Accepted Means of Compliance; Airworthiness Standards: Normal Category Airplanes, 59400-59404 [2020-17911]
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Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Rules and Regulations
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List of Subjects in 10 CFR Part 72
Administrative practice and
procedure, Hazardous waste, Indians,
Intergovernmental relations, Nuclear
energy, Penalties, Radiation protection,
Reporting and recordkeeping
requirements, Security measures, Spent
fuel, Whistleblowing.
For the reasons set out in the
preamble and under the authority of the
Atomic Energy Act of 1954, as amended;
the Energy Reorganization Act of 1974,
as amended; the Nuclear Waste Policy
Act of 1982, as amended; and 5 U.S.C.
552 and 553; the NRC is amending 10
CFR part 72 to read as follows:
PART 72—LICENSING
REQUIREMENTS FOR THE
INDEPENDENT STORAGE OF SPENT
NUCLEAR FUEL, HIGH–LEVEL
RADIOACTIVE WASTE, AND
REACTOR–RELATED GREATER THAN
CLASS C WASTE
1. The authority citation for part 72
continues to read as follows:
■
Amendment Number 1, Revision 1,
Effective Date: February 1, 2016.
Amendment Number 2 Effective Date:
January 30, 2012, superseded by
Amendment Number 2, Revision 1, on
February 1, 2016.
Amendment Number 2, Revision 1,
Effective Date: February 1, 2016.
Amendment Number 3 Effective Date:
July 25, 2013, superseded by
Amendment Number 3, Revision 1, on
February 1, 2016.
Amendment Number 3, Revision 1,
Effective Date: February 1, 2016.
Amendment Number 4 Effective Date:
April 14, 2015.
Amendment Number 5 Effective Date:
June 29, 2015.
Amendment Number 6 Effective Date:
December 21, 2016.
Amendment Number 7 Effective Date:
August 21, 2017, as corrected (ADAMS
Accession No. ML19045A346).
Amendment Number 8, Effective
Date: March 24, 2020.
Amendment Number 9, Effective
Date: December 7, 2020.
SAR Submitted by: NAC
International, Inc.
SAR Title: Final Safety Analysis
Report for the MAGNASTOR® System.
Docket Number: 72–1031.
Certificate Expiration Date: February
4, 2029.
Model Number: MAGNASTOR®.
*
*
*
*
*
Authority: Atomic Energy Act of 1954,
secs. 51, 53, 57, 62, 63, 65, 69, 81, 161, 182,
183, 184, 186, 187, 189, 223, 234, 274 (42
U.S.C. 2071, 2073, 2077, 2092, 2093, 2095,
2099, 2111, 2201, 2210e, 2232, 2233, 2234,
2236, 2237, 2238, 2273, 2282, 2021); Energy
Reorganization Act of 1974, secs. 201, 202,
206, 211 (42 U.S.C. 5841, 5842, 5846, 5851);
National Environmental Policy Act of 1969
(42 U.S.C. 4332); Nuclear Waste Policy Act
of 1982, secs. 117(a), 132, 133, 134, 135, 137,
141, 145(g), 148, 218(a) (42 U.S.C. 10137(a),
10152, 10153, 10154, 10155, 10157, 10161,
10165(g), 10168, 10198(a)); 44 U.S.C. 3504
note.
Dated this September 4, 2020.
For the Nuclear Regulatory Commission.
Margaret M. Doane,
Executive Director for Operations.
2. In § 72.214, Certificate of
Compliance No. 1031 is revised to read
as follows:
[Docket No. FAA–2020–0798; Notice No. 23–
20–01–NOA]
■
[FR Doc. 2020–20666 Filed 9–21–20; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
§ 72.214 List of approved spent fuel
storage casks.
Accepted Means of Compliance;
Airworthiness Standards: Normal
Category Airplanes
*
AGENCY:
*
*
*
*
Certificate Number: 1031.
Initial Certificate Effective Date:
February 4, 2009, superseded by Initial
Certificate, Revision 1, on February 1,
2016.
Initial Certificate, Revision 1, Effective
Date: February 1, 2016.
Amendment Number 1 Effective Date:
August 30, 2010, superseded by
Amendment Number 1, Revision 1, on
February 1, 2016.
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Federal Aviation
Administration, DOT
ACTION: Notification of availability.
This document announces the
availability of means of compliance to
the applicable airworthiness standards
for normal category airplanes. The
Administrator finds these means of
compliance to be an acceptable means,
but not the only means, of showing
compliance to the applicable
SUMMARY:
PO 00000
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airworthiness standards for normal
category airplanes and that they provide
an appropriate level of safety.
DATES: Effective September 22, 2020.
FOR FURTHER INFORMATION CONTACT:
Andy Supinie, Federal Aviation
Administration, Policy and Innovation
Division, Small Airplane Standards
Branch, AIR–690, 901 Locust Street,
Room 301, Kansas City, Missouri 64106;
telephone (316) 946–4150; facsimile:
(316) 946–4107; email: andrew.supinie@
faa.gov.
SUPPLEMENTARY INFORMATION:
Background: Under the provisions of
the National Technology Transfer and
Advancement Act of 1995 1 and Office
of Management and Budget (OMB)
Circular A–119, ‘‘Federal Participation
in the Development and Use of
Voluntary Consensus Standards and in
Conformity Assessment Activities,’’
effective January 27, 2016, the FAA
participates in the development of
consensus standards and uses
consensus standards as a means of
carrying out its policy objectives where
appropriate.
Consistent with the Small Airplane
Revitalization Act of 2013,2 the FAA has
been working with industry and other
stakeholders lop consensus standards
for use as a means of compliance in
certificating small airplanes under Title
14, Code of Federal Regulations (14
CFR) part 23. In promulgating part 23,
amendment 23–64 3 (81 FR 96572,
December 30, 2016), the FAA explained
that if it determined such consensus
standards were acceptable means of
compliance to part 23, it would publish
a notice of availability of those
consensus standards in the Federal
Register.
