Airworthiness Directives; Airbus Airplanes, 77972-77975 [2014-30270]
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Federal Register / Vol. 79, No. 248 / Monday, December 29, 2014 / Proposed Rules
The Boeing Company: Docket No. FAA–
2014–0929; Directorate Identifier 2014–
NM–118–AD.
(a) Comments Due Date
We must receive comments by February
12, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 767–200, –300, –300F, and –400ER
series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin
767–53A0251, dated August 7, 2013.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports that six
fasteners may not have been installed in the
left and right stringer 37 (S–37) between body
station 428 and 431 lap splices on certain
airplanes. We are issuing this AD to detect
and correct missing fasteners, which could
result in cracks in the fuselage skin that
could adversely affect the structural integrity
of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Inspections, Related Investigative
Actions, and Corrective Actions
Except as provided by paragraph (h)(2) of
this AD, at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 767–53A0251, dated
August 7, 2013: Do an external general visual
inspection of the S–37 lap splice for missing
fasteners, and do all applicable related
investigative and corrective actions; in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–53A0251, dated August 7, 2013, except
as provided by paragraph (h)(1) of this AD.
Do all applicable related investigative and
corrective actions before further flight.
(h) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Service Bulletin
767–53A0251, dated August 7, 2013,
specifies to contact Boeing for repair
instructions: Before further flight, do the
repair using an FAA-approved method.
(2) Where Paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 767–53A0251,
dated August 7, 2013, specifies a compliance
time ‘‘after the original issue date of this
service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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,
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send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (j)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (h)(1)
of this AD: If the service information contains
steps that are labeled as RC, those steps must
be done to comply with this AD; any steps
that are not labeled as RC are recommended.
Those steps that are not labeled as RC may
be deviated from, done as part of other
actions, or done using accepted methods
different from those identified in the
specified service information without
obtaining approval of an AMOC, provided
the steps labeled as RC can be done and the
airplane can be put back in a serviceable
condition. Any substitutions or changes to
steps labeled as RC require approval of an
AMOC.
(j) Related Information
(1) For more information about this AD,
contact Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6590; fax: 425–917–6590;
email: Berhane.Alazar@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 20–544–
5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.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.
Issued in Renton, Washington, on
December 17, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–30271 Filed 12–24–14; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0928; Directorate
Identifier 2014–NM–040–AD]
RIN 2120–AA64
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 all
Airbus Model A330–200 Freighter,
A330–200, A330–300, A340–200, A340–
300, A340–500, and A340–600 series
airplanes. This proposed AD was
prompted by a report of skin disbonding
on a composite side panel of a rudder
installed on an A310 airplane. This
proposed AD would require a review of
the maintenance records of the rudder
to determine if any composite side shell
panel repair has been done; a
thermography inspection limited to the
repair areas or complete side shells, as
applicable, to identify possible inservice rudder repairs, damages, or fluid
ingress; and applicable related
investigative and corrective actions. We
are proposing this AD to detect and
correct the rudder skin disbonding,
which could affect the structural
integrity of the rudder, and could result
in reduced controllability of the
airplane.
SUMMARY:
We must receive comments on
this proposed AD by February 12, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
DATES:
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Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.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 Docket No. FAA–2014–
0928; 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 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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
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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–2014–0928; Directorate Identifier
2014–NM–040–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
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 2014–0033,
dated February 4, 2014 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
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MCAI’’), to correct an unsafe condition
for all Airbus Model A330–200
Freighter, A330–200, A330–300, A340–
200, A340–300, A340–500, and A340–
600 series airplanes. The MCAI states:
A case of skin disbonding was reported on
a composite side panel of a rudder installed
on an A310 aeroplane.
The investigation results revealed that this
disbonding started from a skin panel area
previously repaired in-service in accordance
with the Structural Repair Manual (SRM).
The initial damage has been identified as
a disbonding between the core and skin of
the repaired area. This damage may not be
visually detectable and likely propagates
during normal operation due to the variation
of pressure during ground-air-ground cycles.
Composite rudder side shell panels are also
installed on A330 and A340 aeroplanes,
which may have been repaired in-service
using a similar method.
This condition, if not detected and
corrected, could affect the structural integrity
of the rudder, possibly resulting in reduced
control of the aeroplane.
For the reasons described above, this
[EASA] AD requires a one-time
thermography inspection of a repaired rudder
or a rudder whose maintenance records are
incomplete and, depending on findings,
accomplishment of applicable corrective and
follow-up actions [including repetitive
inspections.
