AD 2004-15-22 Airworthiness Directives; Sikorsky Aircraft Corporation Model S-61L, S-61N, S-61-NM, and S-61R Helicopters

Models named: S-61L, S-61N, S-61-NM, S-61R. Read the applicability below — it usually turns on serial or part numbers too.

Model S-61L, S-61N, S-61-NM, and S-61R helicopters, certificated in any category.

Required within 60 days, unless accomplished previously. To detect an impending engine bearing (bearing) failure, which, if undetected and not addressed by appropriate crew action, may result in oil leakage, severing of the shaft housing, an uncontained in-flight fire, and a subsequent emergency landing, accomplish the following: (a) Install an engine chip detector, part number 3049T42P01 or 3018T72P01, in the engine power turbine accessory drive assembly using the Accomplishment Instructions, paragraphs 3.A. and 3.B., in General Electric Aircraft Engines CT58 Service Bulletin Number 72-0195, dated May 1, 2003. (b) Install an on-board engine chip detector annunciation system using Sikorsky Aircraft Corporation Alert Service Bulletin No. 61B30-15, Revision A. dated October 20, 2003 (ASB). For helicopters with a master warning caution panel (MWCP) manufactured by United Controls or Sundstrand Data, install in accordance with paragraph 3.B. of the ASB. For helicopters with a MWCP manufactured by Grimes Mfg., install in accordance with paragraph 3.C. of the ASB. (c) After accomplishing paragraph (b) of this AD, before further flight, perform a functional test of the engine chip detector system and repeat the functional test at intervals not to exceed 150 hours TIS using the Accomplishment Instructions, paragraph 3.D., of the ASB. (d) Insert the emergency procedures for an on-board engine chip detector warning light illumination into the Emergency Procedures section of the applicable Rotorcraft Flight Manual using the Accomplishment Instructions, paragraph 3.E., of the ASB. (e) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Boston Aircraft Certification Office, Engine and Propeller Directorate, FAA, for information about previously approved alternative methods of compliance. (f) The actions, including installations, testing, and inserting information into the Rotorcraft Flight Manual, shall be done in accordance with General Electric Aircraft Engines CT58 Service Bulletin Number 72-0195, dated May 1, 2003; and Sikorsky Aircraft Corporation Alert Service Bulletin No. 61B30-15, Revision A. dated October 20, 2003. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Tech Support, 6900 Main Street, Stratford, Connecticut 06614, phone (203) 386-3001, fax (203) 386-5983; and from GE Aircraft Engines Customer Support Center, M/D 285, 1 Neumann Way, Evendale, OH 45215, telephone (513) 552-3272; fax (513) 552-3329, e-mail GEAE.csc@ae.ge.com. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; 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/code_of_federal_regulations/ibr_locations.html. (g) This amendment becomes effective on September 7, 2004. Issued in Fort Worth, Texas, on July 22, 2004. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-17370 Filed 7-30-04; 8:45 am] BILLING CODE 4910-13-P