[Federal Register Volume 79, Number 208 (Tuesday, October 28, 2014)]
[Rules and Regulations]
[Pages 64084-64086]
[FR Doc No: 2014-25019]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0451; Directorate Identifier 2013-NM-122-AD;
Amendment 39-17996; AD 2014-21-04]
RIN 2120-AA64

Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83),
DC-9-87 (MD-87), and MD-88 airplanes. This AD was prompted by reports
of cracks emanating from the aft-most barrel nut holes of the left and
right upper rear spar caps of the horizontal stabilizer. This AD
requires repetitive high frequency eddy current (ETHF) inspections for
cracks in the areas around the two aft-most barrel nut holes of the
upper rear spar caps, and corrective actions if necessary; and
repetitive ETHF inspections for cracks in the areas around the two aft-
most barrel nut holes of any repaired or replaced upper rear spar cap,
and corrective actions if necessary. We are issuing this AD to detect
and correct cracks in the horizontal stabilizer, which could propagate
until an upper rear spar cap severs, and result in failure of the
horizontal stabilizer upper center or aft skin panel and adversely
affect the structural integrity of the airplane.

DATES: This AD is effective December 2, 2014.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 2,
2014.

ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001;
telephone<PHONE_NUMBER>, extension 2; fax<PHONE_NUMBER>; Internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.
Examining the AD Docket
    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0451; 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 Docket 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: George Garrido, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-
627-5357; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all The Boeing Company
Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-
87), and MD-88 airplanes. The NPRM published in the Federal Register on
July 18, 2014 (79 FR 41946). The NPRM was prompted by reports of cracks
emanating from the aft-most barrel nut holes of the left and right
upper rear spar caps of the horizontal stabilizer. The NPRM proposed to
require repetitive ETHF inspections for cracks in the areas around the
two aft-most barrel nut holes of the upper rear spar caps, and
corrective actions if necessary; and repetitive ETHF inspections for
cracks in the areas around the two aft-most barrel nut holes of any
repaired or replaced upper rear spar cap, and corrective actions if
necessary. We are issuing this AD to detect and correct cracks in the
horizontal stabilizer, which could propagate until an upper rear spar
cap severs, and result in failure of the horizontal stabilizer upper
center or aft skin panel and adversely affect the structural integrity
of the airplane.

Comments

    We gave the public the opportunity to participate in developing
this AD. We have considered the comment received. Boeing supported the
NPRM (79 FR 41946, July 18, 2014).

Conclusion

    We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD as proposed, except for minor editorial changes. We have
determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM (79 FR 41946, July 18, 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 41946, July 18, 2014).

Costs of Compliance

    We estimate that this AD affects 668 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection.......................  5 work-hours x $85             $0  $425 per inspection   $283,900 per
                                    per hour = $425 per                cycle.                inspection cycle.
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
             Action                      Labor cost                 Parts cost              Cost per product
----------------------------------------------------------------------------------------------------------------
Repair..........................  Up to 394                 Up to $32,440............  Up to $65,930.
                                   work[dash]hours x $85
                                   per hour = $33,490.
Replacement.....................  Up to 394                 Up to $60,222............  Up to $93,712.
                                   work[dash]hours x $85
                                   per hour = $33,490.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

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

2014-21-04 The Boeing Company: Amendment 39-17996 ; Docket No. FAA-
2014-0451; Directorate Identifier 2013-NM-122-AD.

(a) Effective Date

    This AD is effective December 2, 2014.

(b) Affected ADs

    None.

(c) Applicability

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

(d) Subject

    Air Transport Association (ATA) Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by reports of cracks emanating from the
aft-most barrel nut holes of the left and right upper rear spar caps
of the horizontal stabilizer. We are issuing this AD to detect and
correct cracks in the horizontal stabilizer, which could propagate
until an upper rear spar cap severs, and result in failure of the
horizontal stabilizer upper center or aft skin panel and adversely
affect the structural integrity of the airplane.

(f) Compliance

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

(g) Inspection

    At the applicable compliance time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin MD80-55A070,
Revision 1, dated December 17, 2013; except as provided by paragraph
(i) of this AD: Do a high frequency eddy current inspection (ETHF)
for cracks in the areas around the two aft-most barrel nut holes of
the left and right upper rear spar caps, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin MD80-
55A070, Revision 1, dated December 17, 2013. Thereafter, repeat the
ETHF inspection at the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin MD80-55A070,
Revision 1, dated December 17, 2013; except as provided by paragraph
(i) of this AD. If any cracking is found during any inspection,
before further flight, do all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin MD80-55A070, Revision 1, dated December 17, 2013.

(h) Post-Repair/Replacement Actions

    For airplanes on which a splice repair or replacement was done,
as specified in Boeing Alert Service Bulletin MD80-55A070: At the
applicable compliance time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin MD80-55A070,
Revision 1, dated December 17, 2013, do a ETHF inspection for cracks
at the two aft-most barrel nut holes of any repaired or replaced
upper rear spar cap, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin MD80-55A070, Revision
1, dated December 17, 2013. Thereafter, repeat the ETHF inspection
at the applicable time specified in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin MD80-55A070, Revision 1, dated
December 17, 2013. If any cracking is found during any inspection,
before further flight, do all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin MD80-55A070, Revision 1, dated December 17, 2013.

