[Federal Register Volume 81, Number 244 (Tuesday, December 20, 2016)]
[Proposed Rules]
[Pages 92749-92753]
[FR Doc No: 2016-30018]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9508; Directorate Identifier 2016-NM-065-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) 2015-22-
06 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD
2015-22-06 currently requires revising the After Start Normal
Procedures section of the airplane flight manual (AFM) to provide
procedures that address latent failures in the Spoiler and Elevator
Computer (SEC). Since we issued AD 2015-22-06, there have been reports
that some maintenance messages pointed out the loss of elevator servo

control monitoring performed by SEC 1, SEC 2, or both, during the
engine start. This proposed AD would add a requirement to install
updated SEC software. We are proposing this AD to address the unsafe
condition on these products.

DATES: We must receive comments on this proposed AD by February 3,
2017.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus,
Airworthiness Office-EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51;
email<EMAIL_ADDRESS>Internet http://www.airbus.com.
You may view this referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call<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-2016-
9508; 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-2016-9508;
Directorate Identifier 2016-NM-065-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 October 22, 2015, we issued AD 2015-22-06, Amendment 39-18311
(80 FR 68429, November 5, 2015) (``AD 2015-22-06''). AD 2015-22-06
requires revision of the AFM intended to address an unsafe condition
that can occur in the SEC for all Airbus Model A318, A319, A320, and
A321 series airplanes.
    Since we issued AD 2015-22-06, there have been reports that some
maintenance messages were recorded within the Post Flight Report (PFR)
that pointed out the loss of elevator servo control monitoring
performed by SEC 1, SEC 2, or both, during the engine start.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive, 2016-0056, dated March 18, 2016 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A318, A319, A320, and A321 series airplanes. The MCAI states:

    Following the introduction of new Spoiler and Elevator Computer
(SEC) hardware C Part Number (P/N) B372CAM0100 with software (SW)
standards 122, 124 and 125 (identified by P/N B372CAM0101, P/N
B372CAM0102 and P/N B372CAM0103, respectively, and hereafter
referred to as an ``affected SEC software standard'' in this [EASA]
AD), some airlines reported receiving maintenance messages, e.g.
``SEC OR WIRING FROM L or R ELEV POS MON XDCR'' and/or ``SEC OR
WIRING FROM G or Y ELEV POS XDCR'', which are associated with servo
control or elevator transducer monitoring. Such messages are
triggered by a short data inconsistency due to power transients,
when the engines are started.
    This condition, if not corrected, could lead to an undetected
loss of redundancy during flight if an affected SEC cannot control
the related elevator servo control(s), possibly resulting in reduced
control of the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2015-
0191 [which corresponds to AD 2015-22-06] to require amendment of
the applicable [Airbus] Airplane Flight Manual (AFM) to include the
flight crew procedure necessary to recover full SEC redundancy.
    Since that [EASA] AD was issued, to fix the software deficiency,
SEC software standard 126 (identified by P/N B372CAM0104) was
developed, which is embodied in production through Airbus
modification (mod) 161208 (installation of SEC software standard
126), and introduced in service through Airbus Service Bulletin (SB)
A320-27-1252.
    For the reason described above, this [EASA] AD retains the AFM
change requirements of EASA AD 2015-0191, which is superseded, and
requires the removal and/or upgrade of [an affected] SEC.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9508.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Service Bulletin A320-27-1252, Revision 01, dated
February 18, 2016.
     Airbus Service Bulletin A320-27-1257, dated December 18,
2015.
    This service information provides information for identifying
affected SECs and updating the software on affected SECs. These
documents are distinct since they apply to different airplane
configurations.
    Airbus also issued A318/A319/A320/A321 Temporary Revision TR572,
Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/A320/A321
Airplane Flight Manual. This service information describes the reset of
SEC 1 and SEC 2 that must be done after engines start.
    This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or

develop on other products of these same type designs.

Differences Between This Proposed AD and the Service Information

    Subtask 271257-832-006-001, Instructions ``2'' and ``3,'' in the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1257,
dated December 18, 2015, have software part numbers that are incorrect.
Paragraph (n) of this proposed AD provides the corrected part numbers.
The correct part numbers were provided by Airbus in Operators
Information Transmission (OIT) 16-0001, Revision 00, dated January 20,
2016.

Costs of Compliance

    We estimate that this proposed AD affects 959 airplanes of U.S.
registry.
    We estimate the following costs to comply with this proposed AD:

                                                                     Estimated Costs
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                                                                                Cost per      Cost on U.S.
                   Action                                             Labor cost                            Parts cost        product        operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
AFM revision (retained action from AD 2015-  1 work-hour x $85 per hour = $85...........................              $0             $85         $81,515
 22-06).
Removal and replacement of SEC (new          4 work-hours x $85 per hour = $340.........................               0             340         326,060
 proposed action).
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Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD)
2015-22-06, Amendment 39-18311 (80 FR 68429, November 5, 2015), and
adding the following new AD:

Airbus: Docket No. FAA-2016-9508; Directorate Identifier 2016-NM-
065-AD.

(a) Comments Due Date

    We must receive comments by February 3, 2017.

(b) Affected ADs

    This AD replaces AD 2015-22-06, Amendment 39-18311 (80 FR 68429,
November 5, 2015) (``AD 2015-22-06'').

(c) Applicability

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

(d) Subject

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

(e) Reason

    This AD was prompted by reports that some maintenance messages
were recorded within the Post Flight Report (PFR) that pointed out
the loss of elevator servo control monitoring performed by Spoiler
and Elevator Computer (SEC) 1, SEC 2, or both, during the engine
start. We are issuing this AD to prevent an undetected loss of
redundancy during flight if an affected SEC cannot control the
related elevator servo control(s), possibly resulting in reduced
control of the airplane.

(f) Compliance

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

(g) Retained Airplane Flight Manual Revision, With Revised Compliance
Language

    This paragraph restates the requirements of paragraph (g) of AD
2015-22-06, with revised compliance language. For airplanes equipped
with SEC hardware C part number (P/N) B372CAM0100 with software
standards 122 (P/N B372CAM0101), 124 (P/N B372CAM0102), or 125 (P/N
B372CAM0103), on SEC position 1 or 2, or both: Within 30 days after
November 20, 2015 (the effective date of AD 2015-22-06), revise the
After Start Normal Procedures section of the airplane flight manual
(AFM) to include the statement specified in figure 1 to paragraph
(g) of this AD. This may be done by inserting a copy of this AD, or
AD 2015-22-06, or Airbus A318/A319/A320/A321 Temporary Revision
TR572, Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/
A320/A321 AFM, into the applicable AFM.

