Airworthiness Directives; Bombardier, Inc. Airplanes, 65810-65812 [2012-26088]
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Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations
panel, which manufacturer fatigue and
damage tolerance analyses demonstrated
could have an effect on panel fatigue life. We
are issuing this AD to detect and correct such
cracking, which could result in the loss of
structural integrity of the airplane.
(j) Related Information
Refer to MCAI EASA Airworthiness
Directive 2011–0176, dated September 13,
2011; and Airbus Service Bulletin A320–53–
1244, excluding Appendix 1, dated March
17, 2011; for related information.
(f) Compliance
(k) 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 the AD specifies otherwise.
(i) Airbus Service Bulletin A320–53–1244,
excluding Appendix 1, dated March 17,
2011.
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus SAS–EAW
(Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@airbus.
com; Internet https://www.airbus.com.
(4) You may review copies of the 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.
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) Repetitive Inspection
Before the accumulation of 35,900 total
flight cycles or 88,100 total flight hours,
whichever occurs first: Do a high frequency
eddy current inspection for cracking of the
two rows of six fasteners at frame 35 between
stringers 5 and 6 on the left and right sides,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1244, excluding Appendix 1, dated
March 17, 2011. Repeat the inspection
thereafter at intervals not to exceed 28,100
flight cycles or 56,300 flight hours,
whichever occurs first.
(h) Corrective Action
If any crack is detected during any
inspection required by paragraph (g) of this
AD: Before further flight, repair the crack
using a method approved by either the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA) or
its delegated agent.
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(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1405; fax (425) 227–
1149. Information may be emailed to: 9ANM–116–AMOC–REQUESTS@faa.gov.
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) 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.
VerDate Mar<15>2010
16:49 Oct 30, 2012
Jkt 229001
Issued in Renton, Washington, on October
16, 2012.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–26198 Filed 10–30–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0592; Directorate
Identifier 2011–NM–253–AD; Amendment
39–17230 AD 2012–21–14]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
certain Bombardier, Inc. Model CL–600–
2B19 (Regional Jet Series 100 & 440)
airplanes. That AD currently requires a
one-time inspection of the shafts of the
SUMMARY:
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main landing gear (MLG) side-brace
fittings to detect corrosion, and the
forward and aft bushings in the lefthand and right-hand MLG side-brace
fittings to detect discrepancies. The
existing AD also requires corrective and
related actions if necessary. This new
AD requires repetitive detailed
inspections for corrosion and damage of
the MLG side-brace fitting, and
replacing the side-brace fitting shaft
with the re-designed side-brace fitting
shaft of the MLG if necessary. This AD
also requires eventual replacement of
certain side-brace fitting shafts with the
re-designed part. Replacement with a redesigned side-brace fitting shaft of the
MLG is terminating action for the
repetitive inspections. This AD was
prompted by reports of failure of the
side-brace fitting shaft of the main
landing gear (MLG) due to corrosion.
We are issuing this AD to prevent
fractures of the side-brace fitting shafts
of the MLG, and possible collapse of the
MLG.
DATES: This AD becomes effective
December 5, 2012.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 5, 2012.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Jeffrey Zimmer, 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–
7306; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on June 12, 2012 (77 FR 34870),
and proposed to supersede AD 2004–
22–23, Amendment 39–13851 (69 FR
64856, November 9, 2004). That NPRM
proposed to correct an unsafe condition
for the specified products. The MCAI
states:
Due to the failure of the main landing gear
(MLG) side brace fitting shaft, caused by
corrosion, [Transport Canada Civil Aviation
(TCCA)] Airworthiness Directive (AD) CF–
2002–41 was issued to require inspection and
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Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations
if needed, parts replacement. However, the
existing MLG side-brace fitting shafts
continued to fail. Failure of the MLG side
brace fitting shaft could result in the collapse
of the main landing gear.
This [TCCA] directive mandates the
repetitive detailed visual inspection [for
cracking and corrosion] of the MLG side
brace fitting and the incorporation of the redesigned MLG side brace fitting shaft part
number (P/N) 601R10247–3 as the
terminating action.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Request to Reference Revised Service
Bulletin
Comair, Inc. requested that we allow
the use of Bombardier Service Bulletin
601R–57–052, Revision A, dated
October 28, 2011, in the AD. Comair,
Inc. provided no reasons for the request.