Pursuant to FAA Advisory Circular
23.2010–1,4 ‘‘FAA Accepted Means of
Compliance Process for 14 CFR part
23,’’ section 3.1.1, this notice serves as
a formal acceptance by the
Administrator of means of compliance
based on consensus standards
developed by ASTM. The means of
compliance accepted by this notice are
one means, but not the only means of
complying with part 23 regulatory
requirements.
The FAA reviewed 35 published
ASTM consensus standards, developed
by ASTM Committee F44, as the basis
for means of compliance to 65 sections
1 Ref Public Law 104–113 as amended by Public
Law 107–107.
2 Ref Public Law 113–53.
3 See https://www.federalregister.gov/documents/
2016/12/30/2016-30246/revision-of-airworthinessstandards-for-normal-utility-acrobatic-andcommuter-category-airplanes.
4 See https://rgl.faa.gov/.
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Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Rules and Regulations
of part 23, amendment 23–64. In some
cases, the Administrator finds sections
of ASTM Standard F3264–19, ‘‘Standard
Specification for Normal Category
Aeroplanes Certification,’’ without
changes, are accepted as means of
complying with the airworthiness
requirements of amendment 23–64,
within the scope and applicability of the
consensus standards. In other cases, the
means of compliance, while based on
ASTM consensus standards, include
additional FAA provisions necessary to
comply with the airworthiness
requirements of amendment 23–64.
This document accepts only the
revisions of standards referenced in
ASTM Standard F3264–19, ‘‘Standard
Specification for Normal Category
Aeroplanes Certification.’’ Applicants
who desire to use means of compliance
reflected by other revisions to ASTM
standards not previously accepted may
seek guidance and possible acceptance
from FAA for the use of those means of
compliance on a case-by-case basis.
Applicants may also propose alternative
means of compliance for FAA review
and possible acceptance.
Amendment 23–64 established
airworthiness requirements based on the
level of safety of amendment 23–63
regulations, except for areas addressing
loss of control and icing where the
safety level was increased. Achieving
this level of safety through compliance
with amendment 23–64—for a given
certification project—may require use of
additional means of compliance beyond
those accepted by this notice,
depending on the details of the specific
design. For example, applicants with
novel designs, such as unmanned
airplanes or vertical takeoff and landing
airplanes that are outside the scope and
applicability of these consensus
standards must propose alternative
means of compliance, applicable to their
designs, to be accepted under § 23.2010.
Further information on supplemental
means of compliance is provided in a
part 23 means of compliance summary
table and in the Small Airplanes Issues
List, which are available on the Small
Airplanes—Regulations, Policies &
Guidance website.5
Means of Compliance Accepted in
this Policy: The following is a list of part
23, amendment 23–64, sections
59401
followed by their corresponding means
of compliance accepted by this notice.
However, for means of compliance
identified in the following list, Aircraft
Type Code compliance matrix tables,
which define applicability of the
individual requirements of given
standards, are not accepted in any
ASTM F44 standard. Due to errors
identified in the Aircraft Type Code
compliance matrix tables, applicability
of individual requirements of standards
must be established with the Small
Airplane Standards Branch.
23.1457: ASTM F3264–19, section 9.12
23.1459: ASTM F3264–19, section 9.13
23.1529: ASTM F3264–19, section 10.6
Subpart B—Flight
23.2100: ASTM F3264–19, section 5.1
23.2105: ASTM F3264–19, section 5.2
23.2110: ASTM F3264–19, section 5.3
23.2115: ASTM F3264–19, section 5.4
23.2120: ASTM F3264–19, section 5.5
23.2125: ASTM F3264–19, section 5.6
23.2130: ASTM F3264–19, section 5.7
23.2135: ASTM F3264–19, section 5.8,
combined with the changes in the
following table:
Replace:
With:
ASTM F3173/F3173M–18,
Section 4.3.2.
FAA Section 4.3.2
‘‘Unless otherwise required, it shall be possible to carry out the following maneuvers without requiring the application of temporary one-hand control forces exceeding those specified in Table 1, appropriate for the type of control. The trimming controls shall not be adjusted during the maneuvers.’’
FAA Section 4.3.2.3
‘‘With landing gear and flaps extended, power necessary to maintain level flight at 1.1 VS0, and the airplane as
nearly as possible in trim, it shall be possible to maintain approximately level flight while retracting the flaps as
rapidly as possible with simultaneous application of maximum continuous power. If the level acceleration will
result in exceeding VFE of the initial flap configuration prior to the flaps reaching their selected setting, power
may be reduced after achieving 1.3 VFE of the initial flap configuration. The maneuver continues until the flaps
reach the selected setting and the airplane achieves VFE of the initial flap configuration. If gated flap positions
are provided, the flap retraction may be demonstrated in stages with power and trim reset for level flight at 1.1
VS1, in the initial configuration for each stage:
(1) From the fully extended position to the most extended gated position;
(2) Between intermediate gated positions, if applicable; and
(3) From the least extended gated position to the fully retracted position.’’
FAA Section 4.7
‘‘It shall be possible, while in the landing configuration, to complete a landing without causing substantial damage
or serious injury, and without exceeding the temporary one-hand control force limits specified in Table 1, appropriate for the type of control, following an approach to land under the following conditions;’’
FAA Section 5.3.1.3
‘‘In a descent with idle power at a speed of 1.3 VS0 with landing gear extended and wing flaps in the landing position.’’
FAA Section 9.3.4
‘‘If the procedure set forth in 9.3.3.2 is used to demonstrate compliance and marginal conditions existing during
flight test with regard to reversal of primary longitudinal control force, flight tests shall be accomplished from the
normal acceleration at which a marginal stick force per g condition is found to exist to the applicable limit specified in 9.3.2.1.’’
ASTM F3173/F3173M–18,
Section 4.3.2.3.
ASTM F3173/F3173M–18,
Section 4.7.
ASTM F3173/F3173M–18
Section 5.3.1.3.
ASTM F3173/F3173M–18
Section 9.3.4.
