[Federal Register Volume 79, Number 156 (Wednesday, August 13, 2014)]
[Proposed Rules]
[Pages 47395-47401]
[FR Doc No: 2014-19157]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0529; Directorate Identifier 2013-NM-260-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) 2011-13-
11 and AD 2013-16-09, for all Airbus Model A318, A319, A320, and A321
series airplanes. AD 2011-13-11 currently requires an amendment of the
airplane flight manual (AFM), repetitive checks of specific centralized
fault display system (CFDS) messages, an inspection of the opening
sequence of the main landing gear (MLG) door actuator for discrepancies
if certain messages are found, and corrective actions if necessary. AD
2013-16-09

currently requires an inspection to determine airplane configuration
and part numbers of the landing gear control interface unit and MLG
door actuators; and, for affected airplanes, repetitive inspections of
the opening sequence of the MLG door actuator, and replacement of the
MLG door actuator if necessary; and provides optional terminating
action for the repetitive inspections. Since we issued AD 2011-13-11
and AD 2013-16-09, we have determined that the interval of the MLG door
opening sequence inspection must be reduced. This proposed AD would
reduce the interval of the MLG door opening sequence inspection. This
proposed AD would also require replacing or modifying certain MLG door
actuators. We are proposing this AD to detect and correct deterioration
of the damping ring and associated retaining ring of the MLG door
actuator, which can sufficiently increase the friction inside the
actuator to restrict opening of the MLG door by gravity, during
operation of the landing gear alternate (free-fall) extension system.
This condition could prevent the full extension and/or down-locking of
the MLG, possibly resulting in MLG collapse during landing and
consequent damage to the airplane and injury to occupants.

DATES: We must receive comments on this proposed AD by September 29,
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 Airbus 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. For General Electric service information
identified in this AD contact GE Aviation, Customer Support Center, 1
Neumann Way, Cincinnati, OH 45215; phone:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>Internet: http://www.geaviation.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<PHONE_NUMBER>.

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-
0529; 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-2014-0529;
Directorate Identifier 2013-NM-260-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 June 16, 2011, we issued AD 2011-13-11, Amendment 39-16734 (76
FR 37241, June 27, 2011). AD 2011-13-11 required actions intended to
address an unsafe condition on all Airbus Model A318, A319, A320, and
A321 series airplanes. The unsafe condition is the deterioration of the
damping ring and associated retaining ring of the MLG door actuator,
which can sufficiently increase the friction inside the actuator to
restrict opening of the MLG door by gravity, during operation of the
landing gear alternate (free-fall) extension system. This condition
could prevent the full extension and/or down-locking of the MLG,
possibly resulting in MLG collapse during landing and consequent damage
to the airplane and injury to occupants.
    On July 26, 2013, we issued AD 2013-16-09, Amendment 39-17547 (78
FR 48286, August 8, 2013). AD 2013-16-09 required actions intended to
detect and correct certain configuration of landing gear control
interface unit and actuators, which could prevent the full extension or
down-locking of the MLG, possibly resulting in MLG collapse during
landing and consequent damage to the airplane and injury to occupants
on all Airbus Model A318, A319, A320, and A321 series airplanes.
    Since we issued AD 2011-13-11, Amendment 39-16734 (76 FR 37241.
June 27, 2011), and AD 2013-16-09, Amendment 39-17547 (78 FR 48286,
August 8, 2013), we have determined that the interval of the MLG door
opening sequence inspection must be reduced in order to detect and
correct deterioration of the damping ring and associated retaining ring
of the MLG door actuator, which can sufficiently increase the friction
inside the actuator to restrict opening of the MLG door by gravity,
during operation of the landing gear alternate (free-fall) extension
system. This condition, if not detected and corrected, could prevent
the full extension and/or down-locking of the MLG, possibly resulting
in MLG collapse during landing and consequent damage to the airplane
and injury to occupants.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0288, dated December 6, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:

    Some operators reported slow operation of the main landing gear
(MLG) door opening/closing sequence, leading to the generation of
ECAM warnings during the landing gear retraction or extension
sequence.
    Investigations showed that the damping ring and associated
retaining ring of the MLG door actuator deteriorate. The resultant
debris increases the friction inside the actuator which can be
sufficiently high to restrict opening of the MLG door by gravity,
during operation of the landing gear alternate (free-fall) extension
system.

