[Federal Register Volume 67, Number 74 (Wednesday, April 17, 2002)]
[Rules and Regulations]
[Pages 18807-18810]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-9115]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE181, Special Condition 23-115-SC]


Special Conditions; Raytheon Aircraft Models 200 and 300; 
Protection of Systems for 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 to Elliott Aviation, Inc., 
Quad City Airport, P.O. Box 100, Moline, Illinois 61266, for a 
Supplemental Type Certificate for the Raytheon Aircraft Model 200, 
B200, 200C, B200C, 200CT, B200CT, B200T, 300, 300LW, B300 and B300C. 
This airplane will have novel and unusual design features when compared 
to the state of technology envisaged in the applicable airworthiness 
standards. These novel and unusual design features include the 
installation of electronic flight instrument system (EFIS) displays 
manufactured by Universal Avionics Corporation 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 April 2, 2002. 
Comments must be received on or before May 17, 2002.

ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation 
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk, 
Docket No. CE181, Room 506, 901 Locust, Kansas City, Missouri 64106. 
All comments must be marked: Docket No. CE181. Comments may be 
inspected in the Rules Docket weekdays, except Federal holidays, 
between 7:30 a.m. and 4:00 p.m.

FOR FURTHER INFORMATION CONTACT: Ervin Dvorak, 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) 329-4123.

SUPPLEMENTARY INFORMATION: The FAA has determined that notice and 
opportunity for prior public comment hereon are impracticable because 
these procedures would significantly delay issuance of the approval 
design and thus delivery of the affected aircraft. In addition, the 
substance of these special conditions has been subject to the public 
comment process in several prior instances with no substantive comments 
received. The FAA, therefore, finds that good cause exists for making 
these special conditions effective upon issuance.

Comments Invited

    Interested persons are invited to submit such written data, views, 
or arguments as they may desire. Communications should identify the 
regulatory docket or notice number and be submitted in duplicate to the 
address specified above. All communications received on or before the 
closing date for comments will be considered by the Administrator. The 
special conditions may be changed in light of the comments received. 
All comments received will be available in the Rules Docket for 
examination by interested persons, both before and after the closing 
date for comments. A report summarizing each substantive public contact 
with FAA personnel concerning this rulemaking will be filed in the 
docket. Commenters wishing the FAA to acknowledge receipt of their 
comments submitted in response to this action must include a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. CE181.'' The postcard will be date stamped and 
returned to the commenter.

Background

    On December 28, 2001, Elliott Aviation, Inc., Quad City Airport, 
P.O. Box 100, Moline, Illinois 61266, made an application to the FAA 
for a new Supplemental Type Certificate for the Raytheon Aircraft Model 
200, B200, 200C, B200C, 200CT, B200CT, B200T, 300, 300LW, B300, and 
B300C. The aircraft is currently approved under TC No. A24CE, revision 
78. The proposed modification incorporates a novel or unusual design 
feature, such as digital avionics consisting of an EFIS, that is

[[Page 18808]]

vulnerable to HIRF external to the airplane.

