Special Conditions; The New Piper Aircraft, Inc.; PA-44-180; Protection of Systems for High Intensity Radiated Fields (HIRF), 2143-2145 [06-341]
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Federal Register / Vol. 71, No. 9 / Friday, January 13, 2006 / Rules and Regulations
§ 391.4
Laboratory services rate.
The rate for laboratory services
provided pursuant to §§ 350.7, 351.9,
352.5, 354.101, 355.12, and 362.5 is
$67.83 per hour per program employee
in fiscal year 2006, $69.31 per hour per
program employee in fiscal year 2007,
and $70.82 per hour per program
employee in fiscal year 2008.
I 3. In § 391.5, paragraph (a) is revised
to read as follows:
§ 391.5
Laboratory accreditation fee.
(a) The annual fee for the initial
accreditation and maintenance of
accreditation provided pursuant to
§§ 318.21 and 381.153 shall be
$4,000.00 for fiscal year 2006; $4,500.00
for fiscal year 2007; and $4,500.00 for
fiscal year 2008.
*
*
*
*
*
PART 590—INSPECTION OF EGGS
AND EGG PRODUCTS (EGG
PRODUCTS INSPECTION ACT)
4. The authority citation for part 590
continues to read as follows:
I
Authority: 21 U.S.C. 1031–1056.
5. Section 590.126 is revised to read
as follows:
I
§ 590.126
Overtime inspection service.
When operations in an official plant
require the services of inspection
personnel beyond their regularly
assigned tour of duty on any day or on
a day outside the established schedule,
such services are considered as overtime
work. The official plant must give
reasonable advance notice to the
inspector of any overtime service
necessary and must pay the Agency for
such overtime at an hourly rate of
$56.40 per hour per program employee
in fiscal year 2006, $57.65 per hour per
program employee in fiscal year 2007,
and $58.93 per hour per program
employee in fiscal year 2008.
I 6. In § 590.128, paragraph (a) is
revised to read as follows:
hsrobinson on PROD1PC70 with RULES
§ 590.128
Holiday inspection service.
(a) When an official plant requires
inspection service on a holiday or a day
designated in lieu of a holiday, such
service is considered holiday work. The
official plant must, in advance of such
holiday work, request that the inspector
in charge furnish inspection service
during such period and must pay the
Agency for such holiday work at an
hourly rate of $56.40 per hour per
program employee in fiscal year 2006,
$57.65 per hour per program employee
in fiscal year 2007, and $58.93 per hour
per program employee in fiscal year
2008.
*
*
*
*
*
VerDate Aug<31>2005
13:51 Jan 12, 2006
Jkt 208001
PART 592—VOLUNTARY INSPECTION
OF EGG PRODUCTS
7. The authority citation for part 592
continues to read as follows:
I
8. Sections 592.510, 592.520 and
592.530 are revised to read as follows:
I
Base time rate.
The base time rate for voluntary
inspection services for egg products is
$47.79 per hour per program employee
in fiscal year 2006, $48.84 per hour per
program employee in fiscal year 2007,
and $49.93 per hour per program
employee in fiscal year 2008.
§ 592.520
Overtime rate.
When operations in an official plant
require the services of inspection
personnel beyond their regularly
assigned tour of duty on any day or on
a day outside the established schedule,
such services are considered as overtime
work. The official plant must give
reasonable advance notice to the
inspection program personnel of any
overtime service necessary and must
pay the Agency for such overtime at an
hourly rate of $56.40 per hour per
program employee in fiscal year 2006,
$57.65 per hour per program employee
in fiscal year 2007, and $58.93 per hour
per program employee in fiscal year
2008.
§ 592.530
Holiday rate.
When an official plant requires
inspection service on a holiday or a day
designated in lieu of a holiday, such
service is considered holiday work. The
official plant must, in advance of such
holiday work, request that the inspector
in charge furnish inspection service
during such period and must pay the
Agency for such holiday work at an
hourly rate of $56.40 per hour per
program employee in fiscal year 2006,
$57.65 per hour per program employee
in fiscal year 2007, and $58.93 per hour
per program employee in fiscal year
2008.
Done in Washington, DC, on January 10,
2006.
Bryce Quick,
Deputy Administrator.
[FR Doc. 06–321 Filed 1–12–06; 8:45 am]
BILLING CODE 3410–DM–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE238, Special Condition 23–
178–SC]
Authority: 7 U.S.C. 1621–1627.
§ 592.510
2143
Special Conditions; The New Piper
Aircraft, Inc.; PA–44–180; Protection of
Systems for 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 The New Piper Aircraft, Inc.,
Vero Beach, Florida, for a type design
change for the PA–44–180 airplanes.