    This condition, if not corrected, could prevent the full
extension and/or down locking of the MLG, possibly resulting in MLG
collapse during landing or rollout and consequent damage to the
aeroplane and injury to occupants.
    EASA AD 2006-0112R1 (http://ad.easa.europa.eu/blob/easa_ad_2006_0112_R1_superseded.pdf/AD_2006-0112R1_1) was issued to
require repetitive inspections of the opening sequence of the MLG
door in order to identify the defective actuators, and to introduce
as an optional terminating action Airbus production Modification
(MOD) 38274 and associated Service Bulletin (SB) A320-32-1338, which
incorporate an improved retaining ring, located on the piston rod's
extension end, and a new piston rod with machined shoulder to
accommodate the thicker section of the modified retaining ring.
    After in-service introduction of the new MLG door actuator, Part
Number (P/N) 114122012 (Post MOD 38274--SB A320-32-1338), several
operators reported failures of internal parts of the MLG door
actuator. Investigations confirmed that these failures could result
in slow extension of the actuator rod, delaying the MLG door
operation, or possibly stopping just before the end of the stroke,
preventing the door to reach the fully open position.
    EASA AD 2011-0069R1 (http://ad.easa.europa.eu/blob/easa--ad--
2011--0069--R1--superseded.pdf/AD--2011-0069R1--1) (which
corresponds to FAA AD 2011-13-11, Amendment 39-16734 (76 FR 37241,
June 27, 2011)), which supersedes EASA AD 2006-0112R1 required an
amendment of the applicable Airplane Flight Manual (AFM), repetitive
checks of specific Centralized Fault Display System (CFDS) messages,
repetitive inspections of the opening sequence of the MLG door
actuator and, depending on findings, corrective action(s).
    Since that [EASA] AD was issued, Airbus introduced a reinforced
MLG door actuator P/N 114122014 (MOD 153655). Airbus issued SB A320-
32-1407 containing instructions for in-service replacement of the
affected MLG door actuators, or modification of the actuators to the
new standard.
    In addition, following a recent occurrence with a gear extension
problem, the result of additional analyses by Airbus revealed that
the CFDS expected specific messages may not be generated and as a
result, repetitive checks of messages are not effective for
aeroplanes fitted with landing gear control interface unit (LGCIU)
interlink communication ARINC 429 (applied in production through
Airbus MOD 39303, or in service through Airbus SB A320-32-1409), in
combination with LGCIUs 80-178-02-88012 or 80-178-03-88013 in both
positions and at least one MLG door actuator pre MOD 153655 (SB
A320-32-1407--SB 114122-32-105) installed.
    Prompted by these findings, EASA issued Emergency AD 2013-0132-E
(http://ad.easa.europa.eu/blob/easa_ad_2013_0132_E_superseded.pdf/EAD_2013-0132-E_1) (which corresponds to FAA AD
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013)) to
require identification of the affected aeroplanes to establish the
configuration and, for those aeroplanes, repetitive inspections of
the opening sequence of the MLG door actuator and, depending on
findings, replacement of the MLG door actuator. That [EASA] AD also
provided an optional terminating action by disconnection of the
interlink for certain LGCIUs, or in-service modification of the
aeroplane through Airbus SB A320-32-1407 (equivalent to production
MOD 153655).
    Since those [EASA] ADs were issues, analyses performed by Airbus
have revealed that the MLG door opening sequence inspection interval
must be reduced, and that the (previously optional) terminating
action must be made mandatory.
    For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2011-0069R1 and [EASA] AD 2013-0132-E, which
are superseded, but with reduced inspection intervals, and requires
replacement or modification [including related investigative and
corrective actions], as applicable, of the affected MLG door
actuators as terminating action for the monitoring, repetitive
checks and inspections.

    The related investigative actions include an inspection for damage
(including nicks and burns) of the damping rings and an inspection for
mechanical damage of the piston rod. Corrective actions include
replacing or modifying parts. You may examine the MCAI in the AD docket
on the Internet at http://www.regulations.gov by searching for and
locating it in Docket No. FAA-2014-0529.

Relevant Service Information

    Airbus has issued Service Bulletin A320-32-1390, Revision 02, dated
October 23, 2013; and General Electric has issued Service Bulletin
114122-32-105, Revision 1, dated March 26, 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

    Paragraph (17) of the MCAI incorrectly refers to paragraph (11) of
the MCAI as requiring inspections; however, paragraph (11) of the MCAI
specifies replacement actions. Paragraphs (j), (l), and (p) of this
proposed AD refer to the inspections specified in paragraph (17) of the
MCAI.

``Contacting the Manufacturer'' Paragraph in This Proposed AD

    Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
    The MCAI or referenced service information in an FAA AD often
directs the owner/operator to contact the manufacturer for corrective
actions, such as a repair. Briefly, the Airworthy Product paragraph
allowed owners/operators to use corrective actions provided by the
manufacturer if those actions were FAA-approved. In addition, the
paragraph stated that any actions approved by the State of Design
Authority (or its delegated agent) are considered to be FAA-approved.
    In an NPRM having Directorate Identifier 2012-NM-101-AD (78 FR
78285, December 26, 2013), we proposed to prevent the use of repairs
that were not specifically developed to correct the unsafe condition,
by requiring that the repair approval provided by the State of Design
Authority or its delegated agent specifically refer to the FAA AD. This
change was intended to clarify the method of compliance and to provide
operators with better visibility of repairs that are specifically
developed and approved to correct the unsafe condition. In addition, we
proposed to change the phrase ``its delegated agent'' to include a
design approval holder (DAH) with State of Design Authority design
organization approval (DOA), as applicable, to refer to a DAH
authorized to approve required repairs for the proposed AD.
    One commenter to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) stated the following: ``The
proposed wording, being specific to repairs, eliminates the
interpretation that Airbus messages are acceptable for approving minor
deviations (corrective actions) needed during accomplishment of an AD
mandated Airbus service bulletin.''
    This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product

paragraph does not approve messages or other information provided by
the manufacturer for deviations to the requirements of the AD-mandated
actions. The Airworthy Product paragraph only addresses the requirement
to contact the manufacturer for corrective actions for the identified
unsafe condition and does not cover deviations from other AD
requirements. However, deviations to AD-required actions are addressed
in 14 CFR 39.17, and anyone may request the approval for an alternative
method of compliance to the AD-required actions using the procedures
found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this proposed AD to obtain corrective actions
from a manufacturer, the actions must be accomplished using a method
approved by the FAA, EASA, or Airbus's EASA DOA.
    The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
    This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.

