Airworthiness Directives; Airbus Airplanes, 17007-17010 [2015-07281]
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Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Amend § 39.13 by adding the
following new airworthiness directive
(AD):
■
Gulfstream Aerospace Corporation: Docket
No. FAA–2015–0677; Directorate
Identifier 2013–NM–244–AD.
(a) Comments Due Date
We must receive comments by May 15,
2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Gulfstream
Aerospace Corporation Model GVI airplanes,
certificated in any category.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(d) Subject
Air Transport Association (ATA) of
America Code 36, Pneumatic.
(e) Unsafe Condition
This AD was prompted by reports of
corrosion on in-service air non-return valves.
We are issuing this AD to ensure the
flightcrew is provided with procedures to
mitigate the risks associated with failure of
the high pressure (HP) Stage 5 air non-return
valve. Failure of the HP Stage 5 air nonreturn valve in the open position could result
in engine instability and uncommanded inflight shutdown.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Revision of the Airplane Flight Manual
(AFM)
Within 30 days after the effective date of
this AD: Revise the Emergency Procedures
section of the AFM by inserting Section 04–
08–20, Normal Airstart-Automatic; Section
04–08–30, Manual Airstart-Starter Assist; and
Section 04–08–40, Manual AirstartWindmilling; of Chapter 04, Emergency
Procedures; of the Gulfstream GVI (G650)
AFM, Document Number GAC–AC–G650–
OPS–0001, Revision 5, dated August 12,
2013.
(h) Revision of Maintenance or Inspection
Program
Within 30 days after the effective date of
this AD: Revise the airplane maintenance
manual or inspection program, as applicable,
by incorporating the requirement for the HP
Stage 5 air non-return valve from Section 05–
10–10, Airworthiness Limitations, of Chapter
05, Time Limits/Maintenance Checks, of the
Gulfstream GVI (G650) Maintenance Manual
(MM), Revision 4, dated September 30, 2013.
The initial compliance time for replacement
of the HP Stage 5 air non-return valve is at
the applicable time specified in Section 05–
10–10, Airworthiness Limitations, of Chapter
05, Time Limits/Maintenance Checks, of the
Gulfstream GVI (G650) MM, Revision 4,
dated September 30, 2013, or within 30 days
after the effective date of this AD, whichever
occurs later.
(i) No Alternative Actions or Intervals
After the maintenance or inspection
program has been revised, as required by
paragraph (h) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are
approved as an alternative method of
compliance in accordance with the
procedures specified in paragraph (j) of this
AD.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Atlanta Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (k)(1) of this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(k) Related Information
(1) For more information about this AD,
contact Eric Potter, Aerospace Engineer,
Propulsion and Services Branch, ACE–118A,
FAA, Atlanta ACO, 1701 Columbia Avenue,
College Park, GA 30337; phone: 404–474–
PO 00000
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17007
5583; fax: 404–474–5606; email: eric.potter@
faa.gov.
(2) For service information identified in
this AD, contact Gulfstream Aerospace
Corporation, Technical Publications Dept.,
P.O. Box 2206, Savannah, GA 31402–2206;
telephone 800–810–4853; fax 912–965–3520;
email pubs@gulfstream.com; Internet https://
www.gulfstream.com/product_support/
technical_pubs/pubs/index.htm. 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
19, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–07301 Filed 3–30–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0678; Directorate
Identifier 2013–NM–207–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) 2013–13–
04, for certain Airbus Model A318,
A319, A320, and A321 series airplanes.
AD 2013–13–04 currently requires
installing a power interruption
protection circuit for the landing gear
control interface unit (LGCIU). Since we
issued AD 2013–13–04, we have
determined that additional work is
necessary to adequately address the
identified unsafe condition. This
proposed AD would require a new
modification of any previously modified
LGCIU. This proposed AD would also
require revising the maintenance or
inspection program to reduce a certain
functional check interval. This proposed
AD also adds airplanes to the
applicability. We are proposing this AD
to prevent untimely unlocking and/or
retraction of the nose landing gear
(NLG), which, while on the ground,
could result in injury to ground
personnel and damage to the airplane.
DATES: We must receive comments on
this proposed AD by May 15, 2015.
