Special Conditions: Societe de Motorisation Aeronautiques (SMA) Engines, Cessna Models 182Q and 182R: Installation of Model SR305-230 Aircraft Diesel Engine for Full Authority Digital Engine Control (FADEC) System and the Protection of the System From the Effects of High Intensity Radiated Fields (HIRF), 34517-34519 [E6-9241]
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Federal Register / Vol. 71, No. 115 / Thursday, June 15, 2006 / Rules and Regulations
employer or the recruiter or referrer,
must attest to the required information
in Form I–9. The system used to capture
the electronic signature should include
a method to acknowledge that the
attestation to be signed has been read by
the signatory. Any person or entity who
has failed to comply with the criteria
established by this regulation for
electronic signatures, if used, and at the
time of inspection does not present a
properly completed Form I–9 for the
employee, is in violation of section
274A(a)(1)(B) of the Act and 8 CFR
274a.2(b)(2).
Dated: June 8, 2006.
Michael Chertoff,
Secretary.
[FR Doc. E6–9283 Filed 6–14–06; 8:45 am]
DEPARTMENT OF AGRICULTURE
Animal and Plant Health Inspection
Service
[Docket No. APHIS–2006–0020]
States Approved To Receive Stallions
and Mares From CEM-Affected
Regions; Indiana
Animal and Plant Health
Inspection Service, USDA.
ACTION: Direct final rule; confirmation of
effective date.
AGENCY:
cprice-sewell on PROD1PC66 with RULES
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE249; Special Conditions No.
23–189–SC]
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions; request
for comments.
AGENCY:
9 CFR Part 93
SUMMARY: On April 27, 2006, the
Animal and Plant Health Inspection
Service published a direct final rule.
(See 71 FR 24806–24808.) The direct
final rule notified the public of our
intention to amend the animal
importation regulations by adding
Indiana to the lists of States approved to
receive certain stallions and mares
imported into the United States from
regions affected with contagious equine
metritis. We did not receive any written
adverse comments regarding the
addition of Indiana to those lists or
written notice of intent to submit
adverse comments in response to the
direct final rule.
DATES: Effective Date: The effective date
of the direct final rule is confirmed as
June 26, 2006.
FOR FURTHER INFORMATION CONTACT: Dr.
Freeda E. Isaac, Senior Staff
Veterinarian, National Center for Import
and Export, VS, APHIS, 4700 River
Road Unit 39, Riverdale, MD 20737–
1231; (301) 734–8364.
Authority: 7 U.S.C. 1622 and 8301–8317;
21 U.S.C. 136 and 136a; 31 U.S.C. 9701; 7
CFR 2.22, 2.80, and 371.4.
14:45 Jun 14, 2006
BILLING CODE 3410–34–P
Special Conditions: Societe de
Motorisation Aeronautiques (SMA)
Engines, Cessna Models 182Q and
182R: Installation of Model SR305–230
Aircraft Diesel Engine for Full
Authority Digital Engine Control
(FADEC) System and the Protection of
the System From the Effects of High
Intensity Radiated Fields (HIRF)
BILLING CODE 4410–10–P
VerDate Aug<31>2005
Done in Washington, DC, this 9th day of
June 2006.
Kevin Shea,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. E6–9350 Filed 6–14–06; 8:45 am]
Jkt 208001
SUMMARY: This proposes special
conditions for the Cessna Models 182Q
and 182R airplanes with a Societe de
Motorisation Aeronautiques (SMA)
Model SR305–230 aircraft diesel engine
(ADE). The supplemental type
certificate for these airplanes will have
a novel or unusual design feature
associated with the installation of an
aircraft diesel engine that uses an
electronic engine control system instead
of a mechanical control system. 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: The effective date of these
special conditions is June 7, 2006.
Comments must be received on or
before July 17, 2006.
ADDRESSES: Comments on the special
conditions may be mailed in duplicate
to: Federal Aviation Administration
(FAA), Regional Counsel, ACE–7,
Attention: Rules Docket, Docket No.
CE249, 901 Locust, Room 506, Kansas
City, Missouri 64106, or delivered in
duplicate to the Regional Counsel at the
above address. Comments must be
marked: Docket No. CE249. Comments
may be inspected in the Rules Docket
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
34517
weekdays, except Federal holidays,
between 7:30 a.m. and 4 p.m.
