[Federal Register Volume 84, Number 128 (Wednesday, July 3, 2019)]
[Rules and Regulations]
[Pages 31710-31713]
[FR Doc No: 2019-14152]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0020; Product Identifier 2018-NM-144-AD; Amendment
39-19659; AD 2019-12-04]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-19-
18, which applied to certain Airbus SAS Model A300 B4-603, B4-620, and
B4-622 airplanes; Model A300 B4-600R series airplanes; Model A300 C4-
605R Variant F airplanes; and Model A300 F4-605R airplanes. AD 2018-19-
18 required, depending on airplane configuration, a modification of
certain angle fitting attachment holes; repetitive inspections for
cracking of certain holes of the internal lower angle fitting web,
certain holes of the internal lower angle fitting horizontal splicing,
the aft bottom panel, and a certain junction area; and related
investigative and corrective actions if necessary. This new AD retains
those actions, expands the applicability, and, for certain airplanes,
requires repetitive inspections for cracking of certain holes of the
center wing box (CWB) lower angle fittings and the CWB lower panel, and
corrective actions if necessary, as specified in an European Aviation
Safety Agency (EASA) AD, which is incorporated by reference. This AD
was prompted by reports of cracking of a certain frame (FR) angle
fitting. The FAA is issuing this AD to address the unsafe condition on
these products.

DATES: This AD is effective August 7, 2019.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 7,
2019.

ADDRESSES: For the material incorporated by reference (IBR) in this AD,
contact the EASA, at Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 89990 1000; email<EMAIL_ADDRESS>internet
www.easa.europa.eu. You may find this IBR material on the EASA website
at https://ad.easa.europa.eu. You may view this IBR material at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195. It is also available in the AD docket on the internet at
http://www.regulations.gov.

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-2019-
0020; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations is U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2018-19-18, Amendment 39-19418 (83 FR
49793, October 3, 2018) (``AD 2018-19-18''). AD 2018-19-18 applied to
certain Airbus SAS Model A300 B4-603, B4-620, and B4-622 airplanes;
Model A300 B4-600R series airplanes; Model A300 C4-605R Variant F
airplanes; and Model A300 F4-605R airplanes. The NPRM published in the
Federal Register on February 15, 2019 (84 FR 4387). The NPRM was
prompted by the determination that additional airplanes may be affected
by the unsafe condition. The NPRM proposed to continue to require,
depending on airplane configuration, a modification of certain angle
fitting attachment holes; repetitive inspections for cracking of
certain holes of the internal lower angle fitting web, certain holes of
the internal lower angle fitting horizontal splicing, the aft bottom
panel, and a certain junction area; and related investigative and
corrective actions if necessary. The NPRM also proposed to expand the
applicability, and, for certain airplanes, proposed to require
repetitive inspections for cracking of certain holes of the CWB lower
angle fittings and the CWB lower panel, and corrective actions if
necessary. The FAA is issuing this AD to address cracking of the FR47
angle fitting, which could result in reduced structural integrity of
the airplane.
    EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2018-0229, dated October 23, 2018
(``EASA AD 2018-0229'') (also referred to as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain Airbus SAS Model A300 B4-603, B4-620, B4-622, B4-
605R, B4-622R, C4-605R Variant F, F4-605R, and F4-622R airplanes. The
MCAI states:

