[Federal Register Volume 59, Number 123 (Tuesday, June 28, 1994)]
[Unknown Section]
[Page ]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-15595]


[Federal Register: June 28, 1994]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-NM-207-AD]


Airworthiness Directives; Canadair Model CL-600-1A11, -2A12, and 
-2B16 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.
ACTION: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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SUMMARY: This document revises an earlier proposed airworthiness 
directive (AD), applicable to certain Canadair Model CL-600-1A11, -
2A12, and -2B16 series airplanes, that would have required a test of 
the engine throttle quadrant to determine if the throttle lever 
bypasses the idle stop into the shut-off position, and modification of 
the throttle quadrant or replacement of the throttle quadrant with a 
modified unit. That proposal was prompted by reports of unintentional 
engine shutdown on certain of these airplanes. This action revises the 
proposed rule by requiring a different test and eventual replacement of 
the throttle quadrant. The actions specified by this proposed AD are 
intended to prevent inadvertent shutdown of an engine while the 
airplane is taxiing or in flight.

DATES: Comments must be received by August 2, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 93-NM-207-AD, 1601 Lind Avenue SW., Renton, 
Washington 98055-4056. Comments may be inspected at this location 
between 9 a.m. and 3 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule may be 
obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 
6087, Station A, Montreal, Quebec H3C 3G9, Canada. This information may 
be examined 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, Valley Stream, New York.

FOR FURTHER INFORMATION CONTACT: Raymond J. O'Neill, Aerospace 
Engineer, Propulsion Branch, ANE-174, FAA, Engine and Propeller 
Directorate, New York Aircraft Certification Office, 181 South Franklin 
Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791-
7421; fax (516) 791-9024.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 93-NM-207-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules 
Docket No. 93-NM-207-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056. Discussion
    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to 
certain Canadair Model CL-600-1A11, -2A12, and -2B16 series airplanes, 
was published as a notice of proposed rulemaking (NPRM) in the Federal 
Register on February 9, 1994 (59 FR 5966). That NPRM would have 
required a test of the engine throttle quadrant to determine if the 
throttle lever bypasses the idle stop into the shut-off position, and 
modification of the throttle quadrant or replacement of the throttle 
quadrant with a modified unit. That NPRM was prompted by reports of 
unintentional engine shutdown on Model CL-600-2A12 and -2B16 series 
airplanes. That condition, if not corrected, could result in 
inadvertent shutdown of an engine while the airplane is taxiing or in 
flight.
    Subsequent to the issuance of that NPRM, Transport Canada Aviation, 
which is the airworthiness authority for Canada, advised the FAA of an 
additional unsafe condition that may exist on these, and additional, 
airplanes. While performing a test of the engine throttle quadrant, one 
operator discovered that a quick, sharp pull of the throttle lever, 
combined with contamination of the surfaces of the idle stop plate and 
pawl, could result in inadvertent run-through of the lever past the 
idle stop and through the shut-off position. If this were to occur 
while the airplane was in flight or while taxiing, it could result in 
the inadvertent shutdown of the engines.
    Canadair has issued Challenger Service Bulletins 600-0629 (for 
Model CL-600-1A11 series airplanes) and 601-0410 (for Model CL-601-2A12 
and -2B16 series airplanes), both dated November 1, 1993. These service 
bulletins contain new procedures for conducting a check of the idle 
stop function of the throttle quadrant and procedures for cleaning, 
retesting, and/or replacement of the throttle quadrant, if necessary. 
These service bulletins also contain instructions for installing a 
modified throttle quadrant. Operators that have previously accomplished 
the check and/or modification of the throttle quadrants in accordance 
with Canadair Challenger Service Bulletin A600-0615, dated June 10, 
1992 (for Model CL-600-1A11 series airplanes), and Service Bulletin 
A601-0374 (for Model CL-600-2A12 and -2B16 series airplanes), Revision 
1, dated September 30, 1992, must re-check and replace in accordance 
with the new service bulletins. The new service bulletins list part 
numbers of additional affected throttle quadrants, and serial numbers 
of additional (Model CL-600-2B16) airplanes that may also be subject to 
the addressed unsafe condition.
    Transport Canada Aviation classified these service bulletins as 
mandatory and issued Canadian Airworthiness Directive CF-92-23R1, dated 
March 31, 1994, in order to assure the continued airworthiness of these 
airplanes in Canada.
    This airplane model is manufactured in Canada and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, Transport Canada Aviation has kept 
the FAA informed of the situation described above. The FAA has examined 
the findings of Transport Canada Aviation, reviewed all available 
information, and determined that AD action is necessary for products of 
this type design that are certificated for operation in the United 
States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would require a check of the idle 
stop function of the throttle quadrant, and repair or replacement of 
the throttle quadrant if the check fails. In addition, this proposed AD 
would require the eventual replacement of the throttle quadrant with a 
new model. The proposed actions would be required to be accomplished in 
accordance with the new service bulletins described previously. 
Additionally, the applicability of the proposed rule would be expanded 
to include additional airplanes that are subject to the addressed 
unsafe condition.
    Since these changes expand the scope of the originally proposed 
rule, the FAA has determined that it is necessary to reopen the comment 
period to provide additional opportunity for public comment.
    The FAA estimates that 150 airplanes of U.S. registry would be 
affected by this proposed AD.
    The proposed functional check of the throttle quadrant would take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $55 per work hour. Based on these figures, the total cost 
impact of the proposed functional check on U.S. operators is estimated 
to be $8,250, or $55 per airplane.
    The proposed installation of a modified throttle quadrant would 
take approximately 10 work hours per airplane to accomplish, at an 
average labor rate of $55 per work hour. Required parts would be 
provided by the manufacturer at no cost to operators. Based on these 
figures, the total cost impact of the proposed installation on U.S. 
operators is estimated to be $82,500, or $550 per airplane.
    Based on the figures discussed above, the total cost impact of this 
proposed AD on U.S. operators is estimated to be $90,750, or $605 per 
airplane. This total cost impact figure is based on assumptions that no 
operator has yet accomplished any of the proposed requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

