Special Conditions: Aviation Technology Group (ATG), Inc.; Javelin Model 100 Series Airplane; Acrobatic Spins, 4661-4663 [E7-1610]
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Federal Register / Vol. 72, No. 21 / Thursday, February 1, 2007 / Proposed Rules
(2) The comment proposes a change
or an addition to the rule, and it is
apparent that the rule would be
ineffective or unacceptable without
incorporation of the change or addition.
(3) The comment causes the NRC staff
to make a change (other than editorial)
to the CoC or Technical Specifications.
List of Subjects in 10 CFR Part 72
Administrative practice and
procedure, Criminal penalties,
Manpower training programs, Nuclear
materials, Occupational safety and
health, Penalties, Radiation protection,
Reporting and recordkeeping
requirements, Security measures, Spent
fuel, Whistleblowing.
For the reasons set out in the
preamble and under the authority of the
Atomic Energy Act of 1954, as amended;
the Energy Reorganization Act of 1974,
as amended; and 5 U.S.C. 553; the NRC
is proposing to adopt the following
amendments to 10 CFR part 72.
PART 72—LICENSING
REQUIREMENTS FOR THE
INDEPENDENT STORAGE OF SPENT
NUCLEAR FUEL, HIGH-LEVEL
RADIOACTIVE WASTE, AND
REACTOR-RELATED GREATER THAN
CLASS C WASTE
rmajette on PROD1PC67 with PROPOSALS
1. The authority citation for part 72
continues to read as follows:
Authority: Secs. 51, 53, 57, 62, 63, 65, 69,
81, 161, 182, 183, 184, 186, 187, 189, 68 Stat.
929, 930, 932, 933, 934, 935, 948, 953, 954,
955, as amended, sec. 234, 83 Stat. 444, as
amended (42 U.S.C. 2071, 2073, 2077, 2092,
2093, 2095, 2099, 2111, 2201, 2232, 2233,
2234, 2236, 2237, 2238, 2282); sec. 274, Pub.
L. 86–373, 73 Stat. 688, as amended (42
U.S.C. 2021); sec. 201, as amended, 202, 206,
88 Stat. 1242, as amended, 1244, 1246 (42
U.S.C. 5841, 5842, 5846); Pub. L. 95–601, sec.
10, 92 Stat. 2951 as amended by Pub. L. 102–
486, sec. 7902, 106 Stat. 3123 (42 U.S.C.
5851); sec. 102, Pub. L. 91–190, 83 Stat. 853
(42 U.S.C. 4332); secs. 131, 132, 133, 135,
137, 141, Pub. L. 97–425, 96 Stat. 2229, 2230,
2232, 2241, sec. 148, Pub. L. 100–203, 101
Stat. 1330–235 (42 U.S.C. 10151, 10152,
10153, 10155, 10157, 10161, 10168); sec.
1704, 112 Stat. 2750 (44 U.S.C. 3504 note);
sec. 651(e), Pub. L. 109–58, 119 Stat. 806–10
(42 U.S.C. 2014, 2021, 2021b, 2111).
Section 72.44(g) also issued under secs.
142(b) and 148(c), (d), Pub. L. 100–203, 101
Stat. 1330–232, 1330–236 (42 U.S.C.
10162(b), 10168(c),(d)). Section 72.46 also
issued under sec. 189, 68 Stat. 955 (42 U.S.C.
2239); sec. 134, Pub. L. 97–425, 96 Stat. 2230
(42 U.S.C. 10154). Section 72.96(d) also
issued under sec. 145(g), Pub. L. 100–203,
101 Stat. 1330–235 (42 U.S.C. 10165(g)).
Subpart J also issued under secs. 2(2), 2(15),
2(19), 117(a), 141(h), Pub. L. 97–425, 96 Stat.
2202, 2203, 2204, 2222, 2244 (42 U.S.C.
10101, 10137(a), 10161(h)). Subparts K and L
are also issued under sec. 133, 98 Stat. 2230
VerDate Aug<31>2005
15:30 Jan 31, 2007
Jkt 211001
(42 U.S.C. 10153) and sec. 218(a), 96 Stat.
2252 (42 U.S.C. 10198).
2. In § 72.214, Certificate of
Compliance 1004 is revised to read as
follows:
§ 72.214 List of approved spent fuel
storage casks.
