[Federal Register Volume 80, Number 82 (Wednesday, April 29, 2015)]
[Rules and Regulations]
[Pages 23699-23707]
[FR Doc No: 2015-08732]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-1083; Directorate Identifier 2014-CE-036-AD;
Amendment 39-18140; AD 2015-08-04]
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 superseding Airworthiness Directive (AD) 99-01-05 R1,
which applied to certain aircraft equipped with wing lift struts. AD
99-01-05 R1 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. This new AD retains
all requirements of AD 99-01-05R1 and adds additional airplane models
to the Applicability section. This AD was prompted by a report that
additional Piper Aircraft, Inc. model airplanes should be added to the
Applicability section. We are issuing this AD to correct the unsafe
condition on these products.

DATES: This AD is effective June 3, 2015.
    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 view
this 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>.
It is also available on the Internet at http://www.regulations.gov by
searching for and locating Docket No. FAA-2014-1083.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
1083; 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: 800-647-
5527) 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 (ACO), 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 ACO, 1601 Lind Avenue SW., Renton, Washington 98057; phone:
(425) 917-6405; 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 supersede AD 99-01-05 R1, Amendment 39-17688 (78 FR 73997,
December 10, 2013; corrected 78 FR 79599, December 31, 2013), (``AD 99-
01-05 R1''). AD 99-01-05 R1 applied to certain aircraft equipped with
wing lift struts. The NPRM published in the Federal Register on
December 31, 2014 (79 FR 78729). The NPRM was prompted by a report that
Piper Aircraft, Inc. (Piper) Models J-3, J3C-65 (Army L-4A), J3P, J4B,
and J4F airplanes should be added to the Applicability section. We were
also informed of a serial number overlap between Piper Model PA-18s
listed in AD 99-01-05 R1 and Piper Model PA-19 (Army L-18C). Certain
serial numbers listed for Model PA-18s should also be listed under
Model PA-19 (Army L-18C). The NPRM proposed to retain all requirements
of AD 99-01-05 R1 and add airplanes to the Applicability section. We
are issuing this AD to correct the unsafe condition on these products.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 78729, December 31, 2014) and the FAA's response to each comment.

Request To Remove the ``NO STEP'' Placard Requirement for Models PA-25,
PA-24-235, and PA-25-260 Airplanes

    Joe Barr stated that LAVIA ARGENTINA S.A. (LAVIASA) Models PA-25,
PA-24-235, and PA-25-260 airplanes should be exempt from the
requirement in paragraph (m) of the proposed AD to install a ``NO
STEP'' placard on each wing lift strut.
    Joe Barr stated that the LAVIASA PA-25 series airplanes are the
only low wing monoplane aircraft of all the affected airplane models
listed in the proposed AD. The LAVIASA PA-25 series airplanes have a
wing support strut that is located on top of, rather than below, the
wing. The upper end of the wing lift strut attaches to the top of the
fuselage and the bottom end of the strut attaches to the top of the
wing at the midpoint region. There is no safe wing walk surface area on
the top of the wing that extends more than a few inches from the wing
root to walk or stand at this mid-wing station. No one could possibly
step on or stand on the strut at or near this wing location without
significant damage to the adjacent fabric covered wing structure
itself. Therefore, it is illogical and irrelevant to have a ``NO STEP''
placard of any kind at the mentioned location on the wing lift struts
of the LAVIASA PA-25 series airplanes. This requirement was clearly
meant for high wing aircraft only.
    We agree with the commenter. The intent of the placard is to
prevent damage from stepping on the lower end of the strut. This would
not occur on LAVIASA Models PA-25, PA-24-235, and PA-25-260 airplanes
due to the configuration discussed above.
    We have changed paragraph (m) in this AD to exclude LAVIASA Models
PA-25, PA-24-235, and PA-25-260 airplanes from this requirement.

Request To Allow a Different Rework Method of an Unsealed Wing Lift
Strut for Model J-3 Airplanes

    Mike Teets stated that he wants the option of using a different
method for reworking a non-sealed wing lift strut to a sealed condition
for Piper Aircraft Inc. Model J-3 airplanes.
    Mike Teets stated that he has been inspecting the wing life struts
on his Piper Aircraft, Inc. Model J-3 airplane for years and has
developed a method for ``reoperating'' an unsealed wing life strut to a
sealed condition, which would remove the need for the repetitive
inspections and thereby reduce costs associated with the requirements
of the proposed AD.
    We do not agree with the commenter. The commenter's request
pertains to only one model airplane affected by this AD and addresses
only a portion of the requirements of the proposed AD. The commenter's
proposal would be more appropriately addressed by requesting an
alternative method of compliance following the procedures specified in
paragraph (n) of this AD.
    We have not changed this AD based on this comment.

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 changes described previously and any minor editorial
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM (79 FR 78729, December 31, 2014) for correcting the unsafe
condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 78729, December 31, 2014).
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Piper Aircraft Corporation Mandatory Service Bulletin
No. 528D, dated October 19, 1990, Piper Aircraft Corporation Mandatory
Service Bulletin No. 910A, dated October 10, 1989; 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; and 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. The service information describes procedures
for wing lift strut assembly inspection and replacement. This
information is reasonably available at http://www.regulations.gov by
searching for and locating Docket No. FAA-2014-1083, or you may see
ADDRESSES for other ways to access this service information.

Costs of Compliance

    We estimate that this AD affects 22,200 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 R1 is addition of 200 airplanes to the
applicability:

                                                 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           $15,096,000 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.............  $2,553,000.
                                  $85.
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    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
                   Action                      Labor cost per wing lift strut    Parts cost per    product per
                                                                                wing lift strut  wing lift strut
----------------------------------------------------------------------------------------------------------------
Replacement of the wing lift strut and/or    4 work-hours x $85 per hour =                $440             $780
 wing lift strut forks.                       $340.
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Authority for This Rulemaking

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

Regulatory Findings

    We 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 R1, Amendment 39-17688 (78 FR 73997, December 10, 2013;
corrected 78 FR 79599, December 31, 2013), and adding the following new
AD:

2015-08-04 Various Aircraft: Amendment 39-18140; Docket No. FAA-
2014-1083; Directorate Identifier 2014-CE-036-AD.

(a) Effective Date

    This AD is effective June 3, 2015.

(b) Affected ADs

    This AD supersedes AD 99-01-05 R1, Amendment 39-17688 (78 FR
73997, December 10, 2013; corrected 78 FR 79599, December 31, 2013)
``AD 99-01-05 R1''. AD 99-26-19 R1, Amendment 39-17681 (78 FR 76040,
December 16, 2013), also relates to the subject of this AD.

(c) Applicability

    This AD applies to the following airplanes identified in Table 1
and Table 2 to paragraph (c) of this AD, that are 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 are certificated
in any category.
    (1) Based on optional engine installations some airplanes may
have been re-identified or registered with another model that is not
listed in the type certificate data sheet (TCDS). For instance,
Piper Model J3C-65 airplanes are type certificated on Type
Certificate Data Sheet (TCDS) A-691 but may also have been re-
identified or registered as a Model J3C-115, J3F-50, J3C-75, J3C-
75D, J3C-75S, J3L-75, J3C-85, J3C-85S, J3C-90, J3F-90, J3F-90S, J3C-
100, or J3-L4J airplane.
    (2) The airplane model number on the affected airplane or its
registry may or may not contain the dash (-), e.g. J3 and J-3. This
AD applies to both variations.

