Accepted Means of Compliance (MOC); Airworthiness Standards: Normal Category Airplanes, 46309-46319 [2024-11596]
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46309
Rules and Regulations
Federal Register
Vol. 89, No. 104
Wednesday, May 29, 2024
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. FAA–2024–0969]
Accepted Means of Compliance (MOC);
Airworthiness Standards: Normal
Category Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of availability (NOA).
AGENCY:
This document announces the
availability of ASTM International
(ASTM) consensus standards for use as
an FAA-accepted means of compliance
(MOC) to the applicable airworthiness
standards for normal category airplanes.
The FAA accepts ASTM F3264–23,
‘‘Standard Specification for Normal
Category Aeroplanes Certification,’’
with changes identified in this
document.
DATES: Acceptance of the means of
compliance is effective on May 29,
2024.
FOR FURTHER INFORMATION CONTACT:
Hieu Nguyen, Federal Aviation
Administration, Policy and Standards
Division, GA, Airplanes, Rotorcraft and
Emerging Aircraft Section, AIR–62B,
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SUMMARY:
VerDate Sep<11>2014
15:42 May 28, 2024
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901 Locust Street, Room 301, Kansas
City, Missouri 64106; telephone: (316)
946–4123; facsimile: (316) 946–4107;
email: hieu.nguyen@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 for use as a means of carrying
out its policy objectives where
appropriate.
Consistent with the Small Airplane
Revitalization Act of 2013, the FAA has
been working with industry and other
stakeholders through the ASTM F44
Committee on General Aviation Aircraft
to develop consensus standards as a
MOC in certificating small airplanes
under part 23.2
In part 23, amendment 23–64 (81 FR
96572), published on December 30,
2016,3 the final rule stated the FAA
would publish an NOA of those
consensus standards in the Federal
Register when the Administrator
accepts the consensus standards as an
acceptable MOC. The FAA reviewed the
published ASTM consensus standards
developed by the ASTM F44 Committee
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.
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on General Aviation Aircraft as the basis
for a MOC to 65 sections of part 23,
amendments 23–64 and 23–65. In some
cases, the Administrator found sections
of ASTM F3264–23, without changes,
are accepted as an MOC for the
airworthiness requirements of part 23,
amendments 23–64 and 23–65. In other
cases, the MOC, while based on ASTM
consensus standards, include additional
FAA provisions necessary to comply
with the airworthiness requirements of
part 23, amendments 23–64 and 23–65.
Part 23, amendment 23–64,
established airworthiness requirements
based on the safety requirements
outlined in amendment 23–63, except in
areas that address loss of control and
icing, where the FAA increased the
safety level. Depending on the details of
a design, the applicant may require use
of a different MOC beyond those
accepted by this NOA. For example,
novel airplane designs, such as
unmanned airplanes or vertical takeoff
and landing airplanes, may be outside
the scope of this NOA, and applicants
may need to propose alternative MOC
applicable to their designs accepted
under § 23.2010.
Means of Compliance Accepted
The FAA accepts only the revisions of
the standards referenced in ASTM
F3264–23, ‘‘Standard Specification for
Normal Category Aeroplanes
Certification,’’ as a means of compliance
for part 23, amendments 23–64 and 23–
65, with the changes identified in table
1. For ease of use, table 2 was added to
provide a side-by-side view, linking the
applicable part 23 regulation to the
ASTM F3264–23 section.
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TABLE 1—PART 23 ACCEPTED MOC BASED ON ASTM CONSENSUS STANDARDS 4 5
ASTM No. as identified in
F3264–23
ASTM document title
F2490–20 .......................
Standard Guide for Aircraft Electrical Load and Power Source Capacity Analysis.
Standard Specification for Systems
and Equipment in Aircraft.
F3061/F3061M–22b .......
F3062/F3062M–20 .........
F3063/F3063M–21 .........
F3064/F3064M–21 .........
F3065/F3065M–21a .......
F3066/F3066M–18 .........
F3082/F3082M–22 .........
F3083/F3083M–20a .......
F3093/F3093M–21 .........
F3114–21 .......................
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F3115/F3115M–23 .........
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Changes required for FAA acceptance 4
Standard Specification for Aircraft
Powerplant Installation.
Standard Specification for Aircraft
Fuel Storage and Delivery.
Standard Specification for Aircraft
Powerplant Control, Operation,
and Indication.
Standard Specification for Aircraft
Propeller System Installation.
Standard Specification for Aircraft
Powerplant Installation Hazard
Mitigation.
Standard Specification for Weights
and Centers of Gravity of Aircraft.
Standard Specification for Emergency Conditions, Occupant Safety and Accommodations.
Standard Specification for
Aeroelasticity Requirements.
Standard Specification for Structures.
Standard Specification for Structural
Durability for Small Aeroplanes.
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Additional information 5
None.
The tables defining applicability of requirements
in sections 4, 10, 13, and 17 are not accepted. Applicability will be determined by the Policy and Standards Division.
Replace 17.3.1.1 with the following:
(a) Each electrical or electronic system that performs a function, the failure of which would
prevent the continued safe flight and landing
of the airplane, must be designed, and installed such that—
(1) The function at the airplane level is not adversely affected during and after the time the
airplane is exposed to lightning; and
(2) The system recovers normal operation of
that function in a timely manner after the airplane is exposed to lightning unless the system’s recovery conflicts with other operational
or functional requirements of the system.
Replace 17.3.1.2 with the following:
(b) Each electrical and electronic system that
performs a function, the failure of which would
significantly reduce the capability of the airplane or the ability of the flight crew to respond to an adverse operating condition,
must be designed and installed such that the
system recovers normal operation of that
function in a timely manner after the airplane
is exposed to lightning.
Remove 17.3.1.3.
Replace 10.4.2, 10.4.3, 10.4.4 Level 1 with
Level 4.
None.
The tables defining applicability found in F3061/
F3061M–22b sections 4, 10, 13, and 17 are
not accepted. Applicability will be determined
by the Policy and Standards Division. Aircraft
certification levels are as defined in 14 CFR
23.2005.
F3061/F3061M–22b does not contain means for
showing compliance to § 23.2310, Buoyancy
for seaplanes and amphibians. If applying for
certification of a seaplane or amphibian, applicants may use the provisions of §§ 23.751,
23.755, and 23.757 at amendment 23–63 as
a means of complying with § 23.2310 or may
obtain FAA acceptance of a different MOC in
accordance with § 23.2010.
None.
None.
None.
None.
None.
Replace 4.1.6 with the following:
Powerplant and ESS mounts and supporting
structures must withstand 18.0 g forward for
powerplants and ESS installed behind and
above the seating compartment.
None.
None.
None ....................................................................
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If the applicant proposes to use F3115/
F3115M–20 sections 4.3 or 6.3.2, the Policy
and Standards Division will be involved as the
standard is applied during projects to review
the approach to determining similarity (F3115/
F3115M–20 section 4.3) and criteria defining
obvious damage (F3115/F3115M–20 section
6.3.2).
If the applicant proposes to use F3115/
F3115M–23 sections 4.1.3 or 4.3.3.2, the Policy and Standards Division will be involved as
the standard is applied during projects to review the approach to determining similarity
(F3115/F3115M–23 section 4.1.3) and criteria
defining obvious damage (F3115/F3115M–23
section 4.3.3.2).
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46311
TABLE 1—PART 23 ACCEPTED MOC BASED ON ASTM CONSENSUS STANDARDS 4 5—Continued
ASTM No. as identified in
F3264–23
F3116/F3116M–18e2 .....
Standard Specification for Design
Loads and Conditions.
F3117/F3117M–23a .......
Standard Specification for Crew
Interface in Aircraft.
Standard Specification for Ice Protection for General Aviation Aircraft.
Standard Specification for Aircraft
Handling Characteristics.
Standard Specification for Establishing Operating Limitations and
Information for Aeroplanes.
Standard Specification for Performance of Aircraft.
Standard Specification for LowSpeed Flight Characteristics of
Aircraft.
F3120/F3120M–20 .........
F3173/F3173M–21a .......
F3174/F3174M–21 .........
F3179/F3179M–22e1 .....
F3180/F3180M–21 .........
F3227/F3227M–22 .........
F3228–21 .......................
Standard Specification for Environmental Systems in Aircraft.
Standard Specification for Flight
Data and Voice Recording in
Small Aircraft.
None.
None.
None.
None.
The FAA does not universally accept all alternatives contained in F3180/F3180M–21. FAA
previously and continues to accept F3180/
F3180M–16.
None.
Applicants are encouraged to propose elements
of F3180/F3180M–21, or other means, for development of their project MOC to § 23.2150
in accordance with § 23.2010.
Remove: Table 1 .................................................
Aircraft Type Code compliance matrix table
found in F3228–21 are not accepted. Applicability will be determined by the Policy and
Standards Division.
Aircraft Type Code compliance matrix table
found in F3229/F3229M–17 is not accepted.
Applicability will be determined by the Policy
and Standards Division.
Aircraft Type Code compliance matrix table
found in F3230–21a is not accepted. Applicability will be determined by the Policy and
Standards Division.
Aircraft Type Code compliance matrix table
found in F3231/F3231M–23 is not accepted.
Applicability will be determined by the Policy
and Standards Division.
Standard Practice for Static Pressure System Tests in Small Aircraft.
Remove: Table 1 .................................................
F3230–21a .....................
Standard Practice for Safety Assessments of Systems and Equipment in Small Aircraft.
Remove: Table 1 .................................................
F3231/F3231M–23 .........
Standard Specification for Electrical
Systems for Aircraft with Combustion Engine Electrical Power Generation.
Standard Specification for Flight
Controls in Small Aircraft.
Standard Specification for Flight and
Navigation Instrumentation in Aircraft.
Remove: Table 1 .................................................
F3234/F3234M–21 .........
Standard Specification for Exterior
Lighting in Small Aircraft.
Remove: Table 1 .................................................
F3235–22 .......................
Standard Specification for Aircraft
Storage Batteries.
Remove: Section 4.2 ...........................................
F3233/F3233M–21 .........
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Additional information 5
Replace: Section 4.1.4 with: ‘‘Appendix X1
through Appendix X4 provides, within the limitations specified within the appendix, a simplified MOC 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.’’
Replace: Section X1.1.1 with: ‘‘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.’’
Replace: Section X2.1.1 with: ‘‘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.’’
Replace: Section X3.1.1 with: ‘‘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.’’
Replace: Section X4.1.1 with: ‘‘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.’’
None.
F3229/F3229M–17 .........
F3232/F3232M–20 .........
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Changes required for FAA acceptance 4
ASTM document title
None.
Remove: Table 1 .................................................
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Aircraft Type Code compliance matrix table
found in F3233/F3233M–21 is not accepted.
Applicability will be determined by the Policy
and Standards Division.
Aircraft Type Code compliance matrix table
found in F3234/F3234M–21 is not accepted.
Applicability will be determined by the Policy
and Standards Division.
If applying for certification of an airplane with installed lithium batteries, applicants may use
the guidance provided by RTCA DO–311A or
may obtain FAA acceptance of a different
MOC in accordance with § 23.2010.
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Federal Register / Vol. 89, No. 104 / Wednesday, May 29, 2024 / Rules and Regulations
TABLE 1—PART 23 ACCEPTED MOC BASED ON ASTM CONSENSUS STANDARDS 4 5—Continued
ASTM No. as identified in
F3264–23
ASTM document title
Changes required for FAA acceptance 4
Additional information 5
Remove: Table 1 .................................................
Aircraft Type Code compliance matrix table
found in F3235–22 is not accepted. Applicability will be determined by the Policy and
Standards Division.
Aircraft Type Code compliance matrix table
found in F3236–21a is not accepted. Applicability will be determined by the Policy and
Standards Division.
Applicants are encouraged to consider proposing F3239–22a for development of their
MOC for electric propulsion systems on a
project-by-project basis. Any MOC proposed
must establish a level of safety equivalent to
certified reciprocating and turbine propulsion
systems and receive acceptance by the FAA
in accordance with § 23.2010.
Other proposed probabilities will be considered
by the FAA on a case-by-case basis.
F3236–21a .....................
Standard Specification for High Intensity Radiated Field (HIRF) Protection in Small Aircraft.
Remove: Table 1 .................................................
F3239–22a .....................
Standard Specification for Aircraft
Electric Propulsion Systems.
The FAA does not universally accept F3239–
22a due to inexperience with the standard.
F3254–22 .......................
Standard Specification for Aircraft
Interaction of Systems and Structures.
F3309/F3309M–21 .........
Standard Practice for Simplified
Safety Assessment of Systems
and Equipment in Small Aircraft.
Standard Specification for Electrical
Systems for Aircraft with Electric
or Hybrid-Electric Propulsion.
Figures 2, 3, and 4 Replace: ‘‘Remote’’ with:
‘‘10¥5’’.
Replace: ‘‘Extremely Improbable’’ with: ‘‘10¥8’’
for Level 1, 2 and 3 airplanes and with
‘‘10¥9’’ for Level 4 airplanes’’.
None.
F3316/F3316M–19 .........
FAA does not universally accept F3316/
F3316M–19 due to inexperience with the
standard.
Remove: Table 1 .................................................
F3331–18 .......................
F3367–21a .....................
F3380–19 .......................
F3396/F3396M–20 .........
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F3397/F3397M–21 .........
F3408/F3408M–21 .........
F3432–20a .....................
F3498–21 .......................
VerDate Sep<11>2014
Standard Practice for Aircraft Water
Loads.
Standard Practice for Simplified
Methods for Addressing High-Intensity Radiated Fields (HIRF)
and Indirect Effects of Lightning
on Aircraft.
Standard Practice for Structural
Compliance of Very Light
Aeroplanes.
Standard Practice for Aircraft Simplified Loads Criteria.
Standard Practice for Aeroplane
Turbine Fuel System Hot Weather
Operations.
Standard Specification for Aircraft
Emergency Parachute Recovery
Systems.
Standard Practice for Powerplant Instruments.
Standard Practice for Developing
Simplified Fatigue Load Spectra.
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Applicants are encouraged to consider proposing F3316/F3316M–19 for development of
their MOC for electrical systems installed on
airplanes with electric or hybrid-electric propulsion systems on a project-by-project basis.
Applicants may obtain FAA acceptance of a
different MOC in accordance with § 23.2010.
Aircraft Type Code compliance matrix table
found in F3316/F3316M–19 is not accepted.
Applicability will be determined by the Policy
and Standards Division.
None.
Replace: paragraph 5.1.1 with: ‘‘Systems that
are part of the Type Certificated Engine must
be installed in accordance with the engine
manufacturer’s requirements. The minimum
HIRF and lightning qualification in accordance
with sections 8 and 9 of this ASTM practice
should be met at the aircraft level, except for
engine control systems in Level 1 and 2 airplanes which should meet the following:
HIRF: DO–160, section 20–R for both radiated
and conducted susceptibility.
Lightning: Utilize guidance in AC 33.28–3.
For metallic fuselage DO–160G, section 22–
A3J3L3 (shielded) and A3H3L3 (unshielded).
For composite fuselage DO–160G, section 22–
B3K3L3 (shielded) and B3H3L3 (unshielded).
Use of lower HIRF and lighting induced voltage
& current levels may be acceptable for electronic engine control systems if substantiated
at the airplane level (by test in the proposed
installation or similar) when exposed to external HIRF environment per AC 20–158 (latest
revision) and lightning per AC20–136 (latest
revision); using shielding and grounding of the
electronic engine control system and accessories in the given installation.’’
None.
None.
None.
None.
None.
None.
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46313
TABLE 1—PART 23 ACCEPTED MOC BASED ON ASTM CONSENSUS STANDARDS 4 5—Continued
ASTM No. as identified in
F3264–23
F3532–22 .......................
Changes required for FAA acceptance 4
ASTM document title
Standard Practice for Protection of
Aircraft Systems from Intentional
Unauthorized Electronic Interactions.
Additional information 5
None.
TABLE 2—SIDE-BY-SIDE VIEW OF PART 23 REGULATIONS AND ASTM F3264–23 SECTION(S)
Part 23 amendments 23–64 and 23–65
regulation(s)
ASTM F3264–23 section(s)1A 6
ASTM F3264–23 subsection(s)1A 7
Subpart B—Flight
§ 23.2100 Weight and center of gravity ..
5.1 Weight/Mass and Center of Gravity
§ 23.2105
§ 23.2110
§ 23.2115
§ 23.2120
§ 23.2125
§ 23.2130
§ 23.2135
5.2
5.3
5.4
5.5
5.6
5.7
5.8
Performance data ...................
Stall speed .............................
Takeoff performance ..............
Climb requirements ................
Climb information ...................
Landing ...................................
Controllability ..........................
Performance Data ............................
Stall Speed .......................................
Takeoff Performance .......................
Climb Requirements ........................
Climb Information .............................
Landing ............................................
Controllability ....................................
§ 23.2140 Trim ........................................
5.9 Trim ..................................................
§ 23.2145 Stability ...................................
5.10 Stability ...........................................
§ 23.2150 Stall characteristics, stall
warning, and spins.
§ 23.2155 Ground and water handling
characteristics.
§ 23.2160 Vibration, buffeting, and highspeed characteristics.
§ 23.2165 Performance and flight characteristics requirements for flight in
icing conditions.
5.11 Stall Characteristics, Stall Warning,
and Spins.
5.12 Ground and Water Handling Characteristics.
5.13 Vibration, Buffeting, and HighSpeed Characteristics.
5.14 Performance and Flight Characteristics Requirements for Flight in Icing
Conditions.
5.1.1 F3082/F3082M–22 Standard Specification for Weights and Centers of
Gravity of Aircraft
5.1.2 F3114–21 Standard Specification for Structures.
5.2.1 F3179/F3179M–22e1 Standard Specification for Performance of Aircraft.
5.3.1 F3179/F3179M–22e1 Standard Specification for Performance of Aircraft.
5.4.1 F3179/F3179M–22e1 Standard Specification for Performance of Aircraft.
5.5.1 F3179/F3179M–22e1 Standard Specification for Performance of Aircraft.
5.6.1 F3179/F3179M–22e1 Standard Specification for Performance of Aircraft.
5.7.1 F3179/F3179M–22e1 Standard Specification for Performance of Aircraft.
5.8.1 F3173/F3173M–21a Standard Specification for Aircraft Handling Characteristics.
5.9.1 F3173/F3173M–21a Standard Specification for Aircraft Handling Characteristics.
5.10.1 F3173/F3173M–21a Standard Specification for Aircraft Handling Characteristics.
5.11.1 F3180/F3180M–21 Standard Specification for Low-Speed Flight Characteristics of Aircraft.
5.12.1 F3173/F3173M–21a Standard Specification for Aircraft Handling Characteristics.
5.13.1 F3173/F3173M–21a Standard Specification for Aircraft Handling Characteristics.
5.14.1 F3120/F3120M–20 Standard Specification for Ice Protection for General
Aviation Aircraft.
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Subpart C—Structures
§ 23.2200 Structural design envelope ....
6.1 Structural Design Envelope .............
§ 23.2205 Interaction of systems and
structures.
§ 23.2210 Structural design loads ..........
6.2 Interaction of Systems and Structure.
6.3 Structural Design Loads ..................
§ 23.2215 Flight load conditions .............
6.4 Flight Load Conditions .....................
§ 23.2220 Ground and water load conditions.
6.5 Ground and Water Load Conditions
§ 23.2225 Component loading conditions
6.6 Component Loading Conditions ......
§ 23.2230 Limit and ultimate loads .........
6.7 Limit and Ultimate Loads .................
4 The MOC are intended for traditional part 23
airplanes, not for novel designs. Novel designs
require evaluation and possible modification of the
MOC.
5 You may find additional information on the
FAA Small Airplane Issues List (SAIL) here: https://
www.faa.gov/aircraft/air_cert/design_approvals/
small_airplanes/small_airplanes_regs/.
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6.1.1 F3116/F3116M–18e2 Standard Specification for Design Loads and Conditions
6.1.1.1 F3396/F3396M–20 Standard Practice for Aircraft Simplified Loads.
6.2.1 F3254–22 Standard Specification for Aircraft Interaction of Systems and
Structures.
6.3.1 F3116/F3116M–18e2 Standard Specification for Design Loads and Conditions
6.3.1.1 F3396/F3396M–20 Standard Practice for Aircraft Simplified Loads
6.3.2 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
6.4.1 F3116/F3116M–18e2 Standard Specification for Design Loads and Conditions
6.4.1.1 F3396/F3396M–20 Standard Practice for Aircraft Simplified Loads.
6.5.1 F3116/F3116M–18e2 Standard Specification for Design Loads and Conditions
6.5.1.1 F3331–18 Standard Practice for Aircraft Water Loads.
6.6.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
6.6.1.1 F3232/F3232M–20 Standard Specification for Flight Controls in Small
Aircraft
6.6.2 F3116/F3116M–18e2 Standard Specification for Design Loads and Conditions.
6.6.2.1 F3396/F3396M–20 Standard Practice for Aircraft Simplified Loads.
6.7.1 F3114–21 Standard Specification for Structures.
6.7.2 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
6 The ASTM F3264–23 section(s) provides a
means of compliance intended to be used on
projects for traditional part 23 airplanes, not for
novel designs. Novel designs require evaluation and
possible modification of the means of compliance.
7 Changes required for FAA acceptance and
additional information per table 1 still applies to
table 2. The FAA does not accept the Aircraft Type
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Code compliance matrix tables included in F3228–
21, F3229/F3229M–17, F3230–21a, F3231/F3231M–
23, F3233/F3233M–21, F3234/F3234M–21, F3235–
22, F3236–21a, and F3316/F3316M–19. The tables
defining applicability found in F3061/F3061M–22b
sections 4, 10, 13, and 17 are not accepted.
Applicability will be determined by the Policy and
Standards Division.
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TABLE 2—SIDE-BY-SIDE VIEW OF PART 23 REGULATIONS AND ASTM F3264–23 SECTION(S)—Continued
Part 23 amendments 23–64 and 23–65
regulation(s)
ASTM F3264–23 section(s)1A 6
ASTM F3264–23 subsection(s)1A 7
§ 23.2235 Structural strength ..................
6.8 Structural Strength ...........................
§ 23.2240 Structural durability ................
6.9 Structural Durability ..........................
§ 23.2245 Aeroelasticity ..........................
6.10 Aeroelasticity ..................................
§ 23.2250 Design and construction principles.
6.11 Design and Construction Principles
§ 23.2255 Protection of structure ............
6.12 Protection of Structure ...................
§ 23.2260 Materials and processes ........
6.13 Materials and Processes ...............
§ 23.2265 Special factors of safety .........
6.14 Special Factors of Safety ...............
§ 23.2270 Emergency conditions ............
6.15 Emergency Conditions ...................
6.8.1 F3114–21 Standard Specification for Structures.
6.8.2 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
6.9.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
6.9.2 F3066/F3066M –18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation
6.9.3 F3115/F3115M–23 Standard Specification for Structural Durability for
Small Aeroplanes.
6.9.3.1 F3380 –19 Standard Practice for Structural Compliance of Very Light
Aeroplanes
6.9.3.2 F3498–21 Standard Practice for Developing Simplified Fatigue Load
Spectra.
6.9.4 F3116/F3116M–18e2 Standard Specification for Design Loads and Conditions.
6.10.1 F3093/F3093M–21 Standard Specification for Aeroelasticity Requirements.
6.11.1 F3061/F3061M–22b Standard Specification for Systems and Equipment
in Small Aircraft.
6.11.1.1 F3232/F3232M–20 Standard Specification for Flight Controls in Small
Aircraft.
6.11.2 F3114–21 Standard Specification for Structures.
6.11.2.1 F3380–19 Standard Practice for Structural Compliance of Very Light
Aeroplanes.
6.11.3 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
6.12.1 F3061/F3061M–22b Standard Specification for Systems and Equipment
in Small Aircraft.
6.12.1.1 F3232/F3232M–20 Standard Specification for Flight Controls in Small
Aircraft.
6.12.2 F3114–21 Standard Specification for Structures.
6.12.2.1 F3380–19 Standard Practice for Structural Compliance of Very Light
Aeroplanes.
6.12.3 F3066/F3066M–18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation.
6.12.4 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
6.13.1 F3114–21 Standard Specification for Structures.
6.13.1.1 F3380–19 Standard Practice for Structural Compliance of Very Light
Aeroplanes.
6.13.2 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
6.14.1 F3061/F3061M–22b Standard Specification for Systems and Equipment
in Small Aircraft.
6.14.2 F3114–21 Standard Specification for Structures.
6.14.2.1 F3380 –19 Standard Practice for Structural Compliance of Very Light
Aeroplanes.
6.15.1 F3061/F3061M–22b Standard Specification for Systems and Equipment
in Small Aircraft.
6.15.1.1 F3232/F3232M–20 Standard Specification for Flight Controls in Small
Aircraft.
6.15.2 F3083/F3083M–20a Standard Specification for Emergency Conditions,
Occupant Safety and Accommodations.
6.15.3 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
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Subpart D—Design and Construction
§ 23.2300 Flight control systems ............
7.1 Flight Control Systems .....................
§ 23.2305 Landing gear systems ............
7.2 Landing Gear Systems ....................
§ 23.2310 Buoyancy for seaplanes and
amphibians.
§ 23.2315 Means of egress and emergency exits.
7.3 Buoyancy for Seaplanes and Amphibians.
7.4 Means of Egress and Emergency
Exits.
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7.1.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
7.1.1.1 F3232/F3232M–20 Standard Specification for Flight Controls in Small
Aircraft.
7.1.2 F3066/F3066M–18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation.
7.1.3 F3117/F3117M–23a Standard Specification for Crew Interface.
7.2.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
7.3.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
7.4.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
7.4.2 F3083/F3083M–20a Standard Specification for Emergency Conditions,
Occupant Safety and Accommodations.
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TABLE 2—SIDE-BY-SIDE VIEW OF PART 23 REGULATIONS AND ASTM F3264–23 SECTION(S)—Continued
Part 23 amendments 23–64 and 23–65
regulation(s)
ASTM F3264–23 section(s)1A 6
ASTM F3264–23 subsection(s)1A 7
§ 23.2320 Occupant physical environment.
7.5 Occupant Physical Environment ......
§ 23.2325 Fire protection ........................
7.6 Fire Protection ..................................
§ 23.2330 Fire protection in designated
fire zones and adjacent areas.
7.7 Fire Protection in Designated Fire
Zones and Adjacent Areas.
§ 23.2335 Lightning protection ................
7.8 Lightning Protection .........................
7.5.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
7.5.1.1 F3227/F3227M–22 Standard Specification for Environmental Systems in
Small Aircraft.
7.5.2 F3083/F3083M–20a Standard Specification for Emergency Conditions,
Occupant Safety and Accommodations
7.5.3 F3114–21 Standard Specification for Structures.
7.5.4 F3117/F3117M–23a Standard Specification for Crew Interface in Aircraft.
7.6.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft
7.6.1.1 F3231/F3231M–23 Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation.
7.6.1.2 F3234/F3234M–21 Standard Specification for Exterior Lighting in Small
Aircraft.
7.6.1.3 F3316/F3316M–19 Standard Specification for Electrical Systems for Aircraft with Electric or Hybrid-Electric Propulsion.
7.6.2 F3066/F3066M–18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation.
7.6.3 F3083/F3083M–20a Standard Specification for Emergency Conditions,
Occupant Safety and Accommodations.
7.6.4 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
7.7.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
7.7.1.1 F3231/F3231M–23 Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation.
7.7.2 F3066/F3066M–18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation.
7.7.3 F3114–21 Standard Specification for Structures.
7.8.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
lotter on DSK11XQN23PROD with RULES1
Subpart E–Powerplant
§ 23.2400 Powerplant installation ...........
8.1 Powerplant Installation .....................
§ 23.2405 Automatic power or thrust
control systems.
8.2 Power or Thrust Control Systems ...
§ 23.2410 Powerplant installation hazard
assessment.
8.3 Powerplant Installation Hazard Assessment.
§ 23.2415 Powerplant ice protection .......
8.4 Powerplant Installation Ice Protection.
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8.1.1 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation.
8.1.2 F3063/F3063M–21 Standard Specification for Aircraft Fuel and Energy
Storage and Delivery.
8.1.3 F3064/F3064M–21 Standard Specification for Aircraft Powerplant Control,
Operation, and Indication.
8.1.3.1 F3432–20a Standard Practice for Powerplant Instruments.
8.1.4 F3065/F3065M–21a Standard Specification for Aircraft Propeller System
Installation.
8.1.5 F3066/F3066M–18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation.
8.1.6 F3239–22a Standard Specification for Aircraft Electric Propulsion Systems.
8.2.1 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation.
8.2.2 F3064/F3064M–21 Standard Specification for Aircraft Powerplant Control,
Operation, and Indication.
8.2.2.1 F3432–20a Standard Practice for Powerplant Instruments.
8.2.3 F3065/F3065M–21a Standard Specification for Aircraft Propeller System
Installation.
8.2.4 F3117/F3117M–23a Standard Specification for Crew Interface.
8.3.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
8.3.2 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation
8.3.3 F3063/F3063M–21 Standard Specification for Aircraft Fuel and Energy
Storage and Delivery.
8.3.4 F3064/F3064M–21 Standard Specification for Aircraft Powerplant Control,
Operation, and Indication.
8.3.4.1 F3432–20a Standard Practice for Powerplant Instruments.
8.3.5 F3065/F3065M–21a Standard Specification for Aircraft Propeller System
Installation.
8.3.6 F3066/F3066M–18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation.
8.3.7 F3117/F3117M–23a Standard Specification for Crew Interface in Aircraft.
8.3.8 F3239–22a Standard Specification for Aircraft Electric Propulsion Systems.
8.4.1 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation.
8.4.2 F3063/F3063M–21 Standard Specification for Aircraft Fuel and Energy
Storage and Delivery.
8.4.3 F3066/F3066M–18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation.
8.4.4 F3239–22a Standard Specification for Aircraft Electric Propulsion Systems.
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Federal Register / Vol. 89, No. 104 / Wednesday, May 29, 2024 / Rules and Regulations
TABLE 2—SIDE-BY-SIDE VIEW OF PART 23 REGULATIONS AND ASTM F3264–23 SECTION(S)—Continued
Part 23 amendments 23–64 and 23–65
regulation(s)
ASTM F3264–23 section(s)1A 6
ASTM F3264–23 subsection(s)1A 7
§ 23.2420 Reversing systems .................
8.5 Reversing Systems ..........................
§ 23.2425 Powerplant operational characteristics.
8.6 Powerplant Operational Characteristics.
§ 23.2430 Fuel systems ..........................
8.7 Fuel and Energy Storage and Distribution Systems.
§ 23.2435 Powerplant induction and exhaust systems.
8.8 Powerplant Induction, Exhaust, and
Support Systems.
§ 23.2440 Powerplant fire protection ......
8.9 Powerplant Installation Fire Protection.
8.5.1 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation.
8.5.2 F3065/F3065M–21a Standard Specification for Aircraft Propeller System
Installation.
8.5.3 F3239–22a Standard Specification for Aircraft Electric Propulsion Systems
8.6.1 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation.
8.6.2 F3064/F3064M–21 Standard Specification for Aircraft Powerplant Control,
Operation, and Indication.
8.6.2.1 F3432–20a Standard Practice for Powerplant Instruments.
8.6.3 F3065/F3065M–21a Standard Specification for Aircraft Propeller System
Installation
8.6.4 F3066/F3066M–18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation.
8.6.5 F3117/F3117M–23a Standard Specification for Crew Interface in Aircraft
8.6.6 F3239–22a Standard Specification for Aircraft Electric Propulsion Systems.
8.7.1 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation.
8.7.2 F3063/F3063M–21 Standard Specification for Aircraft Fuel and Energy
Storage and Delivery.
8.7.2.1 F3397/F3397M–21 Standard Practice for Aeroplane Turbine Fuel System Hot Weather Operations
8.7.3 F3064/F3064M–21 Standard Specification for Aircraft Powerplant Control,
Operation, and Indication.
8.7.3.1 F3432–20a Standard Practice for Powerplant Instruments.
8.7.4 F3066/F3066M–18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation.
8.7.5 F3114–21 Standard Specification for Structures.
8.7.6 F3239–22a Standard Specification for Aircraft Electric Propulsion Systems.
8.8.1 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation.
8.8.2 F3239–22a Standard Specification for Aircraft Electric Propulsion Systems.
8.9.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft
8.9.2 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation
8.9.3 F3063/F3063M–21 Standard Specification for Aircraft Fuel an Energy
Storage and Delivery.
8.9.4 F3064/F3064M–21 Standard Specification for Aircraft Powerplant Control,
Operation, and Indication.
8.9.4.1 F3432–20a Standard Practice for Powerplant Instruments.
8.9.5 F3066/F3066M–18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation.
8.9.6 F3239–22a Standard Specification for Aircraft Electric Propulsion Systems.
Subpart F–Equipment
lotter on DSK11XQN23PROD with RULES1
§ 23.2500 Airplane level systems requirements.
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9.1 Systems and Equipment Function—
Requirements.
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9.1.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
9.1.1.1 F3231/F3231M–23 Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation.
9.1.1.1(a) F3235–22 Standard Specification for Aircraft Storage Batteries.
9.1.1.2 F3232/F3232M–20 Standard Specification for Flight Controls in Small
Aircraft.
9.1.1.3 F3233/F3233M–21 Standard Specification for Flight and Navigation Instrumentation in Aircraft.
9.1.1.3(a) F3229/F3229M–17 Standard Practice for Static Pressure System
Tests in Small Aircraft.
9.1.1.4 F3316/F3316M–19 Standard Specification for Electrical Systems for Aircraft with Electric or Hybrid-Electric Propulsion.
9.1.2 F3064/F3064M–21 Standard Specification for Aircraft Powerplant Control,
Operation, and Indication.
9.1.2.1 F3432–20a Standard Practice for Powerplant Instruments.
9.1.3 F3066/F3066M–18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation.
9.1.4 F3117/F3117M–23a Standard Specification for Crew Interface in Aircraft.
9.1.5 F3120/F3120M–20 Standard Specification for Ice Protection for General
Aviation Aircraft.
9.1.6 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
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Federal Register / Vol. 89, No. 104 / Wednesday, May 29, 2024 / Rules and Regulations
46317
lotter on DSK11XQN23PROD with RULES1
TABLE 2—SIDE-BY-SIDE VIEW OF PART 23 REGULATIONS AND ASTM F3264–23 SECTION(S)—Continued
Part 23 amendments 23–64 and 23–65
regulation(s)
ASTM F3264–23 section(s)1A 6
ASTM F3264–23 subsection(s)1A 7
§ 23.2505 Function and installation ........
9.2 Equipment Function and Installation
Requirements.
§ 23.2510 Equipment, systems, and installations.
9.3 Equipment, Systems, and Installation.
§ 23.2515 Electrical and electronic system lightning protection.
9.4 Electrical and Electronic System
Lightning Protection.
§ 23.2520 High-intensity Radiated Fields
(HIRF) protection.
9.5 High Intensity Radiated Fields
(HIRF) Protection.
§ 23.2525 System power generation,
storage, and distribution.
9.6 System Power Generation, Storage,
and Distribution.
§ 23.2530 External and cockpit lighting ..
9.7 External and Cockpit Lighting ..........
§ 23.2535 Safety equipment ...................
9.8 Safety Equipment .............................
§ 23.2540 Flight in icing conditions .........
9.9 Flight in Icing Conditions .................
§ 23.2545 Pressurized systems elements.
9.10 Pressurized System Elements .......
9.2.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
9.2.1.1 F3231/F3231M–23 Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation.
9.2.1.1(a) F3235–22 Standard Specification for Aircraft Storage Batteries.
9.2.1.2 F3232/F3232M–20 Standard Specification for Flight Controls in Small
Aircraft.
9.2.1.3 F3233/F3233M–21 Standard Specification for Flight and Navigation Instrumentation in Aircraft.
9.2.1.4 F3316/F3316M–19 Standard Specification for Electrical Systems for Aircraft with Electric or Hybrid-Electric Propulsion.
9.2.2 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
9.3.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
9.3.1.1 F3230–21a Standard Practice for Safety Assessments of Systems and
Equipment in Small Aircraft.
9.3.1.2 F3233/F3233M–21 Standard Specification for Flight and Navigation Instrumentation in Aircraft.
9.3.1.3 F3227/F3227M–22 Standard Specification for Environmental Systems in
Small Aircraft.
9.3.1.4 F3309/F3309M–21 Standard Practice for Simplified Safety Assessment
of Systems and Equipment in Small Aircraft.
9.3.1.5 F3532–22 Standard Practice for Protection of Aircraft Systems from Intentional Unauthorized Electronic Interactions.
9.3.2 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
9.4.1 F3061/F3061M–22b22b2322b Standard Specification for Systems and
Equipment in Small Aircraft.
9.4.1.1 F3367–21a Standard Practice for Simplified Methods for Addressing
High-Intensity Radiated Fields (HIRF) and Indirect Effects of Lightning on Aircraft.
9.5.1 F3061/F3061M–22b22b2322b Standard Specification for Systems and
Equipment in Small Aircraft.