FOR FURTHER INFORMATION CONTACT:
Peter L. Rouse, Federal Aviation
Administration, Aircraft Certification
Service, Small Airplane Directorate,
ACE–111, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone:
816–329–4135, fax: 816–329–4090.
The FAA
has determined that notice and
opportunity for prior public comment
hereon are impracticable because these
procedures would significantly delay
issuance of the design approval 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.
SUPPLEMENTARY INFORMATION:
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 special condition
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. CE249.’’ The postcard will
be date stamped and returned to the
commenter.
Background
On March 19, 2004, the Societe de
Motorisation Aeronautiques Engines,
Inc. applied for Supplemental Type
Certification of Cessna Models 182Q
and 182R airplanes for the installation
of an SMA Model SR305–230. The
airplane is powered by a SMA Model
SR305–230 that is equipped with an
electronic engine control system with
full authority capability in these
airplanes.
E:\FR\FM\15JNR1.SGM
15JNR1
34518
Federal Register / Vol. 71, No. 115 / Thursday, June 15, 2006 / Rules and Regulations
Type Certification Basis
Under the provisions of 14 CFR
21.101, SMA Engines, Inc., must show
that the Cessna Models 182Q and 182R
airplanes, with the installation of an
SMA Model SR305–230, meets the
applicable provisions of part 14 CFR
part 23, as amended by Amendments
23–1 through 23–51 and Civil Air
Regulations (CAR) 3 thereto.
If the Administrator finds that the
applicable airworthiness regulations
(i.e., CAR 3; 14 CFR, part 23) do not
contain adequate or appropriate safety
standards for the Cessna Models 182Q
and 182R airplanes 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 certification basis for the
supplemental type certification basis in
accordance with § 21.101. 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
models that are listed on the same type
certificate to incorporate the same novel
or unusual design features, the special
conditions would also apply under the
provisions of § 21.101.
cprice-sewell on PROD1PC66 with RULES
Novel or Unusual Design Features
The SMA Engines, Inc. modified
Cessna Models 182Q and 182R airplanes
will incorporate a novel or unusual
design feature, an engine that includes
an electronic control system with Full
Authority Digital Engine control
(FADEC) capability.
Many advanced electronic systems are
prone to either upsets or damage, or
both, at energy levels lower than analog
systems. The increasing use of high
power radio frequency emitters
mandates requirements for improved
High Intensity Radiated Fields (HIRF)
protection for electrical and electronic
equipment. Since the electronic engine
control system used on the SMA
Engines, Inc., modified Cessna Models
182Q and 182R airplanes will perform
critical functions, provisions for
protection from the effects of HIRF
should be considered and, if necessary,
incorporated into the airplane design
data. The FAA policy contained in
Notice 8110.71, dated April 2, 1998,
establishes the HIRF energy levels that
airplanes will be exposed to in service.
The guidelines set forth in this notice
are the result of an Aircraft Certification
Service review of existing policy on
HIRF, in light of the ongoing work of the
Aviation Rulemaking Advisory
VerDate Aug<31>2005
14:45 Jun 14, 2006
Jkt 208001
Committee (ARAC) Electromagnetic
Effects Harmonization Working Group
(EEHWG). The EEHWG adopted a set of
HIRF environment levels in November
1997 that were agreed upon by the FAA,
the Joint Aviation Authorities (JAA),
and industry participants. As a result,
the HIRF environments in this notice
reflect the environment levels
recommended by this working group.
This notice states that a FADEC is an
example of a system that should address
the HIRF environments.
Even though the control system will
be certificated as part of the engine, the
installation of an engine with an
electronic control system requires
evaluation due to the possible effects on
or by other airplane systems (e.g., radio
interference with other airplane
electronic systems, shared engine and
airplane power sources). The regulatory
requirements in 14 CFR part 23 for
evaluating the installation of complex
systems, including electronic systems,
are contained in § 23.1309. However,
when § 23.1309 was developed, the use
of electronic control systems for engines
was not envisioned; therefore, the
§ 23.1309 requirements were not
applicable to systems certificated as part
of the engine (reference § 23.1309(f)(1)).
