[Federal Register Volume 87, Number 142 (Tuesday, July 26, 2022)]
[Notices]
[Pages 44409-44412]
[FR Doc No: 2022-15954]

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DEPARTMENT OF HEALTH AND HUMAN SERVICES

Food and Drug Administration

[Docket No. FDA-2022-N-0862]

Agency Information Collection Activities; Proposed Collection;
Comment Request; The Real Cost Campaign Outcomes Evaluation Study:
Cohort 3

AGENCY: Food and Drug Administration, HHS.

ACTION: Notice.

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SUMMARY: The Food and Drug Administration (FDA, Agency, or we) is
announcing an opportunity for public comment on the proposed collection
of certain information by the Agency. Under the Paperwork Reduction Act
of 1995 (PRA), Federal Agencies are required to publish a notice in the
Federal Register concerning each proposed collection of information and
to allow 60 days for public comment in response to the notice. This
notice

solicits comments on a proposed information collection titled ``The
Real Cost Campaign Outcomes Evaluation Study: Cohort 3.''

DATES: Submit either electronic or written comments on the collection
of information by September 26, 2022.

ADDRESSES: You may submit comments as follows. Please note that late,
untimely filed comments will not be considered. Electronic comments
must be submitted on or before September 26, 2022. The https://www.regulations.gov electronic filing system will accept comments until
11:59 p.m. Eastern Time at the end of September 26, 2022. 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.

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-2022-N-0862 for ``The Real Cost Campaign Outcomes Evaluation Study:
Cohort 3.'' 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,<PHONE_NUMBER>.
     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.'' The Agency 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 to 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 this 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.govinfo.gov/content/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,<PHONE_NUMBER>.

FOR FURTHER INFORMATION CONTACT: JonnaLynn Capezzuto, Office of
Operations, Food and Drug Administration, Three White Flint North, 10A-
12M, 11601 Landsdown St., North Bethesda, MD 20852,<PHONE_NUMBER>,
[email protected].

SUPPLEMENTARY INFORMATION: Under the PRA (44 U.S.C. 3501-3521), Federal
Agencies must obtain approval from the Office of Management and Budget
(OMB) for each collection of information they conduct or sponsor.
``Collection of information'' is defined in 44 U.S.C. 3502(3) and 5 CFR
1320.3(c) and includes Agency requests or requirements that members of
the public submit reports, keep records, or provide information to a
third party. Section 3506(c)(2)(A) of the PRA (44 U.S.C. 3506(c)(2)(A))
requires Federal Agencies to provide a 60-day notice in the Federal
Register concerning each proposed collection of information before
submitting the collection to OMB for approval. To comply with this
requirement, FDA is publishing notice of the proposed collection of
information set forth in this document.
    With respect to the following collection of information, FDA
invites comments on these topics: (1) whether the proposed collection
of information is necessary for the proper performance of FDA's
functions, including whether the information will have practical
utility; (2) the accuracy of FDA's estimate of the burden of the
proposed collection of information, including the validity of the
methodology and assumptions used; (3) ways to enhance the quality,
utility, and clarity of the information to be collected; and (4) ways
to minimize the burden of the collection of information on respondents,
including through the use of automated collection techniques, when
appropriate, and other forms of information technology.

The Real Cost Campaign Outcomes Evaluation Study: Cohort 3

OMB Control Number 0910--NEW

    This information collection supports the development and
implementation of FDA public education campaigns related to tobacco
use. To reduce the public health burden of tobacco use in the United
States and educate the public--especially young people--about the
dangers of tobacco use, the FDA Center for Tobacco Products (CTP) is
developing and implementing multiple public education campaigns.
    FDA launched ``The Real Cost'' in February 2014, seeking to reduce
tobacco use among at-risk youth ages 12-17 in the United States who are
open to smoking cigarettes and/or using electronic nicotine delivery
systems (ENDS) products, or have already experimented with cigarettes
and/or ENDS products. Complementary

evaluation studies, including the ``Evaluation of FDA's Public
Education Campaign on Teen Tobacco (ExPECTT),'' were designed and
implemented to measure awareness of and exposure to ``The Real Cost''
paid media campaign among youth ages 12-17 in targeted areas of the
United States.
    The first cohort (ExPECTT: Cohort 1) assessed the campaign's impact
on outcome variables of interest from November 2013 to November 2016.
The second cohort (ExPECTT: Cohort 2) has been assessing the campaign's
impact on outcome variables of interest from June 2018 and will run
through August 2022. To continue assessing the impact of ``The Real
Cost'' campaign, FDA will implement The Real Cost Campaign Outcomes
Evaluation Study: Cohort 3. The study will consist of four waves of
data collection, including the baseline survey and three followup (FU)
surveys. Online surveys with youth ages 11-20 will be conducted at
baseline.
    Online surveys of youth will be conducted in the United States to
measure the effectiveness of FDA's ``The Real Cost'' campaign. The
purpose of FDA's The Real Cost Campaign Outcomes Evaluation Study:
Cohort 3 is to provide credible evidence that changes in key outcomes
can be attributed to exposure to the campaign. The strength of the
attribution is determined by the ability of the evaluation approach to
rule out alternative explanations for observed changes in key outcomes.
Attributing effects to a campaign require using multiple, complementary
methods that build a case that exposure to the campaign leads to
changes in key outcomes. For a national campaign evaluation, FDA can
improve attribution by carefully assessing potential confounders. To
improve attribution, we intend to measure variation in both potential
campaign exposure (e.g., market-level delivery) and self-reported
campaign exposure to media advertising.
    The goal of The Real Cost Campaign Outcomes Evaluation Study:
Cohort 3 is to determine whether future waves of ``The Real Cost''
public education campaign will influence any of the following key
outcomes:

 Awareness of campaign messages
 Specific beliefs targeted by messages (message-targeted
beliefs)
 Psychosocial predictors or precursors of tobacco use behavior
    [cir] Health and addiction risk perceptions
    [cir] Perceived loss of control or threat to freedom expected from
tobacco use
    [cir] Anticipated guilt, shame, and regret from tobacco use
    [cir] Perceptions of prevalence, approval, and popularity of
tobacco use
    [cir] Pro-health changes in normative beliefs about tobacco product
use
    [cir] Tobacco use susceptibility
    [cir] Intention or willingness to use tobacco
    [cir] Intention to quit and/or reduce daily consumption

    In support of the provisions of the Tobacco Control Act (Pub. L.
11-31) that require FDA to protect the public health and to reduce
tobacco use by minors, FDA requests OMB approval to collect information
to evaluate CTP's public education campaign ``The Real Cost'' through
the Evaluation Study: Cohort 3.
    FDA estimates the burden of this collection of information as
follows:

                                 Table 1--Estimated Annual Reporting Burden \1\
----------------------------------------------------------------------------------------------------------------
                                                     Number of
       Respondent/activity           Number of     responses per   Total annual   Average burden    Total hours
                                    respondents     respondent       responses     per response
----------------------------------------------------------------------------------------------------------------
Parent Recruitment Study                 545,000               1         545,000  0.17 (10 mins)          92,650
 Materials--Main: Baseline &
 Followup 2 Replenishment.......
Parent Screener--Main: Baseline          272,500               1         272,500   0.08 (5 mins)          21,800
 & Followup 2 Replenishment.....
Household Roster--Main: Baseline           5,500               1           5,500   0.08 (5 mins)             440
 & Followup 2 Replenishment.....
CATI Screener--Main: Baseline &            2,000               1           2,000   0.08 (5 mins)             160
 Followup 2 Replenishment.......
Parent Permission--Main:                  21,600               1          21,600   0.08 (5 mins)           1,728
 Baseline & Followup 1,2,3......
Youth Assent--Main: Baseline &            21,600               1          21,600   0.08 (5 mins)           1,728
 Followup 1,2,3.................
Youth Survey--Main: Baseline &            21,600               1          21,600  0.50 (30 mins)          10,800
 Followup 1,2,3.................
Youth Screener--Supplemental....           5,000               1           5,000   0.08 (5 mins)             400
Youth Assent--Supplemental:                4,428               1           4,428   0.08 (5 mins)             355
 Baseline & Followup 1,2,3......
Youth Survey--Supplemental:                4,428               1           4,428  0.50 (30 mins)           2,214
 Baseline & Followup 1,2,3......
                                 -------------------------------------------------------------------------------
    Total.......................  ..............  ..............  ..............  ..............         132,275
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\1\ There are no capital costs or operating and maintenance costs associated with this collection of
  information.