The related investigative actions in
this AD include, as applicable, an
ultrasonic inspection, an elasticity
laminate checker inspection, a tap test
inspection, detailed inspections,
thermography inspections, and
ventilation of the core. The repetitive
inspections include detailed inspections
and thermography inspections. The
corrective actions in this AD include
repairs.
The compliance time for the related
investigative actions is before further
flight after accomplishing the applicable
inspection required by paragraph (g)(1)
or (g)(2)(ii) of this AD.
The intervals for the repetitive
inspections are either 900 flight hours or
1,000 flight cycles, depending on the
applicable conditions identified in the
service information.
The compliance times for the
corrective actions range, depending on
the applicable conditions identified in
the service information, from before
further flight to within 4,500 flight
cycles but not to exceed 24 months after
accomplishing the applicable inspection
required by paragraphs (g)(1) or (g)(2)(ii)
of this AD.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0928.
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Relevant Service Information
Airbus has issued the following
service information:
• Airbus Service Bulletin A330–55–
3043, dated February 7, 2013.
• Airbus Service Bulletin A340–55–
4039, dated February 7, 2013.
• Airbus Service Bulletin A340–55–
5007, dated February 7, 2013.
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 these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 55 airplanes of U.S. registry.
We also estimate that it would take
about 45 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost about $0 per product.
Based on these figures, we estimate the
cost of this proposed AD on U.S.
operators to be $210,375, or $3,825 per
product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to 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 control
number for the collection of information
required by this proposed AD is 2120–
0056. The paperwork cost associated
with this proposed AD has been
detailed in the Costs of Compliance
section of this document and includes
time for reviewing instructions, as well
as completing and reviewing the
collection of information. Therefore, all
reporting associated with this proposed
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AD is 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.
■
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
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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.
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:
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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. Amend § 39.13 by adding the
following new airworthiness directive
(AD):
Airbus: Docket No. FAA–2014–0928;
Directorate Identifier 2014–NM–040–AD.
(a) Comments Due Date
We must receive comments by February
12, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all airplanes identified
in paragraphs (c)(1) and (c)(2) of this AD,
certificated in any category.
(1) Airbus Model A330–201, –202, –203,
–223, –223F, –243, –243F, –301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes, all manufacturer serial numbers.
(2) Airbus Model A340–211, –212, –213,
–311, –312, –313, –541, and –642 airplanes,
all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 55, Stabilizers.
(e) Reason
This AD was prompted by a report of skin
disbonding on a composite side panel of a
rudder installed on an A310 airplane. We are
issuing this AD to detect and correct the
rudder skin disbonding, which could affect
the structural integrity of the rudder, and
could result in reduced controllability of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Review the Maintenance Records
Within 24 months after the effective date
of this AD: Review the maintenance records
of the rudder to determine if any composite
side shell panel repair has been
accomplished on the rudder since first
installation on an airplane.
(1) If, based on the maintenance record
review, any repair identified in Figure A–
GBBAA (Sheet 01 and 02) or Figure A–
GBCAA (Sheet 02) of the service information
specified in paragraphs (g)(1)(i) through
(g)(1)(iii) of this AD is found: Within 24
months after the effective date of this AD, do
a thermography inspection for repair,
damages, and fluid ingress, limited to the
repaired areas, in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this
AD:
(i) Airbus Service Bulletin A330–55–3043,
dated February 7, 2013 (for Model A330–201,
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–202, –203, –223, –223F, –243, –243F, –301,
–302, –303, –321, –322, –323, –341, –342,
and –343 airplanes).
(ii) Airbus Service Bulletin A340–55–4039,
dated February 7, 2013 (for Model A340–211,
–212, –213, –311, –312, and –313 airplanes).
(iii) Airbus Service Bulletin A340–55–
5007, dated February 7, 2013 (for Model
A340–541 and –642 airplanes).
(2) For a rudder for which maintenance
records are unavailable or incomplete, do the
actions specified in paragraph (g)(2)(i) and
(g)(2)(ii) of this AD:
(i) No later than 3 months before
accomplishment of the thermography
inspection, as required by paragraph (g)(2)(ii)
of this AD, contact Airbus to request related
rudder manufacturing reworked data by
submitting the serial number of the rudder to
Airbus.
(ii) Within 24 months after the effective
date of this AD: Do a thermography
inspection for any repair on complete side
shells to identify and mark any repair, in
accordance with the Accomplishment
Instructions of the applicable service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD.
