Airworthiness Directives; Airbus Airplanes, 19892-19895 [2015-08071]
Download as PDF
<![CDATA[
19892
Federal Register / Vol. 80, No. 71 / Tuesday, April 14, 2015 / Proposed Rules
Issued in Kansas City, Missouri, on April
6, 2015.
Pat Mullen,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–08586 Filed 4–13–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0824; Directorate
Identifier 2013–NM–191–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) 98–20–27,
for all Airbus Model A300 B4–600, B4–
600R, and F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes). AD 98–20–
27 currently requires repetitive
inspections to detect fatigue cracking of
the wing top skin at the front spar joint;
and a follow-on eddy current inspection
and repair, if necessary. Since we issued
AD 98–20–27, we have received reports
of cracking of the wing top skin in an
area not required for inspection by AD
98–20–27. This proposed AD would
reduce the inspection compliance time
and intervals, and extend the inspection
area of the wing top skin at the front
spar joint. We are proposing this AD to
detect and correct fatigue cracking of the
wing top skin at the front spar joint,
which could result in reduced structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by May 29, 2015.
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
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
17:05 Apr 13, 2015
Jkt 235001
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–2015–
0824; 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–2015–0824; Directorate Identifier
2013–NM–191–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 September 16, 1998, we issued AD
98–20–27, Amendment 39–10793 (63
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
FR 50981, September 24, 1998). AD 98–
20–27 requires actions intended to
address an unsafe condition on all
Airbus Model A300 B4–600, B4–600R,
and F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes).
Since we issued AD 98–20–27,
Amendment 39–10793 (63 FR 50981,
September 24, 1998): The European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Union, has
issued EASA Airworthiness Directive
2013–0232R1, dated October 2, 2013
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition. The MCAI states:
During full-scale fatigue testing conducted
in the early 1990’s, cracks were found on the
top skin of the wing between Ribs 1 and 7,
starting at the front spar fastener holes.
This condition, if not detected and
corrected, could adversely affect the
structural integrity of the wing.
Consequently, Airbus issued Service
Bulletin (SB) A300–57–6045 and DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France issued AD 97–374–238 [https://
ad.easa.europa.eu/blob/19973740tb_
superseded.pdf/AD_F-1997-374-238_2] for
A300–600 aeroplanes and AD 1999–008–020
[https://ad.easa.europa.eu/blob/19980080tb_
superseded.pdf/AD_F-1999-008-020_2] for
A300–600ST aeroplanes to require repetitive
detailed inspections of the wing top skin and,
in case of findings, an Eddy Current (EC)
inspection, and, depending on the size of the
cracks, repair.
After those [DGAC] ADs were issued,
further cracks to the wing top skin were
reported by operators, within an area not
covered by the existing [DGAC] ADs. To
address this potential unsafe condition,
Airbus revised SB A300–57–6045 to extend
the area to be inspected.
In addition, a fleet survey and updated
Fatigue and Damage Tolerance analyses were
performed in order to substantiate the second
A300–600 Extended Service Goal (ESG2)
exercise. The results of these analyses have
determined that the inspection thresholds
and intervals must be reduced to allow
timely detection of these cracks and the
accomplishment of applicable corrective
action(s).
As the ESG2 exercise is only applicable to
A300–600 aeroplanes, A300–600ST
aeroplanes are now addressed through new
Airbus SB A300–57–9026.
For the reasons described above, this
[EASA] AD retains the requirements of DGAC
France AD 97–374–238(B) [https://
ad.easa.europa.eu/blob/19973740tb_
superseded.pdf/AD_F-1997-374-238_2]
[which corresponds to FAA AD 98–20–27,
Amendment 39–10793 (63 FR 50981,
September 24, 1998)] and [DGAC] AD 1999–
008–020(B) [https://ad.easa.europa.eu/blob/
19980080tb_superseded.pdf/AD_F-1999-008020_2], which are superseded, but requires
E:\FR\FM\14APP1.SGM
14APP1
Federal Register / Vol. 80, No. 71 / Tuesday, April 14, 2015 / Proposed Rules
those actions, for A300–600 aeroplanes only,
within reduced thresholds and intervals.
