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96-18-15 BELL HELICOPTER TEXTRON, A DIVISION OF TEXTRON CANADA LTD.: Amendment 39-9740. Docket No. 96-SW-08-AD. Supersedes AD 96-01-08, issued December 21, 1995, Docket No. 95-SW-33-AD, which supersedes Priority Letter 95-23-02. \n\n\tApplicability: Model 222 helicopters, serial numbers (S/N) 47006 through 47089, and Model 222B helicopters, S/N 47131 through 47156, with tail rotor blades, part numbers (P/N) 222-016-001-101, -107, -111, -113, -115, and -119; Model 222U helicopters, S/N 47501 through 47574, with tail rotor blades, P/N 222-016-001-107, -111, and -115; and Model 230 helicopters, S/N 23001 through 23038, with tail rotor blades, P/N 222-016-001-111 and -115, installed, certificated in any category. \n\n\tNOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (g) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. \n\n\tCompliance: Required before further flight, unless accomplished previously. \n\n\tTo prevent failure of a tail rotor blade (blade) due to a fatigue crack (see Figure 1), loss of the tail rotor and tail rotor gear box, and subsequent loss of control of the helicopter, accomplish the following: \n\n\t(a)\tClean the painted surfaces of the blades in an area approximately 6 inches spanwise on either side of the doubler tip. Visually check both surfaces of each blade for cracks by pushing the blade tip away from the surface being checked until it contacts the flapping stop and then holding the blade firmly against the stop. Pay particular attention to the area reaching from the doubler tip to 1 inch outboard, centering on an area 2 inches aft of the blade leading edge (see Figure 2). \n\n\t(b)\tThe visual check required by paragraph (a) may be performed by an owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with paragraph (a) of this AD in accordance with sections 43.11 and 91.417(a)(2)(v) of the Federal Aviation Regulations (14 CFR sections 43.11 and 91.417(a)(2)(v)). \n\n\t(c)\tIf the visual check described in paragraph (a) reveals any crack outboard of the doubler tip (Station 14.250), or any chordwise crack inboard of the doubler tip that is longer than 1 inch (see Figure 3), accomplish the following: \n\n\t\t(1)\tRemove the paint from the skin in the cracked area using the following procedures (see Figure 4): \n\n\tNOTE 2: Paint cracking that follows the contour of the doubler is common and requires no action. \n\n\t\t(2)\tUsing a 180 or 220 grit abrasion paper, sand by hand with spanwise strokes until greenish- or yellow-colored primer or bare metal begins to be exposed. \n\n\t\t(3)\tUsing spanwise or circular sanding motions, continue hand-sanding the remaining greenish- or yellow-colored primer in the cracked area using a 320 or 400 grit paper until sufficient metal has been exposed to allow inspection (see area indicated in Figure 4). \n\n\t(d)\tInspect the blade skin for cracks in the area that was exposed in accordance with paragraph (c) using a 10-power or higher magnifying glass. \n\n\t\t(1)\tIf no crack is found in the blade skin, coat the bare metal area with a light-weight oil or an equivalent corrosion preventive compound. \n\n\t\t(2)\tIf any crack is discovered, remove the blade and replace it with an airworthy blade. \n\n\t(e)\tPerform the requirements of this AD upon installation of a replacement blade. \n\n\t(f)\tPerform the visual checks of paragraph (a) of this AD and the subsequent inspections, if appropriate, at intervals not to exceed 3 hours TIS. \n\n\tNOTE 3: A light-weight oil or equivalent corrosion preventive compound may be applied after accomplishing the repetitive requirements of paragraph (f) of this AD. \n\n\t(g)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Rotorcraft Certification Office, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. \n\n\tNOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD,if any, may be obtained from the Rotorcraft Certification Office. \n\n\t(h)\tSpecial flight permits to accomplish the requirements of this AD will not be issued. \n\n\t(i)\tThis amendment becomes effective on September 23, 1996.