ADDRESSES: You may send comments by
any of the following methods:
SUMMARY:
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Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules
• 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 AD, contact Airbus, Airworthiness
Office—EAS, 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.airwortheas@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–
0678; 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–0678; Directorate Identifier
2013–NM–207–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
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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 June 14, 2013, we issued AD
2013–13–04, Amendment 39–17492 (78
FR 41286, July 10, 2013). AD 2013–13–
04 requires actions intended to address
an unsafe condition on certain Airbus
Model A318, A319, A320, and A321
series airplanes. Since we issued AD
2013–13–04, Amendment 39–17492 (78
FR 41286, July 10, 2013), the European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Community, has
issued EASA Airworthiness Directive
2013–0202, dated September 5, 2013
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for Airbus Model A318–111,
–112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115,
–131, –132, and –133 airplanes; Model
A320–211, –212, –214, –231, –232, and
–233 airplanes; and Model A321–111,
–112, –131, –211, –212, –213, –231, and
–232 airplanes. The MCAI states:
After a push back from the gate, an A320
aeroplane was preparing to initiate taxi,
when an uncommanded nose landing gear
(NLG) retraction occurred, causing the nose
of the aeroplane to hit the ground.
Investigations revealed that the retraction
was caused by a combination of a power
interruption to Landing Gear Control and
Interface Units (LGCIU) and an internal
hydraulic leak through the landing gear (LG)
selector valve 40GA.
Deeper investigations have revealed that
LGCIU power interruption appears during
engine start at each flight. Even though no
incident has been reported in service, it has
been determined that a non-compliance to
the safety objective exists when combined
with a dormant single failure of the selector
valve seal leaking.
This condition, if not corrected, could lead
to further incidents of untimely unlocking
and/or retraction of the NLG which, while on
the ground, could result in injury to ground
personnel and damage to the aeroplane.
To address the possible hydraulic leak of
the LG selector valve, EASA issued AD 2007–
0065 [https://ad.easa.europa.eu/blob/easa_
ad_2007_0065.pdf/AD_2007-0065] currently
at Revision 2.
To address the risk of untimely unlocking
and/or retraction of the NLG, EASA issued
AD 2011–0202 [https://ad.easa.europa.eu/
blob/easa_ad_2011_0202.pdf/AD_2011-0202]
to require installation of a power interruption
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protection circuit to the LGCIU and
accomplishment of associated modifications.
Since that [EASA] AD was issued, it has
been discovered that additional work is
necessary to adequately correct this unsafe
condition and consequently, Airbus issued
Service Bulletin (SB) A320–32–1346 to
Revision 05. An update of the maintenance
programme is required as well, following the
required modification.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2011–0202, which is superseded, and
requires certain additional actions, as defined
in the revised Airbus SB, as applicable to
aeroplane model, and an update of the
approved maintenance programme.
The additional actions include a new
modification of any previously modified
LGCIU, and reducing a certain
functional check interval. This proposed
AD also adds airplanes on which Airbus
modification 37866 has been embodied
in production to the applicability. 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–
0678.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–32–1346, Revision 05, dated
January 13, 2012. The service
information describes procedures for
modifying the LGCIU. 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 these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 851 airplanes of U.S. registry.
The actions required by AD 2013–13–
04, Amendment 39–17492 (78 FR
41286, July 10, 2013), take about 48
work-hours per product, at an average
labor rate of $85 per work-hour.
Required parts will cost about $8,220
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Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules
per product. Based on these figures, the
estimated cost of the actions that are
required by AD 2013–13–04 is $12,300
per product.
We estimate that it would take about
46 work-hours per product to comply
with the new modification in this
proposed AD. The average labor rate is
$85 per work-hour. Required parts
would cost about $9,650 per product.
Based on these figures, we estimate the
cost of the new modification on U.S.
operators to be $11,539,560 or $13,560
per product.
We estimate that it would take about
1 work-hour per product to revise the
maintenance or inspection program in
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
revising the maintenance program on
U.S. operators to be $72,335 or $85 per
product.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
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
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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
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)
2013–13–04, Amendment 39–17492 (78
FR 41286, July 10, 2013), and adding the
following new AD:
■
Airbus: Docket No. FAA–2015–0678;
Directorate Identifier 2013–NM–207–AD.
