Airworthiness Directives; Airbus Airplanes, 67348-67351 [2015-27725]
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67348
Proposed Rules
Federal Register
Vol. 80, No. 211
Monday, November 2, 2015
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–4808; Directorate
Identifier 2014–NM–134–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 certain
Airbus Model A330–200, –200
Freighter, and –300 series airplanes; and
Model A340–200 and –300 series
airplanes. This proposed AD was
prompted by reports that cracks were
found on an adjacent hole of certain
frames of the center wing box (CWB).
This proposed AD would require
removing fasteners, a rototest inspection
of fastener holes, installing new
fasteners; and if necessary, oversizing
the holes and doing rototest inspections
for cracks, and repairing any cracking
that is found. We are proposing this AD
to detect and correct cracking on certain
holes of certain frames of the CWB,
which could affect the structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by December 17,
2015.
SUMMARY:
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.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
ADDRESSES:
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• 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
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–2015–
4808; 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.
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
Union, has issued EASA Airworthiness
Directive 2014–0149, dated June 13,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A330–200, –200 Freighter, and
–300 series airplanes; and Model A340–
200 and –300 series airplanes. The
MCAI states:
Comments Invited
During accomplishment of A330
Airworthiness Limitation Item (ALI) task 57–
11–04 on the rear fitting of the Frame (FR)
40 between stringers 38 and 39 on both [lefthand] LH/[right-hand] RH sides, cracks were
found on an adjacent hole. After reaming at
second oversize of the subject hole, the crack
was still present.
Other crack findings on this adjacent hole
have been reported on A330 and A340–200/
–300 aeroplanes as a result of sampling
inspections.
This condition, if not detected and
corrected, could affect the structural integrity
of the aeroplane.
For the reasons described above, this
[EASA] AD requires removal of the fasteners
and repetitive rototest inspections of fastener
holes at FR40 vertical web located above
Center Wing Box (CWB) lower panel
reference and/or below CWB lower panel
reference on both sides and, depending on
findings, accomplishment of the applicable
corrective actions.
Note: These holes affected by this [EASA]
AD are different from the ones affected by
EASA AD 2009–0001 [https://
ad.easa.europa.eu/blob/easa_ad_2009_
0001.pdf/AD_2009-0001_1].
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–2015–4808; Directorate Identifier
2014–NM–134–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
Required actions also include
oversizing certain holes, installing new
fasteners, and repairing any cracking
that is found. The initial compliance
times range from 13,500 to 30,900 flight
cycles, or 57,000 to 162,000 flight hours,
depending on operation and utilization.
The repetitive compliance times are
7,400 flight cycles/24,300 flight hours or
5,950 flight cycles/40,400 flight hours
from ALI embodiment. You may
examine the MCAI in the AD docket on
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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Federal Register / Vol. 80, No. 211 / Monday, November 2, 2015 / Proposed Rules
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
4808.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information. The service
information describes procedures for
removing the fasteners and doing a
repetitive rototest inspection of fastener
holes at frame (FR) 40 vertical web on
both sides, installing new fasteners in
transition fit, and oversizing the holes.
• Airbus Service Bulletin A330–57–
3114, dated March 12, 2013.
• Airbus Service Bulletin A330–57–
3115, dated April 4, 2013.
• Airbus Service Bulletin A330–57–
3116, dated March 12, 2013.
• Airbus Service Bulletin A340–57–
4123, dated March 12, 2013.
• Airbus Service Bulletin A340–57–
4124, Revision 01, dated August 22,
2013.
• Airbus Service Bulletin A340–57–
4125, dated March 12, 2013.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section of
this NPRM.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
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 35 airplanes of U.S. registry.
We also estimate that it would take
about 78 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 $232,050, or $6,630 per
product, per inspection cycle.
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In addition, we estimate that any
necessary follow-on actions would take
up to 98 work-hours and require parts
costing $136,400, for a cost of up to
$144,730 per product. We have no way
of determining the number of aircraft
that might need this action.
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.
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67349
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 airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2015–4808;
Directorate Identifier 2014–NM–134–AD.
