Airworthiness Directives; Airbus Airplanes, 2391-2394 [2014-00495]
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Federal Register / Vol. 79, No. 9 / Tuesday, January 14, 2014 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–1072; Directorate
Identifier 2012–NM–164–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2012–03–
04, for certain Airbus Model A310 series
airplanes. AD 2012–03–04 currently
requires, for certain airplanes,
modifying the wire routing and
installing additional protective sleeves.
Since we issued AD 2012–03–04, we
received reports of new interferences of
newly routed wire bundle 2S. This
proposed AD would continue to require
the actions in AD 2012–03–04, and
would require additional work for
certain airplanes. We are proposing this
AD to prevent short circuits leading to
arcing, and possible fuel tank explosion.
DATES: We must receive comments on
this proposed AD by February 28, 2014.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS,
Airworthiness Office—EAW, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may 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.
tkelley on DSK3SPTVN1PROD with PROPOSALS
SUMMARY:
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2013–
1072; 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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2013–1072; Directorate Identifier
2012–NM–164–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
On January 26, 2012, we issued AD
2012–03–04, Amendment 39–16945 (77
FR 21397, April 10, 2012). AD 2012–03–
04 required actions intended to address
an unsafe condition on certain Airbus
Model A310 series airplanes.
Since we issued AD 2012–03–04,
Amendment 39–16945 (77 FR 21397,
April 10, 2012), we received reports of
new interferences of newly routed wire
bundle 2S.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0188,
dated September 19, 2012 (referred to
after this as the Mandatory Continuing
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2391
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
Within the scope of the Fuel System Safety
Program (FSSP), analyses of the wire routing
showed that the route 2S of the fuel electrical
circuit in the Right Hand (RH) wing ensures
insufficient segregation between fuel quantity
indication wires and the 115 Volts
Alternating Current (VAC) wires of route 2S
which could, under certain conditions, lead
to a short circuit and subsequent arcing,
creating a potential ignition source in the fuel
tank vapour space.
This condition, if not detected, could result
in a fuel tank explosion and consequent loss
of the aeroplane.
To address this potential unsafe condition,
DGAC France issued [an] AD * * * to
require improvements of the design as
specified in Airbus Service Bulletin (SB)
A310–28–2148 original issue or Revision 01.
EASA AD 2007–0230 [(https://
ad.easa.europa.eu/blob/easa_ad_2007_0230_
Superseded.pdf/AD_2007-0230_1)], which
superseded [a] DGAC France AD * * *,
[which] required those same actions, plus
additional work 1, as defined in Airbus SB
A310–28–2148 Revision 02.
Since EASA AD 2007–0230 was issued, an
operator reported the possibility of chafing
between the new routing of the wire bundle
2S in the RH wing pylon area and the wire
bundle of No. 2 engine generator. The
modification of this zone was introduced by
Airbus SB A310–28–2148 Revision 02 as
additional work 1. Investigation results
showed that, to avoid the risk of chafing, the
affected wiring harnesses must be installed at
a higher position to provide sufficient
clearance with the newly routed wire bundle
2S conduit.
Airbus published Revision 03 of SB A310–
28–2148 to implement these changes as
additional work 2. Subsequently, a new
potential interference due to insufficient
clearance was found, which prompted Airbus
to issue SB A310–28–2148 Revision 04.
Prompted by these findings and actions,
EASA issued AD 2011–0005 [(https://
ad.easa.europa.eu/blob/easa_ad_2011_0005_
Superseded.pdf/AD_2011-0005_1)], retaining
the requirements of EASA AD 2007–0230,
which was superseded, and required the
additional work 2 as specified in Revisions
03 and 04 of Airbus SB A310–28–2148.
Since EASA AD 2011–0005 was issued,
several operators of aeroplanes not having
been modified in-service through Airbus SB
A310–36–2015, or without having Airbus
modification 07633 applied in production,
reported to have embodied Airbus SB A310–
28–2148 at Revision 02 or Revision 03 on the
aeroplane. However, the adequate
instructions to avoid the new interferences
were only introduced in Airbus SB A310–28–
2148 Revision 04.
For the reasons described above, this new
[EASA] AD retains the requirements of EASA
AD 2011–0005, which is superseded, and
requires, for certain aeroplanes, the
additional work 3 [segregating wire route 2S
in the RH pylon area or modifying the wire
routings] as defined in Airbus SB A310–28–
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Federal Register / Vol. 79, No. 9 / Tuesday, January 14, 2014 / Proposed Rules
2148 Revision 06. As SB A310–28–2148
Revision 07 was issued to clarify the
additional work 1, 2 and 3 [segregating wire
route 2S in the RH pylon area or modifying
the wire routings] for aeroplanes that have
previously embodied that SB at original
issue, Revision 01 or Revision 02, this AD
also clarifies the required additional work.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating it in Docket No. FAA–
2013–1072.
Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A310–28–2148, Revision 07,
dated February 13, 2012. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
Change to AD 2012–03–04, Amendment
39–16945 (77 FR 21397, April 10, 2012)
This proposed AD would retain all
requirements of AD 2012–03–04,
Amendment 39–16945 (77 FR 21397,
April 10, 2012). Since AD 2012–03–04
was issued, the AD format has been
revised, and certain paragraphs have
been rearranged. As a result, the
corresponding paragraph designators
have changed in this proposed AD, as
listed in the following table:
REVISED PARAGRAPH DESIGNATORS
Requirement in AD
2012–03–04,
Amendment 39–16945
(77 FR 21397, April
10, 2012)
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
Corresponding
requirement in this
proposed AD
(h)
(i)
(j)
(k)
(l)
(m)
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
(l)(1)
(h)
(i)
(j)
(k)
(l)(2)
Also, we have revised certain
paragraphs of AD 2012–03–04,
Amendment 39–16945 (77 FR 21397,
April 10, 2012), by placing the required
service information into sub-paragraphs
in this proposed AD.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD
affects 41 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Cost on
U.S. operators
Labor cost
Modification [retained actions from AD 2012–
03–04, Amendment 39–16945 (77 FR
21397, April 10, 2012)].
Modification (additional work) [new proposed
action].
62 work-hours × $85 per hour = $5,270 ........
$2,210
$7,480
$306,680
32 work-hours × $85 per hour = $2,720 ........
1,100
3,820
156,620
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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 proposed
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
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Parts cost
Cost per
product
Action
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.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2012–03–04, Amendment 39–16945 (77
FR 21397, April 10, 2012), and adding
the following new AD:
■
Airbus: Docket No. FAA–2013–1072;
Directorate Identifier 2012–NM–164–AD.
(a) Comments Due Date
We must receive comments by February
28, 2014.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(b) Affected ADs
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
(c) Applicability
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This AD supersedes AD 2012–03–04,
Amendment 39–16945 (77 FR 21397, April
10, 2012).
This AD applies to Airbus Model A310–
203, –204, –221, –222, –304, –322, –324, and
–325 airplanes, certificated in any category,
all certified models, all serial numbers.
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(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
(e) Reason
This AD was prompted by reports of new
interferences of newly routed wire bundle
2S. We are issuing this AD to prevent short
circuits leading to arcing, and possible fuel
tank explosion.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Retained Modification of Routing Wires
With Revised Service Information
This paragraph restates the modification
required by paragraph (g) of AD 2012–03–04,
Amendment 39–16945 (77 FR 21397, April
10, 2012), with revised service information.
For all airplanes except airplanes on which
Airbus Service Bulletin A310–28–2148,
Revision 02, dated March 9, 2007, has been
done (Airbus Modifications 12427 and
12435): Within 4,000 flight hours after
September 3, 2004 (the effective date of AD
2004–15–16, Amendment 39–13750 (69 FR
45578, July 30, 2004)), modify the routing of
wires in the right-hand (RH) wing by
installing cable sleeves. Do the modification
as per the Accomplishment Instructions of
the service information specified in
paragraph (g)(1), (g)(2), (g)(3), (g)(4), or (g)(5)
of this AD. As of February 20, 2008 (the
effective date of AD 2008–01–05,
Amendment 39–15330 (73 FR 2795, January
16, 2008)), only the service information
specified in paragraphs (g)(2), (g)(3), (g)(4),
and (g)(5) of this AD may be used. As of May
15, 2012 (the effective date of AD 2012–03–
04), only the service information specified in
paragraphs (g)(3), (g)(4), and (g)(5) of this AD
may be used. As of the effective date of this
AD, only the service bulletin specified in
paragraph (g)(5) of this AD may be used.
(1) Airbus Service Bulletin A310–28–2148,
Revision 01, dated October 29, 2002.
(2) Airbus Service Bulletin A310–28–2148,
Revision 02, dated March 9, 2007.
(3) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 05, dated August 3,
2010.
(4) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 06, dated August
31, 2011.
(5) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 07, dated February
13, 2012.
(h) Retained Modification of Protection
Sleeves With Revised Service Information
This paragraph restates the modification
required by paragraph (i) of AD 2012–03–04,
Amendment 39–16945 (77 FR 21397, April
10, 2012), with revised service information.