    Prompted by cracks found on CWB FR47 angle fittings, Airbus
issued SB [service bulletin] A300-57-6049, SB A300-57-6050, and SB
A300-57-6086.
    These cracks, if not detected and corrected, could affect the
structural integrity of the CWB of the aeroplane.
    Consequently, DGAC [Direction G[eacute]n[eacute]rale de
l'Aviation Civile] France published AD 94-241-170, AD 1999-147-279,
AD 2000-533-328 and AD F-2004-159 (EASA approval 2004-9779), each
[DGAC France] AD superseding the previous one, to require repetitive
high frequency eddy current (HFEC) rotating probe inspections of the
FR47 internal lower angle fitting.
    After DGAC France AD F-2004-159 was issued, cracks were
reportedly found on the horizontal flange of the FR47 internal
corner angle fitting during accomplishment of routine maintenance
structural inspection and modification in accordance with the
instructions of Airbus SB A300-57-6050. Prompted by these findings,
Airbus reviewed and amended the inspection programme for the
internal lower angle fitting flange (horizontal face).
    Consequently, EASA issued AD 2012-0092 [which corresponds to FAA
AD 2014-20-18, Amendment 39-17991 (79 FR 65879, November 6, 2014)
(``AD 2014-20-18'')] retaining the requirements of DGAC France AD F-
2004-159, which was superseded, and requiring additional repetitive
inspections of the CWB lower panel through the ultrasonic method
and, depending on findings, re-installation of removed fasteners in
transition fit instead of interference. In addition, DGAC France had
previously issued AD F-2005-124 (EASA approval 2005-6071) to require
CWB FR47 angle fittings inspections for A300 F4-608ST aeroplanes, in
accordance with Airbus SB A300-57-9001 and SB A300-57-9002.
    Following the discovery of numerous cracks during the
accomplishment of SB A300-57-6049 and SB A300-57-6086 inspections,
Airbus developed in a first step a new (recommended) modification
(Airbus SB A300-57-6113), defined associated inspections programme
and methods (ultrasonic/radiographic), and published SB A300-57-
6119. Consequently, EASA issued AD 2016-0198, retaining the
requirements of EASA AD 2012-0092, which was superseded, to require
repetitive inspections for post-SB A300-57-6113 aeroplanes.
    After EASA AD 2016-0198 was issued, Airbus revised in a second
step the inspection programme for A300-600 pre-SB

A300-57-6113 and A300-600ST aeroplanes, reducing inspection
thresholds and intervals. At this opportunity, the existing
ultrasonic inspection of the CWB lower panel for A300-600 aeroplanes
was added for A300-600ST aeroplanes. Consequently, EASA issued AD
2017-0210 [which corresponds to FAA AD 2018-19-18] retaining the
requirements of EASA AD 2016-0198 for A300-600 aeroplanes and DGAC
France AD F-2005-124 for A300-600ST aeroplanes, which were both
superseded, to include these new requirements.
    Since EASA AD 2017-0210 was issued, Airbus revised in a third
step the inspection programme for A300-600 post-mod 12171 and post-
mod 12249 reducing inspection thresholds and intervals, and
introducing the CWB lower panel inspection. Airbus published SB
A300-57-6121, superseding Airworthiness Limitation Items (ALI) tasks
571012 & 571014.
    For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2017-0210, which is superseded, and expands
the Applicability (Group 3) to include post-mod 12171 and post-mod
12249 aeroplanes [and requires sending inspection results to
Airbus].

    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-2019-
0020.

Comments

    The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.

Request To Extend Grace Period for Certain Inspections

    United Parcel Service (UPS) requested that the grace periods
specified in Note 6 and Note 8 of EASA AD 2018-0229 for the inspections
specified in paragraph (7) and paragraph (9) of EASA AD 2018-0229 be
extended to 30 months after the effective date of the AD, or 18,700
flight cycles, whichever occurs later. UPS reasoned that the proposed
AD is being issued to supersede AD 2018-19-18 in order to add airplanes
that are post-modification 12171 and 12249. UPS noted that post-
modification 12171 and 12249 airplanes have not had any crack findings
in service, and that previous related ADs were issued as a result of
inferior fatigue characteristics compared to airplanes that are post-
modification 12171. UPS pointed out that, of the inspections it has
completed so far, there have not been any findings that require part
replacement or major repairs. UPS also reasoned that the airworthiness
limitation item inspections that the service information is superseding
are not required until 18,700 flight cycles at the earliest. Further,
UPS asserted that the proposed grace period would require UPS to send
airplanes to a maintenance facility on a special visit to accomplish
this inspection. UPS maintained that the suggested grace period would
provide an equivalent level of safety for the proposed action.
    The FAA does not agree with the commenter's request to extend the
proposed grace period. In developing an appropriate compliance time for
this action, the FAA considered the urgency associated with the subject
unsafe condition based on similarly affected models and information
received from EASA. In addition, the FAA considered the practical
aspect of accomplishing the required modification within a period of
time that corresponds to the normal scheduled maintenance for most
affected operators. In consideration of these factors, the FAA has
determined that a 12-month grace period will ensure an acceptable level
of safety. However, under the provisions of paragraph (k)(1) of this
AD, the FAA will consider requests for approval of an extension of the
grace period if sufficient data are submitted to substantiate that the
new grace period would provide an acceptable level of safety. The FAA
has not changed this AD in this regard.

Request To Use Later Approved Revisions of Certain Service Information

    FedEx requested clarification to determine if a statement in EASA
AD 2018-0229 is applicable to this AD, and if all later approved
service information revisions are acceptable for compliance with this
AD. FedEx pointed out that the Reference Publications section of EASA
AD 2018-0229 allows the use of later approved revisions to the
specified service information for compliance.
    The FAA agrees to clarify. This AD does not exclude the Reference
Publications section of the MCAI. Therefore, this AD does not disallow
the ``later approved revisions'' language typically used in EASA ADs.
The FAA has not changed this AD in this regard.

Request To Reference Latest Service Information

    FedEx requested that Airbus Service Bulletin A300-57-6086, Revision
7, dated March 26, 2018, be allowed as acceptable for compliance with
the requirements of the proposed AD. FedEx pointed out that EASA AD
2018-0229 references Airbus Service Bulletin A300-57-6086, Revision 6,
dated July 4, 2017, which has since been revised to Airbus Service
Bulletin A300-57-6086, Revision 7, dated March 26, 2018, noting that AD
2018-19-18 allows the use of Airbus Service Bulletin A300-57-6086,
Revision 7, dated March 26, 2018.
    In response, the FAA notes that this AD refers to the MCAI for
compliance, which in turn refers to the service information that is the
required for accomplishing the required actions. As stated previously,
this AD does not exclude the Reference Publications section of the
MCAI. Therefore, this AD does not disallow the ``later approved
revisions'' language typically used in EASA ADs. Therefore, no change
to this AD is necessary in this regard.

Conclusion

    The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule as proposed, except for minor
editorial changes. The FAA has determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2018-0229, dated October 23, 2018, describes procedures for
a modification of the angle fitting attachment holes, an inspection of
certain holes of the internal lower angle fitting web for cracking, an
inspection of certain holes of the internal lower angle fitting
horizontal splicing for cracking, an inspection of the aft bottom panel
for cracking, an inspection of the FR47/Rib 1 junction area for
cracking, an inspection of certain holes of the CWB lower angle
fittings for cracking, an inspection of the CWB lower panel for
cracking, and corrective actions. The corrective actions include a
rotating probe inspection for cracking, replacing damaged fasteners,
reaming and drilling holes, installing the next nominal fastener for
oversized bore holes, and repairing cracks. This material 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.

Costs of Compliance

    The FAA estimates that this AD affects 65 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:

                                     Estimated Costs for Required Actions *
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            Action                Labor cost        Parts cost     Cost per product     Cost on U.S. operators
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Retained actions from AD 2018- Up to 727 work-   Up to $3,370....  Up to $65,165...  Up to $4,235,725.
 19-18.                         hours x $85 per
                                hour = Up to
                                $61,795.
New actions..................  242 work-hours x  $100............  $20,670.........  $1,343,550.
                                $85 per hour =
                                $20,570.
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* Table does not include estimated costs for reporting.

    The FAA estimates that it would take about 1 work-hour per product
to comply with the reporting requirement in this AD. The average labor
rate is $85 per hour. Based on these figures, the FAA estimates the
cost of reporting the inspection results on U.S. operators to be
$5,525, or $85 per product.
    The FAA has received no definitive data that would enable the
agency to provide cost estimates for the on-condition actions specified
in this AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to 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 control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is 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.

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.
    The FAA is 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.
    This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    The FAA determined that this AD will not have federalism
implications under Executive Order 13132. This AD will 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866;
    (2) Will not affect intrastate aviation in Alaska; 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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)
2018-19-18, Amendment 39-19418 (83 FR 49793, October 3, 2018), and
adding the following new AD:

2019-12-04 Airbus SAS: Amendment 39-19659; Docket No. FAA-2019-0020;
Product Identifier 2018-NM-144-AD.

(a) Effective Date

    This AD is effective August 7, 2019.

(b) Affected ADs

    (1) This AD replaces AD 2018-19-18, Amendment 39-19418 (83 FR
49793, October 3, 2018) (``AD 2018-19-18'').
    (2) This AD affects AD 2014-20-18, Amendment 39-17991 (79 FR
65879, November 6, 2014) (``AD 2014-20-18'').

(c) Applicability

    This AD applies to Airbus SAS Model A300 B4-603, B4-620, B4-622,
B4-605R, B4-622R, C4-605R Variant F, F4-605R, and F4-622R airplanes,
certificated in any category, as identified in European Aviation
Safety Agency (EASA) AD 2018-0229, dated October 23, 2018 (``EASA AD
2018-0229'').

