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2005-03-10 Bell Helicopter Textron, a Division of Textron Canada: Amendment 39-13966. Docket No. 2003-SW-23-AD. Supersedes AD 2002-08- 54, Amendment 39-12835, Docket No. 2002-SW-22-AD. \n\n\tApplicability: The following model helicopters with the listed part number (P/N) installed, certificated in any category: \n\n\nModel \nWith hub assembly P/N \nWith grip assembly P/N \nWith pitch horn assembly P/N \n\n\n\n\n(1) 222 or 222B \n222-011-101-103,-105,-107, or -109 \n222-012-101-103, or -107 \n222-010-104-105 \n222-012-104-101 \n222-011-104-101 \n222-012-102-101 \n\n\n\n\n(2) 222U \n222-011-101-105, -107, or -109 \n222-012-101-103, or -107 \n222-010-104-105 \n222-012-104-101 \n222-011-104-101 \n222-012-102-101 \n(3) 230 \n222-012-101-105, or -109 \n222-012-104-101 \n222-012-102-101 \n\n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent failure of the grip or pitch horn and subsequent loss of control of the helicopter, if either the grip or pitch horn has accumulated 1,250 or more hours time-in-service (TIS) since initial installation on any helicopter, accomplish the following: \n\n\t(a) Before further flight and thereafter at intervals not to exceed 8 hours TIS: \n\n\t(1) Wipe clean the main rotor grip and pitch horn surfaces to remove grease and dirt in the check area as shown in Figure 1 of this AD: \n\n\n\n\n\t(2) Visually check both main rotor grips for a crack. Pay particular attention to the inboard and outboard tangs portions of the grip, which are in direct contact with the pitch horns and the main rotor blades and check the area to at least 3 inches beyond the grip to pitch and grip to blade contact areas as shown in Figure 2 of this AD: \n\n\n\n\n\n\n\t\n\t(3) Visually check all visible portions of each pitch horn for a crack. Pay particular attention to the attachment lugs of the pitch horns, which are in direct contact with the inboard tangs of the main rotor grips, as shown in Figure 3 of this AD, and the four large bolt cutouts, as shown in Figure 4 of this AD: \n\n\n\n\n\n\n\n\n\n\n\t(4) An owner/operator (pilot) holding at least a private pilot certificate may perform the visual check required by paragraph (a) of this AD. The pilot must enter compliance with this paragraph into the helicopter records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v)). \n\n\t(b) Within 7 days or 10 hours TIS, whichever occurs first, and thereafter at intervals not to exceed 25 hours TIS, without disassembling the main rotor hub assembly (hub assembly) and using a 10-power or higher magnifying glass, inspect each grip and pitch horn assembly for a crack in accordance with paragraphs (a)(1), (a)(2), and (a)(3) of this AD. \n\n\t(c) Within 300 hours TIS or 6 months, whichever occurs first, for each hub assembly with 2,500 or more and less than 4,500 hours TIS, and within 2,500 hours TIS for each hub assembly with less than 2,500 hours TIS: \n\n\t(1) Disassemble and clean the main rotor hub assembly. \n\n\t(2) Inspect the grip and pitch horn assembly using a fluorescent-penetrant inspection method. \n\n\t(3) Inspect the pitch horn-to-grip attachment bolts and the flapping bearing-to-yoke attachment bolts using a magnetic-particle inspection method. If any of these attachment bolts are made from non-magnetic material, inspect those attachment bolts using a fluorescent-penetrant inspection method. \n\n\t(4) During reassembly, install new buffers on the pitch horn and flapping bearing assemblies. \n\n\t(d) If a crack is found, replace the cracked part with an airworthy part before further flight. \n\n\tNote 1: Bell Helicopter Textron Alert Service Bulletin No. 222- 02-93, Revision A, No. 222U-02-64, Revision A, and 230-02-26, Revision A, all dated March 3, 2003, pertain to the subject of this AD. \n\n\t(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 Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. \n\n\t(f) This amendment becomes effective on March 18, 2005. \n\n\tNote 2: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF-2002-23R1, dated May 7, 2003.
