[Federal Register Volume 79, Number 203 (Tuesday, October 21, 2014)]
[Proposed Rules]
[Pages 62928-62932]
[FR Doc No: 2014-25023]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0753; Directorate Identifier 2014-NM-128-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-19-
04, for all Airbus Model A318, A319, A320, and A321 series airplanes.
AD 2011-19-04 currently requires repetitive inspections of the left-
hand and right-hand inboard and outboard elevator servo-control rod
eye-ends for cracking, and corrective actions if necessary. Since we
issued AD 2011-19-04, we have determined that certain elevator servo-
control parts that do not conform to the approved type design have been
installed and may have the potential of cracks in the rod eye-end. This
proposed AD would also require an inspection to determine if certain
elevator servo-control parts are installed, and replacement if
necessary. We are proposing this AD to detect and correct rod eye-end
cracking, which could result in an uncontrolled elevator surface and
consequent reduced control of the airplane.

DATES: We must receive comments on this proposed AD by December 5,
2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email<EMAIL_ADDRESS>Internet http://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 http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0753; 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<PHONE_NUMBER>) 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<PHONE_NUMBER>; fax<PHONE_NUMBER>.

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-2014-0753;
Directorate Identifier 2014-NM-128-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 http://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 7, 2011, we issued AD 2011-19-04, Amendment 39-16809
(76 FR 57630, September 16, 2011). AD 2011-19-04 requires actions
intended to address an unsafe condition on all Airbus Model A318, A319,
A320, and A321 series airplanes. AD 2011-19-04 superseded AD 2009-17-
04, Amendment 39-15995 (74 FR 41611, August 18, 2009).
    Since we issued AD 2011-19-04, Amendment 39-16809 (76 FR 57630,
September 16, 2011), the European Aviation Safety Agency (EASA), which
is the Technical Agent for the Member States of the European Community,
has issued EASA Airworthiness Directive 2014-0137, dated May 28, 2014
(referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for all
Model A318, A319, A320, and Model A321 series airplanes. The MCAI
states:

    One case of elevator servo-control disconnection was reported on
an A320 family aeroplane. Investigation results revealed that the
failure occurred at the servo-control rod eye-end. Prompted by this
finding, additional inspections revealed cracking at the same
location on a number of other servo-control rod eye-ends. In several
cases, both actuators of the same elevator surface were affected.
    It was determined that the detected rod end cracks are caused by
fatigue, induced by a bending effect which is linked to the
spherical bearing rotational torque. As the elevator surface is
neither actuated nor damped, a dual servo-control disconnection on
the same elevator would result in an uncontrolled surface.
    This condition, if not corrected, could result in reduced
control of the aeroplane.
    To address this potential unsafe condition, EASA issued [an
airworthiness directive (later revised)] [which corresponds to FAA
AD 2009-17-04, Amendment 39-5995 (74 FR 41611, August 18, 2009)] to
require a one-time inspection of the elevator servo-control rod eye-
ends for aeroplanes which had accumulated more than 10,000 flight
cycles (FC) since aeroplane first flight and, in case of findings,
accomplishment of corrective actions.
    As a result of EASA AD 2008-0149, a significant number of rod
eye-ends were found cracked. In addition, some cracks were reported
on rod eye-ends that had not yet accumulated the 10,000 FC of the
established threshold.
    Prompted by these findings, EASA issued [an airworthiness
directive (later revised)] [which corresponds to FAA AD 2011-19-04,
Amendment 39-16809 (76 FR 57630, September 16, 2011)], which
partially retained the initial inspection requirement of EASA AD
2008-0149, which was superseded, reduced the compliance time of the
initial inspection and introduced a repetitive inspection programme.
    After EASA AD 2010-0046R1 (http://ad.easa.europa.eu/blob/easa_ad_2010_0046_R1_superseded.pdf/AD_2010-0046R1_1) was issued, a
new elevator servo-control rod eye-end was developed, incorporating
a re-greasable roller bearing.
    Consequently, EASA issued [EASA] AD 2013-0309 (later corrected)
(http://ad.easa.europa.eu/blob/easa_ad_2013_0309_superseded.pdf/AD_2013-0309_1), retaining the requirements of EASA AD 2010-0046R1,
which was superseded, and introduced an optional terminating action
for the repetitive inspections by replacing the existing elevator
servo-control rod eye-ends with the new elevator servo-control rod
eye-end. In addition, that [EASA] AD prohibited, for aeroplanes that
incorporate this optional modification, (re)installation of
unmodified elevator servo-controls.
    At the time that EASA AD 2013-0309 was issued, it was planned
that Airbus would proceed with the certification of certain elevator
servo-controls, Part Number (P/N) 31075-0xx, P/N 31075-1xx and P/N
31075-3xx (originally certified only for installation on Model A320-
111 aeroplanes, which are no longer in service), to allow
installation of those parts on other A320 family aeroplane Models.
    Since that [EASA] AD was issued, Airbus decided not to progress
with certification of the affected elevator servo-controls for
installation on other Models.
    For the reason described above, and because of evidence that
such parts remain available as spares in the field, this [EASA] AD
retains the requirements of EASA AD 2013-0309, which is superseded,
and adds a prohibition to install the affected elevator servo-
controls that were only intended for A320-111 aeroplanes.

