AD 2002-14-17 Airworthiness Directives; Eurocopter Deutschland GmbH Model EC135 Helicopters

Models named: EC135. Read the applicability below — it usually turns on serial or part numbers too.

Model EC135 helicopters, with main rotor hub shaft (shaft) assemblies, part numbers L623M1003 101, L623M1003 102, L623M1003 103, L623M1003 104, L623M1003 105, L623M1003 106, or L623F1003 107, 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 (f) 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 detect fatigue cracks in the shaft that could lead to shaft failure and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, clean and visually inspect the shaft for cracks in the area as shown in the following Figure 1: ER11JY02.026 BILLING CODE 4910-13-C (b) Within 10 hours time-in-service (TIS) after accomplishing the visual inspection required by paragraph (a) of this AD, clean and dye-penetrant inspect the shaft for cracks in the area as shown in Figure 1 of this AD. (c) Thereafter, visually inspect the shaft for cracks in accordance with paragraph (a) of this AD at intervals not to exceed 15 hours TIS, or dye-penetrant inspect the shaft for cracks in accordance with paragraph (b) of this AD at intervals not to exceed 100 hours TIS. Note 2: Eurocopter Alert Service Bulletin EC135-62A-004, Revision 3, dated November 10, 2000, pertains to the subject of this AD. (d) If a crack is discovered during any shaft inspections, remove the shaft and replace it with an airworthy shaft. (e) Report any cracked shaft within 5 calendar days to the Rotorcraft Standards Staff, Rotorcraft Directorate, Fort Worth, Texas 76193-0110, telephone (817) 222-5116, fax (817) 222-5961. 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. (f) 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, Regulations Group, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Regulations Group. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group. (g) 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. (h) This amendment becomes effective on July 26, 2002. Note 4: The subject of this AD is addressed in Luftfahrt-Bundesamt (Federal Republic of Germany) AD 1999-185/4, dated October 18, 2001. Issued in Fort Worth, Texas, on July 3, 2002. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 02-17300 Filed 7-10-02; 8:45 am] BILLING CODE 4910-13-P