil leakage from the crankcase: (1) Perform a leak check as follows: (i) Clean the crankcase surface to remove any oil. (ii) Warm up the engine to a minimum oil temperature of 50 degrees C (120 degrees F). Information about warming up the engine can be found in the applicable line maintenance manual. (iii) Accelerate the engine to full throttle and stabilize at full throttle speed for a time period of 5 to 10 seconds. Information about performing a full throttle run can be found in the applicable line maintenance manual. (iv) Shutdown after running the engine at idle only long enough to prevent vapor locks in the cooling system and fuel system. (v) Inspect the crankcase for evidence of oil leakage. Oil wetting is permitted, but oil leakage of more than one drip in 3 minutes after engine shutdown is not allowed. (2) Check the crankcase mean pressure to confirm that it is 1.46 pounds-per-square inch gage (psig) (0.1 bar) or higher when checked at takeoff power to ensure proper return of oil from the crankcase to the oil tank. Information about checking crankcase mean pressure is available in the Lubrication System section of the applicable engine installation manual. (3) A ferry flight is not allowed if oil leakage exceeds one drip in 3 minutes or if crankcase mean pressure is below 1.46 psig. Related Information (i) Refer to MCAI EASA AD No.: 2007-0025, dated February 1, 2007, for related information. Material Incorporated by Reference (j) You must use Rotax Aircraft Engines Service Bulletin SB-912-029 R3, dated July 11, 2006, 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 BRP-Powertrain GMBH & Co KG, Welser Strasse 32, A-4623 Gunskirchen, Austria; phone: (+43) (0) 7246 601-0; fax: (+43) (0) 7246 6370; Internet: http://www.rotax.com. (3) You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-4148. (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. Issued in Kansas City, Missouri, on November 1, 2010. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-27980 Filed 11-16-10; 8:45 am] BILLING CODE 4910-13-P