Special Conditions: Aviation Technology Group (ATG), Inc.; Javelin Model 100 Series Airplane; Acrobatic Spins, 31969-31971 [E7-11152]
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31969
Rules and Regulations
Federal Register
Vol. 72, No. 111
Monday, June 11, 2007
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. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE254; Special Conditions No.
23–194–SC]
Special Conditions: Aviation
Technology Group (ATG), Inc.; Javelin
Model 100 Series Airplane; Acrobatic
Spins
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
rmajette on DSK8KYBLC1PROD with MISCELLANEOUS
SUMMARY: These special conditions are
issued 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 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.
DATES: Effective Date: May 29, 2007.
FOR FURTHER INFORMATION CONTACT:
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:
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 seeks
certification of the Javelin in both utility
and acrobatic categories. The
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Jkt 223001
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.
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
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
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.
The FAA did not intend 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.
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
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31970
Federal Register / Vol. 72, No. 111 / Monday, June 11, 2007 / Rules and Regulations
design feature, the special conditions
would also apply to the other model
under the provisions of § 21.101.
The authority citation for these
special conditions is as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704; 14 CFR 21.16 and 21.17 and
14 CFR 11.38 and 11.19.
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.
Discussion
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
appears to allow 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.
Discussion of Comments
A notice of proposed special
conditions No. 23–06–06–SC for the
Aviation Technology Group (ATG), Inc.;
Javelin Model 100 series airplanes was
published in the Federal Register on
February 1, 2007 (72 FR 4661). No
comments were received, and the
special conditions are adopted as
proposed.
Applicability
rmajette on DSK8KYBLC1PROD with MISCELLANEOUS
As discussed above, these special
conditions are applicable to the
Aviation Technology Group (ATG), Inc.;
Javelin Model 100 Series airplane.
Should Aviation Technology Group
apply at a later date for a change to the
type certificate to include another
model on the same type certificate
incorporating the same novel or unusual
design feature, the special conditions
would apply to that model as well.
Conclusion
This action affects only certain novel
or unusual design features on one model
series of airplane. It is not a rule of
general applicability.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and
symbols.
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12:20 Mar 07, 2011
Jkt 223001
The Special Conditions
■ Accordingly, pursuant to the authority
delegated to me by the Administrator,
the following special conditions are
issued 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 adopts 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)(6). 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.
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Sfmt 4700
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) If the applicant demonstrates that
it is impossible 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, the airplane is
considered to meet the requirements of
paragraph (c)(1) of this SC. The
demonstration must be conducted in
accordance with the following—
(i) Reduce the airplane speed using
pitch control at a rate of approximately
1 knot per second until the pitch control
reaches the stop; then, with the pitch
control pulled back and held against the
stop, apply full rudder control in a
manner to promote spin entry for a
period of 7 seconds or through a 360
degree heading change, whichever
occurs first. If the 360 degree heading
change is reached first, it must have
taken no fewer than 4 seconds. This
maneuver must be performed first with
the ailerons in the neutral position, and
then with the ailerons deflected
opposite the direction of turn in the
most adverse manner.
(ii) Power must be set in accordance
with § 23.201(e)(4) without change
during the maneuver. At the end of 7
seconds or a 360 degree heading change,
the airplane must respond immediately
and normally to primary flight controls
applied to regain coordinated, unstalled
flight without reversal of control effect
and without exceeding the temporary
control forces specified by § 23.143(c).
We believe that the above special
condition, which replaces § 23.221(c) in
its entirety, provides the level of safety
established for a part 23 airplane
certificated in the acrobatic category.
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Federal Register / Vol. 72, No. 111 / Monday, June 11, 2007 / Rules and Regulations
Issued in Kansas City, Missouri on May 29,
2007.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–11152 Filed 6–8–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27193; Directorate
Identifier 2007–CE–009–AD; Amendment
39–15091; AD 2007–12–13]
RIN 2120–AA64
Airworthiness Directives; Viking Air
Limited (Type Certificate No. A–806
Previously Held by deHavilland Inc.)
Models DHC–2 Mk. I, DHC–2 Mk. II, and
DHC–2 Mk. III Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
the products listed above. This AD
results from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
SUMMARY:
rmajette on DSK8KYBLC1PROD with MISCELLANEOUS
A report has been received of stress
corrosion cracking occurring in the wing lift
strut lower clevis fitting, part number C2W–
1097A.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective July
16, 2007.
On July 16, 2007 the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the 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:
George J. Duckett, Aerospace Engineer,
FAA, New York Aircraft Certification
Office, 10 Fifth Street, Valley Stream,
New York 11581; telephone: (516) 228–
7325; fax: (516) 794–5531.
