[Federal Register Volume 84, Number 235 (Friday, December 6, 2019)]
[Notices]
[Pages 66915-66916]
[FR Doc No: 2019-26338]

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DEPARTMENT OF HEALTH AND HUMAN SERVICES

Food and Drug Administration

[Docket No. FDA-2019-N-5552]

Joint Meeting of the Anesthetic and Analgesic Drug Products
Advisory Committee and the Drug Safety and Risk Management Advisory
Committee; Notice of Meeting; Establishment of a Public Docket; Request
for Comments

AGENCY: Food and Drug Administration, HHS.

ACTION: Notice; establishment of a public docket; request for comments.

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SUMMARY: The Food and Drug Administration (FDA) announces a forthcoming
public advisory committee meeting of the Anesthetic and Analgesic Drug
Products Advisory Committee and the Drug Safety and Risk Management
Advisory Committee. The general function of the committees is to
provide advice and recommendations to FDA on regulatory issues. The
meeting will be open to the public. FDA is establishing a docket for
public comment on this document.

DATES: The meeting will be held on January 14, 2020, from 8 a.m. to
5:30 p.m.

ADDRESSES: FDA White Oak Campus, 10903 New Hampshire Ave., Bldg. 31
Conference Center, the Great Room (Rm. 1503), Silver Spring, MD 20993-
0002. Answers to commonly asked questions including information
regarding special accommodations due to a disability, visitor parking,
and transportation may be accessed at: https://www.fda.gov/AdvisoryCommittees/AboutAdvisoryCommittees/ucm408555.htm.
    FDA is establishing a docket for public comment on this meeting.
The docket number is FDA-2019-N-5552. The docket will close on January
13, 2020. Submit either electronic or written comments on this public
meeting by January 13, 2020. Please note that late, untimely filed
comments will not be considered. Electronic comments must be submitted
on or before January 13, 2020. The https://www.regulations.gov
electronic filing system will accept comments until 11:59 p.m. Eastern
Time at the end of January 13, 2020. Comments received by mail/hand
delivery/courier (for written/paper submissions) will be considered
timely if they are postmarked or the delivery service acceptance
receipt is on or before that date.
    Comments received on or before December 30, 2019, will be provided
to the committees. Comments received after that date will be taken into
consideration by FDA. In the event that the meeting is cancelled, FDA
will continue to evaluate any relevant applications or information, and
consider any comments submitted to the docket, as appropriate.
    You may submit comments as follows:

Electronic Submissions

    Submit electronic comments in the following way:
     Federal eRulemaking Portal: https://www.regulations.gov.
Follow the instructions for submitting comments. Comments submitted
electronically, including attachments, to https://www.regulations.gov
will be posted to the docket unchanged. Because your comment will be
made public, you are solely responsible for ensuring that your comment
does not include any confidential information that you or a third party
may not wish to be posted, such as medical information, your or anyone
else's Social Security number, or confidential business information,
such as a manufacturing process. Please note that if you include your
name, contact information, or other information that identifies you in
the body of your comments, that information will be posted on https://www.regulations.gov.
     If you want to submit a comment with confidential
information that you do not wish to be made available to the public,
submit the comment as a written/paper submission and in the manner
detailed (see ``Written/Paper Submissions'' and ``Instructions'').

Written/Paper Submissions

    Submit written/paper submissions as follows:
     Mail/Hand Delivery/Courier (for written/paper
submissions): Dockets Management Staff (HFA-305), Food and Drug
Administration, 5630 Fishers Lane, Rm. 1061, Rockville, MD 20852.
     For written/paper comments submitted to the Dockets
Management Staff, FDA will post your comment, as well as any
attachments, except for information submitted, marked and identified,
as confidential, if submitted as detailed in ``Instructions.''
    Instructions: All submissions received must include the Docket No.
FDA-2019-N-5552 for ``Joint Meeting of the Anesthetic and Analgesic
Drug Products Advisory Committee and the Drug Safety and Risk
Management Advisory Committee; Notice of Meeting; Establishment of a
Public Docket; Request for Comments.'' Received comments, those filed
in a timely manner (see ADDRESSES), will be placed in the docket and,
except for those submitted as ``Confidential Submissions,'' publicly
viewable at https://www.regulations.gov or at the Dockets Management
Staff between 9 a.m. and 4 p.m., Monday through Friday.

     Confidential Submissions--To submit a comment with
confidential information that you do not wish to be made publicly
available, submit your comments only as a written/paper submission. You
should submit two copies total. One copy will include the information
you claim to be confidential with a heading or cover note that states
``THIS DOCUMENT CONTAINS CONFIDENTIAL INFORMATION.'' FDA will review
this copy, including the claimed confidential information, in its
consideration of comments. The second copy, which will have the claimed
confidential information redacted/blacked out, will be available for
public viewing and posted on https://www.regulations.gov. Submit both
copies to the Dockets Management Staff. If you do not wish your name
and contact information be made publicly available, you can provide
this information on the cover sheet and not in the body of your
comments and you must identify the information as ``confidential.'' Any
information marked as ``confidential'' will not be disclosed except in
accordance with 21 CFR 10.20 and other applicable disclosure law. For
more information about FDA's posting of comments to public dockets, see
80 FR 56469, September 18, 2015, or access the information at: https://www.gpo.gov/fdsys/pkg/FR-2015-09-18/pdf/2015-23389.pdf.
    Docket: For access to the docket to read background documents or
the electronic and written/paper comments received, go to https://www.regulations.gov and insert the docket number, found in brackets in
the heading of this document, into the ``Search'' box and follow the
prompts and/or go to the Dockets Management Staff, 5630 Fishers Lane,
Rm. 1061, Rockville, MD 20852.

FOR FURTHER INFORMATION CONTACT: Kalyani Bhatt, Center for Drug
Evaluation and Research, Food and Drug Administration, 10903 New
Hampshire Ave., Bldg. 31, Rm. 2417, Silver Spring, MD 20993-0002, 301-
796-9001, Fax:<PHONE_NUMBER>, email<EMAIL_ADDRESS>or FDA Advisory
Committee Information Line, 1-800-741-8138<PHONE_NUMBER> in the
Washington, DC area). A notice in the Federal Register about last
minute modifications that impact a previously announced advisory
committee meeting cannot always be published quickly enough to provide
timely notice. Therefore, you should always check the FDA's website at
https://www.fda.gov/AdvisoryCommittees/default.htm and scroll down to
the appropriate advisory committee meeting link, or call the advisory
committee information line to learn about possible modifications before
coming to the meeting.

SUPPLEMENTARY INFORMATION:
    Agenda: The committees will discuss new drug application 211802 for
oxycodegol, a new molecular entity full mu-opioid receptor agonist,
submitted by Nektar Therapeutics, for the management of chronic low
back pain in adult patients with pain severe enough to require daily,
around-the-clock, long-term opioid treatment and for which alternative
treatment options are inadequate. The committees will be asked to
discuss the safety and efficacy data as well as the overall risk-
benefit profile of the product.
    FDA intends to make background material available to the public no
later than 2 business days before the meeting. If FDA is unable to post
the background material on its website prior to the meeting, the
background material will be made publicly available at the location of
the advisory committee meeting, and the background material will be
posted on FDA's website after the meeting. Background material is
available at https://www.fda.gov/AdvisoryCommittees/Calendar/default.htm. Scroll down to the appropriate advisory committee meeting
link.
    Procedure: Interested persons may present data, information, or
views, orally or in writing, on issues pending before the committees.
All electronic and written submissions submitted to the Docket (see
ADDRESSES) on or before December 30, 2019, will be provided to the
committees. Oral presentations from the public will be scheduled
between approximately 1 p.m. and 2 p.m. Those individuals interested in
making formal oral presentations should notify the contact person and
submit a brief statement of the general nature of the evidence or
arguments they wish to present, the names and addresses of proposed
participants, and an indication of the approximate time requested to
make their presentation on or before December 19, 2019. Time allotted
for each presentation may be limited. If the number of registrants
requesting to speak is greater than can be reasonably accommodated
during the scheduled open public hearing session, FDA may conduct a
lottery to determine the speakers for the scheduled open public hearing
session. The contact person will notify interested persons regarding
their request to speak by December 20, 2019.
    Persons attending FDA's advisory committee meetings are advised
that FDA is not responsible for providing access to electrical outlets.
    For press inquiries, please contact the Office of Media Affairs at
<EMAIL_ADDRESS>or<PHONE_NUMBER>.
    FDA welcomes the attendance of the public at its advisory committee
meetings and will make every effort to accommodate persons with
disabilities. If you require accommodations due to a disability, please
contact Kalyani Bhatt (see FOR FURTHER INFORMATION CONTACT) at least 7
days in advance of the meeting.
    FDA is committed to the orderly conduct of its advisory committee
meetings. Please visit our website at https://www.fda.gov/AdvisoryCommittees/AboutAdvisoryCommittees/ucm111462.htm for procedures
on public conduct during advisory committee meetings.
    Notice of this meeting is given under the Federal Advisory
Committee Act (5 U.S.C. app. 2).

    Dated: December 2, 2019.
Lowell J. Schiller,
Principal Associate Commissioner for Policy.
[FR Doc. 2019-26338 Filed 12-5-19; 8:45 am]
BILLING CODE 4164-01-P


[Federal Register Volume 80, Number 198 (Wednesday, October 14, 2015)]
[Rules and Regulations]
[Pages 61719-61720]
[FR Doc No: 2015-25718]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-1059; Directorate Identifier 2013-NE-36-AD;
Amendment 39-18281; AD 2015-20-03]
RIN 2120-AA64

Airworthiness Directives; Pratt & Whitney Canada Corp. Turboprop
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding airworthiness directive (AD) 2014-14-02 for
certain Pratt & Whitney Canada Corp. (P&WC) PW120, PW121, PW121A,
PW124B, PW127, PW127E, PW127F, PW127G, and PW127M turboprop engines. AD
2014-14-02 required removal of the O-ring seal from the fuel manifold
fitting. This new AD requires replacement of the fuel nozzle and the
fuel manifold flow adapter. This AD was prompted by reports of fuel
leaks at the interface between the fuel manifold and the fuel nozzle
that resulted in engine fire. We are issuing this AD to correct the
unsafe condition on these products.

DATES: This AD is effective November 18, 2015.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 18,
2015.

ADDRESSES: For service information identified in this AD, contact Pratt
& Whitney Canada Corp., 1000 Marie-Victorin, Longueuil, Quebec, Canada,
J4G 1A1; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; Web site: www.pwc.ca.
You may view this service information at the FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA. For
information on the availability of this material at the FAA, call 781-
238-7125. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2013-
1059.