    Note 1 to paragraph (c) of this AD:  There is a serial number
overlap between the Piper PA-18 series airplanes and the Piper Model
PA-19 (Army L-18C) airplanes listed in AD 99-01-05 R1. Serial
numbers 18-1 through 18-7632 listed for the PA-18 series airplanes
are also now listed under Model PA-19 (Army L-18C) and Model PA-19S.

Table 1 to Paragraph (c) of This AD--Airplanes Previously Affected by AD
                               99-01-05 R1
------------------------------------------------------------------------
    Type certificate holder         Aircraft model         Serial Nos.
------------------------------------------------------------------------
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. (LAVIASA)  PA-25, PA-25-235, and   25-1 through 25-
                                 PA-25-260.              8156024.
Piper Aircraft, Inc...........  TG-8 (Army TG-8, Navy   All.
                                 XLNP-1).
Piper Aircraft, Inc...........  E-2 and F-2...........  All.
Piper Aircraft, Inc...........  J3C-40, J3C-50, J3C-    All.
                                 50S, J3C-65 (Army L-
                                 4, L-4B, L-4H, L-4J,
                                 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-18, PA-18S, PA-18    18-1 through 18-
                                 ``105'' (Special), PA-  8309025, 18900
                                 18S ``105''             through
                                 (Special), PA-18A, PA-  1809032, and
                                 18 ``125'' (Army L-     1809034 through
                                 21A), PA-18S ``125'',   1809040.
                                 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).
Piper Aircraft, Inc...........  PA-19 (Army L-18C),     18-1 through 18-
                                 and PA-19S.             7632 and 19-1,
                                                         19-2, and 19-3.
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.
------------------------------------------------------------------------

      Table 2 to Paragraph (c) of This AD--Airplanes New to This AD
------------------------------------------------------------------------
    Type certificate holder       Aircraft model        Serial Nos.
------------------------------------------------------------------------
Piper Aircraft, Inc...........  J-3..............  1100 through 1200 and
                                                    1999 and up that
                                                    were manufactured
                                                    before October 15,
                                                    1939.
Piper Aircraft, Inc...........  J3C-65 (Army L-    All.
                                 4A).
Piper Aircraft, Inc...........  J3P..............  2325, 2327, 2339,
                                                    2340, 2342, 2344,
                                                    2345, 2347, 2349,
                                                    2351, 2355 and up
                                                    that were
                                                    manufactured before
                                                    January 10, 1942.
Piper Aircraft, Inc...........  J4B..............  4-400 and up that
                                                    were manufactured
                                                    before December 11,
                                                    1942.
Piper Aircraft, Inc...........  J4F..............  4-828 and up.
------------------------------------------------------------------------

(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. AD 99-01-05 R1 is
being superseded to include certain Piper Aircraft, Inc. Models J-3,
J3C-65 (Army L4A), J3P, J4B, and J4F airplanes that were
inadvertently omitted from the applicability, paragraph (c), of AD
99-01-05 (64 FR 72524, December 28, 1999) ``99-01-05'' and
subsequently AD 99-01-05 R1.

    Note 2 to paragraph (e) of this AD:  There is a serial number
overlap between the Piper PA-18 series airplanes and the Piper Model
PA-19 (Army L-18C) airplanes listed in AD 99-01-05 R1. Serial
numbers 18-1 through 18-7632 listed for the PA-18 series airplanes
are also now listed under Model PA-19 (Army L-18C) and Model PA-19S.

    (2) AD 99-01-05 R1 was issued to clarify 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 R1. There are no new
requirements in this AD except for the addition of certain model
airplanes to the applicability, paragraph (c) of this AD.
    (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) Compliance

    Unless already done (compliance with AD 99-01-05 R1 and AD 93-
10-06, Amendment 39-8586 (58 FR 29965, May 25, 1993) ``AD 93-010-
06''), do the following actions within the compliance times
specified in paragraphs (g) through (m) 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 (n) of this AD for approving such
actions as an alternative method of compliance (AMOC).

(g) Remove Wing Lift Struts

    (1) For all airplanes previously affected by AD 99-01-05 R1:
Within 1 calendar month after February 8, 1999 (the effective date
retained from AD 99-01-05), or within 24 calendar months after the
last inspection done in accordance with AD 93-10-06 (which was
superseded by AD 99-01-05), whichever 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 (h)(1), (h)(2), (i)(1), (i)(2), or (i)(3) of this AD,
including all subparagraphs.
    (2) For all airplanes new to this AD (not previously affected by
AD 99-01-05 R1): Within 1 calendar month after the effective date of
this AD or within 24 calendar months after the last inspection done
in accordance with AD 93-10-06 (which was superseded by AD 99-01-
05), whichever 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 (h)(1),
(h)(2), (i)(1), (i)(2), or (i)(3) of this AD, including all
subparagraphs.

(h) Inspect Wing Lift Struts

    For all airplanes listed in this AD: Before further flight after
the removal required in paragraph (g) of this AD, inspect each wing
lift strut following paragraph (h)(1) or (h)(2) of this AD,
including all subparagraphs, or do the wing lift strut replacement
following one of the options in paragraph (i)(1), (i)(2), or (i)(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 (h)(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 (h)(1) or (h)(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 (h)(1) of
this AD or during any repetitive inspection required in paragraph
(h)(1)(i) of this AD, before further flight, replace the affected
wing lift strut with one of the replacement options specified in
paragraph (i)(1), (i)(2), or (i)(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).
    (i) If no corrosion is found on any wing lift strut during the
inspection required in paragraph (h)(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 (h)(1) or (h)(2) of
this AD, including all subparagraphs.
    (ii) If corrosion is found on any wing lift strut during the
inspection required in paragraph (h)(2) of this AD or during any
repetitive inspection required in paragraph (h)(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 (i)(1), (i)(2), or (i)(3) of this AD. Do the replacement
following the procedures specified in those paragraphs, as
applicable.

(i) Wing Lift Strut Replacement Options

    Before further flight after the removal required in paragraph
(g) of this AD, replace the wing lift struts following one of the
options in paragraph (i)(1), (i)(2), or (i)(3) of this AD, including
all subparagraphs, or inspect each wing lift strut following
paragraph (h)(1) or (h)(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 (h)(1)
or (h)(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 (h)(1) or (h)(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 (h)(1) and (h)(2) of this AD, and the
wing lift strut fork removal, inspection, and replacement
requirement in paragraphs (j) and (k) 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. Repetitively
thereafter inspect the newly installed wing lift struts at intervals
not to exceed 60 calendar months following the procedures in
paragraph (h)(1) or (h)(2) of this AD, including all subparagraphs.

