Special Conditions: Raytheon Aircraft Company Model BAe.125 Series 800A; High-Intensity Radiated Fields (HIRF), 9905-9907 [06-1808]
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Federal Register / Vol. 71, No. 39 / Tuesday, February 28, 2006 / Rules and Regulations
series airplanes. Should Elliott Aviation
Technical Product Development apply
at a later date for a supplemental type
certificate to modify any other model
included on Type Certificate No.
A27CEU to incorporate the same or
similar novel or unusual design feature,
these special conditions would apply to
that model as well under the provisions
of § 21.101.
Conclusion
This action affects only certain novel
or unusual design features on the
Cessna Model 501 and 551 series
airplanes modified by Elliott Aviation
Technical Product Development. 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 the special
conditions for these airplanes has been
subjected to the notice and comment
procedure in several prior instances and
has been derived without substantive
change from those previously issued.
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 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
I The authority citation for these
special conditions is as follows:
sroberts on PROD1PC70 with RULES
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
I 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 the Cessna Aircraft
Company Model 501 and 551 airplanes
modified by Elliott Aviation Technical
Product Development, Inc.
1. Protection from Unwanted Effects
of High-Intensity Radiated Fields
(HIRF). Each electronic and electrical
system that performs critical functions
must be designed and installed to
ensure that the operation and
operational capability of these systems
to perform critical functions are not
adversely affected when the airplane is
exposed to high intensity radiated
fields.
VerDate Aug<31>2005
16:27 Feb 27, 2006
Jkt 208001
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 Renton, Washington, on February
9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–1810 Filed 2–27–06; 8:45 am]
BILLING CODE 4910–13–P
9905
Directorate at the address indicated
above. You must mark your comments:
Docket No. NM388. You can inspect
comments in the Rules Docket
weekdays, except Federal Holidays,
between 7:30 a.m. and 4 p.m.
Greg
Dunn, FAA, Airplane and Flight Crew
Interface Branch, ANM–111, Transport
Airplane Directorate, Aircraft
Certification Service, 1601 Lind Avenue
SW., Renton, Washington 98055–4056;
telephone (425) 227–2799; facsimile
(425) 227–1320.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
DEPARTMENT OF TRANSPORTATION
Comments Invited
Federal Aviation Administration
The FAA has determined that notice
and opportunity for prior public
comment is impracticable because these
procedures would significantly delay
certification of the airplane 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; however, we invite interested
persons to take part in this rulemaking
by sending written comments, data, or
views. The most helpful comments
reference a specific portion of the
special conditions, explain the reason
for any recommended change, and
include supporting data. We ask that
you send us two copies of written
comments.
We will file in the docket all
comments we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning these special conditions.
You may inspect the docket before and
after the comment closing date. If you
wish to review the docket in person, go
to the address in the ADDRESSES section
of this preamble between 7:30 a.m. and
4 p.m., Monday through Friday, except
Federal holidays.
We will consider all comments we
receive by the closing date for
comments. We will consider comments
filed late if it is possible to do so
without incurring expense or delay. We
may change these special conditions
based on the comments we receive.
If you want the FAA to acknowledge
receipt of your comments on these
special conditions, include with your
comments a pre-addressed, stamped
postcard on which the docket number
appears. We will stamp the date on the
postcard and mail it back to you.
14 CFR Part 25
[Docket No. NM338, Special Conditions No.
25–312–SC]
Special Conditions: Raytheon Aircraft
Company Model BAe.125 Series 800A;
High-Intensity Radiated Fields (HIRF)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions; request
for comments.
AGENCY:
SUMMARY: These special conditions are
issued for Raytheon Aircraft Company
Model BAe.125 Series 800A airplanes
modified by Duncan Aviation Inc. These
modified airplanes will have a novel or
unusual design feature when compared
to the state of technology envisioned in
the airworthiness standards for
transport category airplanes. The
modification incorporates the
installation of the Honeywell Primus
Epic CDS/R Display System. The
applicable airworthiness regulations do
not contain adequate or appropriate
safety standards for protecting these
systems from the effects of highintensity radiated fields (HIRF). These
special conditions contain the
additional safety standards 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 February 9, 2006.
We must receive your comments by
March 30, 2006.
