Special Conditions; Garmin International, Inc.; Raytheon Model C90A King Air; Protection of Electronic Flight Instrument System from the Effects of High Intensity Radiated Fields (HIRF), 58735-58738 [E6-16497]
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58735
Rules and Regulations
Federal Register
Vol. 71, No. 193
Thursday, October 5, 2006
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 AGRICULTURE
Animal and Plant Health Inspection
Service
7 CFR Parts 360 and 361
[Docket No. APHIS–2006–0019]
Noxious Weeds; South African
Ragwort and Madagascar Ragwort
Animal and Plant Health
Inspection Service, USDA.
ACTION: Affirmation of interim rule as
final rule.
AGENCY:
We are adopting as a final
rule, without change, an interim rule
that amended the noxious weed and
imported seed regulations by adding
South African ragwort (Senecio
inaequidens DC.) and Madagascar
ragwort (Senecio madagascariensis
Poir.) to the list of terrestrial noxious
weeds and to the list of seeds with no
tolerances applicable to their
introduction. That action was necessary
to prevent the artificial spread of these
noxious weeds into the United States.
DATES: Effective on October 5, 2006, we
are adopting as a final rule the interim
rule published at 71 FR 35378–35381,
June 20, 2006.
FOR FURTHER INFORMATION CONTACT: Dr.
Alan V. Tasker, Noxious Weeds Program
Coordinator, Invasive Species and Pest
Management, PPQ, APHIS, 4700 River
Road Unit 134, Riverdale, MD 20737–
1237; (301) 734–5225.
SUPPLEMENTARY INFORMATION:
SUMMARY:
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Background
The Plant Protection Act (7 U.S.C.
7701 et seq.) authorizes the Secretary of
Agriculture to prohibit or restrict the
importation, entry, exportation, or
movement in interstate commerce of
any plant, plant product, biological
control organism, noxious weed, article,
or means of conveyance if the Secretary
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15:35 Oct 04, 2006
Jkt 211001
determines that the prohibition or
restriction is necessary to prevent the
introduction of a plant pest or noxious
weed into the United States or the
dissemination of a plant pest or noxious
weed within the United States.
In an interim rule 1 effective June 14,
2006, and published in the Federal
Register on June 20, 2006 (71 FR 35378–
35381, Docket No. APHIS–2006–0019),
we amended the noxious weed and
imported seed regulations by adding
South African ragwort (Senecio
inaequidens DC.) and Madagascar
ragwort (Senecio madagascariensis
Poir.) to the list in § 360.200(c) of
terrestrial noxious weeds and to the list
in § 361.6(a)(1) of seeds with no
tolerances applicable to their
introduction. That action was necessary
to prevent the artificial spread of South
African ragwort and Madagascar ragwort
into the United States.
Comments on the interim rule were
required to be received on or before
August 21, 2006. We did not receive any
comments. Therefore, for the reasons
given in the interim rule, we are
adopting the interim rule as a final rule.
This action also affirms the
information contained in the interim
rule concerning Executive Order 12866
and the Regulatory Flexibility Act,
Executive Order 12988, and the
Paperwork Reduction Act.
Further, for this action, the Office of
Management and Budget has waived its
review under Executive Order 12866.
List of Subjects
7 CFR Part 360
Imports, Plants (Agriculture),
Quarantine, Reporting and
recordkeeping requirements,
Transportation, Weeds.
7 CFR Part 361
Agricultural commodities, Imports,
Labeling, Quarantine, Reporting and
recordkeeping requirements, Seeds,
Vegetables, Weeds.
1 To view the interim rule, go to https://
www.regulations.gov, click on the ‘‘Advanced
Search’’ tab, and select ‘‘Docket Search.’’ In the
Docket ID field, enter APHIS–2006–0019, then click
on ‘‘Submit.’’ Clicking on the Docket ID link in the
search results page will produce a list of all
documents in the docket.