Revisions to Notes in AD 2011-13-11, Amendment 39-16734 (76 FR 37241,
June 27, 2011)

    We have removed Note 1 of AD 2011-13-11, Amendment 39-16734 (76 FR
37241, June 27, 2011), and included that information in paragraph
(g)(3) of this proposed AD.
    We have removed Note 2 of AD 2011-13-11, Amendment 39-16734 (76 FR
37241, June 27, 2011), and included that information in paragraph (i)
of this proposed AD.
    We have removed Note 3 of AD 2011-13-11, Amendment 39-16734 (76 FR
37241, June 27, 2011), from this proposed AD. The note explained
differences with the previous MCAI.

Change to AD 2013-16-09, Amendment 39-17547 (78 FR 48286, August 8,
2013)

    We have moved the information specified in paragraph (l) of AD
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), into
paragraphs (j) and (l) of this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S.
registry.
    The actions that are required by AD 2011-13-11, Amendment 39-16734
(76 FR 37241, June 27, 2011), and retained in this proposed AD take
about 7 work-hours per product, per inspection cycle, 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 2011-13-11 is $595 per
product.
    The actions that are required by AD 2013-16-09, Amendment 39-17547
(78 FR 48286, August 8, 2013), and retained in this proposed AD take
about 3 work-hours per product, per inspection cycle, at an average
labor rate of $85 per work-hour. Based on these figures, the estimated
cost of the actions that were required by AD 2013-16-09 is $255 per
product.
    We also estimate that it would take about 10 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about
$17,140 for two actuators. Based on these figures, we estimate the cost
of this proposed AD on U.S. operators to be $15,309,490, or $17,990 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:
0
a. Removing Airworthiness Directive (AD) 2011-13-11, Amendment 39-16734
(76 FR 37241, June 27, 2011); and AD 2013-16-09, Amendment 39-17547 (78
FR 48286, August 8, 2013); and
0
b. Adding the following new AD:

Airbus: Docket No. FAA-2014-0529; Directorate Identifier 2013-NM-
260-AD.

(a) Comments Due Date

    We must receive comments by September 29, 2014.

(b) Affected ADs

    This AD replaces AD 2011-13-11, Amendment 39-16734 (76 FR 37241,
June 27, 2011); and AD 2013-16-09, Amendment 39-17547 (78 FR 48286,
August 8, 2013).

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1), (c)(2), (c)(3), and
(c)(4) of this AD, all manufacturer serial numbers.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing
Gear.

(e) Reason

    This AD was prompted by a determination that the inspection
interval of the MLG door opening sequence must be reduced. We are
issuing this AD to detect and correct deterioration of the damping
ring and associated retaining ring of the MLG door actuator, which
can sufficiently increase the friction inside the actuator to
restrict opening of the MLG door by gravity, during operation of the
landing gear alternate (free-fall) extension system. This condition
could prevent the full extension and/or down-locking of the MLG,
possibly resulting in MLG collapse during landing and consequent
damage to the aeroplane and injury to occupants.

(f) Compliance

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

(g) Retained Repetitive Inspections/Replacement

    This paragraph restates the requirements of paragraph (g) of AD
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with a
formatting change. At the time specified in paragraph (g)(1) or
(g)(2) of this AD, as applicable: Do a general visual inspection of
the operation of the MLG door opening sequence to determine if a
defective actuator is installed by doing all the applicable actions,
including replacing the door actuator, as applicable, specified in
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1309, Revision 01, dated June 19, 2006. Do all applicable
replacements before further flight. Repeat the inspection thereafter
at intervals not to exceed 900 flight cycles. Accomplishing the
actions before April 27, 2007 (the effective date of AD 2007-06-18,
Amendment 39-14999 (72 FR 13681, March 23, 2007)), in accordance
with Airbus Service Bulletin A320-32-1309, dated March 7, 2006, is
acceptable for compliance with the corresponding requirements in
this paragraph. Doing the inspection required by paragraph (l) of
this AD terminates the requirements of this paragraph.
    (1) For airplanes on which a record of the total number of
flight cycles on the MLG door actuator is available: Before the
accumulation of 3,000 total flight cycles on the MLG door actuator,
or within 800 flight cycles after April 27, 2007 (the effective date
of AD 2007-06-18, Amendment 39-16734 (76 FR 37241, June 27, 2011)),
whichever is later.
    (2) For airplanes on which a record of the total number of
flight cycles on the MLG door actuator is not available: Within 800
flight cycles after April 27, 2007 (the effective date of AD 2007-
06-18, Amendment 39-16734 (76 FR 37241, June 27, 2011)).
    (3) For the purposes of this AD, a general visual inspection is:
``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
enhance visual access to all exposed surfaces in the inspection
area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight,
or droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''

(h) Retained Provision Regarding Reporting/Parts Return

    This paragraph restates the requirements of paragraph (h) of AD
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with no
changes. Although the Accomplishment Instructions of Airbus Service
Bulletin A320-32-1309, Revision 01, dated June 19, 2006, specify
submitting certain information to the manufacturer and sending
defective actuators back to the component manufacturer for
investigation, this AD does not include those requirements.