ADDRESSES: You must mail two copies
of your comments to: Federal Aviation
Administration, Transport Airplane
Directorate, Attention: Rules Docket
(ANM–113), Docket No. NM338, 1601
Lind Avenue SW., Renton, Washington
98055–4056. You may deliver two
copies to the Transport Airplane
PO 00000
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Fmt 4700
Sfmt 4700
E:\FR\FM\28FER1.SGM
28FER1
9906
Federal Register / Vol. 71, No. 39 / Tuesday, February 28, 2006 / Rules and Regulations
Background
On October 15, 2005, Duncan
Aviation, Inc., 3701 Aviation Road,
Lincoln, NE 68524, applied for a
supplemental type certificate (STC) to
modify Raytheon Aircraft Company
Model BAe.125 Series 800A airplanes
currently approved under Type
Certificate No. A3EU. The Model
BAe.125 Series 800A airplanes are small
transport category airplanes. They are
powered by two turbojet engines, with
maximum takeoff weight of 31,000
pounds as modified by Modification No.
253379A or 26,866 pounds as modified
by Modification No. 25B047A. These
airplanes operate with 2-person crew
and can seat up to 15 passengers. The
proposed modification is to install
Honeywell Primus EPIC Cockpit Display
System. The avionics/electronics and
electrical systems installed in this
airplane have the potential to be
vulnerable to high-intensity radiated
fields (HIRF) external to the airplane.
sroberts on PROD1PC70 with RULES
Type Certification Basis
Under 14 CFR 21.101, Duncan
Aviation, Inc. must show the Raytheon
Aircraft Company Model BAe.125 Series
800A aircraft, as changed, continue to
meet the applicable provisions of the
regulations incorporated by reference in
Type Certificate No. A3EU. They must
also continue to meet the applicable
regulations in effect on the date of
application for the change. We
commonly refer to the regulations
incorporated by reference in the type
certificate as the ‘‘original type
certification basis.’’ The regulations
incorporated by reference in Type
Certificate No. A3EU include Part 10 of
the British Civil Airworthiness
Requirements. This certification is
equivalent to Civil Air Regulations
(CAR) 4b dated December 1953, as
amended by Amendment 4b-1 through
Amendment 4b-11, exclusive of CAR 4b
350(e). It includes Special Regulation
SR 422B. In addition, the certification
basis includes certain later amendments
to 14 CFR part 25 that are not relevant
to these special conditions.
If the Administrator finds that the
applicable airworthiness regulations
(i.e., part 25, amended) do not contain
adequate or appropriate safety standards
for the Duncan Aviation, Inc., Raytheon
Aircraft Company Model Bae.125, Series
800A airplanes, because of a novel or
unusual design feature, special
conditions are prescribed under § 21.16.
Besides the applicable airworthiness
regulations and special conditions, the
Raytheon Aircraft Company Model
BAe.125, Series 800A airplanes, must
comply with the fuel vent exhaust
VerDate Aug<31>2005
16:27 Feb 27, 2006
Jkt 208001
emission requirements of 14 CFR part
34. It must also comply with the noise
certification requirements of 14 CFR
part 36.
We issue special conditions, as
defined in 14 CFR 11.19, under § 11.38
and they become part of the type
certification basis under § 21.101.
Special conditions are initially
applicable to the model for which they
are issued. Should Duncan Aviation
Inc., apply later for a supplemental type
certificate to modify any other model
included on Type Certificate No. A3EU
to incorporate the same or similar novel
or unusual design feature, these special
conditions would also apply to the other
model under § 21.101.
Novel or Unusual Design Features
As noted earlier, the Raytheon
Aircraft Company Model BAe.125 Series
800A aircraft, as modified by Duncan
Aviation, Inc., will incorporate the
Honeywell Primus EPIC Cockpit Display
System. The EPIC Displays perform
critical functions. These systems may be
vulnerable to high-intensity radiated
fields external to the airplane. The
current airworthiness standards of part
25 do not contain adequate or
appropriate safety standards for the
protection of this equipment from the
adverse effects of HIRF. Therefore, we
consider this system to be a novel or
unusual design feature.
Discussion
There is no specific regulation that
addresses protection requirements for
electrical and electronic systems from
HIRF. Increased power levels from
ground-based radio transmitters and the
growing use of sensitive avionics/
electronics and electrical systems to
command and control airplanes have
made it necessary to provide adequate
protection.
