[Federal Register Volume 75, Number 117 (Friday, June 18, 2010)]
[Proposed Rules]
[Pages 34657-34661]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-14769]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0550; Directorate Identifier 2009-NM-124-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model CL-600-2B19
(Regional Jet Series 100 & 440) Airplanes; Model CL-600-2C10 (Regional
Jet Series 700, 701, & 702) Airplanes; Model CL-600-2D15 (Regional Jet
Series 705) Airplanes; and Model CL-600-2D24 (Regional Jet Series 900)
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
[[Page 34658]]
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: Two cases of a crack on a ``dry'' ADG [air driven
generator] (Hamilton Sundstrand part number in the 761339 series), in
the aft area of the strut and generator housing assembly, have been
reported on CL-600-2B19 aircraft. The same part is also installed on
CL-600-2C10, -2D15 and -2D24 aircraft. Investigation determined that
the crack was in an area of the strut where the wall thickness of the
casting was below specification, due to a manufacturing anomaly in a
specific batch of ADGs. Structural failure and departure of the ADG
during deployment could possibly result in damage to the aircraft
structure. If deployment was activated by a dual engine shutdown, ADG
structural failure would also result in loss of hydraulics for the
flight controls. 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 August 2, 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: Craig Yates, 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) 228-7355; 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-2010-0550;
Directorate Identifier 2009-NM-124-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, which is the aviation authority
for Canada, has issued Canadian Airworthiness Directive CF-2009-27,
dated June 8, 2009 (referred to after this as ``the MCAI''), to correct
an unsafe condition for the specified products. The MCAI states:
Two cases of a crack on a ``dry'' ADG [air driven generator]
(Hamilton Sundstrand part number in the 761339 series), in the aft
area of the strut and generator housing assembly, have been reported
on CL-600-2B19 aircraft. The same part is also installed on CL-600-
2C10, -2D15 and -2D24 aircraft. Investigation determined that the
crack was in an area of the strut where the wall thickness of the
casting was below specification, due to a manufacturing anomaly in a
specific batch of ADGs. Structural failure and departure of the ADG
during deployment could possibly result in damage to the aircraft
structure. If deployment was activated by a dual engine shutdown,
ADG structural failure would also result in loss of hydraulics for
the flight controls.
This directive gives instructions to check the part number of
the installed ADG and, for ADGs with a part number in the 761339
series, the serial numbers of the ADG and strut and generator
housing assembly are also to be checked. If these serial numbers are
within specified ranges ***, a one-time fluorescent penetrant
inspection of the ADG strut is required [and replacement of the ADG
if necessary].
Note: For ADGs with serial numbers in the *** specified ranges,
subsequent fluorescent penetrant inspections are required after each
scheduled in-flight or on-ground functional check of the ADG and
also after each unscheduled in-flight ADG deployment. These
inspection requirements are not mandated in this directive but are
specified in the approved maintenance program.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Bombardier has issued Alert Service Bulletin A601R-24-120, Revision
C, dated April 20, 2009; and Alert Service Bulletin A670BA-24-020,
Revision C, dated April 20, 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
[[Page 34659]]
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 1,073 products of U.S. registry. We also estimate
that it would take about 1 work-hour 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 $91,205, or $85 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-2010-0550; Directorate Identifier
2009-NM-124-AD.
Comments Due Date
(a) We must receive comments by August 2, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier, Inc. Model CL-600-2B19
(Regional Jet Series 100 & 440) airplanes, serial numbers 7305
through 8051 inclusive; Model CL-600-2C10 (Regional Jet Series 700,
701, & 702) airplanes, serial numbers 10003 through 10260 inclusive;
and Model CL-600-2D15 (Regional Jet Series 705) airplanes and Model
CL-600-2D24 (Regional Jet Series 900) airplanes, serial numbers
15001 through 15106 inclusive; certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 24:
Electrical Power.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Two cases of a crack on a ``dry'' ADG [air driven generator]
(Hamilton Sundstrand part number in the 761339 series), in the aft
area of the strut and generator housing assembly, have been reported
on CL-600-2B19 aircraft. The same part is also installed on CL-600-
2C10, -2D15 and -2D24 aircraft. Investigation determined that the
crack was in an area of the strut where the wall thickness of the
casting was below specification, due to a manufacturing anomaly in a
specific batch of ADGs. Structural failure and departure of the ADG
during deployment could possibly result in damage to the aircraft
structure. If deployment was activated by a dual engine shutdown,
ADG structural failure would also result in loss of hydraulics for
the flight controls.
