[Federal Register Volume 59, Number 201 (Wednesday, October 19, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-25845]


[[Page Unknown]]

[Federal Register: October 19, 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 supplemental proposed 
airworthiness directive (AD), applicable to certain Canadair Model CL-
600-1A11, -2A12, and -2B16 series airplanes, that would have required a 
functional check of the idle stop function of the engine throttle 
quadrant; repair or replacement, if necessary; and eventual replacement 
of the engine throttle quadrant. That proposal was prompted by reports 
of unintentional engine shutdown on certain of these airplanes due to 
problems associated with operation of the engine throttle quadrant. 
This action further revises the proposed rule by adding a second type 
of test of the engine throttle quadrant to determine if the throttle 
levers bypass the idle stop into the shut-off position. The actions 
specified by this proposed 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: Comments must be received by November 23, 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 9:00 a.m. and 3:00 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 Centre-ville, 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 supplemental notice of proposed rulemaking (NPRM) in 
the Federal Register on June 28, 1994 (59 FR 33233). That supplemental 
NPRM would have required a functional check of the idle stop function 
of the throttle quadrant; repair or replacement of the throttle 
quadrant if the check failed; and the eventual replacement of the 
throttle quadrant with a new model. In addition, that supplemental NPRM 
expanded the applicability of the initially-issued NPRM to include 
additional airplanes that were found to be subject to the addressed 
unsafe condition.
    That supplemental NPRM was prompted by reports of unintentional 
engine shutdown that occurred on Model CL-600-2A12 and -2B16 series 
airplanes when a throttle lever over-rode the idle stop during throttle 
retardation, due to a quick, sharp pull on the throttle levers, and the 
throttle lever consequently moved directly to the shut-off position. 
The proposed functional check (hereafter called ``the abrupt-movement 
check'') was intended to ensure that such unintentional shutdowns of 
engines would not occur while the airplane is taxiing or in flight. The 
abrupt-movement check procedures are described in Canadair Challenger 
Service Bulletins A600-0629 and A601-0410, both dated November 1, 1993.
    Subsequent to the issuance of that supplemental NPRM, the FAA 
became aware that a necessary requirement, which was previously 
proposed in the initially-issued NPRM, was incorrectly omitted from the 
supplemental NPRM. The original NPRM was published in the Federal 
Register on February 9, 1994, (59 FR 5966). That action would have 
required operators to test the engine throttle quadrant to determine if 
the throttle levers bypass the idle stop into the shut-off position due 
to side loads on the throttle levers; quadrants that failed the test 
(hereafter called ``the side-load test'') would be required to be 
modified or replaced. Those actions would have been required to be 
accomplished in accordance with the instructions contained in 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).
    The FAA has determined that performance of this side-load test is 
necessary in order to adequately address the unsafe condition presented 
by the problems identified with the operation of the engine throttle 
quadrant.
    Operators should note that the originally-issued NPRM would have 
required that throttle quadrants failing the side-load test be modified 
in accordance with the Canadair service bulletins released in 1992 
(referred to above). However, in accordance with the recommendations of 
the Canadair service bulletins released in November 1993 (referred to 
above), throttle quadrants that failed the abrupt-movement check would 
be replaced with a new unit. The FAA has determined that it is not 
logical to require that the throttle quadrants be modified if they fail 
the side-load test and subsequently be replaced by a new unit if they 
fail the abrupt-movement check. The FAA has determined, instead, that 
both the side-load test and the abrupt-movement check must be 
performed, and units that fail either test must be replaced in 
accordance with the Canadair service bulletins dated November 1993. 
(Units that pass the tests would be required eventually to be replaced 
at a later time.)
    Additionally, the compliance time for the proposed eventual 
replacement of the engine throttle quadrant on all airplanes was 
incorrectly expressed in the previous supplemental NPRM as ``1,200 
flight hours.'' The compliance time for this proposed requirement 
should have been specified as ``4,500 hours time-in-service.'' (The 
``1,200'' figure actually represented the number of landings that is 
approximately equivalent to 4,500 hours time-in-service for the 
majority of the affected fleet.)
    This airplane model is manufactured in Canada and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement.
    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, this supplemental NPRM would require:
    1. A one-time test of the engine throttle quadrant to determine if 
side loads on the throttles will cause the throttle levers to bypass 
the idle stop into the shut-off position, and replacement of the 
throttle quadrant if it fails this test;
    2. A one-time functional check of the engine throttle quadrant to 
determine if a quick, sharp pull on the throttles will cause the 
throttle levers to bypass the idle stop into the shut-off position, and 
replacement of the throttle quadrant if it fails this functional check; 
and
    3. Replacement of the throttle quadrant as terminating action for 
the requirements of this AD.
    Additionally, paragraph (e) of this supplemental NPRM indicates the 
corrected compliance time of ``4,500 hours time-in-service'' for 
replacement of the throttle quadrant. Expressing this compliance time 
in terms of ``hours time-in-service'' makes it consistent with the 
compliance terms for the other requirements of this proposed AD.
    Since certain of these changes expand the scope of the previously 
proposed rule, the FAA has determined that it is necessary to reopen 
the comment period to provide additional opportunity for public 
comment.

Cost Impact

    The FAA estimates that 150 airplanes of U.S. registry would be 
affected by this proposed AD.
    The proposed side-loads test of the engine throttle quadrant would 
take approximately 17 work hours per airplane to accomplish the 
proposed actions, and that the average labor rate is $55 per work hour. 
Based on these figures, the total cost impact of this proposed 
requirement on U.S. operators is estimated to be $140,250, or $935 per 
airplane.
    The proposed abrupt-movement check of the idle stop function 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 $231,000, or $1,540 
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.

Regulatory Impact

    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 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 1: 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 A600-0629, dated November 1, 
1993 (for Model CL-600-1A11 series airplanes); or Canadair 
Challenger Service Bulletin A601-0410, 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 A600-0629, 
dated November 1, 1993 (for Model CL-600-1A11 series airplanes); or 
Canadair Challenger Service Bulletin A601-0410, dated November 1, 
1993 (for Models CL-600-2A12 and -2B16 series airplanes); as 
applicable.

    Note 2: 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 A600-0629 or A601-0410, 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 A600-0629, dated November 1, 1993 (for Model CL-600-1A11 
series airplanes); or Canadair Challenger Service Bulletin A601-
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, 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (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.

    Issued in Renton, Washington, on October 13, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-25845 Filed 10-18-94; 8:45 am]
BILLING CODE 4910-13-U