9.5.1.1 F3236–21a Standard Specification for High Intensity Radiated Field
(HIRF) Protection in Small Aircraft.
9.5.1.2 F3367–21a Standard Practice for Simplified Methods for Addressing
High-Intensity Radiated Fields (HIRF) and Indirect Effects of Lightning on Aircraft.
9.6.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
9.6.1.1 F3231/F3231M–23 Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation.
9.6.1.1(a) F2490–20 Standard Guide for Aircraft Electrical Load and Power
Source Capacity Analysis.
9.6.1.2 F3233/F3233M–21 Standard Specification for Flight and Navigation Instrumentation in Aircraft.
9.6.1.3 F3316/F3316M–19 Standard Specification for Electrical Systems for Aircraft with Electric or Hybrid-Electric Propulsion.
9.6.1.3(a) F2490–20 Standard Guide for Aircraft Electrical Load and Power
Source Capacity Analysis.
9.6.2 F3117/F3117M–23a Standard Specification for Crew Interface in Aircraft.
9.6.3 F3120/F3120M–20 Standard Specification for Ice Protection for General
Aviation Aircraft.
9.7.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
9.7.1.1 F3233/F3233M–21 Standard Specification for Flight and Navigation Instrumentation in Aircraft.
9.7.1.2 F3234/F3234M–21 Standard Specification for Exterior Lighting in Small
Aircraft.
9.7.2 F3117/F3117M–23a Standard Specification for Crew Interface in Aircraft.
9.7.3 F3120/F3120M–20 Standard Specification for Ice Protection for General
Aviation Aircraft.
9.8.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
9.8.2 F3083/F3083M–20a Standard Specification for Emergency Conditions,
Occupant Safety and Accommodations.
9.8.3 F3117/F3117M–23a Standard Specification for Crew Interface.
9.9.1 F3061/F3061M–22b Standard Specification for Systems and Equipment in
Small Aircraft.
9.9.1.1 F3233/F3233M–21 Standard Specification for Flight and Navigation Instrumentation in Aircraft.
9.9.2 F3120/F3120M–20 Standard Specification for Ice Protection for General
Aviation Aircraft.
9.10.1 F3061/F3061M–22b Standard Specification for Systems and Equipment
in Small Aircraft.
9.10.1.1 F3229/F3229M–17 Standard Practice for Static Pressure System Tests
in Small Aircraft.
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Federal Register / Vol. 89, No. 104 / Wednesday, May 29, 2024 / Rules and Regulations
TABLE 2—SIDE-BY-SIDE VIEW OF PART 23 REGULATIONS AND ASTM F3264–23 SECTION(S)—Continued
Part 23 amendments 23–64 and 23–65
regulation(s)
§ 23.2550 Equipment containing highenergy rotors.
ASTM F3264–23 section(s)1A 6
9.11 Equipment Containing High-Energy
Rotors.
ASTM F3264–23 subsection(s)1A 7
9.11.1 F3061/F3061M–22b Standard Specification for Systems and Equipment
in Small Aircraft.
Subpart G—Flight crew Interface and Other Information
§ 23.2600 Flightcrew interface ................
10.1 Flight crew Compartment Interface
§ 23.2605 Installation and operation .......
10.2 Installation and Operation Information.
§ 23.2610 Instrument markings, control
markings, and placards.
10.3 Instrument Markings, Control
Markings, and Placards.
§ 23.2615 Flight, navigation, and powerplant instruments.
10.4 Flight, Navigation, and Powerplant
Instruments.
§ 23.2620 Airplane flight manual ............
5.15 Operating Limitations .....................
lotter on DSK11XQN23PROD with RULES1
10.5 Airplane Flight Manual ...................
The MOC accepted by this NOA
provide one means, but not the only
means of complying with part 23
regulatory requirements. Applicants
who desire to use an MOC reflected by
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10.1.1 F3061/F3061M–22b Standard Specification for Systems and Equipment
in Small Aircraft.
10.1.1.1 F3232/F3232M–20 Standard Specification for Flight Controls in Small
Aircraft.
10.1.2 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation.
10.1.3 F3063/F3063M–21 Standard Specification for Aircraft Fuel and Energy
Storage and Delivery.
10.1.4 F3064/F3064M–21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication.
10.1.4.1 F3432–20a Standard Practice for Powerplant Instruments.
10.1.5 F3114–21 Standard Specification for Structures.
10.1.6 F3117/F3117M–23a Standard Specification for Crew Interface in Aircraft.
10.1.7 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
10.2.1 F3061/F3061M–22b Standard Specification for Systems and Equipment
in Small Aircraft.
10.2.1.1 F3227/F3227M–22 Standard Specification for Environmental Systems
in Small Aircraft.
10.2.1.2 F3231/F3231M–23 Standard Specification for Electrical Systems for
Aircraft with Combustion Engine Electrical Power Generation.
10.2.1.3 F3232/F3232M–20 Standard Specification for Flight Controls in Small
Aircraft.
10.2.1.4 F3233/F3233M–21 Standard Specification for Flight and Navigation Instrumentation in Aircraft.
10.2.2 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation.
10.2.3 F3063/F3063M–21 Standard Specification for Aircraft Fuel and Energy
Storage and Delivery.
10.2.4 F3064/F3064M–21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication.
10.2.4.1 F3432–20a Standard Practice for Powerplant Instruments.
10.2.5 F3117/F3117M–23a Standard Specification for Crew Interface in Aircraft.
10.2.6 F3120/F3120M–20 Standard Specification for Ice Protection for General
Aviation Aircraft.
10.2.7 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
10.3.1 F3061/F3061M–22b Standard Specification for Systems and Equipment
in Small Aircraft.
10.3.2 F3063/F3063M–21 Standard Specification for Aircraft Fuel and Energy
Storage and Delivery.
10.3.3 F3117/F3117M–23a Standard Specification for Crew Interface in Aircraft.
10.3.4 F3120/F3120M–20 Standard Specification for Ice Protection for General
Aviation Aircraft.
10.3.5 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
10.4.1 F3061/F3061M–22b Standard Specification for Systems and Equipment
in Small Aircraft.
10.4.2 F3062/F3062M–20 Standard Specification for Aircraft Powerplant Installation
10.4.3 F3064/F3064M–21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication.
10.4.3.1 F3432–20a Standard Practice for Powerplant Instruments.
10.4.4 F3117/F3117M–23a Standard Specification for Crew Interface in Aircraft.
5.15.1 F3174/F3174M–21 Standard Specification for Establishing Operating
Limitations and Information for Aeroplanes.
5.15.2 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
10.5.1 F3117/F3117M–23a Standard Specification for Crew Interface in Aircraft.
10.5.2 F3174/F3174M–21 Standard Specification for Establishing Operating
Limitations and Information for Aeroplanes.
10.5.3 F3120/F3120M–20 Standard Specification for Ice Protection for General
Aviation Aircraft.
10.5.4 F3408/F3408M–21 Standard Specification for Aircraft Emergency Parachute Recovery Systems.
other revisions to ASTM standards not
previously accepted may seek guidance
and possible acceptance from the FAA
for the use of those MOC on a case-bycase basis. Applicants may propose an
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
alternative MOC for FAA review and
possible acceptance.
E:\FR\FM\29MYR1.SGM
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Federal Register / Vol. 89, No. 104 / Wednesday, May 29, 2024 / Rules and Regulations
Editorial, Reapproval, Revision, or
Withdrawal
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. When an ASTM standard is
reapproved, that reapproval is denoted
by the year in parentheses (e.g., F2427–
05a (2013)). This date indicates the
completion of a review cycle with no
technical changes made to the standard.
In addition, ASTM issues editorial
changes denoted by a superscript
epsilon in the standard designation (e.g.,
F3235–17ε1). This epsilon indicates
information was corrected, and it did
not change the meaning or intent of a
standard. Since reapprovals and
editorial changes do not change the
technical content of standards, then any
standard FAA-accepted by this NOA
that is later reapproved or editorially
changed by ASTM, is also considered
FAA-accepted and without the need for
an updated NOA.
ASTM revises a standard to make
changes to its technical content.
Revisions are identified by a hyphen
after the document number, which is
followed by the last two numbers of the
year of acceptance or of last revision. If
the standard is revised again during the
same year, this is indicated by adding
an ‘‘a’’ for the second revision, ‘‘b’’ for
the third revision, etc. Since revisions
change the technical content, revisions
to consensus standards serving as the
basis for an MOC accepted by this NOA
will not be automatically accepted and
will require further FAA acceptance for
the revisions to be an accepted MOC.
lotter on DSK11XQN23PROD with RULES1
Availability
ASTM F3264–23, ‘‘Standard
Specification for Normal Category
Aeroplanes Certification,’’ is available
online at https://www.astm.org/
READINGLIBRARY/. ASTM 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
online or by contacting ASTM by
telephone: (610) 832–9585; facsimile:
(610) 832–9555; or through email:
service@astm.org. 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 by telephone: (610) 832–9804 or
through email: jkoury@astm.org.
VerDate Sep<11>2014
15:42 May 28, 2024
Jkt 262001
Issued in Kansas City, Missouri, on May
21, 2024.
Patrick Mullen,
Manager, Technical Policy Branch, Policy and
Standards Division, Aircraft Certification
Service.
[FR Doc. 2024–11596 Filed 5–28–24; 8:45 am]
BILLING CODE 4910–13–P
46319
New Jersey Avenue SE, Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aviation Safety Engineer, FAA,
1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 206–
231–3225; email dan.rodina@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
Federal Aviation Administration
part 39 to supersede AD 2021–21–02,
Amendment 39–21762 (86 FR 62898,
14 CFR Part 39
November 15, 2021) (AD 2021–21–02).
AD 2021–21–02 applied to certain
[Docket No. FAA–2024–0221; Project
Identifier AD–2023–01233–T; Amendment
Airbus SAS Model A318, A319, A320,
39–22762; AD 2024–11–01]
A321, A330–200, A330–200 Freighter,
A330–300, A330–800, A330–900, A340–
RIN 2120–AA64
200, A340–300, A340–500, A340–600,
and A380–800 series airplanes. The
Airworthiness Directives; Airbus SAS
NPRM published in the Federal
Airplanes
Register on February 9, 2024 (89 FR
AGENCY: Federal Aviation
9074). The NPRM was prompted by a
Administration (FAA), DOT.
determination that the on-wing
ACTION: Final rule.
preservation procedures originally
provided in that AD did not ensure the
SUMMARY: The FAA is superseding
expected preservation of the battery
Airworthiness Directive (AD) 2021–21–
capacity. In the NPRM, the FAA
02, which applied to certain Airbus SAS proposed to add Model A300 series
Model A318, A319, A320, A321, A330– airplanes; Model A300 B4–600, B4–
200, A330–200 Freighter, A330–300,
600R, and F4–600R series airplanes, and
A330–800, A330–900, A340–200, A340– Model A300 C4–605R Variant F
300, A340–500, A340–600, and A380–
airplanes (collectively called Model
800 series airplanes. AD 2021–21–02
A300–600 series airplanes); Model A310
required replacing certain parts
series airplanes; and Model A350–941
manufacturer approval (PMA) Ni-Cd
and –1041 airplanes to the applicability.
batteries with serviceable Ni-Cd
The FAA proposed that the superseding
batteries or maintaining the electrical
AD would retain none of the
storage capacity of those PMA Ni-Cd
requirements of AD 2021–21–02. The
batteries during airplane storage or
FAA proposed to require replacing each
parking. This AD was prompted by a
affected part with a serviceable part
determination that the on-wing
before release to service of an airplane
preservation procedures originally
after a storage or parking period, as
provided in that AD did not ensure the
applicable. The FAA is issuing this AD
expected preservation of the battery
to address reduced battery endurance
capacity. This AD adds airplanes to the
performance, which could possibly
applicability and requires replacing
result in failure to supply the minimum
each affected part with a serviceable
essential electrical power during
part before release to service of an
abnormal or emergency conditions.
airplane after a storage or parking
Discussion of Final Airworthiness
period, as applicable. The FAA is
Directive
issuing this AD to address the unsafe
condition on these products.
Comments
DATES: This AD is effective July 3, 2024.
The FAA received comments from Air
ADDRESSES:
Line Pilots Association, International
AD Docket: You may examine the AD (ALPA), who supported the SNPRM/
docket at regulations.gov under Docket
NPRM without change.
No. FAA–2024–0221; or in person at
The FAA received additional
Docket Operations between 9 a.m. and
comments from American Airlines (AA)
5 p.m., Monday through Friday, except
and United Airlines (UAL). The
Federal holidays. The AD docket
following presents the comments
contains this final rule, any comments
received on the NPRM and the FAA’s
received, and other information. The
response to each comment.
address for Docket Operations is U.S.
Request for Clarification of Terms
Department of Transportation, Docket
AAL requested clarification of
Operations, M–30, West Building
‘‘parking and storage’’ as intended by
Ground Floor, Room W12–140, 1200
DEPARTMENT OF TRANSPORTATION
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
E:\FR\FM\29MYR1.SGM
29MYR1
]]>Agencies
[Federal Register Volume 89, Number 104 (Wednesday, May 29, 2024)]
[Rules and Regulations]
[Pages 46309-46319]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-11596]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 89, No. 104 / Wednesday, May 29, 2024 / Rules
and Regulations
[[Page 46309]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. FAA-2024-0969]
Accepted Means of Compliance (MOC); Airworthiness Standards:
Normal Category Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of availability (NOA).
-----------------------------------------------------------------------
SUMMARY: This document announces the availability of ASTM International
(ASTM) consensus standards for use as an FAA-accepted means of
compliance (MOC) to the applicable airworthiness standards for normal
category airplanes. The FAA accepts ASTM F3264-23, ``Standard
Specification for Normal Category Aeroplanes Certification,'' with
changes identified in this document.
DATES: Acceptance of the means of compliance is effective on May 29,
2024.
FOR FURTHER INFORMATION CONTACT: Hieu Nguyen, Federal Aviation
Administration, Policy and Standards Division, GA, Airplanes,
Rotorcraft and Emerging Aircraft Section, AIR-62B, 901 Locust Street,
Room 301, Kansas City, Missouri 64106; telephone: (316) 946-4123;
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 for use 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, the
FAA has been working with industry and other stakeholders through the
ASTM F44 Committee on General Aviation Aircraft to develop consensus
standards as a MOC in certificating small airplanes under part 23.\2\
---------------------------------------------------------------------------
\2\ Ref Public Law 113-53.
---------------------------------------------------------------------------
In part 23, amendment 23-64 (81 FR 96572), published on December
30, 2016,\3\ the final rule stated the FAA would publish an NOA of
those consensus standards in the Federal Register when the
Administrator accepts the consensus standards as an acceptable MOC. The
FAA reviewed the published ASTM consensus standards developed by the
ASTM F44 Committee on General Aviation Aircraft as the basis for a MOC
to 65 sections of part 23, amendments 23-64 and 23-65. In some cases,
the Administrator found sections of ASTM F3264-23, without changes, are
accepted as an MOC for the airworthiness requirements of part 23,
amendments 23-64 and 23-65. In other cases, the MOC, while based on
ASTM consensus standards, include additional FAA provisions necessary
to comply with the airworthiness requirements of part 23, amendments
23-64 and 23-65.
---------------------------------------------------------------------------
\3\ See https://www.federalregister.gov/documents/2016/12/30/2016-30246/revision-of-airworthiness-standards-for-normal-utility-acrobatic-and-commuter-category-airplanes.
---------------------------------------------------------------------------
Part 23, amendment 23-64, established airworthiness requirements
based on the safety requirements outlined in amendment 23-63, except in
areas that address loss of control and icing, where the FAA increased
the safety level. Depending on the details of a design, the applicant
may require use of a different MOC beyond those accepted by this NOA.
For example, novel airplane designs, such as unmanned airplanes or
vertical takeoff and landing airplanes, may be outside the scope of
this NOA, and applicants may need to propose alternative MOC applicable
to their designs accepted under Sec. 23.2010.
Means of Compliance Accepted
The FAA accepts only the revisions of the standards referenced in
ASTM F3264-23, ``Standard Specification for Normal Category Aeroplanes
Certification,'' as a means of compliance for part 23, amendments 23-64
and 23-65, with the changes identified in table 1. For ease of use,
table 2 was added to provide a side-by-side view, linking the
applicable part 23 regulation to the ASTM F3264-23 section.
[[Page 46310]]
Table 1--Part 23 Accepted MOC Based on ASTM Consensus Standards \4\ \5\
----------------------------------------------------------------------------------------------------------------
Changes required for FAA Additional information
ASTM No. as identified in F3264-23 ASTM document title acceptance \4\ \5\
----------------------------------------------------------------------------------------------------------------
F2490-20.......................... Standard Guide for None......................
Aircraft Electrical
Load and Power
Source Capacity
Analysis.
F3061/F3061M-22b.................. Standard The tables defining The tables defining
Specification for applicability of applicability found in
Systems and requirements in sections F3061/F3061M-22b
Equipment in 4, 10, 13, and 17 are not sections 4, 10, 13, and
Aircraft. accepted. Applicability 17 are not accepted.
will be determined by the Applicability will be
Policy and Standards determined by the Policy
Division. and Standards Division.
Replace 17.3.1.1 with the Aircraft certification
following:. levels are as defined in
(a) Each electrical or 14 CFR 23.2005.
electronic system that F3061/F3061M-22b does not
performs a function, the contain means for
failure of which would showing compliance to
prevent the continued Sec. 23.2310, Buoyancy
safe flight and landing for seaplanes and
of the airplane, must be amphibians. If applying
designed, and installed for certification of a
such that--. seaplane or amphibian,
(1) The function at the applicants may use the
airplane level is not provisions of Sec. Sec.
adversely affected during 23.751, 23.755, and
and after the time the 23.757 at amendment 23-
airplane is exposed to 63 as a means of
lightning; and. complying with Sec.
(2) The system recovers 23.2310 or may obtain
normal operation of that FAA acceptance of a
function in a timely different MOC in
manner after the airplane accordance with Sec.
is exposed to lightning 23.2010.
unless the system's
recovery conflicts with
other operational or
functional requirements
of the system.
Replace 17.3.1.2 with the
following:
(b) Each electrical and
electronic system that
performs a function, the
failure of which would
significantly reduce the
capability of the
airplane or the ability
of the flight crew to
respond to an adverse
operating condition, must
be designed and installed
such that the system
recovers normal operation
of that function in a
timely manner after the
airplane is exposed to
lightning..
Remove 17.3.1.3...........
Replace 10.4.2, 10.4.3,
10.4.4 Level 1 with Level
4..
F3062/F3062M-20................... Standard None......................
Specification for
Aircraft Powerplant
Installation.
F3063/F3063M-21................... Standard None......................
Specification for
Aircraft Fuel
Storage and Delivery.
F3064/F3064M-21................... Standard None......................
Specification for
Aircraft Powerplant
Control, Operation,
and Indication.
F3065/F3065M-21a.................. Standard None......................
Specification for
Aircraft Propeller
System Installation.
F3066/F3066M-18................... Standard None......................
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
F3082/F3082M-22................... Standard None......................
Specification for
Weights and Centers
of Gravity of
Aircraft.
F3083/F3083M-20a.................. Standard Replace 4.1.6 with the
Specification for following:
Emergency Powerplant and ESS mounts
Conditions, Occupant and supporting structures
Safety and must withstand 18.0 g
Accommodations. forward for powerplants
and ESS installed behind
and above the seating
compartment.
F3093/F3093M-21................... Standard None......................
Specification for
Aeroelasticity
Requirements.
F3114-21.......................... Standard None......................
Specification for
Structures.
F3115/F3115M-23................... Standard None...................... If the applicant proposes
Specification for to use F3115/F3115M-20
Structural sections 4.3 or 6.3.2,
Durability for Small the Policy and Standards
Aeroplanes. Division will be
involved as the standard
is applied during
projects to review the
approach to determining
similarity (F3115/F3115M-
20 section 4.3) and
criteria defining
obvious damage (F3115/
F3115M-20 section
6.3.2).
If the applicant proposes
to use F3115/F3115M-23
sections 4.1.3 or
4.3.3.2, the Policy and
Standards Division will
be involved as the
standard is applied
during projects to
review the approach to
determining similarity
(F3115/F3115M-23 section
4.1.3) and criteria
defining obvious damage
(F3115/F3115M-23 section
4.3.3.2).
[[Page 46311]]
F3116/F3116M-18e2................. Standard Replace: Section 4.1.4
Specification for with: ``Appendix X1
Design Loads and through Appendix X4
Conditions. provides, within the
limitations specified
within the appendix, a
simplified MOC 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.''
Replace: Section X1.1.1
with: ``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.''
Replace: Section X2.1.1
with: ``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.''
Replace: Section X3.1.1
with: ``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.''
Replace: Section X4.1.1
with: ``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.''
F3117/F3117M-23a.................. Standard None......................
Specification for
Crew Interface in
Aircraft.
F3120/F3120M-20................... Standard None......................
Specification for
Ice Protection for
General Aviation
Aircraft.
F3173/F3173M-21a.................. Standard None......................
Specification for
Aircraft Handling
Characteristics.
F3174/F3174M-21................... Standard None......................
Specification for
Establishing
Operating
Limitations and
Information for
Aeroplanes.
F3179/F3179M-22e1................. Standard None......................
Specification for
Performance of
Aircraft.
F3180/F3180M-21................... Standard The FAA does not Applicants are encouraged
Specification for universally accept all to propose elements of
Low-Speed Flight alternatives contained in F3180/F3180M-21, or
Characteristics of F3180/F3180M-21. FAA other means, for
Aircraft. previously and continues development of their
to accept F3180/F3180M-16. project MOC to Sec.
23.2150 in accordance
with Sec. 23.2010.
F3227/F3227M-22................... Standard None......................
Specification for
Environmental
Systems in Aircraft.
F3228-21.......................... Standard Remove: Table 1........... Aircraft Type Code
Specification for compliance matrix table
Flight Data and found in F3228-21 are
Voice Recording in not accepted.
Small Aircraft. Applicability will be
determined by the Policy
and Standards Division.
F3229/F3229M-17................... Standard Practice for Remove: Table 1........... Aircraft Type Code
Static Pressure compliance matrix table
System Tests in found in F3229/F3229M-17
Small Aircraft. is not accepted.
Applicability will be
determined by the Policy
and Standards Division.
F3230-21a......................... Standard Practice for Remove: Table 1........... Aircraft Type Code
Safety Assessments compliance matrix table
of Systems and found in F3230-21a is
Equipment in Small not accepted.
Aircraft. Applicability will be
determined by the Policy
and Standards Division.
F3231/F3231M-23................... Standard Remove: Table 1........... Aircraft Type Code
Specification for compliance matrix table
Electrical Systems found in F3231/F3231M-23
for Aircraft with is not accepted.
Combustion Engine Applicability will be
Electrical Power determined by the Policy
Generation. and Standards Division.
F3232/F3232M-20................... Standard None......................
Specification for
Flight Controls in
Small Aircraft.
F3233/F3233M-21................... Standard Remove: Table 1........... Aircraft Type Code
Specification for compliance matrix table
Flight and found in F3233/F3233M-21
Navigation is not accepted.
Instrumentation in Applicability will be
Aircraft. determined by the Policy
and Standards Division.
F3234/F3234M-21................... Standard Remove: Table 1........... Aircraft Type Code
Specification for compliance matrix table
Exterior Lighting in found in F3234/F3234M-21
Small Aircraft. is not accepted.
Applicability will be
determined by the Policy
and Standards Division.
F3235-22.......................... Standard Remove: Section 4.2....... If applying for
Specification for certification of an
Aircraft Storage airplane with installed
Batteries. lithium batteries,
applicants may use the
guidance provided by
RTCA DO-311A or may
obtain FAA acceptance of
a different MOC in
accordance with Sec.
23.2010.
[[Page 46312]]
Remove: Table 1........... Aircraft Type Code
compliance matrix table
found in F3235-22 is not
accepted. Applicability
will be determined by
the Policy and Standards
Division.
F3236-21a......................... Standard Remove: Table 1........... Aircraft Type Code
Specification for compliance matrix table
High Intensity found in F3236-21a is
Radiated Field not accepted.
(HIRF) Protection in Applicability will be
Small Aircraft. determined by the Policy
and Standards Division.
F3239-22a......................... Standard The FAA does not Applicants are encouraged
Specification for universally accept F3239- to consider proposing
Aircraft Electric 22a due to inexperience F3239-22a for
Propulsion Systems. with the standard. development of their MOC
for electric propulsion
systems on a project-by-
project basis. Any MOC
proposed must establish
a level of safety
equivalent to certified
reciprocating and
turbine propulsion
systems and receive
acceptance by the FAA in
accordance with Sec.
23.2010.
F3254-22.......................... Standard Figures 2, 3, and 4 Other proposed
Specification for Replace: ``Remote'' with: probabilities will be
Aircraft Interaction ``10-\5\''. considered by the FAA on
of Systems and Replace: ``Extremely a case-by-case basis.
