Airworthiness Directives; Bombardier, Inc. Airplanes, 5670-5674 [2015-01661]
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5670
Federal Register / Vol. 80, No. 22 / Tuesday, February 3, 2015 / Rules and Regulations
additional data from advanced
approaches HCs.
Pursuant to the PRA’s emergency
review process, 44 U.S.C. 3507(j), the
Board is filing an emergency clearance
review to eliminate Schedule SC–R,
Regulatory Capital, Part I, on the Parent
Company Only Financial Statements for
Small Holding Companies (FR Y–9SP)
to reduce burden on small SLHCs
immediately. In the emergency
submission, the burden for the FR Y–
9SP related to the elimination of
Schedule SC–R, Regulatory Capital, Part
I, would decrease by 156,935 hours. The
change implemented through the
emergency clearance process would be
effective for six months. The Board is
now proposing to make the change
permanent and welcomes public
comment on any aspect of this
information collection. The burden
estimates below reflect the updated
number from the total emergency
clearance review.
tkelley on DSK3SPTVN1PROD with RULES
Estimated Paperwork Burden
Estimated Burden per Response:
FR Y–9C (non Advanced Approaches
bank holding companies)—48.84
hours;
FR Y–9C (Advanced Approaches bank
holding companies)—50.09 hours;
FR Y–9LP—5.25 hours;
FR Y–9SP—5.40 hours;
FR Y–9ES—0.5 hours; and
FR Y–9CS—0.5 hours.
Number of respondents:
FR Y–9C (non Advanced Approaches
bank holding companies)—644;
FR Y–9C (Advanced Approaches bank
holding companies)—12;
FR Y–9LP—818;
FR Y–9SP—4,390;
FR Y–9ES—86; and
FR Y–9CS—236.
Total estimated annual burden:
FR Y–9C (non Advanced Approaches
bank holding companies)—125,812
hours;
FR Y–9C (Advanced Approaches bank
holding companies)—2,404 hours;
FR Y–9LP—17,178 hours;
FR Y–9SP—47,412 hours;
FR Y–9ES—43 hours; and
FR Y–9CS—472 hours. (Total burden
193,321 hours)
C. Plain Language
Section 722 of the Gramm-LeachBliley Act requires the Federal banking
agencies to use ‘‘plain language’’ in all
proposed and final rules published after
January 1, 2000. In light of this
requirement, the Board has sought to
present the interim final rule in a simple
and straightforward manner. The Board
invites comments on whether there are
additional steps it could take to make
the rule easier to understand.
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List of Subjects in 12 CFR Part 217
DEPARTMENT OF TRANSPORTATION
Administrative practice and
procedure, Banks, banking, Capital,
Federal Reserve System, Holding
companies, Reporting and
recordkeeping requirements, Securities.
Federal Aviation Administration
Board of Governors of the Federal
Reserve System
12 CFR CHAPTER II
For the reasons set forth in the
supplementary information, the Board
amends 12 CFR Chapter II part 217 to
read as follows:
PART 217—CAPITAL ADEQUACY OF
BANK HOLDING COMPANIES,
SAVINGS AND LOAN HOLDING
COMPANIES, AND STATE MEMBER
BANKS (REGULATION Q)
1. The authority citation for part 217
continues to read as follows:
■
Authority: 12 U.S.C. 248(a), 321–338a,
481–486, 1462a, 1467a, 1818, 1828, 1831n,
1831o, 1831p–l, 1831w, 1835, 1844(b), 1851,
3904, 3906–3909, 4808, 5365, 5368, 5371.
2. In § 217.1, amend paragraph
(c)(1)(iii) to read as follows:
■
§ 217.1 Purpose, applicability,
reservations of authority, and timing.
*
*
*
*
*
(c) * * *
(1) * * *
(iii) A covered savings and loan
holding company domiciled in the
United States, other than a savings and
loan holding company that has total
consolidated assets of less than $500
million and meets the requirements of
12 CFR part 225, Appendix C, as if the
savings and loan holding company were
a bank holding company and the
savings association were a bank. For
purposes of compliance with the capital
adequacy requirements and calculations
in this part, savings and loan holding
companies that do not file the FR Y–9C
should follow the instructions to the FR
Y–9C.
*
*
*
*
*
By order of the Board of Governors of the
Federal Reserve System, January 29, 2015.
Michael Lewandowski,
Associate Secretary of the Board.
[FR Doc. 2015–02038 Filed 1–30–15; 11:15 am]
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[Docket No. FAA–2015–0082; Directorate
Identifier 2014–NM–233–AD; Amendment
39–18092; AD 2015–02–23]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Authority and Issuance
BILLING CODE 6210–01–P
14 CFR Part 39
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model CL–600–1A11
(CL–600), CL–600–2A12 (CL–601), and
CL–600–2B16 (CL–601–3A, and CL–
601–3R Variants) airplanes. This AD
requires repetitive inspections for
fractured or incorrectly oriented
fasteners on the inboard flap hinge-box
forward fittings on both wings, and
replacement of all fasteners, if
necessary. This AD was prompted by
several reports of incorrectly oriented
and fractured fasteners found on the
inboard flap hinge-box forward fitting at
wing station (WS) 76.50. We are issuing
this AD to detect and correct incorrectly
oriented or fractured fasteners, which
could result in detachment of the flap
hinge-box and the flap surface, and
consequent reduced controllability of
the airplane.
DATES: This AD becomes effective
February 18, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 18, 2015.
