AD 94-08-15

This amendment adopts a new airworthiness directive (AD), applicable to certain Canadair Model CL-600-2A12 and CL-600-2B16 series airplanes, that requires a one-time visual inspection to verify proper installation of shoulder bolts and to detect damage of the adjacent flap actuator housings, and correction of discrepancies. This amendment is prompted by a report of failure of the flap actuator on the left wing inboard flap. The actions specified by this AD are intended to prevent asymmetric deployment or retraction (blow back) of the flaps, which could reduce controllability of the airplane.

Final rule

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.

A proposal to amend part 39 of the Federal Aviation Regulations to include an airworthiness directive (AD) that is applicable to certain Canadair Model CL-600-2A12 and CL-600-2B16 series airplanes was published in the Federal Register on December 29, 1993 (58 FR 68789). That action proposed to require a one-time visual inspection to verify proper installation of shoulder bolts and to detect damage of adjacent flap actuator housings, and correction of discrepancies.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

The FAA estimates that 196 airplanes of U.S. registry will be affected by this AD, that it will take approximately 1 work hour per airplane to accomplish the required visual inspection, and that the average labor rate is $55 per work hour. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $10,780, or $55 per airplane.

The total cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted.

If replacement of any hinge fitting lug, shoulder bolt, or flap actuator is necessary, accomplishment of such replacement will entail approximately 12 work hours, at an average labor rate of $55 per work hour. Required parts will be provided by the manufacturer at no cost to the operator. Based on these figures, the total cost of any necessary replacement is estimated to be $660 per replaced item.

The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and theStates, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviationsafety, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 of the Federal Aviation Regulations as follows:

PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89.

39.13 - [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive: