Airworthiness Directives; Bombardier, Inc. Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) Airplanes, 68728-68731 [2010-28275]
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68728
Proposed Rules
Federal Register
Vol. 75, No. 216
Tuesday, November 9, 2010
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.
DEPARTMENT OF AGRICULTURE
Agricultural Marketing Service
7 CFR Part 1245
[Document Number AMS–FV–07–0091; FV–
07–706–PR–2A]
RIN 0581–AC78
Establishment of a U.S. Honey
Producer Research, Promotion, and
Consumer Information Order;
Withdrawal of a Proposed Rule
Agricultural Marketing Service,
USDA.
ACTION: Withdrawal of proposed rule
and referendum order.
AGENCY:
This document withdraws a
proposed rule published in the Federal
Register on April 12, 2010, that
proposed a new U.S. honey producer
funded research and promotion program
under the Commodity Promotion,
Research, and Information Act of 1996
(1996 Act). The proposed U.S. Honey
Producer Research, Promotion and
Consumer Information Order (Proposed
Order) was submitted to the Department
of Agriculture (Department) by the
American Honey Producers Association
(AHPA). The Department conducted an
initial referendum from May 17, 2010,
through June 4, 2010, to ascertain
whether the persons to be covered by
and assessed under the Proposed Order
favored the Order prior to it going into
effect. The Proposed Order failed by
vote. Accordingly, based upon the
referendum results, the proposed rule is
being withdrawn.
DATES: Effective Date: November 9,
2010.
FOR FURTHER INFORMATION CONTACT:
Kimberly Coy, Marketing Specialist,
Research and Promotion Branch, Fruit
and Vegetable Programs, AMS, USDA,
Stop 0244, Room 0634–S, 1400
Independence Ave., SW., Washington,
DC 20250–0244; telephone (202) 720–
9915 or (888) 720–9917 (toll free), Fax:
(202) 205–2800 or e-mail
kimberly.coy@ams.usda.gov.
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
SUMMARY:
VerDate Mar<15>2010
14:46 Nov 08, 2010
Jkt 223001
This rule
is issued under the Commodity
Promotion, Research, and Information
Act of 1996 (1996 Act) (7 U.S.C. 7411–
7425).
This action withdraws a proposed
rule and referendum order published in
the Federal Register on April 12, 2010
[75 FR 18430], that proposed a new U.S.
honey producer funded research and
promotion program.
As part of this rulemaking, a proposed
rule was published in the Federal
Register on July 14, 2009 [74 FR 34182],
with a 60-day comment period which
closed on September 4, 2009. Fourteen
comments were received. In addition, a
second proposed rule and referendum
order was published in the Federal
Register on April 12, 2010 [75 FR
18430]. A separate final rule on
referendum procedures was published
in the Federal Register on April 12,
2010 [75 FR 18396].
The Department conducted an initial
referendum from May 17, 2010 through
June 4, 2010 to ascertain whether the
persons to be covered by and assessed
under the Proposed Order favored the
Order prior to it going into effect. To be
eligible to vote, producers must have
produced 100,000 or more pounds of
honey from January 1, 2008 through
December 31, 2008. The Proposed Order
would have been implemented if
approved by a majority of the producers
voting in the referendum, which also
represented a majority of the volume of
U.S. honey produced during the
representative period by those voting in
the referendum. In the referendum, 41
percent of those who voted—
representing 52 percent of the voted
volume of U.S. honey—favored
implementation of the Order. Therefore,
the Proposed Order failed by vote.
Accordingly based upon the referendum
results, the proposed rule is being
withdrawn.
The proposed rule to implement a
new U.S. honey producer funded
research and promotion program under
the 1996 Act published in the Federal
Register on April 12, 2010 (75 FR
18430), is hereby withdrawn.
SUPPLEMENTARY INFORMATION:
List of Subjects in 7 CFR Part 1245
Administrative practice and
procedure, Advertising, Consumer
Education, U.S. Honey, Marketing
agreements, Promotion, Reporting and
recordkeeping requirements.
PO 00000
Frm 00001
Fmt 4702
Sfmt 4702
Authority: 7 U.S.C. 7411–7425; 7 U.S.C.
7401.
Dated: November 3, 2010.
David R. Shipman,
Acting Administrator, Agricultural Marketing
Service.
[FR Doc. 2010–28242 Filed 11–8–10; 8:45 am]
BILLING CODE 3410–02–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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:
SUMMARY:
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.
E:\FR\FM\09NOP1.SGM
09NOP1
Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Proposed Rules
We must receive comments on
this proposed AD by December 27,
2010.
DATES:
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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,
ˆ
Inc., 400 Cote-Vertu Road West, Dorval,
´
Quebec H4S 1Y9, Canada; telephone
514–855–5000; fax 514–855–7401;
e-mail thd.crj@aero.bombardier.com;
Internet https://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.
ADDRESSES:
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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
VerDate Mar<15>2010
14:46 Nov 08, 2010
Jkt 223001
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 https://
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.
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
68729
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,
E:\FR\FM\09NOP1.SGM
09NOP1
68730
Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Proposed Rules
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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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. * * *
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.
§ 39.13
*
*
*
*
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].
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Bombardier, Inc.: Docket No. FAA–2010–
1108; Directorate Identifier 2010–NM–
151–AD.
*
*
*
*
*
Compliance
Comments Due Date
(a) We must receive comments by
December 27, 2010.
(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.
Affected ADs
(b) None.
Inspection To Determine Flight Hours
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.
List of Subjects in 14 CFR Part 39
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight controls; and 32:
Landing gear.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
(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
Use Bombardier
Service Bulletin—
For model—
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
CL–215–1A10 (CL–215) .........................................................................................
CL–215–6B11 (CL–215T) .......................................................................................
CL–600–6B11 (CL–415) .........................................................................................
(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.
VerDate Mar<15>2010
14:46 Nov 08, 2010
Jkt 223001
215–541
215–3155
215–4414
(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
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
Revision—
Dated—
1
1
1
March 12, 2010.
March 12, 2010.
March 12, 2010.
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.
E:\FR\FM\09NOP1.SGM
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Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Proposed Rules
(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.
68731
Repeat the inspections required by paragraph
(h) or (i) of this AD at intervals not to exceed
750 flight cycles.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
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.
(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
Use Bombardier
Service Bulletin—
For model—
CL–215–1A10 (CL–215) .....................................................................................................................
CL–215–6B11 (CL–215T) ...................................................................................................................
CL–600–6B11 (CL–415) .....................................................................................................................
Issued in Renton, Washington, on
November 2, 2010.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows:
No differences.
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Other FAA AD Provisions
[FR Doc. 2010–28275 Filed 11–8–10; 8:45 am]
(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.
BILLING CODE 4910–13–P
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.
VerDate Mar<15>2010
14:46 Nov 08, 2010
Jkt 223001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1107; Directorate
Identifier 2009–NM–263–AD]
RIN 2120–AA64
Airworthiness Directives; The Cessna
Aircraft Company Model 750 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Model 750 airplanes. This proposed AD
would require an inspection to
determine the serial numbers of the
auxiliary power unit (APU) generator
and the left and right engine direct
current (DC) generators, and related
corrective actions if necessary. This
proposed AD would also require
revising the airplane flight manual. This
proposed AD results from a report of a
DC generator overvoltage event which
caused smoke in the cockpit and
damage to numerous avionics and
electrical components. We are
proposing this AD to detect and correct
an overvoltage condition on the DC
electrical busses caused by exciter stator
winding failures, and subsequent failure
of the generator control unit (GCU)
overvoltage protection circuitry, which
SUMMARY:
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Frm 00004
Fmt 4702
Sfmt 4702
215–541
215–3155
215–4414
Dated—
July 9, 2009.
July 9, 2009.
July 9, 2009.
could result in damage to critical
electrical and avionics components.
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
https://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 W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Cessna
Aircraft Co., P.O. Box 7706, Wichita,
Kansas 67277; telephone 316–517–6215;
fax 316–517–5802; e-mail
citationpubs@cessna.textron.com;
Internet https://
www.cessnasupport.com/newlogin.html.
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 https://
www.regulations.gov; or in person at the
Docket Management Facility 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
E:\FR\FM\09NOP1.SGM
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]]>Agencies
[Federal Register Volume 75, Number 216 (Tuesday, November 9, 2010)]
[Proposed Rules]
[Pages 68728-68731]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-28275]
=======================================================================
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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 https://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
thd.crj@aero.bombardier.com; Internet https://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 https://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 https://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
----------------------------------------------------------------------------------------------------------------
Use Bombardier
For model-- Service Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
(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
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
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