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-2013-
1059; 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 AD, the mandatory continuing airworthiness information,
regulatory evaluation, any comments received, and other information.
The address for the Docket Office (phone:<PHONE_NUMBER>) is Document
Management Facility, 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: Barbara Caufield, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2014-14-02, Amendment 39-17896 (79 FR 39958,
July 11, 2014), (``AD 2014-14-02''). AD 2014-14-02 applied to certain
P&WC PW120, PW121, PW121A, PW124B, PW127, PW127E, PW127F, PW127G, and
PW127M turboprop engines. The NPRM published in the Federal Register on
June 2, 2015 (80 FR 31325). The NPRM proposed to require replacement of
the fuel nozzle and the fuel manifold flow adapter.

Related Service Information Under 1 CFR Part 51

    We reviewed P&WC SB No. PW100-72-21861, dated November 21, 2014,
which identifies the final fuel nozzle configuration. 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 of this AD.

Comments

    We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (80 FR 31325, June 2,
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and
the public interest require adopting this AD as proposed.

Costs of Compliance

    We estimate that this AD affects 150 engines installed on airplanes
of U.S. registry. We also estimate that it will take about 2.5 hours
per engine to comply with this AD. The average labor rate is $85 per
hour. Required parts cost about $146,594 per engine. Based on these
figures, we estimate the cost of this AD on U.S. operators to be
$22,020,975.

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

    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) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),

    (3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends part 39 of the Federal Aviation
Regulations (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)
2014-14-02], Amendment 39-17896 (79 FR 39958, July 11, 2014), and
adding the following new AD:

2015-20-03 Pratt & Whitney Canada Corp.: Amendment 39-18281; Docket
No. FAA-2013-1059; Directorate Identifier 2013-NE-36-AD.

(a) Effective Date

    This AD is effective November 18, 2015.

(b) Affected ADs

    This AD replaces AD 2014-14-02, Amendment 39-17896 (79 FR 39958,
July 11, 2014).

(c) Applicability

    This AD applies to Pratt & Whitney Canada Corp. (P&WC) PW120,
PW121, and PW121A turboprop engines with post SB 21610
configuration; PW124B, PW127, PW127E, and PW127F turboprop engines
with post SB 21607 configuration; PW127E and PW127F turboprop
engines with serial numbers (S/Ns) PCE-EB0366 and earlier; PW127G
turboprop engines with S/Ns PCE-AX0275 and earlier; and PW127M
turboprop engines with S/Ns PCE-ED0810 and earlier.

(d) Unsafe Condition

    This AD was prompted by reports of fuel seepage past the metal-
to-metal sealing surfaces of the fuel nozzle and fuel manifold flow
adapter. We are issuing this AD to prevent in-flight fuel leakage,
engine fire, damage to the engine, and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified,
unless already done. Within 1,500 flight hours after the effective
date of this AD, or at the next engine shop visit, whichever occurs
first:
    (1) Remove the O-ring seal from the fuel manifold fitting,
    (2) Remove fuel manifold flow adapter, part numbers (P/Ns)
3059754-01, 3059757-01, and 3059760-01; and
    (3) Install a fuel nozzle gasket and fuel manifold flow adapter
that are eligible for installation, in accordance with paragraphs
3.A, 3.B, and 3.C of P&WC SB No. PW100-72-21861, dated November 21,
2014.

(f) Installation Prohibition

    After the effective date of this AD, fuel manifold adapter, P/Ns
3059754-01, 3059757-01, and 3059760-01, and fuel manifold gasket, P/
N 3079354-01, are not eligible for installation in any engine.

(g) Definition

    For the purpose of this AD, an engine shop visit is the
induction of an engine into the shop for maintenance involving the
separation of pairs of major mating engine flanges. The separation
of engine flanges solely for the purpose of transportation without
subsequent engine maintenance does not constitute an engine shop
visit.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs
to this AD. Use the procedures found in 14 CFR 39.19 to make your
request. You may email your request to<EMAIL_ADDRESS>
(i) Related Information

    (1) For more information about this AD, contact Barbara
Caufield, Aerospace Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New England Executive Park,
Burlington, MA 01803; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>    (2) Refer to MCAI Transport Canada AD CF-2014-41, dated November
26, 2014, for related information. 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-2013-1059.

(j) 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 the AD specifies otherwise.
    (i) Pratt & Whitney Canada Corp. Service Bulletin (SB) No.
PW100-72-21861, dated November 21, 2014.
    (ii) Reserved.
    (3) For Pratt & Whitney Canada Corp. service information
identified in this AD, contact Pratt & Whitney Canada Corp., 1000
Marie-Victorin Blvd., Longueuil, Quebec, Canada, J4G 1A1; phone:
800-268-8000; fax:<PHONE_NUMBER>; Web site: www.pwc.ca.
    (4) You may view this service information at FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington,
MA. For information on the availability of this material at the FAA,
call<PHONE_NUMBER>.
    (5) You may view this service information at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call<PHONE_NUMBER>, or go to:
http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on September 22, 2015.
Colleen M. D'Alessandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2015-25718 Filed 10-13-15; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 83, Number 66 (Thursday, April 5, 2018)]
[Rules and Regulations]
[Pages 14568-14574]
[FR Doc No: 2018-06336]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0245; Product Identifier 2018-CE-012-AD; Amendment
39-19234; AD 2018-07-03]
RIN 2120-AA64

Airworthiness Directives; Piper Aircraft, Inc.

