95-19-15: Wing Attach Shoulder Bolts

95-19-15 AMERICAN GENERAL AIRCRAFT CORPORATION: Amendment 39-9377; Docket No. 94-CE-15-AD. Applicability: Models AA-5, AA-5A, AA-5B, and AG-5B airplanes (all serial numbers), certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability revision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes 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 (d) 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 within the next 100 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To prevent wing attach shoulder bolt failure, which, if not detected and corrected, could lead to structural damage of the wing/fuselage to the point of failure, accomplish the following: (a) Inspect the wing attach shoulder bolts (4), part numbers as specified in paragraphs (a)(1) and (a)(2) below, for fretting, scoring, wear, or enlarged or elongated mounting holes (known as damage from hereon) in accordance with the procedures included in the INSPECTION section of American General Critical Service Bulletin SB-185, dated July 6, 1994. Prior to further flight, replace any damaged parts with new or serviceable parts and repair any damaged areas in accordance with the applicable maintenance manual. (1) The wing attach shoulder bolt part number for serial numbers AA-5-0001 through AA-5-0714 of the AA-5 series airplanes is 901044-1. (2) The wing attach shoulder bolt part numbers for all serial numbers of the AA-5 series airplanes, except for serial numbers AA-5-0001 through AA-5-0714, is either 901044-3 or 901044-2. (b) Inspect the wing spar at the center spar clearance gap for excessive clearance in accordance with the procedures included in the INSPECTION section of American General Critical Service Bulletin SB-185, dated July 6, 1994. If any gap exceeds .016-inch, prior to further flight, shim the spar to reduce the gap to a level not to exceed .008 inches in accordance with the instructions in the applicable maintenance manual. (c) 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 airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office (ACO), Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia 30337-2748. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (e) The inspection required by this AD shall be done in accordance with American General Critical Service Bulletin SB-185, dated July 6, 1994. 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 Fletch Air, Inc., 9000 Randolph Street, Houston, Texas 77061. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on November 17, 1995.