(j) Remove Wing Lift Strut Forks

    (1) For all airplanes previously affected by AD 99-01-05 R1,
except for Model 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) or within 500 hours TIS
after the last inspection done in accordance with AD 93-10-06 (which
was superseded by AD 99-01-05), whichever occurs later, remove the
wing lift strut forks (unless already replaced in accordance with
paragraph (i)(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 (k) or (l) of this
AD, including all subparagraphs.
    (2) For all airplanes new to this AD (not previously affected by
AD 99-01-05 R1): Within the next 100 hours TIS after the effective
date of this AD or within 500 hours TIS after the last inspection
done in accordance with AD 93-10-06 (which was superseded by AD 99-
01-05), whichever occurs later, remove the wing lift strut forks
(unless already replaced in accordance with paragraph (i)(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 (k) or (l) of this AD, including all
subparagraphs.

(k) Inspect and Replace Wing Lift Strut Forks

    For all airplanes affected by this AD: Before further flight
after the removal required in paragraph (j) of this AD, inspect the
wing lift strut forks following paragraph (k) of this AD, including
all subparagraphs, or do the wing lift strut fork replacement
following one of the options in paragraph (l)(1), (l)(2), (l)(3), or
(l)(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
(k)(2) or (k)(3) of this AD is reached provided no cracks are found.
    (1) If cracks are found during any inspection required in
paragraph (k) of this AD or during any repetitive inspection
required in paragraph (k)(2) or (k)(3) of this AD, before further
flight, replace the affected wing lift strut fork with one of the
replacement options specified in paragraph (l)(1), (l)(2), (l)(3),
or (l)(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 (k) 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 (l)(1), (l)(2),
(l)(3), or (l)(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 (k) of this AD,
including all subparagraphs.
    (3) If no cracks are found during the initial inspection
required in paragraph (k) 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 (l)(1), (l)(2), (l)(3), or (l)(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 (k) of this AD, including all subparagraphs.

(l) Wing Lift Strut Fork Replacement Options

    Before further flight after the removal required in paragraph
(j) of this AD, replace the wing lift strut forks following one of
the options in paragraph (l)(1), (l)(2), (l)(3), or (l)(4) of this
AD, including all subparagraphs, or inspect the wing lift strut
forks following paragraph (k) 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 (k) 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 (i)(2) of this
AD. Installing one of these new sealed wing lift strut assemblies
terminates the repetitive inspection requirements in paragraphs
(h)(1) and (h)(2) of this AD, and the wing lift strut fork removal,
inspection, and replacement requirements in paragraphs (j) and (k)
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 (h)(1) or (h)(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. This
installation may have already been done in accordance paragraph
(i)(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 (h)(1) or (h)(2) of this AD, including all
subparagraphs.

(m) Install Placard

    (1) For all airplanes previously affected by AD 99-01-05 R1,
except for Models PA-25, PA-25-235, and PA-25-260 airplanes: Within
1 calendar month after February 8, 1999 (the effective date retained
from AD 99-01-05), or within 24 calendar months after the last
inspection required by AD 93-10-06 (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
one of the following actions in paragraph (m)(1)(i) or (m)(1)(ii) of
this AD. The ``NO STEP'' markings required by paragraph (m)(1)(i) or
(m)(1)(ii) of this AD must remain in place for the life of the
airplane.
    (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) For all airplanes new to this AD (not previously affected by
AD 99-01-05 R1): Within 1 calendar month after the effective date of
this AD or within 24 calendar months after the last inspection
required by AD 93-10-06 (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
one of the following actions in paragraph (m)(2)(i) or (m)(2)(ii) of
this AD. The ``NO STEP'' markings required by paragraph (m)(2)(i) or
(m)(2)(ii) of this AD must remain in place for the life of the
airplane.
    (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.

(n) 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
(o) 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, AD 99-01-05, and AD 99-01-05
R1, are approved as AMOCs for this AD.

(o) 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>
(p) 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>. It is also available on the
Internet at http://www.regulations.gov by searching for and locating
Docket No. FAA-2014-1083.
    (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 2015-08-04

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.
    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.
    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] TR29AP15.000

    Issued in Kansas City, Missouri, on April 8, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015-08732 Filed 4-28-15; 8:45 am]
 BILLING CODE 4910-13-P


Record for the Section 316( b) Phase II Existing Facilities Notice of Data Availability 1 2 3 4 5 6 7 8 A B C D E Date Modified: 2/ 13/ 03 By: Abt Associates Inc.

Data Sources: IPM output EPA Base Case 2000 Purpose: National summary results for EPA Base Case 2000 1d  Base case with EPA electricity demand growth assumptions 2d  Base case with AEO electricity demand growth assumptions March 10, 2003 Page 1 of 8 dwcgi 23902 1049981700 252830000. xls  File Info Record for the Section 316( b) Phase II Existing Facilities Notice of Data Availability 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 A B C D E F EPA ipm2000s100d   EPA Base Case 2000 Region: System Page: 1. 1 Regional Summary Report NOTES:

1. Year 2026 is the End Year and should not be used for analysis.

2005 2010 2015 2020 2026

1. Reserve Margin Capacity [ MW] 831903 868695 926098 976254 1040298 Plus Firm Purchases [ MW] 0 0 0 0 0 Plus Transmission In [ MW] 25817 27338 26113 24911 23008

Total Reserve Margin Capacity [ MW] 857720 896033 952211 1001165 1063306

2. Peak Load [ MW] 719442 761387 812269 856657 913351 Less DSM [ MW] 0 0 0 0 0 Plus Firm Sales [ MW] 0 0 0 0 0 Plus Transmission Out [ MW] 26344 27896 26646 25420 23478

Net Demand [ MW] 745786 789283 838915 882077 936829 3. Reserve Margin [%] 15.01 13.52 13.51 13.5 13.5

4. Generation [ GWh] 3949543 4146158 4391879 4599318 4860517 Inter Region Transmission [ GWh]  9134  8865  8181  8160  7717 Pumping & Storage Losses [ GWh] 13911 15104 15049 14937 14423 Plus Purchases [ GWh] 0 0 0 0 0 Less Sales [ GWh] 0 0 0 0 0

5. Total Supply for Demand [ GWh] 3926498 4122190 4368648 4576221 4838377

6. Projected Demand [ GWh] 3926498 4122190 4368648 4576221 4838377 Energy Not Served [ GWh] 0 0 0 0 0 Less DSM [ GWh] 0 0 0 0 0

Net Demand [ GWh] 3926498 4122190 4368648 4576221 4838377 7. Dumped Energy [ GWh] 0 0 0 0 0

8. Total Supply for Demand [ GWh] 3926498 4122190 4368648 4576221 4838377 Less T& D Losses [ GWh] 301465 316490 335412 351349 371477

9. Total Sales [ GWh] 3625033 3805700 4033236 4224872 4466900 Capacity Avoided Costs [ US$/ kW/ a] 2005 2010 2015 2020 2026