Main Data Collection

    The main data collection will include a baseline survey and three
FU surveys. The recruitment sample for the main data collection is
youth ages 11-17. We intend to replenish the longitudinal sample at FU2
to obtain 6,000 youth respondents to maintain at least 4,800
respondents at each wave. We expect the screening process to yield a
100:1 ratio of eligible responding households. We estimate that we will
mail 400,000 recruitment/study material packages (10 minutes per
response) in order to receive at least 200,000 completed screeners (5
minutes per response) by adults within households. Households
completing the screener by mail will be contacted to complete a
computer-assisted telephone interview (CATI) where an interviewer will
determine eligibility and obtain parental permission (5 minutes per
response). For households identified as eligible for the study during
the screening process (i.e., the presence of one or more youth ages 11
to 17), we will ask the parent/guardian to list all eligible youth in
their households for study selection, a process called rostering (5
minutes per response). We estimate from the 200,000 completed
screeners, we will recruit 6,000 eligible youth from the 4,000 eligible
households.

Baseline

    At baseline, we plan to collect data from approximately 6,000 youth
respondents from the 4,000 eligible households identified through
screening. More than one eligible youth

per household may be recruited for the study. These 6,000 youth
respondents are estimated to provide baseline assent (5 minutes per
response) and complete the survey (30 minutes per response). For these
youth respondents, we will ask the parent/guardian to provide
permission (5 minutes per response) for the youth to participate in the
study. We estimate that we will lose approximately 20 percent of the
original baseline sample at each FU wave.

Followup 1

    We estimate that we will retain 80 percent of the sample from
baseline and collect data from 4,800 respondents (5 minutes per
response) at FU1. These 4,800 youth respondents are estimated to
provide assent (5 minutes per response) for FU1 and complete the survey
(30 minutes per response). For these youth respondents, we will ask the
parent/guardian to provide permission (5 minutes per response) for the
youth to participate in the study. We do not intend to replenish the
sample at FU1.

Followup 2

    We estimate that we will retain 80 percent of the sample from FU1
resulting in 3,840 respondents at FU2. To replenish the longitudinal
sample at FU2, we will send additional ``baseline'' screeners to new
households. We intend to send recruitment/study material packages to an
additional 145,000 households (10 minutes per response) to receive an
estimated 72,500 completed screeners (5 minutes per response). For
households identified as eligible for the study during the screening
process (i.e., the presence of 1 or more youth ages 11 to 17), we will
ask the parent/guardian to list all eligible youth in their households
for study selection, a process called rostering (5 minutes per
response). Households completing the screener by mail will be contacted
to complete a CATI where an interviewer will determine eligibility and
obtain parental permission (5 minutes per response). From these
completed screeners, we estimate that we will obtain data from an
additional 2,160 youth within approximately 1,500 households.
Replenishing the sample will allow us to obtain 6,000 youth respondents
at FU2 (3,840 from the original sample, and 2,160 from the
replenishment sample) and maintain a minimum study sample of 4,800
respondent at all study waves. These 6,000 youth respondents are
estimated to provide assent (5 minutes per response) for FU2 and
complete the survey (30 minutes per response). For these youth
respondents, we will ask the parent/guardian to provide permission (5
minutes per response) for the youth to participate in the study.

Followup 3

    We estimate that we will retain 80 percent of the sample from FU2
and collect data from 4,800 respondents at FU3. We do not intend to
replenish the sample at FU3. These 4,800 youth respondents are
estimated to provide assent (5 minutes per response) for FU2 and
complete the survey (30 minutes per response). For these youth
respondents, we will ask the parent/guardian to provide permission (5
minutes per response) for the youth to participate in the study.

Supplemental Data Collection

    In addition to the main data collection, we intend to collect data
from subpopulations shown to be at higher risk of initiating use of
cigarettes and ENDS products, such as youth who identify as LGBTQ+ and
youth who have a mental health disorder. Data collection will consist
of online self-administered surveys of participants recruited through
social media advertisements. The recruitment sample for this data
collection will be youth ages 14 to 20 who meet the subpopulation
criteria. We intend to collect data at baseline from 1,500 respondents.
We anticipate that we will need to screen 5,000 respondents (5 minutes
per response) to obtain a baseline sample of 1,500 respondents who meet
the subpopulation criteria. At baseline, we plan to collect data from
approximately 1,500 respondents identified as eligible through
screening. These 1,500 youth respondents are estimated to provide
assent (5 minutes per response) and complete the survey (30 minutes per
response). We estimate that we will lose approximately 20 percent of
the original baseline sample at each FU wave; therefore, estimating
1,200 respondents at FU1, 960 respondents at FU2, and 768 respondents
at FU3. For the FU samples, youth will provide assent (5 minutes per
response) and complete the survey (30 minutes per response).

    Dated: July 19, 2022.
Lauren K. Roth,
Associate Commissioner for Policy.
[FR Doc. 2022-15954 Filed 7-25-22; 8:45 am]
BILLING CODE 4164-01-P


[Federal Register Volume 79, Number 223 (Wednesday, November 19, 2014)]
[Notices]
[Pages 68929-68930]
[FR Doc No: 2014-27313]

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SECURITIES AND EXCHANGE COMMISSION

[Release No. 34-73587; File No. SR-NYSE-2014-61]

Self-Regulatory Organizations; New York Stock Exchange LLC;
Notice of Filing and Immediate Effectiveness of Proposed Rule Change To
Amend Its Price List for Certain Executions at the Opening

November 13, 2014.
    Pursuant to Section 19(b)(1) \1\ of the Securities Exchange Act of
1934 (the ``Act'') \2\ and Rule 19b-4 thereunder,\3\ notice is hereby
given that, on November 4, 2014, New York Stock Exchange LLC (``NYSE''
or the ``Exchange'') filed with the Securities and Exchange Commission
(the ``Commission'') the proposed rule change as described in Items I,
II, and III below, which Items have been prepared by the self-
regulatory organization. The Commission is publishing this notice to
solicit comments on the proposed rule change from interested persons.
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    \1\ 15 U.S.C. 78s(b)(1).
    \2\ 15 U.S.C. 78a.
    \3\ 17 CFR 240.19b-4.
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I. Self-Regulatory Organization's Statement of the Terms of Substance
of the Proposed Rule Change

    The Exchange proposes to amend its Price List for certain
executions at the opening. The Exchange proposes to implement the fee
change effective November 4, 2014. The text of the proposed rule change
is available on the Exchange's Web site at www.nyse.com, at the
principal office of the Exchange, and at the Commission's Public
Reference Room.

II. Self-Regulatory Organization's Statement of the Purpose of, and
Statutory Basis for, the Proposed Rule Change

    In its filing with the Commission, the self-regulatory organization
included statements concerning the purpose of, and basis for, the
proposed rule change and discussed any comments it received on the
proposed rule change. The text of those statements may be examined at
the places specified in Item IV below. The Exchange has prepared
summaries, set forth in sections A, B, and C below, of the most
significant parts of such statements.

