AD 2000-15-52 Airworthiness Directives; Bell Helicopter Textron, Inc. Model 204B, 205A, 205A-1, 205B, and 212 Helicopters

Models named: 204B, 205A, 205A-1, 205B, 212. Read the applicability below — it usually turns on serial or part numbers too.

Model 204B, 205A, 205A-1, 205B, and 212 helicopters, with main rotor mast (mast), part number (P/N) 204-011-450-001, -007, -105, -113, or -119, or main rotor trunnion (trunnion), P/N 204-011-105-001 or -103, installed, certificated in any category. Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (i) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance Required as indicated, unless accomplished previously. Note 2: This AD has new requirements which must be complied with even if AD's 98-24-15 and 2000-08-52 have already been accomplished. This AD requires the recalculation of accumulated mast and trunnion RIN and increases the RIN factors for masts and trunnions installed on certain helicopter models. This AD also expands the S/N applicability for the one-time special inspection of the mast. To prevent failure of a mast or trunnion, separation of the main rotor system, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, determine the accumulated Retirement Index Number (RIN) in accordance with the Instructions in Appendix 1 of this AD for the mast and Appendix 2 of this AD for the trunnion. If the helicopter model installation history or hours time-in-service (TIS) of the mast or trunnion is unknown, remove the mast or trunnion from service and replace it with an airworthy mast or trunnion. If the mast has been installed on certain military helicopters (BHTI-manufactured Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1C, UH-1D, UH-1E, UH-1F, UH-1G, UH-1H, UH-1L, UH-1M, UH-1N, and UH-1P; and Southwest Florida Aviation SW204, SW204HP, SW205, or SW205A-1) or restricted category helicopters (Firefly Aviation Helicopter Services (previously Erickson Air Crane Co.); Garlick Helicopters, Inc.; Hawkins and Powers Aviation, Inc.; International Helicopters, Inc.; Tamarack Helicopters, Inc. (previously Ranger Helicopter Services, Inc.); Robinson Air Crane, Inc.; Williams Helicopter Corporation (previously Scott Paper Co.); Smith Helicopters; Southern Helicopter, Inc.; Southwest Florida Aviation; Utah State University; Western International Aviation, Inc.; and U.S. Helicopter, Inc.) and you cannot verify that hub springs have not been installed, remove the mast from service and replace it with an airworthy mast. (b) Before further flight, replace any mast, P/N 204-011-450-113 or 119, that has accumulated 240,000 or more RIN with an airworthy mast. Before further flight, replace any mast, P/N 204-011-450-001, -007, or -105, that has accumulated 265,000 or more RIN with an airworthy mast. (c) Before further flight, replace any trunnion, P/N 204-011-105-103, that has accumulated 240,000 or more RIN with an airworthy trunnion. Before further flight, replace any trunnion, P/N 204-011-105-001, that has accumulated 265,000 or more RIN with an airworthy trunnion. (d) Before reaching 100,000 RIN, inspect the upper and lower snap ring grooves in the damper clamp splined area of any mast with serial number (S/N) 00000 through 52720, S/N 61433 through 61444, and S/N 61457 through S/N 61465 (regardless of prefix) for: (1) A minimum radius of 0.020 inches around the entire circumference (see Figures 1 through 3), using a 100x or higher magnification. If any snap ring groove radius is less than 0.020 inches, replace the mast with an airworthy mast prior to exceeding 100,000 RIN. (2) A burr, using a 200x or higher magnification. If a burr is found in any snap ring groove/spline intersection, replace the mast with an airworthy mast prior to exceeding 170,000 RIN. BILLING CODE 4910-13-U ER13DE00.000 ER13DE00.001 ER13DE00.002 (e) Continue to calculate the accumulated RIN for the mast by multiplying all takeoff and external load lifts by the RIN factors defined in columns (D) and (G) of Table 1 of Appendix 1 of this AD. (f) Continue to calculate the accumulated RIN for the trunnion by multiplying all takeoff and external load lifts by the RIN factors defined in columns (D) and (G) of Table 1 of Appendix 2 of this AD. (g) Before further flight, revise the Airworthiness Limitations section of the maintenance manuals for the masts and trunnions in accordance with Figure 4. Mast and Trunnion Life Limits Mast part No. Hours TIS life limit RIN life limit Trunnion part No. Hours TIS life limit RIN life limit 204-011-450-001 6,000 265,000 204-011-105-001 15,000 265,000 204-011-450-007 15,000 265,000 204-011-105-103 13,000 240,000 204-011-450-105 15,000 265,000 204-011-450-113 13,000 240,000 204-011-450-119 13,000 240,000 (h) Within 10 days after completing the inspections required by this AD, provide the information contained on the AD inspection report, sample format, contained in Appendix 3 of this AD and send it to the Manager, Rotorcraft Certification Office, Federal Aviation Administration, Fort Worth, Texas, 76193-0170, USA. Reporting requirements have been approved by the Office of Management and Budget and assigned OMB control number 2120-0056. (i) 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, Rotorcraft Certification Office, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Rotorcraft Certification Office. (j) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished. (k) This amendment becomes effective on December 28, 2000, to all persons except those persons to whom it was made immediately effective by Emergency AD 2000-15-52, issued July 25, 2000, which contained the requirements of this amendment. APPENDIX 1 ER13DE00.003 ER13DE00.004 ER13DE00.005 ER13DE00.006 ER13DE00.007 ER13DE00.008 ER13DE00.009 ER13DE00.010 ER13DE00.011 APPENDIX 2 ER13DE00.012 ER13DE00.013 ER13DE00.014 ER13DE00.015 ER13DE00.016 ER13DE00.017 ER13DE00.018 ER13DE00.019 ER13DE00.020 BILLING CODE 4910-13-U Appendix 3—Ad Compliance Inspection Report P/N 204-011-450-001/-007/-105/-113/-119 Main Rotor Mast Provide the following information and mail or fax it to: Manager, Rotorcraft Certification Office, Federal Aviation Administration, Fort Worth, Texas, 76193-0170, USA Fax: 817-222-5783 Operator Name: Aircraft Registration No: Helicopter Model: Helicopter S/N: Mast P/N: Mast S/N: Mast RIN: Mast Total TIS: Inspection Results Were any radii during inspection of this mast determined to be less than 0.020 inches? If yes, what was the dimension measured? Was a burr found in the inspected snap ring grooves? Were cracks noted during the inspection? Who performed this inspection? Provide any other comments? Issued in Fort Worth, Texas, on December 5, 2000. Henry A. Armstrong, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 00-31628 Filed 12-12-00; 8:45 am] BILLING CODE 4910-13-U