(a) Comments Due Date
We must receive comments by May 15,
2015.
(b) Affected ADs
This AD replaces AD 2013–13–04,
Amendment 39–17492 (78 FR 41286, July 10,
2013).
(c) Applicability
(1) This AD applies to Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–211,
–212, –214, –231, –232, and –233 airplanes;
and Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes;
certificated in any category; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
(e) Reason
This AD was prompted by a determination
that additional work is necessary to
adequately address the identified unsafe
condition. We are issuing this AD to prevent
untimely unlocking and/or retraction of the
nose landing gear (NLG), which, while on the
ground, could result in injury to ground
personnel and damage to the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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17009
(g) Retained Modification
This paragraph restates the requirements of
paragraph (g) of AD 2013–13–04,
Amendment 39–17492 (78 FR 41286, July 10,
2013). For all airplanes except airplanes on
which Airbus modification 37866 has been
embodied in production: At the applicable
compliance time specified in paragraph (g)(1)
or (g)(2) of this AD: Install a power
interruption protection circuit for the landing
gear control interface unit (LGCIU), in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1346, Revision 04, including Appendices
01 and 02, dated April 22, 2011 (for Model
A318, A319, A320, and A321 series airplanes
other than the Model A319CJ (corporate jet)
airplanes); or Airbus Service Bulletin A320–
32–1349, Revision 03, including Appendix 1,
dated October 5, 2011 (for Model A319CJ
(corporate jet) airplanes).
(1) For airplanes that have embodied
Airbus Modification 38947 specified in
Airbus Service Bulletin A320–32–1348
during production or in service: Within 72
months after August 14, 2013 (the effective
date of AD 2013–13–04, Amendment 39–
17492 (78 FR 41286, July 10, 2013)).
(2) For all airplanes other than those
identified in paragraph (g)(1) of this AD:
Within 60 months after August 14, 2013 (the
effective date of AD 2013–13–04,
Amendment 39–17492 (78 FR 41286, July 10,
2013)).
(h) Retained Re-Identification of
Identification Plates
This paragraph restates the requirements of
paragraph (h) of AD 2013–13–04,
Amendment 39–17492 (78 FR 41286, July 10,
2013). For airplanes on which the installation
required by paragraph (g) of this AD has been
done before August 14, 2013 (the effective
date of AD 2013–13–04, Amendment 39–
17492 (78 FR 41286, July 10, 2013)) using
Airbus Service Bulletin A320–32–1346,
dated December 4, 2008 (for Model A318,
A319, A320, and A321 series airplanes other
than Model A319CJ (corporate jet) airplanes):
Within the applicable times specified in
paragraphs (g)(1) and (g)(2) of this AD, reidentify the identification plates, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1346, Revision 04, including Appendices
01 and 02, dated April 22, 2011 (for Model
A318, A319, A320, and A321 series airplanes
other than Model A319CJ (corporate jet)
airplanes).
(i) New Modification
For airplanes identified in paragraphs
(i)(1), (i)(2), and (i)(3) of this AD except
airplanes on which Airbus modification
37866 has been embodied in production:
Modify the LGCIU at the applicable time
specified in paragraph (i)(1), (i)(2), or (i)(3) of
this AD, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1346, Revision 05,
dated January 13, 2012, or Airbus Service
Bulletin A320–32–1349, Revision 03,
including Appendix 1, dated October 5, 2011
(for Model A319CJ (corporate jet) airplanes).
Accomplishing the modification in this
paragraph terminates the actions required by
paragraphs (g) and (h) of this AD.
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(1) For airplanes on which any LG selector
valve having part number (P/N) 114079019 is
installed and that have embodied Airbus
Modification 38947 specified in Airbus
Service Bulletin A320–32–1348 during
production or in service: Modify the LGCIU
within 72 months after the effective date of
this AD.
(2) For airplanes on which any LG selector
valve 40GA having a part number listed in
paragraphs (i)(2)(i) through (i)(2)(xii) of this
AD, provided the valve has the marking ‘‘DI’’
or ‘‘DI–BE’’ recorded on its amendment
plates: Modify the LGCIU within 72 months
after the effective date of this AD.