A. Self-Regulatory Organization's Statement of the Purpose of, and the
Statutory Basis for, the Proposed Rule Change

1. Purpose
    The Exchange proposes to amend its Price List for certain
executions at the opening. The Exchange proposes to implement the fee
change effective November 4, 2014.
    For securities priced $1.00 or greater, the Exchange currently
charges a fee of $0.0010 per share for executions at the opening or of
$0.0010 per share for executions at the opening only orders, subject to
a monthly fee cap of $20,000 per member organization for such
executions. Designated Market Makers (``DMMs'') are not charged for
executions at the opening.
    The Exchange proposes to modify the monthly fee cap of $20,000 per
member organization for securities priced $1.00 or greater \4\ by
adding a requirement that to qualify for this monthly fee cap, which is
set forth in footnote 2 to the Price List, the member organization must
execute an average daily trading volume (``ADV'') that adds liquidity
to the NYSE during the billing month (``Adding ADV'') of at least
5,000,000 shares, excluding liquidity added by a DMM. DMM executions at
the opening would continue to not be charged.
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    \4\ The existing pricing for executions at the opening in
securities priced below $1.00 would also remain unchanged (i.e.,
0.3% of the total dollar value of the transaction).
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    In addition, the Exchange proposes non-substantive, conforming
changes to the text governing ``Equity per Share Charge'' and ``Tier 1
Adding Credit--Equity per Share Credit--per transaction'' to reflect
that the terms ``ADV'' and ``Adding ADV'' are now defined in footnote
2.
    The proposed change is not otherwise intended to address any other
issues, and the Exchange is not aware of any problems that members and
member organizations would have in complying with the proposed change.
2. Statutory Basis
    The Exchange believes that the proposed rule change is consistent
with Section 6(b) of the Act,\5\ in general, and furthers the
objectives of Sections 6(b)(4) and 6(b)(5) of the Act,\6\ in
particular, because it provides for the

equitable allocation of reasonable dues, fees, and other charges among
its members, issuers and other persons using its facilities and does
not unfairly discriminate between customers, issuers, brokers or
dealers.
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    \5\ 15 U.S.C. 78f(b).
    \6\ 15 U.S.C. 78f(b)(4) and (5).
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    The Exchange believes that it is reasonable to add a requirement
that member organizations execute Adding ADV at least 5,000,000 shares
during the billing month in order to qualify for a fee cap. The
proposed Adding ADV requirement will encourage the submission of
additional liquidity to a national securities exchange, thereby
promoting price discovery and transparency and enhancing order
execution opportunities for member organizations. Moreover, the
requirement is equitable and not unfairly discriminatory because it
would apply equally to all similarly situated member organizations.
    The Exchange believes that it is subject to significant competitive
forces, as described below in the Exchange's statement regarding the
burden on competition.
    For the foregoing reasons, the Exchange believes that the proposal
is consistent with the Act.

B. Self-Regulatory Organization's Statement on Burden on Competition

    In accordance with Section 6(b)(8) of the Act,\7\ the Exchange
believes that the proposed rule change would not impose any burden on
competition that is not necessary or appropriate in furtherance of the
purposes of the Act. Instead, the Exchange believes that the proposed
change would contribute to the Exchange's market quality by promoting
price discovery and ultimately increased competition. For the same
reasons, the proposed change also would not impose any burden on
competition among market participants. Pricing for executions at the
opening would remain at the same relatively low levels and would
continue to reflect the benefit that market participants receive
through the ability to have their orders interact with other liquidity
at the opening.
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    \7\ 15 U.S.C. 78f(b)(8).
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    Finally, the Exchange notes that it operates in a highly
competitive market in which market participants can readily favor
competing venues if they deem fee levels at a particular venue to be
excessive or rebate opportunities available at other venues to be more
favorable. In such an environment, the Exchange must continually adjust
its fees and rebates to remain competitive with other exchanges and
with alternative trading systems that have been exempted from
compliance with the statutory standards applicable to exchanges.
Because competitors are free to modify their own fees and credits in
response, and because market participants may readily adjust their
order routing practices, the Exchange believes that the degree to which
fee changes in this market may impose any burden on competition is
extremely limited. As a result of all of these considerations, the
Exchange does not believe that the proposed changes will impair the
ability of member organizations or competing order execution venues to
maintain their competitive standing in the financial markets.

C. Self-Regulatory Organization's Statement on Comments on the Proposed
Rule Change Received From Members, Participants, or Others

    No written comments were solicited or received with respect to the
proposed rule change.

III. Date of Effectiveness of the Proposed Rule Change and Timing for
Commission Action

    The foregoing rule change is effective upon filing pursuant to
Section 19(b)(3)(A) \8\ of the Act and subparagraph (f)(2) of Rule 19b-
4 \9\ thereunder, because it establishes a due, fee, or other charge
imposed by the Exchange.
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    \8\ 15 U.S.C. 78s(b)(3)(A).
    \9\ 17 CFR 240.19b-4(f)(2).
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    At any time within 60 days of the filing of such proposed rule
change, the Commission summarily may temporarily suspend such rule
change if it appears to the Commission that such action is necessary or
appropriate in the public interest, for the protection of investors, or
otherwise in furtherance of the purposes of the Act. If the Commission
takes such action, the Commission shall institute proceedings under
Section 19(b)(2)(B) \10\ of the Act to determine whether the proposed
rule change should be approved or disapproved.
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    \10\ 15 U.S.C. 78s(b)(2)(B).
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IV. Solicitation of Comments

    Interested persons are invited to submit written data, views, and
arguments concerning the foregoing, including whether the proposed rule
change is consistent with the Act. Comments may be submitted by any of
the following methods:

Electronic Comments

     Use the Commission's Internet comment form (http://www.sec.gov/rules/sro.shtml); or
     Send an email to<EMAIL_ADDRESS>Please include
File Number SR-NYSE-2014-61 on the subject line.

Paper Comments

     Send paper comments in triplicate to Brent J. Fields,
Secretary, Securities and Exchange Commission, 100 F Street NE.,
Washington, DC 20549-1090.

All submissions should refer to File Number SR-NYSE-2014-61. This file
number should be included on the subject line if email is used. To help
the Commission process and review your comments more efficiently,
please use only one method. The Commission will post all comments on
the Commission's Internet Web site (http://www.sec.gov/rules/sro.shtml). Copies of the submission, all subsequent amendments, all
written statements with respect to the proposed rule change that are
filed with the Commission, and all written communications relating to
the proposed rule change between the Commission and any person, other
than those that may be withheld from the public in accordance with the
provisions of 5 U.S.C. 552, will be available for Web site viewing and
printing in the Commission's Public Reference Room, 100 F Street NE.,
Washington, DC 20549, on official business days between the hours of
10:00 a.m. and 3:00 p.m. Copies of the filing will also be available
for inspection and copying at the NYSE's principal office and on its
Internet Web site at www.nyse.com. All comments received will be posted
without change; the Commission does not edit personal identifying
information from submissions. You should submit only information that
you wish to make available publicly. All submissions should refer to
File Number SR-NYSE-2014-61 and should be submitted on or before
December 10, 2014.

    For the Commission, by the Division of Trading and Markets,
pursuant to delegated authority.\11\
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    \11\ 17 CFR 200.30-3(a)(12).
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Kevin M. O'Neill,
Deputy Secretary.
[FR Doc. 2014-27313 Filed 11-18-14; 8:45 am]
BILLING CODE 8011-01-P


[Federal Register Volume 78, Number 237 (Tuesday, December 10, 2013)]
[Rules and Regulations]
[Pages 73997-74004]
[FR Doc No: 2013-29396]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0023; Directorate Identifier 96-CE-072-AD;
Amendment 39-17688; AD 99-01-05 R1]
RIN 2120-AA64

Airworthiness Directives; Various Aircraft Equipped with Wing
Lift Struts

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are revising Airworthiness Directive (AD) 99-01-05 for
certain aircraft equipped with wing lift struts. AD 99-01-05 required
repetitively inspecting the wing lift struts for corrosion;
repetitively inspecting the wing lift strut forks for cracks; replacing
any corroded wing lift strut; replacing any cracked wing lift strut
fork; and repetitively replacing the wing lift strut forks at a
specified time for certain airplanes. AD 99-01-05 also required
incorporating a ``NO STEP'' placard on the wing lift strut. Since we
issued AD 99-01-05, we were informed that paragraph (c) had been
misinterpreted and caused confusion. This AD clarifies the intent of
the language in paragraph (c) of AD 99-01-05 and retains all other
requirements of AD 99-01-05. We are issuing this AD to correct the
unsafe condition on these products.

DATES: This AD is effective January 14, 2014.
    The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
February 8, 1999 (63 FR 72132, December 31, 1998).

