Airworthiness Directives; Airbus Airplanes, 28159-28161 [2013-11380]
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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(k) 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
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
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.
(l) Related Information
(1) Refer to MCAI Canadian Airworthiness
Directive CF–2012–21, dated June 25, 2012;
and the service information specified in
paragraphs (l)(1)(i), (l)(1)(ii), and (l)(1)(iii) of
this AD for related information.
(i) Bombardier Repair Drawing 8/4–32–
0190, Issue 2, dated January 14, 2013.
(ii) Bombardier Q400 All Operator Message
No. 515, DHC8–400–AOM–515, Revision
2009–06–24, dated April 4, 2012.
(iii) Bombardier Temporary Revision
MRB–66, dated December 7, 2011, to Section
1–32, ‘‘Systems/Powerplant Maintenance
Program,’’ of Part 1 of the Bombardier Dash
8 Series 400 Maintenance Requirements
Manual, PSM 1–84–7.
(2) For service information identified in
this AD, contact Bombardier, Inc., Q-Series
Technical Help Desk, 123 Garratt Boulevard,
VerDate Mar<15>2010
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Jkt 229001
Toronto, Ontario M3K 1Y5, Canada;
telephone 416–375–4000; fax 416–375–4539;
email thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com. You
may review copies of the referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on May 6,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–11382 Filed 5–13–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0418; Directorate
Identifier 2012–NM–200–AD]
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A300 series airplanes;
Model A300 B4–600, B4–600R, and F4–
600R series airplanes, and Model A300
C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes). This proposed AD was
prompted by a report that cracking was
found in area 2 of the frame base fittings
between frame 41 and frame 46. This
proposed AD would require a check of
maintenance records to determine if
certain repairs were done in area 1 of
the frame brace fittings, and, for affected
airplanes, a detailed inspection for
cracking in area 2 of the frame base
fittings between frame 41 and frame 46,
and repair if necessary. We are
proposing this AD to detect and correct
cracking in area 2 of the frame base
fittings between frame 41 and frame 46,
which could adversely affect the
structural integrity of the airplane.
DATES: We must receive comments on
this proposed AD by June 28, 2013.
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–
SUMMARY:
Frm 00013
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30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS,
Airworthiness Office—EAW, 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. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Examining the AD Docket
RIN 2120–AA64
PO 00000
28159
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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 this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–227–2125; fax:
425–227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2013–0418; Directorate Identifier
2012–NM–200–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0229,
dated October 31, 2012 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
During accomplishment of Airbus SB
[service bulletin] A300–53–6111, which
addresses detailed visual inspections of the
lower frame fittings between Frame (FR) 41
and FR 46, on one A300–600 aeroplane a
crack was detected in the area 2 of the foot
of frame FR 46 at junction radius level.
This frame, that was previously repaired
due to a crack finding in the area 1, was not
due to be inspected before reaching the postrepair inspection threshold, i.e., 45,400 FC
[flight cycles], from repair embodiment.
It has been determined that the current
repairs proposed in Airbus SB A300–53–
6111 and Airbus [SB] A300–53–0337 are of
limited effect to prevent cracking in the area
2 of the lower frame fittings.
Consequently, as a temporary action and
until an improvement of the existing repairs
is made available, this [EASA] AD requires
a one-time detailed visual inspection [for
cracking] of [the] frame base fittings that were
repaired in accordance with Airbus SB
A300–53–0337, original issue or Rev. 1, or
Airbus SB A300–53–6111 original issue up to
Rev. 4 * * *.
The unsafe condition is cracking in
the frame base fittings, which could
adversely affect the structural integrity
of the airplane. The required actions
include repairing any cracking found.
You may obtain further information by
examining the MCAI in the AD docket.
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Relevant Service Information
Airbus has issued Alert Operators
Transmission (AOT) A53W001–12,
dated July 4, 2012, including
Appendices 1, 2, and 3. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
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information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed AD
and the MCAI
Although EASA AD 2012–0229, dated
October 31, 2012, specifies to contact
the manufacturer for instructions to
repair certain conditions, this proposed
AD would require repairing those
conditions using a method approved by
either the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA (or its
delegated agent).
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 124 products of U.S.
registry. We also estimate that it would
take about 4 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$42,160, or $340 per product.
In addition, we estimate that any
necessary follow-on actions would take
up to 350 work-hours and require parts
costing up to $56,469 for a cost of
$86,219 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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
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Fmt 4702
Sfmt 4702
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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 AD:
■
Airbus: Docket No. FAA–2013–0418;
Directorate Identifier 2012–NM–200–AD.
(a) Comments Due Date
We must receive comments by June 28,
2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1) and (c)(2) of this AD,
certificated in any category.
(1) Airbus Model A300 B2–1A, B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes, on which any repair has been
done as specified in Airbus Service Bulletin
A300–53–0337, dated February 4, 1999; or
Airbus Service Bulletin A300–53–0337,
Revision 01, dated March 17, 2003.
