Airworthiness Directives; Canadair Model CL-215-1A10 Series Airplanes

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.

-----------------------------------------------------------------------

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