58 34 42 44 46 March 10, 2003 Page 2 of 8 dwcgi 23902 1049981700 252830000. xls  Page 1 Record for the Section 316( b) Phase II Existing Facilities Notice of Data Availability 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 A BC D E F G 10. Capacity by Plant Type [ MW] 2005 2010 2015 2020 2026

Scrubbed Coal_ NOx 1 4942 4942 4942 4942 4942 Scrubbed Coal 2 51946 50393 50393 50249 49282 Unscrubbed Coal_ NOx 3 9201 9201 9201 8595 8365 Unscrubbed Coal 4 139419 130486 118473 108574 101490 Oil/ Gas Steam 5 118936 116386 116386 116386 116386 Oil/ Gas Steam_ Nox 6 5024 5024 4463 4374 4374 Nuclear 7 77236 61238 31297 10725 1935 Hydro 8 89788 89788 89788 89788 89788 Comb. Cycle Gas 9 79307 101493 128110 152806 186832 IGCC 10 612 612 612 612 612 Turbine 11 96495 117492 151378 180896 213522 Biomass 12 1108 1108 1108 1108 1108 Geothermal 13 2725 2725 2725 2725 2725 Landfill Gas 14 91 91 91 91 91 Wind 15 1691 1691 1691 1691 1691 Fuel Cell 16 0 0 0 0 0 Solar 17 325 325 325 325 325 Non Fossil_ Other 18 2112 2112 2112 2112 2112 Fossil_ Other 19 45 45 45 45 45 Pump Storage 20 22554 22554 22554 22554 22554 Int. Imports 21 11000 11000 11000 11000 11000 Cgn_ Coal 22 4062 3998 3998 3994 3608 Cgn_ Gas 23 22540 22540 22540 22540 22540 Cgn_ Oil 24 1069 1069 1069 1069 1069 Cgn_ Other 25 1063 1063 1063 1063 1063 NonCG IPP_ Coal 26 0 0 0 0 0 NonCG IPP_ Gas 27 0 0 0 0 0 NonCG IPP_ Other 28 0 0 0 0 0 Blr_ Coal 29 0 0 0 0 0 Blr_ Gas 30 0 0 0 0 0 Blr_ Oil 31 0 0 0 0 0 Blr_ Other 32 0 0 0 0 0 SteamOnly Cogen 33 0 0 0 0 0 Rep. Coal CC 34 0 0 0 0 0 Rep. O/ G CC 35 12886 14171 15293 15472 15472 Rep. Coal IGCC 36 0 0 0 0 0 Ret. Scrubber 37 3532 5412 8216 8216 7672 Ret. ExistSCR & Scrub 38 1900 1900 1900 2494 2718 Ret. ExistSNCR & Scrub 39 0 0 0 0 0 Ret. SCR 40 49517 54291 53303 58852 60741 Ret. ExistScrub & SCR 41 35668 36697 36697 36697 36697 Ret. SNCR 42 2974 5039 10858 15211 20794 Ret. ExistScrub & SNCR 43 1191 1716 1716 1860 2827 Ret. SCR+ Scrb 44 957 1189 5179 5179 5179 Ret. SNCR+ Scrub 45 0 0 238 238 781 Ret. Gas Reburn 46 0 0 0 0 0 Ret. ExistScrub+ GasR 47 0 0 0 0 0 Ret. GasReburn+ Scrub 48 0 0 0 0 0 Ret. ACI 49 0 0 0 0 0 Ret. ExistScrub& ACI 50 0 0 0 0 0 Ret. ExistSCR& ACI 51 0 0 0 0 0 Ret. ExistSNCR& ACI 52 0 0 0 0 0 Ret. ACI & SCR 53 0 0 0 0 0 Ret. ExistScrub& ACI& SCR 54 0 0 0 0 0 Ret. ACI & SNCR 55 0 0 0 0 0 Ret. ExistScrub& ACI& SNCR 56 0 0 0 0 0 Ret. ACI & Srub 57 0 0 0 0 0 Ret. ExistSCR& ACI& Scrub 58 0 0 0 0 0 Ret. ExistSNCR& ACI& Scrub 59 0 0 0 0 0 March 10, 2003 Page 3 of 8 dwcgi 23902 1049981700 252830000. xls  Table 10 Record for the Section 316( b) Phase II Existing Facilities Notice of Data Availability 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 A BC D E F G Ret. ExistSNCR& ExistScrub& ACI 60 0 0 0 0 0 Ret. ExistSCR& ExistScrub& ACI 61 0 0 0 0 0 Ret. ExistNOx& ExistScrub& ACI 62 0 0 0 0 0 Ret. SCR & Scrub & ACI 63 0 0 0 0 0 Ret. SNCR & Scrub & ACI 64 0 0 0 0 0 Ret. O/ G SCR 65 0 506 506 506 506 Ret. O/ G SNCR 66 1225 2303 2303 2303 2303 Ret. Nuclear ( age 30+ 10 yrs) 67 9278 16550 26102 33556 10608 Ret. Nuclear ( age 40+ 20 yrs) 68 0 2062 18940 27924 57058 Ret. Biomass Cofiring 69 0 0 0 0 0 CT Early Retirement 70 0 0 0 0 0 CC Early Retirement 71 0 0 0 0 0 O/ G Early Retirement 72 1234 1557 1557 1557 1557 Coal Early Retirement 73 0 0 0 0 0 Nuke Early Retirement 74 2248 4776 1140 1140 0