To ensure that a level of safety is
achieved equivalent to that intended by
the regulations incorporated by
reference, special conditions are needed
for the Raytheon Aircraft Company
Model BAe.125 Series 800A airplanes as
modified by Duncan Aviation, Inc.
These special conditions require that
new avionics/electronics and electrical
systems that perform critical functions
be designed and installed to preclude
component damage and interruption of
function because of both the direct and
indirect effects of HIRF.
High-Intensity Radiated Fields (HIRF)
With the trend toward increased
power levels from ground-based
transmitters, and the advent of space
and satellite communications, coupled
with electronic command and control of
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
the airplane, the immunity of critical
avionics/electronics and electrical
systems to HIRF must be established.
It is not possible to precisely define
the HIRF to which the airplane will be
exposed in service. There is also
uncertainty concerning the effectiveness
of airframe shielding for HIRF.
Furthermore, coupling of
electromagnetic energy to cockpitinstalled equipment through the cockpit
window apertures is undefined. Based
on surveys and analysis of existing HIRF
emitters, an adequate level of protection
exists when compliance with the HIRF
protection special condition is shown
with either paragraph 1 OR 2 below:
1. A minimum threat of 100 volts rms
(root-mean-square) per meter electric
field strength from 10 KHz to 18 GHz.
a. The threat must be applied to the
system elements and their associated
wiring harnesses without the benefit of
airframe shielding.
b. Demonstration of this level of
protection is established through system
tests and analysis.
2. A threat external to the airframe of
the field strengths identified in the table
below for the frequency ranges
indicated. Both peak and average field
strength components from the table are
to be demonstrated.
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
700
700
2000
3000
3000
1000
3000
2000
600
Average
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 of the root-mean-square (rms) over
the complete modulation period.
The threat levels identified above are
the result of an FAA review of existing
studies on the subject of HIRF, in light
of the ongoing work of the
Electromagnetic Effects Harmonization
Working Group of the Aviation
Rulemaking Advisory Committee.
Applicability
As discussed above, these special
conditions are applicable to Raytheon
Aircraft Company Model BAe.125 Series
E:\FR\FM\28FER1.SGM
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Federal Register / Vol. 71, No. 39 / Tuesday, February 28, 2006 / Rules and Regulations
800A airplanes modified by Duncan
Aviation, Inc. Should Duncan Aviation,
Inc. apply later for a supplemental type
certificate to modify any other model
included on Type Certificate No. A3EU
to incorporate the same or similar novel
or unusual design feature, these special
conditions would apply to that model as
well under § 21.101.
Conclusion
This action affects only certain novel
or unusual design features on Raytheon
Aircraft Company Model BAe.125 Series
800A airplanes as modified by Duncan
Aviation, Inc. 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 procedure in
several prior instances and has been
derived without substantive change
from those previously issued. 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 send views that
may not have been sent in response to
the prior opportunities for comment
described above.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
special conditions is as follows:
sroberts on PROD1PC70 with RULES
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
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
Raytheon Aircraft Company Model
BAe.125 Series 800A airplanes modified
by Duncan Aviation, Inc.
1. Protection from Unwanted Effects
of High-Intensity Radiated Fields
(HIRF). Each electrical and electronic
system that performs critical functions
must be designed and installed to
ensure that the operation and
operational capability of these systems
to perform critical functions are not
adversely affected when the airplane is
exposed to high-intensity radiated
fields.
2. For the purpose of these special
conditions, the following definition
VerDate Aug<31>2005
16:27 Feb 27, 2006
Jkt 208001
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 Renton, Washington, on February
9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–1808 Filed 2–27–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Parts 47 and 49
Federal Aviation
Administration (FAA), DOT.
AGENCY:
Notice in regards to processes at
the FAA, Civil Aviation Registry,
Aircraft Registration Branch (Registry),
in relation to implementation of the
Cape Town Treaty (Treaty).
ACTION:
SUMMARY: On January 3, 2005, the FAA
published final rules implementing the
Cape Town Treaty. on February 17,
2006, the FAA published a notice
advising that the Cape Town Treaty
becomes effective for the United States
on March 1, 2006. The FAA is
publishing this document to advise
interested persons of certain procedures
in the Aircraft Registration Branch
related to the Cape Town Treaty.
