[Federal Register Volume 75, Number 190 (Friday, October 1, 2010)]
[Rules and Regulations]
[Pages 60604-60608]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-24482]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0550; Directorate Identifier 2009-NM-124-AD;
Amendment 39-16454; AD 2010-20-19]
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), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This 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.
* * * * *
[[Page 60605]]
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective November 5, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 5,
2010.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on June 18, 2010 (75 FR
34657). That NPRM proposed 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 [Transport Canada Civil Aviation (TCCA)] 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 [TCCA] directive
but are specified in the approved maintenance program.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received. Air Line Pilots
Association, International supports the NPRM.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD as proposed.
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 required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 1,073 products of U.S.
registry. We also estimate that it will take about 1 work-hour per
product to comply with the basic requirements of this AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this AD to the 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 AD will not have federalism implications
under Executive Order 13132. This AD will 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 AD:
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 AD and placed it in the AD docket.
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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 60606]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2010-20-19 Bombardier, Inc.: Amendment 39-16454. Docket No. FAA-
2010-0550; Directorate Identifier 2009-NM-124-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
5, 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 [Transport Canada Civil Aviation (TCCA)] 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 [TCCA] 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 ``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
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Bombardier, Inc. model-- Service Bulletin-- Revision-- Date--
----------------------------------------------------------------------------------------------------------------
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.
[[Page 60607]]
CL-600-2B19 airplanes; CL-600- Hamilton Sundstrand Original........... April 14, 2005.
2C10 airplanes; and CL-600-2D15 Service Bulletin
and CL-600-2D24 airplanes. ERPS10AG-24-3.
CL-600-2B19 airplanes; CL-600- Hamilton Sundstrand 1.................. April 19, 2005.
2C10 airplanes; and CL-600-2D15 Service Bulletin
and CL-600-2D24 airplanes. ERPS10AG-24-3.
CL-600-2B19 airplanes; CL-600- Hamilton Sundstrand 2.................. November 14, 2006.
2C10 airplanes; and CL-600-2D15 Service Bulletin
and CL-600-2D24 airplanes. ERPS10AG-24-3.
Bombardier, Inc. CL-600-2B19 Hamilton Sundstrand 3.................. March 12, 2009.
airplanes; CL-600-2C10 Service Bulletin
airplanes; and CL-600-2D15 and ERPS10AG-24-3.
CL-600-2D24 airplanes.
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Note 1: 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 may be found in the applicable tasks
identified in Table 2 of this AD. These tasks can be found in Part
2--Airworthiness Limitations, Appendix A--Certification Maintenance
Requirements (CMR), of the Bombardier CL-600-2C10, CL-600-2D15, and
CL-600-2D24 Maintenance Requirements Manual; and the Canadair CRJ
Series Regional Jet Aircraft Maintenance Manual (AMM); as
applicable.
Table 2--Guidance for the Periodic ADG Functional Check Procedure
------------------------------------------------------------------------
Bombardier, Inc. Model-- Task number--
------------------------------------------------------------------------
CL-600-2B19 airplanes.................. CMR Task C24-20-129-01 and AMM
Task 24-23-01-720-803
CL-600-2C10 airplanes.................. CMR Task 24-23-00-102 and AMM
Task 24-23-01-720-802
CL-600-2D15 and CL-600-2D24 airplanes.. CMR Task 24-23-00-102 and AMM
Task 24-23-01-720-802
------------------------------------------------------------------------
Note 2: 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 can be
found in the tasks specified in Table 3 of this AD.
Table 3--Guidance for Inspection Following Unscheduled In-Flight ADG
Deployment
------------------------------------------------------------------------
Bombardier, Inc. Model-- AMM task--
------------------------------------------------------------------------
CL[dash]600-2B19 airplanes, serial numbers 05-51-19-210-801
7305 through 8051 inclusive.
CL-600-2C10 airplanes, serial numbers 10003 05-51-19-210-801
through 10260 inclusive.
CL[dash]600[dash]2D15 and CL-600-2D24 05-51-19-210-801
airplanes, serial numbers 15001 through
15106 inclusive.
------------------------------------------------------------------------
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.
Material Incorporated by Reference
(j) You must use Bombardier Alert Service Bulletin A601R-24-120,
Revision C, dated April 20, 2009; or Bombardier Alert Service
Bulletin A670BA-24-020, Revision C, dated April 20, 2009; as
applicable; to do the actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this 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.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
[[Page 60608]]
availability of this material at the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on September 21, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-24482 Filed 9-30-10; 8:45 am]
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