[Federal Register: July 17, 2008 (Volume 73, Number 138)]
[Rules and Regulations]
[Page 40948-40951]
[DOCID:fr17jy08-2]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0639; Directorate Identifier 2007-NM-003-AD;
Amendment 39-15564; AD 2008-13-01]
RIN 2120-AA64

Airworthiness Directives; Fokker Model F27 Mark 050 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) 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:

    During scheduled X-ray inspections of Fokker 50 (F27 Mark 050)
engine mounting frames, welding defects were discovered. In two
forward frames and one aft frame, defects were found in a total of 4
weld locations. Investigation showed that during manufacture of the
frames, when the tubes were welded to the end fittings,
unintentional sideways movement of the electric arc resulted in some
welds running beside the borderline for a part of the tube
circumference. Where a weld runs beside the borderline, there is no
connection between tube and end fitting for that part of the
circumference, directly affecting the structural integrity of the
engine mounting frame connections. The defective welding process
appears to have happened at some of the welds in an unknown number
of engine mounting frames. This condition, if not corrected, could
lead to failure of the engine mounting frame in cases where multiple
welds are severely affected, potentially resulting in in-flight loss
of an engine. * * *

This AD requires actions that are intended to address the unsafe
condition described in the MCAI.

DATES: This AD becomes effective August 1, 2008.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of August 1,
2008.
    We must receive comments on this AD by August 18, 2008.

ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
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 street address for
the Docket Operations office (telephone<PHONE_NUMBER>) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1137; fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    The Civil Aviation Authority--The Netherlands (CAA-NL), which is
the aviation authority for the Netherlands, has issued Dutch
Airworthiness Directive NL-2005-015, dated November 30, 2005 (referred
to after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:

    During scheduled X-ray inspections of Fokker 50 (F27 Mark 050)
engine mounting frames, welding defects were discovered. In two
forward frames and one aft frame, defects were found in a total of 4
weld locations. Investigation showed that during manufacture of the
frames, when the tubes were welded to the end fittings,
unintentional sideways movement of the electric arc resulted in some
welds running beside the borderline for a part of the tube
circumference. Where a weld runs beside the borderline, there is no
connection between tube and end fitting for that part of the
circumference, directly affecting the structural integrity of the
engine mounting frame connections. The defective welding process
appears to have happened at some of the welds in an unknown number
of engine mounting frames. This condition, if not corrected, could
lead to failure of the engine mounting frame in cases where multiple
welds are severely affected, potentially resulting in in-flight loss
of an engine. Since

an unsafe condition had been identified that may exist on aircraft
of the same type design, Airworthiness Directive NL-2005-007 was
issued to require * * * a one-time inspection for improper welds.
The present AD further specifies the criteria and compliance times
for the follow-up NDT (non-destructive test) inspection and repair
or replacement of engine mounting frames, as necessary.

Corrective action includes contacting Fokker for repair instructions
and repair. You may obtain further information by examining the MCAI in
the AD docket.

Relevant Service Information

    Fokker Services B.V. has issued the service information identified
in the following table. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI.

                           Service Information
------------------------------------------------------------------------
       Fokker Service Bulletin                       Date
------------------------------------------------------------------------
Component Service Bulletin F8200-035- May 30, 2005.
 71-10.
Component Service Bulletin F8200-035- October 25, 2005.
 71-11.
Service Bulletin SBF50-71-048.......  May 30, 2005.
Service Bulletin SBF50-71-049.......  October 25, 2005.
------------------------------------------------------------------------

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
    There are no products of this type currently registered in the
United States. However, this rule is necessary to ensure that the
described unsafe condition is addressed if any of these products are
placed on the U.S. Register in the future.

Differences Between the AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the AD.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this product,
notice and opportunity for public comment before issuing this AD are
unnecessary.

Comments Invited

    This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2007-0639; Directorate
Identifier 2007-NM-003-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this 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 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 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 this AD:
    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); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

0
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 AD:

2008-13-01 Fokker Services B.V.: Amendment 39-15564. Docket No. FAA-
2008-0639; Directorate Identifier 2007-NM-003-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August
1, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Fokker Model F27 Mark 050 airplanes,
certificated in any category, all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 71:
Powerplant.