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12:20 Mar 07, 2011
Jkt 223001
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. The streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This AD references the MCAI and
related service information that we
considered in forming the engineering
basis to correct the unsafe condition.
The AD contains text copied from the
MCAI and for this reason might not
follow our plain language principles.
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on March 22, 2007 (72 FR
13448) and proposed to supersede AD
88–08–02, Amendment 39–5889. That
NPRM proposed to correct an unsafe
condition for the specified products.
The MCAI states:
A report has been received of stress
corrosion cracking occurring in the wing lift
strut lower clevis fitting, part number C2W–
1097A.
This AD revision is being issued to allow
operators the option of continuing with the
existing inspection intervals in accordance
with CF–85–08R3 (Part A) or incorporating
the improved alternate inspection method in
accordance with Part B, to permit an increase
in inspection intervals.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
PO 00000
Frm 00003
Fmt 4700
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31971
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are highlighted in
a Note within the AD.
Costs of Compliance
We estimate that this AD will affect
392 products of U.S. registry. We also
estimate that it will take about 7 workhours per product to comply with basic
requirements of this AD. The average
labor rate is $80 per work-hour. Based
on these figures, we estimate the cost of
this AD to the U.S. operators to be
$219,520, or $560 per product.
In addition, we estimate that any
necessary follow-on actions will take
about 7 work-hours and require parts
costing $6,227 for each wing strut
assembly, for a cost of $6,787 per wing
strut assembly. We have no way of
determining the number of products
that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
E:\ERIC\11JNR1.SGM
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Agencies
[Federal Register Volume 72, Number 111 (Monday, June 11, 2007)]
[Rules and Regulations]
[Pages 31969-31971]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-11152]
========================================================================
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.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 72, No. 111 / Monday, June 11, 2007 / Rules
and Regulations
[[Page 31969]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE254; Special Conditions No. 23-194-SC]
Special Conditions: Aviation Technology Group (ATG), Inc.;
Javelin Model 100 Series Airplane; Acrobatic Spins
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued 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 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.
DATES: Effective Date: May 29, 2007.
FOR FURTHER INFORMATION CONTACT: 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:
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 seeks
certification of 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.
The FAA did not intend 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.
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
[[Page 31970]]
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.
Discussion
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 appears to allow 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.
Discussion of Comments
A notice of proposed special conditions No. 23-06-06-SC for the
Aviation Technology Group (ATG), Inc.; Javelin Model 100 series
airplanes was published in the Federal Register on February 1, 2007 (72
FR 4661). No comments were received, and the special conditions are
adopted as proposed.
Applicability
As discussed above, these special conditions are applicable to the
Aviation Technology Group (ATG), Inc.; Javelin Model 100 Series
airplane. Should Aviation Technology Group apply at a later date for a
change to the type certificate to include another model on the same
type certificate incorporating the same novel or unusual design
feature, the special conditions would apply to that model as well.
Conclusion
This action affects only certain novel or unusual design features
on one model series of airplane. It is not a rule of general
applicability.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and symbols.
0
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704; 14 CFR
21.16 and 21.17 and 14 CFR 11.38 and 11.19.
The Special Conditions
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the following special conditions are issued 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 adopts 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)(6). 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) If the applicant demonstrates that it is impossible 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, the airplane is
considered to meet the requirements of paragraph (c)(1) of this SC. The
demonstration must be conducted in accordance with the following--
(i) Reduce the airplane speed using pitch control at a rate of
approximately 1 knot per second until the pitch control reaches the
stop; then, with the pitch control pulled back and held against the
stop, apply full rudder control in a manner to promote spin entry for a
period of 7 seconds or through a 360 degree heading change, whichever
occurs first. If the 360 degree heading change is reached first, it
must have taken no fewer than 4 seconds. This maneuver must be
performed first with the ailerons in the neutral position, and then
with the ailerons deflected opposite the direction of turn in the most
adverse manner.
(ii) Power must be set in accordance with Sec. 23.201(e)(4)
without change during the maneuver. At the end of 7 seconds or a 360
degree heading change, the airplane must respond immediately and
normally to primary flight controls applied to regain coordinated,
unstalled flight without reversal of control effect and without
exceeding the temporary control forces specified by Sec. 23.143(c).
We believe that the above special condition, which replaces Sec.
23.221(c) in its entirety, provides the level of safety established for
a part 23 airplane certificated in the acrobatic category.
[[Page 31971]]
Issued in Kansas City, Missouri on May 29, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-11152 Filed 6-8-07; 8:45 am]
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