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PART 360—NOXIOUS WEED
REGULATIONS
PART 361—IMPORTATION OF SEED
AND SCREENINGS UNDER THE
FEDERAL SEED ACT
Accordingly, we are adopting as a
final rule, without change, the interim
rule that amended 7 CFR parts 360 and
361 and that was published at 71 FR
35378–35381 on June 20, 2006.
I
Done in Washington, DC, this 29th day of
September 2006.
Kevin Shea,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. E6–16462 Filed 10–4–06; 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE260, Special Condition 23–
200–SC]
Special Conditions; Garmin
International, Inc.; Raytheon Model
C90A King Air; Protection of Electronic
Flight Instrument System from the
Effects of High Intensity Radiated
Fields (HIRF)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions; request
for comments.
AGENCY:
SUMMARY: These special conditions are
issued to Garmin International Inc.,
1200 East 151st Street, Olathe, Kansas,
66062, for a Supplemental Type
Certificate for the Raytheon Model C90A
King Air airplane. This airplane will
have novel and unusual design features
when compared to the state of
technology envisaged in the applicable
airworthiness standards. These novel
and unusual design features include the
installation of electronic flight
instrument system (EFIS) displays in the
Garmin G1000 system, GFC 700
autopilot, Mid-Continent Instrument
Attitude Indicator and Sandia Avionics
cooling fans. The applicable regulations
do not contain adequate or appropriate
airworthiness standards for the
protection of these systems from the
effects of high intensity radiated fields
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Federal Register / Vol. 71, No. 193 / Thursday, October 5, 2006 / Rules and Regulations
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(HIRF). These special conditions
contain the additional safety standards
that the Administrator considers
necessary to establish a level of safety
equivalent to the airworthiness
standards applicable to these airplanes.
DATES: The effective date of these
special conditions is September 27,
2006. Comments must be received on or
before November 6, 2006.
ADDRESSES: Comments may be mailed
in duplicate to: Federal Aviation
Administration, Regional Counsel,
ACE–7, Attention: Rules Docket Clerk,
Docket No. CE260, Room 506, 901
Locust, Kansas City, Missouri 64106. All
comments must be marked: Docket No.
CE260. 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: Jim
Brady, Aerospace Engineer, Standards
Office (ACE–111), Small Airplane
Directorate, Aircraft Certification
Service, Federal Aviation
Administration, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone
(816) 329–4132.
SUPPLEMENTARY INFORMATION: The FAA
has determined that notice and
opportunity for prior public comment
hereon are impracticable because these
procedures would significantly delay
issuance of the approval design and
thus delivery of the affected aircraft. In
addition, the substance of these special
conditions has been subject to the
public comment process in several prior
instances with no substantive comments
received. The FAA, therefore, finds that
good cause exists for making these
special conditions effective upon
issuance.
Comments Invited
Interested persons are invited to
submit 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 special conditions
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. Commenters wishing the FAA to
acknowledge receipt of their comments
submitted in response to this notice
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15:35 Oct 04, 2006
Jkt 211001
must include a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. CE260.’’ The postcard will
be date stamped and returned to the
commenter.
Background
On June 2, 2006, Garmin
International, Inc., 1200 East 151st
Street, Olathe, Kansas, 66062, applied to
the FAA for a new Supplemental Type
Certificate for the Raytheon Model C90A
King Air airplane. The C90A King Air
is currently approved under TC No.
3A20, Revision 62 dated December 7,
2005. The proposed modification
incorporates a novel or unusual design
feature, such as digital avionics
consisting of an EFIS that is vulnerable
to HIRF external to the airplane.
Type Certification Basis
Under the provisions of 14 CFR, part
21, § 21.101, Garmin International, Inc.,
must show that the Raytheon Model
C90A King Air aircraft as changed
continues to meet the following
provisions, or the applicable regulations
in effect on the date of application for
the change to the Raytheon Model C90A
King Air as specified on Type
Certification Data Sheet TCDS No.
