[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]
BILLING CODE 4910-13-U