Effective Date: March 1, 2006.
FOR FURTHER INFORMATION CONTACT:
Walter Binkley, Manager, Aircraft
Registration Branch (AFS–750), Mike
Monroney Aeronautical Center, Federal
Aviation Administration (AFS–750),
Post Office Box 25504, Oklahoma City,
OK 73125. Telephone (405) 954–3131.
The Cape
Town Treaty Implementation Act of
2004, Public Law 108–297, required
conforming changes to the regulations
concerning registration and
deregistration of aircraft, among other
things. The amendments have been
made and published. The Registry is
taking this opportunity to advise
interested persons of the Registry’s
practices for processing certain
documents related to the Cape Town
Treaty. These matters are largely
procedural in nature.
SUPPLEMENTARY INFORMATION:
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
Acceptance of Instruments for Aircraft
Objects Subject to the Treaty
Pursuant to amendments made to 14
CFR part 49, to include § 49.63, FAA
requires that documents representing
transactions meeting the requirements
of subpart C of this part accompany the
completed Entry Point Filing Form—
International Registry, AC Form 8050–
135, unless the form is submitted in
connection with a notice of a
prospective international interest.
Because the Treaty does not enter into
force for the United States until March
1, 2006, instruments completed prior to
March 1, 2006, will continue to be
processed in accordance with the
Geneva Convention.
Interim List of Eligible Aircraft
Federal Aviation Administration, Civil
Aviation Registry, Aircraft Registration
Branch Practices Related to the Cape
Town Treaty
DATES:
9907
Article 2 of the Convention on
International Interests in Mobile
Equipment provides for an international
interest in certain categories of mobile
equipment and associated rights. The
convention refers to uniquely
identifiable objects as designated in the
Aircraft protocol to the Convention on
International Interests in Mobile
Equipment on Matters Specific to
Aircraft Equipment (Protocol).
Designated aircraft equipment includes:
(1) Airframes, that when appropriate
aircraft engines are installed thereon,
are type certified by the competent
aviation authority to transport at least
eight (8) persons including crew; or
goods in excess of 2750 kilograms;
(2) Helicopters, heavier-than-air
machines, supported in flight chiefly by
the reactions of the air on one or more
power-driven rotors on substantially
vertical axes and which are type
certified by the competent aviation
authority to transport at least five (5)
persons including crew; or goods in
excess of 450 kilograms; and
(3) Aircraft engines, powered by jet
propulsion or turbine or piston
technology and:
(a) in the case of jet propulsion
aircraft engines, have at least 1750 lb of
thrust or its equivalent; and
(b) in the case of turbine-powered or
piston-powered aircraft engines, have at
least 550 rated take-off shaft horsepower
or its equivalent.
Since a sanctioned comprehensive list
prepared by an appropriate authority
containing the manufacturer, model and
serial number for each aircraft object
subject to the Treaty has not yet been
provided to the Contracting States; FAA
will begin accepting documents related
to the Cape Town Treaty on March 1,
2006, based on an interim updatable list
of eligible aircraft objects compiled by
the FAA. The eligibility of any aircraft
E:\FR\FM\28FER1.SGM
28FER1
]]>Agencies
[Federal Register Volume 71, Number 39 (Tuesday, February 28, 2006)]
[Rules and Regulations]
[Pages 9905-9907]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-1808]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM338, Special Conditions No. 25-312-SC]
Special Conditions: Raytheon Aircraft Company Model BAe.125
Series 800A; High-Intensity Radiated Fields (HIRF)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; request for comments.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for Raytheon Aircraft
Company Model BAe.125 Series 800A airplanes modified by Duncan Aviation
Inc. These modified airplanes will have a novel or unusual design
feature when compared to the state of technology envisioned in the
airworthiness standards for transport category airplanes. The
modification incorporates the installation of the Honeywell Primus Epic
CDS/R Display System. The applicable airworthiness regulations do not
contain adequate or appropriate safety standards for protecting these
systems from the effects of high-intensity radiated fields (HIRF).
These special conditions contain the additional safety standards 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 February 9,
2006. We must receive your comments by March 30, 2006.
ADDRESSES: You must mail two copies of your comments to: Federal
Aviation Administration, Transport Airplane Directorate, Attention:
Rules Docket (ANM-113), Docket No. NM338, 1601 Lind Avenue SW., Renton,
Washington 98055-4056. You may deliver two copies to the Transport
Airplane Directorate at the address indicated above. You must mark your
comments: Docket No. NM388. You can inspect comments in the Rules
Docket weekdays, except Federal Holidays, between 7:30 a.m. and 4 p.m.