(2) Airbus Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes, Model A300
B4–605R and B4–622R airplanes, Model
A300 F4–605R and F4–622R airplanes, and
A300 C4–605R Variant F airplanes, on which
any repair has been done as specified in any
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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules
of the service information identified in
paragraphs (c)(2)(i), (c)(2)(ii), (c)(2)(iii),
(c)(2)(iv), and (c)(2)(v) of this AD.
(i) Airbus Service Bulletin A300–53–6111,
dated February 4, 1999.
(ii) Airbus Service Bulletin A300–53–6111,
Revision 01, dated March 17, 2003.
(iii) Airbus Service Bulletin A300–53–
6111, Revision 02, dated September 13, 2004.
(iv) Airbus Service Bulletin A300–53–
6111, Revision 03, dated September 30, 2009.
(v) Airbus Mandatory Service Bulletin
A300–53–6111, Revision 04, dated August
25, 2011.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report that
cracking was found in area 2 of the frame
base fittings between frame 41 and frame 46.
We are issuing this AD to detect and correct
cracking in area 2 of the frame base fittings
between frame 41 and frame 46, which could
adversely affect the structural integrity of the
airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Maintenance Records Check and Frame
Base Fitting Inspection
Within 1,000 flight hours after the effective
date of this AD: Check the airplane
maintenance records to determine if repairs
were done in area 1 of the frame base fittings
as defined in Appendix 1 of Airbus Alert
Operators Transmission A53W001–12, dated
July 4, 2012.
(h) Frame Base Fitting Inspection
If, during any records check required by
paragraph (g) of this AD, it is determined that
area 1 of the frame base fittings was repaired:
Within 1,000 flight hours after the effective
date of this AD do a detailed inspection of
the frame base fittings between frame 41 and
frame 46 in the area 2 defined in Appendix
1 of Airbus Alert Operators Transmission
A53W001–12, dated July 4, 2012.
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(i) Corrective Action
If any cracking is found during any
detailed inspection required by paragraph (h)
of this AD: Before further flight, repair the
cracking using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA) (or
its delegated agent).
(j) 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
VerDate Mar<15>2010
16:30 May 13, 2013
Jkt 229001
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–227–2125; 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.
(k) Related Information
(1) Refer to MCAI EASA Airworthiness
Directive 2012–0229, dated October 31, 2012;
and Airbus Alert Operators Transmission
A53W001–12, dated July 4, 2012, including
Appendices 1 and 2, and excluding
Appendix 3; for related information.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 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.airwortheas@airbus.com; Internet https://
www.airbus.com. You may review copies of
the referenced service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425 227–1221.
Issued in Renton, Washington, on May 6,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–11380 Filed 5–13–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0562; Directorate
Identifier 2009–NE–29–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
SUMMARY:
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28161
that applies to all Rolls-Royce plc (RR)
model RB211 Trent 553–61, 553A2–61,
556–61, 556A2–61, 556B–61, 556B2–61,
560–61, and 560A2–61; and RB211
Trent 768–60, 772–60, and 772B–60;
and RB211–Trent 875–17, 877–17, 884–
17, 884B–17, 892–17, 892B–17, and
895–17; and RB211–524G2–T–19,
–524G3–T–19, –524H–T–36, and
–524H2–T–19 turbofan engines that
have a high-pressure (HP) compressor
stage 1 to 4 rotor disc installed, with a
certain part number (P/N) installed. The
existing AD requires repetitive
inspections of the axial dovetail slots,
and follow-on corrective action
depending on findings. This proposed
AD expands the population of affected
parts. This proposed AD also changes,
for the purposes of this AD, the
definition of ‘‘engine shop visit.’’ We are
proposing this AD to detect cracks in
the HP compressor stage 1 and 2 disc
posts, which could result in failure of
the disc post and HP compressor blades,
damage to the engine, and damage to the
airplane.
DATES: We must receive comments on
this proposed AD by July 15, 2013.
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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this AD, contact Rolls-Royce plc,
Corporate Communications, P.O. Box
31, Derby, England, DE248BJ; phone:
011–44–1332–242424; fax: 011–44–
1332–249936; or email: https://
www.rolls-royce.com/contact/
civil_team.jsp; or download the
publication from https://
www.aeromanager.com. You may view
this service information at the FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803. For information on the
availability of this material at the FAA,
call 781–238–7125.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
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]]>Agencies
[Federal Register Volume 78, Number 93 (Tuesday, May 14, 2013)]
[Proposed Rules]
[Pages 28159-28161]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-11380]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0418; Directorate Identifier 2012-NM-200-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R,
and F4-600R series airplanes, and Model A300 C4-605R Variant F
airplanes (collectively called Model A300-600 series airplanes). This
proposed AD was prompted by a report that cracking was found in area 2
of the frame base fittings between frame 41 and frame 46. This proposed
AD would require a check of maintenance records to determine if certain
repairs were done in area 1 of the frame brace fittings, and, for
affected airplanes, a detailed inspection for cracking in area 2 of the
frame base fittings between frame 41 and frame 46, and repair if
necessary. We are proposing this AD to detect and correct cracking in
area 2 of the frame base fittings between frame 41 and frame 46, which
could adversely affect the structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by June 28, 2013.