We must receive comments on this
AD by March 20, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, 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, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
SUMMARY:
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For service information identified in
this AD, contact Bombardier, Inc., 400
ˆ
´
Cote-Vertu Road West, Dorval, Quebec
H4S 1Y9, Canada; telephone 514–855–
5000; fax 514–855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com. You may view
this 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. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0082.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0082; 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 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: Aziz
Ahmed, Aerospace Engineer, Airframe
and Mechanical Systems Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7329; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
tkelley on DSK3SPTVN1PROD with RULES
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Emergency Airworthiness Directive CF–
2013–39R2, dated December 12, 2014
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition on certain Bombardier, Inc.
Model CL–600–1A11 (CL–600), CL–
600–2A12 (CL–601), and CL–600–2B16
(CL–601–3A, and CL–601–3R Variants)
airplanes. The MCAI states:
There have been three in-service reports on
604 Variant aeroplanes of a fractured fastener
head on the inboard flap hinge-box forward
fitting at Wing Station (WS) 76.50, found
during a routine maintenance inspection.
Investigation revealed that the installation of
these fasteners on the inboard flap hinge-box
forward fittings at WS 76.50 and WS 127.25,
on both wings, does not conform to the
engineering drawings. Incorrect installation
may result in premature failure of the
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fasteners attaching the inboard flap hinge-box
forward fitting. Failure of the fasteners could
lead to the detachment of the flap hinge box
and consequently the detachment of the flap
surface. The loss of a flap surface could
* * * [result in reduced controllability of the
airplane].
The original issue of this [Canadian] AD
[dated December 6, 2013] [https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-0054-0002]
[which corresponds to FAA AD 2014–03–17,
Amendment 39–17754 (79 FR 9389, February
19, 2014)] mandated a detailed visual
inspection (DVI) of each inboard flap hingebox forward fitting, on both wings, and
rectification as required. Incorrectly oriented
fasteners require repetitive inspections until
the terminating action is accomplished.
Although there have been no reported
fractured fastener heads found to date on any
model CL–600–1A11, –2A12 or –2B16 (601–
3A–3R Variant) aeroplanes, incorrectly
oriented fasteners may also be installed.
After the issuance of the original
[Canadian] AD [dated August 15, 2014], there
has been one reported incident on a 604
Variant aeroplane where four fasteners were
found fractured on the same flap hinge-box
forward fitting. The investigation determined
that the fasteners were incorrectly installed.
Revision 1 of this [Canadian] AD was
issued to remove the 604 Variant aeroplanes
from the Applicability section since they
were addressed in [Canadian] AD CF–2014–
27 [dated August 15, 2014] [which
corresponds to FAA AD 2014–17–51,
Amendment 39–17999 (79 FR 64088, October
28, 2014)] and to clarify paragraphs A.2. and
C of this [Canadian] AD so that it matched
the Bombardier Alert Service Bulletins.
After the issuance of Revision 1 of this
[Canadian] AD, there have been several
reports of incorrectly oriented fasteners
found on CL–600–1A11, and –2B16 (601–3A
Variant) aeroplanes. Although there have
been no reports of fractured fasteners found
to date, incorrectly oriented fasteners could
result in the premature failure of the forward
flap hinge-box fitting.
Revision 2 of this [Canadian] AD is issued
to reduce the initial and repetitive inspection
intervals and to impose replacement of the
incorrectly oriented fasteners * * *. This
[Canadian] AD also corrects various
terminology errors which were found in
previous French versions of this [Canadian]
AD.
You may examine the MCAI on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2015–0082.
Related Rulemaking
On February 3, 2014, we issued AD
2014–03–17, Amendment 39–17754 (79
FR 9389, February 19, 2014) for
Bombardier, Inc. Model CL–600–1A11
(CL–600) airplanes, having serial
numbers (S/Ns) 1004 through 1085
inclusive; Model CL–600–2A12 (CL–
601) airplanes, having S/Ns 3001
through 3066 inclusive; and Model CL–
600–2B16 (CL–601–3A, CL–601–3R, &
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5671
CL–604 Variants) airplanes, having S/Ns
5001 through 5194 inclusive, 5301
through 5665 inclusive, and 5701
through 5920 inclusive. AD 2014–03–17
requires repetitive inspections for
fractured or incorrectly oriented
fasteners on the inboard flap hinge-box
forward fittings on both wings, and
fastener replacement if necessary, and
was prompted by two reports of
fractured fastener heads found on the
inboard flap hinge-box forward fitting.
AD 2014–03–17 was issued to detect
and correct incorrectly oriented or
fractured fasteners, which could result
in detachment of the flap hinge-box and
the flap surface, and consequent
reduced controllability of the airplane.
After we issued AD 2014–03–17,
Amendment 39–17754 (79 FR 9389,
February 19, 2014), we received a report
of an additional incident of fractured
fasteners on a Model CL–600–2B16 (CL–
604 Variant) airplane. We then issued
AD 2014–17–51, Amendment 39–17999
(79 FR 64088, October 28, 2014), as a
‘‘stand-alone’’ AD to reduce compliance
times for the initial and repetitive
inspections only for Model CL–600–
2B16 airplanes having S/Ns 5301
through 5665 inclusive, and 5701
through 5920 inclusive. Issuing AD
2014–17–51 as a ‘‘stand-alone’’ AD
instead of superseding AD 2014–03–17
was determined to be clearer and less
burdensome for operators with airplanes
unaffected by the reduced compliance
times required by AD 2014–17–51.