3A20, revision 62, dated December 7,
2005.
Discussion
If the Administrator finds that the
applicable airworthiness standards do
not contain adequate or appropriate
safety standards because of novel or
unusual design features of an airplane,
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 after public
notice and become part of the type
certification basis in accordance with
§ 21.101(b)(2).
Special conditions are initially
applicable to the model for which they
are issued. Should the applicant apply
for a supplemental type certificate to
modify any other model already
included on the same type certificate to
incorporate 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
Garmin International, Inc. plans to
incorporate certain novel and unusual
design features into an airplane for
which the airworthiness standards do
not contain adequate or appropriate
safety standards for protection from the
effects of HIRF. These features include
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Frm 00002
Fmt 4700
Sfmt 4700
EFIS as part of the Garmin G1000
system. Additionally, the Garmin GFC
700 autopilot, Mid-Continent
Instrument Attitude Indicator and
Sandia Avionics Cooling Fans, which
are susceptible to the HIRF
environment, are included and were not
envisaged by the existing regulations for
this type of airplane.
Protection of Systems From High
Intensity Radiated Fields (HIRF)
Recent advances in technology have
given rise to the application in aircraft
designs of advanced electrical and
electronic systems that perform
functions required for continued safe
flight and landing. Due to the use of
sensitive solid state advanced
components in analog and digital
electronics circuits, these advanced
systems are readily responsive to the
transient effects of induced electrical
current and voltage caused by the HIRF.
The HIRF can degrade electronic
systems performance by damaging
components or upsetting system
functions.
Furthermore, the HIRF environment
has undergone a transformation that was
not foreseen when the current
requirements were developed. Higher
energy levels are radiated from
transmitters that are used for radar,
radio, and television. Also, the number
of transmitters has increased
significantly. There is also uncertainty
concerning the effectiveness of airframe
shielding for HIRF. Furthermore,
coupling to cockpit-installed equipment
through the cockpit window apertures is
undefined.
The combined effect of the
technological advances in airplane
design and the changing environment
has resulted in an increased level of
vulnerability of electrical and electronic
systems required for the continued safe
flight and landing of the airplane.
Effective measures against the effects of
exposure to HIRF must be provided by
the design and installation of these
systems. The accepted maximum energy
levels in which civilian airplane system
installations must be capable of
operating safely are based on surveys
and analysis of existing radio frequency
emitters. These special conditions
require that the airplane be evaluated
under these energy levels for the
protection of the electronic system and
its associated wiring harness. These
external threat levels, which are lower
than previous required values, are
believed to represent the worst case to
which an airplane would be exposed in
the operating environment.
These special conditions require
qualification of systems that perform
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Federal Register / Vol. 71, No. 193 / Thursday, October 5, 2006 / Rules and Regulations
critical functions, as installed in aircraft,
to the defined HIRF environment in
paragraph 1 or, as an option to a fixed
value using laboratory tests, in
paragraph 2, as follows:
(1) The applicant may demonstrate
that the operation and operational
capability of the installed electrical and
electronic systems that perform critical
functions are not adversely affected
when the aircraft is exposed to the HIRF
environment defined below:
Field Strength
(volts per meter)
Frequency
Peak
10 kHz–100 kHz ..............................................................................................................................................................
100 kHz–500 kHz ............................................................................................................................................................
500 kHz–2 MHz ...............................................................................................................................................................
2 MHz–30 MHz ................................................................................................................................................................
30 MHz–70 MHz ..............................................................................................................................................................
70 MHz–100 MHz ............................................................................................................................................................
100 MHz–200 MHz ..........................................................................................................................................................
200 MHz–400 MHz ..........................................................................................................................................................
400 MHz–700 MHz ..........................................................................................................................................................
700 MHz–1 GHz ..............................................................................................................................................................
1 GHz–2 GHz ..................................................................................................................................................................
