[Federal Register Volume 63, Number 131 (Thursday, July 9, 1998)]
[Rules and Regulations]
[Pages 37063-37065]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-13404]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-03-AD; Amendment 39-10487]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-215-6B11 (CL-415
Variant) Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Direct final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to all Bombardier Model CL-215-6B11 (CL-415 Variant)
series airplanes. This amendment requires revising the Airplane Flight
Manual (AFM) to provide the flightcrew with procedures to address a
temporary loss of battery bus power during engine failure and
consequent erroneous indications of hydraulic system
[[Page 37064]]
pressure, brake pressure, rudder pressure, and rudder and elevator
reversion to manual mode. This amendment is prompted by issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified in this AD are intended
to ensure that the flightcrew is advised of the potential hazard
associated with a temporary loss of battery bus power during failure of
the left engine or the left generator on the left engine and of the
procedures necessary to address it.
DATES: Effective October 7, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 7, 1998.
Comments for inclusion in the Rules Docket must be received on or
before August 10, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-03-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
Centre-ville, 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, 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: Rodrigo J. Huete, Flight Test Pilot,
Systems and Flight Test Branch, ANE-172, FAA, Engine and Propeller
Directorate, New York Aircraft Certification Office, 10 Fifth Street,
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7518;
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-415
Variant) series airplanes. TCA advises that the manufacturer discovered
a design anomaly in the course of reviewing the differences between the
CL-215 and CL-415 variants. This anomaly could result in a temporary
loss of battery bus power during failure of the left engine or the left
generator on the left engine and consequent erroneous indications of
hydraulic system pressure, brake pressure, rudder pressure, and rudder
and elevator reversion to manual mode. If the flightcrew receives such
erroneous indications, they would lack appropriate procedures to
address them. This condition, if not corrected, could result in the
flightcrew taking inappropriate actions which may adversely affect the
rudder and elevator control systems.
Explanation of Relevant Service Information
Bombardier (formerly Canadair) has issued Canadair CL-415 Airplane
Flight Manual (AFM) Temporary Revision No. 491/9, dated November 30,
1995, which describes procedures to advise the flightcrew of the
potential hazard associated with a temporary loss of battery bus power
during failure of the left engine or the left generator on the left
engine and of the procedures necessary to address it. TCA classified
this temporary revision to the AFM as mandatory and issued Canadian
airworthiness directive CF-96-02, dated January 25, 1996, 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 21.29) 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 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 ensure that the
flightcrew is advised of the potential hazard associated with a
temporary loss of battery bus power during failure of the left engine
or the left generator on the left engine and of the procedures
necessary to address it. This AD requires revising the Limitations and
Emergency Procedures Sections of the AFM by incorporating the
previously described temporary AFM revision to provide the flightcrew
with procedures to address erroneous indications of hydraulic system
pressure, brake pressure, rudder pressure, and rudder and elevator
reversion to manual mode during engine failure.
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.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it would require approximately 1 work hour to
accomplish the required AFM revision, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of this AD would
be $60 per airplane.
The Direct Final Rule Procedure
The FAA anticipates that this regulation will not result in adverse
or negative comment and, therefore, is issuing it as a direct final
rule. The requirements of this direct final rule address an unsafe
condition identified by a foreign civil airworthiness authority and do
not impose a significant burden on any operator. In accordance with 14
CFR 11.17, unless a written adverse or negative comment, or a written
notice of intent to submit an adverse or negative comment, is received
within the comment period, the regulation will become effective on the
date specified above. After the close of the comment period, the FAA
will publish a document in the Federal Register indicating that no
adverse or negative comments were received; at that time, the AD number
will be specified, and the date on which the final rule will become
effective will be confirmed. If the FAA does receive, within the
comment period, a written adverse or negative comment, or written
notice of intent to submit such a comment, a document withdrawing the
direct final rule will be published in the Federal Register, and a
notice of proposed rulemaking may be published with a new comment
period.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and an opportunity for public
[[Page 37065]]
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 98-NM-03-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, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is noncontroversial and
unlikely to result in adverse or negative comments. For reasons
discussed in the preamble, I certify that this regulation (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) if promulgated, 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 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:
Bombardier Inc. (Formerly Canadair): Amendment 39-10487. Docket 98-
NM-03-AD.
Applicability: All Bombardier Model CL-215-6B11 (CL-415 Variant)
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 ensure that the flightcrew is advised of the potential hazard
associated with a temporary loss of battery bus power during failure
of the left engine or the left generator on the left engine and of
the procedures necessary to address it, accomplish the following:
(a) Within 10 days after the effective date of this AD, revise
the Limitations and Emergency Procedures Sections of the Canadair
CL-415 Airplane Flight Manual (AFM) by inserting a copy of Canadair
Temporary Revision No. 491/9, dated November 30, 1995, into the AFM
to provide the flightcrew with procedures to address erroneous
indications of hydraulic system pressure, brake pressure, rudder
pressure, and rudder and elevator reversion to manual mode during
engine failure.
Note 2: When the temporary revision has been incorporated into
general revisions of the AFM, the general revisions may be inserted
into the AFM, provided the information contained in the general
revision is identical to that specified in Canadair Temporary
Revision No. 491/9.
(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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Manager, 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 AFM revision shall be done in accordance with Canadair
CL-415 Airplane Flight Manual Temporary Revision No. 491/9, dated
November 30, 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. 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 Aircraft Certification Office, 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 4: The subject of this AD is addressed in Canadian
airworthiness directive CF-96-02, dated January 25, 1996.
(e) This amendment becomes effective on October 7, 1998.
Issued in Renton, Washington, on May 14, 1998.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-13404 Filed 7-8-98; 8:45 am]
BILLING CODE 4910-13-U