(i) Retained Revision of the Airplane Flight Manual (AFM)

    This paragraph restates the requirements of paragraph (i) of AD
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with
formatting changes. Within 14 days after July 12, 2011 (the
effective date of AD 2011-13-11), revise the Emergency Procedure
Section of the AFM to incorporate the information in figure 1 to
paragraph (i) of this AD. This may be done by inserting a copy of
this AD into the AFM. When a statement identical to that in figure 1
to paragraph (i) of this AD has been included in the Emergency
Procedure Section of the general revisions of the AFM, the general
revisions may be inserted into the AFM, and the copy of this AD may
be removed from the AFM.

           Figure 1 to Paragraph (i) of This AD--AFM Revision
------------------------------------------------------------------------

-------------------------------------------------------------------------
 If ECAM triggers the ``L/G GEAR NOT DOWNLOCKED'' warning apply
 the following procedure:
    Recycle landing gear.
 If unsuccessful after 2 min:
    Extend landing gear by gravity. Refer to AGN-32 L/G GRAVITY
     EXTENSION.
------------------------------------------------------------------------

(j) Retained Repetitive Checks

    This paragraph restates the requirements of paragraph (j) of AD
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with
new optional actions. Within 14 days after July 12, 2011 (the
effective date of AD 2011-13-11), or before the accumulation of 800
total flight cycles, whichever occurs later, check the post flight
report (PFR) for centralized fault display system (CFDS) messages
triggered within the last 8 days, in accordance with paragraph 4.2.1
of Airbus All Operators Telex (AOT) A320-32A1390, dated February 10,
2011. Repeat the check thereafter at intervals not to exceed 8 days
or 5 flight cycles, whichever occurs later. If done in accordance
with a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA, the use of an alternative
method to check the PFR for CFDS messages (e.g., AIRMAN) is
acceptable in lieu of this check if the messages can be conclusively
determined from that method. Repetitive inspections of the door
opening sequence of the left-hand (LH) and right-hand (RH) doors of
the MLG, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A320-32-1390, Revision 02, dated
October 23, 2013, are an acceptable method of compliance for the
actions required by this paragraph. Repetitive inspections of the
door opening sequence of the LH and RH doors of the MLG of an
airplane, as required by paragraph (p) of this AD, is an acceptable
method to comply with the requirements of this paragraph.

(k) Retained On-Condition Inspection

    This paragraph restates the requirements of paragraph (k) of AD
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with
new service information. If, during any check required by paragraph
(j) of this AD, a pair of specific CFDS messages specified in
paragraph 4.2.1 of Airbus AOT A320-32A1390, dated February 10, 2011,
has been triggered by both landing gear control and indication units
(LGCIU) for the same flight, before further flight, inspect the door
opening sequence of the affected doors of the MLG for discrepancies
(i.e., if any condition specified in steps (a) through (d) of
paragraph 4.2.2 of Airbus AOT A320-32A1390, dated February 10, 2011,
is not met; or if any door actuator fails any inspection check
specified in Airbus Service Bulletin A320-32-1390,

Revision 02, dated October 23, 2013). Do the inspection in
accordance with paragraph 4.2.2 of Airbus AOT A320-32A1390, dated
February 10, 2011; or Airbus Service Bulletin A320-32-1390, Revision
02, dated October 23, 2013. As of the effective date of this AD, use
only Airbus Service Bulletin A320-32-1390, Revision 02, dated
October 23, 2013, for the actions required by this paragraph.

(l) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (l) of AD
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with
new service information, new optional actions, and reduced
compliance times. At the applicable time specified in paragraph
(l)(1) or (l)(2) of this AD: Inspect the door opening sequence of
the LH and RH doors of the MLG for discrepancies (i.e., if any
condition specified in steps (a) through (d) of paragraph 4.2.2 of
Airbus AOT A320-32A1390, dated February 10, 2011, is not met; or if
any door actuator fails any inspection check specified in Airbus
Service Bulletin A320-32-1390, Revision 02, dated October 23, 2013).
Do the inspection in accordance with the instructions of paragraph
4.2.2 of Airbus AOT A320-32A1390, dated February 10, 2011; or Airbus
Service Bulletin A320-32-1390, Revision 02, dated October 23, 2013.
As of the effective date of this AD, use only Airbus Service
Bulletin A320-32-1390, Revision 02, dated October 23, 2013. Repeat
the inspection within 8 days or 5 flight cycles after the effective
date of this AD, whichever occurs later, without exceeding 425
flight cycles since the most recent inspection; and thereafter
repeat the inspection at intervals not to exceed 8 days or 5 flight
cycles, whichever occurs later. In addition, whenever any airplane
is not operated for a period longer than 8 days, do the inspection
before further flight. Doing this inspection terminates the
requirements of paragraph (g) of this AD. Repetitive inspections of
the door opening sequence of the LH and RH doors of the MLG of an
airplane, as required by paragraph (p) of this AD, is an acceptable
method to comply with the requirements of this paragraph.
    (1) For airplanes on which an inspection required by paragraph
(g) of this AD has been done as of July 12, 2011 (the effective date
of AD 2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011)):
Within 800 flight cycles after doing the most recent inspection
required by paragraph (g) of this AD, or within 100 flight cycles
after July 12, 2011 (the effective date of AD 2011-13-11, Amendment
39-16734 (76 FR 37241, June 27, 2011)), whichever occurs later.
    (2) For airplanes on which an inspection required by paragraph
(g) of this AD has not been done as of July 12, 2011 (the effective
date of AD 2011-13-11, Amendment 39-16734 (76 FR 37241, June 27,
2011)): Within 800 flight cycles after July 12, 2011.

