Airworthiness Directives; Bombardier, Inc. Airplanes, 9389-9392 [2014-02977]
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Federal Register / Vol. 79, No. 33 / Wednesday, February 19, 2014 / Rules and Regulations
inspection for damaged (worn, torn, or
abraded) and missing shims and seals,
between the nacelle lower fairing and the
underwing box of both the left-hand and
right-hand engine nacelles, in accordance
with the Accomplishment Instructions of
´
Avions de Transport Regional Service
Bulletin ATR42–54–0029; or ATR72–54–
1023; both dated July 18, 2012; as applicable.
If any seal or shim is damaged or missing,
before further flight, replace, as applicable, in
accordance with the Accomplishment
´
Instructions of Avions de Transport Regional
Service Bulletin ATR42–54–0029; or ATR72–
54–1023; both dated July 18, 2012; as
applicable.
ehiers on DSK2VPTVN1PROD with RULES
(h) Reporting
At the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD: Submit
a report using the applicable
Accomplishment Report of Avions de
´
Transport Regional Service Bulletin ATR42–
54–0029; or ATR72–54–1023; both dated July
18, 2012; to ATR Engineering, Service
Bulletin Group, 1 Allee Pierre Nadot, 31712
Blagnac Cedex, France; phone: +33 (0) 5 62
21 62 21; fax: +33 (0) 5 62 21 69 41; email:
techdesk@atr.fr.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(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:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-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.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
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9389
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
DEPARTMENT OF TRANSPORTATION
(j) Related Information
SUMMARY:
Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency (EASA)
Airworthiness Directive 2012–0160, dated
August 24, 2012, for related information.
This MCAI may be found in the AD docket
on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2013-0799-0002.
(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 this AD specifies otherwise.
(i) ATR Service Bulletin ATR42–54–0029,
dated July 18, 2012.
(ii) ATR Service Bulletin ATR72–54–1023,
dated July 18, 2012.
(3) For service information identified in
this AD, contact ATR—GIE Avions de
´
´
Transport Regional, 1, Allee Pierre Nadot,
31712 Blagnac Cedex, France; telephone +33
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18;
email continued.airworthiness@atr.fr;
Internet https://www.aerochain.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.
Issued in Renton, Washington, on January
21, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–02774 Filed 2–18–14; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0054; Directorate
Identifier 2014–NM–001–AD; Amendment
39–17754; AD 2014–03–17]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
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, CL–601–3R,
and CL–604 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
fastener replacement if necessary. This
AD was prompted by two reports of
fractured fastener heads found on the
inboard flap hinge-box forward fitting.
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
March 6, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 6, 2014
We must receive comments on this
AD by April 7, 2014.
ADDRESSES: You may send comments 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.
For service information identified in
this AD, contact Bombardier, Inc., 400
ˆ
´
Cote-Vertu Road West, Dorval, Quebec
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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.
oriented or fractured fasteners], on both
wings, and rectification [fastener
replacement] as required. Incorrectly
oriented fasteners require repetitive
inspections until the terminating action
[fastener replacement] is accomplished.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating it in Docket No. FAA–
2014–0054; 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:
Ricardo Garcia, 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) 228–7331;
fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Relevant Service Information
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Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2013–39,
dated December 6, 2013 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or the ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
There have been two in-service reports 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
adversely affect the continued safe operation
of the aeroplane [consequent reduced
controllability of the airplane].
This [Canadian] AD mandates a detailed
visual inspection (DVI) of each inboard flap
hinge-box forward fitting [for incorrectly
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You may examine the MCAI on the
Internet at https://www.regulations.gov
by searching for and locating it in
Docket No. FAA–2014–0054.
Bombardier has issued Alert Service
Bulletins:
• A600–0763, including Appendices
1 and 2, dated September 26, 2013 (for
Model CL–600–1A11 (CL–600)
airplanes);
• A601–0627, including Appendices
1 and 2, dated September 26, 2013 (for
Model CL–600–2A12 (CL–601) and CL–
600–2B16 (CL–601–3A and CL–601–3R
Variants) airplanes;
• A604–57–006, Revision 01, dated
September 26, 2013, including
Appendices 1 and 2, dated September
26, 2013 (for Model CL–600–2B16 (CL–
604 Variant) airplanes with serial
numbers 5301 through 5665 inclusive);
and
• A605–57–004, Revision 01, dated
September 26, 2013, including
Appendices 1 and 2, dated September
26, 2013 (for Model CL–600–2B16 (CL–
604 Variant) airplanes with serial
numbers 5701 through 5920 inclusive).
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of This 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 the same
type design.