Also, electronic control systems often
require inputs from airplane data and
power sources and outputs to other
airplane systems (e.g., automated
cockpit powerplant controls such as
mixture setting). Although the parts of
the system that are not certificated with
the engine could be evaluated using the
criteria of § 23.1309, the integral nature
of systems such as these makes it
unfeasible to evaluate the airplane
portion of the system without including
the engine portion of the system.
However, § 23.1309(f)(1) again prevents
complete evaluation of the installed
airplane system since evaluation of the
engine system’s effects is not required.
Therefore, special conditions are
proposed for the SMA Engines, Inc.,
modified Cessna Models 182Q and 182R
airplanes to provide HIRF protection
and to evaluate the installation of the
electronic engine control system for
compliance with the requirements of
§ 23.1309(a) through (e) at Amendment
23–49.
Applicability
As discussed above, these special
conditions are applicable to the SMA
Engines, Inc., modified Cessna Models
182Q and 182R airplanes. Should SMA
Engines, Inc., apply at a later date for a
supplemental type certificate to modify
any other model included on the same
type certificate as the SMA Engines,
Inc., modified Cessna Models 182Q and
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
182R airplanes to incorporate the same
novel or unusual design features, 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 SMA
Engines, Inc., modified Cessna Models
182Q and 182R airplanes. It is not a rule
of general applicability, and it affects
only the applicant who applied to the
FAA for approval of these features on
the airplane.
Under standard practice, the effective
date of final special conditions would
be 30 days after the date of publication
in the Federal Register. However, as the
certification date for the SMA Engines,
Inc., modified Cessna Models 182Q and
182R is imminent, the FAA finds that
good cause exists to make these special
conditions effective upon issuance.
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
supplemental type certification basis for
SMA Engines, Inc., modified Cessna
Models 182Q and 182R airplanes.
1. High Intensity Radiated Fields
(HIRF) Protection. In showing
compliance with 14 CFR part 21 and the
airworthiness requirements of 14 CFR
part 23, protection against hazards
caused by exposure to HIRF fields for
the full authority digital engine control
system, which performs critical
functions, must be considered. To
prevent this occurrence, the electronic
engine control system must be designed
and installed to ensure that the
operation and operational capabilities of
this critical system are not adversely
affected when the airplane is exposed to
high energy radio fields.
At this time, the FAA and other
airworthiness authorities are unable to
precisely define or control the HIRF
energy level to which the airplane will
be exposed in service; therefore, the
FAA hereby defines two acceptable
interim methods for complying with the
requirement for protection of systems
that perform critical functions.
E:\FR\FM\15JNR1.SGM
15JNR1
Federal Register / Vol. 71, No. 115 / Thursday, June 15, 2006 / Rules and Regulations
(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
external HIRF threat environment
defined in the following table:
Frequency
Field strength
(volts per meter)
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 .......
50
50
50
100
50
50
100
100
50
100
200
200
200
200
300
200
200
cprice-sewell on PROD1PC66 with RULES
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
peak electrical strength, without the
benefit of airplane structural shielding,
in the frequency range of 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.
Data used for engine certification may
be used, when appropriate, for airplane
certification.
2. Electronic Engine Control System.
The installation of the electronic engine
control system must comply with the
requirements of § 23.1309(a) through (e)
at Amendment 23–49. The intent of this
requirement is not to re-evaluate the
inherent hardware reliability of the
control itself, but rather determine the
effects, including environmental effects
addressed in § 23.1309(e), on the
airplane systems and engine control
system when installing the control on
the airplane. When appropriate, engine
certification data may be used when
showing compliance with this
requirement.
With respect to compliance with
§ 23.1309(e), the levels required for
compliance shall be at the levels for
catastrophic failure conditions.
VerDate Aug<31>2005
14:45 Jun 14, 2006
Jkt 208001
BILLING CODE 4910–13–P
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Average
50
50
50
100
50
50
100
100
700
700
2000
3000
3000
1000
3000
2000
600
Issued in Kansas City, Missouri on June 7,
2006.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–9241 Filed 6–14–06; 8:45 am]
Food and Drug Administration
34519
per ton’’ column, in the entry for use of
lasalocid at 30 to 600 grams per ton in
combination with chlortetracycline at
500 to 4000 grams per ton, by removing
the second paragraph designation
‘‘(xxiii)’’ and by adding in its place the
paragraph designation ‘‘(xxviii)’’.