(h) Related Investigative Actions, Corrective
Actions, and Repetitive Inspections
After the inspection as required by
paragraph (g)(1) or (g)(2) of this AD: At the
applicable compliance times specified in
paragraph 1.E., ‘‘Compliance,’’ of Tables 3,
4A, 4B, 4C, 4D, and 5 of the applicable
service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD,
accomplish all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of the applicable service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD; except as
provided by paragraphs (i)(1) and (i)(2) of
this AD. Options provided in the service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD for
accomplishing the actions are acceptable for
the corresponding requirements of this
paragraph provided that the related
investigative and corrective actions are done
at the applicable times specified in paragraph
1.E., ‘‘Compliance,’’ of the applicable service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD, including
applicable repetitive inspection intervals.
Thereafter repeat the inspections of the
restored and repaired areas at the applicable
compliance time specified in paragraph 1.E.,
‘‘Compliance,’’ of Tables 3, 4A, 4B, 4C, 4D,
and 5 of the applicable service information
specified in paragraphs (g)(1)(i) through
(g)(1)(iii) of this AD.
(i) Exceptions to the Service Information
(1) Where the applicable service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD specifies a
compliance time relative to the date of the
service information, this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(2) If the service information in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD specifies
to contact Airbus: At the applicable
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compliance times specified in paragraph 1.E.,
‘‘Compliance,’’ of the applicable service
information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD, repair using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
(j) Provisions for Certain Airplanes
Airplanes fitted with a rudder having a
serial number (S/N) that is not in the range
of S/N TS–1001 through S/N TS–1043
inclusive, S/N TS–2001 through S/N TS–
2074 inclusive, S/N TS–3000 through S/N
TS–3525 inclusive, S/N TS–4001 through S/
N TS–4170 inclusive, S/N TS–6001 through
S/N TS–6246 inclusive, or S/N TS–5001
through S/N TS–5138 inclusive, are not
affected by the requirements of paragraphs (g)
and (h) of this AD provided that it is
determined that no repair has been
accomplished on the composite side shell
panel of that rudder since first installation on
the airplane.
(k) Parts Installation Limitations
As of the effective date of this AD, no
person may install, on any airplane, a rudder,
unless the record review and thermography
inspection specified in paragraph (g) of this
AD has been done on that rudder and
thereafter all applicable related investigative
actions, repetitive inspections, and corrective
actions are done as required by paragraph (h)
of this AD, except as provided in paragraph
(j) of this AD.
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(l) Repair Prohibition
As of the effective date of this AD, no
person may accomplish a side shell repair on
any rudder using a structure repair manual
procedure identified in Figure A–GBBAA
(Sheet 01 and 02) or Figure A–GBCAA (Sheet
02) of the service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this
AD, as applicable, on any airplane.
(m) 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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; 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.
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(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(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.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0033, dated
February 4, 2014, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2014–0928.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. 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.
Issued in Renton, Washington, on
December 17, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–30270 Filed 12–24–14; 8:45 am]
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SECURITIES AND EXCHANGE
COMMISSION
17 CFR Chapter II
[Release Nos. 33–9694, 34–73891, 39–2500,
IC–31389; IA–3986; File No. S7–13–14]
List of Rules To Be Reviewed Pursuant
to the Regulatory Flexibility Act
Securities and Exchange
Commission.
ACTION: Publication of list of rules
scheduled for review.
AGENCY:
The Securities and Exchange
Commission is publishing a list of rules
to be reviewed pursuant to Section 610
of the Regulatory Flexibility Act. The
list is published to provide the public
with notice that these rules are
scheduled for review by the agency and
to invite public comment on whether
the rules should be continued without
change, or should be amended or
rescinded to minimize any significant
economic impact of the rules upon a
substantial number of such small
entities.
SUMMARY:
Comments should be submitted
by January 28, 2015.
ADDRESSES: Comments may be
submitted by any of the following
methods:
DATES:
Electronic Comments
• Use the Commission’s Internet
comment form (https://www.sec.gov/
rules/other.shtml); or
• Send an email to rule-comments@
sec.gov. Please include File Number S7–
13–14 on the subject line; or
• Use the Federal eRulemaking Portal
(https://www.regulations.gov). Follow the
instructions for submitting comments.
Paper Comments
• Send paper comments to Brent
Fields, Secretary, Securities and
Exchange Commission, 100 F Street NE.,
Washington, DC 20549–1090.
All submissions should refer to File No.
S7–13–14. This file number should be
included on the subject line if email is
used. To help us process and review
your comments more efficiently, please
use only one method. The Commission
will post all comments on the
Commission’s Internet Web site (https://
www.sec.gov/rules/other.shtml).