*
*
*
*
*
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0824.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A300–57–6045, Revision 10, dated
November 13, 2013. The service
information describes inspection
procedures for fatigue cracking of the
wing top skin at the front spar joint
between ribs 1 and 7. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI. This service
information is reasonably available; see
ADDRESSES for ways to access this
service information.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed AD
and the MCAI or Service Information
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Unlike the procedures described in
the MCAI and Airbus Service Bulletin
A300–57–6045, Revision 10, dated
November 13, 2013, this proposed AD
would not permit further flight if cracks
are detected in the wing top skin at the
front spar joint. We have determined
that, because of the safety implications
and consequences associated with that
cracking, any cracked wing top skin at
the front spar joint must be repaired
before further flight. This difference has
been coordinated with the EASA.
Costs of Compliance
We estimate that this proposed AD
affects 130 airplanes of U.S. registry.
The actions that are required by AD
98–20–27, Amendment 39–10793 (63
FR 50981, September 24, 1998), and
retained in this proposed AD take about
2 work-hours per product, at an average
labor rate of $85 per work-hour. Based
on these figures, the estimated cost of
VerDate Sep<11>2014
17:05 Apr 13, 2015
Jkt 235001
the actions that are required by AD 98–
20–27 is $170 per product.
We also estimate that it would take
about 2 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $22,100, or $170 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
19893
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
98–20–27, Amendment 39–10793 (63
FR 50981, September 24, 1998), and
adding the following new AD:
■
Airbus: Docket No. FAA–2015–0824;
Directorate Identifier 2013–NM–191–AD.
(a) Comments Due Date
We must receive comments by May 29,
2015.
(b) Affected ADs
This AD replaces AD 98–20–27,
Amendment 39–10793 (63 FR 50981,
September 24, 1998).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes.
(2) Airbus Model A300 B4–605R and B4–
622R airplanes.
(3) Airbus Model A300 F4–605R and F4–
622R airplanes.
(4) Airbus Model A300 C4–605R Variant F
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by reports of
cracking of wing top skin in an area not
required for inspection by AD 98–20–27,
Amendment 39–10793 (63 FR 50981,
September 24, 1998). We are issuing this AD
to detect and correct fatigue cracking of the
wing top skin at the front spar joint, which
could result in reduced structural integrity of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Repetitive Inspections, With
Revised Service Information
This paragraph restates the requirements of
paragraph (a) of AD 98–20–27, Amendment
E:\FR\FM\14APP1.SGM
14APP1
19894
Federal Register / Vol. 80, No. 71 / Tuesday, April 14, 2015 / Proposed Rules
39–10793 (63 FR 50981, September 24, 1998),
with revised service information. Prior to the
accumulation of 22,000 total flight cycles, or
within 2,000 flight cycles after October 29,
1998 (the effective date of AD 98–20–27),
whichever occurs later: Perform a detailed
visual inspection to detect fatigue cracking of
the wing top skin at the front spar joint, in
accordance with Airbus Service Bulletin
A300–57–6045, Revision 1, dated August 3,
1994, including Appendix 1, Revision 1,
dated August 3, 1994; Airbus Service
Bulletin A300–57–6045, Revision 02, dated
April 21, 1998, including Appendix 1,
Revision 02, dated April 21, 1998; or Airbus
Service Bulletin A300–57–6045, Revision 10,
dated November 13, 2013. Repeat the
detailed visual inspection thereafter at
intervals not to exceed 8,000 flight cycles.
(h) Retained Inspection and Repair, With
Revised Service Information
This paragraph restates the requirements of
paragraph (b) of AD 98–20–27, Amendment
39–10793 (63 FR 50981, September 24, 1998),
with revised service information. If any
cracking is suspected or detected during any
inspection required by paragraph (g) of this
AD: Prior to further flight, perform an eddy
current inspection to confirm the findings of
the visual inspection, in accordance with
Airbus Service Bulletin A300–57–6045,
Revision 01, dated August 3, 1994, including
Appendix 1, Revision 01, dated August 3,
1994; Airbus Service Bulletin A300–57–6045,
Revision 02, dated April 21, 1998, including
Appendix 1, Revision 02, dated April 21,
1998; or Airbus Service Bulletin A300–57–
6045, Revision 10, dated November 13, 2013.
