[Federal Register Volume 78, Number 68 (Tuesday, April 9, 2013)]
[Proposed Rules]
[Pages 21074-21077]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-08204]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0296; Directorate Identifier 2012-NM-102-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to certain Bombardier, Inc. Model CL-600-2B19
(Regional Jet Series 100 & 440) airplanes. The existing AD currently
requires revising the airworthiness limitations section of the
Instructions for Continued Airworthiness of the maintenance
requirements manual (MRM) by incorporating procedures for repetitive
functional tests of the pilot input lever of the pitch feel simulator
(PFS) units and new repetitive functional tests of the pilot input
lever of the PFS unit, and corrective actions if necessary; and, after
initiating the new tests, removing of the existing procedures for the
repetitive functional tests from the MRM. The existing AD was prompted
by a report that the shear pin located in the input lever of two PFS
units failed due to fatigue. Since we issued that AD, a new re-designed
PFS unit has been developed, which eliminates the need for repetitive
inspections. This proposed AD would require replacing certain PFS units
with the new redesigned PFS unit. This proposed AD would also remove
certain airplanes from the applicability and add certain airplanes to
the applicability. We are proposing this AD to prevent undetected
failure of the shear pins of both PFS units simultaneously, which could
result in loss of pitch feel forces and consequent reduced control of
the airplane.
DATES: We must receive comments on this proposed AD by May 24, 2013.
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 W12-140, 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; email
[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, WA. 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: Cesar Gomez, 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) 228-7318; 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-2013-0296;
Directorate Identifier 2012-NM-102-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On March 31, 2008, we issued AD 2008-08-09, Amendment 39-15461 (73
FR 19979, April 14, 2008). That AD required actions intended to address
an unsafe condition on the products listed above.
Since we issued AD 2008-08-09, Amendment 39-15461 (73 FR 19979,
April 14, 2008), Transport Canada Civil Aviation (TCCA), which is the
aviation authority for Canada, has issued Canadian Airworthiness
Directive CF-2005-41R1, dated May 10, 2012 (referred to after this as
the Mandatory Continuing Airworthiness Information, or ``the MCAI''),
to correct an unsafe condition for the specified products. The MCAI
states:
The shear pin in the input lever of several Pitch Feel Simulators
(PFS) units has failed due to fatigue. The shear pin failure is not
always detectable by the flight crew in normal operation. Failure of
the shear pins in both PFS units on an aeroplane could result in
loss of pitch feel forces and reduced controllability of the
aeroplane.
Recently, Transport Canada has certified the new design of the PFS
unit--part number (P/N) 601R92300-7 as a terminating action.
[[Page 21075]]
Revision 1 of this [TCCA] AD mandates the retrofit of all in-service
CL-600-2B19 aeroplanes with the redesigned PFS unit.
Required actions include replacing the PFS units having part number (P/
N) 601R92300-3 or 601R92300-5 with PFS units having P/N 601R92300-7,
which would terminate the actions required by AD 2008-08-09, Amendment
39-15461 (73 FR 19979, April 14, 2008). This proposed AD also adds
airplanes having serial numbers (S/Ns) 7991 through 7999 inclusive, and
removes airplanes having S/Ns 8112 and subsequent. You may obtain
further information by examining the MCAI in the AD docket.
Relevant Service Information
Bombardier, Inc. has issued Alert Service Bulletin A601R-27-144,
Revision E, dated October 2, 2012, including Appendix A, Revision A,
dated December 20, 2006; and Service Bulletin 601R-27-139, Revision A,
dated May 28, 2012. 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.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 574 products of U.S. registry.
The actions that are required by AD 2008-08-09, Amendment 39-15461
(73 FR 19979, April 14, 2008), and retained in this proposed AD take
about 2 work-hours per product, at an average labor rate of $85 per
work hour. Required parts cost about $0 per product. Based on these
figures, the estimated cost of the currently required actions is $170
per product.