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by reports of cracking of the frame (FR) 47
angle fitting. The FAA is issuing this AD to address cracking of the
FR47 angle fitting, which could result in reduced structural
integrity of the airplane.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with EASA AD 2018-0229.

(h) Exceptions to EASA AD 2018-0229

    (1) For purposes of determining compliance with the requirements
of this AD:

Where EASA AD 2018-0229 refers to its effective date, this AD
requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2018-0229 does not apply
to this AD.
    (3) Where Note 1 of EASA AD 2018-0229 specifies the grace period
to be counted from January 6, 2001, this AD requires the grace
period to be counted from December 19, 2005 (the effective date of
AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005)
(``AD 2005-23-08'')).
    (4) Where Note 2 and Note 4 of EASA AD 2018-0229 specify the
grace periods to be counted from November 7, 2017, without exceeding
certain inspection thresholds and intervals, the grace periods in
those Notes for this AD are within 12 months after November 7, 2018
(the effective date of AD 2018-19-18).
    (5) Paragraph (11) of EASA AD 2018-0229 specifies to report all
inspection results to Airbus. For this AD, report all inspection
results to Airbus Service Bulletin Reporting Online Application on
Airbus World (https://w3.airbus.com/) at the applicable time
specified in paragraph (h)(5)(i) or (h)(5)(ii) of this AD. The
report must include the inspection results, the method of
inspection, the airplane serial number, and the number of flight
cycles and flight hours on the airplane.
    (i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
    (ii) 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.

(i) Terminating Action for AD 2014-20-18

    Accomplishment of the action required by paragraph (1) of EASA
AD 2018-0229 and the initial inspections required by paragraphs (3),
(4), and (5) of EASA AD 2018-0229 terminates all requirements of AD
2014-20-18.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph
(1) of EASA AD 2018-0229, if those actions were performed before
December 19, 2005 (the effective date of AD 2005-23-08) using Airbus
Service Bulletin A300-57-6050, Revision 02, dated February 10, 2000.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 Section, send it to the attention of
the person identified in paragraph (l)(1) of this AD. 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.
    (2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's
EASA Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): For any service information
referenced in EASA AD 2018-0229 that contains RC procedures and
tests: Except as required by paragraph (k)(2) of this AD, RC
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.
    (4) Paperwork Reduction Act Burden Statement: 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 1
hour 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.

(l) Related Information

    (1) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax<PHONE_NUMBER>.
    (2) For Airbus service information identified in this AD that is
not incorporated by reference, contact Airbus SAS, Airworthiness
Office--EAW, Rond-Point Emile Dewoitine No: 2, 31700 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.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
    (i) European Aviation Safety Agency (EASA) AD 2018-0229, dated
October 23, 2018.
    (ii) [Reserved]
    (3) For EASA AD 2018-0229, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 6017; email
<EMAIL_ADDRESS>Internet www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://ad.easa.europa.eu.
    (4) You may view this EASA AD at the FAA, Transport Standards
Branch, 2200 South 216th St., Des Moines, WA. For information on the
availability of this material at the FAA, call<PHONE_NUMBER>. EASA AD
2018-0229 may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2019-0020.
    (5) You may view this material that is incorporated by reference
at the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on June 12, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-14152 Filed 7-2-19; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 82, Number 51 (Friday, March 17, 2017)]
[Notices]
[Pages 14258-14259]
[FR Doc No: 2017-05362]

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SECURITIES AND EXCHANGE COMMISSION

Proposed Collection; Comment Request

Upon Written Request, Copies Available From: Securities and Exchange
Commission, Office of FOIA Services, 100 F Street NE., Washington, DC
20549-2736.

Extension:
    Rule 17a-5, SEC File No. 270-155, OMB Control No. 3235-0123.

    Notice is hereby given that pursuant to the Paperwork Reduction Act
of 1995 (44 U.S.C. 3501 et seq.) (``PRA''), the Securities and Exchange
Commission (``Commission'') is soliciting comments on the existing
collection of information provided for in Rule 17a-5 (17 CFR 240.17a-
5), under the Securities Exchange Act of 1934 (15 U.S.C. 78a et seq.).
The Commission plans to submit this existing collection of information
to the Office of Management and Budget (``OMB'') for extension and
approval.
    Rule 17a-5 is the basic financial reporting rule for brokers and
dealers.\1\ The rule requires the filing of Form X-17A-5, the Financial
and Operational Combined Uniform Single Report (``FOCUS Report''),
which was the result of years of study and comments by representatives
of the securities industry through advisory committees and through the
normal rule proposal methods. The FOCUS Report was designed to
eliminate the overlapping regulatory reports required by various self-
regulatory organizations and the Commission and to reduce reporting
burdens as much as possible. The rule also requires the filing of an
annual audited report of financial statements.
---------------------------------------------------------------------------

