[Federal Register: December 21, 2004 (Volume 69, Number 244)]
[Rules and Regulations]
[Page 76389-76391]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21de04-7]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM294; Special Conditions No. 25-277-SC]
Special Conditions: Raytheon Aircraft Company Model MU-300 and
MU-300-10 Airplanes and Model 400 Airplanes; High-Intensity Radiated
Fields (HIRF)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; request for comments.
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SUMMARY: These special conditions are issued for Raytheon Aircraft
Company Model MU-300 and MU-300-10 airplanes and Model 400 airplanes
modified by Beechjet TECH. 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 installation of two Shadin
ADC-6400 RVSM-capable air data computers that perform critical
functions. The applicable airworthiness regulations do not contain
adequate or appropriate safety 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 that established by the existing airworthiness standards.
DATES: The effective date of these special conditions is December 6,
2004. Comments must be received on or before January 20, 2005.
ADDRESSES: Comments on these special conditions may be mailed in
duplicate to: Federal Aviation Administration, Transport Airplane
Directorate, Attention: Rules Docket (ANM-113), Docket No. NM294 1601
Lind Avenue, SW., Renton, Washington 98055-4056; or delivered in
duplicate to the Transport Airplane Directorate at the above address.
All comments must be marked Docket No. NM294.
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 participate in this
rulemaking by submitting 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. The docket is available for public
inspection 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 on or before 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.
Background
On July 19, 2004, Beechjet TECH, 4500 S. Garnett, Suite
600, Tulsa, Oklahoma 74146 applied for a supplemental type
certificate (STC) to modify Raytheon Aircraft Company Model MU-300 and
MU-300-10 airplanes and Model 400 airplanes. Model MU-300 is currently
approved under Type Certificate No. A14SW and Models MU-300-10 and 400
are currently approved under Type Certificate No. A16SW. The Raytheon
Aircraft Company Model MU-300 and MU-300-10 airplanes and Model 400
airplanes are small transport category airplanes powered by two
turbojet
[[Page 76390]]
engines. They operate with a 2-pilot crew and can seat up to 9
passengers. The modification incorporates the installation of two
Shadin ADC-6400 air data computers, with the capability for operating
the airplane at a reduced vertical separation minimum (RVSM). 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 the provisions of 14 CFR 21.101, Beechjet TECH must show that
the Raytheon Aircraft Company Model MU-300 and MU-300-10 airplanes and
Model 400 airplanes, as changed, continue to meet the applicable
provisions of the regulations incorporated by reference in Type
Certificates No. A16SW or A14SW, as applicable, or the applicable
regulations in effect on the date of application for the change. The
regulations incorporated by reference in the type certificate are
commonly referred to as the ``original type certification basis.'' The
certification bases for the Raytheon Aircraft Company Model MU-300 and
MU-300-10 airplanes and Model 400 airplanes include 14 CFR part 25, as
amended by Amendments 25-1 through 25-40; Sec. Sec. 25.1351(d),
25.1353(c)(5), and 25.1450 as amended by Amendment 25-41; Sec. Sec.
25.29, 25.255, and 25.1353(c)(6) as amended by Amendment 25-42; Sec.
25.361(b) as amended by Amendment 25-46; and 14 CFR part 36 as amended
by Amendment 36-1 through 36-12.
If the Administrator finds that the applicable airworthiness
regulations (i.e., part 25, as amended) do not contain adequate or
appropriate safety standards for the Raytheon Aircraft Company Model
MU-300 and MU-300-10 airplanes and Model 400 airplanes because of a
novel or unusual design feature, special conditions are prescribed
under the provisions of Sec. 21.16.
In addition to the applicable airworthiness regulations and special
conditions, the Raytheon Aircraft Company Model MU-300 and MU-300-10
airplanes and Model 400 airplanes must comply with the fuel vent and
exhaust emission requirements of 14 CFR part 34 and the noise
certification requirements of 14 CFR part 36.
Special conditions, as defined in 14 CFR 11.19, are issued in
accordance with Sec. 11.38 and become part of the type certification
basis in accordance with Sec. 21.101.
Special conditions are initially applicable to the model for which
they are issued. Should Beechjet TECH apply at a later date for a
supplemental type certificate to modify any other model included on
Type Certificate No. A16SW or A14SW, as applicable, to incorporate the
same or similar novel or unusual design feature, these special
conditions would also apply to the other model under the provisions of
Sec. 21.101.
Novel or Unusual Design Features
As noted earlier, the Raytheon Aircraft Company Model MU-300 and
MU-300-10 airplanes and Model 400 airplanes modified by Beechjet TECH
will incorporate two Shadin ADC-6400 RVSM-capable air data computers
that will 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. Accordingly, this system is considered 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 MU-300
and MU-300-10 airplanes and Model 400 airplanes modified by Beechjet
TECH. 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 due
to 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
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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
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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 MU-300 and MU-300-10 airplanes and
Model 400 airplanes modified by Beechjet TECH. Should Beechjet TECH
apply at a later date for a supplemental type certificate to modify any
other model included on Type Certificate No. A16SW or A14SW, as
applicable, to incorporate the same or similar novel or unusual design
feature, these special conditions would apply to
[[Page 76391]]
that model as well under the provisions of Sec. 21.101.
Conclusion
This action affects only certain novel or unusual design features
on Raytheon Aircraft Company Model MU-300 and MU-300-10 airplanes and
Model 400 airplanes modified by Beechjet TECH. 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 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.
0
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704.
The Special Conditions
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the following special conditions are issued as part of
the supplemental type certification basis for the Raytheon Aircraft
Company Model MU-300 and MU-300-10 airplanes and Model 400 airplanes
modified by Beechjet TECH.
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 December 6, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-27824 Filed 12-20-04; 8:45 am]
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