Airworthiness Directives; The Boeing Company Airplanes, 44246-44249 [2016-15914]
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44246
Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
REIMS AVIATION S.A.: Docket No. FAA–
2016–8161; Directorate Identifier 2016–
CE–018–AD.
(a) Comments Due Date
We must receive comments by August 22,
2016.
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(b) Affected ADs
None.
(c) Applicability
This AD applies to REIMS AVIATION S.A.
F406 airplanes, serial numbers F406–0001
through F406–0098, certificated in any
category.
(d) Subject
Air Transport Association of America
(ATA) Code 55: Stabilizers.
(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
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13:03 Jul 06, 2016
Jkt 238001
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as cracks
found in the horizontal stabilizer rear attach
structure and the vertical fin rear spar attach
structure. We are issuing this AD to prevent
structural failure of the horizontal stabilizer
and/or the vertical fin rear spar attach
structure, which could result in damage to
the airplane and loss of control.
(f) Actions and Compliance
Unless already done, do the following
actions:
(1) At whichever of the compliance times
specified in paragraphs (f)(1)(i) through (iii)
of this AD that occurs the latest after the
effective date of this AD, and repetitively
thereafter every 2,400 hours time-in-service
(TIS), do a visual and non-destructive test
(NDT) inspection of the horizontal stabilizer
splice plate assembly, part number (P/N)
6032183–1 or P/N 406–5518–32183–100 (as
applicable), and the attach structure
assembly P/N 6031210–1. Do the inspections
following the Accomplishment Instructions
in ASI Aviation Service Bulletin CAB01–5
Rev 2, dated December 3, 2015.
(i) Before accumulating 2,500 hours TIS; or
(ii) Within the next 100 hours TIS; or
(iii) At the next 600-hour inspection.
(2) If, during any inspection as required by
paragraph (f)(1) of this AD, any oversized bolt
hole or crack is detected on the horizontal
stabilizer splice plate assembly or attach
structure assembly, before further flight,
repair or replace the affected part with a
serviceable part following the
Accomplishment Instructions in ASI
Aviation Service Bulletin CAB01–5 Rev 2,
dated December 3, 2015. After taking the
necessary corrective action, continue with
the repetitive inspection specified in
paragraph (f)(1) of this AD.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Albert Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4119; fax: (816) 329–
4090; email: albert.mercado@faa.gov. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, a federal
agency may not conduct or sponsor, and a
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person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(h) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No.: 2016–0101, dated 25
May 25, 2016, and ASI Aviation Service Kit
SKRA40611–Rev. 2, dated December 3, 2015,
ASI Service Kit SK406–137, dated December
3, 2015 (which superseded ASI Aviation
Service Kit SKRA406–12–Rev. 2, dated
December 3, 2015), and ASI Aviation Service
Kit SKRA406–13–Rev. 2, dated December 3,
2015, for related information. You may
examine the MCAI on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2016–8161. For
service information related to this AD,
´
contact ASI Aviation, Aerodrome de Reims
Prunay, 51360 Prunay, France; telephone:
+33 3 26 48 46 84; fax: +33 3 26 49 18 57;
email: contact@ask-aviation.fr; Internet:
https://asi-aviation.fr/page-Accueil.html. You
may review 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
(816) 329–4148.
Issued in Kansas City, Missouri, on June
28, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–15862 Filed 7–6–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–7423; Directorate
Identifier 2016–NM–034–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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07JYP1
Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules
We propose to adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 767–200, and
–300 series airplanes. This proposed AD
was prompted by an evaluation by the
design approval holder (DAH)
indicating that the frame-to-floor-beam
joints and frames common to shear ties
at certain locations of fuselage structure
are subject to widespread fatigue
damage (WFD). This proposed AD
would require repetitive inspections for
cracking of the frame inner chords and
webs common to the floor beam joint
and at frames common to the shear ties
at certain sections on the left and right
fuselage sides, and corrective action if
necessary. We are proposing this AD to
detect and correct cracking of the frame
inner chords and webs common to the
floor beam joint and at frames common
to the shear ties at certain sections on
the left and right fuselage sides, which
could result in reduced structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by August 22, 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
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• 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
206–544–5000, extension 1; fax 206–
766–5680; 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 425–227–1221. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
7423.
