99-26-13: Blade Crack Inspection

99-26-13 AGUSTA S.p.A.: Amendment 39-11472. Docket No. 99-SW-64-AD. Supersedes Priority Letter AD 87-03-14 R2, Amendment 39-5742, Docket No. 87-ASW-2. Issued December 9, 1999. Applicability: Model A109A and A109A II helicopters, with tail rotor blade (blade), part number (P/N) 109-0132-02-all dash numbers, with 400 or more hours time-in-service (TIS), installed, certificated in any category. NOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise 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 request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on theunsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue failure of a blade, loss of the tail rotor, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, dye-penetrant inspect each blade for a crack in accordance with the Compliance Instructions, Part I, of Agusta S.p.A. Bollettino Tecnico 109-110, dated July 28, 1999 (technical bulletin). Thereafter, at intervals not to exceed 100 hours TIS, dye-penetrant inspect each blade for a crack in accordance with the Compliance Instructions, Part III, of the technical bulletin. If a crack is found, replace the cracked blade with an airworthy blade before further flight. (b) Before the first flight each day, visually inspect each blade for a crack using a 3 to 5 power magnifying glassin accordance with the Compliance Instructions, Part II, of the technical bulletin. If a crack is found, replace the cracked blade with an unairworthy blade before further flight. (c) An 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, Regulations Group, FAA, Rotorcraft Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Regulations Group. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group. (d) Special flight permits will not be issued. (e) The inspections shall be done in accordance with the Compliance Instructions of Agusta S.p.A. Bollettino Tecnico 109-110, dated July 28, 1999. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Agusta, 21017 Cascina Costa di Samarate (VA), Via Giovanni Agusta 520, telephone (0331) 229111, fax (0331) 229605-222595. 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 Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on January 4, 2000. NOTE 3: The subject of this AD is addressed in Registro Aeronautico Italiano, Italy, AD 99-325, dated August 2, 1999.