Reason

    (e) The mandatory continued airworthiness information (MCAI)
states:

    During scheduled X-ray inspections of Fokker 50 (F27 Mark 050)
engine mounting frames, welding defects were discovered. In two
forward frames and one aft frame, defects were found in a total of 4
weld locations. Investigation showed that during manufacture of the
frames, when the tubes were welded to the end fittings,
unintentional sideways movement of the electric arc resulted in some
welds running beside the borderline for a part of the tube
circumference. Where a weld runs beside the borderline, there is no
connection between tube and end fitting for that part of the
circumference, directly affecting the structural integrity of the
engine mounting frame connections. The defective welding process
appears to have happened at some of the welds in an unknown number
of engine mounting frames. This condition, if not corrected, could
lead to failure of the engine mounting frame in cases where multiple
welds are severely affected, potentially resulting in in-flight loss
of an engine. Since an unsafe condition had been identified that may
exist on aircraft of the same type design, Airworthiness Directive
NL-2005-007 was issued to require * * * a one-time inspection for
improper welds. The [MCAI supersedes Airworthiness Directive NL-
2005-007 and] further specifies the criteria and compliance times
for the follow-up NDT (non-destructive test) inspection and repair
or replacement of engine mounting frames, as necessary.

Corrective action includes contacting Fokker for repair instructions
and repair.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 2 months after the effective date of this AD, inspect
the engine mounting frames to identify those that have any sideways
deviations in the welds, in accordance with Part 3 of the
Accomplishment Instructions of Fokker Service Bulletin SBF50-71-048,
dated May 30, 2005. When deviations are found that are less than or
equal to 2.0 mm, no further action is required on that frame and the
aircraft may be returned to service.
    (2) When, during the inspection required by paragraph (f)(1) of
this AD, deviations are found that are greater than 2.0 mm but less
than or equal to 2.5 mm on any of the welds of the engine mounting
frame, except those of tubes 7, 8, and 12 of the rear frame: Within
12 months after the effective date of this AD, NDT (non-destructive
test) inspect the affected frame tubes in accordance with Part 3 of
the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-
049, dated October 25, 2005.
    (3) When, during the inspection required by paragraph (f)(1) of
this AD, deviations are found that are greater than 2.5 mm but less
than or equal to 3.0 mm on any of the welds of the engine mounting
frame, except those of tubes 7, 8, and 12 of the rear frame: Within
9 months after the effective date of this AD, NDT-inspect the
affected frame tubes in accordance with Part 3 of the Accomplishment
Instructions of Fokker Service Bulletin SBF50-71-049, dated October
25, 2005.
    (4) When, during the inspection required by paragraph (f)(1) of
this AD, deviations are found that are greater than 3.0 mm but less
than or equal to 3.5 mm on any of the welds of the engine mounting
frame, except those of tubes 7, 8, and 12 of the rear frame: Within
6 months after the effective date of this AD, NDT-inspect the
affected frame tubes in accordance with Part 3 of the Accomplishment
Instructions of Fokker Service Bulletin SBF50-71-049, dated October
25, 2005.
    (5) When, during the inspection required by paragraph (f)(1) of
this AD, deviations are found that are greater than 3.5 mm but less
than or equal to 5.0 mm on any of the welds of the engine mounting
frame, except those of tubes 7, 8, and 12 of the rear frame: Within
3 months after the effective date of this AD, NDT-inspect the
affected frame tubes in accordance with Part 3 of the Accomplishment
Instructions of Fokker Service Bulletin SBF50-71-049, dated October
25, 2005.
    (6) When, during the inspection required by paragraph (f)(1) of
this AD, deviations are found that are greater than 2.0 mm but less
than or equal to 5.0 mm on tubes 7, 8, and 12 of the rear frame:
Within 3 months after the effective date of this AD, NDT-inspect the
affected frame tubes in accordance with Part 3 of the Accomplishment
Instructions of Fokker Service Bulletin SBF50-71-049, dated October
25, 2005.
    (7) Within 7 days after doing any NDT-inspection required by
this AD, or within 30 days after the effective date of this AD,
whichever occurs later, report all findings to Fokker Services B.V.,
Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the
Netherlands.
    (8) Within 30 days after reporting in accordance with paragraph
(f)(7) of this AD, or within 30 days after the effective date of
this AD, whichever occurs later, repair any frame deviation in
accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, or by the
European Aviation Safety Agency (EASA) (or its designated agent).
    (9) When, during the inspection required by paragraph (f)(1) of
this AD, deviations are found exceeding 5 mm, before further flight,
report the inspection findings to Fokker Services B.V., Technical
Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands,
and repair any such deviation in accordance with a method approved
by the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA, or by EASA (or its designated agent).
    (10) Except as provided by paragraphs (f)(10)(i), (f)(10)(ii),
(f)(10)(iii), (f)(10)(iv), and (f)(10)(v) of this AD, as of the
effective date of this AD, no person may install an engine mounting
frame having part number F8200-035-427/-441/-451/-463 (forward
frames); F8200-035-425/-443 (A-frames); or F8200-035-403/-439/-449/-
461 (rear frames), as a replacement part, unless it has been
inspected and found to have deviations less than or equal to 2.0 mm,
in accordance with the requirements of Fokker Component Service
Bulletin F8200-035-71-10, dated May 30, 2005.
    (i) Any frame inspected in accordance with Fokker Component
Service Bulletin F8200-035-71-10, and found to have any deviation
greater than 2.0 mm but less than or equal to 2.5 mm on any tube,
except tubes 7, 8, and 12 of the rear frame, is acceptable for
installation. However, if a frame is installed in accordance with
this paragraph, it must be NDT-inspected within 12 months after the
installation, in accordance with Part 3 of the Accomplishment
Instructions of Fokker Service Bulletin SBF50-71-049, dated October
25, 2005.
    (ii) Any frame inspected in accordance with Fokker Component
Service Bulletin F8200-035-71-10, and found to have any deviation
greater than 2.5 mm but less than or equal to 3.0 mm on any tube,
except tubes 7, 8, and 12 of the rear frame, is acceptable for
installation. However, if a frame is installed in accordance with
this paragraph, it must be NDT-inspected within 9 months after the
installation, in accordance with Part 3 of the Accomplishment
Instructions of Fokker Service Bulletin SBF50-71-049, dated October
25, 2005.
    (iii) Any frame inspected in accordance with Fokker Component
Service Bulletin F8200-035-71-10, and found to have any deviation
greater than 3.0 mm but less than or equal to 3.5 mm on any tube,
except tubes 7, 8, and 12 of the rear frame, is acceptable for
installation. However, if a frame is installed in accordance with
this paragraph, it must be NDT-inspected within 6 months after the
installation, in accordance with Part 3 of the Accomplishment
Instructions of Fokker Service Bulletin SBF50-71-049, dated October
25, 2005.
    (iv) Any frame inspected in accordance with Fokker Component
Service Bulletin F8200-035-71-10, and found to have any deviation
greater than 3.5 mm but less than or equal to 5.0 mm on any tube,
except tubes 7, 8, and 12 of the rear frame, is acceptable for
installation. However, if a frame is installed in accordance with
this paragraph, it must be NDT-inspected within 3 months after the
installation, in accordance with Part 3 of the Accomplishment
Instructions of Fokker Service Bulletin SBF50-71-049, dated October
25, 2005.
    (v) Any tube 7, 8, or 12 of the rear frame, inspected in
accordance with Fokker