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 proposed AD, contact
Airbus SAS, Airworthiness Office--EAW, 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. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at 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 this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-227-2125; fax:
425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0418;
Directorate Identifier 2012-NM-200-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
[[Page 28160]]
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2012-0229, dated October 31, 2012 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
During accomplishment of Airbus SB [service bulletin] A300-53-
6111, which addresses detailed visual inspections of the lower frame
fittings between Frame (FR) 41 and FR 46, on one A300-600 aeroplane
a crack was detected in the area 2 of the foot of frame FR 46 at
junction radius level.
This frame, that was previously repaired due to a crack finding
in the area 1, was not due to be inspected before reaching the post-
repair inspection threshold, i.e., 45,400 FC [flight cycles], from
repair embodiment.
It has been determined that the current repairs proposed in
Airbus SB A300-53-6111 and Airbus [SB] A300-53-0337 are of limited
effect to prevent cracking in the area 2 of the lower frame
fittings.
Consequently, as a temporary action and until an improvement of
the existing repairs is made available, this [EASA] AD requires a
one-time detailed visual inspection [for cracking] of [the] frame
base fittings that were repaired in accordance with Airbus SB A300-
53-0337, original issue or Rev. 1, or Airbus SB A300-53-6111
original issue up to Rev. 4 * * *.
The unsafe condition is cracking in the frame base fittings, which
could adversely affect the structural integrity of the airplane. The
required actions include repairing any cracking found. You may obtain
further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Alert Operators Transmission (AOT) A53W001-12,
dated July 4, 2012, including Appendices 1, 2, and 3. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This Proposed AD and the MCAI
Although EASA AD 2012-0229, dated October 31, 2012, specifies to
contact the manufacturer for instructions to repair certain conditions,
this proposed AD would require repairing those conditions using a
method approved by either the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA (or its delegated agent).
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 124 products of U.S. registry. We also estimate that
it would take about 4 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $42,160, or $340 per product.
In addition, we estimate that any necessary follow-on actions would
take up to 350 work-hours and require parts costing up to $56,469 for a
cost of $86,219 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2013-0418; Directorate Identifier 2012-NM-
200-AD.
(a) Comments Due Date
We must receive comments by June 28, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes, on which any repair has been done as
specified in Airbus Service Bulletin A300-53-0337, dated February 4,
1999; or Airbus Service Bulletin A300-53-0337, Revision 01, dated
March 17, 2003.
(2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-
605R and F4-622R airplanes, and A300 C4-605R Variant F airplanes, on
which any repair has been done as specified in any
[[Page 28161]]
of the service information identified in paragraphs (c)(2)(i),
(c)(2)(ii), (c)(2)(iii), (c)(2)(iv), and (c)(2)(v) of this AD.
(i) Airbus Service Bulletin A300-53-6111, dated February 4,
1999.
(ii) Airbus Service Bulletin A300-53-6111, Revision 01, dated
March 17, 2003.
(iii) Airbus Service Bulletin A300-53-6111, Revision 02, dated
September 13, 2004.
(iv) Airbus Service Bulletin A300-53-6111, Revision 03, dated
September 30, 2009.
(v) Airbus Mandatory Service Bulletin A300-53-6111, Revision 04,
dated August 25, 2011.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report that cracking was found in area
2 of the frame base fittings between frame 41 and frame 46. We are
issuing this AD to detect and correct cracking in area 2 of the
frame base fittings between frame 41 and frame 46, which could
adversely affect the structural integrity of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Maintenance Records Check and Frame Base Fitting Inspection
Within 1,000 flight hours after the effective date of this AD:
Check the airplane maintenance records to determine if repairs were
done in area 1 of the frame base fittings as defined in Appendix 1
of Airbus Alert Operators Transmission A53W001-12, dated July 4,
2012.
(h) Frame Base Fitting Inspection
If, during any records check required by paragraph (g) of this
AD, it is determined that area 1 of the frame base fittings was
repaired: Within 1,000 flight hours after the effective date of this
AD do a detailed inspection of the frame base fittings between frame
41 and frame 46 in the area 2 defined in Appendix 1 of Airbus Alert
Operators Transmission A53W001-12, dated July 4, 2012.
(i) Corrective Action
If any cracking is found during any detailed inspection required
by paragraph (h) of this AD: Before further flight, repair the
cracking using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA) (or its delegated agent).
(j) 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: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-227-2125; fax: 425-227-1149. Information may be
emailed to: 9-ANM-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.
(k) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2012-0229, dated
October 31, 2012; and Airbus Alert Operators Transmission A53W001-
12, dated July 4, 2012, including Appendices 1 and 2, and excluding
Appendix 3; for related information.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 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. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on
the availability of this material at the FAA, call 425 227-1221.
Issued in Renton, Washington, on May 6, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-11380 Filed 5-13-13; 8:45 am]
BILLING CODE 4910-13-P
