[Federal Register Volume 76, Number 1 (Monday, January 3, 2011)]
[Proposed Rules]
[Pages 46-50]
[FR Doc No: 2010-32991]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1273; Directorate Identifier 2010-NM-089-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A310-203, -204, -222, -
304, -322, and -324 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:

    A specific area, the lower tail plane cut-out located in the
tail cone is subject to an inspection programme [for cracking] * *
*.
* * * * *
The unsafe condition is reduced structural integrity of the tail cone.
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by February 17,
2011.

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 W12-40, 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--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail<EMAIL_ADDRESS>Internet http://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington. For information on the availability of
this material at the FAA, call<PHONE_NUMBER>.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; 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-2010-1273;
Directorate Identifier 2010-NM-089-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

    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2009-0058, dated March 13, 2009 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:

    A specific area, the lower tail plane cut-out located in the
tail cone is subject to an inspection programme specified in the
Airbus Service Bulletin (SB) A310-53-2074. EASA issued AD 2007-0053
[which superseded French AD 1992-106-132 R6; French AD 1992-106-132
corresponds to FAA AD 98-26-01] to require the accomplishment of
this SB at Revision 03.
    Airbus has established that this SB needed to be revised in
order to state correct threshold and intervals due to errors
introduced at revision 03. Consequently, revision 04 of this SB has
been issued, and opportunity was taken:

--To clarify the inspection area and associated threshold and
intervals
--To take aeroplane utilisation into consideration, in accordance
with the A310 life extension programme.

    For the reasons stated above, this EASA AD takes over the
requirements of paragraph 1.16 of EASA AD 2007-0053R1 [currently at
R3], which has been revised accordingly, and requires accomplishment
of the instructions contained in Airbus SB A310-53-2074 at Revision
04.

The unsafe condition is reduced structural integrity of the tail cone.
The required actions include repetitive and one-time inspections,
depending on the area, of the lower tail plane cut-out, and corrective
actions if necessary. The inspections include the following:
     Detailed inspections in areas 1, 2, and 3 for cracking and
corrosion of the lower horizontal stabilizer cutout longeron, the
corner fitting, the skin strap, and the skin.
     Detailed inspections in areas 1, 2, and 3 for damaged
sealant.
     Eddy current inspections in area 1 for cracking.
     Eddy current inspections in area 2 for cracking.
     Rotating probe inspection for cracking of specified
fastener holes in Area 3.
    The corrective actions, depending on the conditions found, include
the following:
     Repairing corrosion.
     Contacting Airbus for repair instructions.
     Replacing damaged sealant.
     Removing cracking.
     Doing an eddy current inspection for cracking of the
reworked area.
     Installing a new corner fitting.
     Doing a rotating probe inspection for cracking of fastener
holes.
     Doing an eddy current inspection of the longeron and outer
skin.
     Drilling or reaming fastener holes.
    You may obtain further information by examining the MCAI in the AD
docket.

Other Relevant Rulemaking

    We are considering issuing three other NPRMs related to this NPRM:
     Directorate Identifier 2010-NM-092-AD. That NPRM proposes
to supersede AD 98-26-01, amendment 39-10942 (63 FR 69179, December 16,
1998), to continue to require certain actions specified in that AD.
However, that NPRM does not restate paragraph (q) of AD 98-26-01.
Instead, certain requirements of paragraph (q) of that AD are included
in this NPRM, Directorate Identifier 2010-NM-089-AD.
     Directorate Identifiers 2010-NM-090-AD and 2010-NM-091-AD.
Both of these NPRMs include the requirements of certain other
paragraphs of AD 98-26-01.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A310-53-2074, Revision
04, dated October 24, 2008. 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 AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD
would affect about 44 products of U.S. registry. We also estimate that
it would take about 36 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 the proposed
AD on U.S. operators to be $134,640, or $3,060 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); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.

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.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Airbus: Docket No. FAA-2010-1273; Directorate Identifier 2010-NM-
089-AD.

Comments Due Date

    (a) We must receive comments by February 17, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model A310-203, -204, -222, -304, -322,
and -324 airplanes, certificated in any category, all serial
numbers, except airplanes on which Airbus modification 06146 has
been done in production.

Subject

    (d) Air Transport Association (ATA) of America Code 53:
Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI)
states:

    A specific area, the lower tail plane cut-out located in the
tail cone is subject to an inspection programme [for cracking] * *
*.
* * * * *
The unsafe condition is reduced structural integrity of the tail
cone.