Comments also are available for Web
site viewing and printing in the
Commission’s Public Reference Room,
100 F Street NE., Washington, DC 20549
on official business days between the
hours of 10:00 a.m. and 3:00 p.m. All
comments received will be posted
without change; we do not edit personal
E:\FR\FM\29DEP1.SGM
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]]>Agencies
[Federal Register Volume 79, Number 248 (Monday, December 29, 2014)]
[Proposed Rules]
[Pages 77972-77975]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-30270]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0928; Directorate Identifier 2014-NM-040-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 all
Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-
300, A340-500, and A340-600 series airplanes. This proposed AD was
prompted by a report of skin disbonding on a composite side panel of a
rudder installed on an A310 airplane. This proposed AD would require a
review of the maintenance records of the rudder to determine if any
composite side shell panel repair has been done; a thermography
inspection limited to the repair areas or complete side shells, as
applicable, to identify possible in-service rudder repairs, damages, or
fluid ingress; and applicable related investigative and corrective
actions. We are proposing this AD to detect and correct the rudder skin
disbonding, which could affect the structural integrity of the rudder,
and could result in reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by February 12,
2015.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac
[[Page 77973]]
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80;
email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.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 Docket No. FAA-2014-
0928; 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 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: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
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-2014-0928;
Directorate Identifier 2014-NM-040-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
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 2014-0033, dated February 4, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-500,
and A340-600 series airplanes. The MCAI states:
A case of skin disbonding was reported on a composite side panel
of a rudder installed on an A310 aeroplane.
The investigation results revealed that this disbonding started
from a skin panel area previously repaired in-service in accordance
with the Structural Repair Manual (SRM).
The initial damage has been identified as a disbonding between
the core and skin of the repaired area. This damage may not be
visually detectable and likely propagates during normal operation
due to the variation of pressure during ground-air-ground cycles.
Composite rudder side shell panels are also installed on A330
and A340 aeroplanes, which may have been repaired in-service using a
similar method.
This condition, if not detected and corrected, could affect the
structural integrity of the rudder, possibly resulting in reduced
control of the aeroplane.
For the reasons described above, this [EASA] AD requires a one-
time thermography inspection of a repaired rudder or a rudder whose
maintenance records are incomplete and, depending on findings,
accomplishment of applicable corrective and follow-up actions
[including repetitive inspections.
The related investigative actions in this AD include, as
applicable, an ultrasonic inspection, an elasticity laminate checker
inspection, a tap test inspection, detailed inspections, thermography
inspections, and ventilation of the core. The repetitive inspections
include detailed inspections and thermography inspections. The
corrective actions in this AD include repairs.
The compliance time for the related investigative actions is before
further flight after accomplishing the applicable inspection required
by paragraph (g)(1) or (g)(2)(ii) of this AD.
The intervals for the repetitive inspections are either 900 flight
hours or 1,000 flight cycles, depending on the applicable conditions
identified in the service information.
The compliance times for the corrective actions range, depending on
the applicable conditions identified in the service information, from
before further flight to within 4,500 flight cycles but not to exceed
24 months after accomplishing the applicable inspection required by
paragraphs (g)(1) or (g)(2)(ii) of this AD.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0928.
Relevant Service Information
Airbus has issued the following service information:
Airbus Service Bulletin A330-55-3043, dated February 7,
2013.
Airbus Service Bulletin A340-55-4039, dated February 7,
2013.
Airbus Service Bulletin A340-55-5007, dated February 7,
2013.
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 these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 55 airplanes of U.S.
registry.
We also estimate that it would take about 45 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $0 per
product. Based on these figures, we estimate the cost of this proposed
AD on U.S. operators to be $210,375, or $3,825 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to 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 control
number for the collection of information required by this proposed AD
is 2120-0056. The paperwork cost associated with this proposed AD has
been detailed in the Costs of Compliance section of this document and
includes time for reviewing instructions, as well as completing and
reviewing the collection of information. Therefore, all reporting
associated with this proposed
[[Page 77974]]
AD is 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.
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.
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. Amend Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2014-0928; Directorate Identifier 2014-NM-
040-AD.
(a) Comments Due Date
We must receive comments by February 12, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all airplanes identified in paragraphs (c)(1)
and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes,
all manufacturer serial numbers.
(2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541,
and -642 airplanes, all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Reason
This AD was prompted by a report of skin disbonding on a
composite side panel of a rudder installed on an A310 airplane. We
are issuing this AD to detect and correct the rudder skin
disbonding, which could affect the structural integrity of the
rudder, and could result in reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Review the Maintenance Records
Within 24 months after the effective date of this AD: Review the
maintenance records of the rudder to determine if any composite side
shell panel repair has been accomplished on the rudder since first
installation on an airplane.