(a) Comments Due Date
We must receive comments by December
17, 2015.
(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, all manufacturer
serial numbers, except those on which
Airbus Modification (Mod) 55792 or Mod
55306 has been embodied in production, and
except those on which Airbus Repair
Instruction R57115092 has been embodied in
service on both right-hand (RH) and left-hand
(LH) sides.
(1) Airbus Model A330–201, –202, –203,
–223, –223F, –243 –243F, –301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes.
(2) Airbus Model A340–211, –212, –213,
–311, –312, and –313 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by reports that
cracks were found on an adjacent hole of
certain frames of the center wing box (CWB).
We are issuing this AD to detect and correct
cracking on certain holes of the CWB, which
could affect the structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection
Do a rototest inspection of the fastener
holes at the frame (FR) 40 vertical web, on
both sides, as specified in table 1 to
paragraph (g) of this AD, except as required
by paragraph (k) of this AD.
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TABLE 1 TO PARAGRAPH (g) OF THIS AD—COMPLIANCE LOCATION, METHOD, AND TIME
At the later of—
For model
In configuration
In accordance with the
accomplishment instructions of
Inspect
The applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of
A330–300 series
airplanes.
Pre-mod 44360 ..
Below the CWB
lower panel
reference.
Airbus Service Bulletin
A330–57–3114, dated
March 12, 2013.
Airbus Service Bulletin
A330–57–3114, dated
March 12, 2013.
A330–200 and
–300 series airplanes.
Post-mod 44360
and pre-mod
49202.
Below the CWB
lower panel
reference.
Airbus Service Bulletin
A330–57–3116, dated
March 12, 2013.
Airbus Service Bulletin
A330–57–3116, dated
March 12, 2013.
A330–200 and
–300 series airplanes.
Pre-mod 55306
and pre-mod
55792.
Above the CWB
lower panel
reference.
Airbus Service Bulletin
A330–57–3115, dated
April 4, 2013.
Airbus Service Bulletin
A330–57–3115, dated
April 4, 2013.
A340–200 and
–300 series airplanes.
Pre-mod 44360 ..
Below the CWB
lower panel
reference.
Airbus Service Bulletin
A340–57–4123, dated
March 12, 2013.
Airbus Service Bulletin
A340–57–4123, dated
March 12, 2013.
A340–200 and
–300 series airplanes.
Pre-mod 55306
and pre-mod
55792.
Above the CWB
lower panel
reference.
A340–200 and
–300 series airplanes.
Post-mod 44360
and pre-mod
4902.
Below the CWB
lower panel
reference.
Airbus Service Bulletin
A340–57–4124, Revision 01, dated August
22, 2013.
Airbus Service Bulletin
A340–57–4125, dated
March 12, 2013.
Airbus Service Bulletin
A340–57–4124, Revision 01, dated August
22, 2013.
Airbus Service Bulletin
A340–57–4125, dated
March 12, 2013.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(h) Follow-On Actions: No Cracking
If no crack is found during any inspection
required by paragraph (g) of this AD, do the
actions specified in paragraphs (h)(1) and
(h)(2) of this AD.
(1) Before further flight, install new
fasteners in the transition fit, in accordance
with the Accomplishment Instructions of the
service information identified in table 1 to
paragraph (g) of this AD; as applicable.
(2) Repeat the inspection required by
paragraph (g) of this AD thereafter at the
applicable time identified in paragraph 1.E.,
‘‘COMPLIANCE,’’ of the service information
identified in table 1 to paragraph (g) of this
AD; as applicable.
(i) Follow-On Actions for Crack Findings
If any crack is found during any inspection
required by paragraph (g) of this AD: Before
further flight, oversize the holes to the first
oversize in comparison with the current hole
diameter, and do a rototest inspection for
cracks, in accordance with the
Accomplishment Instructions of the service
information identified in table 1 to paragraph
(g) of this AD; as applicable.
(1) If no cracking is found during the
rototest inspection required by paragraph (i)
of this AD, do the actions specified in
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
(i) Before further flight: Install new
fasteners in the transition fit, in accordance
with the Accomplishment Instructions of the
service information identified in table 1 to
paragraph (g) of this AD; as applicable.
