AD 98-04-08 Airworthiness Directives; Bombardier Model CL-215-1A10 and CL- 215-6B11 Series Airplanes

Models named: CL-215-1A10, CL-215-6B11 series. Read the applicability below — it usually turns on serial or part numbers too.

Model CL-215-1A10 and CL-215-6B11 series airplanes, serial numbers 1001 through 1125 inclusive; certificated in any category. 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 (b) 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.

Required as indicated, unless accomplished previously. To detect and correct cracking of the lower caps of the wing front spar and rear spar, which could result in reduced structural integrity of the airplane, accomplish the following: (a) Prior to the accumulation of 3,000 total flight hours, or within 25 flight hours after the effective date of this AD, whichever occurs later: Perform an ultrasonic inspection to detect cracking of the lower cap of the wing front and rear spars at wing station 51, [[Page 7642]] in accordance with the Accomplishment Instructions of Canadair Alert Service Bulletin 215-A463, Revision 1, dated May 25, 1995 (for the front spar); and Canadair Alert Service Bulletin 215-A454, Revision 1, dated May 25, 1995 (for the rear spar). Thereafter, repeat the ultrasonic inspection at intervals not to exceed 600 flight hours. If any cracking is detected, prior to further flight, accomplish paragraphs (a)(1) and (a)(2) of this AD. (1) Rework the lower cap of the front or rear spar, as applicable, in accordance with the alert service bulletin. And (2) Visually inspect, from inside the wing box, the front spar web or the rear spar web, as applicable, and the lower skin area to detect cracks. If any cracking is detected, prior to further flight, repair in accordance with a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (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) The actions shall be done in accordance with Canadair Alert Service Bulletin 215-A454, Revision 1, dated May 25, 1995, and Canadair Alert Service Bulletin 215-A463, Revision 1, dated May 25, 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 Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 3: The subject of this AD is addressed in Canadian airworthiness directives CF-92-26, dated December 23, 1992, and CF- 93-07, dated March 26, 1993. (e) This amendment becomes effective on March 4, 1998. Issued in Renton, Washington, on February 4, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-3262 Filed 2-13-98; 8:45 am] BILLING CODE 4910-13-U