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2018-02-05 for
certain Piper Aircraft, Inc. Models PA-28-140, PA-28-150, PA-28-151,
PA-28-160, PA-28-161, PA-28-180, PA-28-181, PA-28-236, PA-28-201T, PA-
28R-180, PA-28R-200, PA-28R-201, PA-28R-201T, PA-28RT-201, and PA-28RT-
201T airplanes. AD 2018-02-

05 required inspecting the fuel tank selector cover to verify the left
and right fuel tank selector placards are located at the proper
positions and replacing those that are improperly located with new
placards. This AD addresses the same unsafe condition and requires the
same actions as AD 2018-02-05, but changes the inspection of the fuel
tank selector cover to a preflight check and allows for various fuel
selector clocking configurations. This AD was prompted by our
determination to allow the owner/operator (pilot) holding at least a
private pilot certificate to perform the preflight check. We are
issuing this AD to allow the pilot to do a preflight check of the fuel
selector placards.

DATES: This AD is effective April 20, 2018.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 20,
2018.
    We must receive any comments on this AD by May 21, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
    For service information identified in this final rule, contact
Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, FL 32960;
telephone:<PHONE_NUMBER>; internet: www.piper.com/technical-publications-documents/. You may view this service information at the
FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri
64106. For information on the availability of this material at the FAA,
call<PHONE_NUMBER>. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0245.

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-2018-
0245; 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 street address for Docket Operations (phone:
800-647-5527) is listed above. Comments will be available in the AD
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT:  Boyce Jones, Aerospace Engineer,
Atlanta ACO Branch, FAA, 1701 Columbia Avenue, College Park, Georgia
30337; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
[email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued AD 2018-02-05, Amendment 39-19158 (83 FR 3064, January
23, 2018), (``AD 2018-02-05''), for certain Piper Aircraft, Inc. Models
PA-28-140, PA-28-150, PA-28-151, PA-28-160, PA-28-161, PA-28-180, PA-
28-181, PA-28-236, PA-28-201T, PA-28R-180, PA-28R-200, PA-28R-201, PA-
28R-201T, PA-28RT-201, and PA-28RT-201T airplanes. AD 2018-02-05
required inspecting the fuel tank selector cover to verify the left and
right fuel tank selector placards are located at the 12:00 and 3:00
clock positions, respectively, and replacing those that are improperly
located with new placards. AD 2018-02-05 resulted from a quality
control issue that resulted in the installation of fuel tank selector
covers with the placement of the left and right fuel tank selector
placards installed in reverse. We issued AD 2018-02-05 to prevent fuel
management error. The unsafe condition, if not addressed, could result
in fuel starvation and loss of engine power in flight.

Actions Since AD 2018-02-05 Was Issued

    Since we issued AD 2018-02-05, we have determined that the owner/
operator (pilot) holding at least a private pilot certificate will be
allowed to perform the preflight check of the fuel tank selector
placards.

Related Service Information Under 1 CFR Part 51

    We reviewed Piper Aircraft, Inc. Service Bulletin No. 1309A, dated
March 6, 2018. The service bulletin describes procedures for doing a
preflight check of the fuel tank selector cover to verify the left and
right fuel tank selector placards are located in the proper positions,
and replacing those that are improperly located with a new placard.
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

    We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires doing a preflight check of the fuel tank selector
cover to verify the left and right fuel tank selector placards are
located at the proper positions and replacing those that are improperly
located with new placards. The preflight check required in this AD may
be performed by the owner/operator (pilot) holding at least a private
pilot certificate and must be entered into the airplane records showing
compliance with this AD in accordance with 14 CFR 43.9 (a)(1)-(4) and
14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14
CFR 91.417, 121.380, or 135.439.

FAA's Justification and Determination of the Effective Date

    The FAA previously determined that the risk to the flying public
justified waiving notice and comment prior to the adoption of AD 2018-
02-05. This AD is being issued to relieve the maintenance requirements
found in 2018-02-05, by changing the inspection of the fuel tank
selector cover to a preflight check, while also allowing for various
fuel selector clocking configurations. Because the substance of AD
2018-02-05 remains the same, but for the relieving aspects noted in
this AD, we find good cause that notice and opportunity for prior
public comment are unnecessary. In addition, for the reasons stated
above, we find that good cause exists for making this amendment
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this final
rule. Send your comments to an address listed under the ADDRESSES
section. Include the docket number FAA-2018-0245 and product identifier
2018-CE-012-AD at the beginning of your comments. We specifically
invite comments on the overall regulatory, economic, environmental, and
energy

aspects of this final rule. We will consider all comments received by
the closing date and may amend this final rule because of 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 final rule.

Costs of Compliance

    We estimate that this AD affects 17,957 airplanes, of U.S.
registry.
    We estimate the following costs to comply with this AD:
    Since this AD allows the owner/operator (pilot) holding at least a
private pilot certificate to perform the required preflight check of
the fuel tank selector placards, there is a reduction in cost
associated with this AD.
    We estimate the following costs to do any necessary replacements
that will be required based on the results of the preflight check of
the left and right fuel tank selector placards for proper installation
inspection. We have no way of determining the number of aircraft that
might need this replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Install new fuel selector placards on the fuel  .5 work-hour x $85 per hour =              $9.26          $51.76
 selector cover.                                 $42.50.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.