23.2140: ASTM F3264–19, section 5.9
23.2145: ASTM F3264–19, section 5.10
23.2150: ASTM F3264–19, section 5.11,
after replacing ASTM F3180/
F3180M–19 with ASTM F3180/
F3180M–16
23.2155: ASTM F3264–19, section 5.12
23.2160: ASTM F3264–19, section 5.13
23.2165: ASTM F3264–19, section 5.14
Subpart C—Structures
23.2200: ASTM F3264–19, section 6.1
23.2205: ASTM F3264–19, section 6.2,
combined with the changes to
5 See https://www.faa.gov/aircraft/air_cert/
design_approvals/small_airplanes/small_airplanes_
regs/.
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Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Rules and Regulations
ASTM F3254–19, Figures 2, 3, and
4 shown in the following table:
Replace:
With:
‘‘Remote’’ ..............................
‘‘Extremely Improbable’’ .......
‘‘10¥5’’
‘‘10¥8’’ for Level 1, 2 and 3 airplanes and with ‘‘10¥9’’ for Level 4 airplanes’’
23.2210: ASTM F3264–19, section 6.3
23.2215: ASTM F3264–19, section 6.4,
combined with the changes in the
following table:
Replace:
With:
ASTM F3116/F3116M–18,
Section 4.1.4.
FAA Section 4.1.4
‘‘Appendix X1 through Appendix X4 provides, within the limitations specified within the appendix, a simplified
means of compliance with several of the requirements set forth in sections 4.2 to 4.26 and 7.1 to 7.9 that can
be applied as one (but not the only) means to comply. If the simplified methods in appendix X1 through X3 are
used, they must be used together in their entirety.’’
FAA Section X1.1.1
‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compliance and can only be applied to level 1 and level 2 low speed airplanes.’’
ASTM F3116/F3116M–18,
Section X1.1.1.
23.2220: ASTM F3264–19, section 6.5
23.2225: ASTM F3264–19, section 6.6,
combined with the changes in the
following table:
Replace:
With:
ASTM F3116/F3116M–18,
Section X2.1.1.
FAA X2.1.1
‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compliance and can only be applied to level 1 and level 2 low speed airplanes.’’
FAA X3.1.1
‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compliance and can only be applied to level 1 and level 2 low speed airplanes.’’
FAA X4.1.1
‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compliance and can only be applied to level 1 low speed airplanes.’’
ASTM F3116/F3116M–18,
Section X3.1.1.
ASTM F3116/F3116M–18,
Section X4.1.1.
23.2230: ASTM F3264–19, section 6.7
23.2235: ASTM F3264–19, section 6.8
23.2240: ASTM F3264–19, section 6.9,
after replacing ASTM F3115/
F3115M–19 with ASTM F3115/
F3115M–15 and making the
changes in the following table:
Replace:
With:
ASTM F3115/F3115M–15,
Section 4.4.1.
FAA 4.4.1
‘‘For metallic (aluminum), unpressurized, non-aerobatic, low-speed, level 1 airplanes, applicants can demonstrate
a 10,000 hour safe-life by limiting the ‘1g’ gross stress, at maximum takeoff weight, to no more than 5.5 ksi.
The applicant must show effective stress concentration factors of 4 or less in highly loaded joints and use materials or material systems for which the physical and mechanical properties are well established.’’
FAA 6.1
‘‘For bonded airframe structure, the residual strength of bonded joints shall be addressed as follows: For any
bonded joint, the failure of which would result in catastrophic loss of the airplane, the limit load capacity must
be substantiated by one of the following methods.’’
ASTM F3115/F3115M–15,
Section 6.1.
23.2245: ASTM F3264–19, section 6.10
23.2250: ASTM F3264–19, section 6.11
23.2255: ASTM F3264–19, section 6.12
23.2260: ASTM F3264–19, section 6.13
23.2265: ASTM F3264–19, section 6.14
23.2270: ASTM F3264–19, section 6.15,
combined with the changes in the
following table:
Replace:
With:
ASTM F3083/F3083M–19
Section 4.1.6.
FAA Section 4.1.6
‘‘Engine mount and supporting structure must withstand 18.0 g forward for engines installed behind and above
the seating compartment.’’
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Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Rules and Regulations
Subpart D—Design and Construction
23.2300: ASTM F3264–19, section 7.1
23.2305: ASTM F3264–19, section 7.2
23.2310: ASTM F3264–19, section 7.3
23.2315: ASTM F3264–19, section 7.4
23.2320: ASTM F3264–19, section 7.5
23.2325: ASTM F3264–19, section 7.6,
except delete ASTM F3264–19,
section 7.6.1.3
23.2330: ASTM F3264–19, section 7.7
23.2335: ASTM F3264–19, section 7.8
Subpart E—Powerplant
23.2400: ASTM F3264–19, section 8.1,
except delete ASTM F3264–19,
section 8.1.6
23.2405: ASTM F3264–19, section 8.2,
except delete ASTM F3264–19,
section 8.2.4
23.2410: ASTM F3264–19, section 8.3,
except delete ASTM F3264–19,
section 8.3.8
23.2415: ASTM F3264–19, section 8.4,
combined with the following
changes:
1. Delete ASTM F3264–19, section
8.4.4
2. Add: An FAA accepted means of
compliance for the turbine engine
installation ice protection
requirement of § 23.2415, on
airplanes not approved for flight
into known icing, such as the
provisions of F3120/F3120M–19
section 7.2 and 7.3 (regardless of
the operation requirements in
F3120/F3120M–19 Table 1).
23.2420: ASTM F3264–19, section 8.5,
except delete ASTM F3264–19,
section 8.5.3
23.2425: ASTM F3264–19, section 8.6,
except delete ASTM F3264–19,
section 8.6.6
59403
23.2430: ASTM F3264–19, section 8.7,
except delete ASTM F3264–19,
section 8.7.6
23.2435: ASTM F3264–19, section 8.8,
except delete ASTM F3264–19,
section 8.8.2
23.2440: ASTM F3264–19, section 8.9,
except delete ASTM F3264–19,
section 8.9.5
Subpart F—Equipment
23.2500: ASTM F3264–19, section 9.1,
combined with the following
changes:
1. Delete ASTM F3264–19, section
9.1.1.2(a)
2. Delete ASTM F3264–19, section
9.1.1.5
3. As shown in the following table:
Replace:
With:
ASTM F3230–17 Section
3.2.1.