(m) Retained Replacement

    This paragraph restates the requirements of paragraph (m) of AD
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with
new service information. If any discrepancy (i.e., if any condition
specified in steps (a) through (d) of paragraph 4.2.2 of Airbus AOT
A320-32A1390, dated February 10, 2011, is not met; or if any door
actuator fails any inspection check specified in Airbus Service
Bulletin A320-32-1390, Revision 02, dated October 23, 2013) is found
during any inspection required by paragraph (k) or (l) of this AD,
before further flight, replace the affected MLG door actuator with a
new MLG door actuator, in accordance with the instructions of Airbus
AOT A320-32A1390, dated February 10, 2011; or Airbus Service
Bulletin A320-32-1390, Revision 02, dated October 23, 2013. As of
the effective date of this AD, use only Airbus Service Bulletin
A320-32-1390, Revision 02, dated October 23, 2013, to do the actions
required by this paragraph.

(n) Retained: No Terminating Action for Certain Requirements

    This paragraph restates the statement of paragraph (n) of AD
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011), with no
changes. Replacement of the MLG door actuator as required by
paragraph (m) of this AD is not a terminating action for the
repetitive actions required by paragraphs (j) and (l) of this AD.

(o) Retained Configuration and Part Number Determination

    This paragraph restates the requirements of paragraph (g) of AD
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), with
no changes. At the later of the compliance times specified in
paragraphs (o)(1) and (o)(2) of this AD: Do an inspection to
determine the configuration (modification status) of the airplane
and identify the part number of the LH and RH LGCIU and MLG door
actuators. A review of the airplane delivery or maintenance records
is acceptable for compliance with the requirements of this paragraph
provided the airplane configuration and installed components can be
conclusively determined from that review.
    (1) Prior to the accumulation of 800 total flight cycles since
first flight of the airplane.
    (2) Within 14 days after August 23, 2013 (the effective date of
AD 2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013)).

(p) Retained MLG Door Opening Sequence Repetitive Inspections

    This paragraph restates the requirements of paragraph (h) of AD
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), with
no changes. If, during the determination and identification required
by paragraph (o) of this AD, the configuration of the airplane is
determined to be post-Airbus modification 39303 or post-Airbus
Service Bulletin A320-32-1409 (Interlink Communication ARINC 429
installed), and both an LGCIU and a MLG door actuator are installed
with a part number listed in table 1 to paragraph (p) of this AD:
Except as provided by paragraph (s) of this AD, at the later of the
compliance times specified in paragraphs (o)(1) and (o)(2) of this
AD, and thereafter at intervals not to exceed 8 days or 5 flight
cycles, whichever occurs later, do an inspection of the door opening
sequence of the LH and RH MLG doors, in accordance with the
instructions of Airbus Alert Operators Transmission (AOT) A32N001-
13, dated June 24, 2013.

                   Table 1 to Paragraph (p) of This AD
------------------------------------------------------------------------
                    Component name                        Part number
------------------------------------------------------------------------
LGCIU (LH and RH)....................................    80-178-02-88012
LGCIU (LH and RH)....................................    80-178-03-88013
MLG door actuator....................................          114122006
MLG door actuator....................................          114122007
MLG door actuator....................................          114122009
MLG door actuator....................................          114122010
MLG door actuator....................................          114122011
MLG door actuator....................................          114122012
------------------------------------------------------------------------

(q) Retained MLG Door Opening Sequence Corrective Action

    This paragraph restates the requirements of paragraph (i) of AD
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), with
no changes. If a slow door operation or restricted extension is
found during any inspection required by paragraph (p) of this AD:
Before further flight, replace the affected MLG door actuator with a
new or serviceable actuator, in accordance with the instructions of
Airbus AOT A32N001-13, dated June 24, 2013.

(r) Retained Terminating Action Limitation for Certain Actions

    This paragraph restates the requirements of paragraph (j) of AD
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), with
no changes. Replacement of a MLG door actuator, as required by
paragraph (q) of this AD, does not constitute terminating action for
the repetitive inspections required by paragraph (p) of this AD,
unless MLG door actuators having P/N 114122014 are installed on both
LH and RH sides, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-32-1407, dated May 14, 2013.

(s) Retained Repetitive Inspection Exception

    This paragraph restates the requirements of paragraph (k) of AD
2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 2013), with
no changes. Airplanes on which the LGCIU interlink is disconnected
(Airbus modification 155522 applied in production, or modified in-
service in accordance with the instructions of Airbus AOT A32N001-
13, dated June 24, 2013), or on which MLG door actuators having P/N
114122014 are installed on both LH and RH sides (Airbus modification
153655 applied in production, or modified in-service in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-32-1407, dated May 14, 2013), are not required to do the
actions required by paragraph (p) of this AD, provided that the
airplane is not modified to a configuration as defined in paragraph
(p) of this AD.

