[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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