Total 865901 905545 959312 1009469 1072373 March 10, 2003 Page 4 of 8 dwcgi 23902 1049981700 252830000. xls  Table 10 Record for the Section 316( b) Phase II Existing Facilities Notice of Data Availability 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 A B C D E F G 11. Capacity Additions and Changes by Plant Type [ MW] 2005 2010 2015 2020 2026 Scrubbed Coal_ NOx 1 0 0 0 0 0 Scrubbed Coal 2 0 0 0 0 0 Unscrubbed Coal_ NO 3 0 0 0 0 0 Unscrubbed Coal 4 0 0 0 0 0 Oil/ Gas Steam 5 0 0 0 0 0 Oil/ Gas Steam_ Nox 6 0 0 0 0 0 Nuclear 7 0 0 0 0 0 Hydro 8 0 0 0 0 0 Comb. Cycle Gas 9 20493 22186 26618 24695 34027 IGCC 10 0 0 0 0 0 Turbine 11 22761 20997 33886 29518 32636 Biomass 12 0 0 0 0 0 Geothermal 13 0 0 0 0 0 Landfill Gas 14 0 0 0 0 0 Wind 15 0 0 0 0 0 Fuel Cell 16 0 0 0 0 0 Solar 17 0 0 0 0 0 Non Fossil_ Other 18 0 0 0 0 0 Fossil_ Other 19 0 0 0 0 0 Pump Storage 20 0 0 0 0 0 Int. Imports 21 0 0 0 0 0 Cgn_ Coal 22 0 0 0 0 0 Cgn_ Gas 23 0 0 0 0 0 Cgn_ Oil 24 0 0 0 0 0 Cgn_ Other 25 0 0 0 0 0 NonCG IPP_ Coal 26 0 0 0 0 0 NonCG IPP_ Gas 27 0 0 0 0 0 NonCG IPP_ Other 28 0 0 0 0 0 Blr_ Coal 29 0 0 0 0 0 Blr_ Gas 30 0 0 0 0 0 Blr_ Oil 31 0 0 0 0 0 Blr_ Other 32 0 0 0 0 0 SteamOnly Cogen 33 0 0 0 0 0 Rep. Coal CC 34 0 0 0 0 0 Rep. O/ G CC 35 12886 1285 1122 179 0 Rep. Coal IGCC 36 0 0 0 0 0 Ret. Scrubber 37 4489 1880 3815 0 0 Ret. ExistSCR & Scrub 38 1900 0 0 593 225 Ret. ExistSNCR & Scru 39 0 0 0 0 0 Ret. SCR 40 49517 5012 2297 5549 1888 Ret. ExistScrub & SCR 41 35668 1029 0 0 0 Ret. SNCR 42 2974 2065 5819 4353 5583 Ret. ExistScrub & SNC 43 1191 525 0 144 967 Ret. SCR+ Scrb 44 957 233 3990 0 0 Ret. SNCR+ Scrub 45 0 0 238 0 543 Ret. Gas Reburn 46 0 0 0 0 0 Ret. ExistScrub+ GasR 47 0 0 0 0 0 Ret. GasReburn+ Scrub 48 0 0 0 0 0 Ret. ACI 49 0 0 0 0 0 Ret. ExistScrub& ACI 50 0 0 0 0 0 Ret. ExistSCR& ACI 51 0 0 0 0 0 Ret. ExistSNCR& ACI 52 0 0 0 0 0 Ret. ACI & SCR 53 0 0 0 0 0 Ret. ExistScrub& ACI& 54 0 0 0 0 0 Ret. ACI & SNCR 55 0 0 0 0 0 Ret. ExistScrub& ACI& 56 0 0 0 0 0 Ret. ACI & Srub 57 0 0 0 0 0 Ret. ExistSCR& ACI& S 58 0 0 0 0 0 Ret. ExistSNCR& ACI& 59 0 0 0 0 0 March 10, 2003 Page 5 of 8 dwcgi 23902 1049981700 252830000. xls  Table 11 Record for the Section 316( b) Phase II Existing Facilities Notice of Data Availability 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 A B C D E F G Ret. ExistSNCR& ExistS 60 0 0 0 0 0 Ret. ExistSCR& ExistSc 61 0 0 0 0 0 Ret. ExistNOx& ExistSc 62 0 0 0 0 0 Ret. SCR & Scrub & A 63 0 0 0 0 0 Ret. SNCR & Scrub & 64 0 0 0 0 0 Ret. O/ G SCR 65 0 506 0 0 0 Ret. O/ G SNCR 66 1225 1078 0 0 0 Ret. Nuclear ( age 30+ 1 67 9278 7272 18830 14726 2268 Ret. Nuclear ( age 40+ 2 68 0 2062 16878 8984 29134 Ret. Biomass Cofiring 69 0 0 0 0 0 CT Early Retirement 70 0 0 0 0 0 CC Early Retirement 71 0 0 0 0 0 O/ G Early Retirement 72 1234 324 0 0 0 Coal Early Retirement 73 0 0 0 0 0 Nuke Early Retiremen 74 2248 2528 0 0 0

Total 166820 68982 113492 88742 107270 March 10, 2003 Page 6 of 8 dwcgi 23902 1049981700 252830000. xls  Table 11 Record for the Section 316( b) Phase II Existing Facilities Notice of Data Availability 1 2 3 4 5 6 7 8 9 10 11 A B C D E F G 15. Total Annual Production Cost [ MMUS$](*) 2005 2010 2015 2020 2026

Variable O& M 7022.3 7288.7 7606.4 7841.8 8134 Fixed O& M 21740.3 21354.8 21607.5 21726 22133.6 Fuel 42813 44298.4 46431.1 48427.8 51159.9 Capital 4573.5 7630.5 12758.5 16591.9 21182.3

Total 76149.2 80572.4 88403.5 94587.5 102609.8 Sales Revenue 0 0 0 0 0 (*) Costs include only those items that are important for determining incremental cost of pollution control March 10, 2003 Page 7 of 8 dwcgi 23902 1049981700 252830000. xls  Table 15 Record for the Section 316( b) Phase II Existing Facilities Notice of Data Availability 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 A B C D E F Fuel Consumption by Fuel and Fuel Type [ TBtu]

Fuel 2005 2010 2015 2020 2026 Coal 21127.9 21523.9 21844.4 22132.1 22325.1 Oil 24 24 23.2 21.7 21.7 Nuclear 6824.9 6433.9 6197.1 5939.7 5732.3 Hydro 0 0 0 0 0 Gas 6034.6 7436.9 8884 10233 11901 Other 21.5 21.5 23.2 22.9 21.8 None 731.8 731.8 731.8 731.8 731.8 Boimass 93.3 93.4 91.6 89.8 89.8 Total 34857.9 36265.4 37795.3 39171 40823.5 March 10, 2003 Page 8 of 8 dwcgi 23902 1049981700 252830000. xls  Fuel Consumption


[Federal Register Volume 77, Number 125 (Thursday, June 28, 2012)]
[Notices]
[Pages 38616-38618]
[FR Doc No: 2012-15833]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. CP12-461-000]

Eastern Shore Natural Gas Company; Notice of Intent To Prepare an
Environmental Assessment for the Proposed 2012 Greenspring Expansion
Project and Request for Comments on Environmental Issues

    The staff of the Federal Energy Regulatory Commission (FERC or
Commission) will prepare an Environmental Assessment (EA) that will
discuss the environmental impacts of the 2012 Greenspring Expansion
Project involving construction and operation of facilities by Eastern
Shore Natural Gas Company (ESNG) in New Castle and Kent Counties,
Delaware. The Commission will use this EA in its decision-making
process to determine whether the project is in the public convenience
and necessity.
    This notice announces the opening of the scoping process the
Commission will use to gather input from the public and interested
agencies on the project. Your input will help the Commission staff
determine what issues they need to evaluate in the EA. Please note that
the scoping period will close on July 23, 2012.
    You may submit comments in written form or verbally. Further
details on how to submit written comments are in the Public
Participation section of this notice.
    This notice is being sent to the Commission's current environmental
mailing list for this project. State and local government
representatives should notify their constituents of this proposed
project and encourage them to comment on their areas of concern.
    If you are a landowner receiving this notice, you may be contacted
by a pipeline company representative about the acquisition of an
easement to construct, operate, and maintain the proposed facilities.
The company would seek to negotiate a mutually acceptable agreement.
However, if the project is approved by the Commission, that approval
conveys with it the right of eminent domain. Therefore, if easement
negotiations fail to produce an agreement, the pipeline company could
initiate condemnation proceedings where compensation would be
determined in accordance with state law.
    ESNG provided landowners with a fact sheet prepared by the FERC
entitled ``An Interstate Natural Gas Facility On My Land? What Do I
Need To Know?'' along with project notice. This fact sheet addresses a
number of typically-asked questions, including the use of eminent
domain and how to participate in the Commission's proceedings. It is
also available for viewing on the FERC Web site (www.ferc.gov).