If any cracking is detected during any eddy
current inspection, prior to further flight,
repair using a method approved by the
Manager, International Branch, ANM–116,
FAA, Transport Airplane Directorate; or the
´ ´
Direction Generale de l’Aviation Civile (or its
delegated agent).
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(i) New Requirement of This AD: Initial
Inspection
At the applicable time specified in
paragraph (i)(1) or (i)(2) of this AD: Do a
detailed inspection of the wing top skin
between ribs one and seven for cracking, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6045, Revision 10, dated November 13,
2013. Accomplishment of the initial
inspection required by this paragraph
terminates the requirements of paragraph (g)
of this AD.
(1) For Model A300 B4–601, B4–603, B4–
620, and B4–622 airplanes, Model A300 B4–
605R and B4–622R airplanes, and Model
A300 C4–605R Variant F airplanes: At the
later of the times specified in paragraphs
(i)(1)(i) and (i)(1)(ii) of this AD.
(i) Before the accumulation of 17,100 total
flight cycles or 38,400 total flight hours,
whichever occurs first.
(ii) Within 1,000 flight cycles or 2,200
flight hours, whichever occurs first after the
effective date of this AD.
(2) For Model A300 F4–605R and F4–622R
airplanes: At the later of the times specified
in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
VerDate Sep<11>2014
17:05 Apr 13, 2015
Jkt 235001
(i) Before the accumulation of 22,000 total
flight cycles or 49,500 total flight hours,
whichever occurs first.
(ii) Within 1,300 flight cycles or 2,800
flight hours, whichever occurs first after the
effective date of this AD.
(j) New Requirement of This AD: Repetitive
Inspections
Repeat the inspection required by
paragraph (i) of this AD thereafter at the
applicable time and intervals specified in
paragraphs (j)(1) and (j)(2) of this AD.
(1) For Model A300 B4–601, B4–603, B4–
620, and B4–622 airplanes, Model A300 B4–
605R and B4–622R airplanes, and Model
A300 C4–605R Variant F airplanes: At the
applicable time specified in paragraph
(j)(1)(i) or (j)(1)(ii) of this AD.
(i) For airplanes that have an average flight
time (AFT) that is equal to or more than one
and one-half hours: At intervals not to exceed
5,100 flight cycles or 11,000 flight hours,
whichever occurs first.
(ii) For airplanes that have an AFT that is
less than one and one-half hours: At intervals
not to exceed 5,500 flight cycles or 8,300
flight hours, whichever occurs first.
(2) For Model A300 F4–605R and F4–622R
airplanes: At the applicable time specified in
paragraph (j)(2)(i) or (j)(2)(ii) of this AD.
(i) For airplanes that have an AFT that is
equal to or more than one and one-half hours:
At intervals not to exceed 6,500 flight cycles
or 14,100 flight hours, whichever occurs first.
(ii) For airplanes that have an AFT that is
less than one and one-half hours: At intervals
not to exceed 7,000 flight cycles or 10,600
flight hours, whichever occurs first.
(k) New Requirement of This AD: Repair of
Cracking
(1) If any crack in the top skin in the area
forward of the front spar attachment is found
during any inspection required by paragraph
(i) of this AD: Before further flight, repair
using a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA.
(2) If any crack or sign of a crack is found
in the top skin at or aft of the spar attachment
during any inspection required by paragraph
(i) of this AD: Before further flight, do an
eddy current inspection of the cracks or of
the signs of cracking to confirm the findings
of the detailed inspection, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A300–57–6045,
Revision 10, dated November 13, 2013. If
there are any cracks at or aft of the spar
attachment, before further flight, repair using
a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; EASA; or
Airbus’s EASA DOA.
(l) No Terminating Action
Accomplishment of any repair required by
paragraph (k) this AD does not constitute
terminating action for the repetitive
inspections required by paragraph (j) of this
AD.