Compliance

    (f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.

Initial Inspections of the Lower Tail Plane Cut-Out Area and Corrective
Actions

    (g) Within the applicable time specified in Table 1 of this AD,
do the inspections of the lower tail plane cut-out area in the tail
cone specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5),
and (g)(6) of this AD, as applicable, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008 (``the service
bulletin''). Certain compliance times are applicable to short-range
use (i.e., average flight time (AFT) equal to or less than 4 flight
hours), or long-range use (i.e., AFT exceeding 4 flight hours).
Inspection areas are specified in the service bulletin.

    Note 1:  To establish the average flight time, take the
accumulated flight time (counted from the take-off up to the
landing) and divide by the number of accumulated flight cycles. This
gives the average flight time per flight cycle.

                                        Table 1--Initial Compliance Time
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              Airplanes                   Inspection areas          Compliance time (whichever occurs later)
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Model A310-203, A310-204, and A310-   1 and 2.................  Prior to the             Within 1,500 flight
 222 airplanes.                                                  accumulation of 18,000   cycles or 3,000 flight
                                                                 total flight cycles or   hours, whichever
                                                                 36,000 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
Model A310-203, A310-204, and A310-   3.......................  Prior to the             Within 1,500 flight
 222 airplanes.                                                  accumulation of 24,000   cycles or 3,000 flight
                                                                 total flight cycles or   hours, whichever
                                                                 48,000 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
Model A310-304, A310-322, and A310-   1 and 2.................  Prior to the             Within 1,200 flight
 324 short range airplanes.                                      accumulation of 12,000   cycles or 3,300 flight
                                                                 total flight cycles or   hours, whichever
                                                                 33,750 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
Model A310-304, A310-322, and A310-   3.......................  Prior to the             Within 1,200 flight
 324 short range airplanes.                                      accumulation of 18,000   cycles or 3,300 flight
                                                                 total flight cycles or   hours, whichever
                                                                 50,500 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
Model A310-304, A310-322, and A310-   1 and 2.................  Prior to the             Within 750 flight
 324 long range airplanes.                                       accumulation of 7,500    cycles or 3,750 flight
                                                                 total flight cycles or   hours, whichever
                                                                 37,500 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
Model A310-304, A310-322, and A310-   3.......................  Prior to the             Within 750 flight
 324 long range airplanes.                                       accumulation of 11,250   cycles or 3,750 flight
                                                                 total flight cycles or   hours, whichever
                                                                 56,000 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
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     (1) For areas 1, 2, and 3: Do a detailed inspection for
cracking and corrosion of the lower horizontal stabilizer cutout
longeron, the corner fitting, the skin strap, and the skin, in
accordance with the Accomplishment Instructions of the service
bulletin.
    (i) If any corrosion is found, before further flight, repair in
accordance with the Accomplishment Instructions of the service
bulletin.
    (ii) If any cracking is found, before further flight, contact
Airbus for repair instructions and do the repair.
    (2) For areas 1, 2, and 3 on which cracking is not found during
the inspection required by paragraph (g)(1) of this AD: Do a
detailed inspection for damaged sealant; and, if any damaged sealant
is found, before further flight, replace the sealant; in accordance
with the Accomplishment Instructions of the service bulletin.
    (3) For area 1: Do an eddy current inspection for cracking in
area 1; and, if no cracking is found, before further flight, apply
sealant and corrosion compound, as applicable; in accordance with
the Accomplishment Instructions of the service bulletin.
    (i) If cracking is equal to or less than 2.0 mm (0.079 inch)
long and not more than 2 cracks with a minimum distance of 50.0 mm
(1.969 inch) between the cracks: Before further flight, remove any
cracking and do an eddy current inspection for cracking of the
reworked area, in accordance with the Accomplishment Instructions of
the service bulletin. If no cracking is found, before further
flight, shot peen the reworked area, in accordance with the
Accomplishment Instructions of the service bulletin.
    (A) If cracking is found and the radius of the rework is less
than 20.0 mm (0.787 inch), before further flight, increase the
radius and do an eddy current inspection for cracking of the
reworked area, in accordance with the Accomplishment Instructions of
the service bulletin. If no cracking is found, before further
flight, shot peen the reworked area, in accordance with the
Accomplishment Instructions of the service bulletin.
    (1) If any cracking is found in the outer skin, before further
flight, contact Airbus for repair instructions and do the repair.
    (2) If any cracking is found in the corner fitting and area 3
has not been cold expanded, before further flight, install new
corner fitting, in accordance with the Accomplishment Instructions
of the service bulletin, and do the rotating probe inspection in
area 3 specified in paragraph (g)(5) of this AD.
    (3) If any cracking is found in the corner fitting and area 3
has been cold expanded, before further flight, do the eddy current
inspection of the longeron and outer skin specified in paragraph
(g)(6) of this AD.
    (B) If cracking is found and the radius of the rework is 20.0 mm
(0.787 inch) or more, before further flight, repair in accordance
with a method approved by either the Manager, International Branch,
ANM-116, FAA, Transport Airplane Directorate, or the European
Aviation Safety Agency (EASA) (or its delegated agent).