*
*
*
*
*
Certificate Number: 1004.
Initial Certificate Effective Date:
January 23, 1995.
Amendment Number 1 Effective Date:
April 27, 2000.
Amendment Number 2 Effective Date:
September 5, 2000.
Amendment Number 3 Effective Date:
September 12, 2001.
Amendment Number 4 Effective Date:
February 12, 2002.
Amendment Number 5 Effective Date:
January 7, 2004.
Amendment Number 6 Effective Date:
December 22, 2003.
Amendment Number 7 Effective Date:
March 2, 2004.
Amendment Number 8 Effective Date:
December 5, 2005.
Amendment Number 9 Effective Date:
April 17, 2007.
SAR Submitted by: Transnuclear, Inc.
SAR Title: Final Safety Analysis
Report for the Standardized NUHOMS
Horizontal Modular Storage System for
Irradiated Nuclear Fuel.
Docket Number: 72–1004.
Certificate Expiration Date: January
23, 2015.
Model Number: NUHOMS–24P,
–52B, –61BT, –32PT, –24PHB, and
–24PTH.
*
*
*
*
*
Dated at Rockville, Maryland, this 19th day
of January, 2007.
For the Nuclear Regulatory Commission.
Luis A. Reyes,
Executive Director for Operations.
[FR Doc. E7–1643 Filed 1–31–07; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE254; Notice No. 23–06–06–
SC]
Special Conditions: Aviation
Technology Group (ATG), Inc.; Javelin
Model 100 Series Airplane; Acrobatic
Spins
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed special
conditions.
AGENCY:
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
4661
SUMMARY: This notice proposes special
conditions for the Aviation Technology
Group (ATG) Javelin Model 100 Series
airplane. This airplane will have a novel
or unusual design feature(s) associated
with acrobatic spin recovery
requirements. The applicable
airworthiness regulations do not contain
adequate or appropriate safety standards
for this design feature. These proposed
special conditions contain the
additional safety standards that the
Administrator considers necessary to
establish a level of safety equivalent to
that established by the existing
airworthiness standards applicable to
these airplanes.
DATES: Comments must be received on
or before March 5, 2007.
ADDRESSES: Comments on these
proposed special conditions may be
mailed in duplicate to: Federal Aviation
Administration, Regional Counsel,
ACE–7, Attention: Rules Docket CE254,
901 Locust, Room 506, Kansas City,
Missouri 64106; or delivered in
duplicate to the Regional Counsel at the
above address. Comments must be
marked: CE254. Comments may be
inspected in the Rules Docket
weekdays, except Federal holidays,
between 7:30 a.m. and 4 p.m.
FOR FURTHER INFORMATION CONTACT: J.
Lowell Foster, Federal Aviation
Administration, Aircraft Certification
Service, Small Airplane Directorate,
ACE–111, 901 Locust, Room 301,
Kansas City, Missouri, 816–329–4125,
fax 816–329–4090.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to
participate in the making of these
proposed special conditions by
submitting such written data, views, or
arguments as they may desire.
Communications should identify the
regulatory docket or notice number and
be submitted in duplicate to the address
specified above. All communications
received on or before the closing date
for comments will be considered by the
Administrator. The proposals described
in this notice may be changed in light
of the comments received. All
comments received will be available in
the Rules Docket for examination by
interested persons, both before and after
the closing date for comments. A report
summarizing each substantive public
contact with FAA personnel concerning
this rulemaking will be filed in the
docket. Persons wishing the FAA to
acknowledge receipt of their comments
submitted in response to this notice
must include with those comments a
self-addressed, stamped postcard on
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Federal Register / Vol. 72, No. 21 / Thursday, February 1, 2007 / Proposed Rules
which the following statement is made:
‘‘Comments to Docket No. CE254.’’ The
postcard will be date stamped and
returned to the commenter.
rmajette on PROD1PC67 with PROPOSALS
Background
On February 15, 2005, Aviation
Technology Group (ATG); 8001 South
InterPort Boulevard, Suite 310;
Englewood, Colorado 80112–5951,
applied for a type certificate for their
new Model 100 airplane. ATG intends
to certificate the Javelin in both utility
and acrobatic categories. The
preliminary design includes the
following features:
• Two-place, tandem configuration.
• Maximum takeoff weight of
approximately 6,900 pounds.