[GRAPHIC] [TIFF OMITTED] TP20DE16.003

    Note 1 to paragraph (g) of this AD: When a statement identical
to that in figure 1 to paragraph (g) of this AD has been included in
the After Start Normal Procedures section of the general revisions
of the AFM, the general revisions may be inserted into the AFM, and
this AD, or AD 2015-22-06, or Airbus A318/A319/A320/A321 Temporary
Revision TR572, Issue 1.0, dated August 13, 2015, may be removed
from the AFM.

    Note 2 to paragraph (g) of this AD: Airbus Operations
Engineering Bulletin OEB-50 provides additional information on the
subject addressed by this AD.

(h) Retained Parts Installation Limitation, With No Change

    This paragraph restates the requirements of paragraph (i) of AD
2015-22-06, with no change. For all airplanes: As of November 20,
2015 (the effective date of AD 2015-22-06), do not install SEC
hardware C P/N B372CAM0100 with software standard 122 (P/N
B372CAM0101), 124 (P/N B372CAM0102), or 125 (P/N B372CAM0103), on
SEC position 1 or 2, or both, on any airplane, unless the AFM of the
airplane is revised concurrently with that installation, as required
by paragraph (g) of this AD.

(i) New Requirement of This AD: Replacement of Software

    Within 3 months after the effective date of this AD, comply with
the actions in paragraphs (i)(1) or (i)(2) of this AD, as
applicable.
    (1) For an airplane that has received Airbus modification 39429
(installation of SEC hardware C P/N B372CAM0100) in production:
Install SEC software standard 126, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1252,
Revision 01, dated February 18, 2016.
    (2) For an airplane that has not received Airbus modification
39429 in production: Inspect to determine whether an affected SEC
software standard is installed. Do the inspection in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-27-
1257, dated December 18, 2015, except as required by paragraph (n)
of this AD. A review of airplane maintenance records is acceptable
in lieu of this inspection if the part number of the SEC C can be
conclusively determined from that review. If an affected SEC
software standard is found installed, replace the affected software
standard using an installation 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).

(j) New Requirement of This AD: Compliance for Airplanes Having Airbus
Modification 161208 Embodied in Production

    An airplane on which Airbus modification 161208 has been
embodied in production is compliant with the requirements of
paragraph (i) of this AD, provided it is determined that no affected
SEC software standard, as identified in paragraph (g) of this AD, is
installed on that airplane.

(k) New Requirement of This AD: Disposition of AFM After Airplane
Modification

    After modification of an airplane as required by paragraph (i)
of this AD, remove the information specified in Airbus A318/A319/
A320/A321 TR572, Issue 1.0, dated August 13, 2015, to the Airbus
A318/A319/A320/A321 AFM from the AFM of that airplane.

(l) New Requirement of This AD: Parts Installation Prohibition

    As of the effective date of this AD, no person may install on
any airplane an affected SEC software standard, or a SEC hardware C
hosting an affected SEC software standard.

(m) New Provision of This AD: Installation of Equivalent Software and
Hardware

    Installation on an airplane of a SEC software standard, or of a
SEC hardware standard, approved after the effective date of this AD,
is acceptable for compliance with the requirements of paragraph (i)
of this AD for that airplane, provided the conditions specified in
paragraphs (m)(1) and (m)(2) of this AD are met.
    (1) The software and hardware standard, as applicable, is
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA; and
    (2) Replacement of the affected software standard is done using
an installation method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA.

(n) Exception to Service Information Specifications

    Subtask 271257-832-006-001 of Airbus Service Bulletin A320-27-
1257, dated December 18, 2015, includes incorrect instructions. This
AD requires that those instructions be followed as specified in
paragraphs (n)(1) and (n)(2) of this AD.
    (1) For Subtask 271257-832-006-001 instruction ``2'': If SEC C
126 software P/N B372CAM0104 is found, no further action is required
by this AD.
    (2) For Subtask 271257-832-006-001 instruction ``3'': If SEC C
122 software P/N B372CAM0101, SEC C 124 software P/N B372CAM0102, or
SEC C 125 software P/N B372CAM0103 is found, do corrective actions
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA
DOA.

(o) 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: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA. If approved by the DOA, the approval must include
the DOA-authorized signature.
    (3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.

(p) Special Flight Permits

    Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0056, dated March 18, 2016,
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-2016-9508.
    (2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email<EMAIL_ADDRESS>Internet http://www.airbus.com.

    Issued in Renton, Washington, on December 7, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-30018 Filed 12-19-16; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 79, Number 67 (Tuesday, April 8, 2014)]
[Proposed Rules]
[Pages 19299-19301]
[FR Doc No: 2014-07800]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0188; Directorate Identifier 2013-NM-157-AD]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc. 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
certain Bombardier, Inc. Model DHC-8-400 series airplanes. This
proposed AD was prompted by reports of two in-service incidents where
one side of the main landing gear (MLG) did not achieve down-lock. This
proposed AD would require a detailed inspection of the apex joints of
the stabilizer brace lock link in the MLG for clearance; rectifying and
repairing the clearance gap, if necessary; and lubricating the apex
joints of the stabilizer brace lock link in the MLG. We are proposing
this AD to detect and correct insufficiently greased stabilizer brace
lock linkage of the MLG and over-torqued lock linkage attachment bolts,
which could lead to the failure to extend and down-lock the MLG, and
could affect the safe landing of the airplane.

DATES: We must receive comments on this proposed AD by May 23, 2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada; telephone<PHONE_NUMBER>; fax 416-375-
4539; email<EMAIL_ADDRESS>Internet http://www.bombardier.com. You may view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call 425-
227-1221.

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-
0188; 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: Luke Walker, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; 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-2014-0188;
Directorate Identifier 2013-NM-157-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 Transport Canada Civil Aviation, which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2013-19, dated July 18, 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:

    There have been two reported in-service incidents where one side
of the main landing gear (MLG) did not achieve down-lock resulting
in a gear unsafe indication. In both cases, the MLG was ultimately
extended and down-lock was achieved through the use of the alternate
extension system or by cycling the MLG. The investigation revealed
that in both cases, the MLG stabilizer brace lock linkages were
insufficiently greased and the lock linkage attachment bolts were
over-torqued.
    Failure to extend and down-lock the MLG could adversely affect
the safe landing of the aeroplane.
    This [TCCA] AD mandates the [detailed] inspection, rectification
[and repair the clearance gap] as required, and lubrication of both
MLG stabilizer brace lock link apex joints.

    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-2014-0188.

Relevant Service Information

    Bombardier, Inc. has issued Service Bulletin 84-32-121, dated May
27, 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.

Repair Approvals

    In many FAA transport ADs, when the service information specifies
to contact the manufacturer for further instructions if certain
discrepancies are found, we typically include in the AD a requirement
to accomplish the action using a method approved by either the FAA or
the State of Design Authority (or its delegated agent). We have
recently been notified that certain laws in other countries do not
allow such delegation of authority, but some countries do recognize
design approval organizations. In addition, we have become aware that
some U.S. operators have used repair instructions that were previously
approved by a State of Design Authority or a Design Approval Holder
(DAH) as a method of compliance with this provision in FAA ADs.
Frequently, in these cases, the previously approved repair instructions
come from the airplane structural repair manual or the DAH repair
approval statements that were not specifically developed to address the
unsafe condition corrected by the AD. Using repair instructions that
were not specifically approved for a particular AD creates the
potential for doing repairs that were not developed to address the
unsafe condition identified by the MCAI AD, the FAA AD, or the
applicable service information, which could result in the unsafe
condition not being fully corrected.
    To prevent the use of repairs that were not specifically developed
to correct the unsafe condition, certain requirements of this proposed
AD would require that the repair approval specifically refer to the FAA
AD. This change is 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 use the phrase ``its delegated agent, or the DAH with
State of Design Authority design organization approval, as applicable''
in this proposed AD to refer to a DAH authorized to approve certain
required repairs for this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 75 airplanes of U.S.
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per       Cost on U.S.
             Action                       Labor cost              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection and Lubrication.....  $3 work-hours x $85 per hour              $0             $255          $19,125
                                  = $255.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.

Authority for This Rulemaking

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

Regulatory Findings

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

    4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. Amend Sec.  39.13 by adding the following new airworthiness
directive (AD):

Bombardier, Inc.: Docket No. FAA-2014-0188; Directorate Identifier
2013-NM-157-AD.

(a) Comments Due Date

    We must receive comments by May 23, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model DHC-8-400, -401 and -
402 airplanes, certificated in any category, serial numbers 4001
through 4454 inclusive.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of two in-service incidents
where one side of the main landing gear (MLG) did not achieve down-
lock. We are issuing this AD to detect and correct insufficiently
greased stabilizer brace lock linkage of the MLG and over-torqued
lock linkage attachment bolts, which could lead to the failure to
extend and down-lock the MLG, and could affect the safe landing of
the airplane.

(f) Compliance

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

(g) Inspection

    Within 1,000 flight hours or 6 months after the effective date
of this AD, whichever occurs first: Do a detailed inspection of the
apex joints of the stabilizer brace lock link in the main landing
gear (MLG) for clearance, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 84-32-121, dated May 27,
2013.
    (1) If the clearance gap is 0.001 inches (0.025 millimeters) or
greater, do the action in paragraph (h) of this AD at the time
specified in paragraph (h) of this AD.
    (2) If the clearance gap is less than 0.001 inches (0.025
millimeters), before further flight, rectify the clearance gap, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 84-32-121, dated May 27, 2013; and do the action in
paragraph (h) of this AD at the time specified in paragraph (h) of
this AD. If the clearance gap cannot be rectified in accordance with
the Accomplishment Instructions of Bombardier Service Bulletin 84-
32-121, dated May 27, 2013: Before further flight, repair using a
method approved by the Manager, New York Aircraft Certification
Office (ACO), ANE-170, FAA; or Transport Canada Civil Aviation
(TCCA) (or its delegated agent, or the Design Approval Holder with
TCCA's design organization approval, as applicable). For a repair
method to be approved, the repair approval must specifically refer
to this AD. After the repair is done, do the action in paragraph (h)
of this AD at the time specified in paragraph (h) of this AD.

    Note 1 to paragraphs (g) and (h) of this AD:  Completion of the
actions in this AD does not affect the actions specified in the
existing maintenance review board (MRB) task number 320001-201.

(h) Lubrication

    Within 1,000 flight hours or 6 months after the effective date
of this AD, whichever occurs first: Lubricate the apex joints of the
stabilizer brace lock link in the MLG, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-32-
121, dated May 27, 2013.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), ANE-170, 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 ACO, send it to ATTN: Program Manager, Continuing
Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.
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) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the DAH with a State of Design Authority's
design organization approval, as applicable). You are required to
ensure the product is airworthy before it is returned to service.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2013-19, dated July 31,
2013, for related information. This MCAI may be found in the AD
docket on the Internet at http://www.regulations.gov. This MCAI may
be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No.
FAA-2014-0188.
    (2) For service information identified in this AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone<PHONE_NUMBER>;
fax<PHONE_NUMBER>; email<EMAIL_ADDRESS>Internet
http://www.bombardier.com. You may view this service information at
the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at
the FAA, call<PHONE_NUMBER>.

    Issued in Renton, Washington, on March 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-07800 Filed 4-7-14; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 76, Number 85 (Tuesday, May 3, 2011)]
[Proposed Rules]
[Pages 24832-24836]
[FR Doc No: 2011-10624]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0387; Directorate Identifier 2010-NM-222-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A330-201, -202, -203, -
223, and -243 Airplanes, A330-300 Series Airplanes, A340-200 Series
Airplanes, and A340-300 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

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:

    Surface defects were visually detected on the rudder of * * *
[an] in-service aeroplane during scheduled maintenance.
    Investigation has determined that the defects reported on both
rudders corresponded to areas that had been reworked in production.
The investigation confirmed that the surface defects were a result
of de-bonding between the skin and honeycomb core.
* * * * *
    An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
* * * * *
    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 June 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--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; 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: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1138; 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-2011-0387;
Directorate Identifier 2010-NM-222-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 2010-0127, dated June 23, 2010 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:

    Surface defects were visually detected on the rudder of one A319
and one A321 in-service aeroplane during scheduled maintenance.
    Investigation has determined that the defects reported on both
rudders corresponded to areas that had been reworked in production.
The investigation confirmed that the surface defects were a result
of de-bonding between the skin and honeycomb core.
    Such reworks were also performed on some rudders fitted on A330
and A340-200/-300 aeroplanes.
    An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
    To address this unsafe condition, EASA issued AD 2010-0021,
superseding EASA AD 2009-0156, to require inspections of specific
areas and, depending on findings, the accomplishment of corrective
actions for those rudders where production reworks have been
identified.
    In addition, this AD addresses the rudder population that has
also been reworked in production but is not part of EASA AD 2010-
0021 applicability.

Required actions include vacuum loss and elasticity laminate checker
inspections for damage including de-bonding between the skin and
honeycomb core of the rudder on certain areas of the rudder, and repair
if necessary. You may obtain further information by examining the MCAI
in the AD docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletins A330-55-3042 and
A340-55-4038, both dated April 22, 2010. 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 55 products of U.S. registry. We also estimate that
it would take

about 6 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 $28,050, or $510 per product.
    We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this AD.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); 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-2011-0387; Directorate Identifier 2010-NM-
222-AD.

Comments Due Date

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

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330-201, -202, -203, -223,
-243, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes and Model A340-211, -212, -213, -311, -312, and -313
airplanes; certificated in any category, all manufacturer serial
numbers, if equipped with rudders having part numbers and serial
numbers as identified in table 1, table 2, or table 3 of this AD.

 Table 1--Rudder Part Number (P/N) and Affected Rudder Serial Number (S/
                                   N)
------------------------------------------------------------------------
                 Rudder P/N                      Affected rudder  S/N
------------------------------------------------------------------------
F554-70000-000-00..........................  TS-2045
F554-70000-000-00..........................  TS-2046
F554-71000-000-00-0000.....................  TS-3013
F554-71000-000-00-0000.....................  TS-3014
F554-71000-000-00-0000.....................  TS-3020
F554-71000-000-00-0000.....................  TS-3022
F554-71000-000-00-0000.....................  TS-3023
F554-71000-000-00-0000.....................  TS-3027
F554-71000-000-00-0000.....................  TS-3031
F554-71000-000-00-0000.....................  TS-3034
F554-71000-000-00-0000.....................  TS-3036
F554-71000-000-00-0000.....................  TS-3038
F554-71000-000-00-0000.....................  TS-3041
F554-71000-000-00-0000.....................  TS-3046
F554-71000-000-00-0000.....................  TS-3054
F554-70005-000-00-0000.....................  TS-3102
F554-71002-000-00-0002.....................  TS-4018
F554-71002-000-00-0002.....................  TS-4022
F554-71002-000-00-0002.....................  TS-4031
------------------------------------------------------------------------

               Table 2--Rudder P/N and Affected Rudder S/N
------------------------------------------------------------------------
                 Rudder P/N                      Affected Rudder  S/N
------------------------------------------------------------------------
A554-71500-024-00..........................  TS-1014
A554-71500-030-00..........................  TS-1042
F554-70000-000-00..........................  TS-2004
F554-70000-000-00..........................  TS-2005
F554-70000-000-00..........................  TS-2008
F554-70000-000-00..........................  TS-2009
F554-70000-000-00..........................  TS-2010
F554-70000-000-00..........................  TS-2022
F554-70000-000-00..........................  TS-2023
F554-70000-000-00..........................  TS-2028
F554-70000-000-00..........................  TS-2029
F554-70000-000-00..........................  TS-2030
F554-70000-000-00..........................  TS-2032
F554-70000-000-00..........................  TS-2033
F554-70000-000-00..........................  TS-2034
F554-70000-000-00..........................  TS-2041
F554-70000-000-00..........................  TS-2044
F554-70000-000-00..........................  TS-2048
F554-70000-000-00..........................  TS-2049
F554-70000-000-00..........................  TS-2050
F554-70000-000-00..........................  TS-2057
F554-70000-000-00..........................  TS-2067
F554-70000-002-00..........................  TS-2068
F554-70000-002-00..........................  TS-2071
F554-71000-000-00-0000.....................  TS-3001
F554-71000-000-00-0000.....................  TS-3010
F554-71000-000-00-0000.....................  TS-3012
F554-71000-000-00-0000.....................  TS-3017
F554-71000-000-00-0000.....................  TS-3018
F554-71000-000-00-0000.....................  TS-3019
F554-71000-000-00-0000.....................  TS-3021
F554-71000-000-00-0000.....................  TS-3024
F554-71000-000-00-0000.....................  TS-3025
F554-71000-000-00-0000.....................  TS-3026
F554-71000-000-00-0000.....................  TS-3028
F554-71000-000-00-0000.....................  TS-3029
F554-71000-000-00-0000.....................  TS-3030
F554-71000-000-00-0000.....................  TS-3032
F554-71000-000-00-0000.....................  TS-3035
F554-71000-000-00-0000.....................  TS-3037
F554-71000-000-00-0000.....................  TS-3039
F554-71000-000-00-0000.....................  TS-3040
F554-71000-000-00-0000.....................  TS-3042
F554-71000-000-00-0000.....................  TS-3047
F554-71000-000-00-0000.....................  TS-3049
F554-71000-000-00-0000.....................  TS-3055
F554-71000-000-00-0000.....................  TS-3058
F554-71000-000-00-0000.....................  TS-3062
F554-71000-000-00-0000.....................  TS-3063
F554-71000-000-00-0000.....................  TS-3065
F554-71000-000-00-0000.....................  TS-3067
F554-71000-000-00-0000.....................  TS-3069
F554-71000-000-00-0000.....................  TS-3070
F554-71000-000-00-0000.....................  TS-3077
F554-71000-000-00-0000.....................  TS-3078
F554-71000-000-00-0000.....................  TS-3080
F554-71000-000-00-0000.....................  TS-3081
F554-71000-000-00-0000.....................  TS-3086
F554-71000-000-00-0000.....................  TS-3089
F554-71000-000-00-0000.....................  TS-3092
F554-71000-000-00-0000.....................  TS-3093
F554-71000-000-00-0000.....................  TS-3095
F554-71000-000-00-0000.....................  TS-3096
F554-70005-000-00-0000.....................  TS-3098
F554-70005-000-00-0000.....................  TS-3099
F554-70005-000-00-0000.....................  TS-3101
F554-70005-000-00-0000.....................  TS-3103
F554-70005-000-00-0000.....................  TS-3104
F554-70005-000-00-0000.....................  TS-3105
F554-70005-000-00-0000.....................  TS-3108

F554-70005-000-00-0000.....................  TS-3109
F554-70005-000-00-0000.....................  TS-3110
F554-70005-000-00-0000.....................  TS-3111
F554-70005-000-00-0000.....................  TS-3112
F554-70005-000-00-0000.....................  TS-3114
F554-70005-000-00-0000.....................  TS-3116
F554-70005-000-00-0000.....................  TS-3117
F554-70005-000-00-0000.....................  TS-3120
F554-70005-000-00-0000.....................  TS-3131
F554-70005-000-00-0000.....................  TS-3132
F554-70005-000-00-0000.....................  TS-3212
F554-70005-000-00-0002.....................  TS-3323
F554-70005-000-00-0002.....................  TS-3330
F554-71002-000-00-0002.....................  TS-4009
F554-71002-000-00-0002.....................  TS-4010
F554-71002-000-00-0002.....................  TS-4012
F554-71002-000-00-0002.....................  TS-4013
F554-71002-000-00-0002.....................  TS-4014
F554-71002-000-00-0002.....................  TS-4015
F554-71002-000-00-0002.....................  TS-4016
F554-71002-000-00-0002.....................  TS-4017
F554-71002-000-00-0002.....................  TS-4020
F554-71002-000-00-0002.....................  TS-4023
F554-71002-000-00-0002.....................  TS-4025
F554-71002-000-00-0002.....................  TS-4026
F554-71002-000-00-0002.....................  TS-4027
F554-71002-000-00-0002.....................  TS-4029
F554-71002-000-00-0002.....................  TS-4030
F554-71002-000-00-0002.....................  TS-4038
F554-71002-000-00-0002.....................  TS-4047
F554-71002-000-00-0002.....................  TS-4049
F554-71002-000-00-0002.....................  TS-4066
F554-71002-000-00-0003.....................  TS-4083
------------------------------------------------------------------------

               Table 3--Rudder P/N and Affected Rudder S/N
------------------------------------------------------------------------
                 Rudder P/N                      Affected Rudder  S/N
------------------------------------------------------------------------
F554-71000-000-00-0000.....................  TS-3060
F554-71000-000-00-0000.....................  TS-3068
F554-70005-000-00-0000.....................  TS-3128
F554-71002-000-00-0002.....................  TS-4011
------------------------------------------------------------------------

Subject

    (d) Air Transport Association (ATA) of America Code 55:
Stabilizers.

Reason

    (e) The mandatory continuing airworthiness information (MCAI)
states:
    Surface defects were visually detected on the rudder of * * *
[an] in-service aeroplane during scheduled maintenance.
    Investigation has determined that the defects reported on both
rudders corresponded to areas that had been reworked in production.
The investigation confirmed that the surface defects were a result
of de-bonding between the skin and honeycomb core.
* * * * *
    An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
* * * * *

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.

Inspections

    (g) For rudders identified in table 1 and table 2 of this AD,
within the compliance time in paragraph (g)(1) or (g)(2) of this AD
as applicable, do a vacuum loss inspection on the rudder non-
ventilated area (Area 1) for damage including de-bonding between the
skin and honeycomb core of the rudder, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-55-3042 or A340-55-4038, both dated April 22, 2010, as
applicable.
    (1) For rudders identified in table 1 of this AD: Within 1,800
flight hours after the effective date of this AD.
    (2) For rudders identified in table 2 of this AD: Within 21
months after the effective date of this AD.
    (h) For rudders identified in table 1 and table 2 of this AD,
within 21 months after the effective date of this AD, do an
elasticity laminate checker inspection on the trailing edge area
(Area 2) for damage including de-bonding between the skin and
honeycomb core of the rudder, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or
A340-55-4038, both dated April 22, 2010, as applicable. Thereafter,
repeat the inspection two more times at intervals not to exceed
4,500 flight cycles but not less than 4,000 flight cycles from the
most recent inspection.
    (i) For rudders identified in table 3 of this AD, within 4,500
flight cycles but not less than 4,000 flight cycles from the date of
the sampling inspection identified in table 4 of this AD, or within
30 days after the effective date of this AD, whichever occurs later,
do an elasticity laminate checker inspection on the trailing edge
area for damage including de-bonding between the skin and honeycomb
core of the rudder, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or
A340-55-4038, both dated April 22, 2010, as applicable. Repeat the
inspection once within 4,500 flight cycles after doing the
inspection but not less than 4,000 flight cycles from the last
inspection.

                    Table 4--Rudder P/N and Affected Rudder S/N and Sampling Inspection Date
----------------------------------------------------------------------------------------------------------------
                Rudder P/N                      Affected rudder S/N            Date of sampling  inspection
----------------------------------------------------------------------------------------------------------------
F554-71000-000-00-0000...................  TS-3060.....................  March 12, 2009.
F554-71000-000-00-0000...................  TS-3068.....................  April 27, 2009.
F554-70005-000-00-0000...................  TS-3128.....................  July 13, 2009.
F554-71002-000-00-0002...................  TS-4011.....................  February 12, 2009.
----------------------------------------------------------------------------------------------------------------

Corrective Actions

    (j) If damage is found during any inspection required by
paragraph (g), (h), (i), or (k)(1) of this AD, before further
flight, repair the damage using a method approved by either the
Manager, International Branch, ANM 116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or
its delegated agent).