Since we issued AD 2014–17–51,
Amendment 39–17999 (79 FR 64088,
October 28, 2014), we received a report
of incorrectly oriented fasteners on a
Model CL–600–1A11 airplane and on a
Model CL–600–2B16 (601–3A Variant)
airplane. Consequently, we determined
it was necessary to issue this AD to
reduce compliance times for the other
airplane models not affected by AD
2014–17–51. Doing so reduces the
potential complexity for two groups of
airplanes (those that are and are not
affected by AD 2014–17–51).
Related Service Information Under 1
CFR Part 51
Bombardier has issued Alert Service
Bulletins A600–0763, Revision 02,
dated December 9, 2014, including
Appendices 1 and 2, dated September
26, 2013; and A601–0627, Revision 02,
dated December 9, 2014, including
Appendices 1 and 2, dated September
26, 2013. The service information
describes procedures for repetitive
inspections of the fasteners on the
inboard flap hinge-box forward fittings
on both wings, and replacement of all
fasteners, if necessary. The actions
described in this service information are
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intended to correct the unsafe condition
identified in the MCAI. This service
information is reasonably available; see
ADDRESSES for ways to access this
service information.
FAA’s Determination and Requirements
of This 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 issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because we have received several
reports of incorrectly oriented and
fractured fasteners found on the inboard
flap hinge-box forward fitting at WS
76.50. Incorrectly oriented or fractured
fasteners could result in detachment of
the flap hinge-box and the flap surface,
and consequent reduced controllability
of the airplane. Therefore, we
determined that notice and opportunity
for public comment before issuing this
AD are impracticable and that good
cause exists for making this amendment
effective in fewer than 30 days.
tkelley on DSK3SPTVN1PROD with RULES
Interim Action
We consider this AD interim action.
We are currently considering requiring
replacement of incorrectly oriented
fasteners, which will constitute
terminating action for the repetitive
inspections required by this AD action.
However, the planned compliance time
for the replacement would allow enough
time to provide notice and opportunity
for prior public comment on the merits
of the modification.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2015–0082;
Directorate Identifier 2014–NM–233–
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13:22 Feb 02, 2015
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AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this 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 AD.
Costs of Compliance
We estimate that this AD affects 120
airplanes 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 on U.S.
operators to be $10,200, or $85 per
product.
In addition, we estimate that any
necessary follow-on actions will take
about 58 work-hours and require parts
costing $753, for a cost of $5,683 per
product. We have no way of
determining the number of aircraft that
might need this action.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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.
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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 that 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);
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2015–02–23 Bombardier, Inc.: Amendment
39–18092. Docket No. FAA–2015–0082;
Directorate Identifier 2014–NM–233–AD.
(a) Effective Date
This AD becomes effective February 18,
2015.
(b) Affected ADs
This AD affects AD 2014–03–17,
Amendment 39–17754 (79 FR 9389, February
19, 2014).
(c) Applicability
This AD applies to the Bombardier, Inc.
airplanes identified in paragraphs (c)(1),
(c)(2), and (c)(3) of this AD, certificated in
any category.
(1) Bombardier, Inc. Model CL–600–1A11
(CL–600) airplanes, having serial numbers (S/
Ns) 1004 through 1085 inclusive.
(2) Bombardier, Inc. Model CL–600–2A12
(CL–601) airplanes, having S/Ns 3001
through 3066 inclusive.
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(3) Bombardier, Inc. Model CL–600–2B16
(CL–601–3A and CL–601–3R Variants)
airplanes, having S/Ns 5001 through 5194
inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by several reports
of incorrectly oriented and fractured
fasteners found on the inboard flap hinge-box
forward fitting at wing station (WS) 76.50.
We are issuing this AD to detect and correct
incorrectly oriented or fractured fasteners,
which could result in detachment of the flap
hinge-box and the flap surface, and
consequent reduced controllability of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
tkelley on DSK3SPTVN1PROD with RULES
(g) Inspection on Airplanes Not Previously
Inspected
For airplanes that have not been inspected
as required by paragraph (g) of AD 2014–03–
17, Amendment 39–17754 (79 FR 9389,
February 19, 2014), as of the effective date of
this AD: Within 10 flight cycles after the
effective date of this AD or 100 flight cycles
after March 6, 2014 (the effective date of AD
2014–03–17), whichever occurs first, do a
detailed visual inspection for incorrect
orientation and any fractured or missing
fastener heads of each inboard flap fastener
of the hinge-box forward fitting at WS 76.50
and WS 127.25, on both wings, in accordance
with the Accomplishment Instructions of the
applicable service information specified in
paragraphs (g)(1) and (g)(2) of this AD.
Accomplishing the inspection required by
this paragraph terminates the requirements of
paragraph (g) of AD 2014–03–17 for the
inspected airplane only.
(1) For Model CL–600–1A11 (CL–600)
airplanes having S/Ns 1004 through 1085
inclusive: Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(2) For Model CL–600–2A12 (CL–601)
airplanes having S/Ns 3001 through 3066
inclusive, and Model CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes
having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601–
0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated
September 26, 2013.
(h) Corrective Actions for Paragraph (g) of
This AD
(1) If, during any inspection required by
paragraph (g) of this AD, all fasteners are
found correctly oriented and not fractured,
and no fastener heads are missing (fasteners
found intact): No further action is required by
this AD.
(2) If, during any inspection required by
paragraph (g) of this AD, any fastener is
found incorrectly oriented but no fasteners
are fractured or are missing a fastener head
(fasteners found intact), repeat the inspection
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required by paragraph (g) of this AD
thereafter at intervals not to exceed 10 flight
cycles until the replacement specified in
paragraph (h)(3) or (k) of this AD is
accomplished.