Summary of the Proposed Project

    ESNG proposes to construct and operate approximately 11.0 miles of
16-inch-diameter natural gas pipeline in New Castle and Kent Counties,
Delaware. The 2012 Greenspring Expansion Project would provide about
15,040 dekatherms per day (dt/d) of natural gas to the markets in the
Delmarva Peninsula. According to ESNG, its project would provide.
    The Project would consist of the following facilities:
     Approximately 11.0 miles of 16-inch-diameter natural gas
pipeline looping \1\ of ESNG's existing mainline facilities from
Blackbird Greenspring Road, north of Smyrna, Delaware, southward almost
to Dover, Delaware;
---------------------------------------------------------------------------

    \1\ A pipeline loop is a segment of pipe constructed parallel to
an existing pipeline to increase capacity.
---------------------------------------------------------------------------

     Approximately 0.1 mile of 10-inch-diameter natural gas
pipeline;
     Two mainline valve assemblies; and
     One pressure regulating station in Kent County, Delaware.
    The general location of the project facilities is shown in appendix
1.\2\
---------------------------------------------------------------------------

    \2\ The appendices referenced in this notice will not appear in
the Federal Register. Copies of appendices were sent to all those
receiving this notice in the mail and are available at www.ferc.gov
using the link called ``eLibrary'' or from the Commission's Public
Reference Room, 888 First Street NE., Washington, DC 20426, or call
(202) 502-8371. For instructions on connecting to eLibrary, refer to
the last page of this notice.
---------------------------------------------------------------------------

Land Requirements for Construction

    Construction of the proposed facilities would disturb about 131.54
acres of land for the aboveground facilities and the pipeline.
Following construction, about 27.45 acres would be maintained for
permanent operation of the project's facilities; the remaining acreage
would be restored and allowed to revert to former uses. About 98.1
percent of the proposed pipeline route would parallel existing
pipeline, railroad, or road rights-of-way. Construction would utilize a
75-foot-side construction easement. Locations for contractor and/or
pipe yards have yet to be identified.

The EA Process

    The National Environmental Policy Act (NEPA) requires the
Commission to take into account the environmental impacts that could
result from an action whenever it considers the issuance of a
Certificate of Public Convenience and Necessity. NEPA also requires us
\3\ to discover and address concerns the public may have about
proposals. This process is referred to as ``scoping.'' The main goal of
the scoping process is to focus the analysis in the EA on the important
environmental issues. By this notice, the Commission requests public
comments on the scope of the issues to address in the EA. We will
consider all filed comments during the preparation of the EA.
---------------------------------------------------------------------------

    \3\ ``We,'' ``us,'' and ``our'' refer to the environmental staff
of the Commission's Office of Energy Projects.
---------------------------------------------------------------------------

    In the EA we will discuss impacts that could occur as a result of
the construction and operation of the proposed project under these
general headings:
     Geology and soils;
     Land use;
     Water resources, fisheries, and wetlands;
     Cultural resources;
     Vegetation and wildlife;
     Air quality and noise;
     Endangered and threatened species; and
     Public safety.
    We will also evaluate reasonable alternatives to the proposed
project or portions of the project, and make recommendations on how to
lessen or avoid impacts on the various resource areas.
    The EA will present our independent analysis of the issues. The EA
will be available in the public record through eLibrary. Depending on
the comments received during the scoping process, we

may also publish and distribute the EA to the public for an allotted
comment period. We will consider all comments on the EA before making
our recommendations to the Commission. To ensure we have the
opportunity to consider and address your comments, please carefully
follow the instructions in the Public Participation section of this
notice below.
    With this notice, we are asking agencies with jurisdiction by law
and/or special expertise with respect to the environmental issues of
this project to formally cooperate with us in the preparation of the
EA.\4\ Agencies that would like to request cooperating agency status
should follow the instructions for filing comments provided under the
Public Participation section of this notice.
---------------------------------------------------------------------------

    \4\ The Council on Environmental Quality regulations addressing
cooperating agency responsibilities are at Title 40, Code of Federal
Regulations, Sec.  1501.6.
---------------------------------------------------------------------------

Consultations Under Section 106 of the National Historic Preservation
Act

    In accordance with the Advisory Council on Historic Preservation's
implementing regulations for section 106 of the National Historic
Preservation Act, we are using this notice to initiate consultation
with applicable State Historic Preservation Office (SHPO), and to
solicit their views and those of other government agencies, interested
Indian tribes, and the public on the project's potential effects on
historic properties.\5\ We will define the project-specific Area of
Potential Effects (APE) in consultation with the SHPO as the project
develops. On natural gas facility projects, the APE at a minimum
encompasses all areas subject to ground disturbance (examples include
construction right-of-way, contractor/pipe storage yards, compressor
stations, and access roads). Our EA for this project will document our
findings on the impacts on historic properties and summarize the status
of consultations under section 106.
---------------------------------------------------------------------------

    \5\ The Advisory Council on Historic Preservation's regulations
are at Title 36, Code of Federal Regulations, Part 800. Those
regulations define historic properties as any prehistoric or
historic district, site, building, structure, or object included in
or eligible for inclusion in the National Register of Historic
Places.
---------------------------------------------------------------------------

Public Participation

    You can make a difference by providing us with your specific
comments or concerns about the project. Your comments should focus on
the potential environmental effects, reasonable alternatives, and
measures to avoid or lessen environmental impacts. The more specific
your comments, the more useful they will be. To ensure that your
comments are timely and properly recorded, please send your comments so
that the Commission receives them in Washington, DC on or before July
23, 2012.
    For your convenience, there are three methods which you can use to
submit your comments to the Commission. In all instances please
reference the project docket number (CP12-461-000) with your
submission. The Commission encourages electronic filing of comments and
has expert staff available to assist you at<PHONE_NUMBER> or
<EMAIL_ADDRESS>    (1) You can file your comments electronically using the eComment
feature which is located on the Commission's Web site at www.ferc.gov
under the link to Documents and Filings. This is an easy method for
interested persons to submit brief, text-only comments on a project;
    (2) You can file your comments electronically by using the eFiling
feature on the Commission's Web site at www.ferc.gov under the link to
Documents and Filings. With eFiling, you can provide comments in a
variety of formats by attaching them as a file with your submission.
New eFiling users must first create an account by clicking on
``eRegister.'' You must select the type of filing you are making. If
you are filing a comment on a particular project, please select
``Comment on a Filing''; or
    (3) You can file a paper copy of your comments by mailing them to
the following address:

Kimberly D. Bose, Secretary, Federal Energy Regulatory Commission, 888
First Street NE., Room 1A, Washington, DC 20426.

