Accepted Means of Compliance; Airworthiness Standards: Normal Category Airplanes, 21850-21855 [2018-09990]
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Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Rules and Regulations
defined as within the past two years
from the date of the letter requesting the
waiver; and the amount of the request.
§ 3419.5
[Amended]
8. Amend § 3419.5 by removing the
word ‘‘formula’’ and adding, in its
place, the word ‘‘capacity’’.
■ 9. Revise § 3419.6 to read as follows:
■
§ 3419.6
Use of matching funds.
The required matching funds for the
capacity programs must be used by an
eligible institution for the same purpose
as Federal award dollars: Agricultural
research and extension activities that
have been approved in the plan of work
required under sections 1445(c) and
1444(d) of the National Agricultural
Research, Extension, and Teaching
Policy Act of 1977, section 7 of the
Hatch Act of 1887, and section 4 of the
Smith-Lever Act. For all programs,
tuition dollars and student fees may not
be used as matching funds.
■ 10. Redesignate § 3419.7 as § 3419.8
and revise newly redesignated § 3419.8
to read as follows:
§ 3419.8
Redistribution of funds.
Unmatched research and extension
funds will be reapportioned in
accordance with the research and
extension statutory distribution
formulas applicable to the 1890 and
1862 land-grant institutions in insular
areas, respectively. Any redistribution
of funds must be subject to the same
matching requirement under § 3419.2.
■ 11. Add a new § 3419.7 to read as
follows:
§ 3419.7
Reporting of matching funds.
Institutions will report all capacity
matching funds expended annually
using Standard Form (SF) 425, in
accordance with 7 CFR 3430.56(a).
Done at Washington, DC, this 7th day of
May 2018.
Meryl Broussard,
Associate Director for Programs, National
Institute of Food and Agriculture.
BILLING CODE 3410–22–P
DEPARTMENT OF TRANSPORTATION
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14 CFR Part 23
[Notice No. 23–18–01–NOA]
Accepted Means of Compliance;
Airworthiness Standards: Normal
Category Airplanes
Federal Aviation
Administration, DOT.
AGENCY:
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This document announces the
availability of 63 Means of Compliance
(MOC) based on 30 published ASTM
International (ASTM) consensus
standards developed by ASTM
Committee F44 on General Aviation
Aircraft. A total of 46 of these accepted
MOCs consist of ASTM consensus
standards as published, with the
remaining 17 MOCs comprised of a
combination of ASTM standards and
FAA changes. The Administrator finds
these MOCs to be an acceptable means,
but not the only means, of showing
compliance to the applicable regulations
in part 23, amendment 23–64, for
normal category airplanes. The
Administrator further finds that these
accepted means of complying with part
23, amendment 23–64, provide at least
the same level of safety as the
corresponding requirements in part 23,
amendment 23–63.
DATES: Comments must be received on
or before July 10, 2018.
ADDRESSES: Mail comments to: Federal
Aviation Administration, Policy and
Innovation Division, Small Airplane
Standards Branch, AIR–690, Attention:
Steve Thompson, 901 Locust Street,
Room 301, Kansas City, Missouri 64106.
Comments may also be emailed to:
steven.thompson@faa.gov. Specify the
MOC, and if applicable, the standard
being addressed by designation and
title. Mark all comments: Part 23 MOC
Comments.
FOR FURTHER INFORMATION CONTACT:
Steve Thompson, Federal Aviation
Administration, Policy and Innovation
Division, Small Airplane Standards
Branch, AIR–690, 901 Locust Street,
Room 301, Kansas City, Missouri 64106;
telephone (816) 329–4126; facsimile:
(816) 329–4090; email:
steven.thompson@faa.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
Comments Invited
[FR Doc. 2018–10015 Filed 5–10–18; 8:45 am]
Federal Aviation Administration
Notification of availability;
request for comments.
ACTION:
Interested persons are invited to
submit written comments, data, or
views. Communications should identify
the MOC and consensus standard
number, where applicable, and be
submitted to the address previously
specified in the ADDRESSES section of
this NOA. The most helpful comments
reference a specific portion of the
accepted MOC(s) or standard(s), explain
the reason for any recommended
change, and include supporting data.
The FAA may forward communications
regarding the consensus standards to
ASTM Committee F44 for consideration.
The MOC or standard may be revised
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based on received comments. The FAA
will consider all comments received
during the recurring review of the MOC
and consensus standard and will
participate in the consensus standard
revision process.
Background
Under the provisions of the National
Technology Transfer and Advancement
Act of 1995 1 and Office of Management
and Budget (OMB) Circular A–119,
‘‘Federal Participation in the
Development and Use of Voluntary
Consensus Standards and in Conformity
Assessment Activities,’’ effective
January 27, 2016, the FAA participates
in the development of consensus
standards and uses consensus standards
as a means of carrying out its policy
objectives where appropriate.
Consistent with the Small Airplane
Revitalization Act of 2013,2 the FAA has
been working with industry and other
stakeholders through ASTM to develop
consensus standards for use as a MOC
in certificating small airplanes under
part 23. In promulgating part 23,
amendment 23–64, the FAA explained
that if it determined such consensus
standards were acceptable MOC to part
23, it would publish a notice of
availability of those consensus
standards in the Federal Register.
Pursuant to FAA Advisory Circular
23.2010–1, section 3.1.1, this document
serves as a formal acceptance by the
Administrator, of MOCs based on
consensus standards developed by
ASTM. The MOCs accepted by this
document are one means, but not the
only means of complying with part 23
regulatory requirements.
The FAA has reviewed the consensus
standards referenced in this NOA as the
basis for MOCs to the regulatory
requirements of part 23, amendment 23–
64. In some cases, the Administrator
finds sections of ASTM Standard
F3264–17, ‘‘Standard Specification for
Normal Category Aeroplanes
Certification,’’ without changes, are
accepted as means of complying with
the airworthiness requirements of part
23, without degrading safety, and within
the scope and applicability of the
consensus standards. In other cases, the
MOCs, while based on ASTM consensus
standards, include additional FAA
provisions necessary to comply with the
airworthiness requirements of part 23,
amendment 23–64.