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SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
VerDate Sep<11>2014
13:03 Jul 06, 2016
Jkt 238001
7423; 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: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057 3356; phone: 425–917–6447; fax:
425–917–6590; email: wayne.lockett@
faa.gov.
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–
2016–7423; Directorate Identifier 2016–
NM–034–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 https://
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
Fatigue damage can occur locally, in
small areas or structural design details,
or globally, in widespread areas.
Multiple-site damage is widespread
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Widespread damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-site
damage and multiple-element damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane. This
condition is known as widespread
fatigue damage. It is associated with
general degradation of large areas of
structure with similar structural details
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44247
and stress levels. As an airplane ages,
WFD will likely occur, and will
certainly occur if the airplane is
operated long enough without any
intervention.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule (75 FR 69746,
November 15, 2010) does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
development (with FAA approval),
while providing operators with certainty
regarding the LOV applicable to their
airplanes.
An evaluation by the DAH indicates
that the frame to floor beam joints and
frames common to shear ties at certain
locations of fuselage structure are
subject to WFD. This condition, if not
corrected, could result in cracking of the
frame inner chords and webs common
to the floor beam joint and at frames
common to the shear ties at certain
sections on the left and right fuselage
sides, which could result in reduced
structural integrity of the airplane.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 767–53A0265, Revision 1,
dated March 18, 2016. The service
information describes procedures for
doing a detailed inspection and a
surface high frequency eddy current
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44248
Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules
(HFEC) inspection for cracking of the
frame inner chord and web common to
the floor beam joint in section 41 and 43
on the left and right sides, a detailed
inspection and a surface HFEC
inspection for cracking of the section 43
and 46 frames common to the shear ties
on the left and right sides, and repair.
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. For information on the
procedures and compliance times, see
this service information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
7423.
The phrase ‘‘corrective actions’’ is
used in this proposed AD. Corrective
actions correct or address any condition
found. Corrective actions in an AD
could include, for example, repairs.
Costs of Compliance
We estimate that this proposed AD
affects 306 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Inspections ..............................
Labor cost
Up to 350 work-hours × $85
per hour = $29,750 per 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.
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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:
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13:03 Jul 06, 2016
Parts cost
Jkt 238001
$0
Up to $29,750 per inspection
cycle.
(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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2016–7423; Directorate Identifier 2016–
NM–034–AD.
(a) Comments Due Date
We must receive comments by August 22,
2016.
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Fmt 4702
Cost on U.S.
operators
Cost per product
Sfmt 4702
Up to $9,103,500 per inspection cycle.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 767–200, and –300 series
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 53; Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
that the frame-to-floor-beam joints and
frames common to shear ties at certain
locations of fuselage structure are subject to
widespread fatigue damage (WFD). We are
issuing this AD to detect and correct cracking
of the frame inner chords and webs common
to the floor beam joint and at frames common
to the shear ties at certain sections on the left
and right fuselage sides, which could result
in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspections and Corrective Actions
Except as provided by paragraph (h) of this
AD, at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 767–53A0265,
Revision 1, dated March 18, 2016: Do the
actions required in paragraphs (g)(1) and
(g)(2) of this AD; and do all applicable
corrective actions; in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–53A0265, Revision 1,
dated March 18, 2016. Do all applicable
corrective actions before further flight.
Repeat the inspections specified in
paragraphs (g)(1) and (g)(2) of this AD
thereafter at the applicable intervals specified
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07JYP1
Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 767–53A0265,
Revision 1, dated March 18, 2016.
(1) Do a detailed inspection and a surface
high frequency eddy current (HFEC)
inspection for cracking of the frame inner
chord and web common to the floor beam
joint in section 41 and 43 on the left and
right sides.
(2) Do a detailed inspection and a surface
HFEC inspection for cracking of the section
43 and 46 frames common to the shear ties
on the left and right sides.
(h) Service Information Exception
Where Boeing Alert Service Bulletin 767–
53A0265, Revision 1, dated March 18, 2016,
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.
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(i) 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 767–53A0265, dated March
18, 2015. This service information is not
incorporated by reference in this AD.
(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: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(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) For service information that contains
steps that are labeled as Required for
Compliance (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
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13:03 Jul 06, 2016
Jkt 238001
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 Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6447; fax: 425–
917–6590; email: wayne.lockett@faa.gov.
(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 206–766–5680;
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 425–227–1221.
Issued in Renton, Washington, on June 23,
2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–15914 Filed 7–6–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
National Oceanic and Atmospheric
Administration
50 CFR Part 665
[Docket No. 151023986–6557–01]
RIN 0648–XE284
Pacific Island Pelagic Fisheries; 2016
U.S. Territorial Longline Bigeye Tuna
Catch Limits
National Marine Fisheries
Service (NMFS), National Oceanic and
Atmospheric Administration (NOAA),
Commerce.
ACTION: Proposed specifications; request
for comments.
AGENCY:
NMFS proposes a 2016 limit
of 2,000 metric tons (mt) of longlinecaught bigeye tuna for each U.S. Pacific
territory (American Samoa, Guam, and
the Northern Mariana Islands). NMFS
would allow each territory to allocate
up to 1,000 mt each year to U.S.
longline fishing vessels in a specified
fishing agreement that meets established
criteria. As an accountability measure,
NMFS would monitor, attribute, and
restrict (if necessary) catches of
longline-caught bigeye tuna, including
catches made under a specified fishing
agreement. The proposed catch limits
SUMMARY:
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44249
and accountability measures would
support the long-term sustainability of
fishery resources of the U.S. Pacific
Islands.
DATES: NMFS must receive comments
by July 22, 2016.
ADDRESSES: You may submit comments
on this document, identified by NOAA–
NMFS–2015–0140, by either of the
following methods:
• Electronic Submission: Submit all
electronic public comments via the
Federal e-Rulemaking Portal. Go to
https://www.regulations.gov/
#!docketDetail;D=NOAA-NMFS-20150140, click the ‘‘Comment Now!’’ icon,
complete the required fields, and enter
or attach your comments.
• Mail: Send written comments to
Michael D. Tosatto, Regional
Administrator, NMFS Pacific Islands
Region (PIR), 1845 Wasp Blvd., Bldg.
176, Honolulu, HI 96818.
Instructions: Comments sent by any
other method, to any other address or
individual, or received after the end of
the comment period, may not be
considered by NMFS. All comments
received are a part of the public record
and will generally be posted for public
viewing on www.regulations.gov
without change. All personal identifying
information (e.g., name, address, etc.),
confidential business information, or
otherwise sensitive information
submitted voluntarily by the sender will
be publicly accessible. NMFS will
accept anonymous comments (enter
‘‘N/A’’ in the required fields if you wish
to remain anonymous).
NMFS prepared environmental
analyses that describe the potential
impacts on the human environment that
would result from the proposed catch
limits and accountability measures. The
environmental analyses are available at
www.regulations.gov. The information
contained in the environmental analyses
is not repeated here.
FOR FURTHER INFORMATION CONTACT:
Jarad Makaiau, NMFS PIRO Sustainable
Fisheries, 808–725–5176.
SUPPLEMENTARY INFORMATION: NMFS
proposes to specify a catch limit of
2,000 mt of longline-caught bigeye tuna
for each U.S. participating territory in
2016. NMFS would also authorize each
U.S. Pacific territory to allocate up to
1,000 mt of its 2,000-mt bigeye tuna
limit to U.S. longline fishing vessels that
are permitted to fish under the Fishery
Ecosystem Plan for Pelagic Fisheries of
the Western Pacific (FEP). Those vessels
must be identified in a specified fishing
agreement with the applicable territory.
The Western Pacific Fishery
Management Council recommended
these specifications.
