AD 2001-13-03 Airworthiness Directives; Kaman Aerospace Corporation Model K-1200 Helicopters

Models named: K-1200. Read the applicability below — it usually turns on serial or part numbers too.

Model K-1200 helicopters, 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 2 accordance with paragraph (c) 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 the rotor shaft, teeter pin assembly, or flap clevis due to fatigue cracks, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, remove any rotor shaft, part number (P/N) K974112-001, -003, -005, -007, -009, or -101, that has 3,750 or more hours time-in-service (TIS) and replace it with an airworthy part. Remove any teeter pin assembly, P/N K910005-007 or -009, that has 550 or more hours TIS and replace it with an airworthy part. Remove any flap clevis assembly, P/N K911049-001, -003, or -005, that has 640 or more hours TIS, and replace it with an airworthy part. (b) This AD revises the Limitations section of the maintenance manual by removing the life limit of 640 hours TIS established for the flap clevis, P/N K911049-021. The life limit for each rotor shaft, P/N K974112-001, -003, -005, -007, -009, and -101 remains at 3,750 hours TIS; the life limit for each teeter pin assembly, P/N K910005-007 and -009, remains at 550 hours TIS; and the life limit for each flap clevis assembly, P/N K911049-001, -003, and -005 remains at 640 hours TIS. (c) 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, Boston Aircraft 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, Boston Aircraft Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Boston Aircraft Certification Office. (d) Special flight permits will not be issued. (e) This amendment becomes effective on May 27, 2003. Issued in Fort Worth, Texas, on April 9, 2003. Michele M. Owsley, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 03-9576 Filed 4-18-03; 8:45 am] BILLING CODE 4910-13-P