(i) P/N 114079001.
(ii) P/N 114079005.
(iii) P/N 114079009.
(iv) P/N 114079013.
(v) P/N 114079001A.
(vi) P/N 114079005A.
(vii) P/N 114079009A.
(viii) P/N114079015.
(ix) P/N 114079001AB.
(x) P/N 114079005AB.
(xi) P/N 114079009AB.
(xii) P/N 114079017.
(3) For all airplanes other than those
identified in paragraphs (i)(1) and (i)(2) of
this AD: Modify the LGCIU within 60 months
after the effective date of this AD.
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(j) New Modification for Airplanes
Previously Modified
For airplanes that have been modified as of
the effective date of this AD as specified in
the applicable service information identified
in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this
AD, except airplanes on which Airbus
modification 37866 has been embodied in
production: Within 72 months after the
effective date of this AD, do the additional
modification of the LGCIU, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–32–1346,
Revision 05, dated January 13, 2012.
(1) Airbus Service Bulletin A320–32–1346,
Revision 01, dated October 27, 2009, which
is not incorporated by reference in this AD.
(2) Airbus Service Bulletin A320–32–1346,
Revision 02, dated November 4, 2009, which
is not incorporated by reference in this AD.
(3) Airbus Service Bulletin A320–32–1346,
Revision 03, dated January 7, 2010, which is
not incorporated by reference in this AD.
(4) Airbus Service Bulletin A320–32–1346,
including Appendices 01 and 02, Revision
04, dated April 22, 2011, which is
incorporated by reference in AD 2013–13–04,
Amendment 39–17492 (78 FR 41286, July 10,
2013).
(k) New Maintenance or Inspection Program
Revision
Before further flight after accomplishing
the actions specified in paragraph (i) or (j) of
this AD or within 7 days after the effective
date of this AD, whichever occurs later:
Revise the maintenance or inspection
program, as applicable, to incorporate Task
32.30.00.17, ‘‘Functional Check of LGCIU
Power Supply Relays,’’ of Section C–32 of
Section C, Systems and Powerplant, of the
Airbus A318/A319/A320/A321 Maintenance
Review Board Report, Revision 18, dated
March 2013. The initial compliance time is
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within 4,000 flight hours after accomplishing
the additional modification of the LGCIU.
(l) Credit for Previous Actions
This paragraph provides credit for A319
Corporate Jet airplanes for the modification
required by paragraph (g) of this AD if that
modification was performed before the
effective date of this AD using Airbus Service
Bulletin A320–32–1349, dated December 4,
2008; Airbus Service Bulletin A320–32–1349,
Revision 01, dated August 31, 2009; or
Airbus Service Bulletin A320–32–1349,
Revision 02, dated June 16, 2010.
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; 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) AMOCs approved previously for AD
2013–13–04, Amendment 39–17492 (78 FR
41286, July 10, 2013) are approved as
AMOCs for the corresponding provisions of
this AD.
(3) 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
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0202, dated
September 5, 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–2015–0678.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EAS, 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
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
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
20, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–07281 Filed 3–30–15; 8:45 am]
BILLING CODE 4910–13–P
ENVIRONMENTAL PROTECTION
AGENCY
40 CFR Part 52
[EPA–R09–OAR–2015–0165; FRL–9925–31–
Region 9]
Promulgation of Air Quality
Implementation Plans; Arizona;
Regional Haze Federal Implementation
Plan; Reconsideration
Environmental Protection
Agency.
ACTION: Proposed rule.
AGENCY:
The Environmental Protection
Agency (EPA) is proposing to revise part
of the Arizona Regional Haze (RH)
Federal Implementation Plan (FIP)
applicable to the Coronado Generating
Station (Coronado). In response to a
petition for reconsideration from the
Salt River Project Agricultural
Improvement and Power District (SRP),
the owner/operator of Coronado, we are
proposing to replace a plant-wide
compliance method with a unit-specific
compliance method for determining
compliance with the best available
retrofit technology (BART) emission
limits for nitrogen oxides (NOX) from
Units 1 and 2 at Coronado. While the
plant-wide limit for the NOX emissions
from Units 1 and 2 were established as
0.065 lb/MMBtu, we are proposing a
unit-specific limit of 0.065 lb/MMBtu
for Unit 1 and 0.080 lb/MMBtu for Unit
2. In addition, we are proposing to
revise the work practice standard in the
FIP for Coronado. Finally, we are
proposing to remove the affirmative
defense for malfunctions from the
Arizona RH FIP, which applies to both
Coronado and the Cholla Power Plant
(Cholla).