These airplanes 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 Model 700–00006–
XXX(), manufactured by Avidyne
Corporation, Inc. for which 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 (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 January 6, 2006.
Comments must be received on or
before February 13, 2006.
ADDRESSES: Comments may be mailed
in duplicate to: Federal Aviation
Administration, Regional Counsel,
ACE–7, Attention: Rules Docket Clerk,
Docket No. CE238, Room 506, 901
Locust, Kansas City, Missouri 64106. All
comments must be marked: Docket No.
CE238. 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: Wes
Ryan, Aerospace Engineer, Standards
Office (ACE–110), Small Airplane
Directorate, Aircraft Certification
Service, Federal Aviation
Administration, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone
(816) 329–4127.
SUPPLEMENTARY INFORMATION: The FAA
has determined that notice and
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2144
Federal Register / Vol. 71, No. 9 / Friday, January 13, 2006 / Rules and Regulations
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. CE238.’’ The postcard will
be date stamped and returned to the
commenter.
hsrobinson on PROD1PC70 with RULES
Background
The New Piper Aircraft, Inc., Vero
Beach, Florida, has made application to
revise the type design of the PA–44–180
model airplane. The model is currently
approved under the type certification
basis listed on Type Certificate Data
Sheets (TCDS) A19SO. 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, The New Piper Aircraft,
Inc., must show that affected airplane
models, as changed, continue to meet
the applicable provisions of the
regulations identified on the appropriate
TCDS. In addition, the type certification
basis of the airplanes embodying this
modification will include the additional
certification basis for installation of the
VerDate Aug<31>2005
13:51 Jan 12, 2006
Jkt 208001
Avidyne Entegra EFIS is: PA–44–180
model aircraft: 14 CFR Part 23
regulations FAR 23.301, 23.337, 23.341,
23.473, 23.561, 23.607, 23.611, as
amended by Amdt. 23–48; FAR 23.305,
23.397, 23.613, 23.773, 23.1525, 23.1549
as amended by Amdt. 23–45; FAR
23.777, 23.955, 23.1337 as amended by
Amdt. 23–51; FAR 23.1303, 23.1307,
23.1309, 23.1311, 23.1321, 23.1323,
23.1329, 23.1351, 23.1353, 23.1359,
23.1361, 23.1365, 23.1431 as amended
by Amdt. 23–49; FAR 23.1305 as
amended by Amdt. 23–52; FAR 23.1322,
23.1331, 23.1357 as amended by Amdt.
23–43; FAR 23.1325, 23.1543, 23.1545,
23.1555, 23.1563, 23.1581, 23.1583,
23.1585 as amended by Amdt. 23–50;
FAR 23.1523 as amended by Amdt. 23–
34; FAR 23.1529 as amended by Amdt.
23–26; FAR 23.1501 and 23.1541 as
amended by Amdt. 23–21; FAR 23.1327
as amended by Amdt. 23–20; and the
special conditions adopted by this
rulemaking action.
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
The New Piper Aircraft, 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, which are susceptible to the HIRF
environment, that 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
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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
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:
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Federal Register / Vol. 71, No. 9 / Friday, January 13, 2006 / Rules and Regulations
of a redundant system are likely to be
exposed to the fields concurrently.
Field strength
Frequency
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 ...........
(volts
per
meter)
Peak
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
The field strengths are expressed in terms
of peak root-mean-square (rms) values.
hsrobinson on PROD1PC70 with RULES
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
VerDate Aug<31>2005
13:51 Jan 12, 2006
Jkt 208001
Applicability
As discussed above, these special
conditions are applicable to New Piper
PA–44–180 model airplanes.
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 New Piper PA–44–
180 model airplanes modified by
installation of the factory optional
Avidyne Entegra EFIS system.
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
operations, and operational capabilities
of these systems to perform critical
functions, are not adversely affected
when the airplane is exposed to high
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Fmt 4700
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2145
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 January
6, 2006.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–341 Filed 1–12–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Airspace Docket No. 05–AWP–12]
Establishment of a Class E Enroute
Domestic Airspace Area, San Louis
Obispo, CA
Federal Aviation
Administration (FAA), DOT.
ACTION: Direct final rule; withdrawal.
AGENCY:
SUMMARY: This action withdraws the
direct final rule published in the
Federal Register on November 14, 2005,
(70 FR 69077). In that action, the FAA
proposed to establish a Class E enroute
domestic airspace west of San Luis
Obispo, CA, to replace existing Class G
uncontrolled airspace. The FAA has
determined that the boundaries of this
airspace will be revised and another
direct final rule resubmitted for
publication.