This proposed AD would require an inspection to determine whether any
elevator control part having P/N 31075-0xx, 31075-1xx, or 31075-3xx is
installed and replacement if necessary. You may examine the MCAI in the
AD docket on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2014-0753.

Relevant Service Information

    Airbus has issued Service Bulletin A320-27-1223, dated September 3,
2013. The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.

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

    The MCAI does not include an action for airplanes installed with
elevator control parts having part number (P/N) 31075-0xx, 31075-1xx,
or 31075-3xx. This proposed AD would require an inspection to determine
if those elevator servo-control parts are installed, and replacement if
necessary.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S.
registry.
    The actions that are required by AD 2011-19-04, Amendment 39-16809
(76 FR 57630, September 16, 2011), and retained in this proposed AD
take about 25 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 2011-19-04 is $2,125 per product.
    We also estimate that it would take about 14 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 $1,012,690, or
$1,190 per product.
    In addition, we estimate that any necessary follow-on actions would
take about 2 work-hours and require parts costing $4,000, for a cost of
$4,170 per product. We have no way of

determining the number of aircraft that might need this action.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
    We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This proposed regulation is
within the scope of that authority because it addresses an unsafe
condition that is likely to exist or develop on products identified in
this rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD)
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011), and
adding the following new AD:

Airbus: Docket No. FAA-2014-0753; Directorate Identifier 2014-NM-
128-AD.

(a) Comments Due Date

    We must receive comments by December 5, 2014.

(b) Affected ADs

    This AD replaces AD 2011-19-04, Amendment 39-16809 (76 FR 57630,
September 16, 2011).

(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 A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight
Controls.

(e) Reason

    This AD was prompted by a determination that certain elevator
servo-control parts that do not conform to the approved type design
have been installed and may have the potential of cracks in the rod
eye-end. We are issuing this AD to detect and correct rod eye-end
cracking, which could result in uncontrolled elevator surface and
consequent reduced control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Retained Inspections