(m) No Reporting Required
Although Airbus Service Bulletin A300–
57–6045, Revision 10, dated November 13,
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
2013, specifies to submit certain information
to the manufacturer, this AD does not
include that requirement.
(n) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (i), (j) and (k) of this
AD, if those actions were performed before
the effective date of this AD using the Airbus
service bulletins specified in paragraphs
(n)(1) through (n)(10) of this AD, which are
not incorporated by reference in this AD.
(1) Airbus Service Bulletin A300–57–6045,
dated March 18, 1993.
(2) Airbus Service Bulletin A300–57–6045,
Revision 01, dated August 3, 1994.
(3) Airbus Service Bulletin A300–57–6045,
Revision 02, dated April 21, 1998.
(4) Airbus Service Bulletin A300–57–6045,
Revision 03, dated October 25, 1999.
(5) Airbus Service Bulletin A300–57–6045,
Revision 04, dated January 13, 2002.
(6) Airbus Service Bulletin A300–57–6045,
Revision 05, dated June 13, 2003.
(7) Airbus Service Bulletin A300–57–6045,
Revision 06, dated January 13, 2005.
(8) Airbus Service Bulletin A300–57–6045,
Revision 07, dated August 14, 2008.
(9) Airbus Service Bulletin A300–57–6045,
Revision 08, dated June 6, 2011.
(10) Airbus Service Bulletin A300–57–
6045, Revision 09, dated May 21, 2013.
(o) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, 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.
(i) 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.
(ii) AMOCs approved previously for AD
98–20–27, Amendment 39–10793 (63 FR
50981, September 24, 1998), are approved as
AMOCs for the corresponding provisions of
this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
E:\FR\FM\14APP1.SGM
14APP1
Federal Register / Vol. 80, No. 71 / Tuesday, April 14, 2015 / Proposed Rules
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0232R1, dated
October 2, 2013, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2015–0824.
(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.
notice as posted within Docket No.
TTB–2015–0007 at Regulations.gov, the
Federal e-rulemaking portal);
• U.S. Mail: Director, Regulations and
Rulings Division, Alcohol and Tobacco
Tax and Trade Bureau, 1310 G Street
NW., Box 12, Washington, DC 20005; or
• Hand delivery/courier in lieu of
mail: Alcohol and Tobacco Tax and
Trade Bureau, 1310 G Street NW., Suite
200–E, Washington, DC 20005.
See the PUBLIC PARTICIPATION section
of this notice for specific instructions
and requirements for submitting
comments, and for information on how
to request a public hearing or view or
obtain copies of the petition and
supporting materials.
Issued in Renton, Washington, on March
27, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
FOR FURTHER INFORMATION CONTACT:
[FR Doc. 2015–08071 Filed 4–13–15; 8:45 am]
Karen A. Thornton, Regulations and
Rulings Division, Alcohol and Tobacco
Tax and Trade Bureau, 1310 G St. NW.,
Box 12, Washington, DC 20005; phone
202–453–1039, ext. 175.
BILLING CODE 4910–13–P
SUPPLEMENTARY INFORMATION:
Background on Viticultural Areas
DEPARTMENT OF THE TREASURY
TTB Authority
Alcohol and Tobacco Tax and Trade
Bureau
Section 105(e) of the Federal Alcohol
Administration Act (FAA Act), 27
U.S.C. 205(e), authorizes the Secretary
of the Treasury to prescribe regulations
for the labeling of wine, distilled spirits,
and malt beverages. The FAA Act
provides that these regulations should,
among other things, prohibit consumer
deception and the use of misleading
statements on labels, and ensure that
labels provide the consumer with
adequate information as to the identity
and quality of the product. The Alcohol
and Tobacco Tax and Trade Bureau
(TTB) administers the FAA Act
pursuant to section 1111(d) of the
Homeland Security Act of 2002,
codified at 6 U.S.C. 531(d). The
Secretary has delegated various
authorities through Treasury
Department Order 120–01 (Revised),
dated December 10, 2013, to the TTB
Administrator to perform the functions
and duties in the administration and
enforcement of this law.