Component Service Bulletin F8200-035-71-10, and found to have any
deviation greater than 2.0 mm but less than or equal to 5.0 mm, is
acceptable for installation. However, if a frame is installed in
accordance with this paragraph, it must be NDT-inspected within 3
months after the installation, in accordance with Part 3 of the
Accomplishment Instructions of Fokker Service Bulletin SBF50-71-049,
dated October 25, 2005.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information
as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 227-1137; fax<PHONE_NUMBER>. 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, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Dutch Airworthiness Directive NL-2005-015, dated November 30,
2005, and the service bulletins identified in Table 1 of this AD for
related information.

                      Table 1.--Service Information
------------------------------------------------------------------------
       Fokker Service Bulletin                       Date
------------------------------------------------------------------------
Component Service Bulletin F8200-035- May 30, 2005.
 71-10.
Component Service Bulletin F8200-035- October 25, 2005.
 71-11.
Service Bulletin SBF50-71-048.......  May 30, 2005.
Service Bulletin SBF50-71-049.......  October 25, 2005.
------------------------------------------------------------------------

Material Incorporated by Reference

    (i) You must use the service information specified in Table 2 of
this AD to do the actions required by this AD, as applicable, unless
the AD specifies otherwise.
    (1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact
Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150
AE Nieuw-Vennep, the Netherlands.
    (3) You may review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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.

              Table 2.--Material Incorporated by Reference
------------------------------------------------------------------------
          Service Bulletin                           Date
------------------------------------------------------------------------
Fokker Component Service Bulletin     May 30, 2005.
 F8200-035-71-10.
Fokker Service Bulletin SBF50-71-048  May 30, 2005.
Fokker Service Bulletin SBF50-71-049  October 25, 2005.
------------------------------------------------------------------------

    Issued in Renton, Washington, on June 26, 2008.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-15711 Filed 7-16-08; 8:45 am]

BILLING CODE 4910-13-P


[Federal Register Volume 81, Number 142 (Monday, July 25, 2016)]
[Proposed Rules]
[Pages 48364-48365]
[FR Doc No: 2016-17558]

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.