Part 23, amendment 23–64,
established airworthiness requirements
based on the level of safety of
1 Ref Public Law 104–113 as amended by Public
Law 107–107.
2 Ref Public Law 113–53.
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amendment 23–63 regulations, except
for areas addressing loss of control and
icing where the safety level was
increased.3 Achieving this level of
safety through compliance with
amendment 23–64—for a given
certification project—may require use of
additional MOCs beyond those accepted
by this document, depending on the
details of the specific design. For
example, an applicant’s design may
include features that are customary, but
not addressed in the MOCs accepted by
this document. Designs may also
include features that are innovative and
not type certificated previously. In
either case, a supplemental MOC
beyond those accepted in this document
would be required. For example, the
MOCs accepted by this document do not
contain provisions addressing powered-
trim system runaways. Therefore, in
order to maintain the level of safety of
amendment 23–63 regulations,
applicants proposing use of these MOCs
for an airplane with a powered-trim
system would need to supplement the
accepted MOC(s) with additional means
for § 23.2300 to demonstrate safe
controllability after a probable trim
system runaway. To do this, applicants
could use the provisions of § 23.677(d),
amendment 23–49, or other MOC(s)
accepted under § 23.2010. Further
information on supplemental MOCs is
provided in a part 23 means of
compliance summary table and in the
Small Airplanes Issues List, which are
available on the Small Airplanes—
Regulations, Policies & Guidance
website.4
21851
Means of Compliance Accepted in This
Document
The following is a list of sections from
part 23, amendment 23–64, followed by
their corresponding MOC accepted by
this document:
23.1457: ASTM F3264–17, section 9.12
23.1459: ASTM F3264–17, section 9.13
23.1529: ASTM F3264–17, section 10.6
Subpart B—Flight
23.2100: ASTM F3264–17, section 5.1
23.2105: ASTM F3264–17, section 5.2
23.2110: ASTM F3264–17, section 5.3
23.2115: ASTM F3264–17, section 5.4
23.2120: ASTM F3264–17, section 5.5
23.2125: ASTM F3264–17, section 5.6
23.2130: ASTM F3264–17, section 5.7
23.2135: ASTM F3264–17, section 5.8,
combined with the changes in the
following table:
Replace:
With:
ASTM F3173/F3173M–17, Sections
4.9.1.1 and 4.9.1.2.
FAA 4.9.1.1 and 4.9.1.2:
4.9.1.1: ‘‘For a level 1 or 2 airplane, or level 3 or 4 airplane of 6,000 pounds or less maximum
weight, 5 seconds from initiation of roll and’’
4.9.1.2: ‘‘For a level 3 or 4 airplane of over 6,000 pounds maximum weight, (W+500)/1300 seconds, but not more than 10 seconds, where W is the weight in pounds.’’
FAA 4.9.3.1 and 4.9.3.2:
4.9.3.1: ‘‘For a level 1 or 2 airplane, or level 3 or 4 airplane of 6,000 pounds or less maximum
weight, 4 seconds from initiation of roll and’’
4.9.3.2: ‘‘For a level 3 or 4 airplane of over 6,000 pounds maximum weight, (W+2,800)/2,200
seconds, but not more than 7 seconds, where W is the weight in pounds.’’
ASTM F3173/F3173M–17, Sections
4.9.3.1 and 4.9.3.2.
23.2140: ASTM F3264–17, section 5.9
23.2145: ASTM F3264–17, section 5.10
23.2150: ASTM F3264–17, section 5.11
23.2155: ASTM F3264–17, section 5.12
23.2160: ASTM F3264–17, section 5.13
23.2165: ASTM F3264–17, section 5.14
Subpart C—Structures
23.2200: ASTM F3264–17, Section 6.1,
combined with the changes in the
following table:
Replace:
With:
ASTM F3116/F3116M–15, Section
5.1.3.1(1).
FAA 5.1.3.1(1):
‘‘VS is a 1g computed stalling speed with flaps retracted (normally based on the maximum airplane normal force coefficient, CNA) at the design maximum takeoff weight.’’
23.2210: ASTM F3264–17, section 6.3
23.2215: ASTM F3264–17, section 6.4,
combined with the changes in the
following table:
Replace:
With:
ASTM F3116/F3116M–15, Section 4.1.4
FAA 4.1.4:
‘‘Appendix X1 through appendix X4 provide, within the limitations specified within the appendix,
a simplified means of compliance with several of the requirements set forth in 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 appendix X3 are used, they must be used together in their
entirety.’’
FAA 4.10.1.1:
‘‘In condition A, assume 100% of the semispan wing airload acts on one side of the airplane
and 75% of this load acts on the other side. For airplanes with maximum weight of 1,000
pounds or less, 70% of the load acts on the other side.’’
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ASTM F3116/F3116M–15, Section
4.10.1.1.
3 Ref
81 FR 96572, December 30, 2016.
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4 See https://www.faa.gov/aircraft/air_cert/
design_approvals/small_airplanes/small_airplanes_
regs/.
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Replace:
With:
ASTM F3116/F3116M–15, Section X1.1.1
FAA X1.1.1:
‘‘The methods provided in this appendix provide one possible means (but not the only possible
means) of compliance and can only be applied to low-speed, level 1 and level 2 airplanes.’’
X1.1.4 through X1.1.4.5: Same as published in F3116/F3116M–15.
Add FAA X1.1.4.6:
‘‘Wings with winglets, tip tanks, or tip fins.’’
ASTM F3116/F3116M–15, Section X1.1.4
23.2220: ASTM F3264–17, section 6.5
23.2225: ASTM F3264–17, section 6.6,
combined with the changes in the
following table:
Replace:
With:
ASTM F3116/F3116M–15, Section X2.1.1
FAA X2.1.1:
‘‘The methods provided in this appendix provide one possible means (but not the only possible
means) of compliance and can only be applied to low-speed, level 1 and level 2 airplanes.’’
FAA X3.1.1:
‘‘The methods provided in this appendix provide one possible means (but not the only possible
means) of compliance and can only be applied to low-speed, level 1 and level 2 airplanes.’’
FAA X4.1.1:
‘‘The methods provided in this appendix provide one possible means (but not the only possible
means) of compliance and can only be applied to low-speed, level 1 airplanes.’’