(3) If, during any inspection required by
paragraph (g) of this AD, any fastener is
found fractured or has a missing fastener
head: Before further flight, remove and
replace all forward and aft fasteners
(regardless of orientation or condition) at WS
76.50 and WS 127.25, on both wings, in
accordance with the Accomplishment
Instructions of the applicable service
information specified in paragraphs (h)(3)(i)
and (h)(3)(ii) of this AD, except as required
by paragraph (m) of this AD. After
accomplishing the replacement required by
this paragraph, no further action is required
by this AD.
(i) For Model CL–600–1A11 (CL–600)
airplanes having S/Ns 1004 through 1085
inclusive: Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(ii) For Model CL–600–2A12 (CL–601)
airplanes having S/Ns 3001 through 3066
inclusive, and Model CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes
having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601–
0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated
September 26, 2013.
(i) Inspection for Airplanes Previously
Inspected and Found To Have Incorrectly
Oriented Fastener(s)
For airplanes on which an inspection
required by paragraph (g) or (j) of AD 2014–
03–17, Amendment 39–17754 (79 FR 9389,
February 19, 2014), has been done as of the
effective date of this AD, and on which any
incorrectly oriented fastener was found but
no fasteners were fractured (fasteners found
intact): Except as provided by paragraph (l)
of this AD, within 10 flight cycles after the
effective date of this AD, or within 100 flight
cycles after accomplishing the most recent
inspection required by AD 2014–03–17,
whichever occurs first, do a detailed visual
inspection for any fractured or missing
fastener heads of each inboard flap fastener
of the hinge-box forward fitting at WS 76.50
and WS 127.25, on both wings. Do the
inspection in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraphs (i)(1) and (i)(2) of this AD.
Accomplishing the inspection required by
this paragraph terminates the requirements of
paragraphs (g) and (j) of AD 2014–03–17 for
the inspected airplane only.
(1) For Model CL–600–1A11 (CL–600)
airplanes having S/Ns 1004 through 1085
inclusive: Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(2) For Model CL–600–2A12 (CL–601)
airplanes having S/Ns 3001 through 3066
inclusive, and Model CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes
having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601–
PO 00000
Frm 00009
Fmt 4700
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5673
0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated
September 26, 2013.
(j) Corrective Actions for Paragraph (i) of
This AD
(1) If, during any inspection required by
paragraph (i) of this AD, no fasteners are
found fractured or have missing fastener
heads (fasteners are intact), repeat the
inspection required by paragraph (i) of this
AD thereafter at intervals not to exceed 10
flight cycles until the replacement specified
in paragraph (j)(2) or (k) of this AD is
accomplished.
(2) If, during any inspection required by
paragraph (i) of this AD, any fastener is found
fractured or has a missing fastener head:
Before further flight, remove and replace all
forward and aft fasteners (regardless of
orientation or condition) at WS 76.50 and WS
127.25, on both wings, in accordance with
the Accomplishment Instructions of the
applicable service information specified in
paragraphs (j)(2)(i) and (j)(2)(ii) of this AD,
except as required by paragraph (m) of this
AD. After accomplishing the replacement
required by this paragraph, no further action
is required by this AD.
(i) For Model CL–600–1A11 (CL–600)
airplanes having S/Ns 1004 through 1085
inclusive: Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(ii) For Model CL–600–2A12 (CL–601)
airplanes having S/Ns 3001 through 3066
inclusive, and Model CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes
having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601–
0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated
September 26, 2013.
(k) Optional Terminating Action for
Incorrectly Oriented Fasteners
Replacement of all forward and aft
fasteners (regardless of orientation or
condition) at WS 76.50 and WS 127.25, on
both wings, terminates the requirements of
this AD. The replacement must be done in
accordance with the Accomplishment
Instructions of the applicable service
information specified in paragraphs (k)(1)
and (k)(2) of this AD, except as provided by
paragraph (m) of this AD. Doing the
replacement specified in this paragraph
terminates the requirements of paragraphs (g)
and (j) of AD 2014–03–17, Amendment 39–
17754 (79 FR 9389, February 19, 2014), only
for the airplane on which the replacement
was done.
(1) For Model CL–600–1A11 (CL–600)
airplanes having S/Ns 1004 through 1085
inclusive: Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(2) For Model CL–600–2A12 (CL–601)
airplanes having S/Ns 3001 through 3066
inclusive, and Model CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes
having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601–
0627, Revision 02, dated December 9, 2014,
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Federal Register / Vol. 80, No. 22 / Tuesday, February 3, 2015 / Rules and Regulations
including Appendices 1 and 2, dated
September 26, 2013.
(l) Exception for Previously Replaced
Fasteners
Replacement of all fractured and
incorrectly oriented forward and aft
fasteners, as specified in paragraph (i) or (k)
of AD 2014–03–17, Amendment 39–17754
(79 FR 9389, February 19, 2014), if done
before the effective date of this AD, is
considered acceptable for compliance with
the requirements of this AD.
(m) Exception to the Service Information
Where Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013; and Bombardier Alert
Service Bulletin A601–0627, Revision 02,
dated December 9, 2014, including
Appendices 1 and 2, dated September 26,
2013; specify to contact Bombardier for
repair instructions, before further flight,
repair using a method approved by the
Manager, New York Aircraft Certification
Office (ACO), FAA; or Transport Canada
Civil Aviation (TCCA); or Bombardier’s
TCCA Design Approval Organization (DAO).
tkelley on DSK3SPTVN1PROD with RULES
(n) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g), (h), and (i) of this
AD, if those actions were performed before
the effective date of this AD using the
applicable service information identified in
paragraphs (n)(1) through (n)(4) of this AD.
