98-16-04: Inspect Angle Stiffener Along Lower Spar Cap

98-16-04 CESSNA AIRCRAFT COMPANY: Amendment 39-10679; Docket No. 97-CE-14-AD. Applicability: The following airplane models, all serial numbers, certificated in any category, that have wing extension supplemental type certificate (STC) SA00276NY or supplemental type approval (STA) SA93-136 incorporated. NOTE 1: The STA is the Canadian version of the U.S. STC. Models 180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, 180K, 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, 182S, R182, T182, TR182, 185, 185A, 185B, 185C, 185D, 185E, A185E, A185F 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 (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 50 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To prevent wing failure during flight caused by the absence of an angle stiffener, which could cause loss of control of the airplane, accomplish the following: (a) Inspect inside the left and right wings, aft of the spar, closest to where the strut connects to the wing, for an angle stiffener along the lower spar cap between Wing Station (W.S.) 90 and W.S. 110 in accordance with Part A of the Accomplishment Instructions of Air Research Technology, Inc. (ART) Service Bulletin (SB)No. SB-1-96, Issue 1, dated April 11, 1996. (b) If an angle stiffener is not installed, prior to further flight, install a stainless steel reinforcement strap on the underside of each wing, along the spar at W.S. 100.50 in accordance with Part B of the Accomplishment Instructions of ART SB No. SB-1-96, Issue 1, dated April 11, 1996. (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, New York Aircraft Certification Office, 10 Fifth Street, 3rd Floor, Valley Stream, New York, 11581-1200. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York Aircraft Certification Office. (e) The inspection and installation required by this AD shall be done in accordance with Air Research Technology Service Bulletin No. SB-1-96, Issue 1, dated April 11, 1996. 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 Air Research Technology, Inc., 3440 McCarthy, Montreal, Quebec, Canada H4K 2P5. 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. (f) This amendment becomes effective on September 21, 1998.