2 GHz–4 GHz ..................................................................................................................................................................
4 GHz–6 GHz ..................................................................................................................................................................
6 GHz–8 GHz ..................................................................................................................................................................
8 GHz–12 GHz ................................................................................................................................................................
12 GHz–18 GHz ..............................................................................................................................................................
18 GHz–40 GHz ..............................................................................................................................................................
Average
50
50
50
100
50
50
100
100
700
700
2000
3000
3000
1000
3000
2000
600
50
50
50
100
50
50
100
100
50
100
200
200
200
200
300
200
200
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The field strengths are expressed in terms of peak root-mean-square (rms) values.
or,
(2) The applicant may demonstrate by
a system test and analysis that the
electrical and electronic systems that
perform critical functions can withstand
a minimum threat of 100 volts per
meter, electrical field strength, from 10
kHz to 18 GHz. When using this test to
show compliance with the HIRF
requirements, no credit is given for
signal attenuation due to installation.
A preliminary hazard analysis must
be performed by the applicant, for
approval by the FAA, to identify either
electrical or electronic systems that
perform critical functions. The term
‘‘critical’’ means those functions whose
failure would contribute to, or cause, a
failure condition that would prevent the
continued safe flight and landing of the
airplane. The systems identified by the
hazard analysis that perform critical
functions are candidates for the
application of HIRF requirements. A
system may perform both critical and
non-critical functions. Primary
electronic flight display systems, and
their associated components, perform
critical functions such as attitude,
altitude, and airspeed indication. The
HIRF requirements apply only to critical
functions.
Compliance with HIRF requirements
may be demonstrated by tests, analysis,
models, similarity with existing
systems, or any combination of these.
Service experience alone is not
acceptable since normal flight
operations may not include an exposure
to the HIRF environment. Reliance on a
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15:35 Oct 04, 2006
Jkt 211001
system with similar design features for
redundancy as a means of protection
against the effects of external HIRF is
generally insufficient since all elements
of a redundant system are likely to be
exposed to the fields concurrently.
Applicability
As discussed above, these special
conditions are applicable to the
Raytheon Model C90A King Air
airplane. Should Garmin International,
Inc. apply at a later date for a
supplemental type certificate to modify
any other model included on the same
type certificate to incorporate 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 one model
of airplane. 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.
The substance of these special
conditions has been subjected to the
notice and comment period in several
prior instances and has been derived
without substantive change from those
previously issued. It is unlikely that
prior public comment would result in a
significant change from the substance
contained herein. For this reason, and
because a delay would significantly
affect the certification of the airplane,
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
which is imminent, the FAA has
determined that prior public notice and
comment are unnecessary and
impracticable, and good cause exists for
adopting these special conditions upon
issuance. The FAA is requesting
comments to allow interested persons to
submit views that may not have been
submitted in response to the prior
opportunities for comment described
above.
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 21.101; and 14 CFR
11.38 and 11.19.
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 Raytheon
Model C90A King Air airplane modified
by Garmin International, Inc., which
includes the Garmin G1000 system, GFC
700 autopilot, Mid-Continent
Instrument Attitude Indicator and
Sandia Avionics Cooling Fans.
1. Protection of Electrical and
Electronic Systems from High Intensity
Radiated Fields (HIRF). Each system
that performs critical functions must be
designed and installed to ensure that the
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Federal Register / Vol. 71, No. 193 / Thursday, October 5, 2006 / Rules and Regulations
operations and operational capabilities
of these systems to perform critical
functions are not adversely affected
when the airplane is exposed to high
intensity radiated electromagnetic fields
external to the airplane.
2. For the purpose of these special
conditions, the following definition
applies: Critical Functions: Functions
whose failure would contribute to, or
cause, a failure condition that would
prevent the continued safe flight and
landing of the airplane.