(1) Bombardier Alert Service Bulletin
A600–0763, including Appendices 1 and 2,
dated September 26, 2013, which was
previously incorporated by reference on
March 6, 2014 (79 FR 9389, February 19,
2014).
(2) Bombardier Alert Service Bulletin
A600–0763, Revision 01, dated February 26,
2014, including Appendices 1 and 2, dated
September 26, 2013, which is not
incorporated by reference in this AD.
(3) Bombardier Alert Service Bulletin
A601–0627, including Appendices 1 and 2,
dated September 26, 2013, which was
previously incorporated by reference on
March 6, 2014 (79 FR 9389, February 19,
2014).
(4) Bombardier Alert Service Bulletin
A601–0627, Revision 01, dated February 26,
2014, including Appendices 1 and 2, dated
September 26, 2013, which is not
incorporated by reference in this AD.
(o) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York 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. If sending information directly
to the ACO, send it to ATTN: Program
Manager, Continuing Operational Safety,
FAA, New York ACO, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7300; fax 516–794–5531. Before
VerDate Sep<11>2014
13:22 Feb 02, 2015
Jkt 235001
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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170,
Engine and Propeller Directorate, FAA; or
TCCA; or Bombardier, Inc.’s TCCA DAO. If
approved by the DAO, the approval must
include the DAO-authorized signature.
Issued in Renton, Washington, on January
20, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
(p) Special Flight Permits
21 CFR Part 870
Special flight permits to operate the
airplane to a location where the airplane can
be repaired in accordance with sections
21.197 and 31.199 of the Federal Aviation
Regulations (14 CFR 21.197 and 21.199) are
not allowed.
[Docket No. FDA–2013–N–0234]
(q) Related Information
AGENCY:
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Emergency Airworthiness Directive CF–
2013–39R2, dated December 12, 2014, for
related information. You may examine the
MCAI on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2015–0082.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (r)(3) and (r)(4) of this AD.
HHS.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(ii) Bombardier Alert Service Bulletin
A601–0627, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com.
(4) You may view this 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.
(5) You may view this 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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[FR Doc. 2015–01661 Filed 2–2–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
Effective Date of Requirement for
Premarket Approval for Automated
External Defibrillator Systems;
Republication
ACTION:
Food and Drug Administration,
Final order; republication.
The Food and Drug
Administration (FDA or the Agency) is
republishing in its entirety a final order
entitled ‘‘Effective Date of Requirement
for Premarket Approval for Automated
External Defibrillator’’ that published in
the Federal Register on January 29,
2015 (80 FR 4783). FDA is republishing
to correct an inadvertent omission of a
comment regarding adverse tissue
reaction as a risk to health and the
Agency’s response to that comment. The
final order requires the filing of
premarket approval applications (PMA)
for automated external defibrillator
(AED) systems, which consist of an AED
and those AED accessories necessary for
the AED to detect and interpret an
electrocardiogram and deliver an
electrical shock (e.g., pad electrodes,
batteries, adapters, and hardware keys
for pediatric use).
DATES: This order is effective on
February 3, 2015.
FOR FURTHER INFORMATION CONTACT:
Linda Ricci, Center for Devices and
Radiological Health, 10903 New
Hampshire Ave., Bldg. 66, rm. 1314,
Silver Spring, MD 20993, 301–796–
6325, linda.ricci@fda.hhs.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
I. Background—Regulatory Authorities
The Federal Food, Drug, and Cosmetic
Act (the FD&C Act), as amended by the
Medical Device Amendments of 1976
(the 1976 amendments) (Pub. L. 94–
295), the Safe Medical Devices Act of
1990 (Pub. L. 101–629), the Food and
Drug Administration Modernization Act
of 1997 (Pub. L. 105–115), the Medical
Device User Fee and Modernization Act
E:\FR\FM\03FER1.SGM
03FER1
]]>Agencies
[Federal Register Volume 80, Number 22 (Tuesday, February 3, 2015)]
[Rules and Regulations]
[Pages 5670-5674]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-01661]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0082; Directorate Identifier 2014-NM-233-AD;
Amendment 39-18092; AD 2015-02-23]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and
CL-600-2B16 (CL-601-3A, and CL-601-3R Variants) airplanes. This AD
requires repetitive inspections for fractured or incorrectly oriented
fasteners on the inboard flap hinge-box forward fittings on both wings,
and replacement of all fasteners, if necessary. This AD was prompted by
several reports of incorrectly oriented and fractured fasteners found
on the inboard flap hinge-box forward fitting at wing station (WS)
76.50. We are issuing this AD to detect and correct incorrectly
oriented or fractured fasteners, which could result in detachment of
the flap hinge-box and the flap surface, and consequent reduced
controllability of the airplane.
DATES: This AD becomes effective February 18, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 18,
2015.
We must receive comments on this AD by March 20, 2015.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
[[Page 5671]]
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
thd.crj@aero.bombardier.com; Internet https://www.bombardier.com. You
may view this 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. It
is also available on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2015-0082.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0082; 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 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: Aziz Ahmed, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7329; fax 516-794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Emergency Airworthiness
Directive CF-2013-39R2, dated December 12, 2014 (referred to after this
as the Mandatory Continuing Airworthiness Information, or ``the
MCAI''), to correct an unsafe condition on certain Bombardier, Inc.
Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-
601-3A, and CL-601-3R Variants) airplanes. The MCAI states:
There have been three in-service reports on 604 Variant
aeroplanes of a fractured fastener head on the inboard flap hinge-
box forward fitting at Wing Station (WS) 76.50, found during a
routine maintenance inspection. Investigation revealed that the
installation of these fasteners on the inboard flap hinge-box
forward fittings at WS 76.50 and WS 127.25, on both wings, does not
conform to the engineering drawings. Incorrect installation may
result in premature failure of the fasteners attaching the inboard
flap hinge-box forward fitting. Failure of the fasteners could lead
to the detachment of the flap hinge box and consequently the
detachment of the flap surface. The loss of a flap surface could * *
* [result in reduced controllability of the airplane].
The original issue of this [Canadian] AD [dated December 6,
2013] [https://www.regulations.gov/#!documentDetail;D=FAA-2014-0054-
0002] [which corresponds to FAA AD 2014-03-17, Amendment 39-17754
(79 FR 9389, February 19, 2014)] mandated a detailed visual
inspection (DVI) of each inboard flap hinge-box forward fitting, on
both wings, and rectification as required. Incorrectly oriented
fasteners require repetitive inspections until the terminating
action is accomplished.
Although there have been no reported fractured fastener heads
found to date on any model CL-600-1A11, -2A12 or -2B16 (601-3A-3R
Variant) aeroplanes, incorrectly oriented fasteners may also be
installed.
After the issuance of the original [Canadian] AD [dated August
15, 2014], there has been one reported incident on a 604 Variant
aeroplane where four fasteners were found fractured on the same flap
hinge-box forward fitting. The investigation determined that the
fasteners were incorrectly installed.
Revision 1 of this [Canadian] AD was issued to remove the 604
Variant aeroplanes from the Applicability section since they were
addressed in [Canadian] AD CF-2014-27 [dated August 15, 2014] [which
corresponds to FAA AD 2014-17-51, Amendment 39-17999 (79 FR 64088,
October 28, 2014)] and to clarify paragraphs A.2. and C of this
[Canadian] AD so that it matched the Bombardier Alert Service
Bulletins.
After the issuance of Revision 1 of this [Canadian] AD, there
have been several reports of incorrectly oriented fasteners found on
CL-600-1A11, and -2B16 (601-3A Variant) aeroplanes. Although there
have been no reports of fractured fasteners found to date,
incorrectly oriented fasteners could result in the premature failure
of the forward flap hinge-box fitting.
Revision 2 of this [Canadian] AD is issued to reduce the initial
and repetitive inspection intervals and to impose replacement of the
incorrectly oriented fasteners * * *. This [Canadian] AD also
corrects various terminology errors which were found in previous
French versions of this [Canadian] AD.
You may examine the MCAI on the Internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2015-0082.
Related Rulemaking
On February 3, 2014, we issued AD 2014-03-17, Amendment 39-17754
(79 FR 9389, February 19, 2014) for Bombardier, Inc. Model CL-600-1A11
(CL-600) airplanes, having serial numbers (S/Ns) 1004 through 1085
inclusive; Model CL-600-2A12 (CL-601) airplanes, having S/Ns 3001
through 3066 inclusive; and Model CL-600-2B16 (CL-601-3A, CL-601-3R, &
CL-604 Variants) airplanes, having S/Ns 5001 through 5194 inclusive,
5301 through 5665 inclusive, and 5701 through 5920 inclusive. AD 2014-
03-17 requires repetitive inspections for fractured or incorrectly
oriented fasteners on the inboard flap hinge-box forward fittings on
both wings, and fastener replacement if necessary, and was prompted by
two reports of fractured fastener heads found on the inboard flap
hinge-box forward fitting. AD 2014-03-17 was issued to detect and
correct incorrectly oriented or fractured fasteners, which could result
in detachment of the flap hinge-box and the flap surface, and
consequent reduced controllability of the airplane.
After we issued AD 2014-03-17, Amendment 39-17754 (79 FR 9389,
February 19, 2014), we received a report of an additional incident of
fractured fasteners on a Model CL-600-2B16 (CL-604 Variant) airplane.
We then issued AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October
28, 2014), as a ``stand-alone'' AD to reduce compliance times for the
initial and repetitive inspections only for Model CL-600-2B16 airplanes
having S/Ns 5301 through 5665 inclusive, and 5701 through 5920
inclusive. Issuing AD 2014-17-51 as a ``stand-alone'' AD instead of
superseding AD 2014-03-17 was determined to be clearer and less
burdensome for operators with airplanes unaffected by the reduced
compliance times required by AD 2014-17-51.
Since we issued AD 2014-17-51, Amendment 39-17999 (79 FR 64088,
October 28, 2014), we received a report of incorrectly oriented
fasteners on a Model CL-600-1A11 airplane and on a Model CL-600-2B16
(601-3A Variant) airplane. Consequently, we determined it was necessary
to issue this AD to reduce compliance times for the other airplane
models not affected by AD 2014-17-51. Doing so reduces the potential
complexity for two groups of airplanes (those that are and are not
affected by AD 2014-17-51).
Related Service Information Under 1 CFR Part 51
Bombardier has issued Alert Service Bulletins A600-0763, Revision
02, dated December 9, 2014, including Appendices 1 and 2, dated
September 26, 2013; and A601-0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated September 26, 2013. The service
information describes procedures for repetitive inspections of the
fasteners on the inboard flap hinge-box forward fittings on both wings,
and replacement of all fasteners, if necessary. The actions described
in this service information are
[[Page 5672]]
intended to correct the unsafe condition identified in the MCAI. This
service information is reasonably available; see ADDRESSES for ways to
access this service information.