FOR FURTHER INFORMATION CONTACT: Greg Dunn, FAA, Airplane and Flight
Crew Interface Branch, ANM-111, Transport Airplane Directorate,
Aircraft Certification Service, 1601 Lind Avenue SW., Renton,
Washington 98055-4056; telephone (425) 227-2799; facsimile (425) 227-
1320.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA has determined that notice and opportunity for prior public
comment is impracticable because these procedures would significantly
delay certification of the airplane 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; however, we invite interested persons to take part in this
rulemaking by sending written comments, data, or views. The most
helpful comments reference a specific portion of the special
conditions, explain the reason for any recommended change, and include
supporting data. We ask that you send us two copies of written
comments.
We will file in the docket all comments we receive, as well as a
report summarizing each substantive public contact with FAA personnel
concerning these special conditions. You may inspect the docket before
and after the comment closing date. If you wish to review the docket in
person, go to the address in the ADDRESSES section of this preamble
between 7:30 a.m. and 4 p.m., Monday through Friday, except Federal
holidays.
We will consider all comments we receive by the closing date for
comments. We will consider comments filed late if it is possible to do
so without incurring expense or delay. We may change these special
conditions based on the comments we receive.
If you want the FAA to acknowledge receipt of your comments on
these special conditions, include with your comments a pre-addressed,
stamped postcard on which the docket number appears. We will stamp the
date on the postcard and mail it back to you.
[[Page 9906]]
Background
On October 15, 2005, Duncan Aviation, Inc., 3701 Aviation Road,
Lincoln, NE 68524, applied for a supplemental type certificate (STC) to
modify Raytheon Aircraft Company Model BAe.125 Series 800A airplanes
currently approved under Type Certificate No. A3EU. The Model BAe.125
Series 800A airplanes are small transport category airplanes. They are
powered by two turbojet engines, with maximum takeoff weight of 31,000
pounds as modified by Modification No. 253379A or 26,866 pounds as
modified by Modification No. 25B047A. These airplanes operate with 2-
person crew and can seat up to 15 passengers. The proposed modification
is to install Honeywell Primus EPIC Cockpit Display System. The
avionics/electronics and electrical systems installed in this airplane
have the potential to be vulnerable to high-intensity radiated fields
(HIRF) external to the airplane.
Type Certification Basis
Under 14 CFR 21.101, Duncan Aviation, Inc. must show the Raytheon
Aircraft Company Model BAe.125 Series 800A aircraft, as changed,
continue to meet the applicable provisions of the regulations
incorporated by reference in Type Certificate No. A3EU. They must also
continue to meet the applicable regulations in effect on the date of
application for the change. We commonly refer to the regulations
incorporated by reference in the type certificate as the ``original
type certification basis.'' The regulations incorporated by reference
in Type Certificate No. A3EU include Part 10 of the British Civil
Airworthiness Requirements. This certification is equivalent to Civil
Air Regulations (CAR) 4b dated December 1953, as amended by Amendment
4b-1 through Amendment 4b-11, exclusive of CAR 4b 350(e). It includes
Special Regulation SR 422B. In addition, the certification basis
includes certain later amendments to 14 CFR part 25 that are not
relevant to these special conditions.
If the Administrator finds that the applicable airworthiness
regulations (i.e., part 25, amended) do not contain adequate or
appropriate safety standards for the Duncan Aviation, Inc., Raytheon
Aircraft Company Model Bae.125, Series 800A airplanes, because of a
novel or unusual design feature, special conditions are prescribed
under Sec. 21.16.
Besides the applicable airworthiness regulations and special
conditions, the Raytheon Aircraft Company Model BAe.125, Series 800A
airplanes, must comply with the fuel vent exhaust emission requirements
of 14 CFR part 34. It must also comply with the noise certification
requirements of 14 CFR part 36.
We issue special conditions, as defined in 14 CFR 11.19, under
Sec. 11.38 and they become part of the type certification basis under
Sec. 21.101.