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 incorrectly installed or
fractured fasteners could result in
detachment of the flap hinge-box and
the flap surface, and consequently,
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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–2014–0054;
Directorate Identifier 2014–NM–001–
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 105
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 $8,925, or $85 per
product.
In addition, we estimate that any
necessary follow-on actions will take
about 58 work-hours per product. We
have no way of determining the number
of aircraft that might need these actions.
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
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affected individuals. Therefore, the
parts costs are not included 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.
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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:
■
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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):
■
2014–03–17 Bombardier, Inc.: Amendment
39–17754. Docket No. FAA–2014–0054;
Directorate Identifier 2014–NM–001–AD.
(a) Effective Date
This AD becomes effective March 6, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Bombardier, Inc.
airplanes identified in paragraphs (c)(1)
through (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.
(3) Bombardier, Inc. 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.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by two reports of
fractured fastener heads 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
Within 100 flight cycles after the effective
date of this AD: Do a detailed visual
inspection for incorrect orientation and any
fracturing (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 identified in
paragraphs (g)(1) through (g)(4) of this AD.
(1) For Model CL–600–1A11 (CL–600)
airplanes having S/Ns 1004 through 1085
inclusive: Bombardier Alert Service Bulletin
A600–0763, 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, including Appendices 1 and 2, dated
September 26, 2013.
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9391
(3) For Model CL–600–2B16 (CL–604
Variant) airplanes having S/Ns 5301 through
5665 inclusive: Bombardier Alert Service
Bulletin A604–57–006, Revision 01, dated
September 26, 2013, including Appendices 1
and 2, dated September 26, 2013.
(4) For Model CL–600–2B16 (CL–604
Variant) airplanes having S/Ns 5701 through
5920 inclusive: Bombardier Alert Service
Bulletin A605–57–004, Revision 01, dated
September 26, 2013, including Appendices 1
and 2, dated September 26, 2013.
(h) All Fasteners Correctly Oriented and Not
Fractured
If all fasteners are found correctly oriented
and not fractured (intact) during any
inspection required by paragraph (g) of this
AD, no further action is required by this AD.
(i) Fractured Fasteners
If any fastener is found fractured (missing
fastener head) during any inspection required
by paragraph (g) of this AD: Before further
flight, remove and replace all fractured
fasteners and all incorrectly oriented forward
and aft fasteners at WS 76.50 and WS 127.25,
on both wings, in accordance with the
Accomplishment Instructions of the
applicable service information identified in
paragraphs (g)(1) through (g)(4) of this AD.
After accomplishing the replacement
required by this paragraph, no further action
is required by this AD.
(j) Incorrectly Oriented Fasteners
If any fastener is found incorrectly oriented
but none are found to be fractured (fasteners
found intact) during any inspection required
by paragraph (g) of this AD: Repeat the
inspection required by paragraph (g) of this
AD thereafter at intervals not to exceed 100
flight cycles until the terminating action
specified in paragraph (k) of this AD is
accomplished.
(k) Optional Terminating Action for
Incorrectly Oriented Fasteners
Replacement of all incorrectly oriented
forward and aft fasteners at WS 76.50 and
WS 127.25, on both wings, in accordance
with the Accomplishment Instructions of the
applicable service information identified in
paragraphs (g)(1) through (g)(4) of this AD,
terminates the requirements of paragraph (j)
of this AD.
(l) 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, 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
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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, use these actions if they are
FAA-approved. Corrective actions are
considered FAA-approved if they were
approved by the State of Design Authority (or
its delegated agent, or the DAH with a State
of Design Authority’s design organization
approval). For a repair method to be
approved, the repair approval must
specifically refer to this AD. You are required
to ensure the product is airworthy before it
is returned to service.
(m) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2013–39, dated
December 6, 2013, for related information.
You may examine the MCAI on the Internet
at https://www.regulations.gov by searching
for and locating it in Docket No. FAA–2014–
0054.
ehiers on DSK2VPTVN1PROD with RULES
(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, including Appendices 1 and 2,
dated September 26, 2013.
(ii) Bombardier Alert Service Bulletin
A601–0627, including Appendices 1 and 2,
dated September 26, 2013.
(iii) Bombardier Alert Service Bulletin
A604–57–006, Revision 01, dated September
26, 2013, including Appendices 1 and 2,
dated September 26, 2013.
(iv) Bombardier Alert Service Bulletin
A605–57–004, Revision 01, dated September
26, 2013, 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.