Issued in Kansas City, Missouri, on
September 27, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–16497 Filed 10–4–06; 8:45 am]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2006–25502; Airspace
Docket No. 06–ACE–10]
Modification of Class E Airspace; West
Plains, MO
Federal Aviation
Administration (FAA), DOT.
ACTION: Direct final rule; confirmation of
effective date.
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AGENCY:
SUMMARY: This document confirms the
effective date of the direct final rule
which revises Class E Airspace at West
Plains, MO.
DATES: Effective Date: 0901 UTC,
November 23, 2006.
FOR FURTHER INFORMATION CONTACT:
Grant Nichols, System Support, DOT
Regional Headquarters Building, Federal
Aviation Administration, 901 Locust,
Kansas City, MO 64106; telephone:
(816) 329–2522.
SUPPLEMENTARY INFORMATION: The FAA
published this direct final rule with a
request for comments in the Federal
Register on August 11, 2006 (71 FR
46076). The FAA uses the direct final
rulemaking procedure for a noncontroversial rule where the FAA
believes that there will be no adverse
public comment. This direct final rule
advised the public that no adverse
comments were anticipated, and that
unless a written adverse comments, or
a written notice of intent to submit such
an adverse comment, were received
within the comment period, the
regulation would become effective on
November 23, 2006. No adverse
comments were received, and thus this
16:06 Oct 04, 2006
Issued in Fort Worth, Texas, on September
22, 2006.
Walter Tweedy,
Acting Manager, System Support Group, ATO
Central Service Area.
[FR Doc. 06–8494 Filed 10–4–06; 8:45 am]
BILLING CODE 4910–13–M
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2006–24448; Airspace
Docket No. 06–AGL–02]
Establishment of Class E Airspace;
Mineral Point, WI
BILLING CODE 4910–13–P
VerDate Aug<31>2005
notice conforms that this direct final
rule will become effective on that date.
Jkt 211001
Federal Aviation
Administration (FAA), DOT.
ACTION: Direct final rule; request for
comments.
AGENCY:
SUMMARY: This document establishes
Class E airspace at Mineral Point, WI. A
request has been made for a new area of
Class E airspace extending upward from
the surface, due to traffic volume. This
action would establish a radius of class
E airspace for Iowa County Airport.
DATES: Effective 0901 UTC, January 18,
2007. The Director of the Federal
Register approves this incorporation by
reference action under 1 CFR Part 51,
subject to the annual revision of FAA
Order 7400.9 and publication of
conforming amendments. Comments
must be received on or before November
25, 2006.
ADDRESSES: Send comments on the
proposal to the Docket Management
System, U.S. Department of
Transportation, Room Plaza 401, 400
Seventh Street, SW., Washington, DC
20590–0001. You must identify the
docket Number FAA–2006–24448/
Airspace Docket No. 06–AGL–02, at the
beginning of your comments. You may
also submit comments on the Internet at
https://dms.dot.gov. You may review the
public docket containing the proposal,
any comments received, and any final
disposition in person in the Dockets
Office between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
1–800–647–5527) is on the plaza level
of the Department of Transportation
NASSIF Building at the above address.
An informal docket may also be
examined during normal business hours
at FAA Terminal Operations, Central
Service Office, 2300 East Devon
Avenue, Des Plaines, Illinois 60018.
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Fmt 4700
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FOR FURTHER INFORMATION CONTACT:
Steve Davis, FAA Terminal Operations,
Central Service Office, Airspace and
Procedures Branch, AGL–530, Federal
Aviation Administration, 2300 East
Devon Avenue, Des Plaines, Illinois
60018, telephone (847) 294–7131.
SUPPLEMENTARY INFORMATION: This
amendment to 14 CFR part 71
establishes Class E airspace at Mineral
Point, WI, to accommodate aircraft
operating into and out of Iowa County
Airport. The area will be depicted on
appropriate aeronautical charts. Class E
airspace areas extending upward from
the surface of the earth are published in
paragraph 6002, of FAA Order 7400.9P
dated September 1, 2006, and effective
September 15, 2006, airspace which is
incorporated by reference in 14 CFR
71.1. The Class D airspace designation
listed in this document will be
published subsequently in the order.