(ii) Repeat the inspection required by
paragraph (g) of this AD thereafter at the
applicable time identified in paragraph 1.E.,
‘‘COMPLIANCE,’’ of the service information
identified in table 1 to paragraph (g) of this
AD; as applicable.
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(2) If cracking is found during the rototest
inspection required by paragraph (i) of this
AD, before further flight, 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) Terminating Action Specifications
Accomplishment of the initial and
repetitive inspections required by this AD
terminates accomplishment of Airworthiness
Limitation Items Tasks 57–11–04 and 57–11–
02 of the Airworthiness Limitation Section
(ALS) Part 2, Damage Tolerant Airworthiness
Limitation Items (DT ALI).
(1) Installation of new fasteners as
specified in paragraph (h)(1) of this AD does
not terminate the repetitive inspections
required by paragraph (g) of this AD.
(2) Accomplishment of the corrective
actions specified in paragraphs (i) and (i)(1)
of this AD does not terminate the repetitive
inspections required by paragraph (g) of this
AD.
(3) Accomplishment of the repair specified
in paragraph (i)(2) of this AD does not
terminate repetitive inspections required by
paragraph (g) of this AD, unless the approved
repair method specified otherwise.
(k) Exceptions to Service Information
(1) If the service information identified in
table 1 to paragraph (g) of this AD specifies
contacting Airbus for appropriate action:
Before further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the EASA; or Airbus’s
EASA DOA.
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And the earlier of
Within 2,400 flight cycles
or 24 months after the
effective date of this
AD.
Within 2,400 flight cycles
or 24 months after the
effective date of this
AD.
Within 2,400 flight cycles
or 24 months after the
effective date of this
AD.
Within 1,300 flight cycles
or 24 months after the
effective date of this
AD.
Within 1,300 flight cycles
or 24 months after the
effective date of this
AD.
Within 1,300 flight cycles
or 24 months after the
effective date of this
AD.
(2) Where paragraph 1.E., ‘‘Compliance,’’ of
the service information specified in table 1 to
paragraph (g) of this AD specifies a
Compliance Time in terms of a ‘‘Threshold’’
and ‘‘Grace Period,’’ this AD requires
compliance at the later of the applicable
Threshold and Grace Period.
(3) Where paragraph 1.E., ‘‘Compliance,’’ of
the service information specified in table 1 to
paragraph (g) of this AD specifies a
Threshold as ‘‘before next flight,’’ this AD
requires compliance before the next flight
after the applicable finding.
(l) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (i) of this AD,
if those actions were performed before the
effective date of this AD using the service
information specified in paragraph (l)(1),
(l)(2), (l)(3), (l)(4), (l)(5), (l)(6), (l)(7), (l)(8), or
(l)(9) of this AD. This service information is
not incorporated by reference in this AD.
(1) Airbus Technical Disposition Reference
LR57D11023270, Issue B, dated July 12,
2011.
(2) Airbus Technical Disposition Reference
LR57D11029171, Issue B, dated September 6,
2011.
(3) Airbus Technical Disposition Reference
LR57D11029173, Issue B, dated September 6,
2011.
(4) Airbus Technical Disposition Reference
LR57D11030741, Issue B, dated September
22, 2011.
(5) Airbus Technical Disposition Reference
LR57D11029170, Issue C, dated September 6,
2011.
(6) Airbus Technical Disposition Reference
LR57D11023714, Issue B, dated July 12,
2011.
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(7) Airbus Technical Disposition Reference
LR57D11029172, Issue B, dated September 6,
2011.
(8) Airbus Technical Disposition Reference
LR57D11030740, Issue C, dated September
22, 2011.
(9) Airbus Service Bulletin A340–57–4124,
dated April 4, 2013.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(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.
(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 Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0149, dated
June 13, 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–
2015–4808.
