2005-04-09: Tail rotor blades

2005-04-09 Bell Helicopter Textron Canada: Amendment 39-13981. Docket No. FAA-2005-20107; Directorate Identifier 2005-SW-02-AD. Supersedes AD 2004-26-11, Amendment 39-13923, Docket No. FAA-2004-19969, Directorate Identifier 2004-SW-43-AD. \n\n\tApplicability: The following helicopter models, identified by serial number, with one of the following part numbered tail rotor blades installed, certificated in any category. \n\n\nModel\nSerial No.\nTail rotor blade (blade) part no.\n222\n47006 through 47089\n222-016-001-123, -127, -131, and -135.\n222B\n47131 through 47156\n222-016-001-123, -127, -131, and -135.\n222U\n47501 through 47574\n222-016-001-123, and -131.\n230\n23001 through 23038\n222-016-001-123, and -131.\n430\n49001 through 49107\n222-016-001-123, and -131.\n\n\tCompliance: Required as indicated. \n\n\tTo detect a crack in the blade and to prevent loss of the blade and subsequent loss of control of the helicopter, accomplish the following: \n\n\t(a) Within 3 hours time-in-service(TIS), and thereafter at intervals not to exceed 3 hours TIS, clean and visually check both sides of each blade for a crack in the paint in the areas shown in Figure 1 of this AD. An owner/operator (pilot), holding at least a private pilot certificate, may perform this visual check and must enter compliance with this paragraph into the helicopter maintenance records by following 14 CFR 43.11 and 91.417(a)(2)(v). \n\nBILLING CODE 4910-13-P \n\n\n\nBILLING CODE 4910-13-C \n\n\tNote 1: Bell Helicopter Textron Alert Service Bulletin (ASB) No. 222-04-100, No. 222U-04-71, and No. 230-04-31, all dated August 27, 2004, and ASB No. 430-04-31, Revision A, dated November 29, 2004, pertain to the subject of this AD. \n\n\t(b) If the visual check required by paragraph (a) reveals a crack in the paint, before further flight, remove the blade and follow the requirements in paragraphs (c)(2) through (c)(3)(ii) of this AD. \n\n\t(c) Within the next 50 hours TIS, unless accomplished previously, and thereafter at intervals not to exceed 50 hours TIS, clean the blade by wiping down both surfaces of each blade in the inspection area depicted in Figure 1 of this AD using aliphatic naphtha (C-305) or detergent (C-318) or an equivalent. Using a 10X or higher power magnifying glass, visually inspect both sides of the blade in the areas depicted in Figure 1 of this AD. \n\n\t(1) If a crack is found, even if only in the paint, before further flight, remove the blade from the helicopter and proceed with the following: \n\n\t(2) Remove the paint on the blade down to the bare metal in the area of the suspected crack by using plastic metal blasting (PMB) or a nylon web abrasive pad. Abrade the blade surface in a span-wise direction only. \n\n\tNote 2: PMB may cause damage to helicopter parts if untrained personnel perform the paint removal. BHT-ALL-SPM, chapter 3, paragraph 3-24, pertains to the subject of this AD. \n\n\t(3) Using a 10X or higher power magnifying glass, inspect the blade for a crack.(i) If a crack is found, replace the blade with an airworthy blade before further flight. \n\n\t(ii) If no crack is found in the blade surface, refinish the blade by applying one coat of epoxy polyamide primer, MIL-P-23377 or MIL-P-85582, so that the primer overlaps the existing coats just beyond the abraded area. Let the area dry for 30 minutes to 1 hour. Then, apply one sealer coat of polyurethane, MILC85285 TYI CL2, color number 27925 (semi-gloss white), per Fed. Std. 595. Reinstall the blade. \n\n\tNote 3: BHT-ALL-SPM, chapter 4, pertains to painting the blade. \n\n\t(d) 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 Safety Management Group, FAA, for information about previously approved alternative methods of compliance. \n\n\t(e) Special flight permits may be issued by following 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished provided you do not find a crack in the blade paint during a check or inspection. \n\n\t(f) This amendment becomes effective March 4, 2005. \n\n\tNote 4: The subject of this AD is addressed in Transport Canada (Canada) Airworthiness Directive CF-2004-21R1, dated December 9, 2004.