AD 2001-17-16 Airworthiness Directives; Agusta S.p.A. Model A109E Helicopters

Models named: A109E. Read the applicability below — it usually turns on serial or part numbers too.

Model A109E helicopters, with tail rotor blade (blade), part number (P/N) 109-8132-01-107 or -109, 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 (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To prevent failure of a blade and subsequent loss of control of the helicopter, accomplish the following: (a) Before each start of the engines, visually check both sides of each blade for a crack in accordance with Figure 1 of this AD for blade, P/N 109-8132-01-107, or Figure 2 of this AD for blade, P/N 109-8132-01-109. An owner/operator (pilot), holding at least a private pilot certificate, may perform the visual check required by this paragraph and must record compliance with paragraph (a) of this AD in the aircraft maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). ER29AU01.000 ER29AU01.001 (b) Within 10 hours time-in-service (TIS), and thereafter at intervals not to exceed 10 hours TIS or before the next flight after any abnormal tail rotor vibration, inspect each blade for a crack using a 5-power or higher magnifying glass in accordance with the Compliance Instructions, Part II, of Agusta Bollettino Tecnico No. 109EP-14, Revision A, dated March 19, 2001 (ABT). (c) Within 25 hours TIS and thereafter at intervals not to exceed 25 hours TIS, dye-penetrant inspect each blade for a crack in accordance with the Compliance Instructions, Part III, of the ABT. (d) If a crack is found, replace the blade with an airworthy blade before further flight. (e) 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, 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, 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. (f) Special flight permits are prohibited. (g) The inspections shall be done in accordance with the Compliance Instructions, Parts II and III, of Agusta Alert Bollettino Tecnico No. 109EP-14, Revision A, dated March 19, 2001. 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) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (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. (h) This amendment becomes effective on September 13, 2001. Note 3: The subject of this AD is addressed in Ente Nazionale per l'Aviazione Civile (Italy) AD No. 2001-094, dated March 22, 2001. Issued in Fort Worth, Texas, on August 14, 2001. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 01-21219 Filed 8-28-01; 8:45 am] BILLING CODE 4910-13-P