AD 95-03-06

This amendment adopts a new airworthiness directive (AD), applicable to certain Canadair Model CL-600-1A11, -2A12, and -2B16 series airplanes, that requires a functional check and a test of the idle stop function of the engine throttle quadrant; repair or replacement, if necessary; and eventual replacement of the engine throttle quadrant with a new model. This amendment is prompted by reports of unintentional engine shutdown on certain of these airplanes due to problems associated with operation of the engine throttle quadrant. The actions specified by this AD are intended to ensure the proper operation of the throttle quadrant so as to prevent inadvertent shutdown of an engine while the airplane is taxiing or in flight.

Final rule

95-03-06 CANADAIR: Amendment 39-9143. Docket 93-NM-207-AD.
Applicability: Model CL-600-1A11 series airplanes, serial numbers 1004 through 1085, inclusive, equipped with throttle quadrant part numbers 600-90601-69, -71, -73, -75, -77, and -79; Model CL-600-2A12 series airplanes, serial numbers 3001 through 3066, inclusive, equipped with throttle quadrant part numbers 600-90601-983, -987, -989, -1013, -1015, -1017, -1019, -1021, -1023, -1025, and -1027; and Model CL-600-2B16 series airplanes, serial numbers 5001 through 5139, inclusive, equipped with throttle quadrant part numbers 600-90601-983, -987, -989, -1013, -1015, -1017, -1019, -1021, -1023, -1025, and -1027; 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 use the authority provided in paragraph (f) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent inadvertent shutdown of an engine while the airplane is taxiing or in flight, accomplish the following:

(a) Within 50 hours time-in-service after the effective date of this AD, perform a test of the engine throttle quadrant to determine if the throttle levers bypass the idle stop into the shut- off position, in accordance with Canadair Alert Service Bulletin A600-0615, dated June 10, 1992 (for Model CL-600-1A11 series airplanes); or Canadair Alert Service Bulletin A601-0374, Revision 1, dated September 30, 1992 (for Models CL-600-2A12 and CL-600-2B16 series airplanes), as applicable.

NOTE 2: Canadair Alert Service Bulletins A600-0615 and A601-0374 reference Sargent Aerospace Service Bulletins 43058-76-03 (for Model CL-600-1A11 series airplanes) and 43068-76-05 (for Model CL-600-2A12 and -2B16 series airplanes), both dated April 13, 1992, for additional service information.

(b) If the test required by paragraph (a) of this AD indicates that either throttle lever bypasses the idle stop into the shut-off position, prior to further flight, replace the throttle quadrant in accordance with Part B of the Accomplishment Instructions of Canadair Challenger Service Bulletin 600-0629, dated November 1, 1993 (for Model CL-600-1A11 series airplanes); or Canadair ChallengerService Bulletin 601-0410, dated November 1, 1993 (for Models CL-600-2A12 and -2B16 series airplanes); as applicable.

(c) Within 150 hours time-in-service after the effective date of this AD, perform a functional check of the idle stop function of the throttle quadrant in accordance with Part A of the Accomplishment Instructions of Canadair Challenger Service Bulletin 600-0629, dated November 1, 1993 (for Model CL-600-1A11 series airplanes); or Canadair Challenger Service Bulletin 601-0410, dated November 1, 1993 (for Models CL-600-2A12 and -2B16 series airplanes); as applicable.

NOTE 3: Canadair Challenger Service Bulletins A600-0629 and A601-0410 reference Sargent Aerospace Service Bulletins 43058-76-04 (for Model CL-600-1A11 series airplanes) and 43068-76-06 (for Model CL-600-2A12 and -2B16 series airplanes), both dated March 24, 1993, for additional service information.

(d) If the functional check required by paragraph (c) of this AD indicates that the idle stop function of the throttle quadrant fails, prior to further flight, replace the throttle quadrant in accordance with Part B of the Accomplishment Instructions of Canadair Challenger Service Bulletin 600-0629 or 601-0410, both dated November 1, 1993, as applicable.

(e) Within 4,500 hours time-in-service after the effective date of this AD, replace the throttle quadrant in accordance with Part B of the Accomplishment Instructions of Canadair Challenger Service Bulletin 600-0629, dated November 1, 1993 (for Model CL-600-1A11 series airplanes); or Canadair Challenger Service Bulletin 601-0410, dated November 1, 1993 (for Models CL-600-2A12 and CL-600-2B16 series airplanes); as applicable. Such replacement constitutes terminating action for the requirements of this AD.

(f) 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, Engineand 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 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO.

(g) 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.

(h) The replacements and check shall be done in accordance with Canadair Challenger Service Bulletin 600-0629, dated November 1, 1993; or Canadair Challenger Service Bulletin 601-0410, dated November 1, 1993; as applicable. 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, 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.

(i) This amendment becomes effective on March 31, 1995.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Canadair Model CL-600-1A11, -2A12, and -2B16 series airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on October 19, 1994 (59 FR 52720). That action proposed to require a functional check and a test of the idle stop function of the engine throttle quadrant; repair or replacement, if necessary; and eventual replacement of the engine throttle quadrant.

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.

As a result of recent communications with the Air Transport Association (ATA) of America, the FAA has learned that, in general, some operators may misunderstand the legal effect of AD's on airplanes that are identified in the applicability provision of the AD, but that have been altered or repaired in the area addressed by the AD. The FAA points out that all airplanes identified in the applicability provision of an AD are legally subject to the AD. If an airplane has been altered or repaired in the affected area in such a way as to affect compliance with the AD, the owner or operator is required to obtain FAA approval for an alternative method of compliance with the AD, in accordance with the paragraph of each AD that provides for such approvals. A note has been added to this final rule to clarify this requirement.

Additionally, the FAA has recently reviewed the figures it has used over the past several years in calculating the economic impact of AD activity. In order to account for various inflationary costs in the airline industry, the FAA has determined that it is necessary to increase the labor rate used in these calculations from $55 per work hour to $60 perwork hour. The economic impact information, below, has been revised to reflect this increase in the specified hourly labor rate.

After careful review of the available data, the FAA has determined that air safety and the public interest require the adoption of the rule with the changes previously described. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.

The FAA estimates that 150 airplanes of U.S. registry will be affected by this AD.

The side-loads test of the engine throttle quadrant will take approximately 17 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the total cost impact of the side-loads test requirements of this AD on U.S. operators is estimated to be $153,000, or $1,020 per airplane.

The abrupt-movement check of the idle stop function of the throttle quadrant will take approximately 1 work hour per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the total cost impact of the functional check requirements of this AD on U.S. operators is estimated to be $9,000, or $60 per airplane.

The installation of a modified throttle quadrant will take approximately 10 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Required parts will be provided by the manufacturer at no cost to operators. Based on these figures, the total cost impact of the installation requirement of this AD on U.S. operators is estimated to be $90,000, or $600 per airplane.

Based on the figures discussed above, the total cost impact of this AD on U.S. operators is estimated to be $252,000, or $1,680 per airplane. This cost impact figure 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.

The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, 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, Aviation safety, Incorporation by reference, Safety.

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