    (ii) If cracking is greater than 2.0 mm (0.079 inch) long or
there are more than 2 cracks; or if there are more than 2 cracks
with less than a minimum distance of 50.0 mm (1.969 inch) between
the cracks: Before further flight, remove the corner fitting, and do
the applicable actions specified in paragraph (g)(3)(ii)(A) or
(g)(3)(ii)(B) of this AD.
    (A) If any cracking is found and area 3 has not been cold
expanded, before further flight, install a new corner fitting, in
accordance with the Accomplishment Instructions of the service
bulletin; and do the rotating probe inspection in area 3 specified
in paragraph (g)(5) of this AD.
    (B) If any cracking is found and area 3 has been cold expanded,
before further flight, do the eddy current inspection of the
longeron and outer skin specified in paragraph (g)(6) of this AD.
    (4) For area 2: Do an eddy current inspection for cracking of
area 2, in accordance with the Accomplishment Instructions of the
service bulletin. If any cracking is found, before further flight,
contact Airbus for repair instructions and do the repair.
    (5) For area 3: Do a rotating probe inspection for cracking of
specified fastener holes in area 3, in accordance with the
Accomplishment Instructions of the service bulletin.
    (i) If no cracking is found, before further flight, drill or
ream fastener holes, cold expand the fastener holes and
countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of the service bulletin; except where
the service bulletin specifies to contact Airbus if the fastener
diameter does not meet specifications or if the distance between the
hole center and material edge is less than specifications, before
further flight, contact Airbus for repair instructions and do the
repair.
    (ii) If cracking is found, before further flight, drill or ream
fastener holes, and do a rotating probe inspection for cracking of
the fastener holes in accordance with the Accomplishment
Instructions of the service bulletin.
    (A) If no cracking is found, cold expand the fastener holes and
countersinks, drill or ream fastener holes, and wet install with
sealant, in accordance with the Accomplishment Instructions of the
service bulletin; except where the service bulletin specifies to
contact Airbus if the fastener diameter does not meet specifications
or if the distance between the hole center and material edge is less
than the specifications, before further flight, contact Airbus for
repair instructions and do the repair.
    (B) If cracking is found, before further flight, contact Airbus
for repair instructions and do the repair.
    (6) For airplanes on which cracking is found in the corner
fitting during any inspection required by paragraph (g)(3) of this
AD and area 3 is cold-expanded: Do an eddy current inspection for
cracking of the longeron and outer skin, in accordance with the
Accomplishment Instructions of the service bulletin.
    (i) If no cracking is found, before further flight, install a
new corner fitting and do a rotating probe inspection for cracking
of the fastener holes, in accordance with the Accomplishment
Instructions of the service bulletin.
    (A) If no cracking is found, before further flight, drill or
ream fastener holes, cold expand the fastener holes and
countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of the service bulletin.
    (B) If cracking is found and the hole diameter is less than the
maximum oversize specification, before further flight, drill or ream
holes and do a rotating probe inspection for cracking of the
fastener holes, in accordance with the service bulletin.
    (1) If no cracking is found, cold expand the fastener holes and
countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of the service bulletin.
    (2) If cracking is found, before further flight, contact Airbus
for repair instructions and do the repair.
    (C) If cracking is found and the hole diameter is equal to or
greater than the maximum oversize specification, before further
flight, contact Airbus for repair instructions and do the repair.
    (ii) If cracking is found, before further flight, contact Airbus
for repair instructions and do the repair.

Repetitive Inspections of the Lower Tail Plane Cut-Out Area

    (h) Repeat the inspections for area 1 required by paragraphs
(g)(1) and (g)(3) of this AD thereafter at the applicable intervals
specified in Table 2 of this AD. Certain compliance times are
applicable to short-range use (AFT equal to or less than 4 flight
hours), or long-range use (AFT exceeding 4 flight hours). Inspection
areas are specified in the service bulletin.

