AD 2004-12-06 Airworthiness Directives; Eurocopter France Model EC 155 B and B1 Helicopters

Models named: EC 155 B, B1. Read the applicability below — it usually turns on serial or part numbers too.

Model EC 155 B and B1 helicopters, with main rotor blade (blade), part number (P/N) 365A11-0080-00, installed, certificated in any category.

Required as indicated. To detect a crack in a blade tip cap mounting bracket (tenon), which could result in loss of the tip cap, severe vibration, and loss of control of the helicopter, accomplish the following: (a) Unless accomplished previously, remove each blade and each tip cap, and inspect both the upper and lower side of the tenon for a crack using a 10× or higher magnifying glass while applying light manual upward and then downward pressure on the tenon as depicted in Figure 3 of Eurocopter Alert Telex No. 05A004, dated November 3, 2003 (Alert Telex) as follows: (1) For blades with more than 100 hours time-in-service (TIS), inspect each blade within the next 10 hours TIS. (2) For blades with 100 or less hours TIS, inspect each blade before it reaches 110 hours TIS. (3) If a crack is found, replace the blade with an airworthy blade before further flight. (b) After inspecting each blade as required by paragraph (a) of this AD: (1) Unless accomplished previously, before further flight, using a 24″ (500mm) straight edge, measure the clearance between the lower edge of the straight edge and the upper surface of the blade assembly at the blade-to-tip cap junction by following the Accomplishment Instructions, paragraph 2.B.2. of the Alert Telex, except contacting the manufacturer is not required. This initial clearance distance is called “DO”. (2) Thereafter, before the first flight of each day and on or before reaching each 10-hour TIS interval during the day, measure the clearance between the lower edge of the straight edge and the upper surface of the blade assembly at the blade-to-tip cap junction for each blade as required by paragraph (b)(1) of this AD. If the measured clearance is equal to or greater than “DO” + 2mm, replace the blade with an airworthy blade before further flight. (c) 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. (d) Special flight permits will not be issued. (e) The inspections and measurement shall be done in accordance with Eurocopter Alert Telex No. 05A004, dated November 3, 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 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 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. (f) This amendment becomes effective on June 29, 2004. Note: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD No. F-2003-418, dated December 24, 2003. Issued in Fort Worth, Texas, on June 1, 2004. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-12905 Filed 6-10-04; 8:45 am] BILLING CODE 4910-13-P