[Federal Register: February 25, 2004 (Volume 69, Number 37)]
[Rules and Regulations]
[Page 8551-8555]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25fe04-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE203, Special Condition 23-143-SC]
Special Conditions; Avidyne Corporation, Inc.; Various Airplane
Models; 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 Avidyne Corporation, 55
Old Bedford Road, Lincoln, MA 01773, for a Supplemental Type
Certificate for the models listed under the heading ``Type
Certification Basis.'' This special condition includes various airplane
models to streamline the certification process needed to improve the
safety of the airplane fleet by fostering the incorporation of new
technologies that can be certificated affordably under 14 CFR part 23.
The 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 an electronic flight instrument system
(EFIS) display, Model 700-00006- 1XX(), 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 February 11,
2004. Comments must be received on or before March 26, 2004.
ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk,
Docket No. CE203, Room 506, 901 Locust, Kansas City, Missouri 64106.
All comments must be marked: Docket No. CE203. 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
opportunity for prior public comment hereon are impracticable because
these procedures would significantly delay issuance of the approval
design and 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. CE203.'' The postcard will be date stamped and
returned to the commenter.
Background
On July 3, 2003, Avidyne Corporation, 55 Old Bedford Road, Lincoln,
MA 01773, made an application to the FAA for a new Supplemental Type
Certificate for airplane models listed under the type certification
basis. The models are currently approved under the type certification
basis listed in the paragraph headed ``Type Certification Basis.'' 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, Avidyne
Corporation must show that affected airplane models, as changed,
continue to meet the applicable provisions, of the regulations
incorporated by reference in Type Certificate Numbers listed below 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'' and can be found in the Type Certificate Numbers
listed below. In addition, the type certification basis of airplane
models that embody this modification will include Sec. 23.1301 of
Amendment 23-20; Sec. Sec. 23.1309, 23.1311, and 23.1321 of Amendment
[[Page 8552]]
23-49; and Sec. 23.1322 of Amendment 23-43; exemptions, if any; and
the special conditions adopted by this rulemaking action.
----------------------------------------------------------------------------------------------------------------
Type Certificate
Aircraft make Aircraft model(s) No. Certification basis
----------------------------------------------------------------------------------------------------------------
Aerostar Aircraft Corporation.... PA-60-600, PA-60-601, PA- A17WE FAR 23
60-601P, PA60-602P, PA-
60-700P.
360, 400................. A11WE FAR 23
American Champion................ 7AC, 7ACA, S7AC, 7BCM, A-759 CAR 3
7CCM, S7CCM, 7DC, S7DC,
7EC, S7EC, 7ECA, 7FC,
7GC, 7GCA, 7GCB, 7GCBA,
7GCBC, 7GCAA, 7HC, 7JC,
7KC, 7KCAB.
8GCBC, 8KCAB............. A21CE FAR 23
Cessna Aircraft Company.......... 140A..................... 5A2 CAR 3
150, 150A, 150B, 150C, 3A19 CAR 3
150D, 150E, 150F, 150G,
150H, 150J, 150K, A150K,
150L, A150L, 150M,
A150M, 152, A152.
Cessna Aircraft Company (cont'd). 170, 170A, 170B.......... A-799 CAR 3
172, 172A, 172B, 172C, 3A12 CAR 3, 14 CFR 23
172D, 172E, 172F, 172G,
172H, 172I, 172K, 172L,
172M, 172N, 172P, 172Q,
172R, 172S.
172RG, P172D, R172E, 3A17 CAR 3
R172F, R172G, R172H,
R172J, R172K, 175, 175A,
175B, 175C.
177, 177A, 177B, 177RG... A13CE 14 CFR 23
180, 180A, 180B, 180C, 5A6 CAR 3
180D, 180E, 180F, 180G,
180H, 180J, 180K.
182, 182A, 182B, 182C, 3A13 CAR 3, 14 CFR 23
182D, 182E, 182F, 182G,
182H, 182J, 182K, 182L,
182M, 182N, 182P, 182Q,
182R, 182S, R182, T182,
TR182.
185, 185A, 185B, 185C, 3A24 CAR 3
185D, 185E, A185E, A185F.
190, 195, 195A, 195B..... A-790 CAR 3
210, 210A, 210B, 210C, 3A21 CAR 3
210D, 210E, 210F, T210F,
210G, T210G, 210H,
T210H, 210J, T210J,
210K, T210K, 210L,
T210L, 210M, T210M,
210N, P210N, T210N,
210R, P210R, T210-R, 210-
5, 210-5A.
