AD 2002-25-51 Airworthiness Directives; Agusta S.p.A. Model A109E Helicopters

Required as indicated, unless accomplished previously. To prevent fatigue failure of the T/R blade and subsequent loss of control of the helicopter, accomplish the following: Applicability A (a) Before further flight, placard the helicopter and mark the airspeed indicator to reduce the helicopter never-exceed speed (Vne) by 28 KIAS in addition to any reduction in Vne caused by optional equipment installation, in accordance with the Compliance Instructions, Part I, paragraph 1 of Agusta Alert Bollettino Tecnico 109EP-30, Revision B, dated November 27, 2002 (ABT). (b) Before each start of the helicopter engines, visually check both sides of each tail rotor 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 visual check and must enter compliance with this paragraph into the aircraft maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). See Figure 1: ER28FE03.000 (c) Within 5 hours time-in-service (TIS), and thereafter at intervals not to exceed 5 hours TIS, and before further flight any time there is an increase in vibration levels: (1) Using a 5x or higher magnifying glass, visually inspect each T/R blade for a crack in accordance with the Compliance Instructions, Part III, paragraphs 1. through 5., of the ABT. Reporting to Agusta Service Engineering is not required. (2) If you are unable to determine by the visual inspection whether there is a crack, dye-penetrant inspect the T/R blade for a crack in accordance with the Compliance Instructions, Part III, paragraph 6., of the ABT. (d) Before further flight, replace any unairworthy T/R blade with an airworthy blade. (e) This AD establishes a new life limit on the T/R blade, P/N 109-8132-01-111, of 200 hours TIS. (f) Within 10 hours TIS, for helicopters having T/R blades with 190 hours TIS or more, replace the T/R blades with airworthy blades. (g) On or before May 31, 2003, modify the T/R hub and grip assembly in accordance with the Compliance Instructions, Part V, of the ABT. Neither returning the removed blades nor the grips and bushings to the manufacturer is required. Modifying the T/R hub and grip assembly removes the Vne restrictions imposed, restores the T/R blades' life limit to 1,000 hours TIS, and changes the AD requirements for the helicopter from Applicability A to Applicability B. Applicability B (h) Before each start of the helicopter engines, visually check both sides of each tail rotor 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 visual check and must enter compliance with this paragraph into the aircraft maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). See Figure 1. (i) Within 25 hours TIS, and thereafter at intervals not to exceed 25 hours TIS, and before further flight any time there is an increase in vibration levels: (1) Using a 5x or higher magnifying glass, visually inspect each T/R blade for a crack in accordance with the Compliance Instructions, Part III, paragraphs 1. through 5. of the ABT. Reporting to Agusta Service Engineering is not required. (2) If you are unable to determine by the visual inspection whether there is a crack, dye-penetrant inspect the T/R blade for a crack in accordance with the Compliance Instructions, Part III, paragraph 6., of the ABT. (j) Before further flight, replace any unairworthy T/R blade with an airworthy blade. (k) On or before accumulating 150 hours TIS on the T/R hub and grip assembly, P/N 109-8131-02-159, and thereafter at intervals not to exceed 150 hours TIS, inspect the bushings', P/N 109-8131-30-109, linings for wear in accordance with Part VI of the ABT. Replace any unairworthy bushing with an airworthy bushing. (l) This AD revises the helicopter Airworthiness Limitations section of the maintenance manual by establishing a new retirement life for the T/R blade of 200 hours TIS and, after modifying the T/R hub and grip assembly, restores the retirement life to 1,000 hours TIS. (m) T/R blades, P/N 109-8132-01-111, which have been operated as part of the T/R hub and blade assembly, P/N 109-8131-02-151, are considered unairworthy components of the T/R hub and blade assembly, P/N 109-8131-02-157, regardless of TIS. (n) 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. 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. (o) Special flight permits will not be issued. (p) The placarding and marking the airspeed indicator, inspecting the T/R blade and bushing, and modifying the T/R hub and grip assembly shall be done in accordance with the Compliance Instructions in Agusta Alert Bollettino Tecnico 109EP-30, Revision B, dated November 27, 2002. 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. (q) This amendment becomes effective on March 17, 2003, to all persons except those persons to whom it was made immediately effective by Emergency AD 2002-25-51, issued December 17, 2002, which contained the requirements of this amendment. Note 2: The subject of this AD is addressed in Ente Nazionale per l'Aviazione Civile, Italy, AD No. 2002-592, dated November 28, 2002. Issued in Fort Worth, Texas, on February 14, 2003. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 03-4478 Filed 2-27-03; 8:45 am] BILLING CODE 4910-13-P