[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]


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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.

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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 \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.
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    \1\ Ref Public Law 104-113 as amended by Public Law 107-107.
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    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.
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    \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.
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    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.
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    \4\ See https://rgl.faa.gov/.
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    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\
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    \5\ See https://www.faa.gov/aircraft/air_cert/design_approvals/small_airplanes/small_airplanes_regs/.
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    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 
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


