AD 2007-24-05 Airworthiness Directives; Rolls-Royce Corporation AE 3007A and AE 3007C Series Turbofan Engines

This AD applies to Rolls-Royce Corporation (RRC) (formerly Allison Engine Company, Inc.) AE 3007A and AE 3007C series turbofan engines. These engines are installed on, but not limited to, Cessna Aircraft Company 750 series, and Empresa Brasileira de Aeronautica S. A. (EMBRAER) EMB-135 and EMB-145 series airplanes.

You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Prohibited Flights (f) All flights after ground engine starts at engine oil temperatures below 32 °F (0 °C), are prohibited except as follows: (1) If the engine oil temperature has dropped below 32 °F (0 °C), before flight, perform a high-power leak check on each engine (at least three minutes at takeoff power). (2) Oil consumption greater than 0.32 quart per hour, or 300 cc per hour, is not permitted. Instructions for performing the high-power leak check for the AE 3007A series engines can be found in the Rolls-Royce AE 3007A Series Maintenance Manual, TASK 72-00-00-700-801, SUBTASK 72-00-00-790-002. Leak check limits for the AE 3007A series engines can be found in the Rolls-Royce AE 3007A Series Maintenance Manual, TASK 71-00-00-200-801. (3) Instructions for performing the high-power leak check for the AE 3007C series engines (including leak check limits) can be found in the Rolls-Royce AE 3007C Series Maintenance Manual, TASK 72-00-00-700-801, SUBTASK 72-00-00-790-002. Terminating Action (g) No later than September 30, 2009, as terminating action to the requirements in paragraph (f) through (f)(3) of this AD, do the following, as applicable to your engine configuration: (1) Remove seal and related component, part numbers (P/Ns) 42520-71, 42520-196-X, 99004-1-6, 42520-75, or 42520-167, from the accessory gearbox (AGB) air turbine starter mounting pad. (2) Install a new O-ring, P/N AS3209-026, M83248/1-026 or other serviceable part, to the shaft of the starter mounting pad. (3) Install a new bearing locknut, P/N 42520-170, or other serviceable part, and an AGB air turbine starter mounting pad mechanical seal, P/N 42520-192, or other serviceable part. (4) Use paragraphs 2. through 2.G. of the Accomplishment Instructions of RRC Service Bulletin (SB) No. AE 3007A-72-321/AE 3007C-72-250, Revision 2, dated November 12, 2007, to do the removals and installations. (5) For AE 3007A series engines, remove the drain cap or starter drain adapter. Use paragraphs 2. through 2.C.(4)(c) of the Accomplishment Instructions of RRC SB No. AE 3007A-72-274, Revision 1, dated November 12, 2007 to do the removal. (6) For AE 3007A series engines, install an open starter drain adapter. Use paragraphs 2. through 2.C.(2) of the Accomplishment Instructions of RRC SB No. AE 3007A-72-330, Revision 1, dated November 12, 2007 to do the installation. (7) For AE 3007C series engines, install an open starter drain adapter. Use paragraphs 2. through 2.E.(2) of the Accomplishment Instructions of RRC SB No. AE 3007C-72-223, Revision 1, dated November 12, 2007 to do the installation. Definition (h) A serviceable part is any FAA-approved part not being removed from service, or not otherwise specifically addressed by this AD action. Prohibition of Seals (i) Do not install seal and related component P/Ns 42520-71, 42520-196-X, 99004-1-6, 42520-75, and 42520-167, on the air starter mounting pad after the terminating action in this AD is performed. Previous Credit (j) Previous credit is allowed for the terminating action in paragraphs (g)(1) through (g)(7) of this AD, that was done before the effective date of this AD using the Accomplishment Instructions of the SBs listed in the following Table 1: Table 1.—SBs Allowing Previous Credit   For AE 3007A Series Engines: (1) Engine—Accessory Drive Gearbox Assembly—New Starter Shaft Seal; RRC SB No. AE 3007A-72-321/AE 3007C-72-250, Revision 1, dated November 7, 2005; and (2) Engine—Accessory Gearbox Starter Pad Drain—Remove The Drain Cap or Starter Drain Adapter; RRC SB No. AE 3007A-72-274, dated January 19, 2006; and (3) Engine—Accessory Gearbox Starter Pad Drain—Install the Open Starter Drain Adapter (23083402 or 23077526); RRC SB No. AE 3007A-72-330, dated January 19, 2006. For AE 3007C Series Engines: (4) Engine—Accessory Drive Gearbox Assembly—New Starter Shaft Seal; RRC SB No. AE 3007A-72-321/AE 3007C-72-250, Revision 1, dated November 7, 2005; and (5) Engine—Accessory Gearbox Starter Pad Drain—Install the Open Starter Drain Adapter (23077526 or 23083403); RRC SB No. AE 3007C-72-223, dated January 19, 2006. Alternative Methods of Compliance (AMOC) (k) The Manager, Chicago Aircraft Certification Office, has the authority to approve AMOCs for this AD if requested using the procedures found in 14 CFR 39.19. (l) AMOCs currently approved for AD 99-02-51 will remain in effect until the terminating action date for this AD, September 30, 2009. After that date, these AMOCs will expire and will not be approved as AMOCs for this AD. Related Information (m) Contact Kyri Zaroyiannis, Aerospace Engineer, Chicago Aircraft Certification Office, Small Airplane Directorate, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; e-mail: kyri.zaroyiannis@faa.gov; telephone (847) 294-7836; fax (847) 294-7834, for more information about this AD. Material Incorporated by Reference (n) You must use the service information specified in Table 2 to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Rolls-Royce Corporation, P.O. Box 420, Indianapolis, IN 46206; telephone (317) 230-3774; fax (317) 230-8084; e-mail: indy.pubs.services@rolls-royce.com , for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or 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/cfr/ibr-locations.html . Table 2.—Incorporation by Reference Service Bulletin No. Page Revision Date AE 3007A-72-274 ALL 1 November 12, 2007. Total Pages—6 AE 3007A-72-321, AE 3007C-72-250 ALL 2 November 12, 2007. Total Pages—13 AE 3007A-72-330 ALL 1 November 12, 2007. Total Pages—6 AE 3007C-72-223 ALL 1 November 12, 2007. Total Pages—7 Issued in Burlington, Massachusetts, on November 14, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7-22810 Filed 11-27-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from design improvements to components in the accessory gearbox air turbine starter mounting pad. We are issuing this AD to prevent an in-flight engine shutdown due to loss of engine oil from the starter shaft seal and possible loss of the airplane.