FAA Section 3.2.1
‘‘aircraft type code, n—an Aircraft Type Code (ATC) is defined by considering both the technical considerations
regarding the design of the aircraft and the aeroplane certification level established based upon risk-based criteria; the method of defining an ATC applicable to this practice is defined in Specification F3061/F3061M.’’
FAA Section 4 Example
‘‘Example—An aircraft with an ATC of 1SRLLDLN is being considered. Since all applicable columns are empty
for 4.1, that subsection is applicable to the aircraft. Since the ‘‘1’’ aeroplane certification level column, the ‘‘L’’
stall speed column, and the ‘‘D’’ meteorological column for 4.2.1 all contain white circles, then that subsection
is not applicable; however, for an aircraft with an ATC of 1SRMLDLN, 4.2.1 would be applicable since the ‘‘M’’
stall speed column does not contain a white circle.’’
FAA Table 1
Column header ‘‘Aeroplane Certification Level’’.
ASTM F3230–17 Section 4
Example.
ASTM F3230–17 Table 1 .....
Column header ‘‘Airworthiness Level’’.
ASTM F3230–17 Table 3 .....
Column header ‘‘Airworthiness Level’’.
FAA Table 3
Column header ‘‘Aeroplane Certification Level’’.
23.2505: ASTM F3264–19, section 9.2,
combined with the following
changes:
1. Delete ASTM F3264–19, section
9.2.1.1(a)
2. Delete ASTM F3264–19, section
9.2.1.4
23.2510: ASTM F3264–19, section 9.3,
combined with the following
changes:
1. Delete ASTM F3264–19, section
9.3.1.2
2. As shown in the following table:
Replace:
With:
ASTM F3230–17 Section
3.2.1.
FAA Section 3.2.1
‘‘aircraft type code, n—an Aircraft Type Code (ATC) is defined by considering both the technical considerations
regarding the design of the aircraft and the aeroplane certification level established based upon risk-based criteria; the method of defining an ATC applicable to this practice is defined in Specification F3061/F3061M.’’
FAA Section 4 Example
‘‘Example—An aircraft with an ATC of 1SRLLDLN is being considered. Since all applicable columns are empty
for 4.1, that subsection is applicable to the aircraft. Since the ‘‘1’’ aeroplane certification level column, the ‘‘L’’
stall speed column, and the ‘‘D’’ meteorological column for 4.2.1 all contain white circles, then that subsection
is not applicable; however, for an aircraft with an ATC of 1SRMLDLN, 4.2.1 would be applicable since the ‘‘M’’
stall speed column does not contain a white circle.’’
FAA Table 1
Column header ‘‘Aeroplane Certification Level’’
ASTM F3230–17 Section 4
Example.
ASTM F3230–17 Table 1 .....
Column header ‘‘Airworthiness Level’’.
ASTM F3230–17 Table 3 .....
Column header ‘‘Airworthiness Level’’.
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FAA Table 3
Column header ‘‘Aeroplane Certification Level’’
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Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Rules and Regulations
23.2515: ASTM F3264–19, section 9.4
23.2520: ASTM F3264–19, section 9.5,
combined with the changes in the
following table:
Replace:
With:
ASTM F3236–17 Table 2
entry.
400 to 700 Mhz frequency
range field strength average value: ‘‘100 volts/
meter’’.
ASTM F3236–17 Section
4.2.3.3.
FAA Table 2 entry
400 to 700 Mhz frequency range field strength average value:
‘‘50 volts/meter’’
FAA Section 4.2.3.3
‘‘From 40 to 400 MHz, use conducted susceptibility tests, starting at a minimum of 30 mA at 40 MHz, decreasing
20 dB per frequency decade to a minimum of 3 mA at 400 MHz.’’
23.2525: ASTM F3264–19, section 9.6,
except delete ASTM F3264–19,
section 9.6.2.3
23.2530: ASTM F3264–19, section 9.7
23.2535: ASTM F3264–19, section 9.8,
except delete ASTM F3264–19,
section 9.8.1
23.2540: ASTM F3264–19, section 9.9
23.2545: ASTM F3264–19, section 9.10
23.2550: ASTM F3264–19, section 9.11
Subpart G—Flightcrew Interface and
Other Information
23.2600: ASTM F3264–19, section 10.1,
combined with the following
changes:
1. Add an FAA-accepted means of
compliance for the windshield
luminous transmittance aspects of
§ 23.2600, such as the provisions of
§ 23.775(e), amendment 23–49.
2. Add an FAA-accepted means of
compliance for the pilot
compartment view with formation
of fog or frost aspects of § 23.2600,
such as the provisions of
§ 23.773(b), amendment 23–45.
23.2605: ASTM F3264–19, section 10.2
23.2610: ASTM F3264–19, section 10.3
23.2615: ASTM F3264–19, section 10.4,
combined with the changes in the
following table:
Replace:
With:
ASTM F3064/F3064M–19, Section
6.
An FAA-accepted means of compliance for the powerplant instruments aspects of § 23.2615, such as the
provisions of § 23.1305, amendment 23–52.
23.2620: ASTM F3264–19, sections 5.15
AND 10.5
Editorial, reapproval, revision or
withdrawal: The FAA expects a suitable
consensus standard to be reviewed
periodically. ASTM policy is that a
consensus standard should be reviewed
in its entirety by the responsible
subcommittee and must be balloted for
reapproval, revision, or withdrawal,
within five years of its last approval
date. ASTM reapproves a standard—
denoted by the year of reapproval in
parentheses (e.g., F2427–05a(2013))—to
indicate completion of a review cycle
with no technical changes made to the
standard. ASTM issues editorial
changes—denoted by a superscript
epsilon in the standard designation (e.g.,
F3235–17e1)—to correct information
that does not change the meaning or
intent of a standard. Any means of
compliance accepted by this notice that
is based on a standard later reapproved
or editorially changed is also considered
accepted without the need for a NOA.