ADDRESSES: For service information identified in this AD, contact Piper
Aircraft, Inc., Customer Services, 2926 Piper Drive, Vero Beach,
Florida 32960; telephone:<PHONE_NUMBER>; Internet: www.piper.com.
Copies of the instructions to the F. Atlee Dodge supplemental type
certificate (STC) and information about the Jensen Aircraft STCs may be
obtained from F. Atlee Dodge, Aircraft Services, LLC., 6672 Wes Way,
Anchorage, Alaska 99518-0409, Internet: www.fadodge.com. You may review
copies of the referenced service information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City, Missouri 64106. For information
on the availability of this material at the FAA, call<PHONE_NUMBER>.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-
2013-00023; 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 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: For Piper Aircraft, Inc. airplanes,
contact: Gregory ``Keith'' Noles, Aerospace Engineer, FAA, Atlanta
Aircraft Certification Office, 1701 Columbia Avenue, College Park,
Georgia 30337; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>    For FS 2000 Corp, FS 2001 Corp, FS 2002 Corporation, and FS 2003
Corporation airplanes, contact: Jeff Morfitt, Aerospace Engineer, FAA,
Seattle Aircraft Certification Office, 1601 Lind Avenue SW, Renton,
Washington 98057; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>    For LAVIA ARGENTINA S.A. (LAVIASA) airplanes, contact: S.M.
Nagarajan, Aerospace Engineer, FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-
4145; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to revise AD 99-01-05, Amendment 39-10972 (63 FR 72132,
December 31, 1998), (``AD 99-01-05''). AD 99-01-05 applied to the
specified products. The NPRM published in the Federal Register on
January 16, 2013 (78 FR 3356). The NPRM proposed to retain all
requirements of AD 99-01-05 and clarify our intent of required actions
if the seal on a sealed wing lift strut is ever improperly broken.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and the FAA's response to each comment.

Request to Combine This AD with Another AD

    Len J. Buckel stated that AD 99-26-19, Amendment 39-11470 (64 FR
72524, December 28, 1999), (``AD 99-26-19''), and AD 99-01-05 should be
combined into one AD.
    The commenter stated that since AD 99-01-05 is being revised, it
should also be revised to include Piper Aircraft, Inc. (Piper) Model J-
2 airplanes, which are covered separately in AD 99-26-19, so that all
affected Piper airplanes would be covered in one AD.
    We do not agree with the commenter. AD 99-01-05 is being revised
only to clarify language about how to maintain a sealed wing lift strut
assembly if the seal is ever improperly broken. This revision does not
require any additional actions for the owners/operators. The same
confusing and misleading language that prompted this revision is also
included in AD 99-26-19, which will also be revised. In order to avoid
any further confusion, we believe that it is in the best interest of
the owners/operators to maintain two separate ADs.
    We have not changed the final rule AD action based on this comment.

Request to Further Clarify Paragraph (g)

    Jamison Peters of Airframes Alaska stated that stronger and clearer
language should be added to this AD that specifies allowing a sealed
wing lift strut to be temporarily unsealed in order to perform proper
maintenance actions.
    The commenter stated that the proposed language in Note 1 to
paragraph (g) seems somewhat ambiguous using the word ``never'' in
regards to the seal of a strut being ``never broken'' but then saying
that ``. . . nor did we intend to preclude proper maintenance action
that may temporarily unseal a sealed strut . . .''
    We agree with the commenter that the proposed language could be
interpreted as ambiguous or conflicting. We have revised Note 2 to
paragraph (g) to further clarify that properly unsealing and resealing
a sealed wing lift strut for maintenance, as long as all regulations
and issues are considered, is still considered a terminating action for
the repetitive inspection requirements of this AD.

Conclusion

    We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the change described previously and minor editorial
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM (78 FR 3356, January 16, 2013) for correcting the unsafe
condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 3356, January 16, 2013).
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 22,000 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD. However,
the only difference in the costs presented below and the costs
associated with AD 99-01-05 is the change in the labor rate from $65
per hour to $85 per hour:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
             Action                    Labor cost            Parts cost      Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Inspection of the wing lift      8 work-hours x $85 per  Not applicable...  $680 per           $14,960,000 per
 struts and wing lift strut       hour = $680 per                            inspection cycle.  inspection
 forks.                           inspection cycle.                                             cycle.
Installation placard...........  1 work-hour x $85 =     $30..............  $115.............  $2,530,000.
                                  $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements
that will be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need these
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                                                                                Parts cost    product per
                    Action                         Labor cost per wing lift strut       per wing      wing lift
                                                                                lift strut       strut
----------------------------------------------------------------------------------------------------------------
Replacement of the wing lift strut and/or      4 work-hours x $85 per hour = $340...         $440          $780
 wing lift strut forks.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

    We have 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) 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 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)
99-01-05, Amendment 39-10972 (63 FR 72132, December 31, 1998), and
adding the following new AD:

99-01-05 R1 Various Aircraft: Amendment 39-17688; Docket No. FAA-
2013-0023; Directorate Identifier 96-CE-072-AD.

(a) Effective Date

    This AD is effective January 14, 2014

(b) Affected ADs

    This AD revises AD 99-01-05, Amendment 39-10972 (63 FR 72132,
December 31, 1998), which superseded AD 93-10-06, Amendment 39-8586
(58 FR 29965, May 25, 1993). AD 99-26-19, Amendment 39-11479 (64 FR
72524, December 28, 1999), also relates to the subject of this AD.

(c) Applicability

    This AD applies to the following airplanes identified in table 1
of paragraph (c) of this AD, that are:
    (1) Equipped with wing lift struts, including airplanes commonly
known as a ``Clipped Wing Cub,'' which modify the airplane primarily
by removing approximately 40 inches of the inboard portion of each
wing; and
    (2) certificated in any category.

           Table 1 to Paragraph (c) of This AD--Applicability
------------------------------------------------------------------------
   Type certificate holder       Aircraft model          Serial No.
------------------------------------------------------------------------
FS 2000 Corp................  L-14................  All.
FS 2001 Corp................  J5A (Army L-4F), J5A- All.
                               80, J5B (Army L-
                               4G), J5C, AE-1, and
                               HE-1.
FS 2002 Corporation.........  PA-14...............  14-1 through 14-523.
FS 2003 Corporation.........  PA-12 and PA-12S....  12-1 through 12-
                                                     4036.
LAVIA ARGENTINA S.A.          PA-25, PA-25-235,     25-1 through 25-
 (LAVIASA).                    and PA-25-260.        8156024.
Piper Aircraft, Inc.........  TG-8 (Army TG-8,      All.
                               Navy XLNP-1).
Piper Aircraft, Inc.........  E-2 and F-2.........  All.
Piper Aircraft, Inc.........  J3C-40, J3C-50, J3C-  All.
                               50S, (Army L-4, L-
                               4B, L-4H, and L-
                               4J), J3C-65 (Navy
                               NE-1 and NE-2), J3C-
                               65S, J3F-50, J3F-
                               50S, J3F-60, J3F-
                               60S, J3F-65 (Army L-
                               4D), J3F-65S, J3L,
                               J3L-S, J3L-65 (Army
                               L-4C), and J3L-65S.
Piper Aircraft, Inc.........  J4, J4A, J4A-S, and   4-401 through 4-
                               J4E (Army L-4E).      1649.
Piper Aircraft, Inc.........  PA-11 and PA-11S....  11-1 through 11-
                                                     1678.
Piper Aircraft, Inc.........  PA-15...............  15-1 through 15-388.
Piper Aircraft, Inc.........  PA-16 and PA-16S....  16-1 through 16-736.
Piper Aircraft, Inc.........  PA-17...............  17-1 through 17-215.
Piper Aircraft, Inc.........  PA-19 (Army L-18C),   19-1, 19-2, and 19-
                               and PA-19S.           3.
Piper Aircraft, Inc.........  PA-20, PA-20S, PA-20  20-1 through 20-
                               ``115'', PA-20S       1121.
                               ``115'', PA-20
                               ``135'', and PA-20S
                               ``135''.
Piper Aircraft, Inc.........  PA-22, PA-22-108, PA- 22-1 through 22-
                               22-135, PA-22S-135,   9848.
                               PA-22-150, PA-22S-
                               150, PA-22-160, and
                               PA-22S-160.
------------------------------------------------------------------------

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 57, Wings.