For airplanes on which the actions specified
in Airbus Service Bulletin A310–28–2148,
dated January 23, 2002; or Airbus Service
Bulletin A310–28–2148, Revision 01, dated
October 29, 2002; have been done before
February 20, 2008 (the effective date of AD
2008–01–05, Amendment 39–15330 (73 FR
2795, January 16, 2008)), except for airplanes
on which Airbus Service Bulletin A310–28–
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2148, Revision 02, dated March 9, 2007, has
been done (Airbus Modifications 12427 and
12435): Within 6,000 flight hours or 30
months after February 20, 2008 (the effective
date of AD 2008–01–05), whichever occurs
first, perform further modification by
installing additional protection sleeves in the
outer wing area near the cadensicon sensor
and segregating wire route 2S in the RH
pylon area, in accordance with the
Accomplishment Instructions of service
information specified in paragraph (h)(1),
(h)(2), (h)(3), or (h)(4) of this AD. As of May
15, 2012 (the effective date of AD 2012–03–
04), only the service information specified in
paragraphs (h)(2), (h)(3), and (h)(4) of this AD
may be used. As of the effective date of this
AD, only the service bulletin specified in
paragraph (h)(4) of this AD may be used.
(1) Airbus Service Bulletin A310–28–2148,
Revision 02, dated March 9, 2007.
(2) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 05, dated August 3,
2010.
(3) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 06, dated August
31, 2011.
(4) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 07, dated February
13, 2012.
(i) Retained New Modification/Installation of
Wire Routings for Certain Airplanes With
Revised Service Information
This paragraph restates the new
modification/installation required by
paragraph (j) of AD 2012–03–04, Amendment
39–16945 (77 FR 21397, April 10, 2012), with
revised service information. For airplanes on
which the actions specified in Airbus Service
Bulletin A310–28–2148, Revision 02, dated
March 9, 2007, have been accomplished, and
do not have production modification 07633;
and on which Airbus Service Bulletin A310–
36–2015 has not been done: Within 6,000
flight hours or 30 months after May 15, 2012
(the effective date of AD 2012–03–04),
whichever occurs first, modify the wire
routings, in accordance with the
Accomplishment Instructions of the service
information specified in paragraph (i)(1),
(i)(2), or (i)(3) of this AD. As of the effective
date of this AD, only the service bulletin
specified in paragraph (i)(3) of this AD may
be used.
(1) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 05, dated August 3,
2010.
(2) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 06, dated August
31, 2011.
(3) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 07, dated February
13, 2012.
(j) Retained New Modification/Installation of
Bracket for Certain Other Airplanes With
Revised Service Information
This paragraph restates the new
modification/installation required by
paragraph (k) of AD 2012–03–04,
Amendment 39–16945 (77 FR 21397, April
10, 2012), with revised service information.
For airplanes on which the actions specified
in Airbus Service Bulletin A310–28–2148,
Revision 02, dated March 9, 2007, have been
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2393
accomplished, and have production
modification 07633; or on which Airbus
Service Bulletin A310–36–2015 has been
done: Within 1,000 flight hours after May 15,
2012 (the effective date of AD 2012–03–04),
install a modified bracket, in accordance
with paragraph 3.B.(7), ‘‘Additional Work 2,’’
of the Accomplishment Instructions of the
service information specified in paragraph
(j)(1), (j)(2), or (j)(3) of this AD. As of the
effective date of this AD, only the service
bulletin specified in paragraph (j)(3) of this
AD may be used.
(1) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 05, dated August 3,
2010.
(2) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 06, dated August
31, 2011.
(3) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 07, dated February
13, 2012.
(k) Retained Modification/Installation
Provision for Certain Airplanes
This paragraph restates the modification/
installation provision specified in paragraph
(l) of AD 2012–03–04, Amendment 39–16945
(77 FR 21397, April 10, 2012). For airplanes
on which the actions specified in Airbus
Service Bulletin A310–28–2148, Revision 03,
dated June 2, 2009, have been accomplished;
and have modification 07633 done in
production; or on which the actions specified
in Airbus Service Bulletin A310–36–2015
have been done; no further action is required
by paragraphs (g) through (j) of this AD.
(l) Retained Credit for Previous Actions
(1) This paragraph restates the credit for
previous actions required by paragraph (h) of
AD 2012–03–04, Amendment 39–16945 (77
FR 21397, April 10, 2012). This paragraph
provides credit for the modification of the
routing of wires required by paragraph (g) of
AD 2012–03–04, if the modification was
performed before September 3, 2004 (the
effective date of AD 2004–15–16,
Amendment 39–13750 (69 FR 45578, July 30,
2004)), using Airbus Service Bulletin A310–
28–2148, dated January 23, 2002.
