AD 2002-03-16 Airworthiness Directives; Bell Helicopter Textron, Inc.-Manufactured Model OH-13E, OH-13H, and OH-13S Helicopters

Models named: OH-13E, OH-13H, OH-13S. Read the applicability below — it usually turns on serial or part numbers too.

Model OH-13E, OH-13H, and OH-13S helicopters manufactured by Bell Helicopter Textron, Inc. (BHTI), with main rotor blade grips, part number (P/N) 47-120-135-2, 47-120-135-3, 47-120-135-5, 47-120-252-1, 47-120-252-7, 47-120-252-11, 74-120-252-11, 74-120-135-5, R74-120-252-11, or R74-120-135-5, 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 (e) 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.

Required as indicated, unless accomplished previously. To prevent failure of a main rotor blade grip (grip), separation of a main rotor blade, and subsequent loss of control of the helicopter, accomplish the following: (a) Conduct an eddy current inspection of the threads of both grips for a crack in accordance with Appendix 1 of this AD or an equivalent FAA-approved procedure containing the requirements of the procedure in Appendix 1 within 300 hours time-in-service (TIS) since initial installation on any helicopter or within 10 hours TIS for grips with 300 or more hours TIS or within 200 hours TIS since the last liquid penetrant or eddy current inspection of grip threads, whichever comes first. (1) Thereafter, conduct the eddy current inspection in accordance with Appendix 1 of this AD or an equivalent FAA-approved procedure containing the requirements of the procedure in Appendix 1 at intervals not to exceed 300 hours TIS. (2) Report the results of each inspection to the FAA Rotorcraft Certification Office within 7 calendar days. Information collection requirements contained in this AD have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq. ) and have been assigned OMB Control Number 2120-0056. Note 2: See Appendix 2 of this AD for a list of known eddy current inspection facilities. (b) If a crack is detected, before further flight, replace any cracked grip with an airworthy grip. (c) On or before 1200 hours TIS, replace each grip with an airworthy grip. (d) This AD establishes a retirement life of 1200 hours TIS for the grips, P/N 47-120-135-2, 47-120-135-3, 47-120-135-5, 47-120-252-1, 47-120-252-7, 47-120-252-11, 74-120-252-11, 74-120-135-5, R74-120-252-11, and R74-120-135-5. (e) 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 Rotorcraft Certification Office. (f) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (g) This amendment becomes effective on March 27, 2002. Appendix 1 ER20FE02.000 ER20FE02.001 ER20FE02.002 ER20FE02.003 ER20FE02.004 ER20FE02.005 ER20FE02.006 Appendix 2 Partial List of Nondestructive Inspection Testing Facilities Identified by Operators and FAA Met Chem Testing Laboratories Inc., 369 W. Gregson Ave. (3085 S.), Salt Lake City, Utah 84115-3440, Phone: (801) 487-0801, FAX: (801) 466-8790, www.metchemtesting.com . Galactic NDT Services, 10728 D. South Pipeline RD, Hurst, Texas 76053, Phone: (800) 458-6387. Global Testing Technologies, 1173 North Service Rd. Unit D3, Oakville Toronto Canada, Phone: (905) 847-9300, FAX: (905) 847-9330. Paragon Services, Inc., 1015 S. West St., Wichita, KS 67213, Phone: (316) 945-5285, FAX: (316) 945-0629. NOE Services, 8775 E. Orchard Rd. #809, Englewood, CO, Phone: (303) 741-0518, FAX: (303) 741-0519. Applied Technical Services, Inc., 1190 Atlanta Industrial Drive, Marietta, GA 30066, Phone: (770) 423-1400, FAX: (770) 514-3299. Rotorcraft Support, Van Nuys CA 91406, Phone: (818) 997-7667, FAX: (818) 997-1513. Other FAA Approved repair facilities may be used. Appendix 3 AD Compliance Inspection Report (Sample Format) Model OH-13 Main Rotor Blade Grip 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. Aircraft Registration No: Helicopter Model: Helicopter Serial Number: Owner and Operator of the Helicopter: Grip #1———Grip #2 Part Number: Serial Number: Hours TIS on the part at Inspection: Crack Found (Y/N) If yes, describe below. Description of Findings Who performed the inspections? If a crack was found, describe the crack size, location, and orientation (provide a sketch or pictures with the grip part and serial number). Provide any other comments. Issued in Fort Worth, Texas, on February 6, 2002. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 02-3851 Filed 2-19-02; 8:45 am] BILLING CODE 4910-13-U