[Federal Register Volume 75, Number 216 (Tuesday, November 9, 2010)]
[Proposed Rules]
[Pages 68728-68731]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-28275]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1108; Directorate Identifier 2010-NM-151-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model CL-215-1A10 (CL-
215), CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 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:
Seven cases of on-ground hydraulic accumulator screw cap or end
cap failure have been experienced * * * resulting in loss of the
associated hydraulic system and high-energy impact damage to
adjacent systems and structure. * * *
* * * * *
A detailed analysis of the systems and structure in the
potential line of trajectory of a failed screw cap/end cap for each
accumulator has been conducted. It has identified that the worst-
case scenarios would be impact damage to various components,
potentially resulting in fuel spillage, uncommanded flap movement,
or loss of aileron control [and consequent reduced controllability
of the airplane].
* * * * *
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
[[Page 68729]]
DATES: We must receive comments on this proposed AD by December 27,
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-2010-1108;
Directorate Identifier 2010-NM-151-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 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-
2009-42R1, dated May 14, 2010 (referred to after this as ``the MCAI''),
to correct an unsafe condition for the specified products. The MCAI
states:
* * * * *
Seven cases of on-ground hydraulic accumulator screw cap or end
cap failure have been experienced on CL-600-2B19 (CRJ) aircraft,
resulting in loss of the associated hydraulic system and high-energy
impact damage to adjacent systems and structure. To date, the lowest
number of flight cycles accumulated at the time of failure has been
6991.
Although there have been no failures to date on any CL-215-1A10
(CL-215) or CL-215-6B11 (CL-215T and CL-415) aircraft, similar
accumulators, Part Number (P/N) 08-8423-010 (MS28700-3), to those
installed on the CL-600-2B19, are installed on the aircraft listed
in the Applicability section of this directive [MCAI].
A detailed analysis of the systems and structure in the
potential line of trajectory of a failed screw cap/end cap for each
accumulator has been conducted. It has identified that the worst-
case scenarios would be impact damage to various components,
potentially resulting in fuel spillage, uncommanded flap movement,
or loss of aileron control [and consequent reduced controllability
of the airplane].
This directive [MCAI] mandates repetitive [ultrasonic]
inspections of the accumulators for cracks and replacement of any
accumulator in which a crack is detected.
* * * * *
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Bombardier has issued Service Bulletins 215-541, 215-3155, and 215-
4414, all Revision 1, all dated March 12, 2010. 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 6 products of U.S. registry. We also estimate that
it would take about 7 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $3,570, or $595 per product per inspection
cycle.
In addition, we estimate that any necessary follow-on actions would
take about 6 work-hours and require parts costing $4,055, for a cost of
$4,565 per product. We have no way of determining the number of
products that may need these actions.
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,
[[Page 68730]]
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-2010-1108; Directorate Identifier
2010-NM-151-AD.
Comments Due Date
(a) We must receive comments by December 27, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier, Inc. airplanes, certificated
in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3)
of this AD.
(1) Model CL-215-1A10 (CL-215) airplanes, serial numbers 1001
through 1990 inclusive;
(2) Model CL-215-6B11 (CL-215T Variant) airplanes, serial
numbers 1056 through 1125 inclusive;
(3) Model CL-215-6B11 (CL-415 Variant) airplanes, serial numbers
2001 through 2990 inclusive.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls; and 32: Landing gear.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Seven cases of on-ground hydraulic accumulator screw cap or end
cap failure have been experienced * * * resulting in loss of the
associated hydraulic system and high-energy impact damage to
adjacent systems and structure. * * *
* * * * *
A detailed analysis of the systems and structure in the
potential line of trajectory of a failed screw cap/end cap for each
accumulator has been conducted. It has identified that the worst-
case scenarios would be impact damage to various components,
potentially resulting in fuel spillage, uncommanded flap movement,
or loss of aileron control [and consequent reduced controllability
of the airplane].
* * * * *
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.
Inspection To Determine Flight Hours
(g) Within 50 flight hours after the effective date of this AD,
inspect to determine the number of flight cycles accumulated by each
of the applicable accumulators (i.e., brake, aileron, elevator, and
rudder accumulators) having part number (P/N) 08-8423-010 (MS28700-
3) installed on the airplane. A review of airplane maintenance
records is acceptable in lieu of this inspection if the number of
flight cycles accumulated can be conclusively determined from that
review.
