Airworthiness Directives; Airbus Airplanes, 22364-22367 [2014-08597]
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Federal Register / Vol. 79, No. 77 / Tuesday, April 22, 2014 / Rules and Regulations
821 4504060; fax: +49 821 419641; Internet:
www.ballonbau.de.
(4) You may view this service information
at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Kansas City, Missouri, on April
4, 2014.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2014–08072 Filed 4–21–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–1072; Directorate
Identifier 2012–NM–164–AD; Amendment
39–17828; AD 2014–08–04]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2012–03–
04 for certain Airbus Model A310 series
airplanes. AD 2012–03–04 required for
certain airplanes, modifying the wire
routing and installing additional
protective sleeves. This new AD
continues to require the actions in AD
2012–03–04, and requires additional
work for certain airplanes. 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.
DATES: This AD becomes effective May
27, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 27, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of May 15, 2012 (77 FR
21397, April 10, 2012).
ADDRESSES: You may examine the AD
docket on the Internet at https://
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SUMMARY:
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www.regulations.gov/
#!docketDetail;D=FAA-2013-1072; or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
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 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.
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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012–03–04,
Amendment 39–16945 (77 FR 21397,
April 10, 2012). AD 2012–03–04 applied
to certain Airbus Model A310 series
airplanes. The NPRM published in the
Federal Register on January 14, 2014
(79 FR 2391).
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
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Fmt 4700
Sfmt 4700
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–
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/
#!documentDetail;D=FAA-2013-10720002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (79
FR 2391, January 14, 2014) or on the
determination of the cost to the public.
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Federal Register / Vol. 79, No. 77 / Tuesday, April 22, 2014 / Rules and Regulations
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR 2391,
January 14, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
22365
proposed in the NPRM (79 FR 2391,
January 14, 2014).
Costs of Compliance
We estimate that this AD affects 41
airplanes of U.S. registry.
ESTIMATED COSTS
Parts cost
Cost per
product
Cost on U.S.
operators
Action
Labor cost
Modification [retained actions from AD 2012–
03–04, Amendment 39–16945 (77 FR
21397, April 10, 2012)].
Modification (additional work) [new 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
Authority for This Rulemaking
Examining the AD Docket
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.
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=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
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.
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Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
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:
■
2014–08–04 Airbus: Amendment 39–17828.
Docket No. FAA–2013–1072; Directorate
Identifier 2012–NM–164–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective May 27, 2014.
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Sfmt 4700
(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.
(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
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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.
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(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
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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
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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
Accomplishment Instructions of Airbus
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 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
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 Service Bulletin A310–28–2148,
Revision 06, dated August 31, 2011.
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(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-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer, 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 with a State of Design
Authority’s design organization approval, as
applicable). 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. You may
examine the MCAI in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2013-1072-0002.
(2) Service information identified in this
AD that is not incorporated by reference in
this AD may be obtained at the addresses
specified in paragraphs (r)(5) and (r)(6) of this
AD.
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(r) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on May 27, 2014.
(i) Airbus Service Bulletin A310–28–2148,
Revision 07, dated February 13, 2012.
(ii) Reserved.
(4) The following service information was
approved for IBR on May 15, 2012, (77 FR
21397, April 10, 2012).
(i) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 05, dated August 3,
2010.
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(ii) Airbus Mandatory Service Bulletin
A310–28–2148, Revision 06, dated August
31, 2011.
(5) 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.
(6) 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.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
22367
[Docket No. FAA–2014–0042; Directorate
Identifier 2013–CE–050–AD; Amendment
39–17823; AD 2014–07–09]
of a certain publication listed in the AD
as of May 27, 2014.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0042; or in person at Document
Management Facility, U.S. Department
of Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
For service information identified in
this AD, contact BAE Systems
(Operations) Limited, Customer
Information Department, Prestwick
International Airport, Ayrshire, KA9
2RW, Scotland, United Kingdom;
telephone: +44 1292 675207; fax: +44
1292 675704; email: RApublications@
baesystems.com; Internet: https://
www.baesystems.com/Businesses/
RegionalAircraft/. You may review this
referenced service information at the
FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148.
FOR FURTHER INFORMATION CONTACT:
Taylor Martin, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4138; fax: (816) 329–4090; email:
taylor.martin@faa.gov.
