[Federal Register Volume 67, Number 169 (Friday, August 30, 2002)]
[Rules and Regulations]
[Pages 55699-55703]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-22117]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE187, Special Condition 23-127-SC]


Special Conditions; Chelton Flight Systems, 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 Chelton Flight Systems, 
Inc., 1109 Main Street, Suite 560, Boise, ID 83702, 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 as recommended from 
completed Safer Sky Programs. The primary objective of streamlining the 
certification process is to improve the safety of the airplane fleet by 
fostering the incorporation of both 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 electronic flight instrument system (EFIS) 
display Model EFIS II manufactured by Chelton Flight Systems, 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 August 21, 
2002. Comments must be received on or before September 30, 2002.

ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation 
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk, 
Docket No. CE187, Room 506, 901 Locust, Kansas City, Missouri 64106. 
All comments must be marked: Docket No. CE187. 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: 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

[[Page 55700]]

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. 
CE187.'' The postcard will be date stamped and returned to the 
commenter.

Background

    On April 25, 2002, Chelton Flight Systems, Inc., 1109 Main Street, 
Suite 560, Boise, ID 83702, 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, Chelton Flight 
Systems, Inc., 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; Secs. 23.1309, 23.1311, and 23.1321 of Amendment 23-
49; and Sec. 23.1322 of Amendment 23-43; exemptions, if any; and the 
special conditions adopted by this rulemaking action.

------------------------------------------------------------------------
                  Models                       Type certificate number
------------------------------------------------------------------------
Aerostar Models 360/400...................  A11WE, Rev. 4, 10/22/92
Aerostar Models PA-60-600/-601/-601P/-602P/ A17WE, Rev. 22
 -700P.
American Champion Models 8GCBC/8KCAB......  A21CE, Rev. 11, 8/25/97
Aviat A-1/-1A/-1B.........................  A22NM, Rev. 12, 6/15/00
Beechcraft 60/A60/B60.....................  A12CE, Rev. 23, 4/15/96
Beechcraft Model 2000.....................  A38CE, Rev. 10, 8/23/01
Beechcraft Model 3000.....................  A00009WI, Rev. 8, 11/29/01
Beechcraft Model 76.......................  A29CE, Rev. 5, 4/15/96
Beechcraft Model F90......................  A31CE, Rev. 7, 4/15/96
Beechcraft Models 100/99/A/A100/A/C/A99/A/  A14CE, Rev. 35, 5/18/00
 100B9/C9.
Beechcraft Models 18D/A18A/D/S18D/SA18A/D.  A-684, Rev. 2, 4/15/96
Beechcraft Models 35/R/A35/B35/C35/D35/E35/ A-777, Rev. 57, 4/15/96
 F35/G35.
Beechcraft Models 35-33/A33/B33/C33/C33A/   3A15, Rev. 88, 1/15/00
 36/A36/A36TC/B36TC/E33/A/C/F33/A/C/G33/
 H35/J35/K35/M35/N35/P35/S35/V35/V35A/V35B.
Beechcraft Models 3N/3NM/3TM/C-45G/H/D18C/  A-765, Rev. 74, 4/15/96
 D18S/E18S/-9700/G18S/H18/JRB-6/RC-45J/TC-
 45G/TC-45H/TC-45J.
Beechcraft Models 50/B50/C50/D50/D50A/B/C/  5A4, Rev. 60, 4/15/96
 E/E-5990/E50/F50/G50/H50/J50.
Beechcraft Models 56TC/58/58A/95/95-55/95-  3A16, Rev. 80, 1/15/00
 A55/95-B55/95-B55A/95-B55B/95-C55/95-C55A/
 A56TC/B95/B95A/D55/D55A/D95A/E55/E55A/E95.
Beechcraft Models 58P/PA/TC/TCA...........  A23CE, Rev. 14, 4/15/96
Beechcraft Models 65/-80/-88/-90/-A80/-A80- 3A20, Rev. 60, 9/10/01
 8800/-A90/-A90-1/-A90-2/-A90-3/-A90-4/-
 B80/70/A65/-8200/B90/C90/A/E90/H90.
Britten-Norman Models BN-2/A/2A-2/2A-20/2A- A17EU, Rev. 15, 1/3/96
 21/2A-26/2A-27/2A-3/2A-6/2A-8/2A-9/2B-20/
 2B-21/2B-26/2B-27/2T/2T-4R.
Britten-Norman Models BN2A MK. 111/-2/-3..  A29EU, Rev. 3, 6/21/78
Cessna 206/H/P206/A/B/C/D/E/H/TP206A/B/C/D/ A4CE, Rev. 40, 6/19/02
 E/TU206A/B/C/D/E/F/G/U206/A/B/C/D/E/F/G.
Cessna 207/A/T207/A.......................  A16CE, Rev. 20, 10/15/94
Cessna Model 177RG........................  A20CE, Rev. 18, 10/15/94
Cessna Model 336..........................  A2CE, Rev. 6, 6/15/99
Cessna Model 441..........................  A28CE, Rev. 11, 8/15/99
Cessna Model T303.........................  A34CE, Rev. 5, 10/15/94
Cessna Models 172/A/B/C/D/E/F//H/I/K/L/M/N/ 3A12, Rev. 68, 10/11/01
 P/Q/R/S.
Cessna Models 170/A/B.....................  A-799, Rev. 51, 7/15/98
Cessna Models 172RG/175/A/B/C/P172D/R172E/  3A17, Rev. 44, 11/15/97
 F/G/H/J/K.
Cessna Models 177/A/B.....................  A13CE, Rev. 23, 10/15/94
Cessna Models 180A/B/C/D/E/F/G/H/J/K......  5A6, Rev. 64, 10/11/01
Cessna Models 182/A/B/C/D/E/F/G/H/J/K/L/M/  3A13, Rev. 59, 12/12/01
 N/P/Q/R/S/T/R182/T182/T/TR182.
Cessna Models 185/A/B/C/D/E/A185E/F.......  3A24, Rev. 36, 11/15/99
Cessna Models 208/A/B.....................  A37CE, Rev. 12, 6/15/99
Cessna Models 210/-5 (205)/-5A (205A)/A/B/  3A21, Rev. 45, 8/15/96
 C/D/E/F/G/H/J/K/L/M/N/R/P210N/R/T210F/G/H/
 J/K/L/M/N/R.
Cessna Models 310/A/B/C/D/E/F/G/H/I/J/J-1/  3A10, Rev. 61, 11/15/97
 K/L/N/P/Q/R/E310H.
Cessna Models 320/-1/A/B/C/D/E/F/335/340/A  3A25, Rev. 25, 8/15/94
Cessna Models 337/A/B/C/D/E/F/G/H/M337B/    A6CE, Rev. 38, 10/11/01
 P337H/T337B/C/D/E/F/G/H/H-SP.
Cessna Models 401/A/B/402/A/B/C/411/A/414/  A7CE, Rev. 44, 5/15/99
 A/421/A/B/C/425.
Cessna Models 404/406.....................  A25CE, Rev. 11, 6/15/95
Cessna Models 501/551.....................  A27CE, Rev. 15, 2/25/02
Cessna Models 525/A.......................  A1WI, Rev. 11, 7/9/01

