AD 2005-06-01 Airworthiness Directives; Eurocopter France Model EC 155B and EC 155B1 Helicopters

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

Model EC 155B and EC 155B1 helicopters with cabin sliding doors, part number (P/N) 365A82-1064-02 (left-hand door) and P/N 365A82-1064-03 (right-hand door) and stop, P/N 365A25-8085-21, installed, certificated in any category.

Required as indicated, unless accomplished previously. To prevent separation of a door during flight and damage to the helicopter, resulting in a forced landing or loss of control of the helicopter, accomplish the following: (a) Before further flight, revise the Limitations Section of the Rotorcraft Flight Manual (RFM) permitting the opening or closing of the cabin sliding doors only at speeds of less than 40 knots indicated airspeed. (b) Within 50 hours time-in-service, inspect the length of the chamfer on the stop of the lower rail aft fitting on each cabin sliding door (door), and if the chamfer is more than 2mm in length, install an airworthy stop in accordance with paragraph 2.B., Operational Procedure, of Eurocopter Alert Telex No. 52A013, Revision 1, dated September 24, 2003. Note 1: The inspection required by paragraph (b) of this AD has already been accomplished for all Model EC 155B1 helicopters prior to delivery. (c) Before each flight with a door open, check that each open door is locked in the “open” position with the upper roller in its rail and the door open locking latch engaged. (d) Before each flight with a door closed, check that: (1) The locking indicator light on the instrument panel is “off,” (2) The door handle is in the correct “closed” position, and (3) The lower locking pin is positioned in its catch. Note 2: If the door is correctly closed and latched, when viewed from the outside, the door handle will be flush with the profile of the housing and the aft lower corner of the door will be flush with the profile of the fuselage; when viewed from the inside, the door handle will be positioned opposite the locking indicator with no gap between the structure seal and the aft lower sealing surface of the door. Note 3: If the door is closed and the lower locking pin is outside its catch, when viewed from the outside, the aft lower corner of the door is approximately 15 to 20mm from the fuselage; when viewed from the inside, the aft lower corner of the door is approximately 10 to 15mm from the fuselage. (e) An owner/operator (pilot) holding at least a private pilot certificate may perform the visual checks required by paragraphs (c) and (d) of this AD and must enter compliance with those paragraphs into the aircraft maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). (f) After the stops of the lower rail aft fitting with a chamfer 2mm or less in length are installed and in accordance with MOD 0753C48, the mounting plate supports are modified and the door micro-switches are adjusted, the checks required by paragraph (d) of this AD are no longer required. (g) 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. (h) The modification shall be done in accordance with Eurocopter Alert Telex No. 52A013, Revision 1, dated September 24, 2003. The Director of the Federal Register approved this incorporation by reference 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 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 . (i) This amendment becomes effective on April 18, 2005. Note 4: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD No. F-2003-345-R1, dated November 12, 2003. Issued in Fort Worth, Texas, on March 4, 2005. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-4807 Filed 3-11-05; 8:45 am] BILLING CODE 4910-13-P