(2) This paragraph restates the credit for
previous actions required by paragraph (m) of
AD 2012–03–04, Amendment 39–16945 (77
FR 21397, April 10, 2012). This paragraph
provides credit for modifications required by
paragraphs (g), (i), (j), and (k) of AD 2012–
03–04, if the modifications were performed
before May 15, 2012 (the effective date of AD
2012–03–04), using Airbus Mandatory
Service Bulletin A310–28–2148, Revision 04,
dated April 14, 2010.
(m) New Requirement of This AD:
Additional Work 2 and 3
For airplanes on which the actions
specified in Airbus Service Bulletin A310–
28–2148, Revision 02, dated March 9, 2007,
have been accomplished, and on which the
actions specified in Airbus Service Bulletin
A310–36–2015 have not been done; or have
Airbus Modification 07633 done in
production: Within 1,000 flight hours or 12
months after the effective date of this AD,
whichever occurs first, do the modification,
in accordance with paragraphs ‘‘Additional
Work 2’’ and ‘‘Additional Work 3’’ of the
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Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310–28–2148,
Revision 07, dated February 13, 2012.
(n) New Requirement of This AD: Additional
Work 3
For airplanes on which the actions
specified in Airbus Service Bulletin A310–
28–2148, Revision 03, dated June 2, 2009,
have been accomplished, and do not have
production modification 07633 or Airbus
Service Bulletin A310–36–2015 has not been
done: Within 1,000 flight hours or 12 months
after the effective date of this AD, whichever
occurs first, do the modification, in
accordance with paragraph ‘‘Additional
Work 3’’ of the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A310–
28–2148, Revision 07, dated February 13,
2012.
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(o) New Requirement of This AD: Additional
Work 1 and 2
For airplanes on which the actions
specified in Airbus Service Bulletin A310–
36–2015 have not been accomplished and
production modification 07633 has not been
done, and that have done the actions
specified in paragraphs (o)(1) and (o)(2) of
this AD: Within 6,000 flight hours or 30
months after the effective date of this AD,
whichever occurs first, do the modification,
in accordance with paragraphs ‘‘Additional
Work 1’’ and ‘‘Additional Work 2’’ of the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310–28–2148,
Revision 07, dated February 13, 2012.
(1) Modification in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–28–2148, dated
January 23, 2002; or Airbus Service Bulletin
A310–28–2148, Revision 01, dated October
29, 2002.
(2) Further modification by ‘‘Additional
Work 3’’ of the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A310–
28–2148, Revision 06, dated August 31, 2011.
(p) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–2125; fax (425) 227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
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(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer, use these actions if they are
FAA-approved. Corrective actions are
considered FAA-approved if they were
approved by the State of Design Authority (or
its delegated agent, or by the design approval
holder (DAH) with a State of Design
Authority’s design organization approval).
For a repair method to be approved, the
repair approval must specifically refer to this
AD. You are required to ensure the product
is airworthy before it is returned to service.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2012–0188, dated September 19,
2012, 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–
2013–1072.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
You may 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 January
7, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–00495 Filed 1–13–14; 8:45 am]
BILLING CODE 4910–13–P
COMMODITY FUTURES TRADING
COMMISSION
17 CFR Part 150
RIN 3038–AD82
Aggregation of Provisions
Commodity Futures Trading
Commission.
ACTION: Proposed rule; extension of
comment period.
AGENCY:
On November 15, 2013, the
Commodity Futures Trading
Commission (‘‘Commission’’) published
in the Federal Register a notice of
proposed rulemaking (the ‘‘Aggregation
Proposal’’) to amend existing
regulations setting out the Commission’s
policy for aggregation under its position
limits regime. On the same day that the
Commission adopted the Aggregation
Proposal, it also adopted a proposal to
establish speculative position limits for
the 28 exempt and agricultural
commodity futures and options
SUMMARY:
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
contracts and the physical commodity
swaps that are economically equivalent
to such contracts that previously had
been covered by part 151 of its
regulations (the ‘‘Position Limits
Proposal’’). However, the Position
Limits Proposal was not published in
the Federal Register until December 12,
2013. Because the comment period for
both proposals was 60 days after
publication in the Federal Register, the
comment period for the Position Limits
Proposal runs to a later date than the
comment period for the Aggregation
Proposal. In order to provide interested
parties with an opportunity to comment
on the Aggregation Proposal for so long
as the comment period on the Position
Limits Proposal is open, the
Commission is extending the comment
period for the Aggregation Proposal so
that it ends at the same time as the
comment period for the Position Limits
Proposal.
