99-16-06: Wing Attach Fittings

99-16-06 THE NEW PIPER AIRCRAFT, INC.: Amendment 39-11241; Docket No. 99-CE- 01-AD. Applicability: Model PA-46-350P airplanes, serial numbers 4622191 through 4622200 and 4636001 through 4636175, certificated in any category. NOTE 1: The affected serial numbers refer to airplanes that have been delivered since January 1995 and could have insufficient strength wing attach fittings installed. Airplanes manufactured after serial number 4636175 have this problem corrected prior to delivery. NOTE 2: 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 (c) 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 the potential for failure of the wing attach fittings caused by the utilization of substandard material, which could result in the wing separating from the airplane with consequent loss of control of the airplane, accomplish the following: (a) Install reinforcement plates to the wing forward and aft attach fittings by incorporating the Wing to Fuselage Reinforcement Installation Kit, Piper part number 766-656. Accomplishment of the installation is required in accordance with the instructions to the above- referenced kit, as referenced in Piper Service Bulletin No. 1027, dated November19, 1998. (b) Special flight permits may be issued in accordance with Secs. 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. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, FAA, Atlanta Aircraft Certification Office (ACO), One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349. 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 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (d) The installation required by this AD shall be done in accordance with the instructions to the Wing to Fuselage Reinforcement Installation Kit, Piper part number 766-656, as referenced in Piper Service Bulletin No. 1027, dated November 19, 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 The New Piper Aircraft, Inc., Customer Services, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Regional 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. (e) This amendment becomes effective on September 24, 1999.