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.
    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 small airplanes, gliders,
balloons, airships, domestic business jet transport airplanes, and
associated appliances to the Director of the Policy and Innovation
Division.

Regulatory Findings

    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) Is not a ``significant rule'' under 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends part 39 of the Federal Aviation
Regulations (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)
2018-02-05, Amendment 39-19158 (83 FR 3064, January 23, 2018) and
adding the following new AD:

2018-07-03 Piper Aircraft, Inc: Amendment 39-19234; Docket No. FAA-
2018-0245; Product Identifier 2018-CE-012-AD.

(a) Effective Date

    This AD is effective April 20, 2018.

(b) Affected ADs

    This AD replaces 2018-02-05, Amendment 39-19158 (83 FR 3064,
January 23, 2018) (``AD 2018-02-05'').

(c) Applicability

    This AD applies to the following Piper Aircraft, Inc. airplane
models and serial numbers (S/Ns) that are certificated in any
category:

 Table--1 to Paragraph (c) of This AD--Applicable Airplane Models and S/
                                   Ns
------------------------------------------------------------------------
                       Model                             Serial No.
------------------------------------------------------------------------
PA-28-140.........................................  28-20001 through 28-
                                                     26946; 28-7125001
                                                     through 28-7725290.
PA-28-150.........................................  28-03, 28-1 through
                                                     28-4377, and 28-
                                                     1760A.
PA-28-151.........................................  28-7415001 through
                                                     28-7715314.
PA-28-160.........................................  28-03, 28-1 through
                                                     28-4377, and 28-
                                                     1760A.

PA-28-161.........................................  2841001 through
                                                     2841365, 28-7716001
                                                     through 28-8216300,
                                                     28-8316001 through
                                                     28-8616057, 2816001
                                                     through 2816109,
                                                     2816110 through
                                                     2816119, and
                                                     2842001 through
                                                     2842420.
PA-28-180.........................................  28-03, 28-671
                                                     through 28-5859, 28-
                                                     7105001 through 28-
                                                     7205318, 28-E13,
                                                     and 28-7305001
                                                     through 28-7505261.
PA-28-181.........................................  28-7690001 through
                                                     28-8690056, 28-
                                                     8690061, 28-
                                                     8690062, 2890001
                                                     through 2890205,
                                                     2890206 through
                                                     2890231, and
                                                     2843001 through
                                                     2843879.
PA-28-236.........................................  28-7911001 through
                                                     28-8611008 and
                                                     2811001 through
                                                     2811050.
PA-28-201T........................................  28-7921001 through
                                                     28-7921095.
PA-28R-180........................................  28R-30002 through
                                                     28R-31270 and 28R-
                                                     7130001 through 28R-
                                                     7130019.
PA-28R-200........................................  28R-30482, 28R-35001
                                                     through 28R-35820,
                                                     28R-7135001 through
                                                     28R-7135238, and
                                                     28R-7235001 through
                                                     28R-7635545.
PA-28R-201........................................  28R-7737002 through
                                                     28R-7837317,
                                                     2837001 through
                                                     2837061, and
                                                     2844001 through
                                                     2844171.
PA-28R-201T.......................................  28R-7703001 through
                                                     28R-7803374 and
                                                     2803001 through
                                                     2803015.
PA-28RT-201.......................................  28R-7918001 through
                                                     28R-8218026.
PA-28RT-201T......................................  28R-7931001 through
                                                     28R-8631005, and
                                                     2831001 through
                                                     2831038.
------------------------------------------------------------------------

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 11, Placard and Markings.

(e) Unsafe Condition

    This AD was prompted by our determination to change the
inspection of the fuel tank selector cover to a preflight check and
allows for various fuel selector clocking configurations. We are
issuing this AD to allow the pilot to do a preflight check of the
fuel selector placards.

(f) Compliance

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

(g) Preflight Check of the Fuel Selector Cover

    Before further flight after April 20, 2018 (the effective date
of this AD), check the left and right fuel selector cover placards
for proper installation using the Appendix to this AD. If the fuel
selector placards are properly installed, no further action is
required. The preflight check of the fuel selector cover may be
performed by the owner/operator (pilot) holding at least a private
pilot certificate and must be entered into the airplane records
showing compliance with this AD in accordance with 14 CFR 43.9
(a)(1)-(4) and 14 CFR 91.417(a)(2)(v). The record must be maintained
as required by 14 CFR 91.417, 121.380, or 135.439.

(h) Install Temporary Fuel Selector Placards

    If improper (reversed clock positions) installation of the left
and right fuel selector placards is found during the preflight check
of the fuel selector cover required in paragraph (g) of this AD,
before further flight, fabricate and install temporary left and
right fuel selector placards using Part II of Piper SB No. 1309A,
dated March 6, 2018. In lieu of installing the temporary placards
required by this paragraph, you may install the permanent placards
specified in paragraph (i) of this AD. An FAA-approved licensed
mechanic authorized to do maintenance is required to do any
fabrication and installation of the fuel selector placards required
in this AD.