(t) New Replacement of MLG Door Actuator having P/N 114122012

    Within 12 months after the effective date of this AD: Replace
each MLG door actuator having P/N 114122012 with a MLG door actuator
having P/N 14122014, in accordance with the Accomplishment
Instructions of

Airbus Service Bulletin A320-32-1407, dated May, 14 2013; or modify
each actuator, including doing all applicable related investigative
and corrective actions; in accordance with the Accomplishment
Instructions of General Electric Service Bulletin 114122-32-105,
Revision 1, dated March 26, 2013; except where General Electric
Service Bulletin114122-32-105, Revision 1, dated March 26, 2013,
specifies to contact the manufacturer, before further flight, repair
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.

(u) New Replacement of Certain Other MLG Door Actuators

    Within 24 months after the effective date of this AD: Replace
each MLG door actuator having a part number listed in table 1 to
paragraph (p) of this AD, except P/N 114122012, with a MLG door
actuator having P/N 14122014, in accordance with Accomplishment
Instructions of Airbus Service Bulletin A320-32-1407, dated May 14,
2013; or modify each actuator, including doing all applicable
related investigative and corrective actions; in accordance with the
Accomplishment Instructions of General Electric Service Bulletin
114122-32-105, Revision 1, dated March 26, 2013; except where
General Electric Service Bulletin 114122-32-105, Revision 1, dated
March 26, 2013, specifies to contact the manufacturer, before
further flight, repair 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 DOA.
If approved by the DOA, the approval must include the DOA-authorized
signature.

(v) New Terminating Action

    Modification of an airplane as required by paragraphs (t) and
(u) of this AD, as applicable, constitutes terminating action for
all repetitive actions (PFR monitoring checks and inspections)
required by this AD for that airplane.

(w) New Conditional Terminating Action

    Replacement of a MLG door actuator as required by paragraphs (m)
and (q) of this AD; or corrective actions as specified in Airbus AOT
A320-32A1390, dated February 10, 2011; or replacement of a MLG door
actuator as specified in Airbus Service Bulletin A320-32-1390,
Revision 1, dated September 21, 2011; do not constitute terminating
action for the repetitive inspections required by paragraphs (j),
(l), and (p) of this AD, unless MLG door actuators having P/N
114122014 are installed on both LH and RH sides, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1407, dated May 14, 2013.

(x) New Exception to AD Requirements

    An airplane on which MLG door actuators having P/N 114122014 are
installed on both LH and RH sides (Airbus MOD 153655 applied in
production, or modified in service as specified in Airbus Service
Bulletin A320-32-1407, dated May, 14 2013; General Electric Service
Bulletin 114122-32-105, dated January 17, 2013; or General Electric
Service Bulletin 114122-32-105, Revision 1, dated March 26, 2013; is
not affected by the requirements of paragraphs (j) through (u) of
this AD, provided that no MLG door actuator with a part number in
table 1 to paragraph (p) of this AD has been installed on that
airplane since first flight, or since modification, as applicable.

(y) New Parts Installation Prohibitions

    (1) Except as specified in paragraph (y)(2) of this AD, as of
the effective date of this AD, do not install on any airplane a MLG
door actuator, having a part number listed in table 1 to paragraph
(p) of this AD.
    (2) For an airplane subject to the requirements of paragraphs
(t) and (u) of this AD, as applicable, do not install a MLG door
actuator having a part number listed in table 1 to paragraph (p) of
this AD after modification of the airplane.

(z) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by
paragraphs (k), (l), and (m) of this AD, if those actions were
performed before the effective date of this AD using Airbus
Mandatory Service Bulletin A320-32-1390, Revision 01, dated
September 21, 2011, which is not incorporated by reference in this
AD.
    (2) This paragraph provides credit for actions required by
paragraphs (t) and (u) of this AD, if those actions were performed
before the effective date of this AD using General Electric Service
Bulletin 114122-32-105, dated January 17, 2013, which is not
incorporated by reference in this AD.

(aa) 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>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) Contacting the Manufacturer: Except as specified in
paragraph (j) of this AD for the use of an alternative method to
check the PFR for CFDS messages, 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.
    (3) Previously Approved AMOCs: AMOCs approved previously for the
ADs identified in paragraphs (aa)(3)(i) and (aa)(3)(ii) of this AD,
are approved as AMOCs for the corresponding provisions of this AD.
    (i) AD 2011-13-11, Amendment 39-16734 (76 FR 37241, June 27,
2011).
    (ii) AD 2013-16-09, Amendment 39-17547 (78 FR 48286, August 8,
2013).

(bb) Special Flight Permits

    Special flight permits may be issued in accordance with sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate the airplane to a location where the airplane
can be modified (if the operator elects to do so), provided the MLG
remains extended and locked, and that no MLG recycle is done.