This directive gives instructions to check the part number of
the installed ADG and, for ADGs with a part number in the 761339
series, the serial numbers of the ADG and strut and generator
housing assembly are also to be checked. If these serial numbers are
within specified ranges ***, a one-time fluorescent penetrant
inspection of the ADG strut is required [and replacement of the ADG
if necessary].
Note: For ADGs with serial numbers in the * * * specified
ranges, subsequent fluorescent penetrant inspections are required
after each scheduled in-flight or on-ground functional check of the
ADG and also after each unscheduled in-flight ADG deployment. These
inspection requirements are not mandated in this directive but are
specified in the approved maintenance program.
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) Do the following actions.
(1) Within 1,000 flight hours after the effective date of this
AD or before the first scheduled ADG functional test after the
effective date of this AD, whichever occurs first, inspect to
determine the part number of the installed ADG. A review of the
airplane maintenance records is acceptable in lieu of this
inspection if the part number can be conclusively determined from
that review.
(i) If a Hamilton Sundstrand ADG having part number 1711405 is
installed, the strut thickness is within specification and no
further action is required by this AD.
(ii) If a Hamilton Sundstrand ADG having a part number in the
761339 series is installed, within 1,000 flight hours after the
effective date of this AD or before the first scheduled ADG
functional test after the effective date of this AD, whichever
occurs first, inspect to determine the serial number of the ADG. A
review of the airplane maintenance records is acceptable in lieu of
this inspection if the serial number can be conclusively determined
from that review.
(A) If the serial number of the ADG is 2000 or higher, the strut
wall thickness is within specification and no further action is
required by this AD.
(B) If the serial number of the ADG is in the range 0101 through
1999 and symbol ``24-3'' is marked in the serial number block of the
identification plate, the strut wall thickness is within
specification, no further action is required by this AD.
(C) If the serial number of the ADG is in the range 0101 through
1999 and the symbol
[[Page 34660]]
``24-3'' is not marked in the serial block of the identification
plate, within 1,000 flight hours after the effective date of this AD
or before the first scheduled ADG functional test after the
effective date of this AD, whichever occurs first, inspect to
determine the serial number of the strut and generator housing
assembly. A review of the airplane maintenance records is acceptable
in lieu of this inspection if the serial number can be conclusively
determined from that review.
(1) If the serial number of the strut and generator housing
assembly is in the range 0001 through 2503, do a fluorescent
penetrant inspection in accordance with paragraph (g)(2) of this AD
at the times specified in paragraph (g)(2) of this AD.
(2) If the serial number of the strut and generator housing
assembly is 2504 or higher, the strut wall thickness is within
specification and no further action is required by this AD.
(3) If the serial number of the strut and generator housing
assembly is not inspected or it is not possible to determine the
serial number, do a fluorescent penetrant inspection in accordance
with paragraph (g)(2) of this AD at the times specified in paragraph
(g)(2) of this AD.
(2) For ADGs having a strut and generator assembly identified in
paragraph (g)(1)(ii)(C)(1) or (g)(1)(ii)(C)(3) of this AD: Within
1,000 flight hours after the effective date of this AD or before the
first scheduled ADG functional test after the effective date of this
AD, whichever occurs first, do a fluorescent penetrant inspection
for cracking of the ADG strut, and if any crack is found, before
further flight, replace the ADG with a serviceable ADG, in
accordance with the Accomplishment Instructions of Bombardier Alert
Service Bulletin A601R-24-120, Revision C, dated April 20, 2009 (for
Model CL-600-2B19 airplanes); or Bombardier Alert Service Bulletin
A670BA-24-020, Revision C, dated April 20, 2009 (for Model CL-600-
2C10, CL-600-2D15, and CL-600-2D24 airplanes).
(3) Fluorescent penetrant inspections accomplished before the
effective date of this AD in accordance with any applicable service
bulletin specified in Table 1 of this AD are considered acceptable
for compliance with the corresponding fluorescent penetrant
inspection specified in this AD.
Table 1--Credit Service Bulletins
----------------------------------------------------------------------------------------------------------------
Bombardier, Inc. Model-- Service Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
CL-600-2B19 airplanes............... Bombardier Alert Service Original............ April 20, 2005.
Bulletin A601R-24-120.
CL-600-2B19 airplanes............... Bombardier Alert Service A................... December 1, 2005.
Bulletin A601R-24-120.
CL-600-2B19 airplanes............... Bombardier Alert Service B................... December 7, 2006.
Bulletin A601R-24-120.
CL-600-2C10 airplanes and CL-600- Bombardier Alert Service Original............ April 20, 2005.
2D24 airplanes. Bulletin A670BA-24-020.