    This paragraph restates the requirements of paragraph (g) of AD
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011),
with no changes.
    (1) At the applicable times specified in paragraphs (g)(1)(i)
and (g)(1)(ii) of this AD: Inspect both the left-hand and right-hand
inboard elevator servo-control rod eye-ends for cracking, in
accordance with the instructions of Airbus All Operators Telex (AOT)
A320-27A1186, Revision 04, dated April 3, 2009; or the
Accomplishment Instructions of Airbus Service Bulletin A320-27A1186,
Revision 07, dated March 2, 2011. As of October 21, 2011 (the
effective date of AD 2011-19-04, Amendment 39-16809 (76 FR 57630,
September 16, 2011)), use Airbus Service Bulletin A320-27A1186,
Revision 07, dated March 2, 2011.
    (i) For airplanes that have accumulated 10,000 total flight
cycles or more as of September 22, 2009 (the effective date of AD
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At
the later of the times specified in paragraphs (g)(1)(i)(A) and
(g)(1)(i)(B) of this AD.
    (A) Within 1,500 flight cycles after September 22, 2009 (the
effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611,
August 18, 2009)).
    (B) Within 1,500 flight cycles after accumulating 10,000 total
flight cycles since first flight of the airplane.
    (ii) For airplanes that have accumulated less than 10,000 total
flight cycles as of September 22, 2009 (the effective date of AD
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At
the later of the times specified in paragraphs (g)(1)(ii)(A) and
(g)(1)(ii)(B) of this AD.
    (A) Before the accumulation of 5,000 total flight cycles.
    (B) Within 20 months after October 21, 2011 (the effective date
of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16,
2011)) but no later than before the accumulation of 11,500 total
flight cycles.
    (2) At the applicable time specified in paragraphs (g)(2)(i) and
(g)(2)(ii) of this AD: Inspect both the left-hand and right-hand
outboard elevator servo-control rod eye-ends for cracking, in
accordance with the instructions of Airbus AOT A320-27A1186,
Revision 04, dated April 3, 2009; or the Accomplishment Instructions
of Airbus Service Bulletin A320-27A1186, Revision 07, dated March 2,
2011. As of October 21, 2011 (the effective date of AD 2011-19-04,
Amendment 39-16809 (76 FR 57630, September 16, 2011)), use Airbus
Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011.
    (i) For airplanes that have accumulated 10,000 total flight
cycles or more as of September 22, 2009 (the effective date of AD
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At
the later of the times specified in paragraphs (g)(2)(i)(A) and
(g)(2)(i)(B) of this AD.
    (A) Within 3,000 flight cycles after September 22, 2009 (the
effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611,
August 18, 2009)).
    (B) Within 3,000 flight cycles after accumulating 10,000 total
flight cycles since first flight of the airplane.
    (ii) For airplanes that have accumulated less than 10,000 total
flight cycles as of September 22, 2009 (the effective date of AD
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At
the later of the times specified in paragraphs (g)(2)(ii)(A) and
(g)(2)(ii)(B) of this AD.
    (A) Before the accumulation of 7,500 total flight cycles.
    (B) Within 40 months after October 21, 2011 (the effective date
of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16,
2011)) but no later than before the accumulation of 13,000 total
flight cycles.

(h) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (h) of AD
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011),
with no changes. Repeat the inspections of the left-hand and

right-hand inboard and outboard elevator servo-control rod eye-ends
for cracking as required by paragraphs (g)(1) and (g)(2) of this AD
at the later of the times specified in paragraph (h)(1) or (h)(2) of
this AD. Repeat the inspections thereafter at intervals not to
exceed 5,000 flight cycles.
    (1) Within 5,000 flight cycles after the last inspection
required by paragraph (g)(1) or (g)(2) of this AD as applicable.
    (2) Within 6 months after October 21, 2011 (the effective date
of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16,
2011)).

(i) Retained Corrective Actions

    This paragraph restates the requirements of paragraph (i) of AD
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011),
with no changes. If any cracking is found during any inspection
required by paragraph (g) or (h) of this AD, before further flight,
accomplish all applicable corrective actions, in accordance with the
Accomplishment Instructions and figures of Airbus Service Bulletin
A320-27A1186, Revision 07, dated March 2, 2011.

(j) Retained Parts Limitation for Elevator Servo-Control Rod Eye-Ends

    This paragraph restates the requirements of paragraph (j) of AD
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011),
with a new exception. As of October 21, 2011 (the effective date of
AD 2011-19-04, Amendment 39-16809 (76 FR 57360, September 16,
2011)), and except as required by paragraph (p) of this AD, no
person may install on any airplane an elevator servo-control rod
eye-end unless it is new or has been inspected in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-
27A1186, Revision 07, dated March 2, 2011, with no crack findings.

(k) New Requirement of This AD: Inspection To Determine Part Numbers

    As of the effective date of this AD: At the later of the times
specified in paragraphs (k)(1) and (k)(2) of this AD, do an
inspection to determine whether any elevator control part having
part number (P/N) 31075-0xx, 31075-1xx, or 31075-3xx is installed. A
review of airplane maintenance records is acceptable in lieu of this
inspection if the part numbers of the elevator control parts can be
conclusively determined from that review.
    (1) Concurrently with the accomplishment of the next inspection
required by paragraph (g) or (h) of this AD.
    (2) Within 30 days after the effective date of this AD.