205, 206, P206, P206-A, A4CE CAR 3, 14 CFR 23
P206-B, P206-C, P206-D,
P206-E, TP206-A, TP206-
B, TP206-C, TP206-D,
TP206-E, U206, U206-A,
U206-B, U206-C, U206-D,
U206-E, U206-F, U206-G,
TU206A, TU206-B, TU206-
C, TU206-D, TU206-E,
TU206-F, TU206-G, 206H,
T206H.
207, 207A, T207, T207A... A16CE 14 CFR 23
208, 208A, 208B.......... A37CE 14 CFR 23
310, 310A (USAF U-3A), 3A10 CAR 3
310B, 310C, 310D, 310E
(USAF U-3B), 310F, 310G,
310H, E310H, 310I, 310J,
310J-1, E310J, 310K,
310L, 310N, 310P, T310P,
310Q, T310Q, 310R, T310R.
320, 320-1, 320A, 320B, 3A25 CAR 3
320C, 320D, 320E, 320F,
340, 340A, 335, 340,
340A.
336...................... A2CE CAR 3
Cessna Aircraft Company (cont'd). 337 and 337A (USAF O2B), A6CE CAR 3, 14 CFR 23
337B, T337B, 337C,
T337C, 337D, T337D,
M337B (USAF O2A), 337E,
T337E and T337F, 337F,
T337G, 337G, 337H,
T337H, P337H, T337H-SP.
401, 401A, 401B, 402, A7CE CAR 3
402A, 402B, 402C, 411,
411A, 414, 414A, 421,
421A, 421B, 421C, 425.
441...................... A28CE FAR23
404, 406................. A25CE FAR23
500...................... A22CE FAR23
501, 551................. A27CE FAR23
525, 525A................ A1WI FAR23
Cirrus Design Corp............... SR20, SR22............... A00009CH FAR23
Commander Aircraft............... 112, 114, 112TC, 112B, A12SO CAR 3
112TCA, 114A, 114B,
114TC.
De Havilland Inc................. DHC-2 Mk. I, DHC-2 Mk. A-806 CAR 3
II, DHC-2 Mk. III.
(Twin Otter) DHC-6-1, DHC- A9EA CAR 3
6-100, DHC-6-200, DHC-6-
300.
Diamond Aircraft Industries...... DA 20-A1, DA20-C1........ TA4CH 14 CFR 23
DA40..................... A47CE 14 CFR 23
Fairchild........................ SA26-T, SA26-AT, SA226-T, A5SW CAR 3
SA226-AT, SA226-T(B),
SA227-AT, SA227-TT.
SA-226-TC, SA227-AC (C- A8SW 14 CFR 23
26A), SA227-BC (C-26A),
SA227-PC.
Lancair.......................... Columbia 300, LC40-550FG. A00003SE 14 CFR 23
Learjet.......................... 23....................... A5CE CAR 3
Maule Aerospace Technology, Inc.. BEE DEE M-4, M-4, M-4C, M- 3A23 CAR 3
4S, and M-4T, M-4-210, M-
4-210C, M-4-210S, and M-
4-210T, M-4-220, M-4-
220C, M-4-220S, and M-4-
220T, M-4-180C, M-4-
180S, and M-4-180T, M-5-
210C, M-5-220C, M-5-
235C, M-5-180C, M-5-
210TC, M-6-235, M-6-180,
M-5-200, M-7-235, MX-7-
235, MX-7-180, MX-7-420,
MXT-7-180, MT-7-235, M-8-
235, MX-7-160, MXT-7-
160, MX-7-180A, MXT-7-
180A, MX-7-180B, MXT-7-
420, M-7-235B, M-7-235A,
M-7-235C, MX-7-180C.
M-7-260, M-7-420, M7-7- 3A23 CAR3
260, MT-7-420, M-7-260C.
Mitsubishi Heavy Industries, Ltd. MU-2B-25, MU-2B-35, MU-2B- A10SW CAR 3
26, MU-2B-36, MU-2B-26A,
MU-2B-36A, MU-28-40, MU-
2B-60.
[[Page 8553]]
Mooney Aircraft Corp............. M20, M20A, M20B, M20C, 2A3 CAR 3
M20D, M20E, M20F, M20G,
M20J, M20K, M20L, M20M,
M20R, M20S.
M22...................... A6SW CAR 3
Partenavia Costruzioni P 68, P 68B, P 68C, P 68C- A31EU 14 CFR 23
Aeronauticas S.p.A. TC, P 68 ``OBSERVER'',
AP68 TP series 300
``SPARTACUS'', P68TC,
``OBSERVER'', AP68TP 600
``VIATOR'', P68
``OBSERVER 2''.
VA300....................
The New Piper Aircraft, Inc...... PA-23, PA-23-160, PA-23- 1A10 CAR 3
235, PA-23-250, PA-E23-
250.