Part 4 of the TTB regulations (27 CFR
part 4) authorizes TTB to establish
definitive viticultural areas and regulate
the use of their names as appellations of
origin on wine labels and in wine
advertisements. Part 9 of the TTB
regulations (27 CFR part 9) sets forth
standards for the preparation and
submission of petitions for the
establishment or modification of
American viticultural areas (AVAs) and
lists the approved AVAs.
27 CFR Part 9
[Docket No. TTB–2015–0007; Notice No.
151]
RIN 1513–AC17
Proposed Establishment of the
Lamorinda Viticultural Area
Alcohol and Tobacco Tax and
Trade Bureau, Treasury.
ACTION: Notice of proposed rulemaking.
AGENCY:
The Alcohol and Tobacco Tax
and Trade Bureau (TTB) proposes to
establish the approximately 29,369-acre
‘‘Lamorinda’’ viticultural area in Contra
Costa County, California. The proposed
viticultural area lies entirely within the
larger San Francisco Bay viticultural
area and the multicounty Central Coast
viticultural area. TTB designates
viticultural areas to allow vintners to
better describe the origin of their wines
and to allow consumers to better
identify wines they may purchase. TTB
invites comments on this proposed
addition to its regulations.
DATES: Comments must be received by
June 15, 2015.
ADDRESSES: Please send your comments
on this notice to one of the following
addresses:
• Internet: https://www.regulations.gov
(via the online comment form for this
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
17:05 Apr 13, 2015
Jkt 235001
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
19895
Definition
Section 4.25(e)(1)(i) of the TTB
regulations (27 CFR 4.25(e)(1)(i)) defines
a viticultural area for American wine as
a delimited grape-growing region having
distinguishing features, as described in
part 9 of the regulations, and a name
and a delineated boundary, as
established in part 9 of the regulations.
These designations allow vintners and
consumers to attribute a given quality,
reputation, or other characteristic of a
wine made from grapes grown in an area
to the wine’s geographic origin. The
establishment of AVAs allows vintners
to describe more accurately the origin of
their wines to consumers and helps
consumers to identify wines they may
purchase. Establishment of an AVA is
neither an approval nor an endorsement
by TTB of the wine produced in that
area.
Requirements
Section 4.25(e)(2) of the TTB
regulations (27 CFR 4.25(e)(2)) outlines
the procedure for proposing an AVA
and provides that any interested party
may petition TTB to establish a grapegrowing region as an AVA. Section 9.12
of the TTB regulations (27 CFR 9.12)
prescribes the standards for petitions for
the establishment or modification of
AVAs. Petitions to establish an AVA
must include the following:
• Evidence that the area within the
proposed AVA boundary is nationally
or locally known by the AVA name
specified in the petition;
• An explanation of the basis for
defining the boundary of the proposed
AVA;
• A narrative description of the
features of the proposed AVA affecting
viticulture, such as climate, geology,
soils, physical features, and elevation,
that make the proposed AVA distinctive
and distinguish it from adjacent areas
outside the proposed AVA boundary;
• The appropriate United States
Geological Survey (USGS) map(s)
showing the location of the proposed
AVA, with the boundary of the
proposed AVA clearly drawn thereon;
and
• A detailed narrative description of
the proposed AVA boundary based on
USGS map markings.
Lamorinda Petition
TTB received a petition from Patrick
L. Shabram, on behalf of the Lamorinda
Wine Growers Association, proposing
the establishment of the ‘‘Lamorinda’’
AVA. The proposed Lamorinda AVA is
located in Contra Costa County,
California, and contains the cities of
Lafayette, Moraga, and Orinda. The
E:\FR\FM\14APP1.SGM
14APP1
]]>Agencies
[Federal Register Volume 80, Number 71 (Tuesday, April 14, 2015)]
[Proposed Rules]
[Pages 19892-19895]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-08071]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0824; Directorate Identifier 2013-NM-191-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) 98-20-27,
for all Airbus Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4-605R Variant F airplanes (collectively
called Model A300-600 series airplanes). AD 98-20-27 currently requires
repetitive inspections to detect fatigue cracking of the wing top skin
at the front spar joint; and a follow-on eddy current inspection and
repair, if necessary. Since we issued AD 98-20-27, we have received
reports of cracking of the wing top skin in an area not required for
inspection by AD 98-20-27. This proposed AD would reduce the inspection
compliance time and intervals, and extend the inspection area of the
wing top skin at the front spar joint. We are proposing this AD to
detect and correct fatigue cracking of the wing top skin at the front
spar joint, which could result in reduced structural integrity of the
airplane.
