95-23-11: Upper And Lower Horizontal Flanges

95-23-11 AEROSTAR AIRCRAFT CORPORATION: Amendment 39-9431; Docket No. 95-CE-81-AD. Applicability: The following model and serial number airplanes, certificated in any category: Models Serial Numbers PA-60-600 Aerostar 600 60-0001-003 through 60-0933-8161262 PA-60-601 Aerostar 601 61-0001-004 through 61-0880-8162157 PA-60-601P Aerostar 601P 61P-0157-001 through 61P-0860-8163455 PA-60-602P Aerostar 602P 62P-0750-8165001 through 60-8365021 NOTE 1: This AD applies to each airplane 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 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 ofthe 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 initially within the next 25 hours time-in-service (TIS) after the effective date of this AD or within the next 2 calendar months after the effective date of this AD, whichever occurs first, unless already accomplished, and thereafter at intervals not to exceed 100 hours TIS or 12 calendar months, whichever occurs first. To prevent the fuselage horizontal stabilizer from separating from the airplane while in flight because of cracked attach fittings, which, if not detected and replaced, could result in loss of control of the airplane, accomplish the following: (a) Inspect the upper and lower horizontal flanges on the left and right sides of the following parts for cracks in accordance with the INSTRUCTIONS section of Aerostar Service Bulletin SB600-130, dated September 26, 1995. (1) The part number (P/N) 210006-001 fitting (forward fuselage horizontal stabilizer attach fitting); and (2) The P/N 210007-001 fitting (aft fuselage horizontal stabilizer attach fitting). (b) Prior to further flight, replace any fuselage horizontal stabilizer attach fitting found cracked during any inspection required by paragraph (a) of this AD. Accomplish this replacement in accordance with 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 initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, S.W., Renton, Washington 98055-4056. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. (e) The inspections required by this AD shall be done in accordance with Aerostar Service Bulletin SB600-130, dated September 26, 1995. 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 the Aerostar Aircraft Corporation, Customer Service Department, South 3608 Davison Boulevard, Spokane, Washington 99204. 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., 7th Floor, suite 700, Washington, DC. (f) This amendment becomes effective on November 30, 1995.