PA-28-140, PA-28-150, PA- 2A13 CAR 3
28-151, PA-28-160, PA-28-
180, PA-28S-160, PA-28S-
180, PA-28-235, PA-28-
236, PA-28R-180, PA-28R-
200, PA-28-181, PA-28-
161, PA-28R-201, PA-28R-
201T, PA-28RT-201, PA-
28RT-201T, PA-28-201T.
PA-30, PA-39, PA-40...... A1EA CAR 3
PA-31, PA-31-300, PA-31- A20SO CAR 3
325, PA-31-350.
PA-31P, PA-31T, PA-31T1, A8EA CAR 3
PA-31T2, PA-31T3, PA-31P-
350.
PA-32-260, PA-32-300, PA- A3SO CAR 3
32S-300, PA-32R-300, PA-
32RT-300, PA-32RT-300T,
PA-32R-301 (SP), PA-32R-
301 (HP), PA-32R-301T,
PA-32-301, PA-32-301T.
PA-34-200, PA-34-200T, PA- A7SO CAR 3
34-220T, PA-34-220T
(III), PA-34-220T (IV).
PA-42, PA-42-720, PA-42- A23SO FAR 23
1000.
PA-42-720R............... A32SO FAR 23
PA-44-180, PA-44-180T.... A19SO 14 CFR 23
PA-38-112................ A18SO 14 CFR 23
PA-46-310P, PA-46-350P... A25SO 14 CFR 23
Raytheon Aircraft Company........ H35, J35, K35, M35, 35- 3A15 CAR 3
33, N35, 35-A355, 35-
B33, P35, S35, 35-C33,
E33, F33, V35, V35A,
V35B, 35-C33A, E33A,
E33C, 36, A36, F33A,
F33C, G33, A36TC, B36TC.
Raytheon Aircraft Company 95, B95, 95-55, 95-A55, 3A16 CAR 3
(cont'd). B95A, D95A, E95, 95-B55,
95-B55A, 95-B55B, 95-
C55, D55, 95-C55A, D55A,
E55, E55A, 56TC, A56TC,
58, 58A.
58P, 58PA, 58TC, 58TCA... A23CE 14 CFR 23
F90...................... A31CE FAR 23
99, 99A, 99A (FACH), A99, A14CE FAR 23
A99A, B99, C99, 100,
A100 (U-21F), A100A,
A100C, B100.
200, A100-1 (U-21J), A24CE FAR 23
200C, 200CT, 200T, A200
(C-12A) or (C-12C),
A200C (UC-12B), A200CT
(C-12D) or (FWC-12D) or
(RC-12D) or (C-12F) or
(RC-12G), or (RC-12H) or
(RC-12K) or (RC-12P) or
(RC-12Q), B200, B200C (C-
12F) or (UC-12F) or (UC-
12M), or (C-12R),
B200CT, B200T, 300,
B300, B300C, 300LW,
1900, 1900C (C-12J),
1900D.
65-90, 65-A90, B90, C90, 3A20 CAR 3, FAR 23
C90A.
Revo, Incorporated............... Colonial C-1, Colonial C- 1A13 CAR 3, 14 CFR 23
2, Lake LA-4, LA-4A, LA-
4P, Lake LA-4-200, Lake
250.
Sky International................ Husky A-1, A-1A, A-1B.... A22NM FAR 23
Socata Aerospatiale.............. TB 20, TB 10, TB 21, TB9, A51EU 14 CFR 23
TB 200.
TBM 700.................. A60EU 14 CFR 23
Twin Commander Aircraft Corp..... 500, 500-A, 500-B, 500-U, 6A1 CAR 23
500-S, 520, 560, 560-A,
560-E.
560-F, 680, 680E, 680F, 2A4 CAR 23
720, 680FL, 680FL(P),
680T, 680V, 680W, 681,
685, 690, 690A, 690B,
690C, 690D, 695, 695A,
695B.
700...................... A12SW FAR 23
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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) of Amendment 21-69.
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
Avidyne Corporation 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
[[Page 8554]]
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:
------------------------------------------------------------------------
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-GHz 6..................................... 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 one
modification to the airplane models listed under the heading ``Type
Certification Basis.'' Should Avidyne Corporation 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
of one modification to several models of airplanes. 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 some airplane
models, 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
0
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
0
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 airplane models listed under the
``Type Certification Basis'' heading modified by Avidyne Corporation,
to add an EFIS.
1. Protection of Electrical and Electronic Systems from High
Intensity Radiated Fields (HIRF). Each system
[[Page 8555]]
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 February 11, 2004.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-4177 Filed 2-24-04; 8:45 am]
BILLING CODE 4910-13-P