[Federal Register Volume 75, Number 150 (Thursday, August 5, 2010)]
[Proposed Rules]
[Pages 47249-47251]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-19289]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0703; Directorate Identifier 2010-NM-040-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model CL-600-2B19
(Regional Jet Series 100 & 440) Airplanes, CL-600-2C10 (Regional Jet
Series 700, 701, & 702) Airplanes, CL-600-2D15 (Regional Jet Series
705) Airplanes, and CL-600-2D24 (Regional Jet Series 900) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
There have been failures of the harness assembly (power feeder
wires) connecting the Air-Driven Generator (ADG) to the aeroplane
electrical system, in the area close to the ADG cannon plug. Several
electrical wires were found cut as a combined result of corrosion
and bending stress from the harness mounting to the ADG.
The ADG electrical wires are insulated with a silver-plating for
corrosion protection. It has been determined that the silver-plating
of wire strands in the area of tight bend is highly susceptible to
breakdown. The plating layer may crack as a result of mechanical
stress, and consequently lead to the onset of corrosion on all, or a
majority, of the wire strands.
In the event of a damaged harness assembly, the ADG may not be
able to provide emergency electrical power to the aeroplane. * * *
The proposed AD would require actions that are intended to address
the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by September 20,
2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor,
[[Page 47250]]
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec
H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; e-mail
[email protected]; Internet http://www.bombardier.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at the
FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Assata Dessaline, Aerospace Engineer,
Avionics and Flight Test Branch, ANE-172, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7301; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0703;
Directorate Identifier 2010-NM-040-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We have lengthened the 30-day comment period for proposed ADs that
address MCAI originated by aviation authorities of other countries to
provide adequate time for interested parties to submit comments. The
comment period for these proposed ADs is now typically 45 days, which
is consistent with the comment period for domestic transport ADs.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2009-47, dated December 14, 2009 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
There have been failures of the harness assembly (power feeder
wires) connecting the Air-Driven Generator (ADG) to the aeroplane
electrical system, in the area close to the ADG cannon plug. Several
electrical wires were found cut as a combined result of corrosion
and bending stress from the harness mounting to the ADG.
The ADG electrical wires are insulated with a silver-plating for
corrosion protection. It has been determined that the silver-plating
of wire strands in the area of tight bend is highly susceptible to
breakdown. The plating layer may crack as a result of mechanical
stress, and consequently lead to the onset of corrosion on all, or a
majority, of the wire strands.
In the event of a damaged harness assembly, the ADG may not be
able to provide emergency electrical power to the aeroplane. This
directive is issued to correct the identified unsafe condition by
requiring [the modification of the ADG, which includes] the
replacement of the harness assembly with tin-plated electrical
wires, [the replacement of the backshell,] and the re-orientation of
the ADG cannon plug to reduce bending stress.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Bombardier, Inc. issued Service Bulletin 601R-24-128, Revision A,
dated November 27, 2009; and Service Bulletin 670BA-24-027, dated
September 17, 2009. The actions described in this service information
are intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 920 products of U.S. registry. We also estimate that
it would take about 8 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Required parts would cost about $1,881 per product. Where
the service information lists required parts costs that are covered
under warranty, we have assumed that there will be no charge for these
costs. As we do not control warranty coverage for affected parties,
some parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $2,356,120, or $2,561 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures
[[Page 47251]]
the Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses
an unsafe condition that is likely to exist or develop on products
identified in this rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect 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.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new AD:
Bombardier, Inc.: Docket No. FAA-2010-0703; Directorate Identifier
2010-NM-040-AD.
Comments Due Date
(a) We must receive comments by September 20, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.
(1) Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100
& 440) airplanes, serial numbers 7305 through 7990 inclusive, and
8000 through 8111 inclusive.
(2) Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700,
701, & 702) airplanes, serial numbers 10003 through 10302 inclusive.
(3) Bombardier, Inc. Model CL-600-2D15 (Regional Jet Series 705)
and CL-600-2D24 (Regional Jet Series 900) airplanes, serial numbers
15001 through 15259 inclusive.
Subject
(d) Air Transport Association (ATA) of America Code 24:
Electrical power.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
There have been failures of the harness assembly (power feeder
wires) connecting the Air-Driven Generator (ADG) to the aeroplane
electrical system, in the area close to the ADG cannon plug. Several
electrical wires were found cut as a combined result of corrosion
and bending stress from the harness mounting to the ADG.
The ADG electrical wires are insulated with a silver-plating for
corrosion protection. It has been determined that the silver-plating
of wire strands in the area of tight bend is highly susceptible to
breakdown. The plating layer may crack as a result of mechanical
stress, and consequently lead to the onset of corrosion on all, or a
majority, of the wire strands.
In the event of a damaged harness assembly, the ADG may not be
able to provide emergency electrical power to the aeroplane. * * *
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Actions
(g) Within 6,000 flight hours or 72 months after the effective
date of this AD, whichever occurs first, do the applicable actions
specified in paragraph (g)(1) or (g)(2) of this AD.
(1) For Model CL-600-2B19 (Regional Jet Series 100 & 440)
airplanes: Modify the air-driven generator (ADG) in accordance with
the Accomplishment Instructions of Bombardier Service Bulletin 601R-
24-128, Revision A, dated November 27, 2009.
(2) For Model CL-600-2C10 (Regional Jet Series 700, 701, & 702),
CL-600-2D15 (Regional Jet Series 705), and CL-600-2D24 (Regional
Jet Series 900) airplanes: Modify the ADG in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 670BA-24-
027, dated September 17, 2009.
(h) Actions accomplished before the effective date of this AD
according to Bombardier Service Bulletin 601R-24-128, dated
September 17, 2009, are considered acceptable for compliance with
the corresponding action specified in this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service
information as follows: No differences.
Other FAA AD Provisions
(i) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office, ANE-170, FAA, has the authority
to approve AMOCs for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to ATTN: Program Manager,
Continuing Operational Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, New York 11590; telephone 516-228-7300;
fax 516-794-5531. Before using any approved AMOC on any airplane to
which the AMOC applies, notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI), as appropriate, or
lacking a principal inspector, your local Flight Standards District
Office. The AMOC approval letter must specifically reference this
AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(j) Refer to MCAI Canadian Airworthiness Directive CF-2009-47,
dated December 14, 2009; Bombardier Service Bulletin 601R-24-128,
Revision A, dated November 27, 2009; and Bombardier Service Bulletin
670BA-24-027, dated September 17, 2009; for related information.
Issued in Renton, Washington, on July 27, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-19289 Filed 8-4-10; 8:45 am]
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