• Design cruise speed of 500 knots
calibrated airspeed.
• Two Williams FJ33–4A–18M
turbofan engines with dual channel
FADEC controls.
• Major airframe components
constructed of carbon fiber composite
materials.
• Hydraulically boosted flight control
system with floor-mounted control
sticks.
• Integrated avionics including
electronic displays, autopilot, and flight
management system.
Title 14 CFR, part 23, § 23.221
contains spin requirements for normal,
utility, and acrobatic category airplanes.
When part 3 of the Civil Air Regulations
was recodified in 1965 as 14 CFR, part
23, spin requirements for acrobatic
category airplanes were presented in
§ 23.221(c). Since 1965, the spin
requirements in § 23.221(c) have been
amended three times.
The original version of § 23.221(c)
required an acrobatic category airplane
to perform spins of at least six turns and
recover without exceeding an airspeed
limit or positive load factor limit. Spins
were required for flaps-up configuration
and flaps-down configuration. In
addition, the airplane could not enter an
uncontrollable spin with any use of the
controls.
Amendment 23–7 revised the
presentation of the acrobatic category
spin requirements and revised the
minimum turn requirement to six turns
or three seconds, whichever takes
longer. Amendment 23–42 revised
§ 23.221(c)(3) and clarified the term
‘‘controls’’ in the previous version of the
rule by identifying flight controls and
engine controls. It also clarified that the
use of the controls could be at spin
entry or during the spin. Neither of
these two amendments changed the
basic acrobatic category spin
requirements.
VerDate Aug<31>2005
15:30 Jan 31, 2007
Jkt 211001
In July 1994, the FAA proposed
changes to the flight airworthiness
standards for normal, utility, acrobatic,
and commuter category airplanes. The
proposals arose from the joint effort of
the FAA and the European Joint
Aviation Authorities (JAA) to harmonize
14 CFR regulations and the Joint
Aviation Requirements (JAR). The
proposed changes were intended to
provide nearly uniform flight
airworthiness standards for airplanes
certificated in the United States under
14 CFR, part 23 and in the JAA
countries under JAR 23.
Proposed changes to the introductory
paragraph of § 23.221(c) required
acrobatic category airplanes to meet the
one-turn spin requirements of
§ 23.221(a) as well as the emergency
egress requirements of § 23.807, and to
meet the spin requirements of
§§ 23.221(c)(1) through (4) in each
configuration approved for spins. The
addition of normal category spin
requirements was necessary because
acrobatic category airplanes should have
sufficient controllability to recover from
the developing one-turn spin under the
same conditions as normal category
airplanes. The configuration
requirement was added to recognize the
common practice of approving
intentional spins only for a specific
configuration (e.g, gear and flaps up).
The proposed changes were
incorporated into the rule by
Amendment 23–50.
There was never any discussion or
intent by the FAA or JAA to approve an
acrobatic category airplane that met
only the normal category spin
requirements. The assumption has
always been that an inadvertent spin
could result during the performance of
a variety of acrobatic maneuvers.
FAA Position
Title 14 CFR, part 23, § 23.221(c), as
amended by Amendment 23–50,
presents acrobatic category airplane
spin requirements. As the rule is
currently written, the acrobatic category
airplane must comply with normal
category spin requirements, acrobatic
category emergency egress requirements
in § 23.807, and acrobatic spin
requirements for each configuration
requested for spin approval.
ATG proposes to prohibit intentional
spins and requests that no configuration
be approved for spins. This proposal
leads to an acrobatic category airplane
that meets only normal category spin
requirements. This proposal is
unacceptable since the FAA has always
maintained that an acrobatic category
airplane must comply with acrobatic
category spin requirements despite the
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
wording in the current rule. The rule’s
history, coupled with preamble
information for Amendment 23–50,
reveals that the rule was changed to add
the normal category spin requirements
and to accommodate an applicant’s
desire to comply with the acrobatic spin
requirements for at least one
configuration, but not necessarily all
configurations.
Type Certification Basis
Under the provisions of 14 CFR, part
21, § 21.17, ATG must show that the
Model 100 meets the applicable
provisions of part 23, as amended by
Amendment 23–1 through 23–55
thereto. If the Administrator finds that
the applicable airworthiness regulations
(i.e., 14 CFR, part 23) do not contain
adequate or appropriate safety standards
for the ATG Model 100 series because
of a novel or unusual design feature,
special conditions are prescribed under
the provisions of § 21.16.
Special conditions, as appropriate, as
defined in § 11.19, are issued in
accordance with § 11.38, and become
part of the type certification basis in
accordance with § 21.17.
Special conditions are initially
applicable to the model for which they
are issued. Should the type certificate
for that model be amended later to
include any other model that
incorporates the same novel or unusual
design feature, the special conditions
would also apply to the other model
under the provisions of § 21.101.
Novel or Unusual Design Features
The ATG Model 100 will incorporate
the following novel or unusual design
features: High thrust-to-weight ratio,
military training jet configuration with a
higher fuselage mass compared to
typical part 23 acrobatic airplanes.
Applicability
As discussed above, these special
conditions are applicable to the ATG
Model 100 series. Should ATG apply at
a later date for a change to the type
certificate to include another model
incorporating the same novel or unusual
design feature, the special conditions
would apply to that model as well
under the provisions of § 21.101.
Conclusion
This action affects only certain novel
or unusual design features on the ATG
Model 100 series airplanes. It is not a
rule of general applicability and affects
only the applicant who applied to the
FAA for approval of these features on
the airplane.
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Federal Register / Vol. 72, No. 21 / Thursday, February 1, 2007 / Proposed Rules
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and
symbols.
Citation
The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113 and
44701; 14 CFR 21.16 and 21.17; and 14 CFR
11.38 and 11.19.
rmajette on PROD1PC67 with PROPOSALS
The Special Conditions
Accordingly, the Federal Aviation
Administration (FAA) proposes the
following special conditions as part of
the type certification basis for the ATG
Model 100 airplanes.
Title 14 CFR, part 23, § 23.221(c) as
amended by Amendment 23–50
presents acrobatic category airplane
spin requirements. As the rule is
currently written, the acrobatic category
airplane must comply with normal
category spin requirements, acrobatic
category emergency egress requirements
in § 23.807, and acrobatic spin
requirements for each configuration
requested for spin approval.
ATG proposes to prohibit intentional
spins and requests that no configuration
be approved for spins. This proposal
leads to an acrobatic category airplane
that meets only normal category spin
requirements. This proposal is
unacceptable since the FAA has always
maintained that an acrobatic category
airplane must comply with acrobatic
category spin requirements despite the
wording in the current rule. The rule’s
history coupled with preamble
information for Amendment 23–50
reveals that the rule was changed to add
the normal category spin requirements
and to accommodate an applicant’s
desire to comply with the acrobatic spin
requirements for at least one
configuration, but not necessarily all
configurations.
Since the wording of the current rule
combined with ATG’s proposal does not
provide the level of safety envisioned
for an acrobatic category airplane, the
FAA proposes the following special
condition under the authority of 14
CFR, part 21, § 21.16 to replace
§ 23.221(c) in its entirety:
SC 23.221 Spinning
(c) Acrobatic category airplanes. An
acrobatic category airplane must meet
the spin requirements of paragraph (a)
of this section and § 23.807(b)(5). In
addition, the following requirements
must be met in an applicant-designated
acrobatic configuration, and in each
other configuration for which approval
for spinning is requested:
(1) The airplane must recover from
any point in a spin up to and including
VerDate Aug<31>2005
15:30 Jan 31, 2007
Jkt 211001
six turns, or any greater number of turns
for which certification is requested, in
not more than one and one-half
additional turns after initiation of the
first control action for recovery.
However, beyond three turns, the spin
may be discontinued if spiral
characteristics appear.
(2) The applicable airspeed limits and
limit maneuvering load factors must not
be exceeded. For flaps extended
configurations for which approval is
requested, the flaps must not be
retracted during the recovery.
(3) It must be impossible to obtain
unrecoverable spins with any use of the
flight or engine power controls either at
the entry into or during the spin.
(4) There must be no characteristics
during the spin (such as excessive rates
of rotation or extreme oscillatory
motion) that might prevent a successful
recovery due to disorientation or
incapacitation of the pilot.
(5) The airplane is considered to meet
the requirements of paragraph (c) of this
special condition with a specific
demonstration. The applicant must
demonstrate that it is extremely remote
for the airplane in the applicantdesignated acrobatic configuration, and
in each other configuration for which
approval for spinning is requested, to
enter a spin with any use of the flight
or engine power controls, either at or
after entry into the stall maneuver.
Issued in Kansas City, Missouri on January
24, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–1610 Filed 1–31–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26498; Directorate
Identifier 2006–CE–83–AD]
RIN 2120–AA64
Airworthiness Directives; The Cessna
Aircraft Company Models 208 and
208B Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2006–06–
06, which applies to certain Cessna
Aircraft Company (Cessna) Models 208
SUMMARY:
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
4663
and 208B airplanes. AD 2006–06–06
currently requires you to incorporate
information into the applicable section
of the Airplane Flight Manual (AFM)
and Pilot’s Operating Handbook (POH)
and requires installation of placards.
Since we issued AD 2006–06–06,
Cessna issued further revisions to the
AFM Supplement S1 ‘‘Known Icing
Equipment’’ and developed a low
airspeed awareness system.
Consequently, this proposed AD would
require you to incorporate the AFM
Supplement revisions, to install the low
airspeed awareness system, and to
retain the requirements of AD 2006–06–
06 until the above requirements are
incorporated. We are proposing this AD
to assure that the pilot has enough
information and the necessary
equipment to prevent loss of control of
the airplane while in flight during icing
conditions.
DATES: We must receive comments on
this proposed AD by March 5, 2007.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
For service information identified in
this proposed AD, contact The Cessna
Aircraft Company, Product Support,
P.O. Box 7706, Wichita, Kansas 67277.
FOR FURTHER INFORMATION CONTACT:
Robert P. Busto, Aerospace Engineer,
Wichita Aircraft Certification Office,
FAA, 1801 Airport Road, Wichita,
Kansas 67209; telephone: (316) 946–
4157; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
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]]>Agencies
[Federal Register Volume 72, Number 21 (Thursday, February 1, 2007)]
[Proposed Rules]
[Pages 4661-4663]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-1610]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE254; Notice No. 23-06-06-SC]
Special Conditions: Aviation Technology Group (ATG), Inc.;
Javelin Model 100 Series Airplane; Acrobatic Spins
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed special conditions.
-----------------------------------------------------------------------
SUMMARY: This notice proposes special conditions for the Aviation
Technology Group (ATG) Javelin Model 100 Series airplane. This airplane
will have a novel or unusual design feature(s) associated with
acrobatic spin recovery requirements. The applicable airworthiness
regulations do not contain adequate or appropriate safety standards for
this design feature. These proposed special conditions contain the
additional safety standards that the Administrator considers necessary
to establish a level of safety equivalent to that established by the
existing airworthiness standards applicable to these airplanes.
DATES: Comments must be received on or before March 5, 2007.
ADDRESSES: Comments on these proposed special conditions may be mailed
in duplicate to: Federal Aviation Administration, Regional Counsel,
ACE-7, Attention: Rules Docket CE254, 901 Locust, Room 506, Kansas
City, Missouri 64106; or delivered in duplicate to the Regional Counsel
at the above address. Comments must be marked: CE254. Comments may be
inspected in the Rules Docket weekdays, except Federal holidays,
between 7:30 a.m. and 4 p.m.
FOR FURTHER INFORMATION CONTACT: J. Lowell Foster, Federal Aviation
Administration, Aircraft Certification Service, Small Airplane
Directorate, ACE-111, 901 Locust, Room 301, Kansas City, Missouri, 816-
329-4125, fax 816-329-4090.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of
these proposed special conditions by submitting such written data,
views, or arguments as they may desire. Communications should identify
the regulatory docket or notice number and be submitted in duplicate to
the address specified above. All communications received on or before
the closing date for comments will be considered by the Administrator.
The proposals described in this notice may be changed in light of the
comments received. All comments received will be available in the Rules
Docket for examination by interested persons, both before and after the
closing date for comments. A report summarizing each substantive public
contact with FAA personnel concerning this rulemaking will be filed in
the docket. Persons wishing the FAA to acknowledge receipt of their
comments submitted in response to this notice must include with those
comments a self-addressed, stamped postcard on
[[Page 4662]]
which the following statement is made: ``Comments to Docket No.
CE254.'' The postcard will be date stamped and returned to the
commenter.
Background
On February 15, 2005, Aviation Technology Group (ATG); 8001 South
InterPort Boulevard, Suite 310; Englewood, Colorado 80112-5951, applied
for a type certificate for their new Model 100 airplane. ATG intends to
certificate the Javelin in both utility and acrobatic categories. The
preliminary design includes the following features:
Two-place, tandem configuration.
Maximum takeoff weight of approximately 6,900 pounds.
Design cruise speed of 500 knots calibrated airspeed.
Two Williams FJ33-4A-18M turbofan engines with dual
channel FADEC controls.
Major airframe components constructed of carbon fiber
composite materials.
Hydraulically boosted flight control system with floor-
mounted control sticks.
Integrated avionics including electronic displays,
autopilot, and flight management system.
Title 14 CFR, part 23, Sec. 23.221 contains spin requirements for
normal, utility, and acrobatic category airplanes. When part 3 of the
Civil Air Regulations was recodified in 1965 as 14 CFR, part 23, spin
requirements for acrobatic category airplanes were presented in Sec.
23.221(c). Since 1965, the spin requirements in Sec. 23.221(c) have
been amended three times.
The original version of Sec. 23.221(c) required an acrobatic
category airplane to perform spins of at least six turns and recover
without exceeding an airspeed limit or positive load factor limit.
Spins were required for flaps-up configuration and flaps-down
configuration. In addition, the airplane could not enter an
uncontrollable spin with any use of the controls.
Amendment 23-7 revised the presentation of the acrobatic category
spin requirements and revised the minimum turn requirement to six turns
or three seconds, whichever takes longer. Amendment 23-42 revised Sec.
23.221(c)(3) and clarified the term ``controls'' in the previous
version of the rule by identifying flight controls and engine controls.
It also clarified that the use of the controls could be at spin entry
or during the spin. Neither of these two amendments changed the basic
acrobatic category spin requirements.
In July 1994, the FAA proposed changes to the flight airworthiness
standards for normal, utility, acrobatic, and commuter category
airplanes. The proposals arose from the joint effort of the FAA and the
European Joint Aviation Authorities (JAA) to harmonize 14 CFR
regulations and the Joint Aviation Requirements (JAR). The proposed
changes were intended to provide nearly uniform flight airworthiness
standards for airplanes certificated in the United States under 14 CFR,
part 23 and in the JAA countries under JAR 23.
Proposed changes to the introductory paragraph of Sec. 23.221(c)
required acrobatic category airplanes to meet the one-turn spin
requirements of Sec. 23.221(a) as well as the emergency egress
requirements of Sec. 23.807, and to meet the spin requirements of
Sec. Sec. 23.221(c)(1) through (4) in each configuration approved for
spins. The addition of normal category spin requirements was necessary
because acrobatic category airplanes should have sufficient
controllability to recover from the developing one-turn spin under the
same conditions as normal category airplanes. The configuration
requirement was added to recognize the common practice of approving
intentional spins only for a specific configuration (e.g, gear and
flaps up). The proposed changes were incorporated into the rule by
Amendment 23-50.
There was never any discussion or intent by the FAA or JAA to
approve an acrobatic category airplane that met only the normal
category spin requirements. The assumption has always been that an
inadvertent spin could result during the performance of a variety of
acrobatic maneuvers.
FAA Position
Title 14 CFR, part 23, Sec. 23.221(c), as amended by Amendment 23-
50, presents acrobatic category airplane spin requirements. As the rule
is currently written, the acrobatic category airplane must comply with
normal category spin requirements, acrobatic category emergency egress
requirements in Sec. 23.807, and acrobatic spin requirements for each
configuration requested for spin approval.
ATG proposes to prohibit intentional spins and requests that no
configuration be approved for spins. This proposal leads to an
acrobatic category airplane that meets only normal category spin
requirements. This proposal is unacceptable since the FAA has always
maintained that an acrobatic category airplane must comply with
acrobatic category spin requirements despite the wording in the current
rule. The rule's history, coupled with preamble information for
Amendment 23-50, reveals that the rule was changed to add the normal
category spin requirements and to accommodate an applicant's desire to
comply with the acrobatic spin requirements for at least one
configuration, but not necessarily all configurations.
Type Certification Basis
Under the provisions of 14 CFR, part 21, Sec. 21.17, ATG must show
that the Model 100 meets the applicable provisions of part 23, as
amended by Amendment 23-1 through 23-55 thereto. If the Administrator
finds that the applicable airworthiness regulations (i.e., 14 CFR, part
23) do not contain adequate or appropriate safety standards for the ATG
Model 100 series because of a novel or unusual design feature, special
conditions are prescribed under the provisions of Sec. 21.16.