========================================================================

Federal Register / Vol. 81, No. 142 / Monday, July 25, 2016 /
Proposed Rules

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 73

[Docket No. FAA-2016-7055; Airspace Docket No. 15-AWP-11]
RIN 2120-AA66

Proposed Establishment of Restricted Area R-2306F; Yuma Proving
Ground, AZ.

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This action proposes to establish restricted area R-2306F in
the vicinity of Laguna Army Airfield at Yuma Proving Ground, AZ. The
proposed restricted area would allow the Department of the Army to
maximize the existing fixed infrastructure to support hazardous test
programs and segregate these activities from non-participating aircraft
at Yuma Proving Ground (YPG). These programs include ground and
airborne testing of non-eye-safe lasers, high energy radars and the
development of unproven weapons systems. The restricted airspace would
ensure the safe testing and evaluation of these programs without
impacting non-participating aircraft and the general public.

DATES: Comments must be received on or before September 8, 2016.

ADDRESSES: Send comments on this proposal to the U.S. Department of
Transportation, Docket Operations, 1200 New Jersey Avenue SE., West
Building Ground Floor, Room W12-140, Washington, DC 20590; telephone: 1
(800) 647-5527, or<PHONE_NUMBER>. You must identify FAA Docket No.
FAA-2016-7055 and Airspace Docket No. 15-AWP-11, at the beginning of
your comments. You may also submit comments through the Internet at
http://www.regulations.gov. Comments on environmental and land use
aspects should be directed to: Meg McDonald, Environmental Sciences
Division, U.S. Army Garrison-Yuma, Yuma, Arizona 85365-9498. You may
review the public docket containing the proposal, any comments
received, and any final disposition in person in the Docket Office
between 9:00 a.m. and 5:00 p.m., Monday through Friday, except Federal
holidays. The Docket Office (telephone 1<PHONE_NUMBER>), is on the
ground floor of the building at the above address.

FOR FURTHER INFORMATION CONTACT: Paul Gallant, Airspace Policy Group,
Office of Airspace Services, Federal Aviation Administration, 800
Independence Avenue SW., Washington, DC 20591; telephone: (202) 267-
8783.

SUPPLEMENTARY INFORMATION:

Authority for This Rulemaking

    The FAA's authority to issue rules regarding aviation safety is
found in Title 49 of the United States Code. 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.
    This rulemaking is promulgated under the authority described in
Subtitle VII, part A, subpart I, Section 40103. Under that section, the
FAA is charged with prescribing regulations to assign the use of the
airspace necessary to ensure the safety of aircraft and the efficient
use of airspace. This regulation is within the scope of that authority
as it would establish a restricted area at Yuma, AZ, to enhance
aviation safety and accommodate essential Army testing requirements.

Comments Invited

    Interested parties are invited to participate in this proposed
rulemaking by submitting such written data, views, or arguments as they
may desire. Comments that provide the factual basis supporting the
views and suggestions presented are particularly helpful in developing
reasoned regulatory decisions on the proposal. Comments are
specifically invited on the overall regulatory, aeronautical, economic,
environmental, and energy-related aspects of the proposal.
    Communications should identify both docket numbers (FAA Docket No.
FAA-2016-7055 and Airspace Docket No. 15-AWP-11) and be submitted in
triplicate to the Docket Office at the address listed above. You may
also submit comments through the Internet at www.regulations.gov.
    Commenters wishing the FAA to acknowledge receipt of their comments
on this action must submit with those comments a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to FAA Docket No. FAA-2016-7055 and Airspace Docket No. 15-AWP-11.''
The postcard will be date/time stamped and returned to the commenter.
    All communications received on or before the specified closing date
for comments will be considered before taking action on the proposed
rule. The proposal contained in this action may be changed in light of
comments received. All comments submitted will be available for
examination in the public docket both before and after the closing date
for comments. A report summarizing each substantive public contact with
FAA personnel concerned with this rulemaking will be filed in the
docket.

Availability of NPRMs

    An electronic copy of this document may be downloaded through the
Internet at www.regulations.gov.
    You may review the public docket containing the proposal, any
comments received and any final disposition in person at the Docket
Office (see ADDRESSES section for address and phone number) between
9:00 a.m. and 5:00 p.m., Monday through Friday, except Federal
holidays. An informal docket may also be examined during normal
business hours at the office of the Operations Support Group, Western
Service Center, Federal Aviation Administration, 1601 Lind Ave. SW.,
Renton, WA 98057.

