AD 2003-12-13 Airworthiness Directives; Agusta S.p.A. Model A109K2 Helicopters

Models named: A109K2. Read the applicability below — it usually turns on serial or part numbers too.

Model A109K2 helicopters with tail rotor blades (blades), part number (P/N) 109-8132-01-107, having 1,500 or more hours time-in-service (TIS), installed, certificated in any category.

Required as indicated, unless accomplished previously. To detect a fatigue crack on the blades, which could result in loss of the blades and loss of control of the helicopter, accomplish the following: (a) Before each start of the helicopter engines, visually check the upper and lower surfaces of each blade for a crack in the area depicted in Figure 1 of this AD. An owner/operator (pilot) holding at least a private pilot certificate may perform this check, but must enter compliance with this paragraph into the aircraft records in accordance with 14 CFR sections 43.11 and 91.417(a)(2)(v). See Figure 1: ER26JN03.000 Note 1: Paint irregularities on the blade may be due to a crack. (b) Before the first flight of each day, and thereafter at intervals not to exceed 5 hours TIS, and anytime an increase in vibration levels occurs, inspect each blade for a crack using a 5x or higher magnifying glass in accordance with Part II of the Compliance Instructions of Alert Bollettino Tecnico No. 109K-35, dated May 13, 2003 (ABT) and Figure 1 of this AD. (c) After each visual inspection using a 5x or higher magnifying glass and before further flight, if you are unable to determine by the visual inspection whether there is a crack, inspect each blade for a crack using a dye-penetrant method in accordance with Part II of the Compliance Instructions of the ABT and Figure 1 of this AD. (d) If a crack is found, replace each cracked blade with an airworthy blade before further flight. (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. (f) Special flight permits will not be issued. (g) The inspections and replacements, if necessary, shall be done in accordance with Agusta Alert Bollettino Tecnico No. 109K-35, dated May 13, 2003, except reporting findings of cracks to Agusta Service Engineering is not required. 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 July 11, 2003. Note 2: The subject of this AD is addressed in Ente Nazionale per l'Aviazione Civile (Italy) AD N.2003-169, dated May 16, 2003. Issued in Fort Worth, Texas, on June 11, 2003. Jerald E. Strentz, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 03-15447 Filed 6-25-03; 8:45 am] BILLING CODE 4910-13-U