SUPPLEMENTARY INFORMATION:
RIN 2120–AA64
Discussion
Issued in Renton, Washington, on April 4,
2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–08597 Filed 4–21–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; British
Aerospace Regional Aircraft Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for British
Aerospace Regional Aircraft Jetstream
Series 3101 and Jetstream Model 3201
airplanes. This AD results from
mandatory continuing airworthiness
information (MCAI) issued by an
aviation authority of another country to
identify and correct an unsafe condition
on an aviation product. The MCAI
describes the unsafe condition as
inadequate instructions for inspection
for corrosion on the rudder upper hinge
bracket and certain internal wing and
drainage paths. We are issuing this AD
to require actions to address the unsafe
condition on these products.
DATES: This AD is effective May 27,
2014.
The Director of the Federal Register
approved the incorporation by reference
SUMMARY:
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to British Aerospace Regional
Aircraft Jetstream Series 3101 and
Jetstream Model 3201 airplanes. The
NPRM was published in the Federal
Register on January 31, 2014 (79 FR
5323). The NPRM proposed to correct
an unsafe condition for the specified
products and was based on mandatory
continuing airworthiness information
(MCAI) originated by an aviation
authority of another country. The MCAI
states:
Compliance with the inspections in the
Corrosion Prevention and Control Programme
(CPCP) has been identified as a mandatory
action for continued airworthiness and UK
CAA AD 003–04–94 was issued to require
operators to comply with those inspection
instructions.
Since the issuance of that AD, reports have
been received of finding extensive corrosion
on the rudder upper hinge bracket. Although
there is an existing zonal inspection of the
area in the CPCP, it has been concluded that
this is inadequate to identify the corrosion on
this bracket and consequently, a new specific
inspection of the rudder upper hinge bracket,
E:\FR\FM\22APR1.SGM
22APR1
]]>Agencies
[Federal Register Volume 79, Number 77 (Tuesday, April 22, 2014)]
[Rules and Regulations]
[Pages 22364-22367]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-08597]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-1072; Directorate Identifier 2012-NM-164-AD;
Amendment 39-17828; AD 2014-08-04]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2012-03-04 for
certain Airbus Model A310 series airplanes. AD 2012-03-04 required for
certain airplanes, modifying the wire routing and installing additional
protective sleeves. This new AD continues to require the actions in AD
2012-03-04, and requires additional work for certain airplanes. 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.
DATES: This AD becomes effective May 27, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 27,
2014.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 15,
2012 (77 FR 21397, April 10, 2012).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-1072; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
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 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.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012-03-04, Amendment 39-16945 (77 FR 21397,
April 10, 2012). AD 2012-03-04 applied to certain Airbus Model A310
series airplanes. The NPRM published in the Federal Register on January
14, 2014 (79 FR 2391).
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 A310-28-2148 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/#!documentDetail;D=FAA-2013-1072-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 2391, January 14,
2014) or on the determination of the cost to the public.
[[Page 22365]]
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting this AD as proposed except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 2391, January 14, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 2391, January 14, 2014).
Costs of Compliance
We estimate that this AD affects 41 airplanes of U.S. registry.
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
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 regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=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 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2012-03-04, Amendment 39-16945 (77 FR 21397, April 10, 2012), and
adding the following new AD:
2014-08-04 Airbus: Amendment 39-17828. Docket No. FAA-2013-1072;
Directorate Identifier 2012-NM-164-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective May 27,
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.
(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
[[Page 22366]]
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
Accomplishment Instructions of Airbus 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 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 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 Service Bulletin A310-28-2148,
Revision 06, dated August 31, 2011.
[[Page 22367]]
(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 with a State of
Design Authority's design organization approval, as applicable). 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. You may
examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-1072-0002.
(2) Service information identified in this AD that is not
incorporated by reference in this AD may be obtained at the
addresses specified in paragraphs (r)(5) and (r)(6) of this AD.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
May 27, 2014.
(i) Airbus Service Bulletin A310-28-2148, Revision 07, dated
February 13, 2012.
(ii) Reserved.
(4) The following service information was approved for IBR on
May 15, 2012, (77 FR 21397, April 10, 2012).
(i) Airbus Mandatory Service Bulletin A310-28-2148, Revision 05,
dated August 3, 2010.
(ii) Airbus Mandatory Service Bulletin A310-28-2148, Revision
06, dated August 31, 2011.
(5) 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.
(6) 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.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on April 4, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-08597 Filed 4-21-14; 8:45 am]
BILLING CODE 4910-13-P