FAA's Determination and Requirements of This 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 issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because we
have received several reports of incorrectly oriented and fractured
fasteners found on the inboard flap hinge-box forward fitting at WS
76.50. Incorrectly oriented or fractured fasteners could result in
detachment of the flap hinge-box and the flap surface, and consequent
reduced controllability of the airplane. Therefore, we determined that
notice and opportunity for public comment before issuing this AD are
impracticable and that good cause exists for making this amendment
effective in fewer than 30 days.
Interim Action
We consider this AD interim action. We are currently considering
requiring replacement of incorrectly oriented fasteners, which will
constitute terminating action for the repetitive inspections required
by this AD action. However, the planned compliance time for the
replacement would allow enough time to provide notice and opportunity
for prior public comment on the merits of the modification.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2015-0082; Directorate
Identifier 2014-NM-233-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this 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 AD.
Costs of Compliance
We estimate that this AD affects 120 airplanes 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 on U.S. operators to be $10,200, or $85 per product.
In addition, we estimate that any necessary follow-on actions will
take about 58 work-hours and require parts costing $753, for a cost of
$5,683 per product. We have no way of determining the number of
aircraft that might need this action.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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 that 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);
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2015-02-23 Bombardier, Inc.: Amendment 39-18092. Docket No. FAA-
2015-0082; Directorate Identifier 2014-NM-233-AD.
(a) Effective Date
This AD becomes effective February 18, 2015.
(b) Affected ADs
This AD affects AD 2014-03-17, Amendment 39-17754 (79 FR 9389,
February 19, 2014).
(c) Applicability
This AD applies to the Bombardier, Inc. airplanes identified in
paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in
any category.
(1) Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes,
having serial numbers (S/Ns) 1004 through 1085 inclusive.
(2) Bombardier, Inc. Model CL-600-2A12 (CL-601) airplanes,
having S/Ns 3001 through 3066 inclusive.
[[Page 5673]]
(3) Bombardier, Inc. Model CL-600-2B16 (CL-601-3A and CL-601-3R
Variants) airplanes, having S/Ns 5001 through 5194 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by several reports of incorrectly oriented
and fractured fasteners found on the inboard flap hinge-box forward
fitting at wing station (WS) 76.50. We are issuing this AD to detect
and correct incorrectly oriented or fractured fasteners, which could
result in detachment of the flap hinge-box and the flap surface, and
consequent reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection on Airplanes Not Previously Inspected
For airplanes that have not been inspected as required by
paragraph (g) of AD 2014-03-17, Amendment 39-17754 (79 FR 9389,
February 19, 2014), as of the effective date of this AD: Within 10
flight cycles after the effective date of this AD or 100 flight
cycles after March 6, 2014 (the effective date of AD 2014-03-17),
whichever occurs first, do a detailed visual inspection for
incorrect orientation and any fractured or missing fastener heads of
each inboard flap fastener of the hinge-box forward fitting at WS
76.50 and WS 127.25, on both wings, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraphs (g)(1) and (g)(2) of this AD. Accomplishing
the inspection required by this paragraph terminates the
requirements of paragraph (g) of AD 2014-03-17 for the inspected
airplane only.
(1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763,
Revision 02, dated December 9, 2014, including Appendices 1 and 2,
dated September 26, 2013.
(2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated
December 9, 2014, including Appendices 1 and 2, dated September 26,
2013.
(h) Corrective Actions for Paragraph (g) of This AD
(1) If, during any inspection required by paragraph (g) of this
AD, all fasteners are found correctly oriented and not fractured,
and no fastener heads are missing (fasteners found intact): No
further action is required by this AD.
(2) If, during any inspection required by paragraph (g) of this
AD, any fastener is found incorrectly oriented but no fasteners are
fractured or are missing a fastener head (fasteners found intact),
repeat the inspection required by paragraph (g) of this AD
thereafter at intervals not to exceed 10 flight cycles until the
replacement specified in paragraph (h)(3) or (k) of this AD is
accomplished.
(3) If, during any inspection required by paragraph (g) of this
AD, any fastener is found fractured or has a missing fastener head:
Before further flight, remove and replace all forward and aft
fasteners (regardless of orientation or condition) at WS 76.50 and
WS 127.25, on both wings, in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraphs (h)(3)(i) and (h)(3)(ii) of this AD, except as required
by paragraph (m) of this AD. After accomplishing the replacement
required by this paragraph, no further action is required by this
AD.
(i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763,
Revision 02, dated December 9, 2014, including Appendices 1 and 2,
dated September 26, 2013.
(ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated
December 9, 2014, including Appendices 1 and 2, dated September 26,
2013.
(i) Inspection for Airplanes Previously Inspected and Found To Have
Incorrectly Oriented Fastener(s)
For airplanes on which an inspection required by paragraph (g)
or (j) of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February
19, 2014), has been done as of the effective date of this AD, and on
which any incorrectly oriented fastener was found but no fasteners
were fractured (fasteners found intact): Except as provided by
paragraph (l) of this AD, within 10 flight cycles after the
effective date of this AD, or within 100 flight cycles after
accomplishing the most recent inspection required by AD 2014-03-17,
whichever occurs first, do a detailed visual inspection for any
fractured or missing fastener heads of each inboard flap fastener of
the hinge-box forward fitting at WS 76.50 and WS 127.25, on both
wings. Do the inspection in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraphs (i)(1) and (i)(2) of this AD. Accomplishing the
inspection required by this paragraph terminates the requirements of
paragraphs (g) and (j) of AD 2014-03-17 for the inspected airplane
only.