(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 October
21, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–27725 Filed 10–30–15; 8:45 am]
BILLING CODE 4910–13–P
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FEDERAL TRADE COMMISSION
16 CFR Part 305
RIN 3084–AB15
Energy Labeling
Federal Trade Commission
(‘‘FTC’’ or ‘‘Commission’’).
ACTION: Notice of proposed rulemaking.
AGENCY:
SUMMARY: The Commission proposes
amendments to the Energy Labeling
Rule to create requirements related to a
new label database on the Department of
Energy’s (DOE’s) Web site, redesign
ceiling fan labels, improve and update
the comparability ranges for refrigerator
labels, revise central air conditioner
labels in response to new DOE
enforcement requirements, improve
water heater labels, and update current
plumbing disclosures.
DATES: Written comments must be
received on or before January 11, 2016.
ADDRESSES: Interested parties may file a
comment online or on paper, by
following the instructions in the
Request for Comment part of the
SUPPLEMENTARY INFORMATION section
below. Write ‘‘Energy Labeling
Amendments (16 CFR part 305) (Project
No. R611004)’’ on your comment, and
file your comment online at https://
ftcpublic.commentworks.com/ftc/
energylabeling, by following the
instructions on the web-based form. If
you prefer to file your comment on
paper, mail your comment to the
following address: Federal Trade
Commission, Office of the Secretary,
600 Pennsylvania Avenue NW., Suite
CC–5610 (Annex E), Washington, DC
20580, or deliver your comment to the
following address: Federal Trade
Commission, Office of the Secretary,
Constitution Center, 400 7th Street SW.,
5th Floor, Suite 5610 (Annex E),
Washington, DC 20024.
FOR FURTHER INFORMATION CONTACT:
Hampton Newsome, Attorney, (202)
326–2889, Division of Enforcement,
Bureau of Consumer Protection, Federal
Trade Commission, 600 Pennsylvania
Avenue NW., Washington, DC 20580.
SUPPLEMENTARY INFORMATION:
I. Background
The Commission issued the Energy
Labeling Rule (‘‘Rule’’) in 1979,1
pursuant to the Energy Policy and
Conservation Act of 1975 (EPCA).2 The
1 44
FR 66466 (Nov. 19, 1979) (Rule’s initial
promulgation).
2 42 U.S.C. 6294. EPCA also requires DOE to
develop test procedures that measure how much
energy appliances use, and to determine the
representative average cost a consumer pays for
different types of energy.
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67351
Rule requires energy labeling for major
home appliances and other consumer
products to help consumers compare
competing models. It also contains
labeling requirement for refrigerators,
refrigerator-freezers, freezers,
dishwashers, water heaters, clothes
washers, room air conditioners,
furnaces, central air conditioners, heat
pumps, plumbing products, lighting
products, ceiling fans, and televisions.
The Rule requires manufacturers to
attach yellow EnergyGuide labels for
many of the covered products and
prohibits retailers from removing the
labels or rendering them illegible. In
addition, it directs sellers, including
retailers, to post label information on
Web sites and in paper catalogs from
which consumers can order products.
EnergyGuide labels for most covered
products contain three key disclosures:
estimated annual energy cost; a
product’s energy consumption or energy
efficiency rating as determined from
Department of Energy (DOE) test
procedures; and a comparability range
displaying the highest and lowest
energy costs or efficiency ratings for all
similar models. For energy cost
calculations, the Rule specifies national
average costs for applicable energy
sources (e.g., electricity, natural gas, oil)
as calculated by DOE. Under the Rule,
the Commission periodically updates
comparability range and annual energy
cost information based on manufacturer
data submitted pursuant to the Rule’s
reporting requirements.3
II. Proposed Amendments to the Energy
Labeling Rule
This Notice seeks comment on several
proposed changes to the Energy
Labeling Rule, including requirements
related to a new label database on DOE’s
Web site, revised ceiling fan labels, new
refrigerator comparability range
information, portable air conditioner
labeling, labeling for dual-mode
refrigerators, revised central air
conditioner labels in response to
proposed changes to DOE’s enforcement
rules, water heater labels, and plumbing
disclosures. The Commission sought
comment on a few of these issues during
its regulatory review of the Energy
Labeling Rule.4 Other issues discussed
in this Notice reflect recent
developments from DOE rulemakings
and the consumer product marketplace.