[[Page 55701]]

 
Cirrus Models SR20/22.....................  A00009CH, Rev. 3, 9/28/01
Commander Model 700.......................  A12SW, Rev. 10, 1/1/90
Commander Models 112/B/TC/TCA/114/A/B/TC..  A12SO, Rev. 21, 8/4/95
Commander Models 500/-A/-B/-S/-U/520/560/-  6A1, Rev. 45, 1/1/90
 A/-E.
Commander Models 560-F/680/E/F/FL/FL(P)/    2A4, Rev. 46, 04/03/2000
 F(P)/T/V/W681/685/690/A/B/C/D/695/A/B/720.
de Havilland Model DHC-3..................  A-815, Rev. 4, 6/26/98
de Havilland Models DHC-2 Mk.I/II/III.....  A-806, Rev. 21, 1/21/94
de Havilland Models DHC-61/-100/-200/-300.  A9EA, Rev. 11, 6/20/00
Diamond Model DA-40.......................  A47CE, Rev. 2, 4/8/02
Extra Models EA-200/300/L/S...............  A67EU, Rev. 5, 06/03/99
Extra Model EA-400........................  A43CE, Rev. 5, 3/5/02
Grob Models G115EG/G115/A/B/C/C2/D/D2.....  A57EU, Rev. 10, 2/6/01
Helio Courier Models 15A/20...............  3A3, Rev. 7, 3/1/91
Helio Courier Models H-250/295/391/391B/    1A8, Rev. 33, 9/18/97
 395/395A/700/800/T-295.
Lancair Model LC40-550FG..................  A00003SE, Rev. 8, 2/26/02
Learjet Model 23..........................  A5CE, Rev. 10, 7/15/90
Maule Models M-4/-180C/S/T/-210/C/S/T/-220/ 3A23, Rev. 28, 4/6/00
 C/S/T/M-4C/S/T/M-5-180C/-200/-210C/-210TC/
 -220C/-235C/M-6-180/6-235/M-7-235/A/B/C/-
 260 MT-7-235/-260/-160/-160C/-180/A/AC/B/
 C/-235/-420 MXT-7-160/-180/A/-420.
Mitsubishi Models MU-2B/-10/-15/-20/-25/-   A2PC, Rev. 16, 6/30/75
 26/-30/-35/-36.
Mitsubishi Models MU-2B-25/-26/A/-35/-36/A/ A10SW, Rev. 13, 4/2/98
 -40/-60.
Mooney Models M20/A/B/C/D/E/F/G/J/K/L/M/R/  2A3, Rev. 46, 8/10/99
 S.
ParisJet Models M.S. 760 (Paris I)/M.S.     7A3, Rev. 3, 3/17/98
 760B (Paris II)/M.S. 760.A (Paris IA).
Piaggio Model P-180.......................  A59EU, Rev. 9, 10/25/00
Pilatus Model PC-7........................  A50EU, Rev. 2, 7/1/96
Pilatus Models PC-12/-12/45...............  A78EU, Rev. 9, 3/30/01
Pilatus Models PC-6/-H1/-H2/PC-6/350/-H1/-  7A15, Rev. 11, 8/9/99
 H2 PC-6/A/-H1/-H2/B-H2/B1-H2/B2-H2/B2-H4/
 C-H2/C1-H2.
Piper Models PA-12/S......................  A-780, Rev. 13, 3/30/01
Piper Models PA-18/105/125/135A/A-135/A-    1A2, Rev. 37, 9/4/96
 150/AS-125/AS-135/AS-150/S/S-105/S-125/S-
 135/S-150.
Piper Models PA-24/250/260/400............  1A15, Rev. 33, 10/1/97
Piper Models PA-28-140/150/151/160/161/180/ 2A13, Rev. 45, 12/12/01
 181/201T/235/236/R-180 RT-201T/S-160/S-
 180.
Piper Models PA-30/-39/-40................  A1EA, Rev. 15, 10/1/97
Piper Models PA-31/-300/-325/-350.........  A20SO, Rev. 9, 3/19/01
Piper Models PA-31P/-350/PA-31T/1/2/3.....  A8EA, Rev. 21, 4/8/98
Piper Models PA-32-260/-300/-301/T/PA-32R-  A3SO, Rev. 26, 7/23/97
 300/-301/-301T/PA-32RT-300/-300T/PA-32S-
 300.
Piper Models PA-34-200/-200T/-220T........  A7SO, Rev. 14, 6/1/01
Piper Models PA-42/-42-1000/-42-720.......  A23SO, Rev. 14, 11/16/01
Piper Models PA-44-180/T..................  A19SO, Rev. 8, 11/14/01
Piper Models PA-46-310P/-350P/-500TP......  A25SO, Rev. 10, 1/2/02
Revo Models Colonial C-1/-2, Lake LA-4/A/P/ 1A13, Rev. 25, 11/8/99
 -200/250.
Shorts Models SC-7 Series 2/SC-7 Series 3.  A15EU, Rev. 9, 8/1/90
Slingsby Models T67M260/-T3A..............  A73EU, Rev. 4, 7/27/00
Socata Model TBM-700......................  A60EU, Rev. 8, 11/6/01
Socata Models TB 10/20/200/21/9...........  A51EU, Rev. 14, 4/6/01
------------------------------------------------------------------------