We estimate that it would take about 8 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $2,500
per product. Where the service information lists required parts costs
that are covered under warranty, we have assumed that there will be no
charge for these parts. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, we estimate the cost of the proposed AD
on U.S. operators to be $1,825,320, or $3,180 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);
3. Will not affect intrastate aviation in Alaska; and
4. 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
0
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]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2008-08-09, Amendment 39-15461 (73 FR 19979, April 14, 2008), and
adding the following new AD:
Bombardier, Inc.: Docket No. FAA-2013-0296; Directorate Identifier
2012-NM-102-AD.
(a) Comments Due Date
We must receive comments by May 24, 2013.
(b) Affected ADs
This AD supersedes AD 2008-08-09, Amendment 39-15461 (73 FR
19979, April 14, 2008).
(c) Applicability
This AD applies to Bombardier, Inc. Model CL-600-2B19 (Regional
Jet Series 100 & 440) airplanes, certificated in any category,
serial numbers (S/Ns) 7003 through 8111 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by a report that the shear pin located in
the input lever of two pitch feel simulator (PFS) units failed due
to fatigue. We are issuing this AD to prevent undetected failure of
the shear pins of both PFS units simultaneously, which could result
in loss of pitch feel forces and consequent reduced control of the
airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Revision of Airworthiness Limitations (AWL) Section of
Maintenance Requirements Manual
This paragraph restates the requirements of paragraph (f) of AD
2008-08-09, Amendment 39-15461 (73 FR 19979, April 14, 2008). For
airplanes having S/Ns 7003 through 7990 inclusive: Within 14 days
after February 13, 2004 (the effective date of AD 2004-02-07,
Amendment 39-13442 (69 FR 4234, January 29, 2004), which was
superseded by AD 2006-05-11 R1, Amendment 39-14528 (71 FR 15323,
March 28, 2006)), revise the AWL section of the Instructions for
Continued Airworthiness of the maintenance requirements manual by
incorporating the
[[Page 21076]]
functional check of the PFS pilot input lever, Task R27-31-A024-01,
as specified in Bombardier Temporary Revision (TR) 2B-1784, dated
October 24, 2003, to the CL-600-2B19 Canadair Regional Jet
Maintenance Requirements Manual, Part 2, Appendix B, ``Airworthiness
Limitations,'' into the AWL section.
(h) Retained Functional Test of Input Lever With Revised Service
Information
This paragraph restates the requirements of paragraph (g) of AD
2008-08-09, Amendment 39-15461 (73 FR 19979, April 14, 2008), with
revised service information. For airplanes having S/Ns 7003 through
7990 inclusive, and S/Ns 8000 through 8111 inclusive: Before the
accumulation of 4,000 total flight hours, or within 100 flight hours
after March 27, 2006 (the effective date of AD 2006-05-11 R1,
Amendment 39-14528 (71 FR 15323, March 28, 2006), whichever occurs
later, do a functional test of the pilot input lever of the PFS
units to determine if the lever is disconnected, in accordance with
the Accomplishment Instructions of a service bulletin specified in
paragraph (h)(1), (h)(2), or (h)(3) of this AD. Repeat the test at
intervals not to exceed 100 flight hours. Accomplishing the initial
functional test terminates the requirements of paragraph (g) of this
AD and the repetitive functional check of the PFS pilot input lever,
Task R27-31-A024-01, as specified in the AWL section of the
Instructions for Continued Airworthiness of CL-600-2B19 Canadair
Regional Jet Maintenance Requirements Manual. As of the effective
date of this AD, only Bombardier Alert Service Bulletin A601R-27-
144, Revision E, dated October 2, 2012, including Appendix A,
Revision A, dated December 20, 2006, may be used to accomplish the
actions required by this paragraph.
(1) Bombardier Alert Service Bulletin A601R-27-144, Revision A,
dated February 14, 2006, including Appendix A, dated September 15,
2005.
(2) Bombardier Alert Service Bulletin A601R-27-144, Revision B,
dated December 20, 2006, including Appendix A, Revision A, dated
December 20, 2006.