(l) New Requirement of This AD: Replacement of Certain Parts

    If the inspection required by paragraph (k) of this AD reveals
that any elevator servo-controls having P/Ns 31075-0xx, 31075-1xx,
or 31075-3xx are installed: Before further flight, do the actions
specified in paragraph (l)(1) or (l)(2) of this AD.
    (1) Replace all elevator servo-controls having P/N 31075-0xx,
31075-1xx, or 31075-3xx with parts having P/N 31075-2xx or 31075-
4xx, as applicable, 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).
    (2) Replace all elevator servo-controls having P/N 31075-0xx,
31075-1xx, or 31075-3xx with serviceable parts having P/N 31075-6xx
or 31075-8xx, as applicable, in accordance with the Accomplishment
Instruction of Airbus Service Bulletin A320-27-1223, dated September
3, 2013, or Goodrich Service Bulletin 31075-27-22, dated July 2,
2013. Serviceable parts are those that have been inspected for
cracks in the rod eye-ends without any crack findings in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-27A1186, Revision 07, dated March 2, 2011.

(m) New Optional Terminating Action for Certain Inspections

    Modification of an airplane by replacing all 4 elevator servo-
control rod eye-ends with modified (i.e. re-greasable) parts, and
re-identification of those elevator servo-controls to P/N 31075-6xx
or P/N 31075-8xx, as applicable, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1223,
dated September 3, 2013; constitutes terminating action for the
requirements of paragraphs (g), (h), (k), and (l) of this AD.

    Note 1 to paragraph (m) of this AD: Maintenance Review Board
Report task reference 27.34.00/06 is applicable to elevator servo-
controls having P/N 31075-6xx or P/N 31075-8xx.

(n) New Exception to Certain Inspections

    Airplanes on which Airbus modification 154554 (installation of
servo-controls having P/N 31075-6xx or P/N 31075-8xx, fitted with
modified rod eye-end roller bearing) has been embodied in production
are not affected by the requirements of paragraphs (g), (h), (k),
and (l) of this AD, provided that no elevator servo-control having
P/N 31075-0xx, or P/N 31075-1xx, or P/N 31075-2xx, or P/N 31075-3xx,
or P/N 31075-4xx, fitted with rod-end assembly P/N 341203-xxx, has
been reinstalled since first flight.

(o) Credit for Previous Actions

    (1) This paragraph restates the credit specified in paragraph
(k) of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16,
2011).
    (i) This paragraph provides credit for actions required by
paragraphs (g)(1) and (g)(2) of this AD, if those actions were
performed before October 21, 2011 (the effective date of AD 2011-19-
04, Amendment 39-16809 (76 FR 57630, September 16, 2011)), using the
service information specified in table 1 to paragraph (o)(1)(i) of
this AD.

       Table 1 to Paragraph (o)(1)(i) of This AD--Credit Service Information for Paragraph (g) of This AD
----------------------------------------------------------------------------------------------------------------
               Airbus AOT--                            Revision--                           Dated--
----------------------------------------------------------------------------------------------------------------
A320-27A1186.............................  Original..........................  June 23, 2008.
A320-27A1186.............................  01................................  August 11, 2008.
A320-27A1186.............................  02................................  March 30, 2009.
A320-27A1186.............................  03................................  April 1, 2009.
A320-27A1186.............................  04................................  April 3, 2009.
----------------------------------------------------------------------------------------------------------------

    (ii) This paragraph provides credit for actions required by
paragraph (h) of this AD, if those actions were performed before
October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-
16809 (76 FR 57630, September 16, 2011)), using Airbus Service
Bulletin A320-27A1186, Revision 05, dated March 10, 2010; or Airbus
Service Bulletin A320-27A1186, Revision 06, dated December 14, 2010.
    (2) This paragraph provides credit for actions required by
paragraph (i) of this AD, if those actions were performed before
October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-
16809 (76 FR 57630, September 16, 2011)), using Airbus Service
Bulletin A320-27A1186, Revision 06, dated December 14, 2010.

(p) New Parts Installation Prohibition

    (1) As of the effective date of this AD, no person may install
on any airplane an elevator servo-control having P/N 31075-0xx,
31075-1xx, or 31075-3xx.
    (2) No person may install on any airplane an elevator servo-
control having P/N 31075-2xx or P/N 31075-4xx, or an elevator servo-
control rod eye-end having P/N 341203 or P/N 341203-XXX, as required
by paragraphs (p)(2)(i) and (p)(2)(ii) of this AD, as applicable.
    (i) For airplanes that do not have Airbus Modification 154554
embodied in production: After optional modification of the airplane
as specified in paragraph (m) of this AD.
    (ii) For airplanes on which Airbus Modification 154554 has been
embodied in production: As of the effective date of this AD.