14:22 Feb 18, 2014
Jkt 232001
[FR Doc. 2014–02977 Filed 2–18–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0210; Directorate
Identifier 2012–NM–053–AD; Amendment
39–17744; AD 2014–03–07]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2009–26–
16 for certain The Boeing Company
Model MD–11 and MD–11F airplanes.
AD 2009–26–16 required inspecting to
determine if wires touch the upper
surface of the center upper auxiliary
fuel tank, and marking the location, as
necessary; inspecting all wire bundles
above the center upper auxiliary fuel
tank for splices and damage; inspecting
for damage to the fuel vapor barrier seal
and upper surface of the center upper
auxiliary fuel tank; and performing
corrective actions, as necessary. AD
2009–26–16 also required installing
nonmetallic barrier/shield sleeving, new
clamps, new attaching hardware, and a
new extruded channel. This new AD
requires inspections of additional center
upper auxiliary fuel tank locations and
corrective actions as necessary. This AD
was prompted by reports that identified
additional locations where inspections
and corrective actions of the center
upper auxiliary fuel tank are needed.
We are issuing this AD to reduce the
potential of ignition sources inside fuel
tanks, which, in combination with
flammable fuel vapors, could result in
fuel tank explosions and consequent
loss of the airplane.
DATES: This AD is effective March 26,
2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 26, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of February 4, 2010 (74 FR
69249, December 31, 2009).
SUMMARY:
(n) Material Incorporated by Reference
VerDate Mar<15>2010
Issued in Renton, Washington, on February
3, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, 3855
Lakewood Boulevard, MC D800–0019,
Long Beach, CA 90846–0001; telephone
206–544–5000, extension 2; fax 206–
766–5683; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, Washington. For information on
the availability of this material at the
FAA, call 425–227–1221.
ADDRESSES:
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–2013–
0210; or in person at the Docket
Management Facility 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 address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Samuel Lee, Aerospace Engineer,
Propulsion Branch, ANM–140L, FAA,
Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
(562) 627–5262; fax: (562) 627–5210;
email: samuel.lee@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
Part 39 to supersede AD 2009–26–16,
Amendment 39–16155 (74 FR 69249,
December 31, 2009). AD 2009–26–16
applied to certain The Boeing Company
Model MD–11 and MD–11F airplanes.
The NPRM published in the Federal
Register on March 14, 2013 (78 FR
16198). The NPRM was prompted by
reports that identified additional
locations where inspections and
corrective actions of the center upper
auxiliary fuel tank are needed. The
NPRM proposed to continue to require
inspecting to determine if wires touch
the upper surface of the center upper
auxiliary fuel tank, and marking the
location, as necessary; inspecting all
wire bundles above the center upper
auxiliary fuel tank for splices and
damage; inspecting for damage to the
E:\FR\FM\19FER1.SGM
19FER1
]]>Agencies
[Federal Register Volume 79, Number 33 (Wednesday, February 19, 2014)]
[Rules and Regulations]
[Pages 9389-9392]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-02977]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0054; Directorate Identifier 2014-NM-001-AD;
Amendment 39-17754; AD 2014-03-17]
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, CL-601-3R, and CL-604 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 fastener replacement if necessary. This AD was prompted
by two reports of fractured fastener heads found on the inboard flap
hinge-box forward fitting. 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 March 6, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 6, 2014
We must receive comments on this AD by April 7, 2014.
ADDRESSES: You may send comments 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.
For service information identified in this AD, contact Bombardier,
Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec
[[Page 9390]]
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA-
2014-0054; 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: Ricardo Garcia, 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) 228-7331; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2013-39, dated December 6, 2013 (referred to after this as the
Mandatory Continuing Airworthiness Information, or the ``the MCAI''),
to correct an unsafe condition for the specified products. The MCAI
states:
There have been two in-service reports 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 adversely affect the continued safe
operation of the aeroplane [consequent reduced controllability of
the airplane].
This [Canadian] AD mandates a detailed visual inspection (DVI)
of each inboard flap hinge-box forward fitting [for incorrectly
oriented or fractured fasteners], on both wings, and rectification
[fastener replacement] as required. Incorrectly oriented fasteners
require repetitive inspections until the terminating action
[fastener replacement] is accomplished.
You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA-
2014-0054.
Relevant Service Information
Bombardier has issued Alert Service Bulletins:
A600-0763, including Appendices 1 and 2, dated September
26, 2013 (for Model CL-600-1A11 (CL-600) airplanes);
A601-0627, including Appendices 1 and 2, dated September
26, 2013 (for Model CL-600-2A12 (CL-601) and CL-600-2B16 (CL-601-3A and
CL-601-3R Variants) airplanes;
A604-57-006, Revision 01, dated September 26, 2013,
including Appendices 1 and 2, dated September 26, 2013 (for Model CL-
600-2B16 (CL-604 Variant) airplanes with serial numbers 5301 through
5665 inclusive); and
A605-57-004, Revision 01, dated September 26, 2013,
including Appendices 1 and 2, dated September 26, 2013 (for Model CL-
600-2B16 (CL-604 Variant) airplanes with serial numbers 5701 through
5920 inclusive).