    \1\ Rule 17a-5(c) requires a broker or dealer to furnish certain
of its financial information to customers and is subject to a
separate PRA filing (OMB Control Number 3235-0199).
---------------------------------------------------------------------------

    The FOCUS Report consists of: (1) Part I, which is a monthly report
that must be filed by brokers or dealers that clear transactions or
carry customer securities; (2) one of three alternative quarterly
reports: Part II, which must be filed by brokers or dealers that clear
transactions or carry customer securities; Part IIA, which must be
filed by brokers or dealers that do not clear transactions or carry
customer

securities; and Part IIB, which must be filed by specialized broker-
dealers registered with the Commission as OTC derivatives dealers; \2\
(3) supplemental schedules, which must be filed annually; and (4) a
facing page, which must be filed with the annual audited report of
financial statements. Under the rule, a broker or dealer that computes
certain of its capital charges in accordance with Appendix E to
Exchange Act Rule 15c3-1 must file additional monthly, quarterly, and
annual reports with the Commission.
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    \2\ Part IIB of Form X-17A-5 must be filed by OTC derivatives
dealers under Exchange Act Rule 17a-12 and is subject to a separate
PRA filing (OMB control number 3235-0498).
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    The Commission estimates that the total hours burden under Rule
17a-5 is approximately 356,020 hours per year when annualized, and the
total cost burden under Rule 17a-5 is approximately $45,133,148 per
year.
    Written comments are invited on: (a) Whether the proposed
collection of information is necessary for the proper performance of
the functions of the Commission, including whether the information
shall have practical utility; (b) the accuracy of the Commission's
estimate of the burden of the proposed collection of information; (c)
ways to enhance the quality, utility, and clarity of the information
collected; and (d) ways to minimize the burden of the collection of
information on respondents, including through the use of automated
collection techniques or other forms of information technology.
Consideration will be given to comments and suggestions submitted in
writing within 60 days of this publication.
    An agency may not conduct or sponsor, and a person is not required
to respond to, a collection of information under the PRA unless it
displays a currently valid OMB control number.
    Please direct your written comments to: Pamela Dyson, Director/
Chief Information Officer, Securities and Exchange Commission, c/o Remi
Pavlik-Simon, 100 F Street NE., Washington, DC 20549, or send an email
to<EMAIL_ADDRESS>
    Dated: March 14, 2017.
Eduardo A. Aleman,
Assistant Secretary.
[FR Doc. 2017-05362 Filed 3-16-17; 8:45 am]
 BILLING CODE 8011-01-P


[Federal Register: May 28, 2010 (Volume 75, Number 103)]
[Notices]
[Page 30018]
[DOCID:fr28my10-73]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. ER10-1281-000]

Hudson Transmission Partners, LLC; Notice of Filing

May 20, 2010.
    Take notice that on May 19, 2010, Hudson Transmission Partners, LLC
filed an application requesting the Commission to grant it a limited
waiver of PJM Interconnection, LLC, and time to post deferred security
under section 212.4(c) and Attachment O, section 6.5 of the PJM Open
Access Transmission Tariff, PJM OATT 212.4(c), Att. O 6.5 (the pro
forma ISA).
    Any person desiring to intervene or to protest this filing must
file in accordance with Rules 211 and 214 of the Commission's Rules of
Practice and Procedure (18 CFR 385.211, 385.214). 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. Any person wishing to become a party must file a notice of
intervention or motion to intervene, as appropriate. Such notices,
motions, or protests must be filed on or before the comment date. On or
before the comment date, it is not necessary to serve motions to
intervene or protests on persons other than the Applicant.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper using the ``eFiling'' link at http://
www.ferc.gov. Persons unable to file electronically should submit an
original and 14 copies of the protest or intervention to the Federal
Energy Regulatory Commission, 888 First Street, NE., Washington, DC
20426.
    This filing is accessible on-line at http://www.ferc.gov, using the
``eLibrary'' link and is 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>.
    Comment Date: 5 p.m. Eastern Time on May 21, 2010.

Kimberly D. Bose,
Secretary.
[FR Doc. 2010-12854 Filed 5-27-10; 8:45 am]
BILLING CODE 6717-01-P