Structures. Improbable'' with: ``10-
\8\'' for Level 1, 2 and
3 airplanes and with ``10-
\9\'' for Level 4
airplanes''.
F3309/F3309M-21................... Standard Practice for None......................
Simplified Safety
Assessment of
Systems and
Equipment in Small
Aircraft.
F3316/F3316M-19................... Standard FAA does not universally Applicants are encouraged
Specification for accept F3316/F3316M-19 to consider proposing
Electrical Systems due to inexperience with F3316/F3316M-19 for
for Aircraft with the standard. development of their MOC
Electric or Hybrid- for electrical systems
Electric Propulsion. installed on airplanes
with electric or hybrid-
electric propulsion
systems on a project-by-
project basis.
Applicants may obtain
FAA acceptance of a
different MOC in
accordance with Sec.
23.2010.
Remove: Table 1........... Aircraft Type Code
compliance matrix table
found in F3316/F3316M-19
is not accepted.
Applicability will be
determined by the Policy
and Standards Division.
F3331-18.......................... Standard Practice for None......................
Aircraft Water Loads.
F3367-21a......................... Standard Practice for Replace: paragraph 5.1.1
Simplified Methods with: ``Systems that are
for Addressing High- part of the Type
Intensity Radiated Certificated Engine must
Fields (HIRF) and be installed in
Indirect Effects of accordance with the
Lightning on engine manufacturer's
Aircraft. requirements. The minimum
HIRF and lightning
qualification in
accordance with sections
8 and 9 of this ASTM
practice should be met at
the aircraft level,
except for engine control
systems in Level 1 and 2
airplanes which should
meet the following:
HIRF: DO-160, section 20-R
for both radiated and
conducted susceptibility.
Lightning: Utilize
guidance in AC 33.28-3..
For metallic fuselage DO- .........................
160G, section 22-A3J3L3
(shielded) and A3H3L3
(unshielded).
For composite fuselage DO-
160G, section 22-B3K3L3
(shielded) and B3H3L3
(unshielded).
Use of lower HIRF and .........................
lighting induced voltage
& current levels may be
acceptable for electronic
engine control systems if
substantiated at the
airplane level (by test
in the proposed
installation or similar)
when exposed to external
HIRF environment per AC
20-158 (latest revision)
and lightning per AC20-
136 (latest revision);
using shielding and
grounding of the
electronic engine control
system and accessories in
the given installation.''
F3380-19.......................... Standard Practice for None......................
Structural
Compliance of Very
Light Aeroplanes.
F3396/F3396M-20................... Standard Practice for None......................
Aircraft Simplified
Loads Criteria.
F3397/F3397M-21................... Standard Practice for None......................
Aeroplane Turbine
Fuel System Hot
Weather Operations.
F3408/F3408M-21................... Standard None......................
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
F3432-20a......................... Standard Practice for None......................
Powerplant
Instruments.
F3498-21.......................... Standard Practice for None......................
Developing
Simplified Fatigue
Load Spectra.
[[Page 46313]]
F3532-22.......................... Standard Practice for None......................
Protection of
Aircraft Systems
from Intentional
Unauthorized
Electronic
Interactions.
----------------------------------------------------------------------------------------------------------------
---------------------------------------------------------------------------
\4\ The MOC are intended for traditional part 23 airplanes, not
for novel designs. Novel designs require evaluation and possible
modification of the MOC.
\5\ You may find additional information on the FAA Small
Airplane Issues List (SAIL) here: https://www.faa.gov/aircraft/air_cert/design_approvals/small_airplanes/small_airplanes_regs/.
\6\ The ASTM F3264-23 section(s) provides a means of compliance
intended to be used on projects for traditional part 23 airplanes,
not for novel designs. Novel designs require evaluation and possible
modification of the means of compliance.
\7\ Changes required for FAA acceptance and additional
information per table 1 still applies to table 2. The FAA does not
accept the Aircraft Type Code compliance matrix tables included in
F3228-21, F3229/F3229M-17, F3230-21a, F3231/F3231M-23, F3233/F3233M-
21, F3234/F3234M-21, F3235-22, F3236-21a, and F3316/F3316M-19. The
tables defining applicability found in F3061/F3061M-22b sections 4,
10, 13, and 17 are not accepted. Applicability will be determined by
the Policy and Standards Division.
Table 2--Side-by-Side View of Part 23 Regulations and ASTM F3264-23
Section(s)
------------------------------------------------------------------------
Part 23 amendments 23-64 and ASTM F3264-23 ASTM F3264-23
23-65 regulation(s) section(s)1A \6\ subsection(s)1A \7\
------------------------------------------------------------------------
Subpart B--Flight
------------------------------------------------------------------------
Sec. 23.2100 Weight and 5.1 Weight/Mass 5.1.1 F3082/F3082M-22
center of gravity. and Center of Standard
Gravity. Specification for
Weights and Centers
of Gravity of
Aircraft
5.1.2 F3114-21
Standard
Specification for
Structures.
Sec. 23.2105 Performance 5.2 Performance 5.2.1 F3179/F3179M-
data. Data. 22e1 Standard
Specification for
Performance of
Aircraft.
Sec. 23.2110 Stall speed.... 5.3 Stall Speed.. 5.3.1 F3179/F3179M-
22e1 Standard
Specification for
Performance of
Aircraft.
Sec. 23.2115 Takeoff 5.4 Takeoff 5.4.1 F3179/F3179M-
performance. Performance. 22e1 Standard
Specification for
Performance of
Aircraft.
Sec. 23.2120 Climb 5.5 Climb 5.5.1 F3179/F3179M-
requirements. Requirements. 22e1 Standard
Specification for
Performance of
Aircraft.
Sec. 23.2125 Climb 5.6 Climb 5.6.1 F3179/F3179M-
information. Information. 22e1 Standard
Specification for
Performance of
Aircraft.
Sec. 23.2130 Landing........ 5.7 Landing...... 5.7.1 F3179/F3179M-
22e1 Standard
Specification for
Performance of
Aircraft.
Sec. 23.2135 Controllability 5.8 5.8.1 F3173/F3173M-
Controllability. 21a Standard
Specification for
Aircraft Handling
Characteristics.
Sec. 23.2140 Trim........... 5.9 Trim......... 5.9.1 F3173/F3173M-
21a Standard
Specification for
Aircraft Handling
Characteristics.
Sec. 23.2145 Stability...... 5.10 Stability... 5.10.1 F3173/F3173M-
21a Standard
Specification for
Aircraft Handling
Characteristics.
Sec. 23.2150 Stall 5.11 Stall 5.11.1 F3180/F3180M-
characteristics, stall Characteristics, 21 Standard
warning, and spins. Stall Warning, Specification for
and Spins. Low-Speed Flight
Characteristics of
Aircraft.
Sec. 23.2155 Ground and 5.12 Ground and 5.12.1 F3173/F3173M-
water handling Water Handling 21a Standard
characteristics. Characteristics. Specification for
Aircraft Handling
Characteristics.
Sec. 23.2160 Vibration, 5.13 Vibration, 5.13.1 F3173/F3173M-
buffeting, and high-speed Buffeting, and 21a Standard
characteristics. High-Speed Specification for
Characteristics. Aircraft Handling
Characteristics.
Sec. 23.2165 Performance and 5.14 Performance 5.14.1 F3120/F3120M-
flight characteristics and Flight 20 Standard
requirements for flight in Characteristics Specification for
icing conditions. Requirements for Ice Protection for
Flight in Icing General Aviation
Conditions. Aircraft.
------------------------------------------------------------------------
Subpart C--Structures
------------------------------------------------------------------------
Sec. 23.2200 Structural 6.1 Structural 6.1.1 F3116/F3116M-
design envelope. Design Envelope. 18e2 Standard
Specification for
Design Loads and
Conditions
6.1.1.1 F3396/F3396M-
20 Standard Practice
for Aircraft
Simplified Loads.
Sec. 23.2205 Interaction of 6.2 Interaction 6.2.1 F3254-22
systems and structures. of Systems and Standard
Structure. Specification for
Aircraft Interaction
of Systems and
Structures.
Sec. 23.2210 Structural 6.3 Structural 6.3.1 F3116/F3116M-
design loads. Design Loads. 18e2 Standard
Specification for
Design Loads and
Conditions
6.3.1.1 F3396/F3396M-
20 Standard Practice
for Aircraft
Simplified Loads
6.3.2 F3408/F3408M-21
Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
Sec. 23.2215 Flight load 6.4 Flight Load 6.4.1 F3116/F3116M-
conditions. Conditions. 18e2 Standard
Specification for
Design Loads and
Conditions
6.4.1.1 F3396/F3396M-
20 Standard Practice
for Aircraft
Simplified Loads.
Sec. 23.2220 Ground and 6.5 Ground and 6.5.1 F3116/F3116M-
water load conditions. Water Load 18e2 Standard
Conditions. Specification for
Design Loads and
Conditions
6.5.1.1 F3331-18
Standard Practice
for Aircraft Water
Loads.
Sec. 23.2225 Component 6.6 Component 6.6.1 F3061/F3061M-
loading conditions. Loading 22b Standard
Conditions. Specification for
Systems and
Equipment in Small
Aircraft.
6.6.1.1 F3232/F3232M-
20 Standard
Specification for
Flight Controls in
Small Aircraft
6.6.2 F3116/F3116M-
18e2 Standard
Specification for
Design Loads and
Conditions.
6.6.2.1 F3396/F3396M-
20 Standard Practice
for Aircraft
Simplified Loads.
Sec. 23.2230 Limit and 6.7 Limit and 6.7.1 F3114-21
ultimate loads. Ultimate Loads. Standard
Specification for
Structures.
6.7.2 F3408/F3408M-21
Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
[[Page 46314]]
Sec. 23.2235 Structural 6.8 Structural 6.8.1 F3114-21
strength. Strength. Standard
Specification for
Structures.
6.8.2 F3408/F3408M-21
Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
Sec. 23.2240 Structural 6.9 Structural 6.9.1 F3061/F3061M-
durability. Durability. 22b Standard
Specification for
Systems and
Equipment in Small
Aircraft.
6.9.2 F3066/F3066M -
18 Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation
6.9.3 F3115/F3115M-23
Standard
Specification for
Structural
Durability for Small
Aeroplanes.
6.9.3.1 F3380 -19
Standard Practice
for Structural
Compliance of Very
Light Aeroplanes
6.9.3.2 F3498-21
Standard Practice
for Developing
Simplified Fatigue
Load Spectra.
6.9.4 F3116/F3116M-
18e2 Standard
Specification for
Design Loads and
Conditions.
Sec. 23.2245 Aeroelasticity. 6.10 6.10.1 F3093/F3093M-
Aeroelasticity. 21 Standard
Specification for
Aeroelasticity
Requirements.
Sec. 23.2250 Design and 6.11 Design and 6.11.1 F3061/F3061M-
construction principles. Construction 22b Standard
Principles. Specification for
Systems and
Equipment in Small
Aircraft.
6.11.1.1 F3232/F3232M-
20 Standard
Specification for
Flight Controls in
Small Aircraft.
6.11.2 F3114-21
Standard
Specification for
Structures.
6.11.2.1 F3380-19
Standard Practice
for Structural
Compliance of Very
Light Aeroplanes.
6.11.3 F3408/F3408M-
21 Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
Sec. 23.2255 Protection of 6.12 Protection 6.12.1 F3061/F3061M-
structure. of Structure. 22b Standard
Specification for
Systems and
Equipment in Small
Aircraft.
6.12.1.1 F3232/F3232M-
20 Standard
Specification for
Flight Controls in
Small Aircraft.
6.12.2 F3114-21
Standard
Specification for
Structures.
6.12.2.1 F3380-19
Standard Practice
for Structural
Compliance of Very
Light Aeroplanes.
6.12.3 F3066/F3066M-
18 Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
6.12.4 F3408/F3408M-
21 Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
Sec. 23.2260 Materials and 6.13 Materials 6.13.1 F3114-21
processes. and Processes. Standard
Specification for
Structures.
6.13.1.1 F3380-19
Standard Practice
for Structural
Compliance of Very
Light Aeroplanes.
6.13.2 F3408/F3408M-
21 Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
Sec. 23.2265 Special factors 6.14 Special 6.14.1 F3061/F3061M-
of safety. Factors of 22b Standard
Safety. Specification for
Systems and
Equipment in Small
Aircraft.
6.14.2 F3114-21
Standard
Specification for
Structures.
6.14.2.1 F3380 -19
Standard Practice
for Structural
Compliance of Very
Light Aeroplanes.