CANADAIR: 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.
    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 150 hours time-in-service after the effective date of 
this AD, perform a functional test (check) of the idle stop function 
of the throttle quadrant in accordance with Part A of the 
Accomplishment Instructions of Canadair Challenger Service Bulletins 
A600-0629, dated November 1, 1993 (for Model CL-600-1A11 series 
airplanes), or A601-0410, dated November 1, 1993 (for Model CL-600-
2A12 and -2B16 series airplanes), as applicable. If the idle stop 
functional test fails, prior to further flight, repair or replace 
the throttle quadrant in accordance with the applicable service 
bulletin.
    (b) Within 1,200 flight hours after the effective date of this 
AD, replace the throttle quadrant in accordance with Part B of the 
Accomplishment Instructions of Canadair Challenger Service Bulletins 
A600-0629, dated November 1, 1993 (for Model CL-600-1A11 series 
airplanes), or A601-0410, dated November 1, 1993 (for Model CL-600-
2A12 and -2B16 series airplanes), as applicable.
    (c) Replacement of the throttle quadrant in accordance with Part 
B of the Accomplishment Instructions of Canadair Challenger Service 
Bulletins A600-0629, dated November 1, 1993 (for Model CL-600-1A11 
series airplanes), or A601-0410, dated November 1, 1993 (for Model 
CL-600-2A12 and -2B16 series airplanes), as applicable, constitutes 
terminating action for the requirements of this AD.
    (d) 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, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, 
Standardization Branch, ANM-113.

    Note: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (e) 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.

    Issued in Renton, Washington, on June 22, 1994. Original signed 
by:
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-15595 Filed 6-27-94; 8:45 am]
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