ASTM F3116/F3116M–15, Section X3.1.1
ASTM F3116/F3116M–15, Section X4.1.1
23.2230: ASTM F3264–17, section 6.7
23.2235: ASTM F3264–17, section 6.8,
combined with the changes in the
following table:
Replace:
With:
ASTM F3264–17, Section 6.8.1 ...............
FAA 6.8.1:
‘‘F3114–15 Standard Specification for Structures’’.
23.2240: ASTM F3264–17, section 6.9,
combined with the changes in the
following table:
Replace:
With:
ASTM F3115/F3115M–15, Section 4.4.1
FAA 4.4.1:
‘‘For metallic (aluminum), unpressurized, non-aerobatic, low-speed, level 1 airplanes, applicants
can demonstrate a 10,000 hour safe-life by limiting the ‘1g’ gross stress, at maximum takeoff
weight, to no more than 5.5 ksi. The applicant must show effective stress concentration factors of 4 or less in highly loaded joints and use materials or material systems for which the
physical and mechanical properties are well established.’’
FAA 6.1:
‘‘For bonded airframe structure, the residual strength of bonded joints shall be addressed as follows: For any bonded joint, the failure of which would result in catastrophic loss of the airplane, the limit load capacity must be substantiated by one of the following methods.’’
ASTM F3115/F3115M–15, Section 6.1 ....
23.2245: ASTM F3264–17, section 6.10
23.2250: ASTM F3264–17, section 6.11
23.2255: ASTM F3264–17, section 6.12
23.2260: ASTM F3264–17, section 6.13
23.2265: ASTM F3264–17, section 6.14
23.2270: ASTM F3264–17, section 6.15
Subpart D—Design and Construction
23.2300: ASTM F3264–17, section 7.1,
combined with the changes in the
following table:
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Replace:
With:
ASTM F3232/F3232M–17, Table 1, Row
4.4.6.
FAA Table 1, Row 4.4.6:
A white circle (‘‘o’’) in the following Aircraft Type Code (ATC) character fields: ‘‘Airworthiness
Level—1’’ and ‘‘Stall Speed—L’’; a mark-out (‘‘x’’) in the following ATC character field: ‘‘Number of Engines—M’’; and no codes in any other ATC character field.
Note: This change applies the standard of ASTM F3232/F3232M–17, Section 4.4.6, to all single-engine airplanes except level 1 airplanes with a stall speed of 45 knots or less.
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23.2325: ASTM F3264–17, section 7.6,
combined with the changes in the
following table:
23.2305: ASTM F3264–17, section 7.2
23.2315: ASTM F3264–17, section 7.4
23.2320: ASTM F3264–17, section 7.5
Replace:
With:
ASTM F3061/F3061M–17, Section 10.3.2
FAA 10.3.2:
‘‘In each area where flammable fluids or vapors might escape by leakage of a fluid system,
there must be means to minimize the probability of ignition of the fluids and vapors, and the
resultant hazard if ignition does occur. These means must account for the factors prescribed
in 10.3.3 through 10.3.7.’’
23.2330: ASTM F3264–17, section 7.7
23.2335: ASTM F3264–17, section 7.8
Subpart E—Powerplant
23.2400: ASTM F3264–17, section 8.1,
combined with the changes in the
following table:
Replace:
With:
ASTM F3065/F3065M–15, Section 4.3 ....
An FAA-accepted means of compliance for § 23.2400(c), such as the provisions of § 23.905(d),
amendment 23–59.
23.2405: ASTM F3264–17, section 8.2
23.2410: ASTM F3264–17, section 8.3,
combined with the changes in the
following table:
Replace:
With:
ASTM F3264–17, Section 8.3 ..................
8.3 through 8.3.2: Same as published in F3264–17.
Renumber 8.3.3 to 8.3.6.
Add FAA 8.3.3 through 8.3.5, and FAA 8.3.7:
8.3.3: ‘‘F3063/F3063M—16a Standard Specification for Design and Integration of Fuel/Energy
Storage and Delivery System Installations for Aeroplanes’’.
8.3.4: ‘‘F3064/F3064M—15 Standard Specification for Control, Operational Characteristics and
Installation of Instruments and Sensors of Propulsion Systems’’.
8.3.5: ‘‘F3065/F3065M—15 Standard Specification for Installation and Integration of Propeller
System’’.
8.3.7: ‘‘F3117—15 Standard Specification for Crew Interface in Aircraft’’.
23.2415: ASTM F3264–17, section 8.4,
combined with the changes in the
following table:
Replace:
With:
ASTM F3264–17, Section 8.4 ..................
8.4 through 8.4.1: Same as published in F3264–17.
Renumber 8.4.2 to 8.4.3.
Add FAA 8.4.2:
F3063/F3063M—‘‘16a Standard Specification for Design and Integration of Fuel/Energy Storage
and Delivery System Installations for Aeroplanes’’.
An FAA-accepted means of compliance for the induction system ice protection aspects of § 23.2415,
such as the provisions of § 23.1093(a), amendment 23–51.
FAA 5.2.1.1:
‘‘Operate throughout its flight power range, including minimum descent idle speeds, in the icing
and snow conditions specified in Specification F3120/F3120M, without the accumulation of ice
on engine, inlet system components, or airframe components that would do any of the following:’’
[Remove]
FAA 5.2.2:
‘‘Each turbine engine must idle for 30 min on the ground, with the air bleed available for engine
icing protection at its critical condition, without adverse effect, in the ground icing conditions
specified in Specification F3120/F3120M.’’
FAA 5.2.2.1 Followed by momentary operation at takeoff power or thrust.
FAA 5.2.2.2 During the 30 min of idle operation, the engine may be run up periodically to a moderate power or thrust setting.’’
ASTM F3066/F3066M–15, Section 5.1 ....
ASTM F3066/F3066M–15, Section
5.2.1.1.
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ASTM F3066/F3066M–15, Section 5.2.2
ASTM F3066/F3066M–15, Sections 5.2.3,
5.2.3.1, and 5.2.3.2.
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23.2420: ASTM F3264–17, section 8.5,
combined with the changes in the
following table:
Replace:
With:
ASTM F3264–17, Section 8.5 ..................