Sec. 23.2270 Emergency 6.15 Emergency 6.15.1 F3061/F3061M-
conditions. Conditions. 22b Standard
Specification for
Systems and
Equipment in Small
Aircraft.
6.15.1.1 F3232/F3232M-
20 Standard
Specification for
Flight Controls in
Small Aircraft.
6.15.2 F3083/F3083M-
20a Standard
Specification for
Emergency
Conditions, Occupant
Safety and
Accommodations.
6.15.3 F3408/F3408M-
21 Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
------------------------------------------------------------------------
Subpart D--Design and Construction
------------------------------------------------------------------------
Sec. 23.2300 Flight control 7.1 Flight 7.1.1 F3061/F3061M-
systems. Control Systems. 22b Standard
Specification for
Systems and
Equipment in Small
Aircraft.
7.1.1.1 F3232/F3232M-
20 Standard
Specification for
Flight Controls in
Small Aircraft.
7.1.2 F3066/F3066M-18
Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
7.1.3 F3117/F3117M-
23a Standard
Specification for
Crew Interface.
Sec. 23.2305 Landing gear 7.2 Landing Gear 7.2.1 F3061/F3061M-
systems. Systems. 22b Standard
Specification for
Systems and
Equipment in Small
Aircraft.
Sec. 23.2310 Buoyancy for 7.3 Buoyancy for 7.3.1 F3061/F3061M-
seaplanes and amphibians. Seaplanes and 22b Standard
Amphibians. Specification for
Systems and
Equipment in Small
Aircraft.
Sec. 23.2315 Means of egress 7.4 Means of 7.4.1 F3061/F3061M-
and emergency exits. Egress and 22b Standard
Emergency Exits. Specification for
Systems and
Equipment in Small
Aircraft.
7.4.2 F3083/F3083M-
20a Standard
Specification for
Emergency
Conditions, Occupant
Safety and
Accommodations.
[[Page 46315]]
Sec. 23.2320 Occupant 7.5 Occupant 7.5.1 F3061/F3061M-
physical environment. Physical 22b Standard
Environment. Specification for
Systems and
Equipment in Small
Aircraft.
7.5.1.1 F3227/F3227M-
22 Standard
Specification for
Environmental
Systems in Small
Aircraft.
7.5.2 F3083/F3083M-
20a Standard
Specification for
Emergency
Conditions, Occupant
Safety and
Accommodations
7.5.3 F3114-21
Standard
Specification for
Structures.
7.5.4 F3117/F3117M-
23a Standard
Specification for
Crew Interface in
Aircraft.
Sec. 23.2325 Fire protection 7.6 Fire 7.6.1 F3061/F3061M-
Protection. 22b Standard
Specification for
Systems and
Equipment in Small
Aircraft
7.6.1.1 F3231/F3231M-
23 Standard
Specification for
Electrical Systems
for Aircraft with
Combustion Engine
Electrical Power
Generation.
7.6.1.2 F3234/F3234M-
21 Standard
Specification for
Exterior Lighting in
Small Aircraft.
7.6.1.3 F3316/F3316M-
19 Standard
Specification for
Electrical Systems
for Aircraft with
Electric or Hybrid-
Electric Propulsion.
7.6.2 F3066/F3066M-18
Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
7.6.3 F3083/F3083M-
20a Standard
Specification for
Emergency
Conditions, Occupant
Safety and
Accommodations.
7.6.4 F3408/F3408M-21
Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
Sec. 23.2330 Fire protection 7.7 Fire 7.7.1 F3061/F3061M-
in designated fire zones and Protection in 22b Standard
adjacent areas. Designated Fire Specification for
Zones and Systems and
Adjacent Areas. Equipment in Small
Aircraft.
7.7.1.1 F3231/F3231M-
23 Standard
Specification for
Electrical Systems
for Aircraft with
Combustion Engine
Electrical Power
Generation.
7.7.2 F3066/F3066M-18
Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
7.7.3 F3114-21
Standard
Specification for
Structures.
Sec. 23.2335 Lightning 7.8 Lightning 7.8.1 F3061/F3061M-
protection. Protection. 22b Standard
Specification for
Systems and
Equipment in Small
Aircraft.
------------------------------------------------------------------------
Subpart E-Powerplant
------------------------------------------------------------------------
Sec. 23.2400 Powerplant 8.1 Powerplant 8.1.1 F3062/F3062M-20
installation. Installation. Standard
Specification for
Aircraft Powerplant
Installation.
8.1.2 F3063/F3063M-21
Standard
Specification for
Aircraft Fuel and
Energy Storage and
Delivery.
8.1.3 F3064/F3064M-21
Standard
Specification for
Aircraft Powerplant
Control, Operation,
and Indication.
8.1.3.1 F3432-20a
Standard Practice
for Powerplant
Instruments.
8.1.4 F3065/F3065M-
21a Standard
Specification for
Aircraft Propeller
System Installation.
8.1.5 F3066/F3066M-18
Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
8.1.6 F3239-22a
Standard
Specification for
Aircraft Electric
Propulsion Systems.
Sec. 23.2405 Automatic power 8.2 Power or 8.2.1 F3062/F3062M-20
or thrust control systems. Thrust Control Standard
Systems. Specification for
Aircraft Powerplant
Installation.
8.2.2 F3064/F3064M-21
Standard
Specification for
Aircraft Powerplant
Control, Operation,
and Indication.
8.2.2.1 F3432-20a
Standard Practice
for Powerplant
Instruments.
8.2.3 F3065/F3065M-
21a Standard
Specification for
Aircraft Propeller
System Installation.
8.2.4 F3117/F3117M-
23a Standard
Specification for
Crew Interface.
Sec. 23.2410 Powerplant 8.3 Powerplant 8.3.1 F3061/F3061M-
installation hazard Installation 22b Standard
assessment. Hazard Specification for
Assessment. Systems and
Equipment in Small
Aircraft.
8.3.2 F3062/F3062M-20
Standard
Specification for
Aircraft Powerplant
Installation
8.3.3 F3063/F3063M-21
Standard
Specification for
Aircraft Fuel and
Energy Storage and
Delivery.
8.3.4 F3064/F3064M-21
Standard
Specification for
Aircraft Powerplant
Control, Operation,
and Indication.
8.3.4.1 F3432-20a
Standard Practice
for Powerplant
Instruments.
8.3.5 F3065/F3065M-
21a Standard
Specification for
Aircraft Propeller
System Installation.
8.3.6 F3066/F3066M-18
Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
8.3.7 F3117/F3117M-
23a Standard
Specification for
Crew Interface in
Aircraft.
8.3.8 F3239-22a
Standard
Specification for
Aircraft Electric
Propulsion Systems.
Sec. 23.2415 Powerplant ice 8.4 Powerplant 8.4.1 F3062/F3062M-20
protection. Installation Ice Standard
Protection. Specification for
Aircraft Powerplant
Installation.
8.4.2 F3063/F3063M-21
Standard
Specification for
Aircraft Fuel and
Energy Storage and
Delivery.
8.4.3 F3066/F3066M-18
Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
8.4.4 F3239-22a
Standard
Specification for
Aircraft Electric
Propulsion Systems.
[[Page 46316]]
Sec. 23.2420 Reversing 8.5 Reversing 8.5.1 F3062/F3062M-20
systems. Systems. Standard
Specification for
Aircraft Powerplant
Installation.
8.5.2 F3065/F3065M-
21a Standard
Specification for
Aircraft Propeller
System Installation.
8.5.3 F3239-22a
Standard
Specification for
Aircraft Electric
Propulsion Systems
Sec. 23.2425 Powerplant 8.6 Powerplant 8.6.1 F3062/F3062M-20
operational characteristics. Operational Standard
Characteristics. Specification for
Aircraft Powerplant
Installation.
8.6.2 F3064/F3064M-21
Standard
Specification for
Aircraft Powerplant
Control, Operation,
and Indication.
8.6.2.1 F3432-20a
Standard Practice
for Powerplant
Instruments.
8.6.3 F3065/F3065M-
21a Standard
Specification for
Aircraft Propeller
System Installation
8.6.4 F3066/F3066M-18
Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
8.6.5 F3117/F3117M-
23a Standard
Specification for
Crew Interface in
Aircraft
8.6.6 F3239-22a
Standard
Specification for
Aircraft Electric
Propulsion Systems.
Sec. 23.2430 Fuel systems... 8.7 Fuel and 8.7.1 F3062/F3062M-20
Energy Storage Standard
and Distribution Specification for
Systems. Aircraft Powerplant
Installation.
8.7.2 F3063/F3063M-21
Standard
Specification for
Aircraft Fuel and
Energy Storage and
Delivery.
8.7.2.1 F3397/F3397M-
21 Standard Practice
for Aeroplane
Turbine Fuel System
Hot Weather
Operations
8.7.3 F3064/F3064M-21
Standard
Specification for
Aircraft Powerplant
Control, Operation,
and Indication.
8.7.3.1 F3432-20a
Standard Practice
for Powerplant
Instruments.
8.7.4 F3066/F3066M-18
Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
8.7.5 F3114-21
Standard
Specification for
Structures.
8.7.6 F3239-22a
Standard
Specification for
Aircraft Electric
Propulsion Systems.
Sec. 23.2435 Powerplant 8.8 Powerplant 8.8.1 F3062/F3062M-20
induction and exhaust systems. Induction, Standard
Exhaust, and Specification for
Support Systems. Aircraft Powerplant
Installation.
8.8.2 F3239-22a
Standard
Specification for
Aircraft Electric
Propulsion Systems.
Sec. 23.2440 Powerplant fire 8.9 Powerplant 8.9.1 F3061/F3061M-
protection. Installation 22b Standard
Fire Protection. Specification for
Systems and
Equipment in Small
Aircraft
8.9.2 F3062/F3062M-20
Standard
Specification for
Aircraft Powerplant
Installation
8.9.3 F3063/F3063M-21
Standard
Specification for
Aircraft Fuel an
Energy Storage and
Delivery.
8.9.4 F3064/F3064M-21
Standard
Specification for
Aircraft Powerplant
Control, Operation,
and Indication.
8.9.4.1 F3432-20a
Standard Practice
for Powerplant
Instruments.
8.9.5 F3066/F3066M-18
Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
8.9.6 F3239-22a
Standard
Specification for
Aircraft Electric
Propulsion Systems.
------------------------------------------------------------------------
Subpart F-Equipment
------------------------------------------------------------------------
Sec. 23.2500 Airplane level 9.1 Systems and 9.1.1 F3061/F3061M-
systems requirements. Equipment 22b Standard
Function--Requir Specification for
ements. Systems and
Equipment in Small
Aircraft.
9.1.1.1 F3231/F3231M-
23 Standard
Specification for
Electrical Systems
for Aircraft with
Combustion Engine
Electrical Power
Generation.
9.1.1.1(a) F3235-22
Standard
Specification for
Aircraft Storage
Batteries.
9.1.1.2 F3232/F3232M-
20 Standard
Specification for
Flight Controls in
Small Aircraft.
9.1.1.3 F3233/F3233M-
21 Standard
Specification for
Flight and
Navigation
Instrumentation in
Aircraft.
9.1.1.3(a) F3229/
F3229M-17 Standard
Practice for Static
Pressure System
Tests in Small
Aircraft.
9.1.1.4 F3316/F3316M-
19 Standard
Specification for
Electrical Systems
for Aircraft with
Electric or Hybrid-
Electric Propulsion.
9.1.2 F3064/F3064M-21
Standard
Specification for
Aircraft Powerplant
Control, Operation,
and Indication.
9.1.2.1 F3432-20a
Standard Practice
for Powerplant
Instruments.
9.1.3 F3066/F3066M-18
Standard
Specification for
Aircraft Powerplant
Installation Hazard
Mitigation.
9.1.4 F3117/F3117M-
23a Standard
Specification for
Crew Interface in
Aircraft.
9.1.5 F3120/F3120M-20
Standard
Specification for
Ice Protection for
General Aviation
Aircraft.
9.1.6 F3408/F3408M-21
Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
[[Page 46317]]
Sec. 23.2505 Function and 9.2 Equipment 9.2.1 F3061/F3061M-
installation. Function and 22b Standard
Installation Specification for
Requirements. Systems and
Equipment in Small
Aircraft.
9.2.1.1 F3231/F3231M-
23 Standard
Specification for
Electrical Systems
for Aircraft with
Combustion Engine
Electrical Power
Generation.
9.2.1.1(a) F3235-22
Standard
Specification for
Aircraft Storage
Batteries.
9.2.1.2 F3232/F3232M-
20 Standard
Specification for
Flight Controls in
Small Aircraft.