SUMMARY:
Written comments must be
submitted to the designated contact on
or before May 15, 2015. Requests for a
public hearing must be received on or
before April 15, 2015.
ADDRESSES: Submit your comments,
identified by docket number EPA–R09–
OAR–2015–0165, by one of the
following methods:
DATES:
E:\FR\FM\31MRP1.SGM
31MRP1
]]>Agencies
[Federal Register Volume 80, Number 61 (Tuesday, March 31, 2015)]
[Proposed Rules]
[Pages 17007-17010]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-07281]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0678; Directorate Identifier 2013-NM-207-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) 2013-13-
04, for certain Airbus Model A318, A319, A320, and A321 series
airplanes. AD 2013-13-04 currently requires installing a power
interruption protection circuit for the landing gear control interface
unit (LGCIU). Since we issued AD 2013-13-04, we have determined that
additional work is necessary to adequately address the identified
unsafe condition. This proposed AD would require a new modification of
any previously modified LGCIU. This proposed AD would also require
revising the maintenance or inspection program to reduce a certain
functional check interval. This proposed AD also adds airplanes to the
applicability. We are proposing this AD to prevent untimely unlocking
and/or retraction of the nose landing gear (NLG), which, while on the
ground, could result in injury to ground personnel and damage to the
airplane.
DATES: We must receive comments on this proposed AD by May 15, 2015.
ADDRESSES: You may send comments by any of the following methods:
[[Page 17008]]
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 AD, contact Airbus,
Airworthiness Office--EAS, 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-
0678; 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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
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-2015-0678;
Directorate Identifier 2013-NM-207-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 June 14, 2013, we issued AD 2013-13-04, Amendment 39-17492 (78
FR 41286, July 10, 2013). AD 2013-13-04 requires actions intended to
address an unsafe condition on certain Airbus Model A318, A319, A320,
and A321 series airplanes. Since we issued AD 2013-13-04, Amendment 39-
17492 (78 FR 41286, July 10, 2013), the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA Airworthiness Directive 2013-0202,
dated September 5, 2013 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for Airbus Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes;
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes. The MCAI states:
After a push back from the gate, an A320 aeroplane was preparing
to initiate taxi, when an uncommanded nose landing gear (NLG)
retraction occurred, causing the nose of the aeroplane to hit the
ground. Investigations revealed that the retraction was caused by a
combination of a power interruption to Landing Gear Control and
Interface Units (LGCIU) and an internal hydraulic leak through the
landing gear (LG) selector valve 40GA.
Deeper investigations have revealed that LGCIU power
interruption appears during engine start at each flight. Even though
no incident has been reported in service, it has been determined
that a non-compliance to the safety objective exists when combined
with a dormant single failure of the selector valve seal leaking.
This condition, if not corrected, could lead to further
incidents of untimely unlocking and/or retraction of the NLG which,
while on the ground, could result in injury to ground personnel and
damage to the aeroplane.
To address the possible hydraulic leak of the LG selector valve,
EASA issued AD 2007-0065 [https://ad.easa.europa.eu/blob/easa_ad_2007_0065.pdf/AD_2007-0065] currently at Revision 2.
To address the risk of untimely unlocking and/or retraction of
the NLG, EASA issued AD 2011-0202 [https://ad.easa.europa.eu/blob/easa_ad_2011_0202.pdf/AD_2011-0202] to require installation of a
power interruption protection circuit to the LGCIU and
accomplishment of associated modifications.
Since that [EASA] AD was issued, it has been discovered that
additional work is necessary to adequately correct this unsafe
condition and consequently, Airbus issued Service Bulletin (SB)
A320-32-1346 to Revision 05. An update of the maintenance programme
is required as well, following the required modification.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2011-0202, which is superseded, and requires
certain additional actions, as defined in the revised Airbus SB, as
applicable to aeroplane model, and an update of the approved
maintenance programme.