The Direct Final Rule Procedure
The FAA anticipates that this
regulation will not result in adverse or
negative comment and therefore is
issuing it as a direct final rule.
A substantial number of previous
opportunities provided to the public to
comment on substantially identical
actions have resulted in negligible
adverse comments or objections. Unless
a written adverse or negative comment,
or a written notice of intent to submit
an adverse or negative comment is
received within the comment period,
the regulation will become effective on
the date specified above. After the close
of the comment period, the FAA will
publish a document in the Federal
Register indicating that no adverse or
negative comments were received and
confirming the date on which the final
rule will become effective. If the FAA
does receive, within the comment
period, an adverse or negative comment,
or written notice of intent to submit
such a comment, a document will be
published in the Federal Register. This
document may withdraw the direct final
rule in whole or in part.
After considering the adverse or
negative comment, we may publish
another direct final rule or publish a
notice of proposed rulemaking with a
new comment period.
Comments Invited
Although this action is in the form of
a final rule and was not preceded by a
notice of proposed rulemaking,
comments are invited on this rule.
Interested person are invited to
comment on this rule by submitting
such written data, views, or arguments,
as they may desire. Communications
should identify the Rules Docket
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]]>Agencies
[Federal Register Volume 71, Number 193 (Thursday, October 5, 2006)]
[Rules and Regulations]
[Pages 58735-58738]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-16497]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE260, Special Condition 23-200-SC]
Special Conditions; Garmin International, Inc.; Raytheon Model
C90A King Air; Protection of Electronic Flight Instrument System from
the Effects of High Intensity Radiated Fields (HIRF)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; request for comments.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued to Garmin International
Inc., 1200 East 151st Street, Olathe, Kansas, 66062, for a Supplemental
Type Certificate for the Raytheon Model C90A King Air airplane. This
airplane will have novel and unusual design features when compared to
the state of technology envisaged in the applicable airworthiness
standards. These novel and unusual design features include the
installation of electronic flight instrument system (EFIS) displays in
the Garmin G1000 system, GFC 700 autopilot, Mid-Continent Instrument
Attitude Indicator and Sandia Avionics cooling fans. The applicable
regulations do not contain adequate or appropriate airworthiness
standards for the protection of these systems from the effects of high
intensity radiated fields
[[Page 58736]]
(HIRF). These special conditions contain the additional safety
standards that the Administrator considers necessary to establish a
level of safety equivalent to the airworthiness standards applicable to
these airplanes.
DATES: The effective date of these special conditions is September 27,
2006. Comments must be received on or before November 6, 2006.
ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk,
Docket No. CE260, Room 506, 901 Locust, Kansas City, Missouri 64106.
All comments must be marked: Docket No. CE260. 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: Jim Brady, Aerospace Engineer,
Standards Office (ACE-111), Small Airplane Directorate, Aircraft
Certification Service, Federal Aviation Administration, 901 Locust,
Room 301, Kansas City, Missouri 64106; telephone (816) 329-4132.
SUPPLEMENTARY INFORMATION: The FAA has determined that notice and
opportunity for prior public comment hereon are impracticable because
these procedures would significantly delay issuance of the approval
design and thus delivery of the affected aircraft. In addition, the
substance of these special conditions has been subject to the public
comment process in several prior instances with no substantive comments
received. The FAA, therefore, finds that good cause exists for making
these special conditions effective upon issuance.
Comments Invited
Interested persons are invited to submit 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
special conditions 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. Commenters wishing the FAA to acknowledge receipt of their
comments submitted in response to this notice must include a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket No. CE260.'' The postcard will be date stamped and
returned to the commenter.