A. Online Label Database
Background: In a June 18, 2014
Supplemental Notice of Proposed
3 16
CFR 305.10.
77 FR 15298 (Mar. 15, 2012); and 79 FR
34642 (June 18, 2014).
4 See
E:\FR\FM\02NOP1.SGM
02NOP1
]]>Agencies
[Federal Register Volume 80, Number 211 (Monday, November 2, 2015)]
[Proposed Rules]
[Pages 67348-67351]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-27725]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 80, No. 211 / Monday, November 2, 2015 /
Proposed Rules
[[Page 67348]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-4808; Directorate Identifier 2014-NM-134-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 A330-200, -200 Freighter, and -300 series
airplanes; and Model A340-200 and -300 series airplanes. This proposed
AD was prompted by reports that cracks were found on an adjacent hole
of certain frames of the center wing box (CWB). This proposed AD would
require removing fasteners, a rototest inspection of fastener holes,
installing new fasteners; and if necessary, oversizing the holes and
doing rototest inspections for cracks, and repairing any cracking that
is found. We are proposing this AD to detect and correct cracking on
certain holes of certain frames of the CWB, which could affect the
structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by December 17,
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 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-2015-
4808; 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-2015-4808;
Directorate Identifier 2014-NM-134-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 Union, has issued EASA
Airworthiness Directive 2014-0149, dated June 13, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200
and -300 series airplanes. The MCAI states:
During accomplishment of A330 Airworthiness Limitation Item
(ALI) task 57-11-04 on the rear fitting of the Frame (FR) 40 between
stringers 38 and 39 on both [left-hand] LH/[right-hand] RH sides,
cracks were found on an adjacent hole. After reaming at second
oversize of the subject hole, the crack was still present.
Other crack findings on this adjacent hole have been reported on
A330 and A340-200/-300 aeroplanes as a result of sampling
inspections.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
For the reasons described above, this [EASA] AD requires removal
of the fasteners and repetitive rototest inspections of fastener
holes at FR40 vertical web located above Center Wing Box (CWB) lower
panel reference and/or below CWB lower panel reference on both sides
and, depending on findings, accomplishment of the applicable
corrective actions.
Note: These holes affected by this [EASA] AD are different from
the ones affected by EASA AD 2009-0001 [https://ad.easa.europa.eu/blob/easa_ad_2009_0001.pdf/AD_2009-0001_1].
Required actions also include oversizing certain holes, installing
new fasteners, and repairing any cracking that is found. The initial
compliance times range from 13,500 to 30,900 flight cycles, or 57,000
to 162,000 flight hours, depending on operation and utilization. The
repetitive compliance times are 7,400 flight cycles/24,300 flight hours
or 5,950 flight cycles/40,400 flight hours from ALI embodiment. You may
examine the MCAI in the AD docket on
[[Page 67349]]
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2015-4808.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information. The service
information describes procedures for removing the fasteners and doing a
repetitive rototest inspection of fastener holes at frame (FR) 40
vertical web on both sides, installing new fasteners in transition fit,
and oversizing the holes.
Airbus Service Bulletin A330-57-3114, dated March 12,
2013.
Airbus Service Bulletin A330-57-3115, dated April 4, 2013.
Airbus Service Bulletin A330-57-3116, dated March 12,
2013.
Airbus Service Bulletin A340-57-4123, dated March 12,
2013.
Airbus Service Bulletin A340-57-4124, Revision 01, dated
August 22, 2013.
Airbus Service Bulletin A340-57-4125, dated March 12,
2013.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section of this
NPRM.
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 35 airplanes of U.S.
registry.
We also estimate that it would take about 78 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 $232,050, or $6,630 per product, per
inspection cycle.
In addition, we estimate that any necessary follow-on actions would
take up to 98 work-hours and require parts costing $136,400, for a cost
of up to $144,730 per product. We have no way of determining the number
of aircraft that might need this action.
