2000-03-06: Horizontal Stabilizer Spar Tube

2000-03-06 EUROCOPTER FRANCE: Amendment 39-11563. Docket No. 98-SW-65-AD. Supersedes AD 98-12-20, Amendment 39-10574, Docket No. 98-SW-03-AD. Applicability: Model SE 3130, SA 3180, SE 313B, SA 318B, and SA 318C 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 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 (g) 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. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue failure of the horizontal stabilizer spar tube (spar tube), separation of the horizontal stabilizer and impact 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 to determine whether Modification 072214 (installing 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 SA3130/3180 Service Bulletin No. 55.10, Revision 3, dated May 4,1998 (SB). 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 SB. 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 SB. 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 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 SB. (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 or 24 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 SB. (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, 3,200 hours total TIS, or 144 calendar months 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 SB. (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 SB. (f) Within 30 calendar days, visually inspect the four attachment clamps of the half-shells and install a safety wire around the four attachment clamps in accordance with paragraph 2.B.2)d) of the SB. If any attachment clamp is found cracked, replace it with an airworthy attachment clamp and install a safety wire around the replacement attachment clamp before further flight. (g) 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. (h) 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. (i) The inspections and modifications shall be done in accordance with paragraphs 2.A, 2.B.1), 2.B.1)b), 2.B.2)a), 2.B.2)b), 2.B.2)c), 2.B.2)d), and 2.B.3) of the Accomplishment Instructions of Eurocopter France SA3130/3180 Service Bulletin No. 55.10, Revision 3, dated May 4, 1998. 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. (j) This amendment becomes effective on March 21, 2000. NOTE 4: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 96-278-054(A)R2, dated July 29, 1998. FOR FURTHER INFORMATION CONTACT: Richard Monschke, Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, fax (817) 222-5961.