Background
On June 2, 2006, Garmin International, Inc., 1200 East 151st
Street, Olathe, Kansas, 66062, applied to the FAA for a new
Supplemental Type Certificate for the Raytheon Model C90A King Air
airplane. The C90A King Air is currently approved under TC No. 3A20,
Revision 62 dated December 7, 2005. The proposed modification
incorporates a novel or unusual design feature, such as digital
avionics consisting of an EFIS that is vulnerable to HIRF external to
the airplane.
Type Certification Basis
Under the provisions of 14 CFR, part 21, Sec. 21.101, Garmin
International, Inc., must show that the Raytheon Model C90A King Air
aircraft as changed continues to meet the following provisions, or the
applicable regulations in effect on the date of application for the
change to the Raytheon Model C90A King Air as specified on Type
Certification Data Sheet TCDS No. 3A20, revision 62, dated December 7,
2005.
Discussion
If the Administrator finds that the applicable airworthiness
standards do not contain adequate or appropriate safety standards
because of novel or unusual design features of an airplane, 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 after public notice and become
part of the type certification basis in accordance with Sec.
21.101(b)(2).
Special conditions are initially applicable to the model for which
they are issued. Should the applicant apply for a supplemental type
certificate to modify any other model already included on the same type
certificate to incorporate 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
Garmin International, Inc. plans to incorporate certain novel and
unusual design features into an airplane for which the airworthiness
standards do not contain adequate or appropriate safety standards for
protection from the effects of HIRF. These features include EFIS as
part of the Garmin G1000 system. Additionally, the Garmin GFC 700
autopilot, Mid-Continent Instrument Attitude Indicator and Sandia
Avionics Cooling Fans, which are susceptible to the HIRF environment,
are included and were not envisaged by the existing regulations for
this type of airplane.
Protection of Systems From High Intensity Radiated Fields (HIRF)
Recent advances in technology have given rise to the application in
aircraft designs of advanced electrical and electronic systems that
perform functions required for continued safe flight and landing. Due
to the use of sensitive solid state advanced components in analog and
digital electronics circuits, these advanced systems are readily
responsive to the transient effects of induced electrical current and
voltage caused by the HIRF. The HIRF can degrade electronic systems
performance by damaging components or upsetting system functions.
Furthermore, the HIRF environment has undergone a transformation
that was not foreseen when the current requirements were developed.
Higher energy levels are radiated from transmitters that are used for
radar, radio, and television. Also, the number of transmitters has
increased significantly. There is also uncertainty concerning the
effectiveness of airframe shielding for HIRF. Furthermore, coupling to
cockpit-installed equipment through the cockpit window apertures is
undefined.
The combined effect of the technological advances in airplane
design and the changing environment has resulted in an increased level
of vulnerability of electrical and electronic systems required for the
continued safe flight and landing of the airplane. Effective measures
against the effects of exposure to HIRF must be provided by the design
and installation of these systems. The accepted maximum energy levels
in which civilian airplane system installations must be capable of
operating safely are based on surveys and analysis of existing radio
frequency emitters. These special conditions require that the airplane
be evaluated under these energy levels for the protection of the
electronic system and its associated wiring harness. These external
threat levels, which are lower than previous required values, are
believed to represent the worst case to which an airplane would be
exposed in the operating environment.
