AD 2003-26-04 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 a main rotor head damper, part number (P/N) 109-0111-06-103, with a rod-end assembly, P/N 3637GR85, with a rod-end, P/N 3637-14, installed, certificated in any category.

Required as indicated, unless accomplished previously. To prevent failure of the rod-end, extreme vibrations, and a subsequent forced landing or loss of control of the helicopter, accomplish the following: (a) Within 25 hours time-in-service (TIS), inspect by hand the rod-end, P/N 3637-14, for freedom of movement around the spherical bearing, P/N 3637-40. (1) If the rod-end can be rotated by hand, no further action is required by this AD. (2) If the rod-end cannot be rotated by hand, by using a torque wrench, determine the torque required to rotate the rod-end around the spherical bearing by following the Compliance Instructions, Part I, paragraph 3.1, of Agusta Bollettino Tecnico No. 109EP-37, Revision A, dated July 30, 2003, as amended by the Errata Corrige, dated September 2, 2003 (BT). (i) If the torque value is 20 or more Newton-meter (Nm) (177 in-lb), replace the rod-end assembly with an airworthy rod-end assembly containing a rod-end, P/N 3637-14, with the letters “T”, “R”, “RT”, “TR”, or “TRR” after the P/N, by following the Compliance Instructions, paragraphs 3.3.1. through 3.3.3., of the BT, except you are not required to return the removed rod-end assembly to Agusta. (ii) If the torque value is less than 20 Nm, within the next 25 hours TIS, magnetic particle inspect the rod-end for a crack by following the Compliance Instructions, Part II, of the BT. (A) If no crack is found, no further action is required by this AD. (B) If a crack is found, replace the rod-end assembly with an airworthy rod-end assembly containing a rod-end, P/N 3637-14 with the letters “T”, “R”, “RT”, “TR”, or “TRR” after the P/N, by following the Compliance Instructions, paragraphs 3.3.1. through 3.3.3., of the BT, except you are not required to return the removed rod-end assembly to Agusta. (b) 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. (c) The inspections and replacement of the rod-end assembly must be done using Agusta Bollettino Tecnico No. 109EP-37, Revision A, dated July 30, 2003, as amended by the Errata Corrige, dated September 2, 2003. 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. (d) This amendment becomes effective on January 15, 2004. Note: The subject of this AD is addressed in Ente Nazionale per l'Aviazione Civile (Italy) AD Nos. 2003-231, dated July 18, 2003, and 2003-249, dated August 1, 2003. Issued in Fort Worth, Texas, on December 15, 2003. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 03-31849 Filed 12-30-03; 8:45 am] BILLING CODE 4910-13-P