9.2.1.3 F3233/F3233M-
21 Standard
Specification for
Flight and
Navigation
Instrumentation in
Aircraft.
9.2.1.4 F3316/F3316M-
19 Standard
Specification for
Electrical Systems
for Aircraft with
Electric or Hybrid-
Electric Propulsion.
9.2.2 F3408/F3408M-21
Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
Sec. 23.2510 Equipment, 9.3 Equipment, 9.3.1 F3061/F3061M-
systems, and installations. Systems, and 22b Standard
Installation. Specification for
Systems and
Equipment in Small
Aircraft.
9.3.1.1 F3230-21a
Standard Practice
for Safety
Assessments of
Systems and
Equipment in Small
Aircraft.
9.3.1.2 F3233/F3233M-
21 Standard
Specification for
Flight and
Navigation
Instrumentation in
Aircraft.
9.3.1.3 F3227/F3227M-
22 Standard
Specification for
Environmental
Systems in Small
Aircraft.
9.3.1.4 F3309/F3309M-
21 Standard Practice
for Simplified
Safety Assessment of
Systems and
Equipment in Small
Aircraft.
9.3.1.5 F3532-22
Standard Practice
for Protection of
Aircraft Systems
from Intentional
Unauthorized
Electronic
Interactions.
9.3.2 F3408/F3408M-21
Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
Sec. 23.2515 Electrical and 9.4 Electrical 9.4.1 F3061/F3061M-
electronic system lightning and Electronic 22b22b2322b Standard
protection. System Lightning Specification for
Protection. Systems and
Equipment in Small
Aircraft.
9.4.1.1 F3367-21a
Standard Practice
for Simplified
Methods for
Addressing High-
Intensity Radiated
Fields (HIRF) and
Indirect Effects of
Lightning on
Aircraft.
Sec. 23.2520 High-intensity 9.5 High 9.5.1 F3061/F3061M-
Radiated Fields (HIRF) Intensity 22b22b2322b Standard
protection. Radiated Fields Specification for
(HIRF) Systems and
Protection. Equipment in Small
Aircraft.
9.5.1.1 F3236-21a
Standard
Specification for
High Intensity
Radiated Field
(HIRF) Protection in
Small Aircraft.
9.5.1.2 F3367-21a
Standard Practice
for Simplified
Methods for
Addressing High-
Intensity Radiated
Fields (HIRF) and
Indirect Effects of
Lightning on
Aircraft.
Sec. 23.2525 System power 9.6 System Power 9.6.1 F3061/F3061M-
generation, storage, and Generation, 22b Standard
distribution. Storage, and Specification for
Distribution. Systems and
Equipment in Small
Aircraft.
9.6.1.1 F3231/F3231M-
23 Standard
Specification for
Electrical Systems
for Aircraft with
Combustion Engine
Electrical Power
Generation.
9.6.1.1(a) F2490-20
Standard Guide for
Aircraft Electrical
Load and Power
Source Capacity
Analysis.
9.6.1.2 F3233/F3233M-
21 Standard
Specification for
Flight and
Navigation
Instrumentation in
Aircraft.
9.6.1.3 F3316/F3316M-
19 Standard
Specification for
Electrical Systems
for Aircraft with
Electric or Hybrid-
Electric Propulsion.
9.6.1.3(a) F2490-20
Standard Guide for
Aircraft Electrical
Load and Power
Source Capacity
Analysis.
9.6.2 F3117/F3117M-
23a Standard
Specification for
Crew Interface in
Aircraft.
9.6.3 F3120/F3120M-20
Standard
Specification for
Ice Protection for
General Aviation
Aircraft.
Sec. 23.2530 External and 9.7 External and 9.7.1 F3061/F3061M-
cockpit lighting. Cockpit Lighting. 22b Standard
Specification for
Systems and
Equipment in Small
Aircraft.
9.7.1.1 F3233/F3233M-
21 Standard
Specification for
Flight and
Navigation
Instrumentation in
Aircraft.
9.7.1.2 F3234/F3234M-
21 Standard
Specification for
Exterior Lighting in
Small Aircraft.
9.7.2 F3117/F3117M-
23a Standard
Specification for
Crew Interface in
Aircraft.
9.7.3 F3120/F3120M-20
Standard
Specification for
Ice Protection for
General Aviation
Aircraft.
Sec. 23.2535 Safety 9.8 Safety 9.8.1 F3061/F3061M-
equipment. Equipment. 22b Standard
Specification for
Systems and
Equipment in Small
Aircraft.
9.8.2 F3083/F3083M-
20a Standard
Specification for
Emergency
Conditions, Occupant
Safety and
Accommodations.
9.8.3 F3117/F3117M-
23a Standard
Specification for
Crew Interface.
Sec. 23.2540 Flight in icing 9.9 Flight in 9.9.1 F3061/F3061M-
conditions. Icing Conditions. 22b Standard
Specification for
Systems and
Equipment in Small
Aircraft.
9.9.1.1 F3233/F3233M-
21 Standard
Specification for
Flight and
Navigation
Instrumentation in
Aircraft.
9.9.2 F3120/F3120M-20
Standard
Specification for
Ice Protection for
General Aviation
Aircraft.
Sec. 23.2545 Pressurized 9.10 Pressurized 9.10.1 F3061/F3061M-
systems elements. System Elements. 22b Standard
Specification for
Systems and
Equipment in Small
Aircraft.
9.10.1.1 F3229/F3229M-
17 Standard Practice
for Static Pressure
System Tests in
Small Aircraft.
[[Page 46318]]
Sec. 23.2550 Equipment 9.11 Equipment 9.11.1 F3061/F3061M-
containing high-energy rotors. Containing High- 22b Standard
Energy Rotors. Specification for
Systems and
Equipment in Small
Aircraft.
------------------------------------------------------------------------
Subpart G--Flight crew Interface and Other Information
------------------------------------------------------------------------
Sec. 23.2600 Flightcrew 10.1 Flight crew 10.1.1 F3061/F3061M-
interface. Compartment 22b Standard
Interface. Specification for
Systems and
Equipment in Small
Aircraft.
10.1.1.1 F3232/F3232M-
20 Standard
Specification for
Flight Controls in
Small Aircraft.
10.1.2 F3062/F3062M-
20 Standard
Specification for
Aircraft Powerplant
Installation.
10.1.3 F3063/F3063M-
21 Standard
Specification for
Aircraft Fuel and
Energy Storage and
Delivery.
10.1.4 F3064/F3064M-
21 Standard
Specification for
Aircraft Powerplant
Control, Operation,
and Indication.
10.1.4.1 F3432-20a
Standard Practice
for Powerplant
Instruments.
10.1.5 F3114-21
Standard
Specification for
Structures.
10.1.6 F3117/F3117M-
23a Standard
Specification for
Crew Interface in
Aircraft.
10.1.7 F3408/F3408M-
21 Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
Sec. 23.2605 Installation 10.2 Installation 10.2.1 F3061/F3061M-
and operation. and Operation 22b Standard
Information. Specification for
Systems and
Equipment in Small
Aircraft.
10.2.1.1 F3227/F3227M-
22 Standard
Specification for
Environmental
Systems in Small
Aircraft.
10.2.1.2 F3231/F3231M-
23 Standard
Specification for
Electrical Systems
for Aircraft with
Combustion Engine
Electrical Power
Generation.
10.2.1.3 F3232/F3232M-
20 Standard
Specification for
Flight Controls in
Small Aircraft.
10.2.1.4 F3233/F3233M-
21 Standard
Specification for
Flight and
Navigation
Instrumentation in
Aircraft.
10.2.2 F3062/F3062M-
20 Standard
Specification for
Aircraft Powerplant
Installation.
10.2.3 F3063/F3063M-
21 Standard
Specification for
Aircraft Fuel and
Energy Storage and
Delivery.
10.2.4 F3064/F3064M-
21 Standard
Specification for
Aircraft Powerplant
Control, Operation,
and Indication.
10.2.4.1 F3432-20a
Standard Practice
for Powerplant
Instruments.
10.2.5 F3117/F3117M-
23a Standard
Specification for
Crew Interface in
Aircraft.
10.2.6 F3120/F3120M-
20 Standard
Specification for
Ice Protection for
General Aviation
Aircraft.
10.2.7 F3408/F3408M-
21 Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
Sec. 23.2610 Instrument 10.3 Instrument 10.3.1 F3061/F3061M-
markings, control markings, Markings, 22b Standard
and placards. Control Specification for
Markings, and Systems and
Placards. Equipment in Small
Aircraft.
10.3.2 F3063/F3063M-
21 Standard
Specification for
Aircraft Fuel and
Energy Storage and
Delivery.
10.3.3 F3117/F3117M-
23a Standard
Specification for
Crew Interface in
Aircraft.
10.3.4 F3120/F3120M-
20 Standard
Specification for
Ice Protection for
General Aviation
Aircraft.
10.3.5 F3408/F3408M-
21 Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
Sec. 23.2615 Flight, 10.4 Flight, 10.4.1 F3061/F3061M-
navigation, and powerplant Navigation, and 22b Standard
instruments. Powerplant Specification for
Instruments. Systems and
Equipment in Small
Aircraft.
10.4.2 F3062/F3062M-
20 Standard
Specification for
Aircraft Powerplant
Installation
10.4.3 F3064/F3064M-
21 Standard
Specification for
Aircraft Powerplant
Control, Operation,
and Indication.
10.4.3.1 F3432-20a
Standard Practice
for Powerplant
Instruments.
10.4.4 F3117/F3117M-
23a Standard
Specification for
Crew Interface in
Aircraft.
Sec. 23.2620 Airplane flight 5.15 Operating 5.15.1 F3174/F3174M-
manual. Limitations. 21 Standard
Specification for
Establishing
Operating
Limitations and
Information for
Aeroplanes.
5.15.2 F3408/F3408M-
21 Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
10.5 Airplane 10.5.1 F3117/F3117M-
Flight Manual. 23a Standard
Specification for
Crew Interface in
Aircraft.
10.5.2 F3174/F3174M-
21 Standard
Specification for
Establishing
Operating
Limitations and
Information for
Aeroplanes.
10.5.3 F3120/F3120M-
20 Standard
Specification for
Ice Protection for
General Aviation
Aircraft.
10.5.4 F3408/F3408M-
21 Standard
Specification for
Aircraft Emergency
Parachute Recovery
Systems.
------------------------------------------------------------------------
The MOC accepted by this NOA provide one means, but not the only
means of complying with part 23 regulatory requirements. Applicants who
desire to use an MOC reflected by other revisions to ASTM standards not
previously accepted may seek guidance and possible acceptance from the
FAA for the use of those MOC on a case-by-case basis. Applicants may
propose an alternative MOC for FAA review and possible acceptance.
[[Page 46319]]
Editorial, Reapproval, Revision, or Withdrawal
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. When an ASTM standard is reapproved, that reapproval is
denoted by the year in parentheses (e.g., F2427-05a (2013)). This date
indicates the completion of a review cycle with no technical changes
made to the standard. In addition, ASTM issues editorial changes
denoted by a superscript epsilon in the standard designation (e.g.,
F3235-17[egr]\1\). This epsilon indicates information was corrected,
and it did not change the meaning or intent of a standard. Since
reapprovals and editorial changes do not change the technical content
of standards, then any standard FAA-accepted by this NOA that is later
reapproved or editorially changed by ASTM, is also considered FAA-
accepted and without the need for an updated NOA.
ASTM revises a standard to make changes to its technical content.
Revisions are identified by a hyphen after the document number, which
is followed by the last two numbers of the year of acceptance or of
last revision. If the standard is revised again during the same year,
this is indicated by adding an ``a'' for the second revision, ``b'' for
the third revision, etc. Since revisions change the technical content,
revisions to consensus standards serving as the basis for an MOC
accepted by this NOA will not be automatically accepted and will
require further FAA acceptance for the revisions to be an accepted MOC.
Availability
ASTM F3264-23, ``Standard Specification for Normal Category
Aeroplanes Certification,'' is available online at https://www.astm.org/READINGLIBRARY/. ASTM 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
online or by contacting ASTM by telephone: (610) 832-9585; facsimile:
(610) 832-9555; or through email: [email protected]. 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 by telephone: (610) 832-9804 or through email:
[email protected].
Issued in Kansas City, Missouri, on May 21, 2024.
Patrick Mullen,
Manager, Technical Policy Branch, Policy and Standards Division,
Aircraft Certification Service.
[FR Doc. 2024-11596 Filed 5-28-24; 8:45 am]
BILLING CODE 4910-13-P
