Special Conditions; Garmin International, Inc.; Raytheon Model C90A King Air; Protection of Electronic Flight Instrument System from the Effects of High Intensity Radiated Fields (HIRF), 58735-58738 [E6-16497]

Download as PDF 58735 Rules and Regulations Federal Register Vol. 71, No. 193 Thursday, October 5, 2006 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF AGRICULTURE Animal and Plant Health Inspection Service 7 CFR Parts 360 and 361 [Docket No. APHIS–2006–0019] Noxious Weeds; South African Ragwort and Madagascar Ragwort Animal and Plant Health Inspection Service, USDA. ACTION: Affirmation of interim rule as final rule. AGENCY: We are adopting as a final rule, without change, an interim rule that amended the noxious weed and imported seed regulations by adding South African ragwort (Senecio inaequidens DC.) and Madagascar ragwort (Senecio madagascariensis Poir.) to the list of terrestrial noxious weeds and to the list of seeds with no tolerances applicable to their introduction. That action was necessary to prevent the artificial spread of these noxious weeds into the United States. DATES: Effective on October 5, 2006, we are adopting as a final rule the interim rule published at 71 FR 35378–35381, June 20, 2006. FOR FURTHER INFORMATION CONTACT: Dr. Alan V. Tasker, Noxious Weeds Program Coordinator, Invasive Species and Pest Management, PPQ, APHIS, 4700 River Road Unit 134, Riverdale, MD 20737– 1237; (301) 734–5225. SUPPLEMENTARY INFORMATION: SUMMARY: ycherry on PROD1PC64 with RULES Background The Plant Protection Act (7 U.S.C. 7701 et seq.) authorizes the Secretary of Agriculture to prohibit or restrict the importation, entry, exportation, or movement in interstate commerce of any plant, plant product, biological control organism, noxious weed, article, or means of conveyance if the Secretary VerDate Aug<31>2005 15:35 Oct 04, 2006 Jkt 211001 determines that the prohibition or restriction is necessary to prevent the introduction of a plant pest or noxious weed into the United States or the dissemination of a plant pest or noxious weed within the United States. In an interim rule 1 effective June 14, 2006, and published in the Federal Register on June 20, 2006 (71 FR 35378– 35381, Docket No. APHIS–2006–0019), we amended the noxious weed and imported seed regulations by adding South African ragwort (Senecio inaequidens DC.) and Madagascar ragwort (Senecio madagascariensis Poir.) to the list in § 360.200(c) of terrestrial noxious weeds and to the list in § 361.6(a)(1) of seeds with no tolerances applicable to their introduction. That action was necessary to prevent the artificial spread of South African ragwort and Madagascar ragwort into the United States. Comments on the interim rule were required to be received on or before August 21, 2006. We did not receive any comments. Therefore, for the reasons given in the interim rule, we are adopting the interim rule as a final rule. This action also affirms the information contained in the interim rule concerning Executive Order 12866 and the Regulatory Flexibility Act, Executive Order 12988, and the Paperwork Reduction Act. Further, for this action, the Office of Management and Budget has waived its review under Executive Order 12866. List of Subjects 7 CFR Part 360 Imports, Plants (Agriculture), Quarantine, Reporting and recordkeeping requirements, Transportation, Weeds. 7 CFR Part 361 Agricultural commodities, Imports, Labeling, Quarantine, Reporting and recordkeeping requirements, Seeds, Vegetables, Weeds. 1 To view the interim rule, go to http:// www.regulations.gov, click on the ‘‘Advanced Search’’ tab, and select ‘‘Docket Search.’’ In the Docket ID field, enter APHIS–2006–0019, then click on ‘‘Submit.’’ Clicking on the Docket ID link in the search results page will produce a list of all documents in the docket. PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 PART 360—NOXIOUS WEED REGULATIONS PART 361—IMPORTATION OF SEED AND SCREENINGS UNDER THE FEDERAL SEED ACT Accordingly, we are adopting as a final rule, without change, the interim rule that amended 7 CFR parts 360 and 361 and that was published at 71 FR 35378–35381 on June 20, 2006. I Done in Washington, DC, this 29th day of September 2006. Kevin Shea, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. E6–16462 Filed 10–4–06; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. CE260, Special Condition 23– 200–SC] Special Conditions; Garmin International, Inc.; Raytheon Model C90A King Air; Protection of Electronic Flight Instrument System from the Effects of High Intensity Radiated Fields (HIRF) Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. AGENCY: SUMMARY: These special conditions are issued to Garmin International Inc., 1200 East 151st Street, Olathe, Kansas, 66062, for a Supplemental Type Certificate for the Raytheon Model C90A King Air airplane. 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 in the Garmin G1000 system, GFC 700 autopilot, Mid-Continent Instrument Attitude Indicator and Sandia Avionics cooling fans. 