(e) Unsafe Condition

    (1) The subject of this AD was originally prompted by reports of
corrosion damage found on the wing lift struts. We are revising AD
99-01-05, Amendment 39-10972 (63 FR 72132, December 31, 1998),
because of reports that paragraph (c) had been misinterpreted and
caused confusion. This AD removes the language in paragraph (c) of
AD 99-01-05, which caused the confusion.
    (2) This AD clarifies the FAA's intention that if a sealed wing
lift strut assembly is installed as a replacement part, the
repetitive inspection requirement is terminated only if the seal is
never improperly broken. If the seal is improperly broken, then that
wing lift strut becomes subject to continued repetitive inspections.
We did not intend to promote drilling holes into or otherwise
unsealing a sealed strut. This AD retains all the actions required
in AD 99-01-05 and this AD does not require any actions over that
already required by AD 99-01-05. This AD does not add any additional
burden to the owners/operators of the affected airplanes.
    (3) We are issuing this AD to detect and correct corrosion and
cracking on the front and rear wing lift struts and forks, which
could cause the wing lift strut to fail. This failure could result
in the wing separating from the airplane.

(f) Paragraph Designation Changes to AD 99-01-05 R1

    Since AD 99-01-05, Amendment 39-10972 (63 FR 72132, December 31,
1998), was issued, the AD format has been revised, and certain
paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this AD as listed in the
following table:

   Table 2 to Paragraph (f) of This AD--Revised Paragraph Identifiers
------------------------------------------------------------------------
                                             Corresponding  requirement
        Requirement in AD 99-01-05               in  AD 99-01-05 R1
------------------------------------------------------------------------
paragraph (a).............................  paragraph (h).
paragraph (a)(1)..........................  paragraph (i)(1).
paragraph (a)(1)(i).......................  paragraph (i)(1)(i).
paragraph (a)(1)(ii)......................  paragraph (i)(1)(ii).
paragraph (a)(2)..........................  paragraph (i)(2).
paragraph (a)(2)(i).......................  paragraph (i)(2)(i).
paragraph (a)(2)(ii)......................  paragraph (i)(2)(ii).
paragraph (a)(3)..........................  paragraph (j)(1).
paragraph (a)(4)..........................  paragraph (j)(2).
paragraph (a)(5)..........................  paragraph (j)(3).
paragraph (b).............................  paragraph (k).
paragraph (b)(1)..........................  paragraph (l).
paragraph (b)(1)(i).......................  paragraph (l)(1).
paragraph (b)(1)(ii)(B) and (b)(1)(iv)....  paragraph (l)(2).
paragraph (b)(1)(ii)(C) and (b)(1)(iv)....  paragraph (l)(3).
paragraph (b)(1)(ii)(A) and (b)(1)(iv)....  paragraph (l)(4).
paragraph (b)(1)(iii), (b)(2), (b)(1)(iv).  paragraph (m)(1).
paragraph (b)(3) through (b)(3)(ii).......  paragraph (m)(2).
paragraph (b)(4) through (b)(4)(vi).......  paragraph (m)(3) thru
                                             (m)(3)(vi).
paragraph (b)(5) through (b)(5)(ii).......  paragraph (m)(4).
Paragraph (c).............................  Removed.
paragraph (d).............................  paragraph (n)(1).

paragraph (d)(1)..........................  paragraph (n)(1)(i).
paragraph (d)(2)..........................  paragraph (n)(1)(ii).
N/A.......................................  paragraph (n)(2).
------------------------------------------------------------------------

(g) Compliance

    Unless already done (compliance with AD 99-01-05, Amendment 39-
10972 (63 FR 72132, December 31, 1998)), do the following actions
within the compliance times specified in paragraphs (h) through (n)
of this AD, including all subparagraphs. Properly unsealing and
resealing a sealed wing lift strut is still considered a terminating
action for the repetitive inspection requirements of this AD as long
as all appropriate regulations and issues are considered, such as
static strength, fatigue, material effects, immediate and long-term
(internal and external) corrosion protection, resealing methods,
etc. Current FAA regulations in 14 CFR 43.13(b) specify that
maintenance performed will result in the part's condition to be at
least equal to its original or properly altered condition. Any
maintenance actions that unseal a sealed wing lift strut should be
coordinated with the Atlanta Aircraft Certification Office (ACO)
through the local airworthiness authority (e.g., Flight Standards
District Office). There are provisions in paragraph (o) of this AD
for approving such actions as an alternative method of compliance
(AMOC).

(h) Remove Wing Lift Struts

    At whichever of the compliance times specified in paragraphs
(h)(1) or (h)(2) of this AD that occurs later, remove the wing lift
struts following Piper Aircraft Corporation Mandatory Service
Bulletin (Piper MSB) No. 528D, dated October 19, 1990, or Piper MSB
No. 910A, dated October 10, 1989, as applicable. Before further
flight after the removal, do the actions in one of the following
paragraphs (i)(1), (i)(2), (j)(1), (j)(2), or (j)(3) of this AD,
including all subparagraphs.
    (1) Within 1 calendar month after February 8, 1999 (the
effective date retained from AD 99-01-05, Amendment 39-10972 (63 FR
72132, December 31, 1998)); or
    (2) Within 24 calendar months after the last inspection done in
accordance with AD 93-10-06, Amendment 39-8586 (58 FR 29965, May 25,
1993) (which was superseded by AD 99-01-05, Amendment 39-10972 (63
FR 72132, December 31, 1998)), whichever occurs later.

(i) Inspect Wing Lift Struts

    Before further flight after the removal required in paragraph
(h) of this AD, inspect each wing lift strut following paragraph
(i)(1) or (i)(2) of this AD, including all subparagraphs, or do the
wing lift strut replacement following one of the options in
paragraph (j)(1), (j)(2), or (j)(3) of this AD.
    (1) Inspect each wing lift strut for corrosion and perceptible
dents following Piper MSB No. 528D, dated October 19, 1990, or Piper
MSB No. 910A, dated October 10, 1989, as applicable.
    (i) If no corrosion is visible and no perceptible dents are
found on any wing lift strut during the inspection required in
paragraph (i)(1) of this AD, before further flight, apply corrosion
inhibitor to each wing lift strut following Piper MSB No. 528D,
dated October 19, 1990, or Piper MSB No. 910A, dated October 10,
1989, as applicable.
    Repetitively thereafter inspect each wing lift strut at
intervals not to exceed 24 calendar months following the procedures
in paragraph (i)(1) or (i)(2) of this AD, including all
subparagraphs.
    (ii) If corrosion or perceptible dents are found on any wing
lift strut during the inspection required in paragraph (i)(1) of
this AD or during any repetitive inspection required in paragraph
(i)(1)(i) of this AD, before further flight, replace the affected
wing lift strut with one of the replacement options specified in
paragraph (j)(1), (j)(2), or (j)(3) of this AD. Do the replacement
following the procedures specified in those paragraphs, as
applicable.
    (2) Inspect each wing lift strut for corrosion following the
procedures in the Appendix to this AD. This inspection must be done
by a Level 2 or Level 3 inspector certified using the guidelines
established by the American Society for Non-destructive Testing or
the ``Military Standard for Nondestructive Testing Personnel
Qualification and Certification'' (MIL-STD-410E), which can be found
on the Internet at http://aerospacedefense.thomasnet.com/Asset/MIL-STD-410.pdf.
    (i) If no corrosion is found on any wing lift strut during the
inspection required in paragraph (i)(2) of this AD and all
requirements in the Appendix to this AD are met, before further
flight, apply corrosion inhibitor to each wing lift strut following
Piper MSB No. 528D, dated October 19, 1990, or Piper MSB No. 910A,
dated October 10, 1989, as applicable. Repetitively thereafter
inspect each wing lift strut at intervals not to exceed 24 calendar
months following the procedures in paragraph (i)(1) or (i)(2) of
this AD, including all subparagraphs.
    (ii) If corrosion is found on any wing lift strut during the
inspection required in paragraph (i)(2) of this AD or during any
repetitive inspection required in paragraph (i)(2)(i) of this AD, or
if any requirement in the Appendix of this AD is not met, before
further flight after any inspection in which corrosion is found or
the Appendix requirements are not met, replace the affected wing
lift strut with one of the replacement options specified in
paragraph (j)(1), (j)(2), or (j)(3) of this AD. Do the replacement
following the procedures specified in those paragraphs, as
applicable.