Dated: June 1, 2006.
Stephen F. Sundlof,
Director, Center for Veterinary Medicine.
[FR Doc. E6–9321 Filed 6–14–06; 8:45 am]
BILLING CODE 4160–01–S
21 CFR Part 558
New Animal Drugs for Use in Animal
Feeds; Lasalocid; Correction
AGENCY:
HHS.
[Public Notice 5362]
Final rule; correcting
amendments.
SUMMARY: The Food and Drug
Administration (FDA) is correcting a
document amending the animal drug
regulations to reflect approval of an
original new animal drug application
(NADA) that appeared in the Federal
Register of April 27, 2006 (71 FR
24814). FDA is correcting a paragraph
designation in the table for lasalocid
cattle feeds which was drafted in error.
This correction is being made to
improve the accuracy of the animal drug
regulations.
DATES: This rule is effective June 15,
2006.
FOR FURTHER INFORMATION CONTACT:
George K. Haibel, Center for Veterinary
Medicine (HFV–6), Food and Drug
Administration, 7519 Standish Pl.,
Rockville, MD 20855, 240–276–9019, email: george.haibel@fda.hhs.gov.
SUPPLEMENTARY INFORMATION: For the
reasons set forth in the preamble, FDA
is correcting 21 CFR part 558 to read as
follows:
List of Subjects in 21 CFR Part 558
Animal drugs, Animal feeds.
I Therefore, under the Federal Food,
Drug, and Cosmetic Act and under
authority delegated to the Commissioner
of Food and Drugs and redelegated to
the Center for Veterinary Medicine, 21
CFR part 558 is amended as follows:
PART 558—NEW ANIMAL DRUGS FOR
USE IN ANIMAL FEEDS
1. The authority citation for 21 CFR
part 558 continues to read as follows:
I
Authority: 21 U.S.C. 360b, 371.
[Amended]
2. Section 558.311 is corrected in the
table in the ‘‘Lasalocid sodium in grams
I
PO 00000
22 CFR Parts 40, 41, and 42
Food and Drug Administration,
ACTION:
§ 558.311
DEPARTMENT OF STATE
Frm 00013
Fmt 4700
Sfmt 4700
Nomenclature Changes Reflecting
Creation of Department of Homeland
Security
State Department.
Final rule.
AGENCY:
ACTION:
SUMMARY: This rule makes technical
nomenclature changes to Title 22 Code
of Federal Regulations (CFR) parts 40,
41, and 42 to properly reflect the
creation of the Department of Homeland
Security (DHS) and its assumption of
the functions of the former Immigration
and Naturalization Service (INS). This
rule also reflects changes to form
numbers on various visa-related forms.
Because the amendments are entirely
technical, the State Department is not
providing an opportunity for public
comment under the Administrative
Procedure Act ‘‘good cause’’ exemption.
DATES: Effective Date: This rule is
effective June 15, 2006.
Persons with access to the internet
may view this notice by going to the
regulations.gov Web site at: https://
www.regulations.gov/index.cfm.
FOR FURTHER INFORMATION CONTACT:
Barbara J. Kennedy, Legislation and
Regulations Division, Visa Services,
U.S. Department of State, 2401 E Street,
NW., Room L–603, Washington, DC
20520–0106; telephone 202–663–1206
or e-mail KennedyBJ@state.gov.
SUPPLEMENTARY INFORMATION:
Why is the Department Promulgating
This Rule?
On March 1, 2003, the INS’s functions
were transferred to the newly created
Department of Homeland Security
(DHS). The reorganization was required
by the Homeland Security Act of 2002,
Public Law No. 107–296 section 1502.
This final rule includes the changes that
reflect the transfer.
