[Federal Register Volume 75, Number 105 (Wednesday, June 2, 2010)]
[Proposed Rules]
[Pages 30740-30742]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-13230]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 75, No. 105 / Wednesday, June 2, 2010 /
Proposed Rules
[[Page 30740]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0439; Directorate Identifier 2010-NM-029-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model CL-600-2B16 (CL-
604 Variants (Including CL-605 Marketing Variant)) 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: Following five reported cases of balance washer screw
failure on similar ADGs [air-driven generators]/ram air turbines
installed on other aircraft types, investigation by Hamilton Sundstrand
determined that a specific batch of the screws had a metallographic
non-conformity that increased their susceptibility to brittle fracture.
Failure of a balance washer screw can result in loss of the related
balance washer, with consequent turbine imbalance. Such imbalance could
potentially result in ADG structural failure (including blade failure),
loss of ADG electrical power and structural damage to the aircraft and,
if deployment was activated by a dual engine shutdown, could also
result in loss of hydraulic power for the flight controls [and
consequent reduced ability of the flightcrew to maintain the safe
flight and landing of the airplane]. 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 July 19, 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, 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: Christopher Alfano, Aerospace
Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New
York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone (516) 228-7340; 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-2010-0439;
Directorate Identifier 2010-NM-029-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-
2009-50, dated December 17, 2009 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
Following five reported cases of * * * balance washer screw
failure on similar ADGs [air-driven generators]/ram air turbines
installed on other aircraft types, investigation by Hamilton
Sundstrand determined that a specific batch of the screws had a
metallographic non-conformity that increased their susceptibility to
brittle fracture. Subsequently, it was established that 152 ``dry''
ADGs [Hamilton Sundstrand Part Numbers (P/Ns) in the 761339 series
and 1711405; see Note] either had non-conforming screws installed
during production or possibly during maintenance or repair at
Hamilton Sundstrand repair stations.
Failure of a balance washer screw can result in loss of the
related balance washer, with consequent turbine imbalance. Such
imbalance could potentially result in ADG structural failure
(including blade failure), loss of ADG electrical power and
structural
[[Page 30741]]
damage to the aircraft and, if deployment was activated by a dual
engine shutdown, could also result in loss of hydraulic power for
the flight controls [and consequent reduced ability of the
flightcrew to maintain the safe flight and landing of the airplane].
This [Canadian] directive mandates checking of the ADG and
replacing the balance washer screws, if required. It also prohibits
future installation of unmodified ADGs.
Note: ADGs with Hamilton Sundstrand P/Ns in the 761339 series
and 1711405 are installed on the aircraft model listed in the
Applicability section above in addition to Bombardier Inc. Models
CL-600-2B19, CL-600-2C10 and CL-600-2D24. The latter three models
are covered in a separate directive.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Bombardier has issued Service Bulletins 604-24-021 and 605-24-001,
both dated July 13, 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 155 products of U.S. registry. We also estimate that
it would take about 10 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 $0 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 $131,750, or $850 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 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-2010-0439; Directorate Identifier
2010-NM-029-AD.
Comments Due Date
(a) We must receive comments by July 19, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier, Inc. Model CL-600-2B16 (CL-
604 Variant) airplanes; certificated in any category; serial numbers
(S/N) 5408 and subsequent.
Note 1: Some Model CL-600-2B16 (CL-604 Variant) airplanes might
be referred to by a marketing designation of CL-605.
Subject
(d) Air Transport Association (ATA) of America Code 24:
Electrical power.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Following five reported cases of * * * balance washer screw
failure on similar ADGs [air-driven generators]/ram air turbines
installed on other aircraft types, investigation by Hamilton
Sundstrand determined that a specific batch of the screws had a
metallographic non-conformity that increased their susceptibility to
brittle fracture. Subsequently, it was established that 152 ``dry''
ADGs [Hamilton Sundstrand Part Numbers (P/Ns) in the 761339 series
and 1711405; see Note] either had non-conforming screws installed
during production or possibly during maintenance or repair at
Hamilton Sundstrand repair stations.