(1) If, based on the maintenance record review, any repair
identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA
(Sheet 02) of the service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD is found: Within 24 months
after the effective date of this AD, do a thermography inspection
for repair, damages, and fluid ingress, limited to the repaired
areas, in accordance with the Accomplishment Instructions of the
applicable service information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD:
(i) Airbus Service Bulletin A330-55-3043, dated February 7, 2013
(for Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -
302, -303, -321, -322, -323, -341, -342, and -343 airplanes).
(ii) Airbus Service Bulletin A340-55-4039, dated February 7,
2013 (for Model A340-211, -212, -213, -311, -312, and -313
airplanes).
(iii) Airbus Service Bulletin A340-55-5007, dated February 7,
2013 (for Model A340-541 and -642 airplanes).
(2) For a rudder for which maintenance records are unavailable
or incomplete, do the actions specified in paragraph (g)(2)(i) and
(g)(2)(ii) of this AD:
(i) No later than 3 months before accomplishment of the
thermography inspection, as required by paragraph (g)(2)(ii) of this
AD, contact Airbus to request related rudder manufacturing reworked
data by submitting the serial number of the rudder to Airbus.
(ii) Within 24 months after the effective date of this AD: Do a
thermography inspection for any repair on complete side shells to
identify and mark any repair, in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD.
(h) Related Investigative Actions, Corrective Actions, and Repetitive
Inspections
After the inspection as required by paragraph (g)(1) or (g)(2)
of this AD: At the applicable compliance times specified in
paragraph 1.E., ``Compliance,'' of Tables 3, 4A, 4B, 4C, 4D, and 5
of the applicable service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD, accomplish all applicable
related investigative and corrective actions, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD;
except as provided by paragraphs (i)(1) and (i)(2) of this AD.
Options provided in the service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD for accomplishing the
actions are acceptable for the corresponding requirements of this
paragraph provided that the related investigative and corrective
actions are done at the applicable times specified in paragraph
1.E., ``Compliance,'' of the applicable service information
specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD,
including applicable repetitive inspection intervals. Thereafter
repeat the inspections of the restored and repaired areas at the
applicable compliance time specified in paragraph 1.E.,
``Compliance,'' of Tables 3, 4A, 4B, 4C, 4D, and 5 of the applicable
service information specified in paragraphs (g)(1)(i) through
(g)(1)(iii) of this AD.
(i) Exceptions to the Service Information
(1) Where the applicable service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD specifies a
compliance time relative to the date of the service information,
this AD requires compliance within the specified compliance time
after the effective date of this AD.
(2) If the service information in paragraphs (g)(1)(i) through
(g)(1)(iii) of this AD specifies to contact Airbus: At the
applicable
[[Page 77975]]
compliance times specified in paragraph 1.E., ``Compliance,'' of the
applicable service information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD, repair using a method approved by
the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA).
(j) Provisions for Certain Airplanes
Airplanes fitted with a rudder having a serial number (S/N) that
is not in the range of S/N TS-1001 through S/N TS-1043 inclusive, S/
N TS-2001 through S/N TS-2074 inclusive, S/N TS-3000 through S/N TS-
3525 inclusive, S/N TS-4001 through S/N TS-4170 inclusive, S/N TS-
6001 through S/N TS-6246 inclusive, or S/N TS-5001 through S/N TS-
5138 inclusive, are not affected by the requirements of paragraphs
(g) and (h) of this AD provided that it is determined that no repair
has been accomplished on the composite side shell panel of that
rudder since first installation on the airplane.
(k) Parts Installation Limitations
As of the effective date of this AD, no person may install, on
any airplane, a rudder, unless the record review and thermography
inspection specified in paragraph (g) of this AD has been done on
that rudder and thereafter all applicable related investigative
actions, repetitive inspections, and corrective actions are done as
required by paragraph (h) of this AD, except as provided in
paragraph (j) of this AD.
(l) Repair Prohibition
As of the effective date of this AD, no person may accomplish a
side shell repair on any rudder using a structure repair manual
procedure identified in Figure A-GBBAA (Sheet 01 and 02) or Figure
A-GBCAA (Sheet 02) of the service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, as applicable,
on any airplane.
(m) 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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; 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) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(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.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0033, dated February 4,
2014, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2014-0928.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. 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.
Issued in Renton, Washington, on December 17, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-30270 Filed 12-24-14; 8:45 am]
BILLING CODE 4910-13-P