Restoration

    (k) If no damage is found during any inspection required by
paragraph (g) of this AD, before further flight, restore the vacuum
loss holes by doing a temporary restoration with self-adhesive disks
or tapes, a temporary restoration with resin, or a permanent
restoration with resin, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or
A340-55-4038, both dated April 22, 2010, as applicable. Do the
applicable actions specified in paragraph (k)(1) or (k)(2) of this
AD.
    (1) For airplanes on which a temporary restoration with self-
adhesive disks or tapes is done, within 900 flight hours after doing
the restoration, do a detailed inspection for loose or missing self-
adhesive disks or tapes and repeat the inspection thereafter at
intervals not to exceed 900 flight hours until the permanent
restoration is done, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or
A340-55-4038, both dated April 22, 2010, as applicable. If any loose
or missing self-adhesive disks or tapes are found during any
inspection required by this AD, before further flight, close the
holes, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated
April 22, 2010, as applicable. Do the permanent restoration within
21 months after doing the temporary restoration, in accordance with
the Accomplishment Instructions of Airbus

Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated
April 22, 2010, as applicable.
    (2) For airplanes on which a temporary restoration with resin is
done: Within 21 months after doing the temporary restoration, do the
permanent restoration, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or
A340-55-4038, both dated April 22, 2010, as applicable.

Reporting Requirements

    (l) Submit a report of the findings (positive and negative) of
the first inspection required by paragraphs (g), (h), and (i) of
this AD to Airbus, at the applicable time specified in paragraph
(l)(1) or (l)(2) of this AD. The report must include the inspection
results, a description of any discrepancies found, the airplane
serial number, and the number of landings and flight hours on the
airplane.
    (1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.

Parts Installation

    (m) As of the effective date of this AD, no person may install
any affected rudder listed in table 1, table, 2, or table 3 of this
AD, on any airplane, unless the rudder is inspected as specified in
paragraphs (g), (h), and (i) of this AD, as applicable, and all
applicable corrective actions specified in paragraph (j) of this AD
and applicable restoration specified in paragraph (k) of this AD are
done.

FAA AD Differences

    Note 1:  This AD differs from the MCAI and/or service
information as follows: No differences.

Other FAA AD Provisions

    (n) 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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.
Information may be e-mailed 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) 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: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.,
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.

Related Information

    (o) Refer to MCAI EASA Airworthiness Directive 2010-0127, dated
June 23, 2010; Airbus Mandatory Service Bulletin A330-55-3042, dated
April 22, 2010; and Airbus Mandatory Service Bulletin A340-55-4038,
dated April 22, 2010; for related information.

    Issued in Renton, Washington, on April 20, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-10624 Filed 5-2-11; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register: January 10, 2008 (Volume 73, Number 7)]
[Proposed Rules]
[Page 1851-1853]
[DOCID:fr10ja08-20]

=======================================================================
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ENVIRONMENTAL PROTECTION AGENCY

40 CFR Part 52

[EPA-R03-OAR-2007-1001; FRL-8515-3]

Approval and Promulgation of Air Quality Implementation Plans;
Maryland; NOX and SO2 Emissions Limitations for Fifteen Coal-Fired
Electric Generating Units

AGENCY: Environmental Protection Agency (EPA).

ACTION: Proposed rule.

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

SUMMARY: EPA is proposing to approve a State Implementation Plan (SIP)
revision submitted by the Maryland Department of the Environment (MDE).
This revision pertains to regulations for emission limitations at 15
Maryland power plants. The State requested that regulations
establishing statewide tonnage caps for emissions of NOX and
SO2 from 15 coal-fired electric generating units in Maryland
be approved. These regulations also establish monitoring and reporting
requirements, and authorize the MDE to reduce or waive penalties for
non-compliance under certain conditions and provide for judicial review
of decisions by the MDE to grant a reduction or waiver of penalties.
This action is being taken under the Clean Air Act (CAA).

DATES: Written comments must be received on or before February 11,
2008.

ADDRESSES: Submit your comments, identified by Docket ID Number EPA-
R03-OAR-2007-1001, by one of the following methods:
    A. http://www.regulations.gov. Follow the on-line instructions for

submitting comments.
    B. E-mail<EMAIL_ADDRESS>    C. Mail: EPA-R03-OAR-2007-1001, Cristina Fernandez, Branch Chief,
Air Quality Planning Branch, Mailcode 3AP21, U.S. Environmental
Protection Agency, Region III, 1650 Arch Street, Philadelphia,
Pennsylvania 19103.
    D. Hand Delivery: At the previously-listed EPA Region III address.
Such deliveries are only accepted during the Docket's normal hours of
operation, and special arrangements should be made for deliveries of
boxed information.
    Instructions: Direct your comments to Docket ID No. EPA-R03-OAR-
2007-1001. EPA's policy is that all comments received will be included
in the public docket without change, and may be made available online
at http://www.regulations.gov, including any personal information provided,

unless the comment includes information claimed to be Confidential
Business Information (CBI) or other information whose disclosure is
restricted by statute. Do not submit information that you consider to
be CBI or otherwise protected through http://www.regulations.gov or e-mail.

The http://www.regulations.gov Website is an ``anonymous access'' system,

which means EPA will not know your identity or contact information
unless you provide it in the body of your comment. If you send an e-
mail comment directly to EPA without going through http://www.regulations.gov,

your e-mail address will be automatically captured and included as part
of the comment that is placed in the public docket and made available
on the Internet. If you submit an electronic comment, EPA recommends
that you include your name and other contact information in the body of
your comment and with any disk or CD-ROM you submit. If EPA cannot read
your comment due to technical difficulties and cannot contact you for
clarification,

EPA may not be able to consider your comment. Electronic files should
avoid the use of special characters, any form of encryption, and be
free of any defects or viruses.
    Docket: All documents in the electronic docket are listed in the
http://www.regulations.gov index. Although listed in the index, some

information is not publicly available, i.e., CBI or other information
whose disclosure is restricted by statute. Certain other material, such
as copyrighted material, is not placed on the Internet and will be
publicly available only in hard copy form. Publicly available docket
materials are available either electronically in http://www.regulations.gov or

in hard copy during normal business hours at the Air Protection
Division, U.S. Environmental Protection Agency, Region III, 1650 Arch
Street, Philadelphia, Pennsylvania 19103. Copies of the State submittal
are available at Maryland Department of the Environment, 1800
Washington Boulevard, Suite 705, Baltimore, Maryland, 21230.

FOR FURTHER INFORMATION CONTACT: Irene Shandruk,<PHONE_NUMBER>, or by
e-mail at<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION: On July 12, 2007, the Maryland Department of
the Environment (MDE) submitted a revision to its State Implementation
Plan (SIP) for approval of emission limitations and related
requirements for nitrogen oxides (NOX) and sulfur dioxide
(SO2) at 15 coal-fired electric generating units in
Maryland.