Environmental Mailing List

    The environmental mailing list includes: Federal, state, and local
government representatives and agencies; elected officials;
environmental and public interest groups; Native American Tribes; other
interested parties; and local libraries and newspapers. This list also
includes all affected landowners (as defined in the Commission's
regulations) who are potential right-of-way grantors, whose property
may be used temporarily for project purposes, or who own homes within
certain distances of aboveground facilities, and anyone who submits
comments on the project. We will update the environmental mailing list
as the analysis proceeds to ensure that we send the information related
to this environmental review to all individuals, organizations, and
government entities interested in and/or potentially affected by the
proposed project.
    If we publish and distribute the EA, copies will be sent to the
environmental mailing list for public review and comment. If you would
prefer to receive a paper copy of the document instead of the CD
version or would like to remove your name from the mailing list, please
return the attached Information Request (appendix 2).

Becoming an Intervenor

    In addition to involvement in the EA scoping process, you may want
to become an ``intervenor'' which is an official party to the
Commission's proceeding. Intervenors play a more formal role in the
process and are able to file briefs, appear at hearings, and be heard
by the courts if they choose to appeal the Commission's final ruling.
An intervenor formally participates in the proceeding by filing a
request to intervene. Instructions for becoming an intervenor are in
the User's Guide under the ``e-filing'' link on the Commission's Web
site.

Additional Information

    Additional information about the project is available from the
Commission's Office of External Affairs, at (866) 208-FERC, or on the
FERC Web site at www.ferc.gov using the ``eLibrary'' link. Click on the
eLibrary link, click on ``General Search'' and enter the docket number,
excluding the last three digits in the Docket Number field (i.e., CP12-
461). Be sure you have selected an appropriate date range. For
assistance, please contact FERC Online Support at
<EMAIL_ADDRESS>or toll free at<PHONE_NUMBER>, or for TTY,
contact<PHONE_NUMBER>. The eLibrary link also provides access to the
texts of formal documents issued by the Commission, such as orders,
notices, and rulemakings.
    In addition, the Commission now offers a free service called
eSubscription which allows you to keep track of all formal issuances
and submittals in specific dockets. This can reduce the amount of time
you spend researching proceedings by automatically providing you with
notification of these filings, document summaries, and direct links to
the documents. Go to www.ferc.gov/esubscribenow.htm.
    Finally, public meetings or site visits will be posted on the
Commission's calendar located at www.ferc.gov/EventCalendar/EventsList.aspx along with other related information.

    Dated: June 22, 2012.
Kimberly D. Bose,
Secretary.
[FR Doc. 2012-15833 Filed 6-27-12; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 85, Number 71 (Monday, April 13, 2020)]
[Proposed Rules]
[Pages 20454-20455]
[FR Doc No: 2020-07637]

=======================================================================
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DEPARTMENT OF HOMELAND SECURITY

Coast Guard

33 CFR Part 117

[Docket No. USCG-2017-0060]
RIN 1625-AA09

Drawbridge Operation Regulation; Banana River, Indian Harbour
Beach, FL

AGENCY: Coast Guard, DHS.

ACTION: Notice of proposed rulemaking; withdrawal.

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SUMMARY: The Coast Guard is withdrawing its notice of proposed
rulemaking concerning the Mathers Bridge across the Banana River, mile
0.5, at Indian Harbour Beach, FL. The bridge owner, Brevard County
Public Works Department, proposed to change the bridge operating
schedule to allow for scheduled openings in order to reduce traffic
delays. After careful consideration of the comments from all parties,
it was determined to be in the best interest of navigation to withdraw
the NPRM.

DATES: The notice of proposed rulemaking is withdrawn on April 13,
2020.

ADDRESSES: To view documents mentioned in this preamble as being
available in the docket, go to https://www.regulations.gov. Type USCG-
2017-0060 in the ``SEARCH'' box and click ``SEARCH.'' Click on Open
Docket

Folder on the line associated with this rule.

FOR FURTHER INFORMATION CONTACT: If you have questions about this
notice, call or email LT Emily Sysko, Sector Jacksonville Waterways
Management Division, U.S. Coast Guard; telephone<PHONE_NUMBER>, email
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Background Information and Regulatory History

    On April 24, 2017, we published a notice of proposed rulemaking
(NPRM) entitled Drawbridge Operation Regulation; Banana River, Indian
Harbour Beach, FL in the Federal Register (82 FR 18877) to solicit
comments on the proposed rulemaking concerning the request to change
the operating schedule. Minimal comments were received. The City of
Indian Harbour Beach, FL requested to have the comment period re-opened
as they believed their constituency did not have awareness of the
initial notice and comment period. On October 23, 2017, we published a
notice of proposed rulemaking, reopening comment period entitled
``Drawbridge Operation Regulation; Banana River, Indian Harbour Beach,
FL'' in the Federal Register (82 FR 48939).
    Due to the numerous comments received both for and against the
proposed rule, on February 20, 2018, the Coast Guard published a notice
of temporary deviation from regulation; request for comments entitled
``Drawbridge Operation Regulation; Banana River, Indian Harbour Beach,
FL'' in the Federal Register (83 FR 7110). The purpose of this
temporary deviation was to test the proposed schedule change to
determine whether a permanent change is appropriate to better balance
the needs of maritime and vehicle traffic.

Withdrawal

    The Coast Guard received 199 comments, of those, 130 were against
the proposal, 65 were in favor of the proposed change, three suggested
removing the bridge in its entirety or build a new one, and one was
unrelated to the proposed rule. The comments in favor of the proposal
generally felt that placing the bridge on a schedule would help
alleviate vehicular traffic on the bridge. The comments to remove or
rebuild the bridge are not considered viable options. Upon reviewing
the comments against the proposed change, concern was expressed that
the change would increase navigation delays, introduce unnecessary
hazards to navigation by limiting the bridge openings and create longer
bridge openings in an area with a high volume of recreational boaters.
The Coast Guard acknowledges all of the above safety concerns, and for
that reason, we feel that any benefits of the proposed schedule change
at the Mathers Bridge do not outweigh the additional hazards to vessels
and mariners transiting the area around the bridge. The current
regulation as written in 33 CFR 117.263 shall remain in effect.

Authority

    The authority citation for part 117 continues to read as follows:
    33 U.S.C. 499; 33 CFR 1.05-1; Department of Homeland Security
Delegation No. 0170.1.

    Dated: April 7, 2020.
Eric C. Jones,
Rear Admiral, U.S. Coast Guard, Commander, Seventh Coast Guard
District.
[FR Doc. 2020-07637 Filed 4-10-20; 8:45 am]
 BILLING CODE 9110-04-P


[Federal Register Volume 76, Number 40 (Tuesday, March 1, 2011)]
[Notices]
[Pages 11236-11237]
[FR Doc No: 2011-4470]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

Combined Notice of Filings No. 1

    Take notice that the Commission has received the following Natural
Gas Pipeline Rate and Refund Report filings:

    Docket Numbers: RP11-1777-000.
    Applicants: El Paso Natural Gas Company.
    Description: El Paso Natural Gas Company submits tariff filing per
154.204: Revise Grandfathered Receipt Pts Puckett/Sterling to be
effective 4/1/2011.
    Filed Date: 02/15/2011.
    Accession Number: 20110215-5017.
    Comment Date: 5 p.m. Eastern Time on Monday, February 28, 2011.