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 E:\FR\FM\05OCR1.SGM 05OCR1 58736 Federal Register / Vol. 71, No. 193 / Thursday, October 5, 2006 / Rules and Regulations ycherry on PROD1PC64 with RULES (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 September 27, 2006. Comments must be received on or before November 6, 2006. ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation Administration, Regional Counsel, ACE–7, Attention: Rules Docket Clerk, Docket No. CE260, Room 506, 901 Locust, Kansas City, Missouri 64106. All comments must be marked: Docket No. CE260. 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: Jim Brady, Aerospace Engineer, Standards Office (ACE–111), Small Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone (816) 329–4132. 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 notice VerDate Aug<31>2005 15:35 Oct 04, 2006 Jkt 211001 must include a self-addressed, stamped postcard on which the following statement is made: ‘‘Comments to Docket No. CE260.’’ The postcard will be date stamped and returned to the commenter. Background On June 2, 2006, Garmin International, Inc., 1200 East 151st Street, Olathe, Kansas, 66062, applied to the FAA for a new Supplemental Type Certificate for the Raytheon Model C90A King Air airplane. The C90A King Air is currently approved under TC No. 3A20, Revision 62 dated December 7, 2005. 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, § 21.101, Garmin International, Inc., must show that the Raytheon Model C90A King Air aircraft as changed continues to meet the following provisions, or the applicable regulations in effect on the date of application for the change to the Raytheon Model C90A King Air as specified on Type Certification Data Sheet TCDS No. 3A20, revision 62, dated December 7, 2005. 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 § 21.16. Special conditions, as appropriate, as defined in § 11.19, are issued in accordance with § 11.38 after public notice and become part of the type certification basis in accordance with § 21.101(b)(2). 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 § 21.101. Novel or Unusual Design Features Garmin International, 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 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 EFIS as part of the Garmin G1000 system. Additionally, the Garmin GFC 700 autopilot, Mid-Continent Instrument Attitude Indicator and Sandia Avionics Cooling Fans, which are susceptible to the HIRF environment, are included and 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 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 E:\FR\FM\05OCR1.SGM 05OCR1 58737 Federal Register / Vol. 71, No. 193 / Thursday, October 5, 2006 / Rules and Regulations 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 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 .............................................................................................................................................................. Average 50 50 50 100 50 50 100 100 700 700 2000 3000 3000 1000 3000 2000 600 50 50 50 100 50 50 100 100 50 100 200 200 200 200 300 200 200 ycherry on PROD1PC64 with RULES 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 VerDate Aug<31>2005 15:35 Oct 04, 2006 Jkt 211001 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 the Raytheon Model C90A King Air airplane. Should Garmin International, Inc. apply at a later date for a supplemental type certificate to modify any other model included 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 § 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, PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 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 Model C90A King Air airplane modified by Garmin International, Inc., which includes the Garmin G1000 system, GFC 700 autopilot, Mid-Continent Instrument Attitude Indicator and Sandia Avionics Cooling Fans. 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 E:\FR\FM\05OCR1.SGM 05OCR1 58738 Federal Register / Vol. 71, No. 193 / Thursday, October 5, 2006 / Rules and Regulations 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 September 27, 2006. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–16497 Filed 10–4–06; 8:45 am] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2006–25502; Airspace Docket No. 06–ACE–10] Modification of Class E Airspace; West Plains, MO Federal Aviation Administration (FAA), DOT. ACTION: Direct final rule; confirmation of effective date. ycherry on PROD1PC64 with RULES AGENCY: SUMMARY: This document confirms the effective date of the direct final rule which revises Class E Airspace at West Plains, MO. DATES: Effective Date: 0901 UTC, November 23, 2006. FOR FURTHER INFORMATION CONTACT: Grant Nichols, System Support, DOT Regional Headquarters Building, Federal Aviation Administration, 901 Locust, Kansas City, MO 64106; telephone: (816) 329–2522. SUPPLEMENTARY INFORMATION: The FAA published this direct final rule with a request for comments in the Federal Register on August 11, 2006 (71 FR 46076). The FAA uses the direct final rulemaking procedure for a noncontroversial rule where the FAA believes that there will be no adverse public comment. This direct final rule advised the public that no adverse comments were anticipated, and that unless a written adverse comments, or a written notice of intent to submit such an adverse comment, were received within the comment period, the regulation would become effective on November 23, 2006. No adverse comments were received, and thus this 16:06 Oct 04, 2006 Issued in Fort Worth, Texas, on September 22, 2006. Walter Tweedy, Acting Manager, System Support Group, ATO Central Service Area. [FR Doc. 06–8494 Filed 10–4–06; 8:45 am] BILLING CODE 4910–13–M DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2006–24448; Airspace Docket No. 06–AGL–02] Establishment of Class E Airspace; Mineral Point, WI BILLING CODE 4910–13–P VerDate Aug<31>2005 notice conforms that this direct final rule will become effective on that date. Jkt 211001 Federal Aviation Administration (FAA), DOT. ACTION: Direct final rule; request for comments. AGENCY: SUMMARY: This document establishes Class E airspace at Mineral Point, WI. A request has been made for a new area of Class E airspace extending upward from the surface, due to traffic volume. This action would establish a radius of class E airspace for Iowa County Airport. DATES: Effective 0901 UTC, January 18, 2007. The Director of the Federal Register approves this incorporation by reference action under 1 CFR Part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. Comments must be received on or before November 25, 2006. ADDRESSES: Send comments on the proposal to the Docket Management System, U.S. Department of Transportation, Room Plaza 401, 400 Seventh Street, SW., Washington, DC 20590–0001. You must identify the docket Number FAA–2006–24448/ Airspace Docket No. 06–AGL–02, at the beginning of your comments. You may also submit comments on the Internet at http://dms.dot.gov. You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Dockets Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647–5527) is on the plaza level of the Department of Transportation NASSIF Building at the above address. An informal docket may also be examined during normal business hours at FAA Terminal Operations, Central Service Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 FOR FURTHER INFORMATION CONTACT: Steve Davis, FAA Terminal Operations, Central Service Office, Airspace and Procedures Branch, AGL–530, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018, telephone (847) 294–7131. SUPPLEMENTARY INFORMATION: This amendment to 14 CFR part 71 establishes Class E airspace at Mineral Point, WI, to accommodate aircraft operating into and out of Iowa County Airport. The area will be depicted on appropriate aeronautical charts. Class E airspace areas extending upward from the surface of the earth are published in paragraph 6002, of FAA Order 7400.9P dated September 1, 2006, and effective September 15, 2006, airspace which is incorporated by reference in 14 CFR 71.1. The Class D airspace designation listed in this document will be published subsequently in the order. The Direct Final Rule Procedure The FAA anticipates that this regulation will not result in adverse or negative comment and therefore is issuing it as a direct final rule. A substantial number of previous opportunities provided to the public to comment on substantially identical actions have resulted in negligible adverse comments or objections. Unless a written adverse or negative comment, or a written notice of intent to submit an adverse or negative comment is received within the comment period, the regulation will become effective on the date specified above. After the close of the comment period, the FAA will publish a document in the Federal Register indicating that no adverse or negative comments were received and confirming the date on which the final rule will become effective. If the FAA does receive, within the comment period, an adverse or negative comment, or written notice of intent to submit such a comment, a document will be published in the Federal Register. This document may withdraw the direct final rule in whole or in part. After considering the adverse or negative comment, we may publish another direct final rule or publish a notice of proposed rulemaking with a new comment period. Comments Invited Although this action is in the form of a final rule and was not preceded by a notice of proposed rulemaking, comments are invited on this rule. Interested person are invited to comment on this rule by submitting such written data, views, or arguments, as they may desire. Communications should identify the Rules Docket E:\FR\FM\05OCR1.SGM 05OCR1