ASTM revises a standard to make
changes to its technical content.
Revisions to consensus standards
serving as the basis for means of
compliance accepted by this notice will
not be automatically accepted and will
require further FAA acceptance in order
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16:32 Sep 21, 2020
Jkt 250001
for the revisions to be an accepted
means of compliance.
Availability
ASTM Standard F3264–19, ‘‘Standard
Specification for Normal Category
Aeroplanes Certification,’’ is available
for online reading at https://
www.astm.org/READINGLIBRARY/.
ASTM International copyrights these
consensus standards and charges the
public a fee for service. Individual
downloads or reprints of a standard
(single or multiple copies, or special
compilations and other related technical
information) may be obtained through
www.astm.org or contacting ASTM at
(610) 832–9585 (phone), (610) 832–9555
(fax), or through service@astm.org
(email). To inquire about consensus
standard content and/or membership or
about ASTM Offices abroad, contact Joe
Koury, Staff Manager for Committee F44
on General Aviation Aircraft: (610) 832–
9804, jkoury@astm.org.
The FAA maintains a list of accepted
means of compliance on the FAA
website at https://www.faa.gov/aircraft/
air_cert/design_approvals/small_
airplanes/small_airplanes_regs/.
PO 00000
Frm 00028
Fmt 4700
Sfmt 4700
Issued in Kansas City, Missouri on August
12, 2020.
Pat Mullen,
Manager, Small Airplanes Standards Branch,
Policy and Innovation Division, Aircraft
Certification Service.
[FR Doc. 2020–17911 Filed 9–21–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0411; Product
Identifier 2018–SW–061–AD; Amendment
39–21254; AD 2020–19–11]
RIN 2120–AA64
Airworthiness Directives; Leonardo
S.p.a. Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Leonardo S.p.a. (Leonardo) Model A119
and AW119 MKII helicopters. This AD
requires repetitive borescope
inspections of the tail rotor gearbox
(TGB) and depending on the inspection
results, removing the TGB from service.
SUMMARY:
E:\FR\FM\22SER1.SGM
22SER1
]]>Agencies
[Federal Register Volume 85, Number 184 (Tuesday, September 22, 2020)]
[Rules and Regulations]
[Pages 59400-59404]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-17911]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. FAA-2020-0798; Notice No. 23-20-01-NOA]
Accepted Means of Compliance; Airworthiness Standards: Normal
Category Airplanes
AGENCY: Federal Aviation Administration, DOT
ACTION: Notification of availability.
-----------------------------------------------------------------------
SUMMARY: This document announces the availability of means of
compliance to the applicable airworthiness standards for normal
category airplanes. The Administrator finds these means of compliance
to be an acceptable means, but not the only means, of showing
compliance to the applicable airworthiness standards for normal
category airplanes and that they provide an appropriate level of
safety.
DATES: Effective September 22, 2020.
FOR FURTHER INFORMATION CONTACT: Andy Supinie, Federal Aviation
Administration, Policy and Innovation Division, Small Airplane
Standards Branch, AIR-690, 901 Locust Street, Room 301, Kansas City,
Missouri 64106; telephone (316) 946-4150; facsimile: (316) 946-4107;
email: [email protected].
SUPPLEMENTARY INFORMATION: Background: Under the provisions of the
National Technology Transfer and Advancement Act of 1995 \1\ and Office
of Management and Budget (OMB) Circular A-119, ``Federal Participation
in the Development and Use of Voluntary Consensus Standards and in
Conformity Assessment Activities,'' effective January 27, 2016, the FAA
participates in the development of consensus standards and uses
consensus standards as a means of carrying out its policy objectives
where appropriate.
---------------------------------------------------------------------------
\1\ Ref Public Law 104-113 as amended by Public Law 107-107.
---------------------------------------------------------------------------
Consistent with the Small Airplane Revitalization Act of 2013,\2\
the FAA has been working with industry and other stakeholders lop
consensus standards for use as a means of compliance in certificating
small airplanes under Title 14, Code of Federal Regulations (14 CFR)
part 23. In promulgating part 23, amendment 23-64 \3\ (81 FR 96572,
December 30, 2016), the FAA explained that if it determined such
consensus standards were acceptable means of compliance to part 23, it
would publish a notice of availability of those consensus standards in
the Federal Register.
---------------------------------------------------------------------------
\2\ Ref Public Law 113-53.
\3\ See https://www.federalregister.gov/documents/2016/12/30/2016-30246/revision-of-airworthiness-standards-for-normal-utility-acrobatic-and-commuter-category-airplanes.
---------------------------------------------------------------------------
Pursuant to FAA Advisory Circular 23.2010-1,\4\ ``FAA Accepted
Means of Compliance Process for 14 CFR part 23,'' section 3.1.1, this
notice serves as a formal acceptance by the Administrator of means of
compliance based on consensus standards developed by ASTM. The means of
compliance accepted by this notice are one means, but not the only
means of complying with part 23 regulatory requirements.
---------------------------------------------------------------------------
\4\ See https://rgl.faa.gov/.
---------------------------------------------------------------------------
The FAA reviewed 35 published ASTM consensus standards, developed
by ASTM Committee F44, as the basis for means of compliance to 65
sections
[[Page 59401]]
of part 23, amendment 23-64. In some cases, the Administrator finds
sections of ASTM Standard F3264-19, ``Standard Specification for Normal
Category Aeroplanes Certification,'' without changes, are accepted as
means of complying with the airworthiness requirements of amendment 23-
64, within the scope and applicability of the consensus standards. In
other cases, the means of compliance, while based on ASTM consensus
standards, include additional FAA provisions necessary to comply with
the airworthiness requirements of amendment 23-64.
