AD 94-08-15

94-08-15 CANADAIR: Amendment 39-8888. Docket 93-NM-188-AD.

Applicability: Model CL-600-2A12 series airplanes, serial numbers 3002 through 3066, inclusive; and Model CL-600-2B16 series airplanes, serial numbers 5001 through 5131, inclusive; certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent asymmetric deployment or retraction (blow back) of the flaps, which could reduce the controllability of the airplane, accomplish the following:

(a) Within 30 days after the effective date of this AD, conduct a visual inspection to verify the proper installation of shoulder bolts, and to detect damage of adjacent flap actuator housings, in accordance with Canadair Alert Service Bulletin A601-0415, dated June 25, 1993 (hereafter referred to as "the alert service bulletin").

NOTE 1: Inspections accomplished prior to the effective date in accordance with Canadair Alert Service Wire TA601-0415-036, dated May 3, 1993,are considered to be in compliance with this paragraph.

(b) If all shoulder bolts are found to be installed properly and no flap actuator housings are found to be damaged, no further action is required by this AD.

(c) If any shoulder bolt is found to be improperly installed, but no flap actuator housing is found to be damaged, prior to further flight, remove the improperly installed shoulder bolt and reinstall it in accordance with the alert service bulletin.

(d) If any flap actuator housing is found to be damaged (as defined in the alert service bulletin), prior to further flight, accomplish the requirements of paragraphs (d)(1) and (d)(2) of this AD:

(1) Perform either an eddy current inspection or a dye penetrant inspection to detect cracking of the hinge fitting lugs on the flap actuator in accordance with the alert service bulletin. If any cracking is detected, prior to further flight, replace the hinge fitting lug with new or serviceable parts in accordancewith the alert service bulletin.

(2) Replace the shoulder bolt and damaged flap actuator with new or serviceable parts in accordance with the alert service bulletin.

(e) 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 Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. 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.

(f) 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.(g) The inspections, replacement, removal, and reinstallation shall be done in accordance with Canadair Alert Service Bulletin A601-0415, dated June 25, 1993, including Appendix 1. 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 A, 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, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(h) This amendment becomes effective on May 20, 1994.