8.5 through 8.5.1: Same as published in F3264–17.
Remove 8.5.2 and 8.5.3.
Add FAA 8.5.2:
F3065/F3065M—‘‘15 Standard Specification for Installation and Integration of Propeller System’’.
23.2425: ASTM F3264–17, section 8.6,
combined with the changes in the
following table:
Replace:
With:
ASTM F3264–17, Section 8.6 ..................
8.6 through 8.6.2: Same as published in F3264–17.
Renumber 8.6.3 to 8.6.4.
Add FAA 8.6.3 and FAA 8.6.5:
8.6.3: ‘‘F3065/F3065M—15 Standard Specification for Installation and Integration of Propeller
System’’.
8.6.5: ‘‘F3117—15 Standard Specification for Crew Interface in Aircraft’’.
23.2430: ASTM F3264–17, section 8.7,
combined with the changes in the
following table:
Replace:
With:
ASTM F3264–17, Section 8.7 ..................
8.7.1 through 8.7.5: Same as published in F3264–17.
Add an FAA-accepted means of compliance for the fuel supply aspects of § 23.2430, such as the
provisions of § 23.991(b), amendment 23–43.
An FAA-accepted means of compliance for the fuel/oil tank aspects of § 23.2430, such as the provisions of § 23.967(d), amendment 23–43.
ASTM F3066/F3066M–15, Section 6.3 ....
23.2435: ASTM F3264–17, section 8.8
23.2440: ASTM F3264–17, section 8.9,
combined with the changes in the
following table:
Replace:
With:
ASTM Section 8.9, F3264–17 ..................
8.9 through 8.9.2: Same as published in F3264–17.
Renumber 8.9.3 to 8.9.4.
Renumber 8.9.4 to 8.9.5 and change to, ‘‘F3066/F3066M–15 Standard Specification for Powerplant
Systems Specific Hazard Mitigation.’’
Add FAA 8.9.3:
8.9.3: ‘‘F3063/F3063M–16a Standard Specification for Design and Integration of Fuel/Energy
Storage and Delivery System Installations for Aeroplanes.’’
Subpart F—Equipment
23.2500: ASTM F3264–17, section 9.1
23.2505: ASTM F3264–17, section 9.2
23.2510: ASTM F3264–17, section 9.3
23.2515: ASTM F3264–17, section 9.4
23.2520: ASTM F3264–17, section 9.5
23.2525: ASTM F3264–17, section 9.6
23.2530: ASTM F3264–17, section 9.7
23.2535: ASTM F3264–17, section 9.8
23.2540: ASTM F3264–17, section 9.9
23.2545: ASTM F3264–17, section 9.10
23.2550: ASTM F3061/F3061M–17,
section 10.9
Subpart G—Flightcrew Interface and
Other Information
23.2600: ASTM F3264–17, section 10.1,
combined with the changes in the
following table:
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Replace:
With:
ASTM Section 10.1, F3264–17 ................
10.1.1 through 10.1.5: Same as published in F3264–17.
Add an FAA-accepted means of compliance for the windshield luminous transmittance aspects of
§ 23.2600, such as the provisions of § 23.775(e), amendment 23–49.
Add an FAA-accepted means of compliance for the pilot compartment view with formation of fog or
frost aspects of § 23.2600, such as the provisions of § 23.773(b), amendment 23–45.
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23.2605: ASTM F3264–17, section 10.2
23.2610: ASTM F3264–17, section 10.3
21855
23.2615: ASTM F3264–17, section 10.4,
combined with the changes in the
following table:
Replace:
With:
ASTM Section 6, F3064/F3064M–15 .......
An FAA-accepted means of compliance for the powerplant instruments aspects of § 23.2615, such
as the provisions of § 23.1305, amendment 23–52.
23.2620: ASTM F3264–17, sections 5.15
and 10.5
Editorial, Reapproval, Revision Or
Withdrawal
The FAA expects a suitable consensus
standard to be reviewed periodically.
ASTM policy is that a consensus
standard should be reviewed in its
entirety by the responsible
subcommittee and must be balloted for
reapproval, revision, or withdrawal,
within five years of its last approval
date. ASTM reapproves a standard—
denoted by the year of reapproval in
parentheses (e.g., F2427–05a(2013))—to
indicate completion of a review cycle
with no technical changes made to the
standard. ASTM issues editorial
changes—denoted by a superscript
epsilon in the standard designation
(F3235–17 ε1)—to correct information
that does not change the meaning or
intent of a standard. Any MOC accepted
by this document that is based on a
standard later reapproved or editorially
changed is also considered accepted
without the need for a NOA. ASTM
revises a standard to make changes to its
technical content. Revisions to
consensus standards serving as the basis
for MOC accepted by this document will
not be automatically accepted and will
require further FAA acceptance in order
for the revisions to be an accepted MOC.
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Availability
ASTM Standard F3264–17, ‘‘Standard
Specification for Normal Category
Aeroplanes Certification,’’ is available
for online reading at https://
www.astm.org/READINGLIBRARY/.
ASTM International copyrights these
consensus standards and charges the
public a fee for service. Individual
downloads or reprints of a standard
(single or multiple copies, or special
compilations and other related technical
information) may be obtained through
www.astm.org or by contacting ASTM at
(610) 832–9585 (phone), (610) 832–9555
(fax), or through service@astm.org
(email). To inquire about consensus
standard content and/or membership or
about ASTM Offices abroad, contact Joe
Koury, Staff Manager for Committee F44
on General Aviation: (610) 832–9804,
jkoury@astm.org.
VerDate Sep<11>2014
22:27 May 10, 2018
Jkt 244001
The FAA maintains a list of accepted
MOCs on the FAA website at https://
www.faa.gov/aircraft/air_cert/design_
approvals/small_airplanes/small_
airplanes_regs/.
Issued in Kansas City, Missouri, on May 3,
2018.
Pat Mullen,
Manager, Small Airplanes Standards Branch,
Aircraft Certification Service.
[FR Doc. 2018–09990 Filed 5–10–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0775; Product
Identifier 2017–NM–048–AD; Amendment
39–19272; AD 2018–09–15]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
of certain publications listed in this AD
as of June 15, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of January 3, 2017 (81 FR
90961, December 16, 2016).