DATES: The comment period for the
Aggregation Proposal published
November 15, 2013, at 78 FR 68946, is
extended until February 10, 2014.
ADDRESSES: You may submit comments,
identified by RIN 3038–AD82, by any of
the following methods:
• Agency Web site: https://
comments.cftc.gov;
• Mail: Melissa D. Jurgens, Secretary
of the Commission, Commodity Futures
Trading Commission, Three Lafayette
Centre, 1155 21st Street NW.,
Washington, DC 20581;
• Hand Delivery/Courier: Same as
mail, above; or
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow
instructions for submitting comments.
Please submit your comments using
only one method.
All comments must be submitted in
English, or if not, accompanied by an
English translation. Comments will be
posted as received to https://
www.cftc.gov. You should submit only
information that you wish to make
available publicly. If you wish the
Commission to consider information
that may be exempt from disclosure
under the Freedom of Information Act,
a petition for confidential treatment of
the exempt information may be
submitted according to the procedures
established in CFTC regulations at 17
CFR part 145.
The Commission reserves the right,
but shall have no obligation, to review,
pre-screen, filter, redact, refuse or
remove any or all of your submission
from https://www.cftc.gov that it may
deem to be inappropriate for
publication, such as obscene language.
All submissions that have been redacted
E:\FR\FM\14JAP1.SGM
14JAP1
]]>Agencies
[Federal Register Volume 79, Number 9 (Tuesday, January 14, 2014)]
[Proposed Rules]
[Pages 2391-2394]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-00495]
[[Page 2391]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-1072; Directorate Identifier 2012-NM-164-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-03-
04, for certain Airbus Model A310 series airplanes. AD 2012-03-04
currently requires, for certain airplanes, modifying the wire routing
and installing additional protective sleeves. Since we issued AD 2012-
03-04, we received reports of new interferences of newly routed wire
bundle 2S. This proposed AD would continue to require the actions in AD
2012-03-04, and would require additional work for certain airplanes. We
are proposing this AD to prevent short circuits leading to arcing, and
possible fuel tank explosion.
DATES: We must receive comments on this proposed AD by February 28,
2014.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may 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-2013-
1072; 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-2125;
fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-1072;
Directorate Identifier 2012-NM-164-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
On January 26, 2012, we issued AD 2012-03-04, Amendment 39-16945
(77 FR 21397, April 10, 2012). AD 2012-03-04 required actions intended
to address an unsafe condition on certain Airbus Model A310 series
airplanes.
Since we issued AD 2012-03-04, Amendment 39-16945 (77 FR 21397,
April 10, 2012), we received reports of new interferences of newly
routed wire bundle 2S.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2012-0188, dated September 19, 2012 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Within the scope of the Fuel System Safety Program (FSSP),
analyses of the wire routing showed that the route 2S of the fuel
electrical circuit in the Right Hand (RH) wing ensures insufficient
segregation between fuel quantity indication wires and the 115 Volts
Alternating Current (VAC) wires of route 2S which could, under
certain conditions, lead to a short circuit and subsequent arcing,
creating a potential ignition source in the fuel tank vapour space.
This condition, if not detected, could result in a fuel tank
explosion and consequent loss of the aeroplane.
To address this potential unsafe condition, DGAC France issued
[an] AD * * * to require improvements of the design as specified in
Airbus Service Bulletin (SB) A310-28-2148 original issue or Revision
01. EASA AD 2007-0230 [(https://ad.easa.europa.eu/blob/easa_ad_2007_0230_Superseded.pdf/AD_2007-0230_1)], which superseded [a]
DGAC France AD * * *, [which] required those same actions, plus
additional work 1, as defined in Airbus SB A310-28-2148 Revision 02.
Since EASA AD 2007-0230 was issued, an operator reported the
possibility of chafing between the new routing of the wire bundle 2S
in the RH wing pylon area and the wire bundle of No. 2 engine
generator. The modification of this zone was introduced by Airbus SB
A310-28-2148 Revision 02 as additional work 1. Investigation results
showed that, to avoid the risk of chafing, the affected wiring
harnesses must be installed at a higher position to provide
sufficient clearance with the newly routed wire bundle 2S conduit.
Airbus published Revision 03 of SB A310-28-2148 to implement
these changes as additional work 2. Subsequently, a new potential
interference due to insufficient clearance was found, which prompted
Airbus to issue SB A310-28-2148 Revision 04.
Prompted by these findings and actions, EASA issued AD 2011-0005
[(https://ad.easa.europa.eu/blob/easa_ad_2011_0005_Superseded.pdf/AD_2011-0005_1)], retaining the requirements of
EASA AD 2007-0230, which was superseded, and required the additional
work 2 as specified in Revisions 03 and 04 of Airbus SB A310-28-
2148.