Background

    Yuma Proving Ground (YPG) is a Major Range and Test Facility Base
that conducts the development and testing of emerging aviation weapon
technologies. This testing includes both ground and air-to-ground
propagation of non-eye-safe lasers, high power radars and
developmental, unproven weapons systems. Testing includes the actual
operation of these systems using various proven and unproven aircraft
platforms. Due to the hazards of these systems, it is imperative that
these activities be segregated within a restricted area. To safely and
efficiently test and evaluate

these technologies, YPG needs to use the existing airspace and ground
infrastructure at Laguna Army Airfield. Use of the Airfield is limited
to ``official business only'' with ``prior permission required.''
Therefore, hazardous testing could be conducted safely within proposed
R-2306F without impacting non-participating aircraft.

The Proposal

    The FAA is proposing an amendment to 14 CFR part 73 to establish a
new restricted area, R-2306F, extending from the surface to 1,700 feet
MSL, in the vicinity of Laguna Army Airfield at Yuma Proving Ground,
AZ. The proposed area would be used for the testing of various
hazardous systems including non-eye-safe lasers, high energy radars and
the development of experimental weapons. Testing would include the
operation of these systems from various aircraft platforms. Restricted
airspace is required to effectively test these complex integrated
systems without posing a hazard to non-participating aircraft and/or
ground personnel. Proposed R-2306F would be completely contained over
YPG-owned land. No supersonic flights would be conducted within the
proposed airspace.

Regulatory Notices and Analyses

    The FAA has determined that this proposed regulation only involves
an established body of technical regulations for which frequent and
routine amendments are necessary to keep them operationally current.
It, therefore: (1) Is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under
Department of Transportation (DOT) Regulatory Policies and Procedures
(44 FR 11034; February 26, 1979); and (3) does not warrant preparation
of a regulatory evaluation as the anticipated impact is so minimal.
Since this is a routine matter that will only affect air traffic
procedures and air navigation, it is certified that this proposed rule,
when promulgated, will not have a significant economic impact on a
substantial number of small entities under the criteria of the
Regulatory Flexibility Act.

Environmental Review

    This proposal will be subjected to an environmental analysis in
accordance with FAA Order 1050.1F, ``Environmental Impacts: Policies
and Procedures,'' prior to any FAA final regulatory action.

List of Subjects in 14 CFR Part 73

    Airspace, Prohibited areas, Restricted areas.

The Proposed Amendment

    In consideration of the foregoing, the Federal Aviation
Administration proposes to amend 14 CFR part 73 as follows:

PART 73--SPECIAL USE AIRSPACE

0
1. The authority citation for part 73 continues to read as follows:

    Authority:  49 U.S.C. 106(f), 106(g); 40103, 40113, 40120; E.O.
10854, 24 FR 9565, 3 CFR, 1959-1963 Comp., p. 389.

Sec.  73.23  Arizona [Amended]

0
2. Sec.  73.23 is amended as follows:
* * * * *

R-2306F, Yuma West, AZ [New]

    Boundaries. Beginning at lat. 32[deg] 51' 52'' N., long.
114[deg] 26' 52'' W.; to lat. 32[deg] 52' 30'' N., long. 114[deg]
21' 03'' W.; to lat. 32[deg] 51' 15'' N., long. 114[deg] 21' 03''
W.; to lat. 32[deg] 51' 18'' N., long. 114[deg] 19' 29'' W.; then
clockwise along a 3.5 NM arc centered at lat. 32[deg] 51' 52'' N.,
long. 114[deg] 23' 34'' W.; to lat. 32[deg] 49' 30'' N., long.
114[deg] 26' 39'' W.; to lat. 32[deg] 49' 51'' N., long. 114[deg]
26' 38'' W.; to lat. 32[deg] 50' 08'' N., long. 114[deg] 26' 33''
W.; to lat. 32[deg] 50' 17'' N., long. 114[deg] 26' 19'' W.; to lat.
32[deg] 50' 31'' N., long. 114[deg] 26' 17'' W.; to lat. 32[deg] 50'
42'' N., long. 114[deg] 26' 29'' W.; to lat. 32[deg] 51' 11'' N.,
long. 114[deg] 26' 34'' W.; to the point of beginning
    Designated altitudes. Surface to 1,700 feet MSL.
    Time of designation. Intermittent, 0600-1800 local time, Monday-
Saturday; other times by NOTAM.
    Controlling agency. Yuma Approach Control, MCAS Yuma, AZ.
    Using agency. U.S., Army, Commanding Officer, Yuma Proving
Ground, Yuma, AZ.
* * * * *

    Issued in Washington, DC, on July 19, 2016.
Leslie M. Swann,
Acting Manager, Airspace Policy Group.
[FR Doc. 2016-17558 Filed 7-22-16; 8:45 am]
 BILLING CODE 4910-13-P