             Table 2--Repetitive Interval for Areas 1 and 2
------------------------------------------------------------------------
           Affected airplanes                Interval (not to exceed)
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(1) Model A310-203, A310-204, and A310-  6,000 flight cycles or 12,000
 222 airplanes that have accumulated      flight hours, whichever occurs
 less than 30,000 total flight cycles     first, until the airplane
 and 60,000 total flight hours, as of     accumulates 30,000 total
 the effective date of this AD.           flight cycles or 60,000 total
                                          flight hours; then perform the
                                          inspections within the
                                          interval specified in
                                          paragraph (h)(2) of this AD.
(2) Model A310-203, A310-204, and A310-  3,900 flight cycles or 7,800
 222 airplanes that have accumulated      flight hours, whichever occurs
 30,000 total flight cycles or more or    first.
 60,000 total flight hours or more, as
 of the effective date of this AD.
(3) Model A310-304, A310-322 and A310-   4,800 flight cycles or 13,500
 324 short range airplanes that have      flight hours, whichever occurs
 accumulated less than 24,000 total       first, until the airplane
 flight cycles and 67,500 total flight    accumulates 24,000 total
 hours, as of the effective date of       flight cycles or 67,500 total
 this AD.                                 flight hours; then perform the
                                          inspections within the
                                          interval specified in
                                          paragraph (h)(4) of this AD.
(4) Model A310-304, A310-322 and A310-   3,100 flight cycles or 8,750
 324 short range airplanes that have      flight hours, whichever occurs
 accumulated 24,000 total flight cycles   first.
 or more or 67,500 total flight hours
 or more, as of the effective date of
 this AD.
(5) Model A310-304, A310-322 and A310-   3,000 flight cycles or 15,000
 324 long range airplanes that have       flight hours, whichever occurs
 accumulated less than 15,000 total       first, until the airplane
 flight cycles and 75,000 total flight    accumulates 15,000 total
 hours, as of the effective date of       flight cycles or 75,000 total
 this AD.                                 flight hours; then perform the
                                          inspections within the
                                          interval specified in
                                          paragraph (h)(6) of this AD.
(6) Model A310-304, A310-322 and A310-   1,950 flight cycles or 9,750
 324 long range airplanes that have       flight hours, whichever occurs
 accumulated 15,000 total flight cycles   first.
 or more or 75,000 total flight hours
 or more, as of the effective date of
 this AD.
------------------------------------------------------------------------

    (i) Repeat the inspections for area 2 required by paragraphs
(g)(1) and (g)(4) of this AD thereafter at the applicable intervals
specified in Table 2 of this AD. Certain compliance times are
applicable to short-range use (AFT equal to or less than 4 flight
hours), or long-range use (AFT exceeding 4 flight hours). Inspection
areas are specified in the service bulletin.

Credit for Actions Accomplished in Accordance With Previous Service
Information

    (j) Inspections accomplished before the effective date of this
AD in accordance with Airbus Mandatory Service Bulletin A310-53-

2074, Revision 03, dated October 13, 2006, are considered acceptable
for compliance with the corresponding action specified in this AD.

FAA AD Differences

    Note 2:  This AD differs from the MCAI and/or service
information as follows: The MCAI and service information do not
specify a corrective action if cracking is found and the radius of
the rework is 20.0 mm (0.787 inch) or more. Paragraph (g)(3)(i)(B)
of this AD requires repair in accordance with a method approved by
either the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate, or EASA (or its delegated agent).

Other FAA AD Provisions

    (k) 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. Send information to ATTN: Dan
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards District Office. The AMOC
approval letter must specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.

Related Information

    (l) Refer to MCAI EASA Airworthiness Directive 2009-0058, dated
March 13, 2009; and Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008; for related information.

    Issued in Renton, Washington, on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-32991 Filed 12-30-10; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 79, Number 98 (Wednesday, May 21, 2014)]
[Rules and Regulations]
[Pages 29102-29103]
[FR Doc No: 2014-11793]

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DEPARTMENT OF HOMELAND SECURITY

Coast Guard

33 CFR Part 165

[Docket No. USCG-2014-0319]

Security Zone; Portland Rose Festival on Willamette River

AGENCY: Coast Guard, DHS.

ACTION: Notice of enforcement of regulation.