Since EASA AD 2011-0005 was issued, several operators of
aeroplanes not having been modified in-service through Airbus SB
A310-36-2015, or without having Airbus modification 07633 applied in
production, reported to have embodied Airbus SB A310-28-2148 at
Revision 02 or Revision 03 on the aeroplane. However, the adequate
instructions to avoid the new interferences were only introduced in
Airbus SB A310-28-2148 Revision 04.
For the reasons described above, this new [EASA] AD retains the
requirements of EASA AD 2011-0005, which is superseded, and
requires, for certain aeroplanes, the additional work 3 [segregating
wire route 2S in the RH pylon area or modifying the wire routings]
as defined in Airbus SB A310-28-
[[Page 2392]]
2148 Revision 06. As SB A310-28-2148 Revision 07 was issued to
clarify the additional work 1, 2 and 3 [segregating wire route 2S in
the RH pylon area or modifying the wire routings] for aeroplanes
that have previously embodied that SB at original issue, Revision 01
or Revision 02, this AD also clarifies the required additional work.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA-
2013-1072.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A310-28-2148, Revision
07, dated February 13, 2012. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI.
Change to AD 2012-03-04, Amendment 39-16945 (77 FR 21397, April 10,
2012)
This proposed AD would retain all requirements of AD 2012-03-04,
Amendment 39-16945 (77 FR 21397, April 10, 2012). Since AD 2012-03-04
was issued, the AD format has been revised, and certain paragraphs have
been rearranged. As a result, the corresponding paragraph designators
have changed in this proposed AD, as listed in the following table:
Revised Paragraph Designators
------------------------------------------------------------------------
Requirement in AD 2012-03-04,
Amendment 39-16945 (77 FR 21397, Corresponding requirement in this
April 10, 2012) proposed AD
------------------------------------------------------------------------
paragraph (h) paragraph (l)(1)
paragraph (i) paragraph (h)
paragraph (j) paragraph (i)
paragraph (k) paragraph (j)
paragraph (l) paragraph (k)
paragraph (m) paragraph (l)(2)
------------------------------------------------------------------------
Also, we have revised certain paragraphs of AD 2012-03-04,
Amendment 39-16945 (77 FR 21397, April 10, 2012), by placing the
required service information into sub-paragraphs in this proposed AD.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD affects 41 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Modification [retained actions from AD 62 work-hours x $85 per $2,210 $7,480 $306,680
2012-03-04, Amendment 39-16945 (77 FR hour = $5,270.
21397, April 10, 2012)].
Modification (additional work) [new 32 work-hours x $85 per 1,100 3,820 156,620
proposed action]. hour = $2,720.
----------------------------------------------------------------------------------------------------------------
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 proposed 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 removing airworthiness directive (AD)
2012-03-04, Amendment 39-16945 (77 FR 21397, April 10, 2012), and
adding the following new AD:
Airbus: Docket No. FAA-2013-1072; Directorate Identifier 2012-NM-
164-AD.
(a) Comments Due Date
We must receive comments by February 28, 2014.
(b) Affected ADs
This AD supersedes AD 2012-03-04, Amendment 39-16945 (77 FR
21397, April 10, 2012).
(c) Applicability
This AD applies to Airbus Model A310-203, -204, -221, -222, -
304, -322, -324, and -325 airplanes, certificated in any category,
all certified models, all serial numbers.
[[Page 2393]]
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Reason
This AD was prompted by reports of new interferences of newly
routed wire bundle 2S. We are issuing this AD to prevent short
circuits leading to arcing, and possible fuel tank explosion.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Modification of Routing Wires With Revised Service
Information
This paragraph restates the modification required by paragraph
(g) of AD 2012-03-04, Amendment 39-16945 (77 FR 21397, April 10,
2012), with revised service information. For all airplanes except
airplanes on which Airbus Service Bulletin A310-28-2148, Revision
02, dated March 9, 2007, has been done (Airbus Modifications 12427
and 12435): Within 4,000 flight hours after September 3, 2004 (the
effective date of AD 2004-15-16, Amendment 39-13750 (69 FR 45578,
July 30, 2004)), modify the routing of wires in the right-hand (RH)
wing by installing cable sleeves. Do the modification as per the
Accomplishment Instructions of the service information specified in
paragraph (g)(1), (g)(2), (g)(3), (g)(4), or (g)(5) of this AD. As
of February 20, 2008 (the effective date of AD 2008-01-05, Amendment
39-15330 (73 FR 2795, January 16, 2008)), only the service
information specified in paragraphs (g)(2), (g)(3), (g)(4), and
(g)(5) of this AD may be used. As of May 15, 2012 (the effective
date of AD 2012-03-04), only the service information specified in
paragraphs (g)(3), (g)(4), and (g)(5) of this AD may be used. As of
the effective date of this AD, only the service bulletin specified
in paragraph (g)(5) of this AD may be used.
