[Federal Register Volume 81, Number 90 (Tuesday, May 10, 2016)]
[Proposed Rules]
[Pages 28774-28777]
[FR Doc No: 2016-10634]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6426; Directorate Identifier 2016-NM-023-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model 737-300, -400, and -500 series airplanes. This
proposed AD was prompted by reports of intergranular cracks on the
front spar chord lugs of the outboard horizontal stabilizer. This
proposed AD would require repetitive inspections of the front spar
chord lugs and lug bores of the horizontal stabilizer, and repair if

necessary. We are proposing this AD to detect and correct cracking of
the front spar chord lugs of the horizontal stabilizer. Such cracking
could cause stabilizer instability, adversely affect controllability of
the airplane, and adversely affect the structural integrity of the
airplane.

DATES: We must receive comments on this proposed AD by June 24, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Data & Services Management, P.O. Box
3707, MC 2H-65, Seattle, WA 98124-2207; telephone<PHONE_NUMBER>,
extension 1; 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>. It
is also available on the internet at http://www.regulations.gov by
searching for and locating Docket No. FAA-2016-6426.

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-2016-
6426; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone:<PHONE_NUMBER>) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Gaetano Settineri, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6577; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2016-6426;
Directorate Identifier 2016-NM-023-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

    We have received reports of intergranular cracks on the front spar
chord lugs of the outboard horizontal stabilizer. The cracks have been
found along the axis of the front spar chord and in the lug faces, lug
bores, and lug spot-face surfaces. The stabilizer front spar chords are
an extrusion made from 7075-T6511 aluminum. This material is
susceptible to stress corrosion in a corrosive environment where
residual machining stresses are present and where the material finish
and sealant have degraded. A single joint failure will significantly
reduce the remaining fatigue life in the rear spar. A dual failure of
the upper and lower front spar joints of the horizontal stabilizer
could cause stabilizer instability, adversely affect controllability of
the airplane, and adversely affect the structural integrity of the
airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-55A1092, dated August
7, 2015. The service information describes procedures for doing
inspections for corrosion and cracking of the front spar chord lugs of
the horizontal stabilizer, and inspections for corrosion of the lug
bores. This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.

FAA's Determination

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

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between this Proposed AD and the Service
Information. For information on the procedures and compliance times,
see this service information at http://www.regulations.gov by searching
for and locating Docket No. FAA-2016-6426.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 737-55A1092, dated August 7, 2015,
specifies to contact the manufacturer for instructions on how to repair
certain conditions, but this AD would require repairing those
conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 346 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections....................  14 work-hours x $85 per              $0  $1,190 per          $411,740 per
                                  hour = $1,190 per                        inspection cycle.   inspection cycle
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.

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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):

The Boeing Company: Docket No. FAA-2016-6426; Directorate Identifier
2016-NM-023-AD.

(a) Comments Due Date

    We must receive comments by June 14, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 737-300, -400,
and -500 series airplanes, certificated in any category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of intergranular cracks on the
front spar chord lugs of the outboard horizontal stabilizer. We are
issuing this AD to detect and correct cracking of the front spar
chord lugs of the horizontal stabilizer. Such cracking could cause
stabilizer instability, adversely affect controllability of the
airplane, and adversely affect the structural integrity of the
airplane.

(f) Compliance

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

(g) Repetitive Inspections and Repairs

    Within 27 months after the effective date of this AD: Do the
actions required by paragraphs (g)(1) and (g)(2) of this AD, and do
all applicable repairs, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-55A1092, dated
August 7, 2015, except as required by paragraph (h) of this AD. Do
all applicable repairs before further flight. Repeat the inspections
specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at
the applicable intervals specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1092, dated
August 7, 2015.
    (1) Do a detailed inspection for corrosion and an ultrasonic
inspection for cracking of the front spar chord lugs of the left and
right horizontal stabilizers.
    (2) Do a detailed inspection for corrosion of the lug bores of
the front spar chord of the left and right horizontal stabilizers.

(h) Service Information Exception

    Where Boeing Alert Service Bulletin 737-55A1092, dated August 7,
2015, specifies to contact Boeing for appropriate action, and
specifies that action as ``RC'' (Required for Compliance): Before
further flight, repair using a method approved in accordance with
the procedures specified in paragraph (j) of this AD.

(i) Parts Installation Limitation

    As of the effective date of this AD: No person may install a
replacement horizontal stabilizer on any airplane, unless the
actions required by paragraphs (g)(1) and (g)(2) of this AD, and all
applicable repairs are done prior to installation in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-55A1092, dated August 7, 2015, except as required by paragraph
(h) of this AD. Repeat the inspections specified in paragraph (g)(1)
and (g)(2) of this AD thereafter at the applicable intervals
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-55A1092, dated August 7, 2015.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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 (k)(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, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet

the certification basis of the airplane, and the approval must
specifically refer to this AD.
    (4) Except as required by paragraph (h) of this AD: For service
information that contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. An AMOC is required for any deviations to RC steps,
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.

(k) Related Information

    (1) For more information about this AD, contact Gaetano
Settineri, Aerospace Engineer, Airframe Branch, ANM-120S, FAA,
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>;
email<EMAIL_ADDRESS>    (2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax<PHONE_NUMBER>; Internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, 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>.

    Issued in Renton, Washington, on April 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

[FR Doc. 2016-10634 Filed 5-9-16; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register: September 15, 2009 (Volume 74, Number 177)]
[Notices]
[Page 47242]
[DOCID:fr15se09-70]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. EL09-70-000]

Milford Wind Corridor LLC; Notice of Filing

September 4, 2009.
    Take notice that on September 2, 2009, Milford Wind Corridor LLC,
pursuant to section 207 of the Federal Energy Regulatory Commission's
Rules of Practice and Procedure, 18 CFR 385.207, filed a petition for
declaratory order requesting confirmation of its firm rights to use the
Milford Wind Project, in Milford, Utah, generator lead to interconnect
the full planned capacity of the Milford Wind Project to the integrated
transmission system.
    Any person desiring to intervene or to protest this filing must
file in accordance with Rules 211 and 214 of the Commission's Rules of
Practice and Procedure (18 CFR 385.211, 385.214). Protests will be
considered by the Commission in determining the appropriate action to
be taken, but will not serve to make protestants parties to the
proceeding. Any person wishing to become a party must file a notice of
intervention or motion to intervene, as appropriate. Such notices,
motions, or protests must be filed on or before the comment date. On or
before the comment date, it is not necessary to serve motions to
intervene or protests on persons other than the Applicant.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper using the ``eFiling'' link at http://
www.ferc.gov. Persons unable to file electronically should submit an
original and 14 copies of the protest or intervention to the Federal
Energy Regulatory Commission, 888 First Street, NE., Washington, DC
20426.
    This filing is accessible on-line at http://www.ferc.gov, using the
``eLibrary'' link and is available for review in the Commission's
Public Reference Room in Washington, DC. There is an ``eSubscription''
link on the Web site that enables subscribers to receive e-mail
notification when a document is added to a subscribed docket(s). For
assistance with any FERC Online service, please e-mail
<EMAIL_ADDRESS>or call<PHONE_NUMBER> (toll free). For
TTY, call<PHONE_NUMBER>.
    Comment Date: 5 p.m. Eastern Time on October 2, 2009.

Kimberly D. Bose,
Secretary.
[FR Doc. E9-22087 Filed 9-14-09; 8:45 am]

BILLING CODE 6717-01-P