(3) Bombardier Alert Service Bulletin A601R-27-144, Revision E,
dated October 2, 2012, including Appendix A, Revision A, dated
December 20, 2006.
(i) Retained Replacement With Revised Service Information
This paragraph restates the requirements of paragraph (h) of AD
2008-08-09, Amendment 39-15461 (73 FR 19979, April 14, 2008), with
revised service information. If any lever is found to be
disconnected during any functional test required by paragraph (h) of
this AD, before further flight, replace the defective PFS unit with
a serviceable PFS unit, in accordance with the Accomplishment
Instructions of a service bulletin specified in paragraph (i)(1),
(i)(2), or (i)(3) of this AD. As of the effective date of this AD,
only Bombardier Alert Service Bulletin A601R-27-144, Revision E,
dated October 2, 2012, including Appendix A, Revision A, dated
December 20, 2006, may be used to accomplish the actions required by
this paragraph.
(1) Bombardier Alert Service Bulletin A601R-27-144, Revision A,
dated February 14, 2006, including Appendix A, dated September 15,
2005.
(2) Bombardier Alert Service Bulletin A601R-27-144, Revision B,
dated December 20, 2006, including Appendix A, Revision A, dated
December 20, 2006.
(3) Bombardier Alert Service Bulletin A601R-27-144, Revision E,
dated October 2, 2012, including Appendix A, Revision A, dated
December 20, 2006.
(j) New Functional Test of Input Lever
For airplanes having S/Ns 7991 through 7999 inclusive: At the
later of the times specified in paragraphs (j)(1) and (j)(2) of this
AD, do a functional test of the pilot input lever of the PFS units
to determine if the lever is disconnected, in accordance with the
Accomplishment Instructions of Bombardier Alert Service Bulletin
A601R-27-144, Revision E, dated October 2, 2012, including Appendix
A, Revision A, dated December 20, 2006. Repeat the test thereafter
at intervals not to exceed 100 flight hours. Accomplishing the
initial functional test specified in this paragraph terminates the
requirements of paragraph (g) of this AD and the repetitive
functional check of the PFS pilot input lever, Task R27-31-A024-01,
as specified in the AWL section of the Instructions for Continued
Airworthiness of CL-600-2B19 Canadair Regional Jet Maintenance
Requirements Manual.
(1) Before the accumulation of 4,000 total flight hours.
(2) Within 100 flight hours from the effective date of this AD.
(k) New Replacement of Defective Pitch Feel Simulator Unit
For airplanes having S/Ns 7991 through 7999 inclusive: If any
disconnected lever is found to be detected during any functional
test required by paragraph (j) of this AD, before further flight,
replace the defective PFS unit with a serviceable PFS unit, in
accordance with the Accomplishment Instructions of Bombardier Alert
Service Bulletin A601R-27-144, Revision E, dated October 2, 2012,
including Appendix A, Revision A, dated December 20, 2006.
(l) New Replacement of Pitch Feel Simulator Units
At the applicable time specified in paragraph (l)(1), (l)(2),
(l)(3), or (l)(4) of this AD: Replace PFS units having part number
(P/N) 601R92300-3 or 601R92300-5, with PFS units having P/N
601R92300-7, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 601R-27-139, Revision A, dated May 28,
2012. Accomplishment of the replacement required by this paragraph
terminates the requirements of paragraphs (g), (h), (i), (j), and
(k) of this AD, and does not alter the approved maintenance program
for the new redesigned PFS unit P/N 601R92300-7.
(1) For PFS units having P/N 601R92300-3 or 601R92300-5 that
have accumulated less than 18,000 total flight hours as of the
effective date of this AD: Within 6,000 flight hours after the
effective date of this AD, but not to exceed 23,000 total flight
hours on the PFS unit, or within 36 months after the effective date
of this AD, whichever occurs first.
(2) For PFS units having P/N 601R92300-3 or 601R92300-5 that
have accumulated more than or equal to 18,000 total flight hours but
less than 19,000 total flight hours as of the effective date of this
AD: Within 5,000 flight hours after the effective date of this AD,
but not to exceed 23,000 total flight hours on the PFS unit, or
within 30 months after the effective date of this AD, whichever
occurs first.