(1) Airbus Service Bulletin A310-28-2148, Revision 01, dated
October 29, 2002.
(2) Airbus Service Bulletin A310-28-2148, Revision 02, dated
March 9, 2007.
(3) Airbus Mandatory Service Bulletin A310-28-2148, Revision 05,
dated August 3, 2010.
(4) Airbus Mandatory Service Bulletin A310-28-2148, Revision 06,
dated August 31, 2011.
(5) Airbus Mandatory Service Bulletin A310-28-2148, Revision 07,
dated February 13, 2012.
(h) Retained Modification of Protection Sleeves With Revised Service
Information
This paragraph restates the modification required by paragraph
(i) of AD 2012-03-04, Amendment 39-16945 (77 FR 21397, April 10,
2012), with revised service information. For airplanes on which the
actions specified in Airbus Service Bulletin A310-28-2148, dated
January 23, 2002; or Airbus Service Bulletin A310-28-2148, Revision
01, dated October 29, 2002; have been done before February 20, 2008
(the effective date of AD 2008-01-05, Amendment 39-15330 (73 FR
2795, January 16, 2008)), except for airplanes on which Airbus
Service Bulletin A310-28-2148, Revision 02, dated March 9, 2007, has
been done (Airbus Modifications 12427 and 12435): Within 6,000
flight hours or 30 months after February 20, 2008 (the effective
date of AD 2008-01-05), whichever occurs first, perform further
modification by installing additional protection sleeves in the
outer wing area near the cadensicon sensor and segregating wire
route 2S in the RH pylon area, in accordance with the Accomplishment
Instructions of service information specified in paragraph (h)(1),
(h)(2), (h)(3), or (h)(4) of this AD. As of May 15, 2012 (the
effective date of AD 2012-03-04), only the service information
specified in paragraphs (h)(2), (h)(3), and (h)(4) of this AD may be
used. As of the effective date of this AD, only the service bulletin
specified in paragraph (h)(4) of this AD may be used.
(1) Airbus Service Bulletin A310-28-2148, Revision 02, dated
March 9, 2007.
(2) Airbus Mandatory Service Bulletin A310-28-2148, Revision 05,
dated August 3, 2010.
(3) Airbus Mandatory Service Bulletin A310-28-2148, Revision 06,
dated August 31, 2011.
(4) Airbus Mandatory Service Bulletin A310-28-2148, Revision 07,
dated February 13, 2012.
(i) Retained New Modification/Installation of Wire Routings for Certain
Airplanes With Revised Service Information
This paragraph restates the new modification/installation
required by paragraph (j) of AD 2012-03-04, Amendment 39-16945 (77
FR 21397, April 10, 2012), with revised service information. For
airplanes on which the actions specified in Airbus Service Bulletin
A310-28-2148, Revision 02, dated March 9, 2007, have been
accomplished, and do not have production modification 07633; and on
which Airbus Service Bulletin A310-36-2015 has not been done: Within
6,000 flight hours or 30 months after May 15, 2012 (the effective
date of AD 2012-03-04), whichever occurs first, modify the wire
routings, in accordance with the Accomplishment Instructions of the
service information specified in paragraph (i)(1), (i)(2), or (i)(3)
of this AD. As of the effective date of this AD, only the service
bulletin specified in paragraph (i)(3) of this AD may be used.
(1) Airbus Mandatory Service Bulletin A310-28-2148, Revision 05,
dated August 3, 2010.
(2) Airbus Mandatory Service Bulletin A310-28-2148, Revision 06,
dated August 31, 2011.
(3) Airbus Mandatory Service Bulletin A310-28-2148, Revision 07,
dated February 13, 2012.
(j) Retained New Modification/Installation of Bracket for Certain Other
Airplanes With Revised Service Information
This paragraph restates the new modification/installation
required by paragraph (k) of AD 2012-03-04, Amendment 39-16945 (77
FR 21397, April 10, 2012), with revised service information. For
airplanes on which the actions specified in Airbus Service Bulletin
A310-28-2148, Revision 02, dated March 9, 2007, have been
accomplished, and have production modification 07633; or on which
Airbus Service Bulletin A310-36-2015 has been done: Within 1,000
flight hours after May 15, 2012 (the effective date of AD 2012-03-
04), install a modified bracket, in accordance with paragraph
3.B.(7), ``Additional Work 2,'' of the Accomplishment Instructions
of the service information specified in paragraph (j)(1), (j)(2), or
(j)(3) of this AD. As of the effective date of this AD, only the
service bulletin specified in paragraph (j)(3) of this AD may be
used.