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

    Chelton Flight Systems, 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.

[[Page 55702]]

    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-6 GHz.......................................       3000        200
6 GHz-8 GHz.......................................       1000        200
8 GHz-12 GHz......................................       3000        300
12 GHz-18 GHz.....................................       2000        200
18 GHz-40 GHz.....................................        600       200
------------------------------------------------------------------------
The field strengths are expressed in terms of peak root-mean-square
  (rms) values.

or,

    (2) The applicant may demonstrate by a system test and analysis 
that the electrical and electronic systems that perform critical 
functions can withstand a minimum threat of 100 volts per meter, 
electrical field strength, from 10 kHz to 18 GHz. When using this test 
to show compliance with the HIRF requirements, no credit is given for 
signal attenuation due to installation.
    A preliminary hazard analysis must be performed by the applicant, 
for approval by the FAA, to identify either electrical or electronic 
systems that perform critical functions. The term ``critical'' means 
those functions whose failure would contribute to, or cause, a failure 
condition that would prevent the continued safe flight and landing of 
the airplane. The systems identified by the hazard analysis that 
perform critical functions are candidates for the application of HIRF 
requirements. A system may perform both critical and non-critical 
functions. Primary electronic flight display systems, and their 
associated components, perform critical functions such as attitude, 
altitude, and airspeed indication. The HIRF requirements apply only to 
critical functions.
    Compliance with HIRF requirements may be demonstrated by tests, 
analysis, models, similarity with existing systems, or any combination 
of these. Service experience alone is not acceptable since normal 
flight operations may not include an exposure to the HIRF environment. 
Reliance on a system with similar design features for redundancy as a 
means of protection against the effects of external HIRF is generally 
insufficient since all elements of a redundant system are likely to be 
exposed to the fields concurrently.

Applicability

    As discussed above, these special conditions are applicable to one 
modification to the airplane models listed under the heading ``Type 
Certification Basis.'' Should Chelton Flight Systems, Inc., apply to 
extend this modification to include additional airplane models, the 
special conditions would extend to these models 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

    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 airplane models listed under the 
``Type Certification Basis'' heading modified by Chelton Flight 
Systems, 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

[[Page 55703]]

cause, a failure condition that would prevent the continued safe flight 
and landing of the airplane.

    Issued in Kansas City, Missouri on August 21, 2002.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-22117 Filed 8-29-02; 8:45 am]
BILLING CODE 4910-13-U