We agree to reference the most recent
service information. Bombardier, Inc.
has issued Service Bulletin 601R–57–
052, Revision A, dated October 28,
2011. This service bulletin includes
editorial changes, but does not add work
for airplanes that have done the actions
using Bombardier Service Bulletin
601R–57–052, dated July 28, 2011
(which was referenced to as the
appropriate source of service
information in the NPRM (77 FR 34870,
June 12, 2012). Therefore we have
revised paragraphs (g)(1), (g)(2), (h)(1),
and (h)(2) of this AD to refer to
Bombardier Service Bulletin 601R–57–
052, Revision A, dated October 28,
2011. We have also added paragraph (i)
to this AD to allow credit for actions
performed before the effective date of
this AD using Bombardier Service
Bulletin 601R–57–052, dated July 28,
2011. We have re-designated subsequent
paragraphs accordingly.
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Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously
and except for minor editorial changes.
We have determined that these changes:
• Are consistent with the intent that
was proposed in the NPRM (77 FR
34870, June 12, 2012) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (77 FR 34870,
June 12, 2012).
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16:49 Oct 30, 2012
Jkt 229001
Costs of Compliance
We estimate that this AD will affect
about 584 products of U.S. registry.
We estimate that it will take about 10
work-hours per product to comply with
the new basic requirements of this AD.
The average labor rate is $85 per workhour. Required parts will cost about $0
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
this AD to the U.S. operators to be
$496,400, or $850 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 14 work-hours and require parts
costing $3,860, for a cost of $5,050 per
product. We have no way of
determining the number of products
that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
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);
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65811
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 AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM (77 FR 34870, June
12, 2012), the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
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
removing airworthiness directive (AD)
2004–22–23, Amendment 39–13851 (69
FR 64856, November 9, 2004), and
adding the following new AD:
■
2012–21–14 Bombardier, Inc.: Amendment
39–17230. Docket No. FAA–2012–0592;
Directorate Identifier 2011–NM–253–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective December 5, 2012.
(b) Affected ADs
This AD supersedes AD 2004–22–23,
Amendment 39–13851 (69 FR 64856,
November 9, 2004).
(c) Applicability
This AD applies to Bombardier, Inc. Model
CL–600–2B19 (Regional Jet Series 100 & 440)
airplanes; certificated in any category; serial
numbers 7003 through 7990 inclusive, and
8000 through 8999 inclusive.
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Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations
(d) Subject
Air Transport Association (ATA) of
America Code 57: Wings.
(e) Reason
This AD was prompted by reports of failure
of the side-brace fitting shaft of the main
landing gear (MLG) due to corrosion. We are
issuing this AD to prevent fractures of the
side-brace fitting shafts of the MLG, and
possible collapse of the MLG.
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(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) Inspection of MLG Side-Brace Fitting
Shaft and Replacement
(1) At the applicable times specified in
paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), and
(g)(1)(iv) of this AD, do a detailed inspection
for corrosion and damage of each side-brace
fitting shaft of the MLG, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 601R–57–052,
Revision A, dated October 28, 2011. Repeat
the inspections at the applicable times
specified in paragraphs (g)(1)(i), (g)(1)(ii),
(g)(1)(iii), and (g)(1)(iv) of this AD.
(i) For airplanes that average greater than
900 flight hours per year and have side-brace
shafts part number (P/N) 601R10237–1
installed in either the left- or right-hand
MLG, or if the side-brace shaft part number
cannot be identified without removal: Within
1,000 flight hours after the effective date of
this AD, do the inspection. Repeat the
inspections thereafter at intervals not to
exceed 1,000 flight hours until the
replacement specified in paragraph (g)(2) or
(h) of this AD is done.
(ii) For airplanes that average 900 flight
hours or less per year and have side-brace
shafts P/N 601R10237–1 installed on either
the left- or right-hand MLG, or if the sidebrace shaft part number cannot be identified
without removal: Within 18 months after the
effective date of this AD, do the inspection.