(j) Wing Lift Strut Replacement Options

    Before further flight after the removal required in paragraph
(h) of this AD, replace the wing lift struts following one of the
options in paragraph (j)(1), (j)(2), or (j)(3) of this AD, including
all subparagraphs, or inspect each wing lift strut following
paragraph (i)(1) or (i)(2) of this AD.
    (1) Install original equipment manufacturer (OEM) part number
wing lift struts (or FAA-approved equivalent part numbers) that have
been inspected following the procedures in either paragraph (i)(1)
or (i)(2) of this AD, including all subparagraphs, and are found to
be airworthy. Do the installations following Piper MSB No. 528D,
dated October 19, 1990, or Piper MSB No. 910A, dated October 10,
1989, as applicable. Repetitively thereafter inspect the newly
installed wing lift struts at intervals not to exceed 24 calendar
months following the procedures in either paragraph (i)(1) or (i)(2)
of this AD, including all subparagraphs.
    (2) Install new sealed wing lift strut assemblies (or FAA-
approved equivalent part numbers) (these sealed wing lift strut
assemblies also include the wing lift strut forks) following Piper
MSB No. 528D, dated October 19, 1990, and Piper MSB No. 910A, dated
October 10, 1989, as applicable. Installing one of these new sealed
wing lift strut assemblies terminates the repetitive inspection
requirements in paragraphs (i)(1) and (i)(2) of this AD, and the
wing lift strut fork removal, inspection, and replacement
requirement in paragraphs (k) and (l) of this AD, including all
subparagraphs, for that wing lift strut assembly.
    (3) Install F. Atlee Dodge wing lift strut assemblies following
F. Atlee Dodge Aircraft Services, Inc. Installation Instructions No.
3233-I for Modified Piper Wing Lift Struts Supplemental Type
Certificate (STC) SA4635NM, dated February 1, 1991, which can be
found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/E726AAA2831BD20085256CC2000E3DB7?OpenDocument&Highlight=sa4635nm.
Repetitively thereafter inspect the newly installed wing lift struts
at intervals not to exceed 60 calendar months following the
procedures in paragraph (i)(1) or (i)(2) of this AD, including all
subparagraphs.

(k) Remove Wing Lift Strut Forks

    For all affected airplane models, except for Models PA-25, PA-
25-235, and PA-25-260 airplanes, within the next 100 hours time-in-
service (TIS) after February 8, 1999 (the effective date retained
from AD 99-01-05, Amendment 39-10972 (63 FR 72132, December 31,
1998)) or within 500 hours TIS after the last inspection done in
accordance with AD 93-10-06, Amendment 39-8586 (58 FR 29965, May 25,
1993) (which was superseded by AD 99-01-05), whichever occurs later,
remove the wing lift strut forks (unless already replaced in
accordance with paragraph (j)(2) of this AD). Do the removal
following Piper MSB No. 528D, dated October 19, 1990, or Piper MSB
No. 910A, dated October 10, 1989, as applicable. Before further
flight after the removal, do the actions in one of the following
paragraphs (l) or (m) of this AD, including all subparagraphs.

(l) Inspect and Replace Wing Lift Strut Forks

    Before further flight after the removal required in paragraph
(k) of this AD, inspect the wing lift strut forks following
paragraph (l) of this AD, including all subparagraphs, or do the
wing lift strut fork replacement following one of the options in
paragraph (m)(1), (m)(2), (m)(3), or (m)(4) of this AD, including
all subparagraphs. Inspect the wing

lift strut forks for cracks using magnetic particle procedures, such
as those contained in FAA Advisory Circular (AC) 43.13-1B, Chapter
5, which can be found on the Internet http://rgl.faa.gov/
Regulatory--and--Guidance--Library/rgAdvisoryCircular.nsf/0/
99c827db9baac81b86256b4500596c4e/$FILE/Chapter%2005.pdf.
Repetitively thereafter inspect at intervals not to exceed 500 hours
TIS until the replacement time requirement specified in paragraph
(l)(2) or (l)(3) of this AD is reached provided no cracks are found.
    (1) If cracks are found during any inspection required in
paragraph (l) of this AD or during any repetitive inspection
required in paragraph (l)(2) or (l)(3) of this AD, before further
flight, replace the affected wing lift strut fork with one of the
replacement options specified in paragraph (m)(1), (m)(2), (m)(3),
or (m)(4) of this AD, including all subparagraphs. Do the
replacement following the procedures specified in those paragraphs,
as applicable.
    (2) If no cracks are found during the initial inspection
required in paragraph (l) of this AD and the airplane is currently
equipped with floats or has been equipped with floats at any time
during the previous 2,000 hours TIS since the wing lift strut forks
were installed, at or before accumulating 1,000 hours TIS on the
wing lift strut forks, replace the wing lift strut forks with one of
the replacement options specified in paragraph (m)(1), (m)(2),
(m)(3), or (m)(4) of this AD, including all subparagraphs. Do the
replacement following the procedures specified in those paragraphs,
as applicable. Repetitively thereafter inspect the newly installed
wing lift strut forks at intervals not to exceed 500 hours TIS
following the procedures specified in paragraph (l) of this AD,
including all subparagraphs.
    (3) If no cracks are found during the initial inspection
required in paragraph (l) of this AD and the airplane has never been
equipped with floats during the previous 2,000 hours TIS since the
wing lift strut forks were installed, at or before accumulating
2,000 hours TIS on the wing lift strut forks, replace the wing lift
strut forks with one of the replacement options specified in
paragraph (m)(1), (m)(2), (m)(3), or (m)(4) of this AD, including
all subparagraphs. Do the replacement following the procedures
specified in those paragraphs, as applicable. Repetitively
thereafter inspect the newly installed wing lift strut forks at
intervals not to exceed 500 hours TIS following the procedures
specified in paragraph (l) of this AD, including all subparagraphs.