DATES: We must receive comments on this proposed AD by May 29, 2015.
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-2015-
0824; 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-2015-0824;
Directorate Identifier 2013-NM-191-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 September 16, 1998, we issued AD 98-20-27, Amendment 39-10793
(63 FR 50981, September 24, 1998). AD 98-20-27 requires actions
intended to address an unsafe condition on all Airbus Model A300 B4-
600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R
Variant F airplanes (collectively called Model A300-600 series
airplanes).
Since we issued AD 98-20-27, Amendment 39-10793 (63 FR 50981,
September 24, 1998): The European Aviation Safety Agency (EASA), which
is the Technical Agent for the Member States of the European Union, has
issued EASA Airworthiness Directive 2013-0232R1, dated October 2, 2013
(referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition. The MCAI
states:
During full-scale fatigue testing conducted in the early 1990's,
cracks were found on the top skin of the wing between Ribs 1 and 7,
starting at the front spar fastener holes.
This condition, if not detected and corrected, could adversely
affect the structural integrity of the wing.
Consequently, Airbus issued Service Bulletin (SB) A300-57-6045
and DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France issued AD 97-374-238 [https://ad.easa.europa.eu/blob/19973740tb_superseded.pdf/AD_F-1997-374-238_2] for A300-600
aeroplanes and AD 1999-008-020 [https://ad.easa.europa.eu/blob/19980080tb_superseded.pdf/AD_F-1999-008-020_2] for A300-600ST
aeroplanes to require repetitive detailed inspections of the wing
top skin and, in case of findings, an Eddy Current (EC) inspection,
and, depending on the size of the cracks, repair.
After those [DGAC] ADs were issued, further cracks to the wing
top skin were reported by operators, within an area not covered by
the existing [DGAC] ADs. To address this potential unsafe condition,
Airbus revised SB A300-57-6045 to extend the area to be inspected.
In addition, a fleet survey and updated Fatigue and Damage
Tolerance analyses were performed in order to substantiate the
second A300-600 Extended Service Goal (ESG2) exercise. The results
of these analyses have determined that the inspection thresholds and
intervals must be reduced to allow timely detection of these cracks
and the accomplishment of applicable corrective action(s).
As the ESG2 exercise is only applicable to A300-600 aeroplanes,
A300-600ST aeroplanes are now addressed through new Airbus SB A300-
57-9026.
For the reasons described above, this [EASA] AD retains the
requirements of DGAC France AD 97-374-238(B) [https://ad.easa.europa.eu/blob/19973740tb_superseded.pdf/AD_F-1997-374-238_2] [which corresponds to FAA AD 98-20-27, Amendment 39-10793 (63
FR 50981, September 24, 1998)] and [DGAC] AD 1999-008-020(B) [https://ad.easa.europa.eu/blob/19980080tb_superseded.pdf/AD_F-1999-008-020_2], which are superseded, but requires
[[Page 19893]]
those actions, for A300-600 aeroplanes only, within reduced
thresholds and intervals.
* * * * *
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0824.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A300-57-6045, Revision 10, dated
November 13, 2013. The service information describes inspection
procedures for fatigue cracking of the wing top skin at the front spar
joint between ribs 1 and 7. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI. This service information is reasonably available; see
ADDRESSES for ways to access this service information.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This Proposed AD and the MCAI or Service
Information
Unlike the procedures described in the MCAI and Airbus Service
Bulletin A300-57-6045, Revision 10, dated November 13, 2013, this
proposed AD would not permit further flight if cracks are detected in
the wing top skin at the front spar joint. We have determined that,
because of the safety implications and consequences associated with
that cracking, any cracked wing top skin at the front spar joint must
be repaired before further flight. This difference has been coordinated
with the EASA.