    Docket Numbers: RP11-1778-000.
    Applicants: Gulf South Pipeline Company, LP.
    Description: Gulf South Pipeline Company, LP submits tariff filing
per 154.204: ETC Amendment to Negotiated Rate Agreement to be effective
2/1/2011.
    Filed Date: 02/15/2011.
    Accession Number: 20110215-5047.
    Comment Date: 5 p.m. Eastern Time on Monday, February 28, 2011.

    Docket Numbers: RP11-1779-000.
    Applicants: B-R Pipeline Company.
    Description: B-R Pipeline Company submits tariff filing per
154.204: RTF file correction to be effective 11/1/2010.
    Filed Date: 02/15/2011.
    Accession Number: 20110215-5090.
    Comment Date: 5 p.m. Eastern Time on Monday, February 28, 2011.

    Docket Numbers: RP11-1780-000.
    Applicants: USG Pipeline Company.
    Description: USG Pipeline Company submits tariff filing per
154.204: RTF file correction to be effective 11/1/2010.
    Filed Date: 02/15/2011.
    Accession Number: 20110215-5104.
    Comment Date: 5 p.m. Eastern Time on Monday, February 28, 2011.

    Docket Numbers: RP11-1781-000.
    Applicants: Northern Natural Gas Company.
    Description: Northern Natural Gas Company submits tariff filing per
154.204: 20110215 Recoupment of Kansas Ad Valorem Tax Refunds to be
effective 3/18/2011.
    Filed Date: 02/15/2011.
    Accession Number: 20110215-5118.
    Comment Date: 5 p.m. Eastern Time on Monday, February 28, 2011.

    Docket Numbers: RP11-1782-000.
    Applicants: Questar Overthrust Pipeline Company.
    Description: Questar Overthrust Pipeline Company submits tariff
filing per 154.204: Negotiated-Rate Filing for K4229 to be effective 3/
31/2011.
    Filed Date: 02/16/2011.
    Accession Number: 20110216-5022.
    Comment Date: 5 p.m. Eastern Time on Monday, February 28, 2011.

    Docket Numbers: RP11-1783-000.
    Applicants: Golden Triangle Storage, Inc.
    Description: Golden Triangle Storage, Inc. submits tariff filing
per 154.203: GTS Compliance Filing in Docket No. CP07-414-002, to be
effective 2/28/2011.
    Filed Date: 02/16/2011.
    Accession Number: 20110216-5084.
    Comment Date: 5 p.m. Eastern Time on Monday, February 28, 2011.

    Docket Numbers: RP11-1784-000.
    Applicants: Millennium Pipeline Company, LLC.
    Description: Millennium Pipeline Company, LLC submits tariff filing
per 154.204: FT-2 Minimum Commodity to be effective 3/21/2011.
    Filed Date: 02/17/2011.
    Accession Number: 20110217-5023.
    Comment Date: 5 p.m. Eastern Time on Tuesday, March 01, 2011.

    Any person desiring to intervene or to protest in any of the above
proceedings must file in accordance with Rules 211 and 214 of the
Commission's Rules of

Practice and Procedure (18 CFR 385.211 and 385.214) on or before 5 p.m.
Eastern time on the specified comment date. It is not necessary to
separately intervene again in a subdocket related to a compliance
filing if you have previously intervened in the same docket. Protests
will be considered by the Commission in determining the appropriate
action to be taken, but will not serve to make protestants parties to
the proceeding. Anyone filing a motion to intervene or protest must
serve a copy of that document on the Applicant. In reference to filings
initiating a new proceeding, interventions or protests submitted on or
before the comment deadline need not be served on persons other than
the Applicant.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper, using the FERC Online links at http://www.ferc.gov. To facilitate electronic service, persons with Internet
access who will eFile a document and/or be listed as a contact for an
intervenor must create and validate an eRegistration account using the
eRegistration link. Select the eFiling link to log on and submit the
intervention or protests.
    Persons unable to file electronically should submit an original and
14 copies of the intervention or protest to the Federal Energy
Regulatory Commission, 888 First St., NE., Washington, DC 20426.
    The filings in the above proceedings are accessible in the
Commission's eLibrary system by clicking on the appropriate link in the
above list. They are also available for review in the Commission's
Public Reference Room in Washington, DC. There is an eSubscription link
on the Web site that enables subscribers to receive e-mail notification
when a document is added to a subscribed docket(s). For assistance with
any FERC Online service, please e-mail<EMAIL_ADDRESS>or
call<PHONE_NUMBER> (toll free). For TTY, call<PHONE_NUMBER>.

    Dated: February 17, 2011.
Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2011-4470 Filed 2-28-11; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 78, Number 190 (Tuesday, October 1, 2013)]
[Notices]
[Page 60271]
[FR Doc No: 2013-23881]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Project No. 6972-032]

 Hollow Dam Power Company; Ampersand Hollow Dam Hydro, LLC;
Notice of Application for Transfer of License, and Soliciting Comments
and Motions To Intervene

    On September 10, 2013, Hollow Dam Power Company (transferor) and
Ampersand Hollow Dam Hydro, LLC (transferee) filed an application for
transfer of license for the Hollow Dam Project, FERC No. 6972, located
on the West Branch of the Oswegatchie River in St. Lawrence County, New
York.
    Applicants seek Commission approval to transfer the license for the
Hollow Dam Project from transferor to transferee.
    Applicants' Contact: Transferor: Mr. Peter Howe, Hollow Dam Power
Company, c/o SilverStreet Hydro, 15 East Silver Street, Westfield, MA
01085,<PHONE_NUMBER>. Transferee: Mr. Lutz Loegters, Ampersand Hollow
Dam Hydro, LLC, c/o Ampersand Hydro, LLC, 717 Atlantic Avenue, Suite
1A, Boston, MA 02111,<PHONE_NUMBER>.
    FERC Contact: Patricia W. Gillis<PHONE_NUMBER>.
    Deadline for filing comments and motions to intervene: 30 days from
the issuance date of this notice by the Commission. Comments and
motions to intervene may be filed electronically via the Internet. See
18 CFR 385.2001(a)(1) and the instructions on the Commission's Web site
under http://www.ferc.gov/docs-filing/efiling.asp. Commenters can
submit brief comments up to 6,000 characters, without prior
registration, using the eComment system at http://www.ferc.gov/docs-filing/ecomment.asp. You must include your name and contact information
at the end of your comments. If unable to be filed electronically,
documents may be paper-filed. To paper-file, mail to: Kimberly D. Bose,
Secretary, Federal Energy Regulatory Commission, 888 First Street NE.,
Washington, DC 20426. More information about this project can be viewed
or printed on the eLibrary link of Commission's Web site at http://www.ferc.gov/docs-filing/elibrary.asp. Enter the docket number (P-6972)
in the docket number field to access the document. For assistance, call
toll-free 1-866-208-3372.

    Dated: September 25, 2013.
Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2013-23881 Filed 9-30-13; 8:45 am]
BILLING CODE 6717-01-P