These special conditions require qualification of systems that
perform
[[Page 58737]]
critical functions, as installed in aircraft, to the defined HIRF
environment in paragraph 1 or, as an option to a fixed value using
laboratory tests, in paragraph 2, as follows:
(1) The applicant may demonstrate that the operation and
operational capability of the installed electrical and electronic
systems that perform critical functions are not adversely affected when
the aircraft is exposed to the HIRF environment defined below:
------------------------------------------------------------------------
Field Strength (volts
per meter)
Frequency -------------------------
Peak Average
------------------------------------------------------------------------
10 kHz-100 kHz................................ 50 50
100 kHz-500 kHz............................... 50 50
500 kHz-2 MHz................................. 50 50
2 MHz-30 MHz.................................. 100 100
30 MHz-70 MHz................................. 50 50
70 MHz-100 MHz................................ 50 50
100 MHz-200 MHz............................... 100 100
200 MHz-400 MHz............................... 100 100
400 MHz-700 MHz............................... 700 50
700 MHz-1 GHz................................. 700 100
1 GHz-2 GHz................................... 2000 200
2 GHz-4 GHz................................... 3000 200
4 GHz-6 GHz................................... 3000 200
6 GHz-8 GHz................................... 1000 200
8 GHz-12 GHz.................................. 3000 300
12 GHz-18 GHz................................. 2000 200
18 GHz-40 GHz................................. 600 200
------------------------------------------------------------------------
The field strengths are expressed in terms of peak root-mean-square
(rms) values.
or,
(2) The applicant may demonstrate by a system test and analysis
that the electrical and electronic systems that perform critical
functions can withstand a minimum threat of 100 volts per meter,
electrical field strength, from 10 kHz to 18 GHz. When using this test
to show compliance with the HIRF requirements, no credit is given for
signal attenuation due to installation.
A preliminary hazard analysis must be performed by the applicant,
for approval by the FAA, to identify either electrical or electronic
systems that perform critical functions. The term ``critical'' means
those functions whose failure would contribute to, or cause, a failure
condition that would prevent the continued safe flight and landing of
the airplane. The systems identified by the hazard analysis that
perform critical functions are candidates for the application of HIRF
requirements. A system may perform both critical and non-critical
functions. Primary electronic flight display systems, and their
associated components, perform critical functions such as attitude,
altitude, and airspeed indication. The HIRF requirements apply only to
critical functions.
Compliance with HIRF requirements may be demonstrated by tests,
analysis, models, similarity with existing systems, or any combination
of these. Service experience alone is not acceptable since normal
flight operations may not include an exposure to the HIRF environment.
Reliance on a system with similar design features for redundancy as a
means of protection against the effects of external HIRF is generally
insufficient since all elements of a redundant system are likely to be
exposed to the fields concurrently.
Applicability
As discussed above, these special conditions are applicable to the
Raytheon Model C90A King Air airplane. Should Garmin International,
Inc. apply at a later date for a supplemental type certificate to
modify any other model included on the same type certificate to
incorporate 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 one model of airplane. 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.
The substance of these special conditions has been subjected to the
notice and comment period in several prior instances and has been
derived without substantive change from those previously issued. It is
unlikely that prior public comment would result in a significant change
from the substance contained herein. For this reason, and because a
delay would significantly affect the certification of the airplane,
which is imminent, the FAA has determined that prior public notice and
comment are unnecessary and impracticable, and good cause exists for
adopting these special conditions upon issuance. The FAA is requesting
comments to allow interested persons to submit views that may not have
been submitted in response to the prior opportunities for comment
described above.
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
21.101; and 14 CFR 11.38 and 11.19.
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 Raytheon Model C90A King Air
airplane modified by Garmin International, Inc., which includes the
Garmin G1000 system, GFC 700 autopilot, Mid-Continent Instrument
Attitude Indicator and Sandia Avionics Cooling Fans.
1. Protection of Electrical and Electronic Systems from High
Intensity Radiated Fields (HIRF). Each system that performs critical
functions must be designed and installed to ensure that the
[[Page 58738]]
operations and operational capabilities of these systems to perform
critical functions are not adversely affected when the airplane is
exposed to high intensity radiated electromagnetic fields external to
the airplane.
2. For the purpose of these special conditions, the following
definition applies: Critical Functions: Functions whose failure would
contribute to, or cause, a failure condition that would prevent the
continued safe flight and landing of the airplane.
Issued in Kansas City, Missouri, on September 27, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-16497 Filed 10-4-06; 8:45 am]
BILLING CODE 4910-13-P