This document accepts only the revisions of standards referenced in
ASTM Standard F3264-19, ``Standard Specification for Normal Category
Aeroplanes Certification.'' Applicants who desire to use means of
compliance reflected by other revisions to ASTM standards not
previously accepted may seek guidance and possible acceptance from FAA
for the use of those means of compliance on a case-by-case basis.
Applicants may also propose alternative means of compliance for FAA
review and possible acceptance.
Amendment 23-64 established airworthiness requirements based on the
level of safety of amendment 23-63 regulations, except for areas
addressing loss of control and icing where the safety level was
increased. Achieving this level of safety through compliance with
amendment 23-64--for a given certification project--may require use of
additional means of compliance beyond those accepted by this notice,
depending on the details of the specific design. For example,
applicants with novel designs, such as unmanned airplanes or vertical
takeoff and landing airplanes that are outside the scope and
applicability of these consensus standards must propose alternative
means of compliance, applicable to their designs, to be accepted under
Sec. 23.2010.
Further information on supplemental means of compliance is provided
in a part 23 means of compliance summary table and in the Small
Airplanes Issues List, which are available on the Small Airplanes--
Regulations, Policies & Guidance website.\5\
---------------------------------------------------------------------------
\5\ See https://www.faa.gov/aircraft/air_cert/design_approvals/small_airplanes/small_airplanes_regs/.
---------------------------------------------------------------------------
Means of Compliance Accepted in this Policy: The following is a
list of part 23, amendment 23-64, sections followed by their
corresponding means of compliance accepted by this notice. However, for
means of compliance identified in the following list, Aircraft Type
Code compliance matrix tables, which define applicability of the
individual requirements of given standards, are not accepted in any
ASTM F44 standard. Due to errors identified in the Aircraft Type Code
compliance matrix tables, applicability of individual requirements of
standards must be established with the Small Airplane Standards Branch.
23.1457: ASTM F3264-19, section 9.12
23.1459: ASTM F3264-19, section 9.13
23.1529: ASTM F3264-19, section 10.6
Subpart B--Flight
23.2100: ASTM F3264-19, section 5.1
23.2105: ASTM F3264-19, section 5.2
23.2110: ASTM F3264-19, section 5.3
23.2115: ASTM F3264-19, section 5.4
23.2120: ASTM F3264-19, section 5.5
23.2125: ASTM F3264-19, section 5.6
23.2130: ASTM F3264-19, section 5.7
23.2135: ASTM F3264-19, section 5.8, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3173/F3173M-18, Section FAA Section 4.3.2
4.3.2. ``Unless otherwise required, it shall be
possible to carry out the following
maneuvers without requiring the
application of temporary one-hand
control forces exceeding those specified
in Table 1, appropriate for the type of
control. The trimming controls shall not
be adjusted during the maneuvers.''
ASTM F3173/F3173M-18, Section FAA Section 4.3.2.3
4.3.2.3. ``With landing gear and flaps extended,
power necessary to maintain level flight
at 1.1 VS0, and the airplane as nearly
as possible in trim, it shall be
possible to maintain approximately level
flight while retracting the flaps as
rapidly as possible with simultaneous
application of maximum continuous power.
If the level acceleration will result in
exceeding VFE of the initial flap
configuration prior to the flaps
reaching their selected setting, power
may be reduced after achieving 1.3 VFE
of the initial flap configuration. The
maneuver continues until the flaps reach
the selected setting and the airplane
achieves VFE of the initial flap
configuration. If gated flap positions
are provided, the flap retraction may be
demonstrated in stages with power and
trim reset for level flight at 1.1 VS1,
in the initial configuration for each
stage:
(1) From the fully extended position to
the most extended gated position;
(2) Between intermediate gated positions,
if applicable; and
(3) From the least extended gated
position to the fully retracted
position.''
ASTM F3173/F3173M-18, Section FAA Section 4.7
4.7. ``It shall be possible, while in the
landing configuration, to complete a
landing without causing substantial
damage or serious injury, and without
exceeding the temporary one-hand control
force limits specified in Table 1,
appropriate for the type of control,
following an approach to land under the
following conditions;''
ASTM F3173/F3173M-18 Section FAA Section 5.3.1.3
5.3.1.3. ``In a descent with idle power at a speed
of 1.3 VS0 with landing gear extended
and wing flaps in the landing
position.''
ASTM F3173/F3173M-18 Section FAA Section 9.3.4
9.3.4. ``If the procedure set forth in 9.3.3.2
is used to demonstrate compliance and
marginal conditions existing during
flight test with regard to reversal of
primary longitudinal control force,
flight tests shall be accomplished from
the normal acceleration at which a
marginal stick force per g condition is
found to exist to the applicable limit
specified in 9.3.2.1.''
------------------------------------------------------------------------
23.2140: ASTM F3264-19, section 5.9
23.2145: ASTM F3264-19, section 5.10
23.2150: ASTM F3264-19, section 5.11, after replacing ASTM F3180/
F3180M-19 with ASTM F3180/F3180M-16
23.2155: ASTM F3264-19, section 5.12
23.2160: ASTM F3264-19, section 5.13
23.2165: ASTM F3264-19, section 5.14
Subpart C--Structures
23.2200: ASTM F3264-19, section 6.1
23.2205: ASTM F3264-19, section 6.2, combined with the changes to
[[Page 59402]]
ASTM F3254-19, Figures 2, 3, and 4 shown in the following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
``Remote''................... ``10-5''
``Extremely Improbable''..... ``10-8'' for Level 1, 2 and 3 airplanes
and with ``10-9'' for Level 4
airplanes''
------------------------------------------------------------------------
23.2210: ASTM F3264-19, section 6.3
23.2215: ASTM F3264-19, section 6.4, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3116/F3116M-18, Section FAA Section 4.1.4
4.1.4. ``Appendix X1 through Appendix X4
provides, within the limitations
specified within the appendix, a
simplified means of compliance with
several of the requirements set forth in
sections 4.2 to 4.26 and 7.1 to 7.9 that
can be applied as one (but not the only)
means to comply. If the simplified
methods in appendix X1 through X3 are
used, they must be used together in
their entirety.''
