98-12-20: Horizontal Stabilizer Spar Tube

98-12-20 EUROCOPTER FRANCE: Amendment 39-10574. Docket No. 98-SW-03-AD. Applicability: SE3130, SA3180, SE313B, SA318B, and SA318C helicopters with horizontal stabilizer, part number (P/N) 3130-35-60-000, 3130-35-60-000-1, 3130-35-60-000-2, 3130-35-60-000-3, 3130-35-60-000-4 or higher dash numbers, 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 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 use the authority provided in paragraph (f) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such arequest should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue failure of the horizontal stabilizer spar tube (spar tube), impact of the horizontal stabilizer with the main or tail rotor and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight: (1) Inspect the aircraft records and the horizontal stabilizer installation to determine whether Modification 072214 (installation of the spar tube without play) or Modification 072215 (adding two half-shells on the spar) has been accomplished. (2) If Modification 072214 has not been installed, comply with paragraphs 2.A., 2.B.1), 2.B.2)a), and 2.B.2)b) of the Accomplishment Instructions of Eurocopter France Service Bulletin No. 55.10, Revision 2, dated April 25, 1997 (service bulletin). If the fit and dimensions of the components specified in paragraph 2.B.2)a) exceed the tolerances in the applicable structural repair manual, replace with airworthy parts. (3) If Modification 072215 has not been installed, first comply with paragraphs 2.A., 2.B.1), and 2.B.3), and then comply with paragraph 2.B.2)c) of the Accomplishment Instructions of the service bulletin. NOTE 2: Modification kit P/N 315A-07-0221571 contains the necessary materials to accomplish this modification. (b) Before the first flight of each day: (1) Visually inspect the installation of the half-shells, the horizontal stabilizer supports, and the horizontal stabilizer for corrosion or cracks. Repair any corroded parts in accordance with the applicable maintenance manual. Replace any cracked components with airworthy parts before further flight. (2) Confirm that there is no play in the horizontal stabilizer supports by lightly shaking the horizontal stabilizer. If play is detected, comply with paragraphs 2.A. and 2.B.2)a) of the service bulletin. If the fit and dimensions of the components specified in paragraph 2.B.2)a) exceed the tolerances in the applicable structural repair manual, replace with airworthy parts before further flight. (c) At intervals not to exceed 400 hours time-in-service (TIS) or four calendar months, whichever occurs first, inspect and lubricate the spar tube attachment bolts. (d) For stabilizers, P/N 3130-35-60-000, 3130-35-60-000-1, 3130-35-60-000-2, or 3130-35-60-000-3, within 90 calendar days and thereafter at intervals not to exceed 18 calendar months, visually inspect the inside of the horizontal spar tube in accordance with paragraph 2.A. and 2.B.1) of the service bulletin. (1) If corrosion is found inside the tube, other than in the half-shell area, replace the tube with an airworthy tube within the next 500 hours TIS or24 calendar months, whichever occurs first. (2) If corrosion is found inside the tube in the half-shell area, apply a protective treatment as described in paragraph 2.B.1)b) of the service bulletin. (e) For stabilizers, P/N 3130-35-60-000-4 or higher dash numbers, accomplish the following: (1) At or before the next major inspection, 3200 hours total TIS, or 12 calendar years total TIS, whichever occurs first, and thereafter at each major inspection, visually inspect the inside of the horizontal spar tube in accordance with paragraph 2.A. and 2.B.1) of the service bulletin. (2) If corrosion is found inside the tube, other than in the half-shell area, replace the tube with an airworthy tube within the next 500 hours TIS or 18 calendar months, whichever occurs first. If corrosion is found inside the tube in the half-shell area, apply a protective treatment as described in paragraph 2.B.1)b) of the service bulletin. (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, Rotorcraft Standards Staff, FAA, Rotorcraft Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished. (h) The modification shall be done in accordance with Eurocopter France Service Bulletin No. 55.10, Revision 2, dated April 25, 1997. 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. 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. NOTE 4: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 96-278-054(B)R1, dated May 21, 1997. (i) This amendment becomes effective on July 14, 1998.