(3) For PFS units having P/N 601R92300-3 or 601R92300-5 that
have accumulated more than or equal to 19,000 total flight hours but
less than 20,000 total flight hours as of the effective date of this
AD: Within 4,000 flight hours after the effective date of this AD,
but not to exceed 23,000 total flight hours on the PFS unit, or
within 24 months after the effective date of this AD, whichever
occurs first.
(4) For PFS units having P/N 601R92300-3 or 601R92300-5 that
have accumulated more than or equal to 20,000 total flight hours as
of the effective date of this AD: Within 3,000 flight hours or 18
months, after the effective date of this AD, whichever occurs first.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraphs (h) and (i) of this AD, if those actions were performed
before the effective date of this AD using a service bulletin
identified in paragraph (m)(1)(i) or (m)(1)(ii) of this AD.
(i) Bombardier Alert Service Bulletin A601R-27-144, Revision C,
dated July 21, 2008, including Appendix A, dated December 20, 2006,
which is not incorporated by reference in this AD.
(ii) Bombardier Alert Service Bulletin A601R-27-144, Revision D,
dated December 22, 2011, including Appendix A, dated December 20,
2006, which is not incorporated by reference in this AD.
(2) This paragraph provides credit for replacement of the PFS
units required by paragraph (l) of this AD, if those actions were
performed before the effective date of this AD using Bombardier
Service Bulletin 601R-27-139, dated December 22, 2011, which is not
incorporated by reference in this AD.
(3) This paragraph provides credit for the actions required by
paragraph (h) of this AD, if those actions were performed before
March 27, 2006 (the effective date of AD 2006-05-11 R1, Amendment
39-14528 (71 FR 15323, March 28, 2006)), using Bombardier Alert
Service Bulletin A601R-27-144, Revision B, dated December 20, 2006,
including Appendix A, Revision A, dated December 20, 2006.
(4) This paragraph provides credit for actions required by
paragraph (i) of this AD, if those actions were performed before May
19, 2008 (the effective date of AD 2008-08-09, Amendment 39-15461
(73 FR 19979, April 14, 2008)), using Bombardier Alert Service
Bulletin A601R-27-144, Revision B, dated December 20, 2006,
including Appendix A, Revision A, dated December 20, 2006.
[[Page 21077]]
(n) Other FAA AD Provisions
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. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. 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,
notify your appropriate principal inspector, or lacking a principal
inspector, the manager of the local flight standards district
office/certificate holding district office. The AMOC approval letter
must specifically reference this AD. AMOCs approved previously in
accordance with AD 2008-08-09, Amendment 39-15461 (73 FR 19979,
April 14, 2008), are approved as AMOCs for the corresponding
provisions of paragraphs (g), (h), and (i) of 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.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2005-41R1, dated May 10,
2012, and the service bulletins specified in paragraphs (o)(1)(i)
through (o)(1)(v) of this AD, for related information.
(i) Bombardier Alert Service Bulletin A601R-27-144, Revision A,
dated February 14, 2006, including Appendix A, dated September 15,
2005.
(ii) Bombardier Alert Service Bulletin A601R-27-144, Revision B,
dated December 20, 2006, including Appendix A, Revision A, dated
December 20, 2006.
(iii) Bombardier Alert Service Bulletin A601R-27-144, Revision
E, dated October 2, 2012, including Appendix A, Revision A, dated
December 20, 2006.
(iv) Bombardier Service Bulletin 601R-27-139, Revision A, dated
May 28, 2012.
(v) Bombardier Temporary Revision (TR) 2B-1784, dated October
24, 2003, to the CL-600-2B19 Canadair Regional Jet Maintenance
Requirements Manual, Part 2, Appendix B, ``Airworthiness
Limitations.''
(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; email [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, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on March 28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-08204 Filed 4-8-13; 8:45 am]
BILLING CODE 4910-13-P