The additional actions include a new modification of any previously
modified LGCIU, and reducing a certain functional check interval. This
proposed AD also adds airplanes on which Airbus modification 37866 has
been embodied in production to the applicability. 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-2015-0678.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-32-1346, Revision 05, dated
January 13, 2012. The service information describes procedures for
modifying the LGCIU. 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 these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 851 airplanes of U.S.
registry.
The actions required by AD 2013-13-04, Amendment 39-17492 (78 FR
41286, July 10, 2013), take about 48 work-hours per product, at an
average labor rate of $85 per work-hour. Required parts will cost about
$8,220
[[Page 17009]]
per product. Based on these figures, the estimated cost of the actions
that are required by AD 2013-13-04 is $12,300 per product.
We estimate that it would take about 46 work-hours per product to
comply with the new modification in this proposed AD. The average labor
rate is $85 per work-hour. Required parts would cost about $9,650 per
product. Based on these figures, we estimate the cost of the new
modification on U.S. operators to be $11,539,560 or $13,560 per
product.
We estimate that it would take about 1 work-hour per product to
revise the maintenance or inspection program in this proposed AD. The
average labor rate is $85 per work-hour. Based on these figures, we
estimate the cost of revising the maintenance program on U.S. operators
to be $72,335 or $85 per product.
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)
2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 2013), and adding
the following new AD:
Airbus: Docket No. FAA-2015-0678; Directorate Identifier 2013-NM-
207-AD.
(a) Comments Due Date
We must receive comments by May 15, 2015.
(b) Affected ADs
This AD replaces AD 2013-13-04, Amendment 39-17492 (78 FR 41286,
July 10, 2013).
(c) Applicability
(1) This AD applies to Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes; certificated in any category; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by a determination that additional work is
necessary to adequately address the identified unsafe condition. We
are issuing this AD to prevent untimely unlocking and/or retraction
of the nose landing gear (NLG), which, while on the ground, could
result in injury to ground personnel and damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Modification
This paragraph restates the requirements of paragraph (g) of AD
2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 2013). For all
airplanes except airplanes on which Airbus modification 37866 has
been embodied in production: At the applicable compliance time
specified in paragraph (g)(1) or (g)(2) of this AD: Install a power
interruption protection circuit for the landing gear control
interface unit (LGCIU), in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-32-1346, Revision 04,
including Appendices 01 and 02, dated April 22, 2011 (for Model
A318, A319, A320, and A321 series airplanes other than the Model
A319CJ (corporate jet) airplanes); or Airbus Service Bulletin A320-
32-1349, Revision 03, including Appendix 1, dated October 5, 2011
(for Model A319CJ (corporate jet) airplanes).
(1) For airplanes that have embodied Airbus Modification 38947
specified in Airbus Service Bulletin A320-32-1348 during production
or in service: Within 72 months after August 14, 2013 (the effective
date of AD 2013-13-04, Amendment 39-17492 (78 FR 41286, July 10,
2013)).
(2) For all airplanes other than those identified in paragraph
(g)(1) of this AD: Within 60 months after August 14, 2013 (the
effective date of AD 2013-13-04, Amendment 39-17492 (78 FR 41286,
July 10, 2013)).
(h) Retained Re-Identification of Identification Plates
This paragraph restates the requirements of paragraph (h) of AD
2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 2013). For
airplanes on which the installation required by paragraph (g) of
this AD has been done before August 14, 2013 (the effective date of
AD 2013-13-04, Amendment 39-17492 (78 FR 41286, July 10, 2013))
using Airbus Service Bulletin A320-32-1346, dated December 4, 2008
(for Model A318, A319, A320, and A321 series airplanes other than
Model A319CJ (corporate jet) airplanes): Within the applicable times
specified in paragraphs (g)(1) and (g)(2) of this AD, re-identify
the identification plates, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-32-1346, Revision 04,
including Appendices 01 and 02, dated April 22, 2011 (for Model
A318, A319, A320, and A321 series airplanes other than Model A319CJ
(corporate jet) airplanes).