ADDRESSES: For service information
identified in this final rule, contact
ˆ
Bombardier, Inc., 400 Cote-Vertu Road
´
West, Dorval, Quebec H4S 1Y9, Canada;
telephone: 514–855–5000; fax: 514–
855–7401; email: thd.crj@
aero.bombardier.com; internet: https://
www.bombardier.com. You may view
this referenced service information at
the FAA, Transport Standards Branch,
2200 South 216th Street, Des Moines,
WA. For information on the availability
of this material at the FAA, call 206–
231–3195. It is also available on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2017–0775.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0775; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone: 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Aziz
Ahmed, Aerospace Engineer, Airframe
and Mechanical Systems Section, FAA,
New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone: 516–228–7329; fax:
516–794–5531.
SUPPLEMENTARY INFORMATION:
We are superseding
Airworthiness Directive (AD) 2016–25–
18, which applied to certain
Bombardier, Inc., Model BD–700–1A10
and BD–700–1A11 airplanes. AD 2016–
25–18 required an inspection for
discrepancies of the attachment points
of the links between the engine rear
mount assemblies, and corrective
actions if necessary. This AD requires
an inspection of certain attachment
points, corrective action if necessary,
and replacement of certain bolts and
nuts in the engine rear mount
assemblies. This AD also adds airplanes
to the applicability. This AD was
prompted by the determination that
replacement of certain nuts and bolts in
the engine rear mount assemblies is
necessary. We are issuing this AD to
address the unsafe condition on these
products.
Discussion
This AD is effective June 15,
2018.
The Director of the Federal Register
approved the incorporation by reference
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016–25–18,
Amendment 39–18744 (81 FR 90961,
SUMMARY:
DATES:
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
E:\FR\FM\11MYR1.SGM
11MYR1
]]>Agencies
[Federal Register Volume 83, Number 92 (Friday, May 11, 2018)]
[Rules and Regulations]
[Pages 21850-21855]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09990]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Notice No. 23-18-01-NOA]
Accepted Means of Compliance; Airworthiness Standards: Normal
Category Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notification of availability; request for comments.
-----------------------------------------------------------------------
SUMMARY: This document announces the availability of 63 Means of
Compliance (MOC) based on 30 published ASTM International (ASTM)
consensus standards developed by ASTM Committee F44 on General Aviation
Aircraft. A total of 46 of these accepted MOCs consist of ASTM
consensus standards as published, with the remaining 17 MOCs comprised
of a combination of ASTM standards and FAA changes. The Administrator
finds these MOCs to be an acceptable means, but not the only means, of
showing compliance to the applicable regulations in part 23, amendment
23-64, for normal category airplanes. The Administrator further finds
that these accepted means of complying with part 23, amendment 23-64,
provide at least the same level of safety as the corresponding
requirements in part 23, amendment 23-63.
DATES: Comments must be received on or before July 10, 2018.
ADDRESSES: Mail comments to: Federal Aviation Administration, Policy
and Innovation Division, Small Airplane Standards Branch, AIR-690,
Attention: Steve Thompson, 901 Locust Street, Room 301, Kansas City,
Missouri 64106. Comments may also be emailed to:
[email protected]. Specify the MOC, and if applicable, the
standard being addressed by designation and title. Mark all comments:
Part 23 MOC Comments.
FOR FURTHER INFORMATION CONTACT: Steve Thompson, Federal Aviation
Administration, Policy and Innovation Division, Small Airplane
Standards Branch, AIR-690, 901 Locust Street, Room 301, Kansas City,
Missouri 64106; telephone (816) 329-4126; facsimile: (816) 329-4090;
email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to submit written comments, data, or
views. Communications should identify the MOC and consensus standard
number, where applicable, and be submitted to the address previously
specified in the ADDRESSES section of this NOA. The most helpful
comments reference a specific portion of the accepted MOC(s) or
standard(s), explain the reason for any recommended change, and include
supporting data. The FAA may forward communications regarding the
consensus standards to ASTM Committee F44 for consideration. The MOC or
standard may be revised based on received comments. The FAA will
consider all comments received during the recurring review of the MOC
and consensus standard and will participate in the consensus standard
revision process.
Background
Under the provisions of the National Technology Transfer and
Advancement Act of 1995 \1\ and Office of Management and Budget (OMB)
Circular A-119, ``Federal Participation in the Development and Use of
Voluntary Consensus Standards and in Conformity Assessment
Activities,'' effective January 27, 2016, the FAA participates in the
development of consensus standards and uses consensus standards as a
means of carrying out its policy objectives where appropriate.
---------------------------------------------------------------------------
\1\ Ref Public Law 104-113 as amended by Public Law 107-107.
---------------------------------------------------------------------------
Consistent with the Small Airplane Revitalization Act of 2013,\2\
the FAA has been working with industry and other stakeholders through
ASTM to develop consensus standards for use as a MOC in certificating
small airplanes under part 23. In promulgating part 23, amendment 23-
64, the FAA explained that if it determined such consensus standards
were acceptable MOC to part 23, it would publish a notice of
availability of those consensus standards in the Federal Register.
---------------------------------------------------------------------------
\2\ Ref Public Law 113-53.
---------------------------------------------------------------------------
Pursuant to FAA Advisory Circular 23.2010-1, section 3.1.1, this
document serves as a formal acceptance by the Administrator, of MOCs
based on consensus standards developed by ASTM. The MOCs accepted by
this document are one means, but not the only means of complying with
part 23 regulatory requirements.
The FAA has reviewed the consensus standards referenced in this NOA
as the basis for MOCs to the regulatory requirements of part 23,
amendment 23-64. In some cases, the Administrator finds sections of
ASTM Standard F3264-17, ``Standard Specification for Normal Category
Aeroplanes Certification,'' without changes, are accepted as means of
complying with the airworthiness requirements of part 23, without
degrading safety, and within the scope and applicability of the
consensus standards. In other cases, the MOCs, while based on ASTM
consensus standards, include additional FAA provisions necessary to
comply with the airworthiness requirements of part 23, amendment 23-64.