Costs of Compliance
We estimate that this proposed AD affects 130 airplanes of U.S.
registry.
The actions that are required by AD 98-20-27, Amendment 39-10793
(63 FR 50981, September 24, 1998), and retained in this proposed AD
take about 2 work-hours per product, at an average labor rate of $85
per work-hour. Based on these figures, the estimated cost of the
actions that are required by AD 98-20-27 is $170 per product.
We also estimate that it would take about 2 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $22,100, or $170
per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), and
adding the following new AD:
Airbus: Docket No. FAA-2015-0824; Directorate Identifier 2013-NM-
191-AD.
(a) Comments Due Date
We must receive comments by May 29, 2015.
(b) Affected ADs
This AD replaces AD 98-20-27, Amendment 39-10793 (63 FR 50981,
September 24, 1998).
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes.
(2) Airbus Model A300 B4-605R and B4-622R airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
(4) Airbus Model A300 C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of cracking of wing top skin in
an area not required for inspection by AD 98-20-27, Amendment 39-
10793 (63 FR 50981, September 24, 1998). We are issuing this AD to
detect and correct fatigue cracking of the wing top skin at the
front spar joint, which could result in reduced structural integrity
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Repetitive Inspections, With Revised Service Information
This paragraph restates the requirements of paragraph (a) of AD
98-20-27, Amendment
[[Page 19894]]
39-10793 (63 FR 50981, September 24, 1998), with revised service
information. Prior to the accumulation of 22,000 total flight
cycles, or within 2,000 flight cycles after October 29, 1998 (the
effective date of AD 98-20-27), whichever occurs later: Perform a
detailed visual inspection to detect fatigue cracking of the wing
top skin at the front spar joint, in accordance with Airbus Service
Bulletin A300-57-6045, Revision 1, dated August 3, 1994, including
Appendix 1, Revision 1, dated August 3, 1994; Airbus Service
Bulletin A300-57-6045, Revision 02, dated April 21, 1998, including
Appendix 1, Revision 02, dated April 21, 1998; or Airbus Service
Bulletin A300-57-6045, Revision 10, dated November 13, 2013. Repeat
the detailed visual inspection thereafter at intervals not to exceed
8,000 flight cycles.
(h) Retained Inspection and Repair, With Revised Service Information
This paragraph restates the requirements of paragraph (b) of AD
98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), with
revised service information. If any cracking is suspected or
detected during any inspection required by paragraph (g) of this AD:
Prior to further flight, perform an eddy current inspection to
confirm the findings of the visual inspection, in accordance with
Airbus Service Bulletin A300-57-6045, Revision 01, dated August 3,
1994, including Appendix 1, Revision 01, dated August 3, 1994;
Airbus Service Bulletin A300-57-6045, Revision 02, dated April 21,
1998, including Appendix 1, Revision 02, dated April 21, 1998; or
Airbus Service Bulletin A300-57-6045, Revision 10, dated November
13, 2013. If any cracking is detected during any eddy current
inspection, prior to further flight, repair using a method approved
by the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate; or the Direction G[eacute]n[eacute]rale de
l'Aviation Civile (or its delegated agent).
(i) New Requirement of This AD: Initial Inspection
At the applicable time specified in paragraph (i)(1) or (i)(2)
of this AD: Do a detailed inspection of the wing top skin between
ribs one and seven for cracking, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6045,
Revision 10, dated November 13, 2013. Accomplishment of the initial
inspection required by this paragraph terminates the requirements of
paragraph (g) of this AD.
(1) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes,
Model A300 B4-605R and B4-622R airplanes, and Model A300 C4-605R
Variant F airplanes: At the later of the times specified in
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
(i) Before the accumulation of 17,100 total flight cycles or
38,400 total flight hours, whichever occurs first.
(ii) Within 1,000 flight cycles or 2,200 flight hours, whichever
occurs first after the effective date of this AD.
(2) For Model A300 F4-605R and F4-622R airplanes: At the later
of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of
this AD.
(i) Before the accumulation of 22,000 total flight cycles or
49,500 total flight hours, whichever occurs first.