(i) Install Permanent Fuel Selector Placards

    Within the next 100 hours time-in-service (TIS) after April 20,
2018 (the effective date of this AD), replace the temporary placard
installed in paragraph (h) of this AD with permanent left and right
fuel selector placards using Part III of Piper SB No. 1309A, dated
March 6, 2018, unless already done in lieu of installing the
temporary placards specified in paragraph (h) of this AD.

(j) Credit for Previous Actions

    This AD allows credit for doing the actions required in
paragraphs (g) through (i) of this AD using Piper Aircraft, Inc.
Service Bulletin No. 1309, dated October 10, 2017, if done before
the effective date of this AD in compliance with AD 2018-02-05.

(k) Special Flight Permit

    A special flight permit is allowed for this AD per 14 CFR 39.23
with the following limitations: Flights are not to exceed a total of
100 hours TIS with temporary placards installed.

(l) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta ACO 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
manager of the certification office, send it to the attention of the
person identified in paragraph (m) of this AD.
    (2) 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.
    (3) AMOCs approved for AD 2018-02-05 are not approved as AMOCs
for the corresponding provisions of this AD.

(m) Related Information

    For more information about this AD, contact Boyce Jones,
Aerospace Engineer, Atlanta ACO Branch, FAA, 1701 Columbia Avenue,
College Park, Georgia 30337; phone:<PHONE_NUMBER>; fax: (404) 474-
5606; email: [email protected].

(n) 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) Piper Aircraft, Inc. Service Bulletin No. 1309A, dated March
6, 2018.
    (ii) Reserved.
    (3) For Piper Aircraft, Inc. service information identified in
this AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach,
FL 32960; telephone:<PHONE_NUMBER>; internet: www.piper.com/technical-publications-documents/.
    (4) You may view this service information at FAA, Policy and
Innovation Division, 901 Locust, Kansas City, Missouri 64106. For
information on the availability of this material at the FAA, call
(816) 329-4148.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

Appendix to AD 2018-07-03

Special Preflight Check

    Note: This action may be performed by the owner/operator (pilot)
holding at least a private pilot certificate and must be entered
into the airplane records showing compliance with AD 2018-07-03 in
accordance with 14 CFR 43.9 (a)(1)-(4) and 14 CFR 91.417(a)(2)(v).
The record must be maintained as required by 14 CFR 91.417, 121.380,
or 135.439. This action may also be performed by an FAA-approved
licensed mechanic.
    (1) Compare the currently installed fuel selector cover against
the covers shown in Figure 2, View A-A:
    (a) If the currently installed fuel selector cover matches the
cover shown in Figure 2, View A-A, then proceed to Step 2.
    (b) If the currently installed fuel selector cover does not
match the cover shown Figure 2, View A-A (Note: The fuel selector
cover

that does not match View A-A is a flat round plate without any
features that limit the rotational travel of the fuel selector
lever), then the remaining instructions in AD 2018-07-03 do not
apply and no further action is required. Compliance with this part
of AD 2018-07-03 must be documented by the owner/operator (pilot)
holding at least a private pilot certificate, and must be entered
into the aircraft records showing compliance with this AD in
accordance with 14 CFR 43.9 (a)(1)-(4) and 14 CFR 91.417(a)(2)(v).
The record must be maintained as required by 14 CFR 91.417, 121.380,
or 135.439.

    Note: Documentation in the aircraft logbook should include: (1)
Current Date (2) Tach Time (3) Statement that the comparison has
been accomplished, including the AD number and Revision date (4)
Sign and Print Name (5) Certificate Type & Number.
BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TR05AP18.001

[GRAPHIC] [TIFF OMITTED] TR05AP18.002

BILLING CODE 4910-13-C
    (2) Compare the currently installed fuel selector cover to the
illustration in Figure 2, View A-A. Examine all placards for proper
placement, with specific emphasis on the location of the placards
labeled L TANK and R TANK.

    Note: The fuel selector cover placard positions will vary. See
Figure 2, View A-A.

    (a) If the placards are in the proper locations, then no further
action is required. Compliance with this part AD 2018-07-03 must be
documented by the owner/operator (pilot) holding at least a private
pilot

certificate, and must be entered into the aircraft records showing
compliance with this AD in accordance with 14 CFR 43.9 (a)(1)-(4)
and 14 CFR 91.417(a)(2)(v). The record must be maintained as
required by 14 CFR 91.417, 121.380, or 135.439.

    Note: Documentation in the aircraft logbook should include: (1)
Current Date (2) Tach Time (3) Statement that the comparison has
been accomplished, including the AD number and Revision date (4)
Sign and Print Name (5) Certificate Type & Number.

    (b) If replacement is required, proceed to either paragraph (h)
and (i) of AD 2018-07-03.

    Issued in Kansas City, Missouri, on March 23, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division, Aircraft Certification
Service.
[FR Doc. 2018-06336 Filed 4-4-18; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 88, Number 29 (Monday, February 13, 2023)]
[Rules and Regulations]
[Pages 9185-9188]
[FR Doc No: 2023-02934]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1050; Project Identifier AD-2021-01257-T;
Amendment 39-22316; AD 2023-02-09]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2007-10-
04, which applied to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-
82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. AD
2007-10-04 required repetitive inspections to detect cracks in the
horizontal stabilizer, and related investigative and corrective actions
if necessary. Since the FAA issued AD 2007-10-04, it has been
determined that certain compliance times and repetitive intervals must
be reduced to address the unsafe condition. This AD continues to
require the actions specified in AD 2007-10-04 with revised compliance
times for certain actions. The FAA is issuing this AD to address the
unsafe condition on these products.