ASTM F3116/F3116M-18, Section FAA Section X1.1.1
X1.1.1. ``The methods provided in this appendix
provide one possible means (but not the
only possible means) of compliance and
can only be applied to level 1 and level
2 low speed airplanes.''
------------------------------------------------------------------------
23.2220: ASTM F3264-19, section 6.5
23.2225: ASTM F3264-19, section 6.6, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3116/F3116M-18, Section FAA X2.1.1
X2.1.1. ``The methods provided in this appendix
provide one possible means (but not the
only possible means) of compliance and
can only be applied to level 1 and level
2 low speed airplanes.''
ASTM F3116/F3116M-18, Section FAA X3.1.1
X3.1.1. ``The methods provided in this appendix
provide one possible means (but not the
only possible means) of compliance and
can only be applied to level 1 and level
2 low speed airplanes.''
ASTM F3116/F3116M-18, Section FAA X4.1.1
X4.1.1. ``The methods provided in this appendix
provide one possible means (but not the
only possible means) of compliance and
can only be applied to level 1 low speed
airplanes.''
------------------------------------------------------------------------
23.2230: ASTM F3264-19, section 6.7
23.2235: ASTM F3264-19, section 6.8
23.2240: ASTM F3264-19, section 6.9, after replacing ASTM F3115/F3115M-
19 with ASTM F3115/F3115M-15 and making the changes in the following
table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3115/F3115M-15, Section FAA 4.4.1
4.4.1. ``For metallic (aluminum), unpressurized,
non-aerobatic, low-speed, level 1
airplanes, applicants can demonstrate a
10,000 hour safe-life by limiting the
`1g' gross stress, at maximum takeoff
weight, to no more than 5.5 ksi. The
applicant must show effective stress
concentration factors of 4 or less in
highly loaded joints and use materials
or material systems for which the
physical and mechanical properties are
well established.''
ASTM F3115/F3115M-15, Section FAA 6.1
6.1. ``For bonded airframe structure, the
residual strength of bonded joints shall
be addressed as follows: For any bonded
joint, the failure of which would result
in catastrophic loss of the airplane,
the limit load capacity must be
substantiated by one of the following
methods.''
------------------------------------------------------------------------
23.2245: ASTM F3264-19, section 6.10
23.2250: ASTM F3264-19, section 6.11
23.2255: ASTM F3264-19, section 6.12
23.2260: ASTM F3264-19, section 6.13
23.2265: ASTM F3264-19, section 6.14
23.2270: ASTM F3264-19, section 6.15, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3083/F3083M-19 Section FAA Section 4.1.6
4.1.6. ``Engine mount and supporting structure
must withstand 18.0 g forward for
engines installed behind and above the
seating compartment.''
------------------------------------------------------------------------
[[Page 59403]]
Subpart D--Design and Construction
23.2300: ASTM F3264-19, section 7.1
23.2305: ASTM F3264-19, section 7.2
23.2310: ASTM F3264-19, section 7.3
23.2315: ASTM F3264-19, section 7.4
23.2320: ASTM F3264-19, section 7.5
23.2325: ASTM F3264-19, section 7.6, except delete ASTM F3264-19,
section 7.6.1.3
23.2330: ASTM F3264-19, section 7.7
23.2335: ASTM F3264-19, section 7.8
Subpart E--Powerplant
23.2400: ASTM F3264-19, section 8.1, except delete ASTM F3264-19,
section 8.1.6
23.2405: ASTM F3264-19, section 8.2, except delete ASTM F3264-19,
section 8.2.4
23.2410: ASTM F3264-19, section 8.3, except delete ASTM F3264-19,
section 8.3.8
23.2415: ASTM F3264-19, section 8.4, combined with the following
changes:
1. Delete ASTM F3264-19, section 8.4.4
2. Add: An FAA accepted means of compliance for the turbine engine
installation ice protection requirement of Sec. 23.2415, on airplanes
not approved for flight into known icing, such as the provisions of
F3120/F3120M-19 section 7.2 and 7.3 (regardless of the operation
requirements in F3120/F3120M-19 Table 1).
23.2420: ASTM F3264-19, section 8.5, except delete ASTM F3264-19,
section 8.5.3
23.2425: ASTM F3264-19, section 8.6, except delete ASTM F3264-19,
section 8.6.6
23.2430: ASTM F3264-19, section 8.7, except delete ASTM F3264-19,
section 8.7.6
23.2435: ASTM F3264-19, section 8.8, except delete ASTM F3264-19,
section 8.8.2
23.2440: ASTM F3264-19, section 8.9, except delete ASTM F3264-19,
section 8.9.5
Subpart F--Equipment
23.2500: ASTM F3264-19, section 9.1, combined with the following
changes:
1. Delete ASTM F3264-19, section 9.1.1.2(a)
2. Delete ASTM F3264-19, section 9.1.1.5
3. As shown in the following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3230-17 Section 3.2.1.. FAA Section 3.2.1
``aircraft type code, n--an Aircraft Type
Code (ATC) is defined by considering
both the technical considerations
regarding the design of the aircraft and
the aeroplane certification level
established based upon risk-based
criteria; the method of defining an ATC
applicable to this practice is defined
in Specification F3061/F3061M.''
ASTM F3230-17 Section 4 FAA Section 4 Example
Example. ``Example--An aircraft with an ATC of
1SRLLDLN is being considered. Since all
applicable columns are empty for 4.1,
that subsection is applicable to the
aircraft. Since the ``1'' aeroplane
certification level column, the ``L''
stall speed column, and the ``D''
meteorological column for 4.2.1 all
contain white circles, then that
subsection is not applicable; however,
for an aircraft with an ATC of 1SRMLDLN,
4.2.1 would be applicable since the
``M'' stall speed column does not
contain a white circle.''
ASTM F3230-17 Table 1........ FAA Table 1
Column header ``Airworthiness Column header ``Aeroplane Certification
Level''. Level''.