Repeat the inspections thereafter at intervals
not to exceed 18 months until the
replacement specified in paragraph (g)(2) or
(h) of this AD is done.
(iii) For airplanes that average greater than
900 flight hours per year and have side-brace
shafts P/N 601R10237–3 installed on either
the left- or right-hand MLG: Within 36
months after the effective date of this AD, do
the inspection. Repeat the inspections
thereafter at intervals not to exceed 36
months until the replacement specified in
paragraph (g)(2) or (h) of this AD is done.
(iv) For airplanes that average 900 flight
hours or less per year and have side-brace
shafts P/N 601R10237–3 installed on either
the left- or right-hand MLG: Within 60
months after the effective date of this AD, do
the inspection. Repeat the inspections
thereafter at intervals not to exceed 60
months until the replacement specified in
paragraph (g)(2) or (h) of this AD is done.
(2) If any corrosion or damage is found
during any inspection required by paragraph
(g) of this AD: Before further flight, replace
the side-brace fitting shaft with a new shaft
VerDate Mar<15>2010
16:49 Oct 30, 2012
Jkt 229001
P/N 601R10247–3, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 601R–57–052, Revision A,
dated October 28, 2011. Doing this
replacement terminates the inspection
requirements of paragraph (g) of this AD.
(h) Replacement
Do the replacement at the applicable time
specified in paragraph (h)(1) or (h)(2) of this
AD.
(1) For any airplanes that have side-brace
shafts P/N 601R10237–1 installed, or if the
side-brace shaft part number cannot be
identified without removal: Within 27
months after the effective date of this AD,
replace the side-brace fitting shaft of the MLG
with a new shaft having P/N 601R10247–3,
in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
601R–57–052, Revision A, dated October 28,
2011. Doing this replacement terminates the
inspection requirements of paragraph (g) of
this AD.
(2) For airplanes that have side-brace shafts
P/N 601R10237–3 installed: Within 117
months after the effective date of this AD,
replace the side-brace fitting shaft of the MLG
with a new shaft P/N 601R10247–3, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
601R–57–052, Revision A, dated October 28,
2011. Doing this replacement terminates the
inspection requirements of paragraph (g) of
this AD.
(i) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraphs (g) and (h) of
this AD, if those actions were performed
before the effective date of this AD using
Bombardier Service Bulletin 601R–57–052,
dated July 28, 2011 (which is not
incorporated by reference in this AD).
(j) 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. 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, 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.
(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
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to assure the product is airworthy before it
is returned to service.
(k) Related Information
Refer to MCAI Canadian Airworthiness
Directive CF–2011–39, dated October 25,
2011; and Bombardier Service Bulletin 601R–
57–052, dated July 28, 2011; for related
information.
(l) 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 the AD specifies otherwise.
(i) Bombardier Service Bulletin 601R–57–
052, Revision A, dated October 28, 2011.
(ii) Reserved.
(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 review copies of the 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.
Issued in Renton, Washington, on October
14, 2012.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–26088 Filed 10–30–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0719; Directorate
Identifier 2011–NM–240–AD; Amendment
39–17235; AD 2012–21–19]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A330–200 freighter series
airplanes; Model A330–200 and –300
SUMMARY:
E:\FR\FM\31OCR1.SGM
31OCR1
]]>Agencies
[Federal Register Volume 77, Number 211 (Wednesday, October 31, 2012)]
[Rules and Regulations]
[Pages 65810-65812]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-26088]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0592; Directorate Identifier 2011-NM-253-AD;
Amendment 39-17230 AD 2012-21-14]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100
& 440) airplanes. That AD currently requires a one-time inspection of
the shafts of the main landing gear (MLG) side-brace fittings to detect
corrosion, and the forward and aft bushings in the left-hand and right-
hand MLG side-brace fittings to detect discrepancies. The existing AD
also requires corrective and related actions if necessary. This new AD
requires repetitive detailed inspections for corrosion and damage of
the MLG side-brace fitting, and replacing the side-brace fitting shaft
with the re-designed side-brace fitting shaft of the MLG if necessary.