(cc) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0288, dated December 6,
2013, 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-2014-0529.
    (2) For Airbus 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.
    (3) For General Electric service information identified in this
AD, contact GE Aviation, Customer Support Center, 1 Neumann Way,
Cincinnati, OH 45215; phone:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>Internet: http://www.geaviation.com.
    (4) 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 August 1, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-19157 Filed 8-12-14; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register: October 25, 2010 (Volume 75, Number 205)]
[Notices]
[Page 65469-65470]
[DOCID:fr25oc10-39]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

Combined Notice of Filings

October 14, 2010.
    Take notice that the Commission has received the following Natural
Gas Pipeline Rate and Refund Report filings:

    Docket Numbers: RP11-59-000.
    Applicants: Northwest Pipeline GP.
    Description: Northwest Pipeline GP submits a Non-Conforming Service
Agreement, Contract 138587 as part of its FERC Gas Tariff, Fifth
Revised Volume No. 1, to be effective 11/8/2010.
    Filed Date: 10/13/2010.
    Accession Number: 20101013-5089.
    Comment Date: 5 p.m. Eastern Time on Monday, October 25, 2010.

    Docket Numbers: RP11-60-000.
    Applicants: Southern Natural Gas Company.
    Description: Southern Natural Gas Company submits tariff filing per
154.204: Miscellaneous Filing 2 to be effective 12/1/2010.
    Filed Date: 10/13/2010.
    Accession Number: 20101013-5094.
    Comment Date: 5 p.m. Eastern Time on Monday, October 25, 2010.

    Docket Numbers: RP11-61-000.
    Applicants: Colorado Interstate Gas Company.
    Description: Colorado Interstate Gas Company submits tariff filing
per 154.203: CP10-434-000 Latigo Compliance Filing to be effective 10/
1/2010.
    Filed Date: 10/13/2010.
    Accession Number: 20101013-5128.
    Comment Date: 5 p.m. Eastern Time on Monday, October 25, 2010.

    Docket Numbers: RP11-62-000.
    Applicants: Columbia Gulf Transmission Company.
    Description: Columbia Gulf Transmission Company submits tariff
filing per 154.204: Evergreen Non-Conforming 10.13.10 to be effective
11/15/2010.
    Filed Date: 10/13/2010.
    Accession Number: 20101013-5173.
    Comment Date: 5 p.m. Eastern Time on Monday, October 25, 2010.

    Docket Numbers: CP11-4-000.
    Applicants: Transcontinental Gas Pipe Line Company, LLC.
    Description: Application of Transcontinental Gas Pipe Line Company,
LLC to Abandon Service to Atlanta Gas Light Company under Rate Schedule
SS-17(copyright) Storage Service and Rate Schedule SS-
17(copyright) Transportation Service.
    Filed Date: 10/07/2010.
    Accession Number: 20101007-5069.
    Comment Date: 5 p.m. Eastern Time on Monday, October 25, 2010.

    Docket Numbers: TS10-4-000.
    Applicants: City of Roseville, California.
    Description: City of Roseville, California request for waiver from
certain Commission orders and regulations relating to the Commission's
implementation of reciprocity obligations under its open access
requirements and the standards of conduct rules.
    Filed Date: 09/13/2010.
    Accession Number: 20100913-5213.
    Comment Date: 5 p.m. Eastern Time on Wednesday, November 4, 2010.

    Any person desiring to intervene or to protest in any of the above
proceedings must file in accordance with Rules 211 and 214 of the
Commission's Rules of Practice and Procedure (18 CFR 385.211 and
385.214) on or before 5 p.m. Eastern time on the specified comment
date. It is not necessary to separately intervene again in a subdocket
related to a compliance filing if you have previously intervened in the
same docket. Protests will be considered by the Commission in
determining the appropriate action to be taken, but will not serve to
make protestants parties to the proceeding.

Anyone filing a motion to intervene or protest must serve a copy of
that document on the Applicant. In reference to filings initiating a
new proceeding, interventions or protests submitted on or before the
comment deadline need not be served on persons other than the
Applicant.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper, using the FERC Online links at http://
www.ferc.gov. To facilitate electronic service, persons with Internet
access who will eFile a document and/or be listed as a contact for an
intervenor must create and validate an eRegistration account using the
eRegistration link. Select the eFiling link to log on and submit the
intervention or protests.
    Persons unable to file electronically should submit an original and
14 copies of the intervention or protest to the Federal Energy
Regulatory Commission, 888 First St., NE., Washington, DC 20426.
    The filings in the above proceedings are accessible in the
Commission's eLibrary system by clicking on the appropriate link in the
above list. They are also available for review in the Commission's
Public Reference Room in Washington, DC. There is an eSubscription link
on the Web site that enables subscribers to receive e-mail notification
when a document is added to a subscribed docket(s). For assistance with
any FERC Online service, please e-mail<EMAIL_ADDRESS>or
call<PHONE_NUMBER> (toll free). For TTY, call<PHONE_NUMBER>.

Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2010-26856 Filed 10-22-10; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 81, Number 37 (Thursday, February 25, 2016)]
[Notices]
[Page 9582]
[FR Doc No: 2016-04032]

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DEPARTMENT OF TRANSPORTATION

Federal Motor Carrier Safety Administration

[Docket No. FMCSA-2015-0436]

Agency Information Collection Activities; Extension of a
Currently-Approved Information Collection Request: Financial
Responsibility for Motor Carriers of Passengers and Motor Carriers of
Property

AGENCY: Federal Motor Carrier Safety Administration (FMCSA), DOT.

ACTION: Notice and request for comments.

