[Federal Register Volume 63, Number 44 (Friday, March 6, 1998)]
[Rules and Regulations]
[Pages 11108-11110]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-5347]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-328-AD; Amendment 39-10372; AD 98-05-11]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-215-6B11 (CL-215T)
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 Bombardier Model CL-215-6B11 (CL-215T) series
airplanes. This action requires either replacement of the switching
valve-to-rear inlet case sealing air tube assembly with a tube assembly
that includes an integral fire detector (intercompressor case [ICC]
fire detector loop), and modification of the nacelle fire detection
system; or modification of the No. 5 bearing air system. This amendment
is prompted by the issuance of mandatory continuing airworthiness
information by a foreign civil airworthiness authority. The actions
specified in this AD are intended to detect internal engine fire within
the ICC; or to prevent air/oil from leaking into the ICC, which could
result in such fire.
DATES: Effective March 23, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 23, 1998.
Comments for inclusion in the Rules Docket must be received on or
before April 6, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-328-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
[[Page 11109]]
The service information referenced in this AD may be obtained from
Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station
Centreville, Montreal, Quebec H3C 3G9, Canada; and Pratt & Whitney, 400
Main Street, East Hartford, Connecticut 06108. 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 (ACO), 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: James E. Delisio, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, Engine and Propeller
Directorate, New York ACO, 10 Fifth Street, Third Floor, Valley Stream,
New York, 11581-1200; telephone (516) 256-7521; fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: Transport Canada Aviation (TCA), which is
the airworthiness authority for Canada, notified the FAA that an unsafe
condition may exist on all Bombardier Model CL-215-6B11 (CL-215T)
series airplanes. TCA advises that it has received reports of five
incidents of internal engine fire that had penetrated the
intercompressor case (ICC) and required extinguishing by the flight
crew. Investigation revealed failures of the No. 5 engine bearing,
which could cause oil leakage or reverse flow of air or oil into the
ICC. This condition, if not corrected, could result in internal engine
fire within the ICC.
Explanation of Relevant Service Information
Pratt & Whitney Canada has issued Service Bulletin PW100-72-21113,
Revision 1, dated May 4, 1992, which describes procedures for
replacement of the switching valve-to-rear inlet case sealing air tube
assembly with a tube assembly that includes an integral fire detector
(ICC fire detector loop).
Canadair has issued Alert Service Bulletin 215-A3030, Revision 1,
dated April 16, 1992, which describes procedures for installation of an
ICC fire detector loop (as described above) and modification of the
nacelle fire detection system.
Pratt & Whitney Canada also has issued Service Bulletin PW100-72-
21211, Revision 4, dated April 20, 1995, which describes procedures for
a modification of the No. 5 bearing air system that will minimize the
risk of internal engine fire.
Accomplishment of the actions specified in these service bulletins
is intended to adequately address the identified unsafe condition. TCA
classified the service bulletins as mandatory and issued Canadian
airworthiness directive CF-92-10R1, dated January 24, 1995, in order to
assure the continued airworthiness of these airplanes in Canada.
FAA's Conclusions
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, TCA has kept the FAA informed of the
situation described above. The FAA has examined the findings of TCA,
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.
Explanation of Requirements of the Rule
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 require the actions to
be accomplished as specified in the service bulletins described
previously.
Cost Impact
None of the 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 subject airplanes
are imported and placed on the U.S. Register in the future. In that
event, the following cost estimates are provided.
It would require approximately 9 work hours to accomplish the
required incorporation of the engine fire detection loop, at an average
labor rate of $60 per work hour. Required parts would cost
approximately $985. Based on these figures, the cost impact of this
action would be $1,525 per airplane.
It would require approximately 45 work hours to accomplish the
required modification of the No. 5 bearing air system, at an average
labor rate of $60 per work hour. Required parts would cost
approximately $225,000. Based on these figures, the cost impact of this
action would be $227,700 per airplane.
Determination of Rule's Effective Date
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, prior 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 97-NM-328-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
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,
[[Page 11110]]
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:
98-05-11 Bombardier, Inc. [Formerly Canadair]: Amendment 39-10372.
Docket 97-NM-328-AD.
Applicability: All Model CL-215-6B11 (CL-215T) 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 detect internal engine fire within the intercompressor case
(ICC); or to prevent air/oil from leaking into the ICC, which could
result in such fire; accomplish the following:
(a) Within 30 days after the effective date of this AD,
accomplish either paragraph (a)(1) or (a)(2) of this AD.
(1) Replace the switching valve-to-rear inlet case sealing air
tube assembly with a tube assembly that includes an integral fire
detector (ICC fire detector loop), in accordance with Pratt &
Whitney Canada Service Bulletin PW100-72-21113, Revision 1, dated
May 4, 1992; and modify the nacelle fire detection system in
accordance with Canadair Alert Service Bulletin 215-A3030, Revision
1, dated April 16, 1992, or
(2) Modify the No. 5 bearing air system in accordance with Pratt
& Whitney Canada Service Bulletin PW100-72-21211, Revision 4, dated
April 20, 1995.
(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 actions shall be done in accordance with Canadair Alert
Service Bulletin 215-A3030, Revision 1, dated April 16, 1992; Pratt
& Whitney Canada Service Bulletin PW100-72-21113, Revision 1, dated
May 4, 1992; and Pratt & Whitney Canada Service Bulletin PW100-72-
21211, Revision 4, dated April 20, 1995. 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 Centreville, Montreal, Quebec H3C 3G9, Canada; and
Pratt & Whitney, 400 Main Street, East Hartford, Connecticut 06108.
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, 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.
Note 3: The subject of this AD is addressed in Canadian
airworthiness directive CF-92-10R1, dated January 24, 1995.
(e) This amendment becomes effective on March 23, 1998.
Issued in Renton, Washington, on February 24, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-5347 Filed 3-5-98; 8:45 am]
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