Part 23, amendment 23-64, established airworthiness requirements
based on the level of safety of
[[Page 21851]]
amendment 23-63 regulations, except for areas addressing loss of
control and icing where the safety level was increased.\3\ Achieving
this level of safety through compliance with amendment 23-64--for a
given certification project--may require use of additional MOCs beyond
those accepted by this document, depending on the details of the
specific design. For example, an applicant's design may include
features that are customary, but not addressed in the MOCs accepted by
this document. Designs may also include features that are innovative
and not type certificated previously. In either case, a supplemental
MOC beyond those accepted in this document would be required. For
example, the MOCs accepted by this document do not contain provisions
addressing powered-trim system runaways. Therefore, in order to
maintain the level of safety of amendment 23-63 regulations, applicants
proposing use of these MOCs for an airplane with a powered-trim system
would need to supplement the accepted MOC(s) with additional means for
Sec. 23.2300 to demonstrate safe controllability after a probable trim
system runaway. To do this, applicants could use the provisions of
Sec. 23.677(d), amendment 23-49, or other MOC(s) accepted under Sec.
23.2010. Further information on supplemental MOCs is provided in a part
23 means of compliance summary table and in the Small Airplanes Issues
List, which are available on the Small Airplanes--Regulations, Policies
& Guidance website.\4\
---------------------------------------------------------------------------
\3\ Ref 81 FR 96572, December 30, 2016.
\4\ See https://www.faa.gov/aircraft/air_cert/design_approvals/small_airplanes/small_airplanes_regs/.
---------------------------------------------------------------------------
Means of Compliance Accepted in This Document
The following is a list of sections from part 23, amendment 23-64,
followed by their corresponding MOC accepted by this document:
23.1457: ASTM F3264-17, section 9.12
23.1459: ASTM F3264-17, section 9.13
23.1529: ASTM F3264-17, section 10.6
Subpart B--Flight
23.2100: ASTM F3264-17, section 5.1
23.2105: ASTM F3264-17, section 5.2
23.2110: ASTM F3264-17, section 5.3
23.2115: ASTM F3264-17, section 5.4
23.2120: ASTM F3264-17, section 5.5
23.2125: ASTM F3264-17, section 5.6
23.2130: ASTM F3264-17, section 5.7
23.2135: ASTM F3264-17, section 5.8, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3173/F3173M-17, Sections 4.9.1.1 and 4.9.1.2... FAA 4.9.1.1 and
4.9.1.2:
4.9.1.1: ``For a
level 1 or 2
airplane, or
level 3 or 4
airplane of
6,000 pounds or
less maximum
weight, 5
seconds from
initiation of
roll and''
4.9.1.2: ``For
a level 3 or
4 airplane of
over 6,000
pounds
maximum
weight,
(W+500)/1300
seconds, but
not more than
10 seconds,
where W is
the weight in
pounds.''
ASTM F3173/F3173M-17, Sections 4.9.3.1 and 4.9.3.2... FAA 4.9.3.1 and
4.9.3.2:
4.9.3.1: ``For a
level 1 or 2
airplane, or
level 3 or 4
airplane of
6,000 pounds or
less maximum
weight, 4
seconds from
initiation of
roll and''
4.9.3.2: ``For
a level 3 or
4 airplane of
over 6,000
pounds
maximum
weight,
(W+2,800)/
2,200
seconds, but
not more than
7 seconds,
where W is
the weight in
pounds.''
------------------------------------------------------------------------
23.2140: ASTM F3264-17, section 5.9
23.2145: ASTM F3264-17, section 5.10
23.2150: ASTM F3264-17, section 5.11
23.2155: ASTM F3264-17, section 5.12
23.2160: ASTM F3264-17, section 5.13
23.2165: ASTM F3264-17, section 5.14
Subpart C--Structures
23.2200: ASTM F3264-17, Section 6.1, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3116/F3116M-15, Section 5.1.3.1(1)............. FAA 5.1.3.1(1):
``VS is a 1g
computed
stalling speed
with flaps
retracted
(normally based
on the maximum
airplane normal
force
coefficient,
CNA) at the
design maximum
takeoff
weight.''
------------------------------------------------------------------------
23.2210: ASTM F3264-17, section 6.3
23.2215: ASTM F3264-17, section 6.4, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3116/F3116M-15, Section 4.1.4.................. FAA 4.1.4:
``Appendix X1
through appendix
X4 provide,
within the
limitations
specified within
the appendix, a
simplified means
of compliance
with several of
the requirements
set forth in 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 appendix
X3 are used,
they must be
used together in
their
entirety.''
ASTM F3116/F3116M-15, Section 4.10.1.1............... FAA 4.10.1.1:
``In condition A,
assume 100% of
the semispan
wing airload
acts on one side
of the airplane
and 75% of this
load acts on the
other side. For
airplanes with
maximum weight
of 1,000 pounds
or less, 70% of
the load acts on
the other
side.''
[[Page 21852]]
ASTM F3116/F3116M-15, Section X1.1.1................. FAA X1.1.1:
``The methods
provided in this
appendix provide
one possible
means (but not
the only
possible means)
of compliance
and can only be
applied to low-
speed, level 1
and level 2
airplanes.''
ASTM F3116/F3116M-15, Section X1.1.4................. X1.1.4 through
X1.1.4.5: Same
as published in
F3116/F3116M-15.
Add FAA X1.1.4.6:
``Wings with
winglets, tip
tanks, or tip
fins.''
------------------------------------------------------------------------
23.2220: ASTM F3264-17, section 6.5
23.2225: ASTM F3264-17, section 6.6, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3116/F3116M-15, Section X2.1.1................. FAA X2.1.1:
``The methods
provided in this
appendix provide
one possible
means (but not
the only
possible means)
of compliance
and can only be
applied to low-
speed, level 1
and level 2
airplanes.''
ASTM F3116/F3116M-15, Section X3.1.1................. FAA X3.1.1:
``The methods
provided in this
appendix provide
one possible
means (but not
the only
possible means)
of compliance
and can only be
applied to low-
speed, level 1
and level 2
airplanes.''
ASTM F3116/F3116M-15, Section X4.1.1................. FAA X4.1.1:
``The methods
provided in this
appendix provide
one possible
means (but not
the only
possible means)
of compliance
and can only be
applied to low-
speed, level 1
airplanes.''