E:\FR\FM\15JNR1.SGM
15JNR1
]]>Agencies
[Federal Register Volume 71, Number 115 (Thursday, June 15, 2006)]
[Rules and Regulations]
[Pages 34517-34519]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-9241]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE249; Special Conditions No. 23-189-SC]
Special Conditions: Societe de Motorisation Aeronautiques (SMA)
Engines, Cessna Models 182Q and 182R: Installation of Model SR305-230
Aircraft Diesel Engine for Full Authority Digital Engine Control
(FADEC) System and the Protection of the System From the Effects of
High Intensity Radiated Fields (HIRF)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; request for comments.
-----------------------------------------------------------------------
SUMMARY: This proposes special conditions for the Cessna Models 182Q
and 182R airplanes with a Societe de Motorisation Aeronautiques (SMA)
Model SR305-230 aircraft diesel engine (ADE). The supplemental type
certificate for these airplanes will have a novel or unusual design
feature associated with the installation of an aircraft diesel engine
that uses an electronic engine control system instead of a mechanical
control system. 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: The effective date of these special conditions is June 7, 2006.
Comments must be received on or before July 17, 2006.
ADDRESSES: Comments on the special conditions may be mailed in
duplicate to: Federal Aviation Administration (FAA), Regional Counsel,
ACE-7, Attention: Rules Docket, Docket No. CE249, 901 Locust, Room 506,
Kansas City, Missouri 64106, or delivered in duplicate to the Regional
Counsel at the above address. Comments must be marked: Docket No.
CE249. 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: Peter L. Rouse, Federal Aviation
Administration, Aircraft Certification Service, Small Airplane
Directorate, ACE-111, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: 816-329-4135, fax: 816-329-4090.
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 design
approval 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 special condition 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. CE249.'' The postcard will be date stamped and
returned to the commenter.
Background
On March 19, 2004, the Societe de Motorisation Aeronautiques
Engines, Inc. applied for Supplemental Type Certification of Cessna
Models 182Q and 182R airplanes for the installation of an SMA Model
SR305-230. The airplane is powered by a SMA Model SR305-230 that is
equipped with an electronic engine control system with full authority
capability in these airplanes.
[[Page 34518]]
Type Certification Basis
Under the provisions of 14 CFR 21.101, SMA Engines, Inc., must show
that the Cessna Models 182Q and 182R airplanes, with the installation
of an SMA Model SR305-230, meets the applicable provisions of part 14
CFR part 23, as amended by Amendments 23-1 through 23-51 and Civil Air
Regulations (CAR) 3 thereto.
If the Administrator finds that the applicable airworthiness
regulations (i.e., CAR 3; 14 CFR, part 23) do not contain adequate or
appropriate safety standards for the Cessna Models 182Q and 182R
airplanes 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
certification basis for the supplemental type certification basis in
accordance with Sec. 21.101. 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 models
that are listed on the same type certificate to incorporate the same
novel or unusual design features, the special conditions would also
apply under the provisions of Sec. 21.101.
Novel or Unusual Design Features
The SMA Engines, Inc. modified Cessna Models 182Q and 182R
airplanes will incorporate a novel or unusual design feature, an engine
that includes an electronic control system with Full Authority Digital
Engine control (FADEC) capability.
Many advanced electronic systems are prone to either upsets or
damage, or both, at energy levels lower than analog systems. The
increasing use of high power radio frequency emitters mandates
requirements for improved High Intensity Radiated Fields (HIRF)
protection for electrical and electronic equipment. Since the
electronic engine control system used on the SMA Engines, Inc.,
modified Cessna Models 182Q and 182R airplanes will perform critical
functions, provisions for protection from the effects of HIRF should be
considered and, if necessary, incorporated into the airplane design
data. The FAA policy contained in Notice 8110.71, dated April 2, 1998,
establishes the HIRF energy levels that airplanes will be exposed to in
service. The guidelines set forth in this notice are the result of an
Aircraft Certification Service review of existing policy on HIRF, in
light of the ongoing work of the Aviation Rulemaking Advisory Committee
(ARAC) Electromagnetic Effects Harmonization Working Group (EEHWG). The
EEHWG adopted a set of HIRF environment levels in November 1997 that
were agreed upon by the FAA, the Joint Aviation Authorities (JAA), and
industry participants. As a result, the HIRF environments in this
notice reflect the environment levels recommended by this working
group. This notice states that a FADEC is an example of a system that
should address the HIRF environments.