CL-600-2C10 airplanes; and CL-600- Bombardier Alert Service A................... May 17, 2005.
2D15 and CL-600-2D24 airplanes. Bulletin A670BA-24-020.
CL-600-2C10 airplanes; and CL-600- Bombardier Alert Service B................... December 7, 2006.
2D15 and CL-600-2D24 airplanes. Bulletin A670BA-24-020.
CL-600-2B19 airplanes; CL-600-2C10 Hamilton Sundstrand Service Original............ April 14, 2005.
airplanes; and CL-600-2D15 and CL- Bulletin ERPS10AG-24-3.
600-2D24 airplanes.
CL-600-2B19 airplanes; CL-600-2C10 Hamilton Sundstrand Service 1................... April 19, 2005.
airplanes; and CL-600-2D15 and CL- Bulletin ERPS10AG-24-3.
600-2D24 airplanes.
CL-600-2B19 airplanes; CL-600-2C10 Hamilton Sundstrand Service 2................... November 14, 2006.
airplanes; and CL-600-2D15 and CL- Bulletin ERPS10AG-24-3.
600-2D24 airplanes.
Bombardier, Inc. CL-600-2B19 Hamilton Sundstrand Service 3................... March 12, 2009.
airplanes; CL-600-2C10 airplanes; Bulletin ERPS10AG-24-3.
and CL-600-2D15 and CL-600-2D24
airplanes.
----------------------------------------------------------------------------------------------------------------
Note 1: For additional guidance on the ADGs specified in
paragraphs (g)(1)(ii)(C)(1)and (g)(1)(ii)(C)(3) of this AD and the
repetitive fluorescent penetrant inspections specified as part of
the periodic ADG functional check procedure, refer to the applicable
tasks identified in Table 2 of this AD. These tasks can be found in
Part 2 -Airworthiness Requirements, Appendix A--Certification
Maintenance Requirements (CMR) of the Bombardier (Canadair) Regional
Jet Maintenance Requirements Manual, and the Bombardier CRJ Series
Regional Jet Aircraft Maintenance Manual (AMM).
Table 2--Guidance for the Periodic ADG Functional Check Procedure
------------------------------------------------------------------------
Bombardier, Inc. Model-- Task Number (No.)--
------------------------------------------------------------------------
CL-600-2B19 airplanes............. CMR Task No. C24-20-129-01 and AMM
Task No: 24-23-01-720-803.
CL-600-2C10 airplanes............. CMR Task No. 24-23-00-102 and AMM
Task No. 24-23-01-720-802.
CL-600-2D15 and CL-600-2D24 CMR Task No. 24-23-00-102 and AMM
airplanes. Task No. 24-23-01-720-802.
------------------------------------------------------------------------
Note 2: For additional guidance on the ADGs specified in
paragraph (g)(1)(ii)(C)(1), and the fluorescent penetrant inspection
necessary following each future unscheduled in-flight ADG
deployment, refer to following task specified in Table 3 of this AD.
Table 3--Guidance for Inspection Following Unscheduled In-Flight ADG
Deployment
------------------------------------------------------------------------
Bombardier, Inc. Model-- AMM Task No.--
------------------------------------------------------------------------
CL-600-2B19 airplanes, serial numbers 7305 05-51-19-210-801
through 8051 inclusive........................
CL-600-2C10 airplanes, serial numbers 10003 05-51-19-210-801
through 10260 inclusive.......................
CL-600-2D15 and CL-600-2D24 airplanes, serial 05-51-19-210-801
numbers 15001 through 15106 inclusive.........
------------------------------------------------------------------------
[[Page 34661]]
Note 3: In Hamilton Sundstrand Service Bulletin ERPS10AG-24-3,
the fluorescent penetrant inspection is referred to as a ``Penetrant
Check.''
FAA AD Differences
Note 4: This AD differs from the MCAI and/or service
information as follows: No differences.
Other FAA AD Provisions
(h) 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.
(4) Special Flight Permits: Special flight permits, as described
in section 21.197 and section 21.199 of the Federal Aviation
Regulations (14 CFR 21.197 and 21.199), are not allowed.
Related Information
(i) Refer to MCAI Canadian Airworthiness Directive CF-2009-27,
dated June 8, 2009; Bombardier Alert Service Bulletin A601R-24-120,
Revision C, dated April 20, 2009; and Bombardier Alert Service
Bulletin A670BA-24-020, Revision C, dated April 20, 2009; for
related information.
Issued in Renton, Washington, on June 10, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-14769 Filed 6-17-10; 8:45 am]
BILLING CODE 4910-13-P