AD 2006-15-14 Airworthiness Directives; Eurocopter Canada Limited Model BO 105 LS A-3 Helicopters

Models named: BO 105 LS A-3. Read the applicability below — it usually turns on serial or part numbers too.

Model BO 105 LS A-3 helicopters certificated in any category.

Required as indicated, unless accomplished previously. To prevent fatigue failure of a fixed bolt and main rotor nut, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 30 days: (1) Modify the Airworthiness Limitation section, Time Change Items (TCI) list, or table of life-limited components, with their revised life limits by adding part number (P/N) 105-142241.01 and by changing P/N LN 9038 K08018 to P/N 105-101021.17, as shown in the following table.   Part name P/N Life limit Fixed Bolt (Bolt) 105-101021.17 (Formerly P/N LN 9038-K08018) 6,000 hours time-in-service (TIS). Main Rotor Nut (Nut) 105-142241.01 122,850 flights or 18,900 hours TIS, whichever occurs first. The number of flights equals the number of landings (i.e., ground contacts). (2) Create a historical or equivalent record for each of the parts listed in the preceding table. (3) Review the aircraft records and determine the TIS and landings on each nut, P/N 105-142241.01. If the number of flights ( i.e. , landings) is unknown, the initial life limit is 18,900 hours TIS. Thereafter, record the number of flights for use when determining the retirement life. (b) Before further flight, replace any nut that has less than 150 hours TIS remaining before reaching its life limit. Unless accomplished previously, prior to replacing a nut, re-identify the nut in accordance with paragraph (c)(2) of this AD. (c) Within 150 hours TIS: (1) Replace the 4 bolts, P/N LN 9038 K08018, with bolts, P/N 105-101021.17, as shown in Figure 1 of Eurocopter Alert Service Bulletin No. ASB BO 105 LS 10-11, dated May 11, 2005 (ASB). (2) For those nuts with 150 or more hours TIS remaining on their life, remove and re-identify those nuts, P/N 105-142241.01, by adding the serial number of the main rotor head, followed by a dash and a consecutive number, in accordance with the procedures stated in Figure 2 of the ASB. (d) Before further flight, remove any life-limited part on which the life limit has been equaled or exceeded. (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, Regulations and Policy Group, Rotorcraft Directorate, FAA, ATTN: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-5961, for information about previously approved alternative methods of compliance. (f) The replacements shall be done in accordance with the specified portion of Eurocopter Alert Service Bulletin No. ASB BO 105 LS 10-11, dated May 11, 2005. 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 American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected 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 . (g) This amendment becomes effective on August 31, 2006. Note: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF-2005-17, dated June 6, 2005. Issued in Fort Worth, Texas, on July 18, 2006. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E6-11909 Filed 7-26-06; 8:45 am] BILLING CODE 4910-13-P