Agencies

[Federal Register Volume 71, Number 193 (Thursday, October 5, 2006)]
[Rules and Regulations]
[Pages 58735-58738]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-16497]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE260, Special Condition 23-200-SC]


Special Conditions; Garmin International, Inc.; Raytheon Model 
C90A King Air; Protection of Electronic Flight Instrument System from 
the Effects of High Intensity Radiated Fields (HIRF)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued to Garmin International 
Inc., 1200 East 151st Street, Olathe, Kansas, 66062, for a Supplemental 
Type Certificate for the Raytheon Model C90A King Air airplane. 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 in 
the Garmin G1000 system, GFC 700 autopilot, Mid-Continent Instrument 
Attitude Indicator and Sandia Avionics cooling fans. 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

[[Page 58736]]

(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 September 27, 
2006. Comments must be received on or before November 6, 2006.

ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation 
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk, 
Docket No. CE260, Room 506, 901 Locust, Kansas City, Missouri 64106. 
All comments must be marked: Docket No. CE260. 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: Jim Brady, Aerospace Engineer, 
Standards Office (ACE-111), Small Airplane Directorate, Aircraft 
Certification Service, Federal Aviation Administration, 901 Locust, 
Room 301, Kansas City, Missouri 64106; telephone (816) 329-4132.

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 notice must include a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. CE260.'' The postcard will be date stamped and 
returned to the commenter.

Background

    On June 2, 2006, Garmin International, Inc., 1200 East 151st 
Street, Olathe, Kansas, 66062, applied to the FAA for a new 
Supplemental Type Certificate for the Raytheon Model C90A King Air 
airplane. The C90A King Air is currently approved under TC No. 3A20, 
Revision 62 dated December 7, 2005. 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, Garmin 
International, Inc., must show that the Raytheon Model C90A King Air 
aircraft as changed continues to meet the following provisions, or the 
applicable regulations in effect on the date of application for the 
change to the Raytheon Model C90A King Air as specified on Type 
Certification Data Sheet TCDS No. 3A20, revision 62, dated December 7, 
2005.

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).
    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

    Garmin International, 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 as 
part of the Garmin G1000 system. Additionally, the Garmin GFC 700 
autopilot, Mid-Continent Instrument Attitude Indicator and Sandia 
Avionics Cooling Fans, which are susceptible to the HIRF environment, 
are included and 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 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

[[Page 58737]]

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 the 
Raytheon Model C90A King Air airplane. Should Garmin International, 
Inc. apply at a later date for a supplemental type certificate to 
modify any other model included 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 Model C90A King Air 
airplane modified by Garmin International, Inc., which includes the 
Garmin G1000 system, GFC 700 autopilot, Mid-Continent Instrument 
Attitude Indicator and Sandia Avionics Cooling Fans.
    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

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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 September 27, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-16497 Filed 10-4-06; 8:45 am]
BILLING CODE 4910-13-P