Special conditions are initially applicable to the model for which
they are issued. Should Duncan Aviation Inc., apply later for a
supplemental type certificate to modify any other model included on
Type Certificate No. A3EU to incorporate the same or similar novel or
unusual design feature, these special conditions would also apply to
the other model under Sec. 21.101.
Novel or Unusual Design Features
As noted earlier, the Raytheon Aircraft Company Model BAe.125
Series 800A aircraft, as modified by Duncan Aviation, Inc., will
incorporate the Honeywell Primus EPIC Cockpit Display System. The EPIC
Displays perform critical functions. These systems may be vulnerable to
high-intensity radiated fields external to the airplane. The current
airworthiness standards of part 25 do not contain adequate or
appropriate safety standards for the protection of this equipment from
the adverse effects of HIRF. Therefore, we consider this system to be a
novel or unusual design feature.
Discussion
There is no specific regulation that addresses protection
requirements for electrical and electronic systems from HIRF. Increased
power levels from ground-based radio transmitters and the growing use
of sensitive avionics/electronics and electrical systems to command and
control airplanes have made it necessary to provide adequate
protection.
To ensure that a level of safety is achieved equivalent to that
intended by the regulations incorporated by reference, special
conditions are needed for the Raytheon Aircraft Company Model BAe.125
Series 800A airplanes as modified by Duncan Aviation, Inc. These
special conditions require that new avionics/electronics and electrical
systems that perform critical functions be designed and installed to
preclude component damage and interruption of function because of both
the direct and indirect effects of HIRF.
High-Intensity Radiated Fields (HIRF)
With the trend toward increased power levels from ground-based
transmitters, and the advent of space and satellite communications,
coupled with electronic command and control of the airplane, the
immunity of critical avionics/electronics and electrical systems to
HIRF must be established.
It is not possible to precisely define the HIRF to which the
airplane will be exposed in service. There is also uncertainty
concerning the effectiveness of airframe shielding for HIRF.
Furthermore, coupling of electromagnetic energy to cockpit-installed
equipment through the cockpit window apertures is undefined. Based on
surveys and analysis of existing HIRF emitters, an adequate level of
protection exists when compliance with the HIRF protection special
condition is shown with either paragraph 1 OR 2 below:
1. A minimum threat of 100 volts rms (root-mean-square) per meter
electric field strength from 10 KHz to 18 GHz.
a. The threat must be applied to the system elements and their
associated wiring harnesses without the benefit of airframe shielding.
b. Demonstration of this level of protection is established through
system tests and analysis.
2. A threat external to the airframe of the field strengths
identified in the table below for the frequency ranges indicated. Both
peak and average field strength components from the table are to be
demonstrated.
------------------------------------------------------------------------
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 of the root-mean-
square (rms) over the complete modulation period.
The threat levels identified above are the result of an FAA review
of existing studies on the subject of HIRF, in light of the ongoing
work of the Electromagnetic Effects Harmonization Working Group of the
Aviation Rulemaking Advisory Committee.
Applicability
As discussed above, these special conditions are applicable to
Raytheon Aircraft Company Model BAe.125 Series
[[Page 9907]]
800A airplanes modified by Duncan Aviation, Inc. Should Duncan
Aviation, Inc. apply later for a supplemental type certificate to
modify any other model included on Type Certificate No. A3EU to
incorporate the same or similar novel or unusual design feature, these
special conditions would apply to that model as well under Sec.
21.101.
Conclusion
This action affects only certain novel or unusual design features
on Raytheon Aircraft Company Model BAe.125 Series 800A airplanes as
modified by Duncan Aviation, Inc. 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 procedure in several prior instances and has been
derived without substantive change from those previously issued.
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 send views that may
not have been sent in response to the prior opportunities for comment
described above.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting and recordkeeping
requirements.
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704.
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 Raytheon Aircraft Company
Model BAe.125 Series 800A airplanes modified by Duncan Aviation, Inc.
1. Protection from Unwanted Effects of High-Intensity Radiated
Fields (HIRF). Each electrical and electronic system that performs
critical functions must be designed and installed to ensure that the
operation and operational capability of these systems to perform
critical functions are not adversely affected when the airplane is
exposed to high-intensity radiated fields.
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 Renton, Washington, on February 9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-1808 Filed 2-27-06; 8:45 am]
BILLING CODE 4910-13-P
