95-19-15 R1: Wing attach shoulder bolts

95-19-15 R1 Tiger Aircraft LLC: (Type Certificate A16EA formerly held by American General Aircraft Corporation and Grumman American Aviation Corporation): Amendment 39-14222; Docket No. FAA-2005- 20968; Directorate Identifier 94-CE-15-AD. When Does This AD Become Effective? (a) This AD becomes effective on October 3, 2005. What Other ADs Are Affected By This Action? (b) This AD revises AD 95-19-15, Amendment 39-9377. What Airplanes Are Affected by This AD? (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model Serial numbers AA 5 All Serial Numbers. AA 5A All Serial Numbers. AA 5B All Serial Numbers. AG 5B 99998, 10000 through 10174. What Is the Unsafe Condition Presented in This AD? (d) AD 95-19-15 currently requires you to inspect the wing attach shoulder bolts for fretting, scoring, wear, or enlarged or elongated mounting holes (known as damage from hereon); replace any damaged parts; repair any damaged areas; inspect the wing spar at the center spar clearance gap for excessive clearance; and shim the spar if excessive clearance is found. That AD was written to apply to all serial numbers of all models. A design change was made in this area beginning with serial number 10175 of the Model AG-5B airplanes. Therefore, the action should not apply to Model AG-5B airplanes with a serial number of 10175 or higher. This AD retains all the actions of AD 95-19-15 for all airplanes originally affected, but cuts off the applicability for the Model AG-5B airplanes at serial number 10174. We are issuing this AD to continue 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. What Must I Do To Address This Problem? (e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures(1) Inspect any inboard wing attach shoulder bolt for: (i) Fretting, scoring, or wear (removal of the cad plating) to the shoulder of the bolt (ii) A smooth machined area between the threads and the shoulder bevel of the shoulder bolt profile Within the next 100 hours aircraft time-in- service (TIS) after November 17, 1995 (the effective date of AD 95 19 15, unless already done Follow American General Aircraft Corporation Service Bulletin No. SB 185 A, Revision A, dated January 10, 2005. (2) Replace any inboard wing attach shoulder bolt with wear (removal of the cad plating from the shoulder of the bolt) or if the threads contact the shoulder of the bolt found during the inspections required in paragraph (e)(1) of this AD Before further flight after the inspection required by paragraph (e)(1) of this AD Follow American General Aircraft Corporation Service Bulletin No. SB 185 A, Revision A, dated January 10, 2005. (3) Inspect the mounting holes in the wing spar and the center section spar for enlargementor elongation that exceeds the specified dimension Within the next 100 hours aircraft time-in- service (TIS) after November 17, 1995 (the effective date of AD 95 19 15), unless already done Follow American General Aircraft Corporation Service Bulletin No. SB 185 A, Revision A, dated January 10, 2005. (4) Ream and bush any mounting hole that exceeds the specified dimension found during the inspection required by paragraph (e)(3) of this AD Before further flight after the inspection required by paragraph (e)(3) of this AD Follow American General Aircraft Corporation Service Bulletin No. SB 185 A, Revision A, dated January 10, 2005 (5) Inspect the wing spar at the center spar clearance gap for excessive clearance, and shim the spar if excessive clearance is found Before further flight after the inspections required by paragraphs (e)(1) and (e)(3) of this AD Follow American General Aircraft Corporation Service Bulletin No. SB 185 A, Revision A, dated January 10, 2005. (6) Do not install any wing attach shoulder bolt that has wear resulting in removal of the cad plating from the shoulder of the bolt or if the threads contact the shoulder bevel of the shoulder bolt profile As of October 3, 2005 (the effective date of this AD) Not Applicable. May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, New York Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Richard Beckwith, Aerospace Engineer, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516-794-5531; facsimile: 516-794-5531. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in American General Aircraft Corporation Service Bulletin No. SB-185-A, Revision A, dated January 10, 2005. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Tiger Aircraft LLC, 226 Pilot Way, Martinsburg, WV 25401. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Departmentof Transportation, 400 Seventh Street, SW., Nassif Building, Room PL- 401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2005-20968; Directorate Identifier 94-CE-15-AD.