This AD also requires eventual replacement of certain side-brace
fitting shafts with the re-designed part. Replacement with a re-
designed side-brace fitting shaft of the MLG is terminating action for
the repetitive inspections. This AD was prompted by reports of failure
of the side-brace fitting shaft of the main landing gear (MLG) due to
corrosion. We are issuing this AD to prevent fractures of the side-
brace fitting shafts of the MLG, and possible collapse of the MLG.
DATES: This AD becomes effective December 5, 2012.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 5,
2012.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Jeffrey Zimmer, 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) 228-7306; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on June 12, 2012 (77 FR
34870), and proposed to supersede AD 2004-22-23, Amendment 39-13851 (69
FR 64856, November 9, 2004). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states:
Due to the failure of the main landing gear (MLG) side brace
fitting shaft, caused by corrosion, [Transport Canada Civil Aviation
(TCCA)] Airworthiness Directive (AD) CF-2002-41 was issued to
require inspection and
[[Page 65811]]
if needed, parts replacement. However, the existing MLG side-brace
fitting shafts continued to fail. Failure of the MLG side brace
fitting shaft could result in the collapse of the main landing gear.
This [TCCA] directive mandates the repetitive detailed visual
inspection [for cracking and corrosion] of the MLG side brace
fitting and the incorporation of the re-designed MLG side brace
fitting shaft part number (P/N) 601R10247-3 as the terminating
action.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received.
Request to Reference Revised Service Bulletin
Comair, Inc. requested that we allow the use of Bombardier Service
Bulletin 601R-57-052, Revision A, dated October 28, 2011, in the AD.
Comair, Inc. provided no reasons for the request.
We agree to reference the most recent service information.
Bombardier, Inc. has issued Service Bulletin 601R-57-052, Revision A,
dated October 28, 2011. This service bulletin includes editorial
changes, but does not add work for airplanes that have done the actions
using Bombardier Service Bulletin 601R-57-052, dated July 28, 2011
(which was referenced to as the appropriate source of service
information in the NPRM (77 FR 34870, June 12, 2012). Therefore we have
revised paragraphs (g)(1), (g)(2), (h)(1), and (h)(2) of this AD to
refer to Bombardier Service Bulletin 601R-57-052, Revision A, dated
October 28, 2011. We have also added paragraph (i) to this AD to allow
credit for actions performed before the effective date of this AD using
Bombardier Service Bulletin 601R-57-052, dated July 28, 2011. We have
re-designated subsequent paragraphs accordingly.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously and except for minor editorial
changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 34870, June 12, 2012) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 34870, June 12, 2012).
Costs of Compliance
We estimate that this AD will affect about 584 products of U.S.
registry.
We estimate that it will take about 10 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will cost about $0 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 this AD to the
U.S. operators to be $496,400, or $850 per product.
In addition, we estimate that any necessary follow-on actions would
take about 14 work-hours and require parts costing $3,860, for a cost
of $5,050 per product. We have no way of determining the number of
products that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM (77 FR 34870, June 12, 2012),
the regulatory evaluation, any comments received, and other
information. The street address for the Docket Operations office
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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 removing airworthiness directive (AD)
2004-22-23, Amendment 39-13851 (69 FR 64856, November 9, 2004), and
adding the following new AD:
2012-21-14 Bombardier, Inc.: Amendment 39-17230. Docket No. FAA-
2012-0592; Directorate Identifier 2011-NM-253-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective December 5,
2012.
(b) Affected ADs
This AD supersedes AD 2004-22-23, Amendment 39-13851 (69 FR
64856, November 9, 2004).
(c) Applicability
This AD applies to Bombardier, Inc. Model CL-600-2B19 (Regional
Jet Series 100 & 440) airplanes; certificated in any category;
serial numbers 7003 through 7990 inclusive, and 8000 through 8999
inclusive.
[[Page 65812]]
(d) Subject
Air Transport Association (ATA) of America Code 57: Wings.