(m) Wing Lift Strut Fork Replacement Options

    Before further flight after the removal required in paragraph
(k) of this AD, replace the wing lift strut forks following one of
the options in paragraph (m)(1), (m)(2), (m)(3), or (m)(4) of this
AD, including all subparagraphs, or inspect the wing lift strut
forks following paragraph (1) of this AD, including all
subparagraphs.
    (1) Install new OEM part number wing lift strut forks of the
same part numbers of the existing part (or FAA-approved equivalent
part numbers) that were manufactured with rolled threads. Wing lift
strut forks manufactured with machine (cut) threads are not to be
used. Do the installations following Piper MSB No. 528D, dated
October 19, 1990, or Piper MSB No. 910A, dated October 10, 1989, as
applicable. Repetitively thereafter inspect and replace the newly
installed wing lift strut forks at intervals not to exceed 500 hours
TIS following the procedures specified in paragraph (l) of this AD,
including all subparagraphs.
    (2) Install new sealed wing lift strut assemblies (or FAA-
approved equivalent part numbers) (these sealed wing lift strut
assemblies also include the wing lift strut forks) following Piper
MSB No. 528D, dated October 19, 1990, and Piper MSB No. 910A, dated
October 10, 1989, as applicable. This installation may have already
been done through the option specified in paragraph (j)(2) of this
AD. Installing one of these new sealed wing lift strut assemblies
terminates the repetitive inspection requirements in paragraphs
(i)(1) and (i)(2) of this AD, and the wing lift strut fork removal,
inspection, and replacement requirements in paragraphs (k) and (l)
of this AD, including all subparagraphs, for that wing lift strut
assembly.
    (3) For the airplanes specified below, install Jensen Aircraft
wing lift strut fork assemblies specified below in the applicable
STC following Jensen Aircraft Installation Instructions for Modified
Lift Strut Fitting. Installing one of these wing lift strut fork
assemblies terminates the repetitive inspection requirement of this
AD only for that wing lift strut fork. Repetitively inspect each
wing lift strut as specified in paragraph (i)(1) or (i)(2) of this
AD, including all subparagraphs.
    (i) For Models PA-12 and PA-12S airplanes: STC SA1583NM, which
can be found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2E708575849845B285256CC1008213CA?OpenDocument&Highlight=sa1583nm;
    (ii) For Model PA-14 airplanes: STC SA1584NM, which can be found
on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/39872B814471737685256CC1008213D0?OpenDocument&Highlight=sa1584nm;
    (iii) For Models PA-16 and PA-16S airplanes: STC SA1590NM, which
can be found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/B28C4162E30D941F85256CC1008213F6?OpenDocument&Highlight=sa1590nm;
    (iv) For Models PA-18, PA-18S, PA-18 ``105'' (Special), PA-18S
``105'' (Special), PA-18A, PA-18 ``125'' (Army L-21A), PA-18S
``125'', PA-18AS ``125'', PA-18 ``135'' (Army L-21B), PA-18A
``135'', PA-18S ``135'', PA-18AS ``135'', PA-18 ``150'', PA-18A
``150'', PA-18S ``150'', PA-18AS ``150'', PA-18A (Restricted), PA-
18A ``135'' (Restricted), and PA-18A ``150'' (Restricted) airplanes:
STC SA1585NM, which can be found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/A2BE010FB1CA61A285256CC1008213D6?OpenDocument&Highlight=sa1585nm;
    (v) For Models PA-20, PA-20S, PA-20 ``115'', PA-20S ``115'', PA-
20 ``135'', and PA-20S ``135'' airplanes: STC SA1586NM, which can be
found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/873CC69D42C87CF585256CC1008213DC?OpenDocument&Highlight=sa1586nm;
and
    (vi) For Model PA-22 airplanes: STC SA1587NM, which can be found
on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/B051D04CCC0BED7E85256CC1008213E0?OpenDocument&Highlight=sa1587nm.
    (4) Install F. Atlee Dodge wing lift strut assemblies following
F. Atlee Dodge Installation Instructions No. 3233-I for Modified
Piper Wing Lift Struts (STC SA4635NM), dated February 1, 1991, which
can be found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/E726AAA2831BD20085256CC2000E3DB7?OpenDocument&Highlight=sa4635nm.
This installation may have already been done in accordance paragraph
(j)(3) of this AD. Installing these wing lift strut assemblies
terminates the repetitive inspection requirements of this AD for the
wing lift strut fork only. Repetitively inspect the wing lift struts
as specified in paragraph (i)(1) or (i)(2) of this AD, including all
subparagraphs.

(n) Install Placard

    (1) Within 1 calendar month after February 8, 1999 (the
effective date retained from AD 99-01-05, Amendment 39-10972 (63 FR
72132, December 31, 1998)), or within 24 calendar months after the
last inspection required by AD 93-10-06, Amendment 39-8586 (58 FR
29965, May 25, 1993) (which was superseded by AD 99-01-05),
whichever occurs later, and before further flight after any
replacement of a wing lift strut assembly required by this AD, do
the actions in one of the following paragraphs (n)(1)(i) or
(n)(1)(ii) of this AD:
    (i) Install ``NO STEP'' decal, Piper (P/N) 80944-02, on each
wing lift strut approximately 6 inches from the bottom of the wing
lift strut in a way that the letters can be read when entering and
exiting the airplane; or
    (ii) Paint the words ``NO STEP'' approximately 6 inches from the
bottom of the wing lift strut in a way that the letters can be read
when entering and exiting the airplane. Use a minimum of 1-inch
letters using a color that contrasts with the color of the airplane.
    (2) The ``NO STEP'' markings required by paragraph (n)(1)(i) or
(n)(1)(ii) of this AD must remain in place for the life of the
airplane.

(o) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta ACO, FAA, has the authority to approve
AMOCs for this AD related to Piper Aircraft, Inc. airplanes; the
Manager, Seattle ACO, FAA has the authority to approve AMOCs for
this AD related to FS 2000 Corp, FS 2001 Corp, FS 2002 Corporation,
and FS 2003 Corporation airplanes; and the Manager, Standards
Office, FAA, has the authority to approve AMOCs for this AD related
to LAVIA ARGENTINA S.A. (LAVIASA) airplanes, 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 ACO, send it
to the attention of the appropriate person identified in paragraph
(p) 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 93-10-06, Amendment 39-8586 (58 FR
29965, May 25, 1993) and AD 99-01-05, Amendment 39-10972 (63 FR
72132, December 31, 1998) are approved as AMOCs for this AD.

(p) Related Information

    (1) For more information about this AD related to Piper
Aircraft, Inc. airplanes, contact: Gregory ``Keith'' Noles,
Aerospace Engineer, FAA, Atlanta ACO, 1701 Columbia Avenue, College
Park, Georgia 30337; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>;
email<EMAIL_ADDRESS>    (2) For more information about this AD related to FS 2000 Corp,
FS 2001 Corp, FS 2002 Corporation, and FS 2003 Corporation
airplanes, contact: Jeff Morfitt, Aerospace Engineer, FAA, Seattle
ACO, 1601 Lind Avenue SW, Renton, Washington 98057; phone: (425)
917-6405; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>    (3) For more information about this AD related to LAVIA
ARGENTINA S.A. (LAVIASA) airplanes, contact: S.M. Nagarajan,
Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106; telephone:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
(q) 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.
    (3) The following service information was approved for IBR on
February 8, 1999 (63 FR 72132, December 31, 1998).
    (i) Piper Aircraft Corporation Mandatory Service Bulletin No.
528D, dated October 19, 1990.
    (ii) Piper Aircraft Corporation Mandatory Service Bulletin No.
910A, dated October 10, 1989.
    (iii) F. Atlee Dodge Aircraft Services, Inc. Installation
Instructions No. 3233-I for Modified Piper Wing Lift Struts
Supplemental Type Certificate (STC) SA4635NM, dated February 1,
1991.
    (iv) Jensen Aircraft Installation Instructions for Modified Lift
Strut Fittings, which incorporates pages 1 and 5, Original Issue,
dated July 15, 1983; pages 2, 4, and 6, Revision No. 1, dated March
30, 1984; and pages a and 3, Revision No. 2, dated April 20, 1984.
    (4) For Piper Aircraft, Inc. service information identified in
this AD, contact Piper Aircraft, Inc., Customer Services, 2926 Piper
Drive, Vero Beach, Florida 32960; telephone:<PHONE_NUMBER>;
Internet: www.piper.com. Copies of the instructions to the F. Atlee
Dodge STC and information about the Jensen Aircraft STCs may be
obtained from F. Atlee Dodge, Aircraft Services, LLC., 6672 Wes Way,
Anchorage, Alaska 99518-0409, Internet: www.fadodge.com.
    (5) You may review copies of the referenced service information
at the FAA, Small Airplane Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the availability of this material
at the FAA, call<PHONE_NUMBER>.
    (6) 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 99-01-05 R1

Procedures and Requirements for Ultrasonic Inspection of Piper Wing
Lift Struts

Equipment Requirements

    1. A portable ultrasonic thickness gauge or flaw detector with
echo-to-echo digital thickness readout capable of reading to 0.001-
inch and an A-trace waveform display will be needed to do this
inspection.
    2. An ultrasonic probe with the following specifications will be
needed to accomplish this inspection: 10 MHz (or higher), 0.283-inch
(or smaller) diameter dual element or delay line transducer designed
for thickness gauging. The transducer and ultrasonic system shall be
capable of accurately measuring the thickness of AISI 4340 steel
down to 0.020-inch. An accuracy of +/- 0.002-inch throughout a
0.020-inch to 0.050-inch thickness range while calibrating shall be
the criteria for acceptance.
    3. Either a precision machined step wedge made of 4340 steel (or
similar steel with equivalent sound velocity) or at least three shim
samples of same material will be needed to accomplish this
inspection. One thickness of the step wedge or shim shall be less
than or equal to 0.020-inch, one shall be greater than or equal to
0.050-inch, and at least one other step or shim shall be between
these two values.
    4. Glycerin, light oil, or similar non-water based ultrasonic
couplants are recommended in the setup and inspection procedures.
Water-based couplants, containing appropriate corrosion inhibitors,
may be utilized, provided they are removed from both the reference
standards and the test item after the inspection procedure is
completed and adequate corrosion prevention steps are then taken to
protect these items.
     Note: Couplant is defined as ``a substance used between
the face of the transducer and test surface to improve transmission
of ultrasonic energy across the transducer/strut interface.''
     Note: If surface roughness due to paint loss or
corrosion is present, the surface should be sanded or polished
smooth before testing to assure a consistent and smooth surface for
making contact with the transducer. Care shall be taken to remove a
minimal amount of structural material. Paint repairs may be
necessary after the inspection to prevent further corrosion damage
from occurring. Removal of surface irregularities will enhance the
accuracy of the inspection technique.