-----------------------------------------------------------------------

SUMMARY: The Coast Guard will enforce the Portland Rose Festival
Security Zone from 11:00 a.m. on June 4, 2014 until 11:00 a.m. on June
9, 2014. This action is necessary to ensure the security of vessels
participating in the 2014 Portland Rose Festival on the Willamette
River during the Portland Rose festival. During the enforcement period,
no person or vessel may enter or remain in the security zone without
permission from the Sector Columbia River Captain of the Port.

DATES: The regulations in 33 CFR 165.1312 will be enforced from 11:00
a.m. on June 4, 2014 until 11:00 a.m. on June 9, 2014.

FOR FURTHER INFORMATION CONTACT: If you have questions on this notice,
call or email LTJG Ian McPhillips, Waterways Management Division, MSU
Portland, Oregon, Coast Guard; telephone<PHONE_NUMBER>, email
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION: The Coast Guard will enforce the security
zone for the Portland Rose Festival detailed in 33 CFR 165.1312 from
11:00 a.m. on June 4, 2014 until 11:00 a.m. on June 9, 2014.
    Under the provisions of 33 CFR 165.1312 and 33 CFR 165 Subpart D,
no person or vessel may enter or remain in the security zone,
consisting of all waters of the Willamette River, from surface to
bottom, encompassed by the Hawthorne and Steel Bridges, without
permission from the Sector Columbia River Captain of the Port. Persons
or vessels wishing to enter the security zone may request permission to
do so from the on scene Captain of the Port representative via VHF
Channel 16 or 13. The Coast Guard may be assisted by other Federal,
State, or local enforcement agencies in enforcing this regulation.
    This notice is issued under authority of 33 CFR 165.1312 and 5
U.S.C. 552(a). In addition to this notice in the Federal Register, the
Coast Guard will provide the maritime community with notification of
this enforcement period via the Local Notice to Mariners.

    Dated: April 29, 2014.
B.C. Jones,
Captain, U.S. Coast Guard, Captain of the Port, Sector Columbia River.
[FR Doc. 2014-11793 Filed 5-20-14; 8:45 am]
BILLING CODE 9110-04-P


[Federal Register Volume 80, Number 69 (Friday, April 10, 2015)]
[Notices]
[Page 19399]
[FR Doc No: 2015-08257]

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DEPARTMENT OF TRANSPORTATION

National Highway Traffic Safety Administration

Retooling Recalls Workshop

AGENCY: National Highway Traffic Safety Administration (NHTSA),
Department of Transportation (DOT).

ACTION: Announcement of public workshop.

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SUMMARY: The National Highway Traffic Safety Administration (NHTSA) is
announcing a workshop that will be held in Washington, DC on April 28,
2015 to discuss options to improve vehicle safety recall completion
rates. The workshop will include brief NHTSA presentations outlining
recent agency activities aimed at improving recall completion rates as
well as recent examples of steps vehicle manufacturers have taken.
Information on the date, time, location, and framework for this public
event is included in this notice. Attendance requires prior
registration; there will be no registration at the door. There are no
fees to register or to attend this event.

DATES: The workshop will be held on April 28, 2015, at the location
indicated in the ADDRESSES section below. The workshop will start at
9:00 a.m. and is scheduled to continue until 5:00 p.m., local time. If
you would like to register to attend the workshop, please contact the
person identified under FOR FURTHER INFORMATION CONTACT no later than
April 21, 2015. Registrations may be accepted after that date, space
permitting.

ADDRESSES: The April 28, 2015 workshop will be held in the Media Center
of the U.S. Department of Transportation, 1200 New Jersey Avenue SE.,
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: If you would like to attend the
workshop, please contact Heather Laca by the date specified under DATES
section above, at: Telephone<PHONE_NUMBER>; email address:
<EMAIL_ADDRESS>Please provide her with the following
information: Name, title, affiliation, address, email address, and
telephone number, and indicate whether you require accommodations such
as a sign language interpreter or translator. If you are not a U.S.
citizen, also provide your country of citizenship, date of birth, title
or position, and passport or diplomatic ID number, along with
expiration date.