Failure of a balance washer screw can result in loss of the
related balance washer, with consequent turbine imbalance. Such
imbalance could potentially result in ADG structural failure
(including blade failure), loss of ADG electrical power and
structural damage to the aircraft and, if deployment was
[[Page 30742]]
activated by a dual engine shutdown, could also result in loss of
hydraulic power for the flight controls [and consequent reduced
ability of the flightcrew to maintain the safe flight and landing of
the airplane].
This [Canadian] directive mandates checking of the ADG and
replacing the balance washer screws, if required. It also prohibits
future installation of unmodified ADGs.
Note: ADGs with Hamilton Sundstrand P/Ns in the 761339 series
and 1711405 are installed on the aircraft model listed in the
Applicability section above in addition to Bombardier Inc. Models
CL-600-2B19, CL-600-2C10 and CL-600-2D24. The latter three models
are covered in a separate directive.
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) At the earliest of the times identified in paragraphs
(g)(1), (g)(2), (g)(3), and (g)(4) of this AD, do an inspection to
determine the serial number of the installed ADG. A review of
airplane maintenance records is acceptable in lieu of this
inspection if the serial number of the ADG can be conclusively
determined from that review.
(1) Within 400 flight hours or 12 months after the effective
date of this AD, whichever occurs first, or
(2) Prior to the next in-flight or on-ground functional test of
the ADG, whichever occurs first after the effective date of this AD,
or
(3) Prior to the next in-flight or on-ground operational test of
the ADG, whichever occurs first after the effective date of this AD,
or
(4) Prior to the next scheduled ADG in-flight deployment.
(h) If the ADG serial number, as determined in paragraph (g) of
this AD, is not listed in paragraph 1.A of the applicable Bombardier
Service Bulletin listed in Table 1 of this AD, no further action is
required by this AD, except for paragraph (j) of this AD.
Table 1--Service Bulletins
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Model-- Bombardier service bulletin-- Dated--
----------------------------------------------------------------------------------------------------------------
CL-600-2B16 (CL-604) airplanes......... 604-24-021......................... July 13, 2009.
CL-600-2B16 (CL-605) airplanes......... 605-24-001......................... July 13, 2009.
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(i) If the ADG serial number determined in paragraph (g) of
this AD is identified in paragraph 1.A. of the applicable service
bulletin listed in Table 1 of this AD, before further flight, do an
inspection to determine if the symbol ``24-5'' is marked on the ADG
identification plate. A review of airplane maintenance records is
acceptable in lieu of this inspection if the symbol ``24-5'' can be
conclusively determined from that review.
(1) If the symbol ``24-5'' is marked on the ADG identification
plate, and the balance washer screws have already been replaced, no
further action is required by this AD, except for paragraph (j) of
this AD.
(2) If the symbol ``24-5'' is not marked on the ADG
identification plate, before further flight, replace all balance
washer screws with new screws having part number MS24667-14 and mark
the ADG identification plate with symbol ``24-5,'' in accordance
with the Accomplishment Instructions of the applicable service
bulletin listed in Table 1 of this AD.
(j) As of the effective date of this AD, no person may install
on any airplane a replacement or spare ADG, Hamilton Sundstrand part
number in the 761339 or 1711405 series, having one of the serial
numbers identified in paragraph 1.A. of the applicable service
bulletin listed in Table 1 of this AD, unless the ADG is identified
with the symbol ``24-5'' on the identification plate.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service
information as follows: The MCAI specifies to inspect only airplanes
having certain serial numbers that are part of the MCAI
applicability. Because the affected part could be rotated onto any
of the airplanes listed in the applicability, this AD requires the
inspection be done on all airplanes. We have coordinated this
difference with TCCA.
Other FAA AD Provisions
(k) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), 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
(l) Refer to MCAI Canadian Airworthiness Directive CF-2009-50,
dated December 17, 2009; and Bombardier Service Bulletins 604-24-
021, dated July 13, 2009, and 605-24-001, dated July 13, 2009; for
related information.
Issued in Renton, Washington, on April 30, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-13230 Filed 6-1-10; 8:45 am]
BILLING CODE 4910-13-P