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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2015-4808; Directorate Identifier 2014-NM-
134-AD.
(a) Comments Due Date
We must receive comments by December 17, 2015.
(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, all
manufacturer serial numbers, except those on which Airbus
Modification (Mod) 55792 or Mod 55306 has been embodied in
production, and except those on which Airbus Repair Instruction
R57115092 has been embodied in service on both right-hand (RH) and
left-hand (LH) sides.
(1) Airbus Model A330-201, -202, -203, -223, -223F, -243 -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(2) Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports that cracks were found on an
adjacent hole of certain frames of the center wing box (CWB). We are
issuing this AD to detect and correct cracking on certain holes of
the CWB, which could affect the structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection
Do a rototest inspection of the fastener holes at the frame (FR)
40 vertical web, on both sides, as specified in table 1 to paragraph
(g) of this AD, except as required by paragraph (k) of this AD.
[[Page 67350]]
Table 1 to paragraph (g) of this AD--Compliance Location, Method, and Time
--------------------------------------------------------------------------------------------------------------------------------------------------------
At the later of--
---------------------------------------------
In accordance with The applicable time
For model In configuration Inspect the accomplishment specified in
instructions of paragraph 1.E., And the earlier of
``Compliance,'' of
--------------------------------------------------------------------------------------------------------------------------------------------------------
A330-300 series airplanes.......... Pre-mod 44360......... Below the CWB lower Airbus Service Airbus Service Within 2,400 flight
panel reference. Bulletin A330-57- Bulletin A330-57- cycles or 24 months
3114, dated March 3114, dated March after the effective
12, 2013. 12, 2013. date of this AD.
A330-200 and -300 series airplanes. Post-mod 44360 and pre- Below the CWB lower Airbus Service Airbus Service Within 2,400 flight
mod 49202. panel reference. Bulletin A330-57- Bulletin A330-57- cycles or 24 months
3116, dated March 3116, dated March after the effective
12, 2013. 12, 2013. date of this AD.
A330-200 and -300 series airplanes. Pre-mod 55306 and pre- Above the CWB lower Airbus Service Airbus Service Within 2,400 flight
mod 55792. panel reference. Bulletin A330-57- Bulletin A330-57- cycles or 24 months
3115, dated April 4, 3115, dated April 4, after the effective
2013. 2013. date of this AD.
A340-200 and -300 series airplanes. Pre-mod 44360......... Below the CWB lower Airbus Service Airbus Service Within 1,300 flight
panel reference. Bulletin A340-57- Bulletin A340-57- cycles or 24 months
4123, dated March 4123, dated March after the effective
12, 2013. 12, 2013. date of this AD.
A340-200 and -300 series airplanes. Pre-mod 55306 and pre- Above the CWB lower Airbus Service Airbus Service Within 1,300 flight
mod 55792. panel reference. Bulletin A340-57- Bulletin A340-57- cycles or 24 months
4124, Revision 01, 4124, Revision 01, after the effective
dated August 22, dated August 22, date of this AD.
2013. 2013.
A340-200 and -300 series airplanes. Post-mod 44360 and pre- Below the CWB lower Airbus Service Airbus Service Within 1,300 flight
mod 4902. panel reference. Bulletin A340-57- Bulletin A340-57- cycles or 24 months
4125, dated March 4125, dated March after the effective
12, 2013. 12, 2013. date of this AD.
--------------------------------------------------------------------------------------------------------------------------------------------------------
(h) Follow-On Actions: No Cracking
If no crack is found during any inspection required by paragraph
(g) of this AD, do the actions specified in paragraphs (h)(1) and
(h)(2) of this AD.
(1) Before further flight, install new fasteners in the
transition fit, in accordance with the Accomplishment Instructions
of the service information identified in table 1 to paragraph (g) of
this AD; as applicable.
(2) Repeat the inspection required by paragraph (g) of this AD
thereafter at the applicable time identified in paragraph 1.E.,
``COMPLIANCE,'' of the service information identified in table 1 to
paragraph (g) of this AD; as applicable.