(1) Airbus Mandatory Service Bulletin A310-28-2148, Revision 05,
dated August 3, 2010.
(2) Airbus Mandatory Service Bulletin A310-28-2148, Revision 06,
dated August 31, 2011.
(3) Airbus Mandatory Service Bulletin A310-28-2148, Revision 07,
dated February 13, 2012.
(k) Retained Modification/Installation Provision for Certain Airplanes
This paragraph restates the modification/installation provision
specified in paragraph (l) of AD 2012-03-04, Amendment 39-16945 (77
FR 21397, April 10, 2012). For airplanes on which the actions
specified in Airbus Service Bulletin A310-28-2148, Revision 03,
dated June 2, 2009, have been accomplished; and have modification
07633 done in production; or on which the actions specified in
Airbus Service Bulletin A310-36-2015 have been done; no further
action is required by paragraphs (g) through (j) of this AD.
(l) Retained Credit for Previous Actions
(1) This paragraph restates the credit for previous actions
required by paragraph (h) of AD 2012-03-04, Amendment 39-16945 (77
FR 21397, April 10, 2012). This paragraph provides credit for the
modification of the routing of wires required by paragraph (g) of AD
2012-03-04, if the modification was performed before September 3,
2004 (the effective date of AD 2004-15-16, Amendment 39-13750 (69 FR
45578, July 30, 2004)), using Airbus Service Bulletin A310-28-2148,
dated January 23, 2002.
(2) This paragraph restates the credit for previous actions
required by paragraph (m) of AD 2012-03-04, Amendment 39-16945 (77
FR 21397, April 10, 2012). This paragraph provides credit for
modifications required by paragraphs (g), (i), (j), and (k) of AD
2012-03-04, if the modifications were performed before May 15, 2012
(the effective date of AD 2012-03-04), using Airbus Mandatory
Service Bulletin A310-28-2148, Revision 04, dated April 14, 2010.
(m) New Requirement of This AD: Additional Work 2 and 3
For airplanes on which the actions specified in Airbus Service
Bulletin A310-28-2148, Revision 02, dated March 9, 2007, have been
accomplished, and on which the actions specified in Airbus Service
Bulletin A310-36-2015 have not been done; or have Airbus
Modification 07633 done in production: Within 1,000 flight hours or
12 months after the effective date of this AD, whichever occurs
first, do the modification, in accordance with paragraphs
``Additional Work 2'' and ``Additional Work 3'' of the
[[Page 2394]]
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-28-2148, Revision 07, dated February 13, 2012.
(n) New Requirement of This AD: Additional Work 3
For airplanes on which the actions specified in Airbus Service
Bulletin A310-28-2148, Revision 03, dated June 2, 2009, have been
accomplished, and do not have production modification 07633 or
Airbus Service Bulletin A310-36-2015 has not been done: Within 1,000
flight hours or 12 months after the effective date of this AD,
whichever occurs first, do the modification, in accordance with
paragraph ``Additional Work 3'' of the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A310-28-2148, Revision 07,
dated February 13, 2012.
(o) New Requirement of This AD: Additional Work 1 and 2
For airplanes on which the actions specified in Airbus Service
Bulletin A310-36-2015 have not been accomplished and production
modification 07633 has not been done, and that have done the actions
specified in paragraphs (o)(1) and (o)(2) of this AD: Within 6,000
flight hours or 30 months after the effective date of this AD,
whichever occurs first, do the modification, in accordance with
paragraphs ``Additional Work 1'' and ``Additional Work 2'' of the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-28-2148, Revision 07, dated February 13, 2012.
(1) Modification in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310-28-2148, dated January
23, 2002; or Airbus Service Bulletin A310-28-2148, Revision 01,
dated October 29, 2002.
(2) Further modification by ``Additional Work 3'' of the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-28-2148, Revision 06, dated August 31, 2011.
(p) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227-2125; fax (425) 227-1149. Information may
be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or by the design approval holder (DAH) with a State
of Design Authority's design organization approval). For a repair
method to be approved, the repair approval must specifically refer
to this AD. You are required to ensure the product is airworthy
before it is returned to service.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency Airworthiness Directive 2012-
0188, dated September 19, 2012, 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-
2013-1072.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You may 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 January 7, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-00495 Filed 1-13-14; 8:45 am]
BILLING CODE 4910-13-P