(q) 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<PHONE_NUMBER>; fax<PHONE_NUMBER>. Information may be
emailed to<EMAIL_ADDRESS>    (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 2011-19-04, Amendment 39-
16809 (76 FR 57630, September 16, 2011), are approved as AMOCs for
the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0137, dated May 28, 2014,
for related information. This MCAI may be found in the AD docket on
the Internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2014-0753.
    (2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email<EMAIL_ADDRESS>Internet http://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<PHONE_NUMBER>.

    Issued in Renton, Washington, on October 13, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-25023 Filed 10-20-14; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 77, Number 95 (Wednesday, May 16, 2012)]
[Notices]
[Page 28866]
[FR Doc No: 2012-11828]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[ Docket No. CP12-455-000]

Pivotal Utility Holdings, Inc. d/b/a Elkton Gas; Notice of
Application

    Take notice that on May 4, 2012, Pivotal Utility Holdings, Inc. d/
b/a Elkton Gas (Elkton Gas), 125 B East High Street, Elkton, Maryland
21921, filed an abbreviated application pursuant to Section 7(f) of the
Natural Gas Act (NGA) and Part 157 of the Commission's Regulations
seeking a service area determination to include 744 feet of pipe and
appurtenant facilities extended from Maryland border into Delaware.
Elkton Gas also requests: (i) A finding that Elkton Gas continues to
qualify as a local distribution company (LDC) in Maryland, for purposes
of section 311 of the Natural Gas Policy Act of 1978 (NGPA); and (ii) a
waiver of the Commission's accounting and reporting requirements and
other regulatory requirements ordinarily applicable to natural gas
companies under the NGA and NGPA. The filing may also be viewed on the
Web at http://www.ferc.gov using the ``eLibrary'' link. Enter the
docket number excluding the last three digits in the docket number
field to access the document. For assistance, contact FERC at
<EMAIL_ADDRESS>or call toll-free,<PHONE_NUMBER> or TYY,
(202) 502-8659.
    In early 2012, Elkton Gas has determined that its Maryland LDC
system includes 744 feet of pipe and appurtenant facilities crossing
Maryland/Delaware border in order to reach a gate station owned and
operated by Eastern Shore Natural Gas Company (Eastern Shore), known as
the North Gate Station. Elkton Gas does not provide service in Delaware
and is not subject to regulation by the Delaware Public Service
Commission. Elkton Gas does not contemplate any changes in its
operations as a result of this change in regulatory status. The purpose
of owning facilities in Delaware is to bring gas to Maryland to serve
Elkton Gas' customers in Maryland.
    Any questions regarding this application should be directed to
Shannon Pierce, Senior Counsel, AGL Resources Inc., Ten Peachtree
Place, Suite 1000, Atlanta, GA 30309; phone number<PHONE_NUMBER>; or
email<EMAIL_ADDRESS>    Any person wishing to obtain legal status by becoming a party to
the proceedings for this project should, on or before the below listed
comment date, file with the Federal Energy Regulatory Commission, 888
First Street NE., Washington, DC 20426, a motion to intervene in
accordance with the requirements of the Commission's Rules of Practice
and Procedure (18 CFR 385.214 or 385.211) and the Regulations under the
NGA (18 CFR 157.10). A person obtaining party status will be placed on
the service list maintained by the Secretary of the Commission and will
receive copies of all documents filed by the applicant and by all other
parties. A party must submit original and 7 copies of filings made with
the Commission and must mail a copy to the applicant and to every other
party in the proceeding. Only parties to the proceeding can ask for
court review of Commission orders in the proceeding.
    Motions to intervene, protests and comments may be filed
electronically via the Internet in lieu of paper, see, 18 CFR
385.2001(a)(1)(iii) and the instructions on the Commission's Web site
under the ``e-Filing'' link. The Commission strongly encourages
electronic filings.
    Comment Date: 5:00 p.m. Eastern Time on May 31, 2012.

    Dated: May 10, 2012.
Kimberly D. Bose,
Secretary.
[FR Doc. 2012-11828 Filed 5-15-12; 8:45 am]
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