59400 Federal Register / Vol. 85, No. 184 / Tuesday, September 22, 2020 / Rules and Regulations 
1Ref Public Law 104–113 as amended by Public 
Law 107–107. 
2Ref Public Law 113–53. 
3See https://www.federalregister.gov/documents/ 
2016/12/30/2016-30246/revision-of-airworthiness- 
standards-for-normal-utility-acrobatic-and- commuter-category-airplanes. 
4See https://rgl.faa.gov/. to receive alerts when changes or 
additions occur in a docket folder. To subscribe: (1) Navigate to the docket folder NRC–2020–0166; (2) click the ‘‘Sign up for Email Alerts’’ link; and (3) enter your email address and select how frequently you would like to receive emails (daily, weekly, or monthly). 
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: 
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. 
■2. In § 72.214, Certificate of 
Compliance No. 1031 is revised to read 
as follows: 
§ 72.214 List of approved spent fuel 
storage casks. 
* * * * * 
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February 4, 2009, superseded by Initial 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. 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®. 
* * * * * 
Dated this September 4, 2020. 
For the Nuclear Regulatory Commission. 
Margaret M. Doane, Executive Director for Operations. 
[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 
[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: andrew.supinie@faa.gov. 
SUPPLEMENTARY INFORMATION : 
Background: Under the provisions of 
the National Technology Transfer and Advancement Act of 1995
1and 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,
2the 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 
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5See https://www.faa.gov/aircraft/air _cert/ 
design_ approvals/small_ airplanes/small_ airplanes_
regs/. 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 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 applica-
tion of temporary one-hand control forces exceeding those specified in Table 1, appropriate for the type of con-trol. The trimming controls shall not be adjusted during the maneuvers.’’ 
ASTM F3173/F3173M–18, 
Section 4.3.2.3.FAA Section 4.3.2.3 ‘‘With landing gear and flaps extended, power necessary to maintain level flight at 1.1 V
S0, 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 V
FEof the initial flap configuration prior to the flaps reaching their selected setting, power 
may be reduced after achieving 1.3 V FEof the initial flap configuration. The maneuver continues until the flaps 
reach the selected setting and the airplane achieves V FEof 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 V
S1, 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 4.7.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, appro-priate for the type of control, following an approach to land under the following conditions;’’ 
ASTM F3173/F3173M–18 
Section 5.3.1.3.FAA Section 5.3.1.3 ‘‘In a descent with idle power at a speed of 1.3 V
S0with landing gear extended and wing flaps in the landing po-
sition.’’ 
ASTM F3173/F3173M–18 
Section 9.3.4.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 speci-fied 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 
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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 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.’’ 
ASTM F3116/F3116M–18, 
Section X1.1.1.FAA Section X1.1.1 ‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compli-
ance 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 X2.1.1.FAA X2.1.1 
‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compli-
ance and can only be applied to level 1 and level 2 low speed airplanes.’’ 
ASTM F3116/F3116M–18, 
Section X3.1.1.FAA X3.1.1 ‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compli-
ance and can only be applied to level 1 and level 2 low speed airplanes.’’ 
ASTM F3116/F3116M–18, 
Section X4.1.1.FAA X4.1.1 ‘‘The methods provided in this appendix provide one possible means (but not the only possible means) of compli-
ance 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 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 ma-terials or material systems for which the physical and mechanical properties are well established.’’ 
ASTM F3115/F3115M–15, 
Section 6.1.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.’’ 
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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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 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 cri-teria; the method of defining an ATC applicable to this practice is defined in Specification F3061/F3061M.’’ 
ASTM F3230–17 Section 4 
Example.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.’’ 
ASTM F3230–17 Table 1 ..... FAA Table 1 
Column header ‘‘Airworthi-
ness Level’’.Column header ‘‘Aeroplane Certification Level’’. 
ASTM F3230–17 Table 3 ..... FAA Table 3 
Column header ‘‘Airworthi-
ness Level’’.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 cri-teria; the method of defining an ATC applicable to this practice is defined in Specification F3061/F3061M.’’ 
ASTM F3230–17 Section 4 
Example.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.’’ 
ASTM F3230–17 Table 1 ..... FAA Table 1 
Column header ‘‘Airworthi-
ness Level’’.Column header ‘‘Aeroplane Certification Level’’ 
ASTM F3230–17 Table 3 ..... FAA Table 3 
Column header ‘‘Airworthi-
ness Level’’.Column header ‘‘Aeroplane Certification Level’’ 
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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 aver-
age value: ‘‘100 volts/ meter’’.FAA Table 2 entry 400 to 700 Mhz frequency range field strength average value: ‘‘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 § 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., F3235–17e
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 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/. 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 
AGENCY : Federal Aviation 
Administration (FAA), DOT. 
ACTION : Final rule. 
SUMMARY : 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. 
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