[Federal Register Volume 61, Number 46 (Thursday, March 7, 1996)]
[Rules and Regulations]
[Pages 9090-9091]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-5078]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-272-AD; Amendment 39-9532; AD 96-05-06]
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 adopts a new airworthiness directive (AD),
applicable to all Canadair Model CL-215-1A10 series airplanes. This
action requires a one-time inspection of the main distribution center
for loose or missing attachment hardware, and correction of any
discrepancy identified. This amendment is prompted by a report of total
loss of electrical power on one airplane during flight, which was
caused by shorting out of the voltage regulator in the main
distribution center. The actions specified in this AD are intended to
prevent total electrical failure during flight, which could adversely
affect the continued safe flight of the airplane.
DATES: Effective March 22, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 22, 1996.
Comments for inclusion in the Rules Docket must be received on or
before May 6, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-272-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
Centreville, 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, New York Aircraft Certification
Office, Engine and Propeller Directorate, 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: Peter Cuneo, Aerospace Engineer,
Systems and Equipment Branch, ANE-173, FAA, New York Aircraft
Certification Office, Engine and Propeller Directorate, 10 Fifth
Street, Third Floor, Valley Stream, New York 11581; telephone (516)
256-7506; fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: Transport Canada Aviation, which is the
airworthiness authority for Canada, has notified the FAA that an unsafe
condition may exist on all Canadair Model CL-215-1A10 series airplanes.
Transport Canada Aviation advises that there has been a report of the
total loss of electrical power on one airplane during flight.
Investigation revealed that the electrical failure occurred when loose
hardware (nut and washers) on a terminal from an inverter power relay
shorted out a voltage regulator in the main distribution center. Total
loss of electrical power during flight, if not corrected, could
adversely affect the continued safe flight of the airplane.
Canadair has issued Alert Service Bulletin 215-A439, dated July 24,
1991, which describes procedures for inspecting the main distribution
center and all electrical components for loose attaching hardware, and
for inspecting the attaching hardware itself for looseness. It also
provides instructions for:
1. verifying and adjusting the torque values of those items;
2. restoring or applying a humiseal coating at required locations;
3. safety-wiring electrical connectors and components, as
necessary; and
4. removing any loose hardware, lockwire, or foreign objects found
between electrical wires, around electrical components, and at the
bottom or hidden areas of the main distribution center.
Transport Canada Aviation classified this service bulletin as
mandatory and issued Canadian Airworthiness Directive CF-91-23, dated
July 17, 1991, in order to assure 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
section 21.29 of the Federal Aviation Regulations (14 CFR 21.19) 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 registered
in the United States, this AD is being issued to prevent total loss of
electrical power on the airplane. This AD requires a one-time
inspection to detect looseness of components and attaching hardware of
the main distribution center, and correction of any discrepancy
identified. The actions are required to be accomplished in accordance
with the service bulletin described previously.
None of the Model CL-215-1A10 series airplanes affected by this
action are on the U.S. Register. All airplanes included in the
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 this rule is necessary
to ensure that the unsafe condition is addressed in the event that any
of these
[[Page 9091]]
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 2 work hours to
accomplish the required actions, at an average labor charge of $60 per
work hour. Based on these figures, the cost impact of this AD would be
$120 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
Although 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 rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 95-NM-272-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 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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
96-05-06 Canadair: Amendment 39-9532. Docket 95-NM-272-AD.
Applicability: Model CL-215-1A10 series airplanes, 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 request approval for an
alternative method of compliance in accordance with paragraph (b) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent total loss of electrical power on the airplane,
accomplish the following:
(a) Within 10 flight hours after the effective date of this AD,
inspect the complete main distribution center and all electrical
components for loose or missing hardware, in accordance with
paragraphs 2.A., 2.B., 2.C., and 2.D of the Accomplishment
Instructions of Canadair Alert Service Bulletin 215-A439, dated July
24, 1991. If any discrepancy is identified during the inspection,
prior to further flight, correct the discrepancy in accordance with
the alert service bulletin.
(b) 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(c) 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.
(d) The inspection and corrective action shall be done in
accordance with Canadair Alert Service Bulletin 215-A439, dated July
24, 1991. 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 Centre-ville,
Quebec H3C 3G9, Canada. Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, New York Aircraft Certification Office,
Engine and Propeller Directorate, 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.
(e) This amendment becomes effective on March 22, 1996.
Issued in Renton, Washington, on February 28, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-5078 Filed 3-6-96; 8:45 am]
BILLING CODE 4910-13-U