DATES: The direct final rule published
November 14, 2005 (70 FR 69077) is
withdrawn as of January 13, 2006.
FOR FURTHER INFORMATION CONTACT:
Francie Hope, Western Terminal
Operations Airspace Specialist, AWP–
520.3, Federal Aviation Administration,
15000 Aviation Boulevard, Lawndale,
California 90261, telephone (310) 725–
6502.
SUPPLEMENTARY INFORMATION: On
November 14, 2005, a direct final rule
was published in the Federal Register to
establish a Class E enroute domestic
airspace area west of San Luis Obispo to
contain aircraft while in Instrument
Flight Rules (IFR) conditions and under
control of Santa Barbara Terminal Radar
Approach Control (TRACON). On
November 2, 2005, airspace was
transferred from Los Angeles Air Route
Traffic Control Center (ARTCC) to Santa
Barbara TRACON. In order to provide
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]]>Agencies
[Federal Register Volume 71, Number 9 (Friday, January 13, 2006)]
[Rules and Regulations]
[Pages 2143-2145]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-341]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE238, Special Condition 23-178-SC]
Special Conditions; The New Piper Aircraft, Inc.; PA-44-180;
Protection of Systems for 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 The New Piper Aircraft,
Inc., Vero Beach, Florida, for a type design change for the PA-44-180
airplanes. These airplanes 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 Model 700-00006-XXX(), manufactured by Avidyne Corporation,
Inc. for which 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 (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 January 6,
2006. Comments must be received on or before February 13, 2006.
ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk,
Docket No. CE238, Room 506, 901 Locust, Kansas City, Missouri 64106.
All comments must be marked: Docket No. CE238. 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: Wes Ryan, Aerospace Engineer,
Standards Office (ACE-110), Small Airplane Directorate, Aircraft
Certification Service, Federal Aviation Administration, 901 Locust,
Room 301, Kansas City, Missouri 64106; telephone (816) 329-4127.
SUPPLEMENTARY INFORMATION: The FAA has determined that notice and
[[Page 2144]]
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. CE238.'' The postcard will be date stamped and
returned to the commenter.
Background
The New Piper Aircraft, Inc., Vero Beach, Florida, has made
application to revise the type design of the PA-44-180 model airplane.
The model is currently approved under the type certification basis
listed on Type Certificate Data Sheets (TCDS) A19SO. 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, The New Piper
Aircraft, Inc., must show that affected airplane models, as changed,
continue to meet the applicable provisions of the regulations
identified on the appropriate TCDS. In addition, the type certification
basis of the airplanes embodying this modification will include the
additional certification basis for installation of the Avidyne Entegra
EFIS is: PA-44-180 model aircraft: 14 CFR Part 23 regulations FAR
23.301, 23.337, 23.341, 23.473, 23.561, 23.607, 23.611, as amended by
Amdt. 23-48; FAR 23.305, 23.397, 23.613, 23.773, 23.1525, 23.1549 as
amended by Amdt. 23-45; FAR 23.777, 23.955, 23.1337 as amended by Amdt.
23-51; FAR 23.1303, 23.1307, 23.1309, 23.1311, 23.1321, 23.1323,
23.1329, 23.1351, 23.1353, 23.1359, 23.1361, 23.1365, 23.1431 as
amended by Amdt. 23-49; FAR 23.1305 as amended by Amdt. 23-52; FAR
23.1322, 23.1331, 23.1357 as amended by Amdt. 23-43; FAR 23.1325,
23.1543, 23.1545, 23.1555, 23.1563, 23.1581, 23.1583, 23.1585 as
amended by Amdt. 23-50; FAR 23.1523 as amended by Amdt. 23-34; FAR
23.1529 as amended by Amdt. 23-26; FAR 23.1501 and 23.1541 as amended
by Amdt. 23-21; FAR 23.1327 as amended by Amdt. 23-20; and the special
conditions adopted by this rulemaking action.
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
The New Piper Aircraft, 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, which are susceptible to the HIRF environment, that 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 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:
[[Page 2145]]
------------------------------------------------------------------------
Field strength
-----------------------------
Frequency (volts
per Peak Average
meter)
----------------------------------------------------------------- ---------
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 New
Piper PA-44-180 model airplanes.
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 New Piper PA-44-180 model airplanes
modified by installation of the factory optional Avidyne Entegra EFIS
system.
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 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 January 6, 2006.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-341 Filed 1-12-06; 8:45 am]
BILLING CODE 4910-13-P