DATES: This AD is effective March 20, 2023.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 20,
2023.

ADDRESSES:
    AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2022-1050; 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, 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.
    Material Incorporated by Reference:
     For service information incorporated by reference in this
AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone<PHONE_NUMBER>; website myboeingfleet.com.
     You may view this service information at the FAA,
Airworthiness

Products Section, Operational Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the availability of this material at the
FAA, call<PHONE_NUMBER>. It is also available at regulations.gov under
Docket No. FAA-2022-1050.

FOR FURTHER INFORMATION CONTACT: Manuel Hernandez, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone:<PHONE_NUMBER>; email:
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2007-10-04, Amendment 39-15045 (72 FR
25960, May 8, 2007) (AD 2007-10-04). AD 2007-10-04 applied to all
McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-
83), DC-9-87 (MD-87), and MD-88 airplanes. The NPRM published in the
Federal Register on September 15, 2022 (87 FR 56593). The NPRM was
prompted by the determination that certain compliance times and
repetitive intervals must be reduced for the high frequency eddy
current (HFEC) surface and open hole inspections of the rear spar upper
caps. The FAA received a report from Boeing of a crack found along
fasteners in the upper rear spar that was longer than two inches during
an inspection of the horizontal rear spar upper cap on a Model DC-9-82
(MD-82) airplane with 69,799 flight hours and 38,520 flight cycles. The
crack was discovered prior to the compliance time intervals for the
repetitive inspections required by AD 2007-10-04; it was determined
that certain compliance times do not provide at least two opportunities
to reliably detect dual origin cracks before they reach critical
length.
    In addition, since the FAA issued AD 2007-10-04, the legal name of
the manufacturer has been changed from McDonnell Douglas Corporation to
The Boeing Company on the most recent type certificate data sheet for
the affected airplane models.
    In the NPRM, the FAA proposed to continue to require the actions
specified in AD 2007-10-04, with revised compliance times for certain
actions. The FAA is issuing this AD to detect and correct cracks in the
upper and lower aft skin panels and rear spar upper caps, which, if not
corrected, could lead to the loss of overall structural integrity of
the horizontal stabilizer.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from one commenter, Boeing. The following
presents the comments received on the NPRM and the FAA's response to
each comment.

Request To Revise ``Related Service Information Under 1 CFR Part 51''

    Boeing requested that the FAA revise the description of the service
information in the ``Related Service Information under 1 CFR part 51''
paragraph in the NPRM. The paragraph in the NPRM reads as follows:
``Corrective actions include stop drilling the end of the crack,
trimming out the crack and installing filler, installing a horizontal
stabilizer upper and lower aft skin panel splice, replacing the
horizontal stabilizer upper and lower aft skin panel, installing
bushings and cold working holes, removing the crack and performing a
repair, replacing the horizontal stabilizer rear spar upper cap splice,
and replacing the splice repair with a new horizontal stabilizer rear
spar upper cap.'' Boeing suggested the FAA revise the text to read:
``Corrective actions to the horizontal stabilizer skin panel upper and
lower aft skin panel include options for (1) stop drilling the end of
the crack or trimming out the crack, and then doing a skin splice
repair or replacing the skin at the given compliance time, (2)
installing a skin panel splice, or (3) replacing the skin panel.
Corrective actions to the horizontal stabilizer rear spar upper cap
include options for (1) enlarging the hole to remove the crack, (2)
performing a cap splice repair, (3) performing a cap splice repair and
cold-working certain holes, (4) performing a cap replacement, or (5)
performing a cap replacement and cold-working certain holes.'' Boeing
reasoned that the revised text would distinguish between corrective
actions specifically for skins and those for spar cap, per the Boeing
Service Bulletin, and would also clarify that replacing a temporarily
repaired structure is applicable only to the skin panel and not the
spar cap; a repaired spar cap is inspected repetitively.
    The FAA agrees and revised the ``Related Service Information under
1 CFR part 51'' paragraph in the final rule as requested.

Conclusion

    The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, and
any other changes described previously, this AD is adopted as proposed
in the NPRM. None of the changes will increase the economic burden on
any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Service Bulletin MD80-55A065,
Revision 2, dated October 11, 2021. This service information specifies
procedures for repetitive eddy current inspections (HFEC or low
frequency eddy current inspections, as applicable) of the horizontal
stabilizer; and applicable corrective actions. Corrective actions to
the horizontal stabilizer skin panel upper and lower aft skin panel
include options for (1) stop drilling the end of the crack or trimming
out the crack, and then doing a skin splice repair or replacing the
skin at the given compliance time, (2) installing a skin panel splice,
or (3) replacing the skin panel. Corrective actions to the horizontal
stabilizer rear spar upper cap include options for (1) enlarging the
hole to remove the crack, (2) performing a cap splice repair, (3)
performing a cap splice repair and cold-working certain holes, (4)
performing a cap replacement, or (5) performing a cap replacement and
cold-working certain holes.
    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 ADDRESSES.

Costs of Compliance

    The FAA estimates that this AD affects 22 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections (retained actions      8 work-hours x $85               $0  $680 per inspection  $14,960 per
 from AD 2007-10-04).               per hour = $680,                     cycle.               inspection cycle.
                                    per inspection
                                    cycle.