I. Background

    On April 6, 2006, Maryland signed into law the Healthy Air Act (Ch.
23, Acts of 2006), which requires MDE to adopt certain regulations. One
such requirement under the Act is to establish caps on the amount of
NOX and SO2 emissions that certain affected
facilities can emit. These proposed regulations are more stringent than
the Clean Air Interstate Rule (CAIR), which was published by EPA on May
12, 2005 (70 FR 25162).
    In the CAIR rule, EPA determined that 28 States and the District of
Columbia contribute significantly to nonattainment and interfere with
maintenance of the NAAQS for fine particles (PM2.5) and/or
8-hour ozone in downwind States in the eastern part of the country. As
a result, EPA required those upwind States to revise their State
Implementation Plans (SIPs) to include control measures that reduce
emissions of SO2, which is a precursor to PM2.5
formation, and/or NOX, which is a precursor to both ozone
and PM2.5 formation. Under CAIR, States may implement these
reduction requirements by participating in the EPA-administered cap-
and-trade programs or by adopting any other control measures.
    Maryland's proposed regulations are more restrictive than the CAIR
rules in that they establish specific emission limitations for certain
Maryland sources and, unlike the CAIR rules, do not permit surrender of
allowances to achieve compliance. While these regulations modify some
of the flexibility of CAIR by requiring the installation of on-site
pollution controls at the 15 Maryland power plants, they ensure that
appropriate local emissions reductions will occur where they are needed
in order to attain the NAAQS by 2010.

II. Summary of SIP Revision

    The MDE is requesting that regulations (under COMAR 26.11.27)
establishing tonnage caps for emissions of NOX and SO2
from 15 coal-fired electric generating units (EGUs) in Maryland be
approved. The purpose of these regulations is to help bring Maryland
into attainment with the NAAQS for ozone and fine particulate matter by
the 2010 attainment deadline. The 15 affected units are as follows:

------------------------------------------------------------------------
         Electric generating unit                   Jurisdiction
------------------------------------------------------------------------
Constellation Energy Group System:
  Brandon Shores 1 & 2....................  Anne Arundel County.
  H. A. Wagner 2 & 3......................  Anne Arundel County.
  C. P. Crane 1 & 2.......................  Baltimore County.
Mirant System:
  Chalk Point 1 & 2.......................  Prince George's County.
  Dickerson 1, 2, & 3.....................  Montgomery County.
  Morgantown 1 & 2........................  Charles County.
Allegheny Energy:
  R. Paul Smith 3 & 4.....................  Washington County.
------------------------------------------------------------------------

III. Proposed Action

    Maryland has met the requirements for submitting a SIP revision for
limiting NOX and SO2 emissions from certain
Maryland power plants. EPA is proposing to approve the Maryland SIP
revision for limiting NOX and SO2 emissions at 15
coal-fired EGUs, which was submitted on July 12, 2007. EPA is
soliciting public comments on the issues discussed in this document.
These comments will be considered before taking final action.

IV. Statutory and Executive Order Reviews

    Under Executive Order 12866 (58 FR 51735, October 4, 1993), this
proposed action is not a ``significant regulatory action'' and
therefore is not subject to review by the Office of Management and
Budget. For this reason, this action is also not subject to Executive
Order 13211, ``Actions Concerning Regulations That Significantly Affect
Energy Supply, Distribution, or Use'' (66 FR 28355 (May 22, 2001)).
This action merely proposes to approve state law as meeting Federal
requirements and imposes no additional requirements beyond those
imposed by state law. Accordingly, the Administrator certifies that
this proposed rule will not have a significant economic impact on a
substantial number of small entities under the Regulatory Flexibility
Act (5 U.S.C. 601, et seq.). Because this rule proposes to approve pre-
existing requirements under state law and does not impose any
additional enforceable duty beyond that required by state law, it does
not contain any unfunded mandate or significantly or uniquely affect
small governments, as described in the Unfunded Mandates Reform Act of
1995 (Pub. L. 104-4). This proposed rule also does not have a
substantial direct effect on one or more Indian tribes, on the
relationship between the Federal Government and Indian tribes, or on
the distribution of power and responsibilities between the Federal
Government and Indian tribes, as specified by Executive Order 13175 (65
FR 67249, November 9, 2000), nor will it have substantial direct
effects 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, as specified
in Executive Order 13132 (64 FR 43255, August 10, 1999), because it
merely proposes to approve a state rule implementing a Federal
requirement, and does not alter the relationship or the distribution of
power and responsibilities established in the CAA. This proposed rule
also is not subject to Executive Order 13045 (62 FR 19885, April 23,
1997), because it approves a state rule implementing a Federal
standard.
    In reviewing SIP submissions, EPA's role is to approve state
choices, provided that they meet the criteria of the CAA. In this
context, in the absence of a prior existing requirement for the State
to use voluntary consensus standards (VCS), EPA has no authority to
disapprove a SIP submission for failure to use VCS. It would thus be

inconsistent with applicable law for EPA, when it reviews a SIP
submission, to use VCS in place of a SIP submission that otherwise
satisfies the provisions of the CAA. Thus, the requirements of section
12(d) of the National Technology Transfer and Advancement Act of 1995
(15 U.S.C. 272 note) do not apply. As required by section 3 of
Executive Order 12988 (61 FR 4729, February 7, 1996), in issuing this
proposed rule, EPA has taken the necessary steps to eliminate drafting
errors and ambiguity, minimize potential litigation, and provide a
clear legal standard for affected conduct. EPA has complied with
Executive Order 12630 (53 FR 8859, March 15, 1988) by examining the
takings implications of the rule in accordance with the ``Attorney
General's Supplemental Guidelines for the Evaluation of Risk and
Avoidance of Unanticipated Takings'' issued under the executive order.
This action proposing approval of Maryland's SIP revision concerning
emission limitations for NOX and SO2 at 15 coal-
fired EGUs does not impose an information collection burden under the
provisions of the Paperwork Reduction Act of 1995 (44 U.S.C. 3501, et
seq.).

List of Subjects in 40 CFR Part 52

    Environmental protection, Air pollution control, Nitrogen dioxide,
Reporting and recordkeeping requirements, Sulfur oxides.

