AD 2011-17-14 Airworthiness Directives; Agusta S.p.A. Model A109A and A109AII Helicopters

Models named: A109A, A109A II. Read the applicability below — it usually turns on serial or part numbers too.

Models A109A and A109A II helicopters, with tail rotor special hub plug (hub plug), part number (P/N) 109-0133-18-103; certificated in any category.

Required within 5 hours time-in-service (TIS) or 8 days, whichever occurs first, unless accomplished previously. To detect an improperly torqued hub plug that could lead to tail rotor failure and subsequent loss of control of the helicopter, accomplish the following: (a) Determine if the tightening torque value of the hub plug is between 600 kgcm and 700 kgcm. (b) If the tightening torque value of the hub plug is between 600 kgcm and 700 kgcm, remove and replace the lock washer, P/N 109-0133-17-103, and the o-ring, P/N MS29561-119, with airworthy parts. (c) If the tightening torque value of the hub plug is greater than 700 kgcm, remove and replace the hub plug, P/N 109-0133-18-103 with an airworthy part. Torque the hub plug to the specified tightening torque between 600 and 700 kgcm. (d) If the tightening torque value of the hub plug is less than the 600 kgcm, do the following: (1) Remove the tail rotor hub and blades assembly, P/N 109-0131-02 (all dash numbers). (2) Inspect the broaching faces (splined area “F”) and bearing faces (area “D”) of the trunnion, P/N 109-0131-05 or 109-8131-33, for spalling, fretting, or wear by reference to Figure 2 of Agusta Mandatory Alert Bollettino Tecnico No. 109-132, dated October 22, 2010 (BT). If there is spalling, fretting, or wear that is outside allowable damage tolerances specified in Figure 2 of the BT, replace the trunnion with an airworthy trunnion. (3) Inspect the hub plug, the spacers, P/N 109-0133-16-103 and 109-0130-89-1, and the static stop, P/N 109-0130-27-5, for spalling, fretting, wear, or corrosion. If there is any spalling, fretting, wear, or corrosion, replace the part with an airworthy part. (4) Inspect the broaching area “H” of the output drive shaft, P/N 109-0445-08-3 or 109-0445-08-7, of the tail rotor gearbox assembly, P/N 109-0440-01, for fretting, wear, or other damage by referring to Figure 3 of the BT. If there is any fretting, wear, or other damage of 0.07 mm or more in depth between loaded and unloaded areas, replace the output drive shaft with an airworthy output drive shaft. (5) Reinstall the tail rotor hub and blade assembly, and tighten the torque on the hub plug to between 600 kgcm and 700 kgcm. (6) Accomplish a flap axis play inspection, a flap hinge friction inspection, and a tail rotor dynamic balance. (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 Manager, Safety Management Group, ATTN: DOT/FAA Southwest Region, Sharon Miles, Rotorcraft Directorate, Regulations and Policy Group, ASW-111, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222-5122; fax: (817) 222-5961, for information about previously approved alternative methods of compliance. (f) The Joint Aircraft System/Component (JASC) Code is 6500: Tail rotor drive system. (g) The inspection shall be done in accordance with the specified portions of Agusta Mandatory Alert Bollettino Tecnico No. 109-132, dated October 22, 2010. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Agusta Westland, Customer Support & Services, Via Per Tornavento 15, 21019 Somma Lombardo (VA) Italy, ATTN: Giovanni Cecchelli; telephone 39-0331-711133; fax 39 0331 711180; or at http://www.agustawestland.com/technical-bullettins . 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 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. (h) This amendment becomes effective on September 12, 2011. Note: The subject of this AD is addressed in the European Aviation Safety Agency (Italy), Emergency AD 2010-0222-E, dated October 22, 2010. Issued in Fort Worth, Texas, on August 8, 2011. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2011-21475 Filed 8-25-11; 8:45 am] BILLING CODE 4910-13-P