Even though the control system will be certificated as part of the
engine, the installation of an engine with an electronic control system
requires evaluation due to the possible effects on or by other airplane
systems (e.g., radio interference with other airplane electronic
systems, shared engine and airplane power sources). The regulatory
requirements in 14 CFR part 23 for evaluating the installation of
complex systems, including electronic systems, are contained in Sec.
23.1309. However, when Sec. 23.1309 was developed, the use of
electronic control systems for engines was not envisioned; therefore,
the Sec. 23.1309 requirements were not applicable to systems
certificated as part of the engine (reference Sec. 23.1309(f)(1)).
Also, electronic control systems often require inputs from airplane
data and power sources and outputs to other airplane systems (e.g.,
automated cockpit powerplant controls such as mixture setting).
Although the parts of the system that are not certificated with the
engine could be evaluated using the criteria of Sec. 23.1309, the
integral nature of systems such as these makes it unfeasible to
evaluate the airplane portion of the system without including the
engine portion of the system. However, Sec. 23.1309(f)(1) again
prevents complete evaluation of the installed airplane system since
evaluation of the engine system's effects is not required.
Therefore, special conditions are proposed for the SMA Engines,
Inc., modified Cessna Models 182Q and 182R airplanes to provide HIRF
protection and to evaluate the installation of the electronic engine
control system for compliance with the requirements of Sec. 23.1309(a)
through (e) at Amendment 23-49.
Applicability
As discussed above, these special conditions are applicable to the
SMA Engines, Inc., modified Cessna Models 182Q and 182R airplanes.
Should SMA Engines, Inc., apply at a later date for a supplemental type
certificate to modify any other model included on the same type
certificate as the SMA Engines, Inc., modified Cessna Models 182Q and
182R airplanes to incorporate the same novel or unusual design
features, 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 SMA Engines, Inc., modified Cessna Models 182Q and 182R airplanes.
It is not a rule of general applicability, and it affects only the
applicant who applied to the FAA for approval of these features on the
airplane.
Under standard practice, the effective date of final special
conditions would be 30 days after the date of publication in the
Federal Register. However, as the certification date for the SMA
Engines, Inc., modified Cessna Models 182Q and 182R is imminent, the
FAA finds that good cause exists to make these special conditions
effective upon issuance.
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 supplemental type certification basis for SMA Engines, Inc.,
modified Cessna Models 182Q and 182R airplanes.
1. High Intensity Radiated Fields (HIRF) Protection. In showing
compliance with 14 CFR part 21 and the airworthiness requirements of 14
CFR part 23, protection against hazards caused by exposure to HIRF
fields for the full authority digital engine control system, which
performs critical functions, must be considered. To prevent this
occurrence, the electronic engine control system must be designed and
installed to ensure that the operation and operational capabilities of
this critical system are not adversely affected when the airplane is
exposed to high energy radio fields.
At this time, the FAA and other airworthiness authorities are
unable to precisely define or control the HIRF energy level to which
the airplane will be exposed in service; therefore, the FAA hereby
defines two acceptable interim methods for complying with the
requirement for protection of systems that perform critical functions.
[[Page 34519]]
(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 external HIRF threat environment defined
in the following table:
------------------------------------------------------------------------
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 peak
electrical strength, without the benefit of airplane structural
shielding, in the frequency range of 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. Data used for engine
certification may be used, when appropriate, for airplane
certification.
2. Electronic Engine Control System. The installation of the
electronic engine control system must comply with the requirements of
Sec. 23.1309(a) through (e) at Amendment 23-49. The intent of this
requirement is not to re-evaluate the inherent hardware reliability of
the control itself, but rather determine the effects, including
environmental effects addressed in Sec. 23.1309(e), on the airplane
systems and engine control system when installing the control on the
airplane. When appropriate, engine certification data may be used when
showing compliance with this requirement.
With respect to compliance with Sec. 23.1309(e), the levels
required for compliance shall be at the levels for catastrophic failure
conditions.
Issued in Kansas City, Missouri on June 7, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-9241 Filed 6-14-06; 8:45 am]
BILLING CODE 4910-13-P
