[Federal Register Volume 59, Number 30 (Monday, February 14, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-3349]
[[Page Unknown]]
[Federal Register: February 14, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-NM-09-AD; Amendment 39-8826; AD 93-16-06 R1]
Airworthiness Directives; Canadair Model CL-215-1A10 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment revises an existing airworthiness directive
(AD), applicable to certain Canadair Model CL-215-1A10 series
airplanes, that currently requires modification of the right aileron
and aileron tab. That AD was prompted by an updated flutter analysis
performed by the manufacturer, which revealed a potential flutter
condition on these airplanes. The actions specified in that AD are
intended to prevent potential flutter of the rudder-aileron
interconnect tab, which could result in reduced controllability of the
airplane. This amendment revises the applicability of the rule by
adding additional airplanes that are subject to the addressed unsafe
condition.
DATES: March 1, 1994.
The incorporation by reference of Canadair Alert Service Bulletin
215-A435, dated August 14, 1990, listed in the regulations, was
approved previously by the Director of the Federal Register as of
October 4, 1993 (58 FR 46766, September 3, 1993).
Comments for inclusion in the Rules Docket must be received on or
before April 15, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-09-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
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 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, room 202,
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: Jeff Casale, Aerospace Engineer,
Airframe Branch, ANE-172, FAA, Engine and Propeller Directorate, New
York Aircraft Certification Office, 181 South Franklin Avenue, room
202, Valley Stream, New York 11581; telephone (516) 791-6220; fax (516)
791-9024.
SUPPLEMENTARY INFORMATION: On August 13, 1993, the FAA issued AD 93-16-
06, Amendment 39-8663 (58 FR 46766, September 3, 1993), applicable to
certain Canadair Model CL-215-1A10 series airplanes, to require
installing weights to the aileron balance weight mounting channel and
installing washers to the interconnect tab mass balance arms. That
modification will maintain an aileron control surface mass balance
within specified limits. That action was prompted by an updated flutter
analysis, performed by Canadair during the development of the Model CL-
215-6B11 turboprop airplane, which revealed that a potential flutter
condition affecting the rudder-aileron interconnect tab could occur on
certain Canadair Model CL-215-1A10 series airplanes. (The Model CL-215-
6B11 is a Model CL-215-1A10 that has been converted from piston engine
power to turbopropeller power.) This flutter analysis further revealed
that, if the rudder-aileron interconnect mechanism fails, a flutter
condition could occur at pressure altitudes above 10,000 feet. The
actions required by that AD are intended to prevent potential flutter
of the rudder-aileron interconnect tab, which could result in reduced
controllability of the airplane.
AD 93-16-06 is applicable only to Canadair Model CL-215-1A10 series
airplanes that are not equipped with powered ailerons. Since issuance
of that AD, however, Transport Canada Aviation, which is the
airworthiness authority for Canada, has advised that additional
airplanes may be subject to the same unsafe condition addressed by the
previous AD action. Further analysis has indicated that the flutter
problems associated with the rudder-aileron interconnect tab may occur
on all Canadair Model CL-215-1A10 series airplanes, including those
equipped with powered ailerons.
Transport Canada Aviation revised Canadian AD CF-90-11, dated June
26, 1990, to require installation of the aileron modification on all
Model CL-215-1A10 series airplanes, thereby assuring 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
Sec. 21.29 of the Federal Aviation Regulations 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, this AD is
being issued to prevent potential flutter of the rudder-aileron
interconnect tab, which could result in reduced controllability of the
airplane. This AD expands the applicability of the current rule to
include all Model CL-215-1A10 series airplanes. The requirements of the
current rule remain unchanged. (The AD requires modification of the
right aileron and aileron tab.)
There currently are no Model CL-215-1A10 series airplanes on the
U.S. Register. All airplanes included in the revised applicability of
this rule currently are operated by non-U.S. operators under foreign
registry; therefore, they are not directly affected by this AD action.
However, the FAA considers that the revision to the applicability of
the rule is necessary to ensure that the unsafe condition is addressed
in the event that any of these subject airplanes are imported and
placed on the U.S. Register in the future.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it would require approximately 20 work hours to
accomplish the required actions, at an average labor charge of $55 per
work hour. Based on these figures, the total cost impact of this AD
would be $1,100 per airplane.
Since this AD action does not affect any airplane that is currently
on the U.S. register, it has no adverse economic impact and imposes no
additional burden on any person. Therefore, notice and public
procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
Comments Invited
Athough this action is in the form of a final rule and was not
preceded by notice and opportunity for public comment, comments are
invited on this rule. Interested persons are invited to comment on this
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 under the caption
``ADDRESSES.'' All communications received on or before the closing
date for comments will be considered, and this rule may be amended in
light of the comments received. Factual information that supports the
commenter's ideas and suggestions is extremely helpful in evaluating
the effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD 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 94-NM-09-AD.'' The postcard will be date stamped and
returned to the commenter.
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 14 CFR part
39 of the Federal Aviation Regulations 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 removing amendment 39-8663 (58 FR
46766, September 3, 1993), and by adding a new airworthiness directive
(AD), amendment 39-8826, to read as follows:
93-16-06 R1 Canadair: Amendment 39-8826. Docket 94-NM-09-AD. Revises
AD 93-16-06, Amendment 39-8663.
Applicability: All Model CL-215-1A10 series airplanes,
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent potential flutter of the rudder-aileron interconnect
tab, which could result in reduced controllability of the airplane,
accomplish the following:
(a) For Model CL-215-1A10 series airplanes; serial numbers 1001
through 1125 inclusive, not equipped with powered ailerons: Within
12 months after October 4, 1993 (the effective date of AD 93-16-06,
amendment 39-8663), on the right wing install weights to the aileron
balance weight mounting channel and washers to the interconnect tab
mass balance arms, in accordance with Canadair Alert Service
Bulletin 215-A435, dated August 14, 1990.
(b) For all other airplanes not subject to paragraph (a) of this
AD: Within 12 months after the effective date of this AD, on the
right wing install weights to the aileron balance weight mounting
channel and washers to the interconnect tab mass balance arms, in
accordance with Canadair Alert Service Bulletin 215-A435, dated
August 14, 1990.
(c) 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: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(d) Special flight permits may be issued in accordance with
Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate the
airplane to a location where the requirements of this AD can be
accomplished.
(e) The installation shall be done in accordance with Canadair
Alert Service Bulletin 215-A435, dated August 14, 1990. The
incorporation by reference of this document was approved previously
by the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51 as of October 4, 1993 (58 FR 46766,
September 3, 1993). 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 ACO, 181 South Franklin Avenue, room 202, Valley Stream, New
York; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
(f) This amendment becomes effective on March 1, 1994.
Issued in Renton, Washington, on February 8, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-3349 Filed 2-11-94; 8:45 am]
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