------------------------------------------------------------------------
23.2230: ASTM F3264-17, section 6.7
23.2235: ASTM F3264-17, section 6.8, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3264-17, Section 6.8.1......................... FAA 6.8.1:
``F3114-15
Standard
Specification
for
Structures''.
------------------------------------------------------------------------
23.2240: ASTM F3264-17, section 6.9, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3115/F3115M-15, Section 4.4.1.................. FAA 4.4.1:
``For metallic
(aluminum),
unpressurized,
non-aerobatic,
low-speed, level
1 airplanes,
applicants can
demonstrate a
10,000 hour safe-
life by limiting
the `1g' gross
stress, at
maximum takeoff
weight, to no
more than 5.5
ksi. The
applicant must
show effective
stress
concentration
factors of 4 or
less in highly
loaded joints
and use
materials or
material systems
for which the
physical and
mechanical
properties are
well
established.''
ASTM F3115/F3115M-15, Section 6.1.................... FAA 6.1:
``For bonded
airframe
structure, the
residual
strength of
bonded joints
shall be
addressed as
follows: For any
bonded joint,
the failure of
which would
result in
catastrophic
loss of the
airplane, the
limit load
capacity must be
substantiated by
one of the
following
methods.''
------------------------------------------------------------------------
23.2245: ASTM F3264-17, section 6.10
23.2250: ASTM F3264-17, section 6.11
23.2255: ASTM F3264-17, section 6.12
23.2260: ASTM F3264-17, section 6.13
23.2265: ASTM F3264-17, section 6.14
23.2270: ASTM F3264-17, section 6.15
Subpart D--Design and Construction
23.2300: ASTM F3264-17, section 7.1, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3232/F3232M-17, Table 1, Row 4.4.6............. FAA Table 1, Row
4.4.6:
A white circle
(``o'') in the
following
Aircraft Type
Code (ATC)
character
fields:
``Airworthiness
Level--1'' and
``Stall Speed--
L''; a mark-out
(``x'') in the
following ATC
character field:
``Number of
Engines--M'';
and no codes in
any other ATC
character field.
Note: This change
applies the
standard of ASTM
F3232/F3232M-17,
Section 4.4.6,
to all single-
engine airplanes
except level 1
airplanes with a
stall speed of
45 knots or
less.
------------------------------------------------------------------------
[[Page 21853]]
23.2305: ASTM F3264-17, section 7.2
23.2315: ASTM F3264-17, section 7.4
23.2320: ASTM F3264-17, section 7.5
23.2325: ASTM F3264-17, section 7.6, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3061/F3061M-17, Section 10.3.2................. FAA 10.3.2:
``In each area
where flammable
fluids or vapors
might escape by
leakage of a
fluid system,
there must be
means to
minimize the
probability of
ignition of the
fluids and
vapors, and the
resultant hazard
if ignition does
occur. These
means must
account for the
factors
prescribed in
10.3.3 through
10.3.7.''
------------------------------------------------------------------------
23.2330: ASTM F3264-17, section 7.7
23.2335: ASTM F3264-17, section 7.8
Subpart E--Powerplant
23.2400: ASTM F3264-17, section 8.1, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3065/F3065M-15, Section 4.3.................... An FAA-accepted
means of
compliance for
Sec.
23.2400(c), such
as the
provisions of
Sec.
23.905(d),
amendment 23-59.
------------------------------------------------------------------------
23.2405: ASTM F3264-17, section 8.2
23.2410: ASTM F3264-17, section 8.3, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3264-17, Section 8.3........................... 8.3 through
8.3.2: Same as
published in
F3264-17.
Renumber 8.3.3 to
8.3.6.
Add FAA 8.3.3
through 8.3.5,
and FAA 8.3.7:
8.3.3: ``F3063/
F3063M--16a
Standard
Specification
for Design and
Integration of
Fuel/Energy
Storage and
Delivery System
Installations
for
Aeroplanes''.
8.3.4: ``F3064/
F3064M--15
Standard
Specification
for Control,
Operational
Characteristi
cs and
Installation
of
Instruments
and Sensors
of Propulsion
Systems''.
8.3.5: ``F3065/
F3065M--15
Standard
Specification
for
Installation
and
Integration
of Propeller
System''.
8.3.7:
``F3117--15
Standard
Specification
for Crew
Interface in
Aircraft''.
------------------------------------------------------------------------
23.2415: ASTM F3264-17, section 8.4, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3264-17, Section 8.4........................... 8.4 through
8.4.1: Same as
published in
F3264-17.
Renumber 8.4.2 to
8.4.3.
Add FAA 8.4.2:
F3063/F3063M--
``16a Standard
Specification
for Design and
Integration of
Fuel/Energy
Storage and
Delivery System
Installations
for
Aeroplanes''.
ASTM F3066/F3066M-15, Section 5.1.................... An FAA-accepted
means of
compliance for
the induction
system ice
protection
aspects of Sec.
23.2415, such
as the
provisions of
Sec.
23.1093(a),
amendment 23-51.
ASTM F3066/F3066M-15, Section 5.2.1.1................ FAA 5.2.1.1:
``Operate
throughout its
flight power
range, including
minimum descent
idle speeds, in
the icing and
snow conditions
specified in
Specification
F3120/F3120M,
without the
accumulation of
ice on engine,
inlet system
components, or
airframe
components that
would do any of
the following:''
ASTM F3066/F3066M-15, Section 5.2.2.................. [Remove]
ASTM F3066/F3066M-15, Sections 5.2.3, 5.2.3.1, and FAA 5.2.2:
5.2.3.2. ``Each turbine
engine must idle
for 30 min on
the ground, with
the air bleed
available for
engine icing
protection at
its critical
condition,
without adverse
effect, in the
ground icing
conditions
specified in
Specification
F3120/F3120M.''
FAA 5.2.2.1
Followed by
momentary
operation at
takeoff power or
thrust.
FAA 5.2.2.2
During the 30
min of idle
operation, the
engine may be
run up
periodically to
a moderate power
or thrust
setting.''
------------------------------------------------------------------------
[[Page 21854]]
23.2420: ASTM F3264-17, section 8.5, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3264-17, Section 8.5........................... 8.5 through
8.5.1: Same as
published in
F3264-17.