SUPPLEMENTARY INFORMATION: NHTSA is hosting a public workshop to
discuss options to improve vehicle safety recall completion rates.
    NHTSA marked a record year in 2014, with the highest number of
vehicle recalls in more than three decades. Last year alone, there were
803 vehicle recalls involving 63.9 million vehicles, including two of
the largest vehicle recalls in history.
    The sessions will focus on public education of the recall process;
customer and dealership outreach; parts production challenges and
recall repair rates. The input gathered by the working groups will be
used to identify best practices and new approaches for improving the
recall process.
    Workshop Procedures. NHTSA will conduct the workshop informally.
Thus, technical rules of evidence will not apply. The workshop will
include brief presentations and panel discussions with representatives
from NHTSA, automobile manufacturers, suppliers, and dealers. There
will be opportunities for attendees to ask questions of NHTSA and of
the panelists.
    To attend this workshop, please register with NHTSA by the date
specified under the DATES section above by sending the required
information to the person listed in the FOR FURTHER INFORMATION CONTACT
section. Registration is necessary for security and space limitation
reasons. After registration, NHTSA will send attendees follow-up
information regarding workshop day logistics (i.e., directions to the
building, parking accommodations, etc.).
    For security purposes, photo identification is required to enter
the Department of Transportation building. To allow sufficient time to
clear security and enter the building, NHTSA recommends that workshop
participants arrive 30 to 60 minutes prior to the start of the event.

    Authority: 49 U.S.C. 30118-30120; 49 U.S.C. 30181-30182; 49 CFR
573 and 577.

    Dated: April 3, 2015.
Mark R. Rosekind,
Administrator.
[FR Doc. 2015-08257 Filed 4-9-15; 8:45 am]
BILLING CODE 4910-59-P


[Federal Register Volume 83, Number 126 (Friday, June 29, 2018)]
[Notices]
[Pages 30812-30813]
[FR Doc No: 2018-13972]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

[Summary Notice No. PE-2018-54]

Petition for Exemption; Summary of Petition Received; Victor Lee
& Associates Inc.

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice.

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SUMMARY: This notice contains a summary of a petition seeking relief
from specified requirements of Title 14 of the Code of Federal
Regulations. The purpose of this notice is to improve the public's
awareness of, and participation in, the FAA's exemption process.
Neither publication of this notice nor the inclusion or omission of
information in the summary is intended to affect the legal status of
the petition or its final disposition.

DATES: Comments on this petition must identify the petition docket
number and must be received on or before July 19, 2018.

ADDRESSES: Send comments identified by docket number FAA-2018-0183
using any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the online instructions for sending your
comments electronically.
     Mail: Send comments to Docket Operations, M-30; U.S.
Department of Transportation (DOT), 1200 New Jersey Avenue SE, Room
W12-140, West Building, Ground Floor, Washington, DC 20590-0001.
     Hand Delivery or Courier: Take comments to Docket
Operations in Room W12-140 of the West Building Ground Floor at 1200
New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
     Fax: Fax comments to Docket Operations at<PHONE_NUMBER>.

    Privacy: In accordance with 5 U.S.C. 553(c), DOT solicits comments
from the public to better inform its rulemaking process. DOT posts
these comments, without edit, including any personal information the
commenter provides, to http://www.regulations.gov, as described in the
system of records notice (DOT/ALL-14 FDMS), which can be reviewed at
http://www.dot.gov/privacy.
    Docket: Background documents or comments received may be read at
http://www.regulations.gov at any time. Follow the online instructions
for accessing the docket or go to the Docket Operations in Room W12-140
of the West Building Ground Floor at 1200 New Jersey Avenue SE,
Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Jake Troutman,<PHONE_NUMBER>, 800
Independence Avenue SW, Washington, DC 20591.
    This notice is published pursuant to 14 CFR 11.85.

    Issued in Washington, DC, on June 22, 2018.
Lirio Liu,
Director, Office of Rulemaking.

Petition for Exemption

    Docket No.: FAA-2018-0183.
    Petitioner: Victor Lee & Associates Inc.
    Section(s) of 14 CFR Affected: Part 21; Sec. Sec.  45.23(b);
61.113(a) and (b); 91.7(a); 91.9(b)(2); 91.103; 91.105; 91.109; 91.119;
91.121; 91.151(a); 91.203(a) and (b); 91.405(a); 91.407(a)(1);
91.409(a)(2); and 91.417(a) and (b).
    Description of Relief Sought: The petitioner is requesting relief
in order to operate the Shotover U-1 unmanned aircraft system, weighing
approximately 89 pounds, for the purpose of conducting aerial
photography and videography operations. The proposed operation will
occur: During the day time; within visual line of sight of the pilot-
in-command, at or below 400 feet above ground level; with geo fencing;
and on private property in the United States of America.

[FR Doc. 2018-13972 Filed 6-28-18; 8:45 am]
 BILLING CODE 4910-13-P