E:\FR\FM\07JYP1.SGM
07JYP1
Agencies
[Federal Register Volume 81, Number 130 (Thursday, July 7, 2016)]
[Proposed Rules]
[Pages 44246-44249]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-15914]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-7423; Directorate Identifier 2016-NM-034-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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[[Page 44247]]
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model 767-200, and -300 series airplanes. This
proposed AD was prompted by an evaluation by the design approval holder
(DAH) indicating that the frame-to-floor-beam joints and frames common
to shear ties at certain locations of fuselage structure are subject to
widespread fatigue damage (WFD). This proposed AD would require
repetitive inspections for cracking of the frame inner chords and webs
common to the floor beam joint and at frames common to the shear ties
at certain sections on the left and right fuselage sides, and
corrective action if necessary. We are proposing this AD to detect and
correct cracking of the frame inner chords and webs common to the floor
beam joint and at frames common to the shear ties at certain sections
on the left and right fuselage sides, which could result in reduced
structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by August 22, 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 https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
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 206-544-5000,
extension 1; fax 206-766-5680; 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 425-227-1221. It
is also available on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2016-7423.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7423; 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: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057 3356; phone: 425-917-6447; fax:
425-917-6590; email: wayne.lockett@faa.gov.
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-2016-7423;
Directorate Identifier 2016-NM-034-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 https://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
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as widespread fatigue damage. It is
associated with general degradation of large areas of structure with
similar structural details and stress levels. As an airplane ages, WFD
will likely occur, and will certainly occur if the airplane is operated
long enough without any intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
An evaluation by the DAH indicates that the frame to floor beam
joints and frames common to shear ties at certain locations of fuselage
structure are subject to WFD. This condition, if not corrected, could
result in cracking of the frame inner chords and webs common to the
floor beam joint and at frames common to the shear ties at certain
sections on the left and right fuselage sides, which could result in
reduced structural integrity of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 767-53A0265, Revision 1,
dated March 18, 2016. The service information describes procedures for
doing a detailed inspection and a surface high frequency eddy current
[[Page 44248]]
(HFEC) inspection for cracking of the frame inner chord and web common
to the floor beam joint in section 41 and 43 on the left and right
sides, a detailed inspection and a surface HFEC inspection for cracking
of the section 43 and 46 frames common to the shear ties on the left
and right sides, and repair. 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. For information on the
procedures and compliance times, see this service information at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7423.
The phrase ``corrective actions'' is used in this proposed AD.
Corrective actions correct or address any condition found. Corrective
actions in an AD could include, for example, repairs.
Costs of Compliance
We estimate that this proposed AD affects 306 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...................... Up to 350 work-hours $0 Up to $29,750 per Up to $9,103,500
x $85 per hour = inspection cycle. per inspection
$29,750 per 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-2016-7423; Directorate Identifier
2016-NM-034-AD.
(a) Comments Due Date
We must receive comments by August 22, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 767-200, and -
300 series airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 53; Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the frame-to-floor-beam joints and
frames common to shear ties at certain locations of fuselage
structure are subject to widespread fatigue damage (WFD). We are
issuing this AD to detect and correct cracking of the frame inner
chords and webs common to the floor beam joint and at frames common
to the shear ties at certain sections on the left and right fuselage
sides, which could result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections and Corrective Actions
Except as provided by paragraph (h) of this AD, at the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 767-53A0265, Revision 1, dated March
18, 2016: Do the actions required in paragraphs (g)(1) and (g)(2) of
this AD; and do all applicable corrective actions; in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 767-53A0265, Revision 1, dated March 18, 2016. Do all
applicable corrective actions before further flight. Repeat the
inspections specified in paragraphs (g)(1) and (g)(2) of this AD
thereafter at the applicable intervals specified
[[Page 44249]]
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
767-53A0265, Revision 1, dated March 18, 2016.
(1) Do a detailed inspection and a surface high frequency eddy
current (HFEC) inspection for cracking of the frame inner chord and
web common to the floor beam joint in section 41 and 43 on the left
and right sides.
(2) Do a detailed inspection and a surface HFEC inspection for
cracking of the section 43 and 46 frames common to the shear ties on
the left and right sides.
(h) Service Information Exception
Where Boeing Alert Service Bulletin 767-53A0265, Revision 1,
dated March 18, 2016, 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.
(i) 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 767-
53A0265, dated March 18, 2015. This service information is not
incorporated by reference in this AD.
(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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(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) For service information that contains steps that are labeled
as Required for Compliance (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 Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447;
fax: 425-917-6590; email: wayne.lockett@faa.gov.
(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 206-766-5680; 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 425-227-1221.
Issued in Renton, Washington, on June 23, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-15914 Filed 7-6-16; 8:45 am]
BILLING CODE 4910-13-P