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

SUMMARY: In accordance with the Paperwork Reduction Act of 1995, FMCSA
announces its plan to submit the Information Collection Request (ICR)
described below to the Office of Management and Budget (OMB) for its
review and approval and invites public comment. The information
collected will be used to help ensure that motor carriers of passengers
and property maintain appropriate levels of financial responsibility to
operate on public highways.

DATES: We must receive your comments on or before April 25, 2016.

ADDRESSES: You may submit comments identified by Federal Docket
Management System (FDMS) Docket Number FMCSA-2015-0436 using any of the
following methods:
     Federal eRulemaking Portal: http://www.regulations.gov.
Follow the online instructions for submitting comments.
     Fax: 1-202-493-2251.
     Mail: Docket Management Facility; U.S. Department of
Transportation, 1200 New Jersey Avenue SE., West Building, Ground
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery or Courier: U.S. Department of
Transportation, 1200 New Jersey Avenue SE., West Building, Ground
Floor, Room W12-140, Washington, DC 20590-0001 between 9 a.m. and 5
p.m. e.t., Monday through Friday, except Federal holidays.
    Instructions: All submissions must include the Agency name and
docket number. For detailed instructions on submitting comments and
additional information on the exemption process, see the Public
Participation heading below. Note that all comments received will be
posted without change to http://www.regulations.gov, including any
personal information provided. Please see the Privacy Act heading
below.
    Docket: For access to the docket to read background documents or
comments received, go to http://www.regulations.gov, and follow the
online instructions for accessing the dockets, or go to the street
address listed above.
    Privacy Act: 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 www.regulations.gov, as described in the
system of records notice (DOT/ALL-14 FDMS), which can be reviewed at
www.dot.gov/privacy.
    Public Participation: The Federal eRulemaking Portal is available
24 hours each day, 365 days each year. You can obtain electronic
submission and retrieval help and guidelines under the ``help'' section
of the Federal eRulemaking Portal Web site. If you want us to notify
you that we received your comments, please include a self-addressed,
stamped envelope or postcard, or print the acknowledgement page that
appears after submitting comments online. Comments received after the
comment closing date will be included in the docket and will be
considered to the extent practicable.

FOR FURTHER INFORMATION CONTACT: Mr. Jeff Secrist, Office of
Registration and Safety Information, Chief, East and South Division,
Department of Transportation, Federal Motor Carrier Safety
Administration, West Building 6th Floor, 1200 New Jersey Avenue SE.,
Washington, DC 20590. Telephone:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:
    Background: The Secretary of Transportation is responsible for
implementing regulations which establish minimal levels of financial
responsibility for: (1) For-hire motor carriers of property to cover
public liability, property damage and environmental restoration, and
(2) for-hire motor carriers of passengers to cover public liability and
property damage. The Endorsement for Motor Carrier Policies of
Insurance for Public Liability (Forms MCS-90/90B) and the Motor Carrier
Public Liability Surety Bond (Forms MCS-82/82B) contain the minimum
amount of information necessary to document that a motor carrier of
property or passengers has obtained, and has in effect, the minimum
levels of financial responsibility as set forth in applicable
regulations (motor carriers of property--49 CFR 387.9; and motor
carriers of passengers--49 CFR 387.33). FMCSA and the public can verify
that a motor carrier of property or passengers has obtained, and has in
effect, the required minimum levels of financial responsibility, by use
of the information enclosed within these documents.
    Title: Financial Responsibility for Motor Carrier of Passengers and
Motor Carriers of Property.
    OMB Control Number: 2126-0008.
    Type of Request: Extension of a currently-approved information
collection.
    Respondents: Insurance and surety companies of motor carriers of
property (Forms MCS-90 and MCS-82) and motor carriers of passengers
(Forms MCS-90B and MCS-82B).
    Estimated Number of Respondents: 8,004.
    Estimated Time per Response: The FMCSA estimates it takes two
minutes to complete the Endorsement for Motor Carrier Policies of
Insurances for Public Liability or the Motor Carrier Public Liability
Surety Bond; and one minute to place either document on board the
vehicle [49 CFR 387.7(f)(property); 387.31(f)(passengers)]. These
endorsements and surety bonds are maintained at the motor carrier's
principal place of business [49 CFR 387.7(d); 49 CFR 387.31(d)].
    Expiration Date: June 30, 2016.
    Frequency of Response: Upon creation, change or replacement of an
insurance policy or surety bond.
    Estimated Total Annual Burden: 4,777 hours [4,065 annual burden
hours for ICs 1-4 + 712 annual burden hours for IC-5 document
replacement = 4,777].
    Public Comments Invited: You are asked to comment on any aspect of
this information collection, including: (1) Whether the proposed
collection is necessary for the performance of FMCSA's functions; (2)
the accuracy of the estimated burden; (3) ways for the FMCSA to enhance
the quality, usefulness, and clarity of the collected information; and
(4) ways that the burden could be minimized without reducing the
quality of the collected information. The agency will summarize or
include your comments in the request for OMB's clearance of this
information collection.

    Issued on: February 17, 2016.
G. Kelly Regal,
Associate Administrator for Office of Research and Information
Technology.
[FR Doc. 2016-04032 Filed 2-24-16; 8:45 am]
BILLING CODE 4910-EX-P