(e) Reason
This AD was prompted by reports of failure of the side-brace
fitting shaft of the main landing gear (MLG) due to corrosion. We
are issuing this AD to prevent fractures of the side-brace fitting
shafts of the MLG, and possible collapse of the MLG.
(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) Inspection of MLG Side-Brace Fitting Shaft and Replacement
(1) At the applicable times specified in paragraphs (g)(1)(i),
(g)(1)(ii), (g)(1)(iii), and (g)(1)(iv) of this AD, do a detailed
inspection for corrosion and damage of each side-brace fitting shaft
of the MLG, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 601R-57-052, Revision A, dated October
28, 2011. Repeat the inspections at the applicable times specified
in paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), and (g)(1)(iv) of
this AD.
(i) For airplanes that average greater than 900 flight hours per
year and have side-brace shafts part number (P/N) 601R10237-1
installed in either the left- or right-hand MLG, or if the side-
brace shaft part number cannot be identified without removal: Within
1,000 flight hours after the effective date of this AD, do the
inspection. Repeat the inspections thereafter at intervals not to
exceed 1,000 flight hours until the replacement specified in
paragraph (g)(2) or (h) of this AD is done.
(ii) For airplanes that average 900 flight hours or less per
year and have side-brace shafts P/N 601R10237-1 installed on either
the left- or right-hand MLG, or if the side-brace shaft part number
cannot be identified without removal: Within 18 months after the
effective date of this AD, do the inspection. Repeat the inspections
thereafter at intervals not to exceed 18 months until the
replacement specified in paragraph (g)(2) or (h) of this AD is done.
(iii) For airplanes that average greater than 900 flight hours
per year and have side-brace shafts P/N 601R10237-3 installed on
either the left- or right-hand MLG: Within 36 months after the
effective date of this AD, do the inspection. Repeat the inspections
thereafter at intervals not to exceed 36 months until the
replacement specified in paragraph (g)(2) or (h) of this AD is done.
(iv) For airplanes that average 900 flight hours or less per
year and have side-brace shafts P/N 601R10237-3 installed on either
the left- or right-hand MLG: Within 60 months after the effective
date of this AD, do the inspection. Repeat the inspections
thereafter at intervals not to exceed 60 months until the
replacement specified in paragraph (g)(2) or (h) of this AD is done.
(2) If any corrosion or damage is found during any inspection
required by paragraph (g) of this AD: Before further flight, replace
the side-brace fitting shaft with a new shaft P/N 601R10247-3, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 601R-57-052, Revision A, dated October 28, 2011.
Doing this replacement terminates the inspection requirements of
paragraph (g) of this AD.
(h) Replacement
Do the replacement at the applicable time specified in paragraph
(h)(1) or (h)(2) of this AD.
(1) For any airplanes that have side-brace shafts P/N 601R10237-
1 installed, or if the side-brace shaft part number cannot be
identified without removal: Within 27 months after the effective
date of this AD, replace the side-brace fitting shaft of the MLG
with a new shaft having P/N 601R10247-3, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 601R-57-
052, Revision A, dated October 28, 2011. Doing this replacement
terminates the inspection requirements of paragraph (g) of this AD.
(2) For airplanes that have side-brace shafts P/N 601R10237-3
installed: Within 117 months after the effective date of this AD,
replace the side-brace fitting shaft of the MLG with a new shaft P/N
601R10247-3, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 601R-57-052, Revision A, dated October
28, 2011. Doing this replacement terminates the inspection
requirements of paragraph (g) of this AD.
(i) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Bombardier Service
Bulletin 601R-57-052, dated July 28, 2011 (which is not incorporated
by reference in this AD).
(j) 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. 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, 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.
(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.
(k) Related Information
Refer to MCAI Canadian Airworthiness Directive CF-2011-39, dated
October 25, 2011; and Bombardier Service Bulletin 601R-57-052, dated
July 28, 2011; for related information.
(l) 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 the AD specifies otherwise.
(i) Bombardier Service Bulletin 601R-57-052, Revision A, dated
October 28, 2011.
(ii) Reserved.
(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 review copies of the 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 October 14, 2012.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-26088 Filed 10-30-12; 8:45 am]
BILLING CODE 4910-13-P