Instrument Setup

    1. Set up the ultrasonic equipment for thickness measurements as
specified in the instrument's user's manual. Because of the variety
of equipment available to perform ultrasonic thickness measurements,
some modification to this general setup procedure may be necessary.
However, the tolerance requirement of step 13 and the record keeping
requirement of step 14, must be satisfied.
    2. If battery power will be employed, check to see that the
battery has been properly charged. The testing will take
approximately two hours. Screen brightness and contrast should be
set to match environmental conditions.
    3. Verify that the instrument is set for the type of transducer
being used, i.e. single or dual element, and that the frequency
setting is compatible with the transducer.
    4. If a removable delay line is used, remove it and place a drop
of couplant between the transducer face and the delay line to assure
good transmission of ultrasonic energy. Reassemble the delay line
transducer and continue.
    5. Program a velocity of 0.231-inch/microsecond into the
ultrasonic unit unless an alternative instrument calibration
procedure is used to set the sound velocity.
    6. Obtain a step wedge or steel shims per item 3 of the
Equipment Requirements. Place the probe on the thickest sample using
couplant. Rotate the transducer slightly back and forth to ``ring''
the transducer to the sample. Adjust the delay and range settings to
arrive at an A-trace signal display with the first backwall echo
from the steel near the left side of the screen and the second
backwall echo near the right of the screen. Note that when a single
element transducer is used, the initial pulse and the delay line/
steel interface will be off of the screen to the left. Adjust the
gain to place the amplitude of the first backwall signal at
approximately 80% screen height on the A-trace.
    7. ``Ring'' the transducer on the thinnest step or shim using
couplant. Select positive half-wave rectified, negative half-wave
rectified, or filtered signal display to obtain the cleanest signal.
Adjust the pulse voltage, pulse width, and damping to obtain the
best signal resolution. These settings can vary from one transducer
to another and are also user dependent.
    8. Enable the thickness gate, and adjust the gate so that it
starts at the first backwall echo and ends at the second backwall
echo. (Measuring between the first and second backwall echoes will
produce a measurement of the steel thickness that is not affected by
the paint layer on the strut). If instability of the gate trigger
occurs, adjust the gain, gate level, and/or damping to stabilize the
thickness reading.
    9. Check the digital display reading and if it does not agree
with the known thickness

of the thinnest thickness, follow your instrument's calibration
recommendations to produce the correct thickness reading. When a
single element transducer is used this will usually involve
adjusting the fine delay setting.
    10. Place the transducer on the thickest step of shim using
couplant. Adjust the thickness gate width so that the gate is
triggered by the second backwall reflection of the thick section. If
the digital display does not agree with the thickest thickness,
follow your instruments calibration recommendations to produce the
correct thickness reading. A slight adjustment in the velocity may
be necessary to get both the thinnest and the thickest reading
correct. Document the changed velocity value.
    11. Place couplant on an area of the lift strut which is thought
to be free of corrosion and ``ring'' the transducer to surface.
Minor adjustments to the signal and gate settings may be required to
account for coupling improvements resulting from the paint layer.
The thickness gate level should be set just high enough so as not to
be triggered by irrelevant signal noise. An area on the upper
surface of the lift strut above the inspection area would be a good
location to complete this step and should produce a thickness
reading between 0.034-inch and 0.041-inch.
    12. Repeat steps 8, 9, 10, and 11 until both thick and thin shim
measurements are within tolerance and the lift strut measurement is
reasonable and steady.
    13. Verify that the thickness value shown in the digital display
is within +/- 0.002-inch of the correct value for each of the three
or more steps of the setup wedge or shims. Make no further
adjustments to the instrument settings.
    14. Record the ultrasonic versus actual thickness of all wedge
steps or steel shims available as a record of setup.

Inspection Procedure

    1. Clean the lower 18 inches of the wing lift struts using a
cleaner that will remove all dirt and grease. Dirt and grease will
adversely affect the accuracy of the inspection technique. Light
sanding or polishing may also be required to reduce surface
roughness as noted in the Equipment Requirements section.
    2. Using a flexible ruler, draw a \1/4\-inch grid on the surface
of the first 11 inches from the lower end of the strut as shown in
Piper MSB No. 528D, dated October 19, 1990, or Piper MSB No. 910A,
dated October 10, 1989, as applicable. This can be done using a soft
(2) pencil and should be done on both faces of the strut.
As an alternative to drawing a complete grid, make two rows of marks
spaced every \1/4\-inch across the width of the strut. One row of
marks should be about 11 inches from the lower end of the strut, and
the second row should be several inches away where the strut starts
to narrow. Lay the flexible ruler between respective tick marks of
the two rows and use tape or a rubber band to keep the ruler in
place. See Figure 1.
    3. Apply a generous amount of couplant inside each of the square
areas or along the edge of the ruler. Re-application of couplant may
be necessary.
    4. Place the transducer inside the first square area of the
drawn grid or at the first \1/4\-inch mark on the ruler and ``ring''
the transducer to the strut. When using a dual element transducer,
be very careful to record the thickness value with the axis of the
transducer elements perpendicular to any curvature in the strut. If
this is not done, loss of signal or inaccurate readings can result.
    5. Take readings inside each square on the grid or at \1/4\-inch
increments along the ruler and record the results. When taking a
thickness reading, rotate the transducer slightly back and forth and
experiment with the angle of contact to produce the lowest thickness
reading possible. Pay close attention to the A-scan display to
assure that the thickness gate is triggering off of maximized
backwall echoes.
     NOTE: A reading shall not exceed .041 inch. If a
reading exceeds .041-inch, repeat steps 13 and 14 of the Instrument
Setup section before proceeding further.
    6. If the A-trace is unsteady or the thickness reading is
clearly wrong, adjust the signal gain and/or gate setting to obtain
reasonable and steady readings. If any instrument setting is
adjusted, repeat steps 13 and 14 of the Instrument Setup section
before proceeding further.
    7. In areas where obstructions are present, take a data point as
close to the correct area as possible.
     NOTE: The strut wall contains a fabrication bead at
approximately 40% of the strut chord. The bead may interfere with
accurate measurements in that specific location.
    8. A measurement of 0.024-inch or less shall require replacement
of the strut prior to further flight.
    9. If at any time during testing an area is encountered where a
valid thickness measurement cannot be obtained due to a loss of
signal strength or quality, the area shall be considered suspect.
These areas may have a remaining wall thickness of less than 0.020-
inch, which is below the range of this setup, or they may have small
areas of localized corrosion or pitting present. The latter case
will result in a reduction in signal strength due to the sound being
scattered from the rough surface and may result in a signal that
includes echoes from the pits as well as the backwall. The suspect
area(s) shall be tested with a Maule ``Fabric Tester'' as specified
in Piper MSB No. 528D, dated October 19, 1990, or Piper MSB No.
910A, dated October 10, 1989.
    10. Record the lift strut inspection in the aircraft log book.

[GRAPHIC] [TIFF OMITTED] TR10DE13.377

    Issued in Kansas City, Missouri, on November 22, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013-29396 Filed 12-9-13; 8:45 am]
BILLING CODE 4910-13-P