(i) New Modification
For airplanes identified in paragraphs (i)(1), (i)(2), and
(i)(3) of this AD except airplanes on which Airbus modification
37866 has been embodied in production: Modify the LGCIU at the
applicable time specified in paragraph (i)(1), (i)(2), or (i)(3) of
this AD, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-32-1346, Revision 05, dated January 13,
2012, or Airbus Service Bulletin A320-32-1349, Revision 03,
including Appendix 1, dated October 5, 2011 (for Model A319CJ
(corporate jet) airplanes). Accomplishing the modification in this
paragraph terminates the actions required by paragraphs (g) and (h)
of this AD.
[[Page 17010]]
(1) For airplanes on which any LG selector valve having part
number (P/N) 114079019 is installed and that have embodied Airbus
Modification 38947 specified in Airbus Service Bulletin A320-32-1348
during production or in service: Modify the LGCIU within 72 months
after the effective date of this AD.
(2) For airplanes on which any LG selector valve 40GA having a
part number listed in paragraphs (i)(2)(i) through (i)(2)(xii) of
this AD, provided the valve has the marking ``DI'' or ``DI-BE''
recorded on its amendment plates: Modify the LGCIU within 72 months
after the effective date of this AD.
(i) P/N 114079001.
(ii) P/N 114079005.
(iii) P/N 114079009.
(iv) P/N 114079013.
(v) P/N 114079001A.
(vi) P/N 114079005A.
(vii) P/N 114079009A.
(viii) P/N114079015.
(ix) P/N 114079001AB.
(x) P/N 114079005AB.
(xi) P/N 114079009AB.
(xii) P/N 114079017.
(3) For all airplanes other than those identified in paragraphs
(i)(1) and (i)(2) of this AD: Modify the LGCIU within 60 months
after the effective date of this AD.
(j) New Modification for Airplanes Previously Modified
For airplanes that have been modified as of the effective date
of this AD as specified in the applicable service information
identified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this
AD, except airplanes on which Airbus modification 37866 has been
embodied in production: Within 72 months after the effective date of
this AD, do the additional modification of the LGCIU, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-32-1346, Revision 05, dated January 13, 2012.
(1) Airbus Service Bulletin A320-32-1346, Revision 01, dated
October 27, 2009, which is not incorporated by reference in this AD.
(2) Airbus Service Bulletin A320-32-1346, Revision 02, dated
November 4, 2009, which is not incorporated by reference in this AD.
(3) Airbus Service Bulletin A320-32-1346, Revision 03, dated
January 7, 2010, which is not incorporated by reference in this AD.
(4) Airbus Service Bulletin A320-32-1346, including Appendices
01 and 02, Revision 04, dated April 22, 2011, which is incorporated
by reference in AD 2013-13-04, Amendment 39-17492 (78 FR 41286, July
10, 2013).
(k) New Maintenance or Inspection Program Revision
Before further flight after accomplishing the actions specified
in paragraph (i) or (j) of this AD or within 7 days after the
effective date of this AD, whichever occurs later: Revise the
maintenance or inspection program, as applicable, to incorporate
Task 32.30.00.17, ``Functional Check of LGCIU Power Supply Relays,''
of Section C-32 of Section C, Systems and Powerplant, of the Airbus
A318/A319/A320/A321 Maintenance Review Board Report, Revision 18,
dated March 2013. The initial compliance time is within 4,000 flight
hours after accomplishing the additional modification of the LGCIU.
(l) Credit for Previous Actions
This paragraph provides credit for A319 Corporate Jet airplanes
for the modification required by paragraph (g) of this AD if that
modification was performed before the effective date of this AD
using Airbus Service Bulletin A320-32-1349, dated December 4, 2008;
Airbus Service Bulletin A320-32-1349, Revision 01, dated August 31,
2009; or Airbus Service Bulletin A320-32-1349, Revision 02, dated
June 16, 2010.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; 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) AMOCs approved previously for AD 2013-13-04, Amendment 39-
17492 (78 FR 41286, July 10, 2013) are approved as AMOCs for the
corresponding provisions of this AD.
(3) 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 the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0202, dated September 5,
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-2015-0678.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EAS, 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 20, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-07281 Filed 3-30-15; 8:45 am]
BILLING CODE 4910-13-P