Inspections (new proposed action)  Up to 20 work-hours               0  Up to $1,700 per     Up to $37,400 per
                                    x $85 per hour =                     inspection cycle.    inspection cycle.
                                    $1,700 per
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary
corrective actions (e.g., repairs, replacements, installation) that
would be required based on the results of the inspection. The FAA has
no way of determining the number of aircraft that might need these
corrective actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
             Action                     Labor cost                Parts cost               Cost per product
----------------------------------------------------------------------------------------------------------------
Repair, replacement and          Up to 656 work-hours x   Up to $128,892...........  Up to $184,652.
 installation of upper or lower   $85 per hour = $55,760.
 aft skin panel or splice.
Stop drill repair..............  4 work-hours x $85 per   $0.......................  $340.
                                  hour = $340.
Trim out.......................  8 work-hours x $85 per   $0.......................  $680.
                                  hour = $680.
Install bushings and cold work.  26 work-hours x $85 per  $9,827...................  $12,037.
                                  hour = $2,210.
Crack removal and repair.......  6 work-hours x $85 per   $2,033...................  $2,543.
                                  hour = $510.
Replace rear spar upper cap....  368 work-hours x $85     $36,402..................  $67,682.
                                  per hour = $31,280.
----------------------------------------------------------------------------------------------------------------

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.

Regulatory Findings

    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.

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:
0
a. Removing Airworthiness Directive (AD) 2007-10-04, Amendment 39-15045
(72 FR 25960, May 8, 2007); and
0
b. Adding the following new AD:

2023-02-09 The Boeing Company: Amendment 39-22316; Docket No. FAA-
2022-1050; Project Identifier AD-2021-01257-T.

(a) Effective Date

    This airworthiness directive (AD) is effective March 20, 2023.

(b) Affected ADs

    This AD replaces AD 2007-10-04, Amendment 39-15045 (72 FR 25960,
May 8, 2007) (AD 2007-10-04).

(c) Applicability

    This AD applies to all The Boeing Company Model DC-9-81 (MD-81),
DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88
airplanes, certificated in any category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of cracks found in the
horizontal stabilizer in the upper and lower aft skin panels at the
aft inboard corner at station XH = 8.2 and in the rear spar upper
caps adjacent to the aft skin panel at station XH = 10.0; and by a
determination that certain compliance times and inspection intervals
must be reduced. The FAA is issuing this AD to detect and correct
cracks in the upper and lower aft skin panels and rear spar upper
caps, which, if not corrected, could lead to the loss of overall
structural integrity of the horizontal stabilizer.

(f) Compliance

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

(g) Repetitive Inspections and Corrective Actions

    Except as specified in paragraph (h) of this AD: At the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin MD80-55A065, Revision 2, dated October
11, 2021, do an eddy current inspection to detect any cracking in
the horizontal stabilizer and do all applicable repetitive
inspections and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin MD80-
55A065, Revision 2, dated October 11, 2021. Do all applicable
repetitive inspections and corrective actions at the times specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
MD80-55A065, Revision 2, dated October 11, 2021.

(h) Exceptions to Service Information Specifications

    (1) Where the Compliance Time columns of the tables in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin MD80-55A065,
Revision 2, dated October 11, 2021, use the phrase ``the original
issue date of this service bulletin,'' this AD requires using May
23, 2007 (the effective date of AD 2007-10-04).
    (2) Where the Compliance Time columns of the tables in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin MD80-55A065,
Revision 2, dated October 11, 2021, use the phrase ``the Revision 2
date of this service bulletin,'' this AD requires using ``the
effective date of this AD.''

(i) Credit for Previous Actions

    (1) This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin MD80-
55A065, dated April 25, 2007. This service information was
incorporated by reference in AD 2007-10-04, Amendment 39-15045 (72
FR 25960, May 8, 2007).
    (2) This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin MD80-
55A065, Revision 1, dated September 23, 2008. This service
information is not incorporated by reference in this AD.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO 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 responsible Flight Standards
Office, as appropriate. If sending information directly to the
manager of the certification office, send it to the attention of the
person identified in paragraph (k)(1) of this AD. Information may be
emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
    (3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Los
Angeles ACO Branch, FAA, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
    (4) AMOCs approved for AD 2007-10-04 are approved as AMOCs for
the corresponding provisions of Boeing Alert Service Bulletin MD80-
55A065, Revision 2, dated October 11, 2021, that are required by
paragraph (g) of this AD, except the AMOCs specified in paragraphs
(j)(4)(i) through (iii) of this AD are not approved as AMOCs for
this AD.
    (i) FAA Letter Number 120L-14-226a, dated January 29, 2015.
    (ii) FAA Letter Number 120L-15-384b, dated November 2, 2015.
    (iii) FAA Letter Number 120L-10-345, dated August 3, 2010.

(k) Related Information

    (1) For more information about this AD, contact Manuel
Hernandez, Aerospace Engineer, Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone:<PHONE_NUMBER>; email: [email protected].
    (2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (l)(3) and (4) of this AD.

(l) 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 the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin MD80-55A065, Revision 2, dated
October 11, 2021.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone<PHONE_NUMBER>; website myboeingfleet.com.
    (4) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability
of this material at the FAA, call<PHONE_NUMBER>.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on January 24, 2023.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2023-02934 Filed 2-10-23; 8:45 am]
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