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This 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 the same
type design.
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
incorrectly installed or fractured fasteners could result in detachment
of the flap hinge-box and the flap surface, and consequently, 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-2014-0054; Directorate
Identifier 2014-NM-001-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 105 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 $8,925, or $85 per product.
In addition, we estimate that any necessary follow-on actions will
take about 58 work-hours per product. We have no way of determining the
number of aircraft that might need these actions.
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
[[Page 9391]]
affected individuals. Therefore, the parts costs are not included 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):
2014-03-17 Bombardier, Inc.: Amendment 39-17754. Docket No. FAA-
2014-0054; Directorate Identifier 2014-NM-001-AD.
(a) Effective Date
This AD becomes effective March 6, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Bombardier, Inc. airplanes identified in
paragraphs (c)(1) through (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.
(3) Bombardier, Inc. 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.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by two reports of fractured fastener heads
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
Within 100 flight cycles after the effective date of this AD: Do
a detailed visual inspection for incorrect orientation and any
fracturing (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 identified in paragraphs (g)(1)
through (g)(4) of this AD.
(1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763,
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, including Appendices 1
and 2, dated September 26, 2013.
(3) For Model CL-600-2B16 (CL-604 Variant) airplanes having S/Ns
5301 through 5665 inclusive: Bombardier Alert Service Bulletin A604-
57-006, Revision 01, dated September 26, 2013, including Appendices
1 and 2, dated September 26, 2013.
(4) For Model CL-600-2B16 (CL-604 Variant) airplanes having S/Ns
5701 through 5920 inclusive: Bombardier Alert Service Bulletin A605-
57-004, Revision 01, dated September 26, 2013, including Appendices
1 and 2, dated September 26, 2013.
(h) All Fasteners Correctly Oriented and Not Fractured
If all fasteners are found correctly oriented and not fractured
(intact) during any inspection required by paragraph (g) of this AD,
no further action is required by this AD.
(i) Fractured Fasteners
If any fastener is found fractured (missing fastener head)
during any inspection required by paragraph (g) of this AD: Before
further flight, remove and replace all fractured fasteners and all
incorrectly oriented forward and aft fasteners at WS 76.50 and WS
127.25, on both wings, in accordance with the Accomplishment
Instructions of the applicable service information identified in
paragraphs (g)(1) through (g)(4) of this AD. After accomplishing the
replacement required by this paragraph, no further action is
required by this AD.
(j) Incorrectly Oriented Fasteners
If any fastener is found incorrectly oriented but none are found
to be fractured (fasteners found intact) during any inspection
required by paragraph (g) of this AD: Repeat the inspection required
by paragraph (g) of this AD thereafter at intervals not to exceed
100 flight cycles until the terminating action specified in
paragraph (k) of this AD is accomplished.
(k) Optional Terminating Action for Incorrectly Oriented Fasteners
Replacement of all incorrectly oriented forward and aft
fasteners at WS 76.50 and WS 127.25, on both wings, in accordance
with the Accomplishment Instructions of the applicable service
information identified in paragraphs (g)(1) through (g)(4) of this
AD, terminates the requirements of paragraph (j) of this AD.
(l) 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, 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
[[Page 9392]]
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, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the DAH with a State of Design Authority's
design organization approval). For a repair method to be approved,
the repair approval must specifically refer to this AD. You are
required to ensure the product is airworthy before it is returned to
service.
(m) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
Canadian Airworthiness Directive CF-2013-39, dated December 6, 2013,
for related information. You may examine the MCAI on the Internet at
https://www.regulations.gov by searching for and locating it in
Docket No. FAA-2014-0054.
(n) 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, including
Appendices 1 and 2, dated September 26, 2013.
(ii) Bombardier Alert Service Bulletin A601-0627, including
Appendices 1 and 2, dated September 26, 2013.
(iii) Bombardier Alert Service Bulletin A604-57-006, Revision
01, dated September 26, 2013, including Appendices 1 and 2, dated
September 26, 2013.
(iv) Bombardier Alert Service Bulletin A605-57-004, Revision 01,
dated September 26, 2013, 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 February 3, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-02977 Filed 2-18-14; 8:45 am]
BILLING CODE 4910-13-P