(ii) Within 1,300 flight cycles or 2,800 flight hours, whichever
occurs first after the effective date of this AD.
(j) New Requirement of This AD: Repetitive Inspections
Repeat the inspection required by paragraph (i) of this AD
thereafter at the applicable time and intervals specified in
paragraphs (j)(1) and (j)(2) of this AD.
(1) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes,
Model A300 B4-605R and B4-622R airplanes, and Model A300 C4-605R
Variant F airplanes: At the applicable time specified in paragraph
(j)(1)(i) or (j)(1)(ii) of this AD.
(i) For airplanes that have an average flight time (AFT) that is
equal to or more than one and one-half hours: At intervals not to
exceed 5,100 flight cycles or 11,000 flight hours, whichever occurs
first.
(ii) For airplanes that have an AFT that is less than one and
one-half hours: At intervals not to exceed 5,500 flight cycles or
8,300 flight hours, whichever occurs first.
(2) For Model A300 F4-605R and F4-622R airplanes: At the
applicable time specified in paragraph (j)(2)(i) or (j)(2)(ii) of
this AD.
(i) For airplanes that have an AFT that is equal to or more than
one and one-half hours: At intervals not to exceed 6,500 flight
cycles or 14,100 flight hours, whichever occurs first.
(ii) For airplanes that have an AFT that is less than one and
one-half hours: At intervals not to exceed 7,000 flight cycles or
10,600 flight hours, whichever occurs first.
(k) New Requirement of This AD: Repair of Cracking
(1) If any crack in the top skin in the area forward of the
front spar attachment is found during any inspection required by
paragraph (i) of this AD: Before further flight, repair using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(2) If any crack or sign of a crack is found in the top skin at
or aft of the spar attachment during any inspection required by
paragraph (i) of this AD: Before further flight, do an eddy current
inspection of the cracks or of the signs of cracking to confirm the
findings of the detailed inspection, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6045,
Revision 10, dated November 13, 2013. If there are any cracks at or
aft of the spar attachment, before further flight, repair using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; EASA; or Airbus's EASA DOA.
(l) No Terminating Action
Accomplishment of any repair required by paragraph (k) this AD
does not constitute terminating action for the repetitive
inspections required by paragraph (j) of this AD.
(m) No Reporting Required
Although Airbus Service Bulletin A300-57-6045, Revision 10,
dated November 13, 2013, specifies to submit certain information to
the manufacturer, this AD does not include that requirement.
(n) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (i), (j) and (k) of this AD, if those actions were
performed before the effective date of this AD using the Airbus
service bulletins specified in paragraphs (n)(1) through (n)(10) of
this AD, which are not incorporated by reference in this AD.
(1) Airbus Service Bulletin A300-57-6045, dated March 18, 1993.
(2) Airbus Service Bulletin A300-57-6045, Revision 01, dated
August 3, 1994.
(3) Airbus Service Bulletin A300-57-6045, Revision 02, dated
April 21, 1998.
(4) Airbus Service Bulletin A300-57-6045, Revision 03, dated
October 25, 1999.
(5) Airbus Service Bulletin A300-57-6045, Revision 04, dated
January 13, 2002.
(6) Airbus Service Bulletin A300-57-6045, Revision 05, dated
June 13, 2003.
(7) Airbus Service Bulletin A300-57-6045, Revision 06, dated
January 13, 2005.
(8) Airbus Service Bulletin A300-57-6045, Revision 07, dated
August 14, 2008.
(9) Airbus Service Bulletin A300-57-6045, Revision 08, dated
June 6, 2011.
(10) Airbus Service Bulletin A300-57-6045, Revision 09, dated
May 21, 2013.
(o) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, 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.
(i) 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.
(ii) AMOCs approved previously for AD 98-20-27, Amendment 39-
10793 (63 FR 50981, September 24, 1998), are approved as AMOCs for
the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
[[Page 19895]]
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0232R1, dated October 2,
2013, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2015-0824.
(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 March 27, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-08071 Filed 4-13-15; 8:45 am]
BILLING CODE 4910-13-P