Initial Ultrasonic Inspection
(h) For Model CL-215-1A10 (CL-215) and CL-215-6B11 (CL-215T)
airplanes: Do an ultrasonic inspection for cracking of the
accumulator at the applicable time specified in paragraph (h)(1) or
(h)(2) of this AD, in accordance with Part B of the Accomplishment
Instructions of the applicable service bulletin listed in Table 1 of
this AD.
Table 1--Service Bulletins
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Use Bombardier
For model-- Service Bulletin-- Revision-- Dated--
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CL-215-1A10 (CL-215).................. 215-541 1 March 12, 2010.
CL-215-6B11 (CL-215T)................. 215-3155 1 March 12, 2010.
CL-600-6B11 (CL-415).................. 215-4414 1 March 12, 2010.
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(1) For any accumulator on which the inspection required by
paragraph (g) of this AD shows an accumulation of more than 875
total flight cycles or on which it is not possible to determine the
number of total accumulated flight cycles, do the inspection within
125 flight cycles after the effective date of this AD.
(2) For any accumulator on which the inspection required by
paragraph (g) of this AD shows an accumulation of 875 total flight
cycles or fewer, do the inspection before the accumulation of 1,000
flight cycles on the accumulator.
(i) For Model CL-215-6B11 (CL-415) airplanes, do an ultrasonic
inspection for cracking of the accumulator at the applicable time
specified in paragraph (i)(1) or (i)(2) of this AD, in accordance
with Part B of the Accomplishment Instructions of the applicable
service bulletin listed in Table 1 of this AD.
(1) For any accumulator on which the inspection required by
paragraph (g) of this AD shows an accumulation of more than 750
flight cycles or on which it is not possible to determine the number
of total accumulated flight cycles, do the inspection within 250
flight cycles after the effective date of this AD.
(2) For any accumulator on which the inspection required by
paragraph (g) of this AD shows an accumulation of 750 total flight
cycles or fewer, do the inspection before the accumulation of 1,000
flight cycles on the accumulator.
Repetitive Inspections
(j) If no cracking is found during any inspection required by
paragraph (h) or (i) of this AD, repeat the inspection thereafter at
intervals not to exceed 750 flight cycles.
[[Page 68731]]
(k) If any cracking is found during any inspection required by
paragraph (h) or (i) of this AD, before further flight, replace the
accumulator with a serviceable accumulator, in accordance with Part
B of the Accomplishment Instructions of the applicable service
bulletin listed in Table 1 of this AD. Doing the replacement does
not end the inspection requirements of this AD. Repeat the
inspections required by paragraph (h) or (i) of this AD at intervals
not to exceed 750 flight cycles.
Parts Installation
(l) As of the effective date of this AD, no person may install
an accumulator (P/N) 08-8423-010 (MS28700-3) on any airplane unless
the accumulator has been inspected in accordance with the
requirements of this AD.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(m) Inspections accomplished before the effective date of this
AD in accordance with the applicable service bulletin listed in
Table 2 of this AD are considered acceptable for compliance with the
corresponding action specified in this AD.
Table 2--Credit Service Bulletins
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Use Bombardier
For model-- Service Bulletin-- Dated--
----------------------------------------------------------------------------------------------------------------
CL-215-1A10 (CL-215).......................... 215-541 July 9, 2009.
CL-215-6B11 (CL-215T)......................... 215-3155 July 9, 2009.
CL-600-6B11 (CL-415).......................... 215-4414 July 9, 2009.
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FAA AD Differences
Note 1: This AD differs from the MCAI and/or service
information as follows:
No differences.
Other FAA AD Provisions
(n) 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
(o) Refer to MCAI Transport Canada Civil Aviation Airworthiness
Directive CF-2009-42R1, dated May 14, 2010; and the service
bulletins listed in Table 1 of this AD; for related information.
Issued in Renton, Washington, on November 2, 2010.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-28275 Filed 11-8-10; 8:45 am]
BILLING CODE 4910-13-P