ASTM F3230-17 Table 3........ FAA Table 3
Column header ``Airworthiness Column header ``Aeroplane Certification
Level''. Level''.
------------------------------------------------------------------------
23.2505: ASTM F3264-19, section 9.2, combined with the following
changes:
1. Delete ASTM F3264-19, section 9.2.1.1(a)
2. Delete ASTM F3264-19, section 9.2.1.4
23.2510: ASTM F3264-19, section 9.3, combined with the following
changes:
1. Delete ASTM F3264-19, section 9.3.1.2
2. As shown in the following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3230-17 Section 3.2.1.. FAA Section 3.2.1
``aircraft type code, n--an Aircraft Type
Code (ATC) is defined by considering
both the technical considerations
regarding the design of the aircraft and
the aeroplane certification level
established based upon risk-based
criteria; the method of defining an ATC
applicable to this practice is defined
in Specification F3061/F3061M.''
ASTM F3230-17 Section 4 FAA Section 4 Example
Example. ``Example--An aircraft with an ATC of
1SRLLDLN is being considered. Since all
applicable columns are empty for 4.1,
that subsection is applicable to the
aircraft. Since the ``1'' aeroplane
certification level column, the ``L''
stall speed column, and the ``D''
meteorological column for 4.2.1 all
contain white circles, then that
subsection is not applicable; however,
for an aircraft with an ATC of 1SRMLDLN,
4.2.1 would be applicable since the
``M'' stall speed column does not
contain a white circle.''
ASTM F3230-17 Table 1........ FAA Table 1
Column header ``Airworthiness Column header ``Aeroplane Certification
Level''. Level''
ASTM F3230-17 Table 3........ FAA Table 3
Column header ``Airworthiness Column header ``Aeroplane Certification
Level''. Level''
------------------------------------------------------------------------
[[Page 59404]]
23.2515: ASTM F3264-19, section 9.4
23.2520: ASTM F3264-19, section 9.5, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3236-17 Table 2 entry.. FAA Table 2 entry
400 to 700 Mhz frequency 400 to 700 Mhz frequency range field
range field strength average strength average value:
value: ``100 volts/meter''. ``50 volts/meter''
ASTM F3236-17 Section 4.2.3.3 FAA Section 4.2.3.3
``From 40 to 400 MHz, use conducted
susceptibility tests, starting at a
minimum of 30 mA at 40 MHz, decreasing
20 dB per frequency decade to a minimum
of 3 mA at 400 MHz.''
------------------------------------------------------------------------
23.2525: ASTM F3264-19, section 9.6, except delete ASTM F3264-19,
section 9.6.2.3
23.2530: ASTM F3264-19, section 9.7
23.2535: ASTM F3264-19, section 9.8, except delete ASTM F3264-19,
section 9.8.1
23.2540: ASTM F3264-19, section 9.9
23.2545: ASTM F3264-19, section 9.10
23.2550: ASTM F3264-19, section 9.11
Subpart G--Flightcrew Interface and Other Information
23.2600: ASTM F3264-19, section 10.1, combined with the following
changes:
1. Add an FAA-accepted means of compliance for the windshield
luminous transmittance aspects of Sec. 23.2600, such as the provisions
of Sec. 23.775(e), amendment 23-49.
2. Add an FAA-accepted means of compliance for the pilot
compartment view with formation of fog or frost aspects of Sec.
23.2600, such as the provisions of Sec. 23.773(b), amendment 23-45.
23.2605: ASTM F3264-19, section 10.2
23.2610: ASTM F3264-19, section 10.3
23.2615: ASTM F3264-19, section 10.4, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3064/F3064M-19, Section 6... An FAA-accepted means of compliance
for the powerplant instruments
aspects of Sec. 23.2615, such as
the provisions of Sec. 23.1305,
amendment 23-52.
------------------------------------------------------------------------
23.2620: ASTM F3264-19, sections 5.15 AND 10.5
Editorial, reapproval, revision or withdrawal: The FAA expects a
suitable consensus standard to be reviewed periodically. ASTM policy is
that a consensus standard should be reviewed in its entirety by the
responsible subcommittee and must be balloted for reapproval, revision,
or withdrawal, within five years of its last approval date. ASTM
reapproves a standard--denoted by the year of reapproval in parentheses
(e.g., F2427-05a(2013))--to indicate completion of a review cycle with
no technical changes made to the standard. ASTM issues editorial
changes--denoted by a superscript epsilon in the standard designation
(e.g., F3235-17[epsi]1)--to correct information that does
not change the meaning or intent of a standard. Any means of compliance
accepted by this notice that is based on a standard later reapproved or
editorially changed is also considered accepted without the need for a
NOA. ASTM revises a standard to make changes to its technical content.
Revisions to consensus standards serving as the basis for means of
compliance accepted by this notice will not be automatically accepted
and will require further FAA acceptance in order for the revisions to
be an accepted means of compliance.
Availability
ASTM Standard F3264-19, ``Standard Specification for Normal
Category Aeroplanes Certification,'' is available for online reading at
https://www.astm.org/READINGLIBRARY/. ASTM International copyrights
these consensus standards and charges the public a fee for service.
Individual downloads or reprints of a standard (single or multiple
copies, or special compilations and other related technical
information) may be obtained through www.astm.org or contacting ASTM at
(610) 832-9585 (phone), (610) 832-9555 (fax), or through
[email protected] (email). To inquire about consensus standard content
and/or membership or about ASTM Offices abroad, contact Joe Koury,
Staff Manager for Committee F44 on General Aviation Aircraft: (610)
832-9804, [email protected].
The FAA maintains a list of accepted means of compliance on the FAA
website at https://www.faa.gov/aircraft/air_cert/design_approvals/small_airplanes/small_airplanes_regs/.
Issued in Kansas City, Missouri on August 12, 2020.
Pat Mullen,
Manager, Small Airplanes Standards Branch, Policy and Innovation
Division, Aircraft Certification Service.
[FR Doc. 2020-17911 Filed 9-21-20; 8:45 am]
BILLING CODE 4910-13-P
