[Federal Register Volume 60, Number 40 (Wednesday, March 1, 1995)]
[Rules and Regulations]
[Pages 11020-11022]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-3246]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-NM-207-AD; Amendment 39-9143; AD 95-03-06]


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: 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.

DATES: Effective March 31, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 31, 1995.

ADDRESSES:  The service information referenced in this AD 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 Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 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.

FOR FURTHER INFORMATION CONTACT: Raymond J. O'Neill, Aerospace 
Engineer, Propulsion Branch, ANE-174, FAA, Engine and Propeller 
Directorate, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7421; 
fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: 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 per work 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. [[Page 11021]] 
    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.


Sec. 39.13  [Amended]

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

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 
Challenger Service 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, 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 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 
Secs. 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.

    [[Page 11022]] Issued in Renton, Washington, on February 3, 
1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-3246 Filed 2-28-95; 8:45 am]

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