AD 2008-16-04 Airworthiness Directives; Bell Helicopter Textron Canada (BHTC) Model 222, 222B, and 222U Helicopters

Models named: 222B, S/N 47131 through 47156, Model 222U, all S/N. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the Model 222, serial numbers (S/N) 47006 through 47089; Model 222B, S/N 47131 through 47156, and Model 222U, all S/N, helicopters, certificated in any category. Reason (d) The mandatory continuing airworthiness information (MCAI) states: “It has been determined that the existing rigging procedures for the tail rotor pitch change mechanism have to be changed due to possibility of parts interference.” This “possibility of parts interference” occurs because the cumulative effect of the tolerances on the various parts may result in the total assemblage outboard of the counterweight bellcrank being out of tolerance and the tail rotor yoke may contact the nut, part number (P/N) 222-012-731-001, before contacting the flapping stop. Further, the manufacturer has indicated that the tail rotor counterweight bellcranks may be misaligned, resulting in higher tail rotor pedal forces and higher pilot workload after failure of the #1 hydraulic system. Both the parts interference and the higher pedal forces constitute unsafe conditions. This AD requires actions that are intended to address these unsafe conditions.

Within the next 150 hours time-in-service (TIS) or at the next annual inspection, whichever occurs first, unless already done, do the following actions: (1) Adjust the rigging of the tail rotor pitch change mechanism in accordance with the Accomplishment Instructions, paragraphs 1 and 2, of the applicable Bell Helicopter Textron Alert Service Bulletin (ASB) listed in the following Table 1: Table 1 Helicopter model Applicable ASB No. & date 222 and 222B No. 222-07-104, dated January 9, 2007. 222U No. 222U-07-75, dated January 9, 2007. (2) If either at full left pedal position or full right pedal position a gap exists between the tail rotor yoke and the flapping stop, replace the tail rotor yoke with an airworthy tail rotor yoke. (3) If no gap exists between the tail rotor yoke and the flapping stop at either full left pedal position or full right pedal position, measure the gap between the tail rotor yoke and nut, P/N 222-012-731-001, adjust the tail rotor pitch change mechanism, and adjust the tail rotor pedal forces in accordance with the Accomplishment Instructions, paragraphs 4 through 6, of the applicable ASB listed in Table 1 of this AD. Differences Between This AD and the MCAI (f) This AD requires compliance within the next 150 hours TIS or at the next annual inspection, whichever occurs first, instead of “at the next 150 hour or annual inspection but no later than 31 December 2007.” Other Information (g) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, FAA, ATTN: Tyrone Millard, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 76193-0111, telephone (817) 222-5439, fax (817) 222-5961 has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (h) MCAI Transport Canada Airworthiness Directive No. CF-2007-07, dated April 11, 2007, contains related information. Air Transport Association of America (ATA) Tracking Code (i) Air Transport Association of America (ATA) Code JASC 6720: Tail Rotor Control System, Tail Rotor Pitch Change. Material Incorporated by Reference (j) You must use the specified portions of Bell Helicopter Textron ASB No. 222-07-104 or No. 222U-07-75, both dated January 9, 2007, to do the actions required. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272. (3) You may review copies at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Fort Worth, Texas 76193; 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/cfr/ibr-locations.html. Issued in Fort Worth, Texas, on July 18, 2008. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8-17991 Filed 8-8-08; 8:45 am] BILLING CODE 4910-13-P

Within the next 150 hours time-in-service (TIS) or at the next annual inspection, whichever occurs first, unless already done, do the following actions: (1) Adjust the rigging of the tail rotor pitch change mechanism in accordance with the Accomplishment Instructions, paragraphs 1 and 2, of the applicable Bell Helicopter Textron Alert Service Bulletin (ASB) listed in the following Table 1: Table 1 Helicopter model Applicable ASB No. & date 222 and 222B No. 222-07-104, dated January 9, 2007. 222U No. 222U-07-75, dated January 9, 2007. (2) If either at full left pedal position or full right pedal position a gap exists between the tail rotor yoke and the flapping stop, replace the tail rotor yoke with an airworthy tail rotor yoke. (3) If no gap exists between the tail rotor yoke and the flapping stop at either full left pedal position or full right pedal position, measure the gap between the tail rotor yoke and nut, P/N 222-012-731-001, adjust the tail rotor pitch change mechanism, and adjust the tail rotor pedal forces in accordance with the Accomplishment Instructions, paragraphs 4 through 6, of the applicable ASB listed in Table 1 of this AD. Differences Between This AD and the MCAI (f) This AD requires compliance within the next 150 hours TIS or at the next annual inspection, whichever occurs first, instead of “at the next 150 hour or annual inspection but no later than 31 December 2007.” Other Information (g) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, FAA, ATTN: Tyrone Millard, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 76193-0111, telephone (817) 222-5439, fax (817) 222-5961 has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (h) MCAI Transport Canada Airworthiness Directive No. CF-2007-07, dated April 11, 2007, contains related information. Air Transport Association of America (ATA) Tracking Code (i) Air Transport Association of America (ATA) Code JASC 6720: Tail Rotor Control System, Tail Rotor Pitch Change. Material Incorporated by Reference (j) You must use the specified portions of Bell Helicopter Textron ASB No. 222-07-104 or No. 222U-07-75, both dated January 9, 2007, to do the actions required. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272. (3) You may review copies at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Fort Worth, Texas 76193; 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/cfr/ibr-locations.html. Issued in Fort Worth, Texas, on July 18, 2008. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8-17991 Filed 8-8-08; 8:45 am] BILLING CODE 4910-13-P