    Authority: 42 U.S.C. 7401, et seq.

    Dated: December 27, 2007.
William T. Wisniewski,
Acting Regional Administrator, Region III.
 [FR Doc. E8-276 Filed 1-9-08; 8:45 am]

BILLING CODE 6560-50-P


[Federal Register Volume 81, Number 173 (Wednesday, September 7, 2016)]
[Notices]
[Pages 61733-61734]
[FR Doc No: 2016-21426]

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DEPARTMENT OF TRANSPORTATION

National Highway Traffic Safety Administration

[Docket No. NHTSA-2016-0053]

Reports, Forms and Recordkeeping Requirements, Agency Information
Collection Activity Under OMB Review

AGENCY: National Highway Traffic Safety Administration (NHTSA), DOT

ACTION: Notice.

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

SUMMARY: In compliance with the Paperwork Reduction Act of 1995 (44
U.S.C. 3501 et seq.), this notice announces that the collection of
information abstracted below will be forwarded to the Office of
Management and Budget (OMB) for review and comment. The notice
describes the nature of the information collection and its expected
burden. The Federal Register Notice with a 60-day comment period was
published on May 2, 2016 (81 FR 26312). No comments were received.

COMMENTS:  Comments should be directed to the Office of Information and
Regulatory Affairs, Office of Management and Budget, 725 17th Street
NW., Washington, DC 20503, Attention NHTSA Desk Officer.

TYPE OF REQUEST:  Extension of a currently approved collection.

FORM NUMBER:  This collection of information uses no standard forms.

DATES: Comments must be submitted on or before October 7, 2016.

FOR FURTHER INFORMATION CONTACT: Jordan Stephens, Office of the Chief
Counsel, NCC-100, National Highway Traffic Safety Administration, 1200
New Jersey Avenue SE., Washington, DC 20590 (telephone:<PHONE_NUMBER>).
Please identify the relevant collection of information by referring to
OMB Clearance Number 2127-0609 ``Criminal Penalty Safe Harbor
Provision.''

SUPPLEMENTARY INFORMATION:
    Agency: National Highway Traffic Safety Administration
    Title: Criminal Penalty Safe Harbor Provision
    OMB Control Number: 2127-0609
    Frequency: We believe that there will be very few criminal
prosecutions under 49 U.S.C. 30170, given its elements. Since the safe
harbor related rule has been in place, the Agency has not received any
reports. Accordingly, the rule is not likely to be a substantial
motivating force for a submission of a proper report. See Summary of
the Collection of Information below. We estimate that no more than one
person a year would invoke this collection of information, and we do
not anticipate receiving more than one report a year from any
particular person.
    Affected Public: This collection of information applies to any
person who seeks a ``safe harbor'' from potential criminal liability
for violating section 1001 of title 18 with respect to the reporting
requirements of 49 U.S.C. 30166, with the specific intention of
misleading the Secretary with respect to a safety-related defect in
motor vehicles or motor vehicle equipment that caused death or serious
bodily injury to an individual. Thus, the collection of information
applies to the manufacturers, and any officers or employees thereof,
who respond or have a duty to respond to an information provision
requirement pursuant to 49 U.S.C. 30166 or a regulation, requirement,
request or order issued thereunder.
    Abstract: This information collection was mandated by Section 5 of
the Transportation Recall Enhancement, Accountability, and
Documentation (TREAD) Act, codified at 49 U.S.C. 30170(a)(2). The
information collected will provide NHTSA with information the Agency
should have received previously and will also promptly provide the
Agency with correct information to do its analyses, such as, for
example, conducting tests or drawing conclusions about possible safety-
related defects. NHTSA anticipates using this information to help it
accomplish its statutory assignment of identifying safety-related
defects in motor vehicles and motor vehicle equipment and, when
appropriate, seeking safety recalls.
    Estimated Annual Burden: As stated before, we estimate that no more
than one person a year would be subject to this collection of
information. Incrementally, we estimate that on average it will take no
longer than two hours for a person to compile and submit the
information we are requiring to be reported. Therefore, the total
burden hours on the public per year is estimated to be a maximum of two
hours.
    Since nothing in the rule requires those persons who submit reports
pursuant to this rule to keep copies of any records or reports
submitted to us, recordkeeping costs imposed would be zero hours and
zero costs.
    Number of Respondents: We estimate that there will be no more than
one per year.
    Summary of the Collection of Information: Each person seeking
protection from criminal penalties under 49 U.S.C. 30170 related to an

improper report or failure to report is required to report the
following information to NHTSA: (1) A signed and dated document that
identifies (a) each previous improper report and each failure to report
as required under 49 U.S.C. 30166, including a regulation, requirement,
request or order issued thereunder, for which protection is sought and
(b) the specific predicate under which the improper or omitted report
should have been provided; and (2) the complete and correct information
that was required to be submitted but was improperly submitted or was
not previously submitted, including relevant documents that were not
previously submitted to NHTSA or, if the person cannot do so, provide a
detailed description of that information and/or the content of those
documents and the reason why the individual cannot provide them to
NHTSA. See 49 U.S.C. 30170(a)(2) and 49 CFR 578.7; see also 66 FR 38380
(July 24, 2001) (safe harbor final rule); 65 FR 81414 (Dec. 26, 2000)
(safe harbor interim final rule).

ADDRESSES: Send comments, within 30 days, to the Office of Information
and Regulatory Affairs, Office of Management and Budget, 725 17th
Street NW., Washington, DC 20503, Attention NHTSA Desk Officer.
    Comments are invited on: Whether the proposed collection of
information is necessary for the proper performance of the functions of
the Department, including whether the information will have practical
utility; the accuracy of the Department's estimate of the burden of the
proposed information collection; ways to enhance the quality, utility,
and clarity of the information to be collected; and ways to minimize
the burden of the collection of information on respondents, including
the use of automated collection techniques or other forms of
information technology. A comment to OMB is most effective if OMB
receives it within 30 days of publication.

    Authority: 44 U.S.C. 3506; delegation of authority at 49 CFR
1.95.

    Issued: August 30, 2016.
Paul A. Hemmersbaugh,
Chief Counsel.
[FR Doc. 2016-21426 Filed 9-6-16; 8:45 am]
 BILLING CODE 4910-59-P