Special conditions, as appropriate, as defined in Sec. 11.19, are
issued in accordance with Sec. 11.38, and become part of the type
certification basis in accordance with Sec. 21.17.
Special conditions are initially applicable to the model for which
they are issued. Should the type certificate for that model be amended
later to include any other model that incorporates the same novel or
unusual design feature, the special conditions would also apply to the
other model under the provisions of Sec. 21.101.
Novel or Unusual Design Features
The ATG Model 100 will incorporate the following novel or unusual
design features: High thrust-to-weight ratio, military training jet
configuration with a higher fuselage mass compared to typical part 23
acrobatic airplanes.
Applicability
As discussed above, these special conditions are applicable to the
ATG Model 100 series. Should ATG apply at a later date for a change to
the type certificate to include another model incorporating the same
novel or unusual design feature, the special conditions would apply to
that model as well under the provisions of Sec. 21.101.
Conclusion
This action affects only certain novel or unusual design features
on the ATG Model 100 series airplanes. It is not a rule of general
applicability and affects only the applicant who applied to the FAA for
approval of these features on the airplane.
[[Page 4663]]
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and symbols.
Citation
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and
21.17; and 14 CFR 11.38 and 11.19.
The Special Conditions
Accordingly, the Federal Aviation Administration (FAA) proposes the
following special conditions as part of the type certification basis
for the ATG Model 100 airplanes.
Title 14 CFR, part 23, Sec. 23.221(c) as amended by Amendment 23-
50 presents acrobatic category airplane spin requirements. As the rule
is currently written, the acrobatic category airplane must comply with
normal category spin requirements, acrobatic category emergency egress
requirements in Sec. 23.807, and acrobatic spin requirements for each
configuration requested for spin approval.
ATG proposes to prohibit intentional spins and requests that no
configuration be approved for spins. This proposal leads to an
acrobatic category airplane that meets only normal category spin
requirements. This proposal is unacceptable since the FAA has always
maintained that an acrobatic category airplane must comply with
acrobatic category spin requirements despite the wording in the current
rule. The rule's history coupled with preamble information for
Amendment 23-50 reveals that the rule was changed to add the normal
category spin requirements and to accommodate an applicant's desire to
comply with the acrobatic spin requirements for at least one
configuration, but not necessarily all configurations.
Since the wording of the current rule combined with ATG's proposal
does not provide the level of safety envisioned for an acrobatic
category airplane, the FAA proposes the following special condition
under the authority of 14 CFR, part 21, Sec. 21.16 to replace Sec.
23.221(c) in its entirety:
SC 23.221 Spinning
(c) Acrobatic category airplanes. An acrobatic category airplane
must meet the spin requirements of paragraph (a) of this section and
Sec. 23.807(b)(5). In addition, the following requirements must be met
in an applicant-designated acrobatic configuration, and in each other
configuration for which approval for spinning is requested:
(1) The airplane must recover from any point in a spin up to and
including six turns, or any greater number of turns for which
certification is requested, in not more than one and one-half
additional turns after initiation of the first control action for
recovery. However, beyond three turns, the spin may be discontinued if
spiral characteristics appear.
(2) The applicable airspeed limits and limit maneuvering load
factors must not be exceeded. For flaps extended configurations for
which approval is requested, the flaps must not be retracted during the
recovery.
(3) It must be impossible to obtain unrecoverable spins with any
use of the flight or engine power controls either at the entry into or
during the spin.
(4) There must be no characteristics during the spin (such as
excessive rates of rotation or extreme oscillatory motion) that might
prevent a successful recovery due to disorientation or incapacitation
of the pilot.
(5) The airplane is considered to meet the requirements of
paragraph (c) of this special condition with a specific demonstration.
The applicant must demonstrate that it is extremely remote for the
airplane in the applicant-designated acrobatic configuration, and in
each other configuration for which approval for spinning is requested,
to enter a spin with any use of the flight or engine power controls,
either at or after entry into the stall maneuver.
Issued in Kansas City, Missouri on January 24, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-1610 Filed 1-31-07; 8:45 am]
BILLING CODE 4910-13-P