Type Certification Basis

    Under the provisions of 14 CFR part 21, Sec. 21.101, Elliott 
Aviation, Inc. must show that the Raytheon 200 and 300 series aircraft 
meet the following provisions, or the applicable regulations in effect 
on the date of application for the change to the Model 200 and 300.
    Model 200 Series: 14 CFR part 23 effective February 1, 1965, as 
amended by 23-1 through 23-9, Amendment 23-11, 14 CFR part 23, 
Sec. 23.175, and associated part 23 Secs. 23.143(a), 23.145(d), 23.153, 
23.161(c)(3), and 23.173(a) as amended by Amendment 23-14; 
Sec. 23.951(c) and Sec. 23.997(d) as amended by Amendment 23-15 (A200CT 
and B200 series only); Sec. 23.1545(a) as amended by Amendment 23-23, 
and Sec. 23.1325(e) as amended by Amendment 23-20 (B200 Series only); 
Sec. 23.1305(n) as amended by Amendment 23-26; FAA Special Conditions 
23-47-CE-5 issued October 30, 1972, Amendment 1 dated December 18, 
1973, and Amendment 2 dated January 12, 1979; 14 CFR part 25, 
Secs. 25.929 and 25.1419 as amended to December 31, 1972, and 
Sec. 25.831(d) through Amendment 25-41 (for all Model 200 and B200 
series aircraft approved for 35,000 feet); SFAR 27 through Amendment 
27-4; and 14 CFR part 36 through Amendment 36-10. For B200 through 
Serial Number BB-1438 and B200C through Serial Number BL-138, part 36 
through amendment 36-10. For B200 Serial Numbers BB-1439, BB-1444 and 
after, B200C Serial Numbers BL-139 and after, A200CT Serial Numbers FE-
25 and after, part 36 through Amendment 36-20. Compliance with ice 
protection has been demonstrated in accordance with Sec. 25.1419 when 
ice protection equipment is installed in accordance with the airplane 
equipment list. Effective April 20, 1993, Electronic Flight Instrument 
Systems shall meet the requirements of Secs. 23.1301, 23.1309, 23.1311, 
23.1321, 23.1322, and 23.1335 as amended through Amendment 23-41 and 
Special Condition 23-ACW-68. Effective January 20, 1994, Sec. 23.1457 
as amended by Amendment 23-35. In addition, part 135 Appendix A, 
effective December 1, 1978 (B200 High Density Configuration). 
Equivalent Safety Findings: Sec. 23.621 (BB-2 through BB-1042 only); 
Sec. 23.997(d) (all models except A200CT and B200 series); Sec. 23.1443 
through Amendment 23-9-200 (BB-38, BB-39, BB-42, BB-44, BB-54 and 
after), 200C, 200CT, 200T, plus any earlier Model 200 modified by 
Beechcraft kits 101-5007 and 101-5008 in compliance with Beech Service 
instruction No. 0776-341. Model UC-12F (BU-1 through BU-12). Not 
Applicable to B200 Series. Special conditions adopted by this 
rulemaking action.
    Model 300 and 300LW: Special Federal Aviation Regulation (SFAR) 
41C, effective September 13, 1982 (300 only); 14 CFR part 23 effective 
February 1, 1965, through Amendment 23-9; Amendment 23-11; Amendment 
23-14, Secs. 23.143(a), 23.145(d), 23.153, 23.161(c)(3), 23.173(a), 
23.175, 23.427, 23.441, and 23.445; Amendment 23-15, Sec. 23.951(c) and 
Sec. 23.997(d); Secs. 23.1301, 23.1309, 23.1311, 23.1321, and 23.1322 
to Amendment 23-49; Amendment 23-23, Sec. 23.1545(a); Amendment 23-26, 
Secs. 23.967 and 23.1305(n); Special Conditions No. 23-47-CE-5, 
including Amendments Nos. 1, 2, 3 dated November 15, 1982, and 4 dated 
October 17, 1986; 14 CFR part 25, Sec. 25.929, effective February 1, 
1965, Amendment 25-23, Sec. 25.1419; Amendment 25-41, Sec. 25.831(d); 
14 CFR part 36 through Amendment 36-10, and SFAR 27 through Amendment 
27-4. Compliance with ice protection has been demonstrated in 
accordance with part 25, Sec. 25.1419 when ice protection equipment is 
installed in accordance with the Equipment List. Special conditions 
adopted by this rulemaking action.
    Model B300 and B300C: 14 CFR part 23 effective February 1, 1965, as 
amended by Amendments 23-1 through 23-34; 14 CFR part 36 effective 
December 1, 1969, as amended by Amendment 36-1 through 36-15; SFAR 27 
effective February 1, 1974, as amended by Amendments 27-1 through 27-6 
and Exemption No. 5077 from compliance with section 23.207(c). Special 
Conditions 23-ACE-48A effective August 13, 1990, apply to Electronic 
Flight Instrument System (EFIS) equipped airplanes. Part 23, 
Secs. 23.201, 23.203, 23.205 through amendment 23-45 (S/N FN-1 and up 
only). Effective January 20, 1994, Sec. 23.1457 as amended by Amendment 
23.35. Sections 23.1301, 23.1309, 23.1311, 23.1321, and 23.1322 to 
Amendment 23-49. Exemption 5599 from compliance with Sec. 23.53(c)(1), 
for use of ground minimum control speed (Vmcg) for 
determination of takeoff decision speed (V1), (serials FL-
111, FM-9, FN-2 and after, or prior airplanes modified by Beech Kit No. 
130-3004). Compliance with ice protection has been demonstrated in 
accordance with the Equipment List. Equivalent Level of Safety 
Findings: Sec. 23.781(b) for shape of the propeller control knob; 
Sec. 23.1305(g) for use of fuel low pressure warning annunciators in 
lieu of the fuel pressure indicators; Sec. 23.1321(d) for the basic 
``T'' instrument panel arrangement. 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.
    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

    Elliott Aviation, 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

[[Page 18809]]

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:

------------------------------------------------------------------------
                                                        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 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 
Raytheon Aircraft models 200, B200, 200C, B200C, 200CT, B200CT, B200T, 
300, 300LW, B300, B300C. Should Elliott Aviation, Inc. apply at a later 
date for a supplemental type certificate to modify any other model on 
the same type certificate to incorporate the same novel or unusual 
design feature, the special conditions would apply to that model as 
well under the provisions of Sec. 21.101.

Conclusion

    This action affects only certain novel or unusual design features 
on one model of airplane. It is not a rule of general applicability and 
affects only the applicant who applied to the FAA for approval of these 
features on the airplane.
    The substance of these special conditions has been subjected to the 
notice and comment period in several prior instances and has been 
derived without substantive change from those previously issued. It is 
unlikely that prior public comment would result in a significant change 
from the substance contained herein. For this reason, and because a 
delay would significantly affect the certification of the airplane, 
which is imminent, the FAA has determined that prior public notice and 
comment are unnecessary and impracticable, and good cause exists for 
adopting these special conditions upon issuance. The FAA is requesting 
comments to allow interested persons to submit views that may not have 
been submitted in response to the prior opportunities for comment 
described above.

List of Subjects in 14 CFR Part 23

    Aircraft, Aviation safety, Signs and symbols.

Citation

    The authority citation for these special conditions is as follows:

    Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and 
21.101; and 14 CFR 11.38 and 11.19.

The Special Conditions

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the following special conditions are issued as part of 
the type certification basis for the Raytheon Aircraft Model 200, B200, 
200C, B200C, 200CT, B200CT, B200T, 300, 300LW, B300, and B300C airplane 
modified by Elliott Aviation, Inc. to add an EFIS.
    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.


[[Page 18810]]


    Issued in Kansas City, Missouri on April 2, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-9115 Filed 4-16-02; 8:45 am]
BILLING CODE 4910-13-P