(i) Follow-On Actions for Crack Findings
If any crack is found during any inspection required by
paragraph (g) of this AD: Before further flight, oversize the holes
to the first oversize in comparison with the current hole diameter,
and do a rototest inspection for cracks, in accordance with the
Accomplishment Instructions of the service information identified in
table 1 to paragraph (g) of this AD; as applicable.
(1) If no cracking is found during the rototest inspection
required by paragraph (i) of this AD, do the actions specified in
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
(i) Before further flight: Install new fasteners in the
transition fit, in accordance with the Accomplishment Instructions
of the service information identified in table 1 to paragraph (g) of
this AD; as applicable.
(ii) Repeat the inspection required by paragraph (g) of this AD
thereafter at the applicable time identified in paragraph 1.E.,
``COMPLIANCE,'' of the service information identified in table 1 to
paragraph (g) of this AD; as applicable.
(2) If cracking is found during the rototest inspection required
by paragraph (i) of this AD, before further flight, 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) Terminating Action Specifications
Accomplishment of the initial and repetitive inspections
required by this AD terminates accomplishment of Airworthiness
Limitation Items Tasks 57-11-04 and 57-11-02 of the Airworthiness
Limitation Section (ALS) Part 2, Damage Tolerant Airworthiness
Limitation Items (DT ALI).
(1) Installation of new fasteners as specified in paragraph
(h)(1) of this AD does not terminate the repetitive inspections
required by paragraph (g) of this AD.
(2) Accomplishment of the corrective actions specified in
paragraphs (i) and (i)(1) of this AD does not terminate the
repetitive inspections required by paragraph (g) of this AD.
(3) Accomplishment of the repair specified in paragraph (i)(2)
of this AD does not terminate repetitive inspections required by
paragraph (g) of this AD, unless the approved repair method
specified otherwise.
(k) Exceptions to Service Information
(1) If the service information identified in table 1 to
paragraph (g) of this AD specifies contacting Airbus for appropriate
action: Before further flight, repair using a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the EASA; or Airbus's EASA DOA.
(2) Where paragraph 1.E., ``Compliance,'' of the service
information specified in table 1 to paragraph (g) of this AD
specifies a Compliance Time in terms of a ``Threshold'' and ``Grace
Period,'' this AD requires compliance at the later of the applicable
Threshold and Grace Period.
(3) Where paragraph 1.E., ``Compliance,'' of the service
information specified in table 1 to paragraph (g) of this AD
specifies a Threshold as ``before next flight,'' this AD requires
compliance before the next flight after the applicable finding.
(l) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (i) of this AD, if those actions were performed
before the effective date of this AD using the service information
specified in paragraph (l)(1), (l)(2), (l)(3), (l)(4), (l)(5),
(l)(6), (l)(7), (l)(8), or (l)(9) of this AD. This service
information is not incorporated by reference in this AD.
(1) Airbus Technical Disposition Reference LR57D11023270, Issue
B, dated July 12, 2011.
(2) Airbus Technical Disposition Reference LR57D11029171, Issue
B, dated September 6, 2011.
(3) Airbus Technical Disposition Reference LR57D11029173, Issue
B, dated September 6, 2011.
(4) Airbus Technical Disposition Reference LR57D11030741, Issue
B, dated September 22, 2011.
(5) Airbus Technical Disposition Reference LR57D11029170, Issue
C, dated September 6, 2011.
(6) Airbus Technical Disposition Reference LR57D11023714, Issue
B, dated July 12, 2011.
[[Page 67351]]
(7) Airbus Technical Disposition Reference LR57D11029172, Issue
B, dated September 6, 2011.
(8) Airbus Technical Disposition Reference LR57D11030740, Issue
C, dated September 22, 2011.
(9) Airbus Service Bulletin A340-57-4124, dated April 4, 2013.
(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 Design Organization Approval (DOA). If approved by
the DOA, the approval must include the DOA-authorized signature.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0149, dated June 13, 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-2015-4808.
(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 October 21, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-27725 Filed 10-30-15; 8:45 am]
BILLING CODE 4910-13-P
