AD 2004-01-14 Airworthiness Directives; Eurocopter France Model EC130B4 Helicopters

Models named: EC130B4. Read the applicability below — it usually turns on serial or part numbers too.

Eurocopter France Model EC130B4 helicopters with an air intake cowling forward attachment fitting (fitting), part number (P/N) 350A25-0405-00, -01, -02, -03, -04, and -05, installed, certificated in any category.

Required as indicated. To prevent failure of a forward fitting, an excess load on the other fittings, which could cause them to crack and break, which could result in loss of the air intake cowling in flight, and subsequent damage or loss of control of the helicopter, or both, accomplish the following: (a) Visually inspect the forward fittings for breaks or cracks by following paragraph 2.B.1. of the Operational Procedure in Eurocopter Alert Service Bulletin No. 53A004, dated September 11, 2003 (ASB). (1) For helicopters with less than 100 hours time-in-service (TIS), inspect before the helicopter reaches 110 hours TIS, unless accomplished previously, and thereafter, at intervals not to exceed 110 hours TIS. (2) For helicopters with 100 or more hours TIS, inspect within 10 hours TIS, unless accomplished previously, and thereafter at intervals not to exceed 110 hours TIS. (b) If one or two forward fittings are broken or cracked, inspect the center and aft fittings for breaks or cracks before further flight by following paragraph 2.B.2.b. of the ASB. (c) Before further flight, replace any fitting that is broken or has more than two cracks, or any fitting with a crack that exceeds 10 mm in length by following paragraph 2.B.2.c. of the Operational Procedure in the ASB. (d) For any cracked fitting that has no more than two cracks, and neither crack exceeds 10 mm in length, you are not required to replace that cracked fitting provided that you stop-drill each crack and re-inspect that fitting at intervals not to exceed 20 hours TIS. During a later inspection, if you discover that the fitting has failed, another crack has developed, or a stop-drilled crack has grown to exceed 10mm in length, replace the fitting before further flight. (e) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (f) The inspections and replacements, if necessary, shall be done using Eurocopter Alert Service Bulletin No. 53A004, dated September 11, 2003. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on January 26, 2004. Note: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 2003-358(A), dated October 15, 2003. Issued in Fort Worth, Texas, on December 31, 2003. Kim Smith, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-368 Filed 1-8-04; 8:45 am] BILLING CODE 4910-13-P