Remove 8.5.2 and
8.5.3.
Add FAA 8.5.2:
F3065/F3065M--
``15 Standard
Specification
for Installation
and Integration
of Propeller
System''.
------------------------------------------------------------------------
23.2425: ASTM F3264-17, section 8.6, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3264-17, Section 8.6........................... 8.6 through
8.6.2: Same as
published in
F3264-17.
Renumber 8.6.3 to
8.6.4.
Add FAA 8.6.3 and
FAA 8.6.5:
8.6.3: ``F3065/
F3065M--15
Standard
Specification
for
Installation
and
Integration
of Propeller
System''.
8.6.5:
``F3117--15
Standard
Specification
for Crew
Interface in
Aircraft''.
------------------------------------------------------------------------
23.2430: ASTM F3264-17, section 8.7, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM F3264-17, Section 8.7........................... 8.7.1 through
8.7.5: Same as
published in
F3264-17.
Add an FAA-
accepted means
of compliance
for the fuel
supply aspects
of Sec.
23.2430, such as
the provisions
of Sec.
23.991(b),
amendment 23-43.
ASTM F3066/F3066M-15, Section 6.3.................... An FAA-accepted
means of
compliance for
the fuel/oil
tank aspects of
Sec. 23.2430,
such as the
provisions of
Sec.
23.967(d),
amendment 23-43.
------------------------------------------------------------------------
23.2435: ASTM F3264-17, section 8.8
23.2440: ASTM F3264-17, section 8.9, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM Section 8.9, F3264-17........................... 8.9 through
8.9.2: Same as
published in
F3264-17.
Renumber 8.9.3 to
8.9.4.
Renumber 8.9.4 to
8.9.5 and change
to, ``F3066/
F3066M-15
Standard
Specification
for Powerplant
Systems Specific
Hazard
Mitigation.''
Add FAA 8.9.3:
8.9.3: ``F3063/
F3063M-16a
Standard
Specification
for Design
and
Integration
of Fuel/
Energy
Storage and
Delivery
System
Installations
for
Aeroplanes.''
------------------------------------------------------------------------
Subpart F--Equipment
23.2500: ASTM F3264-17, section 9.1
23.2505: ASTM F3264-17, section 9.2
23.2510: ASTM F3264-17, section 9.3
23.2515: ASTM F3264-17, section 9.4
23.2520: ASTM F3264-17, section 9.5
23.2525: ASTM F3264-17, section 9.6
23.2530: ASTM F3264-17, section 9.7
23.2535: ASTM F3264-17, section 9.8
23.2540: ASTM F3264-17, section 9.9
23.2545: ASTM F3264-17, section 9.10
23.2550: ASTM F3061/F3061M-17, section 10.9
Subpart G--Flightcrew Interface and Other Information
23.2600: ASTM F3264-17, section 10.1, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM Section 10.1, F3264-17.......................... 10.1.1 through
10.1.5: Same as
published in
F3264-17.
Add an FAA-
accepted means
of compliance
for the
windshield
luminous
transmittance
aspects of Sec.
23.2600, such
as the
provisions of
Sec.
23.775(e),
amendment 23-49.
Add an FAA-
accepted means
of compliance
for the pilot
compartment view
with formation
of fog or frost
aspects of Sec.
23.2600, such
as the
provisions of
Sec.
23.773(b),
amendment 23-45.
------------------------------------------------------------------------
[[Page 21855]]
23.2605: ASTM F3264-17, section 10.2
23.2610: ASTM F3264-17, section 10.3
23.2615: ASTM F3264-17, section 10.4, combined with the changes in the
following table:
------------------------------------------------------------------------
Replace: With:
------------------------------------------------------------------------
ASTM Section 6, F3064/F3064M-15...................... An FAA-accepted
means of
compliance for
the powerplant
instruments
aspects of Sec.
23.2615, such
as the
provisions of
Sec. 23.1305,
amendment 23-52.
------------------------------------------------------------------------
23.2620: ASTM F3264-17, sections 5.15 and 10.5
Editorial, Reapproval, Revision Or Withdrawal
The FAA expects a suitable consensus standard to be reviewed
periodically. ASTM policy is that a consensus standard should be
reviewed in its entirety by the responsible subcommittee and must be
balloted for reapproval, revision, or withdrawal, within five years of
its last approval date. ASTM reapproves a standard--denoted by the year
of reapproval in parentheses (e.g., F2427-05a(2013))--to indicate
completion of a review cycle with no technical changes made to the
standard. ASTM issues editorial changes--denoted by a superscript
epsilon in the standard designation (F3235-17 [egr]\1\)--to correct
information that does not change the meaning or intent of a standard.
Any MOC accepted by this document that is based on a standard later
reapproved or editorially changed is also considered accepted without
the need for a NOA. ASTM revises a standard to make changes to its
technical content. Revisions to consensus standards serving as the
basis for MOC accepted by this document will not be automatically
accepted and will require further FAA acceptance in order for the
revisions to be an accepted MOC.
Availability
ASTM Standard F3264-17, ``Standard Specification for Normal
Category Aeroplanes Certification,'' is available for online reading at
https://www.astm.org/READINGLIBRARY/. ASTM International copyrights
these consensus standards and charges the public a fee for service.
Individual downloads or reprints of a standard (single or multiple
copies, or special compilations and other related technical
information) may be obtained through www.astm.org or by contacting ASTM
at (610) 832-9585 (phone), (610) 832-9555 (fax), or through
[email protected] (email). To inquire about consensus standard content
and/or membership or about ASTM Offices abroad, contact Joe Koury,
Staff Manager for Committee F44 on General Aviation: (610) 832-9804,
[email protected].
The FAA maintains a list of accepted MOCs on the FAA website at
https://www.faa.gov/aircraft/air_cert/design_approvals/small_airplanes/small_airplanes_regs/.
Issued in Kansas City, Missouri, on May 3, 2018.
Pat Mullen,
Manager, Small Airplanes Standards Branch, Aircraft Certification
Service.
[FR Doc. 2018-09990 Filed 5-10-18; 8:45 am]
BILLING CODE 4910-13-P