(1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763,
Revision 02, dated December 9, 2014, including Appendices 1 and 2,
dated September 26, 2013.
(2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated
December 9, 2014, including Appendices 1 and 2, dated September 26,
2013.
(j) Corrective Actions for Paragraph (i) of This AD
(1) If, during any inspection required by paragraph (i) of this
AD, no fasteners are found fractured or have missing fastener heads
(fasteners are intact), repeat the inspection required by paragraph
(i) of this AD thereafter at intervals not to exceed 10 flight
cycles until the replacement specified in paragraph (j)(2) or (k) of
this AD is accomplished.
(2) If, during any inspection required by paragraph (i) of this
AD, any fastener is found fractured or has a missing fastener head:
Before further flight, remove and replace all forward and aft
fasteners (regardless of orientation or condition) at WS 76.50 and
WS 127.25, on both wings, in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraphs (j)(2)(i) and (j)(2)(ii) of this AD, except as required
by paragraph (m) of this AD. After accomplishing the replacement
required by this paragraph, no further action is required by this
AD.
(i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763,
Revision 02, dated December 9, 2014, including Appendices 1 and 2,
dated September 26, 2013.
(ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated
December 9, 2014, including Appendices 1 and 2, dated September 26,
2013.
(k) Optional Terminating Action for Incorrectly Oriented Fasteners
Replacement of all forward and aft fasteners (regardless of
orientation or condition) at WS 76.50 and WS 127.25, on both wings,
terminates the requirements of this AD. The replacement must be done
in accordance with the Accomplishment Instructions of the applicable
service information specified in paragraphs (k)(1) and (k)(2) of
this AD, except as provided by paragraph (m) of this AD. Doing the
replacement specified in this paragraph terminates the requirements
of paragraphs (g) and (j) of AD 2014-03-17, Amendment 39-17754 (79
FR 9389, February 19, 2014), only for the airplane on which the
replacement was done.
(1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763,
Revision 02, dated December 9, 2014, including Appendices 1 and 2,
dated September 26, 2013.
(2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated
December 9, 2014,
[[Page 5674]]
including Appendices 1 and 2, dated September 26, 2013.
(l) Exception for Previously Replaced Fasteners
Replacement of all fractured and incorrectly oriented forward
and aft fasteners, as specified in paragraph (i) or (k) of AD 2014-
03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), if done
before the effective date of this AD, is considered acceptable for
compliance with the requirements of this AD.
(m) Exception to the Service Information
Where Bombardier Alert Service Bulletin A600-0763, Revision 02,
dated December 9, 2014, including Appendices 1 and 2, dated
September 26, 2013; and Bombardier Alert Service Bulletin A601-0627,
Revision 02, dated December 9, 2014, including Appendices 1 and 2,
dated September 26, 2013; specify to contact Bombardier for repair
instructions, before further flight, repair using a method approved
by the Manager, New York Aircraft Certification Office (ACO), FAA;
or Transport Canada Civil Aviation (TCCA); or Bombardier's TCCA
Design Approval Organization (DAO).
(n) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g), (h), and (i) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service information identified in paragraphs (n)(1) through (n)(4)
of this AD.
(1) Bombardier Alert Service Bulletin A600-0763, including
Appendices 1 and 2, dated September 26, 2013, which was previously
incorporated by reference on March 6, 2014 (79 FR 9389, February 19,
2014).
(2) Bombardier Alert Service Bulletin A600-0763, Revision 01,
dated February 26, 2014, including Appendices 1 and 2, dated
September 26, 2013, which is not incorporated by reference in this
AD.
(3) Bombardier Alert Service Bulletin A601-0627, including
Appendices 1 and 2, dated September 26, 2013, which was previously
incorporated by reference on March 6, 2014 (79 FR 9389, February 19,
2014).
(4) Bombardier Alert Service Bulletin A601-0627, Revision 01,
dated February 26, 2014, including Appendices 1 and 2, dated
September 26, 2013, which is not incorporated by reference in this
AD.
(o) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York 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.
If sending information directly to the ACO, send it to ATTN: Program
Manager, Continuing Operational Safety, FAA, New York ACO, 1600
Stewart Avenue, Suite 410, Westbury, NY 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.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, New York ACO,
ANE-170, Engine and Propeller Directorate, FAA; or TCCA; or
Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval
must include the DAO-authorized signature.
(p) Special Flight Permits
Special flight permits to operate the airplane to a location
where the airplane can be repaired in accordance with sections
21.197 and 31.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) are not allowed.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Emergency Airworthiness Directive CF-2013-39R2,
dated December 12, 2014, for related information. You may examine
the MCAI on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2015-0082.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (r)(3) and (r)(4) of this AD.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Bombardier Alert Service Bulletin A600-0763, Revision 02,
dated December 9, 2014, including Appendices 1 and 2, dated
September 26, 2013.
(ii) Bombardier Alert Service Bulletin A601-0627, Revision 02,
dated December 9, 2014, including Appendices 1 and 2, dated
September 26, 2013.
(3) 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 thd.crj@aero.bombardier.com; Internet https://www.bombardier.com.
(4) You may view this 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.
(5) You may view this 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on January 20, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-01661 Filed 2-2-15; 8:45 am]
BILLING CODE 4910-13-P