(i) Exception to the Service Information Specifications

    Where Boeing Alert Service Bulletin MD80-55A070, Revision 1,
dated December 17, 2013, specifies a compliance time ``after the
original issue date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin MD80-
55A070, dated May 22, 2013, which is not incorporated by reference
in this AD.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance
with 14 CFR 39.19, send your request to your principal inspector or
local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (l)(1) of this AD.
Information may

be emailed to<EMAIL_ADDRESS>    (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) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Los Angeles ACO, to
make those findings. For a repair method to be approved, the repair
must meet the certification basis of the airplane, and 14 CFR
25.571, Amendment 45, and the approval must specifically refer to
this AD.

(l) Related Information

    (1) For more information about this AD, contact George Garrido,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
CA 90712-4137; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>    (2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin MD80-55A070, Revision 1, dated
December 17, 2013.
    (ii) Reserved.
    (3) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA
90846-0001; telephone<PHONE_NUMBER>, extension 2; fax<PHONE_NUMBER>;
Internet https://www.myboeingfleet.com.
    (4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 13, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-25019 Filed 10-27-14; 8:45 am]
BILLING CODE 4910-13-P


Record for the Final Metal Product and Machinery Rule Adult Lead Benefits, Weighted Estimates ( Final Option: Post Stratification Extrapolation) Category Health Effect Reduced Cases Annual Benefits ( 2001$) Female BI 0.0000 $ 0.00 CBA 0.0000 $ 0.00 CHD 0.0000 $ 0.00 Mortality 0.0000 $ 0.00 BI 0.0000 $ 0.00 Male CBA 0.0000 $ 0.00 CHD 0.0000 $ 0.00 Hypertension 0.0000 $ 0.00 Mortality 0.0000 $ 0.00 Total $ 0.00 February 14, 2003 Page 1 of 1 exlleadw. xls  Adult Lead


[Federal Register: August 17, 2009 (Volume 74, Number 157)]
[Notices]
[Page 41416-41417]
[DOCID:fr17au09-54]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Project No. 13499-000]

Lock + TM Hydro Friends Fund X, LLC; Notice of Preliminary Permit
Application Accepted for Filing and Soliciting Comments, Motions To
Intervene, and Competing Applications

August 7, 2009.
    On June 2, 2009, Lock + TM Hydro Friends Fund X, LLC, filed an
application, pursuant to section 4(f) of the Federal Power Act,
proposing to study the feasibility of the Green Thunder Hydroelectric
Project, to be located on the Ohio River, in Ballard County, Kentucky
and Pulaski County, Illinois.
    The proposed Green Thunder Project would be located at the U.S.
Army Corps of Engineers (Corps) Olmstead Lock and Dam, which is
presently under construction on the Ohio River, near

Olmstead, Illinois. The newly constructed Olmstead Lock and Dam will
extend in a south easterly direction across the Ohio River from
Illinois to Kentucky.
    Once the Corps dam is completed, the proposed Green Thunder Project
would include facilities upstream and downstream of the dam and on the
Illinois and Kentucky sides of the river. The proposed project would
consist of: (1) Two new underwater frame modules containing nine
turbines each with a total installed capacity of 36 megawatts; (2) a
new pre-fabricated, concrete-lined, power canal that would transport
water from above the dam to below the dam on the Kentucky side of the
river and contain the two aforementioned turbine modules installed side
by side; (3) a new switchyard, transformer, and control room which
would be located on the Illinois side of the river; (4) a new
transmission line, which would extend across the river from the
turbines to an existing transformer tie-in located about 1,000 feet
from the Corps' lock and dam facilities; and (5) appurtenant
facilities. The Green Thunder Project would have an estimated average
annual generation of 284,018 megawatts-hours, which would be sold to a
local utility.
    Applicant Contact: Mr. Wayne F. Krouse, Managing Partner, Lock+
Hydro Friends Fund X, 5090 Richmond Avenue 390, Houston, TX
77056,<PHONE_NUMBER> x709.
    FERC Contact: John Ramer,<PHONE_NUMBER>.
    Deadline for filing comments, motions to intervene, competing
applications (without notices of intent), or notices of intent to file
competing applications: 60 days from the issuance of this notice.
Comments, motions to intervene, notices of intent, and competing
applications may be filed electronically via the Internet. See 18 CFR
385.2001(a)(1)(iii) and the instructions on the Commission's Web site
under the ``e-Filing'' link. If unable to be filed electronically,
documents may be paper-filed. To paper-file, an original and eight
copies should be mailed to: Kimberly D. Bose, Secretary, Federal Energy
Regulatory Commission, 888 First Street, NE., Washington, DC 20426. For
more information on how to submit these types of filings please go to
the Commission's Web site located at http://www.ferc.gov/filing-
comments.asp. 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-
13499) in the docket number field to access the document. For
assistance, call toll-free 1-866-208-3372.

Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. E9-19618 Filed 8-14-09; 8:45 am]

BILLING CODE 6717-01-P