4 January 2003. Add notice of 3 January 2003. 3 January 2003 Source: http://www.access.gpo.gov/su_docs/aces/fr-cont.html ------------------------------------------------------------------------- [Federal Register: January 2, 2003 (Volume 68, Number 1)] [Rules and Regulations] [Page 1-3] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr02ja03-1] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ 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. ======================================================================== [[Page 1]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. CE188, Special Condition 23-131-SC] Special Conditions; Rockwell Collins, Incorporated on the Raytheon Model B300/B300C; Protection of Systems for 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 Rockwell Collins, Cedar Rapids, Iowa 52498 for a Supplemental Type Certificate for the Raytheon Model B300/B300C airplanes. 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 a ProLine 21 avionics system, which includes an electronic flight instrument system (EFIS) display 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 this airplane. DATES: The effective date of these special conditions is December 18, 2002. Comments must be received on or before February 3, 2003. ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk, Docket No. CE188, Room 506, 901 Locust, Kansas City, Missouri 64106. All comments must be marked: Docket No. CE188. 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: 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 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. CE188.'' The postcard will be date stamped and returned to the commenter. Background On November 7, 2001, Rockwell Collins, Incorporated, Cedar Rapids, Iowa 52498 made an application to the FAA for a new Supplemental Type Certificate for the Raytheon Aircraft Model B300/B300C airplanes. The airplane is currently approved under TC No. A24CE. The proposed modification incorporates the installation of the Rockwell Collins ProLine 21 Display System. The ProLine 21 system will replace the EFIS originally installed on the airplane. Like the original EFIS, the new system has the potential to be vulnerable to high-intensity radiated fields (HIRF) external to the airplane. Type Certification Basis Under the provisions of 14 CFR part 21, Sec. 21.101, Rockwell Collins must show that the Raytheon Model B300/B300C aircraft meets the following provisions, or the applicable regulations in effect on the date of application for the change to the Raytheon Model B300/B300C. The regulations incorporated by reference in the type certificate are commonly referred to as the ``original type certification basis.'' The regulations incorporated by reference in Type Certificate Data Sheet A24CE are as follows: Certification Basis FAR Part 23 effective February 1, 1965, as amended by Amendments 23-1 through 23-34; Federal Aviation Regulations 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 Sec. 23.207(c). Federal Aviation Regulations part 23, Sec. Sec. 23.201, 23.203, and 23.205 through Amendment 23-45 (S/N FN-1 and up only). Effective January 20, 1994, Federal Aviation Regulations Sec. 23.1457 as amended by Amendment 23-35. 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 Sec. 23.1419 when ice protection equipment is installed in accordance with the Equipment List. Equivalent Safety Findings: Sec. 23.781(b) for shape of the propeller control knob; Sec. 23.1305(g) [[Page 2]] 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. 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 14 CFR part 21 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 Rockwell Collins will incorporate certain novel and unusual design features into the Raytheon Model B300/B300C airplane for which the airworthiness standards do not contain adequate or appropriate safety standards for protection from the effects of HIRF. These features, including EFIS, are susceptible to the HIRF environment 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 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-500kHz.................................. 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 over the complete modulation period. 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 rms 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 B300/B300C airplanes. Should Rockwell Collins 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 [[Page 3]] 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 part 21, Sec. 21.16 and Sec. 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 Company Model B300/B300C airplanes modified by Rockwell Collins 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. Issued in Kansas City, Missouri on December 18, 2002. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 02-33126 Filed 12-31-02; 8:45 am] BILLING CODE 4910-13-P ----------------------------------------------------------------------- [Federal Register: January 2, 2003 (Volume 68, Number 1)] [Rules and Regulations] [Page 3-5] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr02ja03-2] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. CE193, Special Condition 23-133-SC] Special Conditions: S-TEC Corporation; 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. ----------------------------------------------------------------------- SUMMARY: These special conditions are issued to S-TEC Corporation, One S-TEC Way Municipal Airport, Mineral Wells, TX 76067, for a Supplemental Type Certificate for the models listed under the heading ``Type Certification Basis.'' These special conditions include 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 single or dual Meggitt Avionics Magic electronic flight instrument system (EFIS) manufactured by Meggitt Avionics, 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 December 18, 2002. Comments must be received on or before before February 3, 2003. ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk, Docket No. CE193, Room 506, 901 Locust, Kansas City, Missouri 64106. All comments must be marked: Docket No. CE193. 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: 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 design approval 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. CE193.'' The postcard will be date stamped and returned to the commenter. Background On September 16, 2002, S-TEC Corporation, One S-TEC Way, Mineral Wells Airport, Mineral Wells, Texas 76067, made an application to the FAA for a new Supplemental Type Certificate for the Raytheon (Beech) 65-90, 55-A90, 65-A90-1, 65-A90-4, B90, and C90 airplane models. They have also identified future STC projects that need the special conditions. All models are currently approved under the type [[Page 4]] 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, S-TEC 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 23-49; and Sec. 23.1322 of Amendment 23-43; exemptions, if any; and the special conditions adopted by this rulemaking action. ---------------------------------------------------------------------------------------------------------------- Aircraft model Type certificate number ---------------------------------------------------------------------------------------------------------------- Raytheon (Beech) 65-90, 65-A90, 65-A90-1, 65-A90-4, B90, 3A20, Rev. 60, 9/10/01 C90, and E90. Raytheon (Beech) King Air 200............................... A24CE, Rev. 82, 4/23/02 Twin Commander Aircraft Corporation 690C, 695, 695A, and 2A4, Rev. 46, 4/3/00 695B. Cessna 425 Conquest I....................................... A7CE, Rev. 45, 7/12/02 Piper PA-31T Cheyenne II.................................... A8EA, Rev. 21, 4/8/98 ---------------------------------------------------------------------------------------------------------------- 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 S-TEC 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 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 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 [[Page 5]] 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 by 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 S-TEC Corporation 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 part 21, Sec. Sec. 21.16 and 21.101; and 14 CFR part 11, Sec. Sec. 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 S-TEC Corporation 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. Issued in Kansas City, Missouri, on December 18, 2002. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 02-33131 Filed 12-31-02; 8:45 am] BILLING CODE 4910-13-P --------------------------------------------------------------------- [Federal Register: January 3, 2003 (Volume 68, Number 2)] [Rules and Regulations] [Page 255-257] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr03ja03-1] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ 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. ======================================================================== [[Page 255]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. NM242, Special Conditions No. 25-225-SC] Special Conditions: Raytheon Aircraft Company Model HS.125 Series 700A Airplanes; High Intensity Radiated Fields (HIRF) AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. ----------------------------------------------------------------------- SUMMARY: These special conditions are issued for Raytheon Aircraft Company Model HS.125 Series 700A airplanes modified by Elliott Aviation Technical Products Development, Inc. These modified airplanes will have a novel and unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. The modification incorporates the installation of an Electronic Flight Instrument System (EFIS) for display of critical flight parameters (altitude, airspeed, and attitude) to the crew. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for the protection of these systems from the effects of high-intensity-radiated fields (HIRF). These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that provided by the existing airworthiness standards. DATES: The effective date of these special conditions is December 23, 2002. Comments must be received on or before February 3, 2003. ADDRESSES: Comments on these special conditions may be mailed in duplicate to: Federal Aviation Administration, Transport Airplane Directorate, Attn: Rules Docket (ANM-113), Docket No. NM242, 1601 Lind Avenue SW., Renton, Washington, 98055-4056; or delivered in duplicate to the Transport Airplane Directorate at the above address. All comments must be marked: Docket No. NM242. FOR FURTHER INFORMATION CONTACT: Meghan Gordon, FAA, Standardization Branch, ANM-113, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington, 98055-4056; telephone (425) 227-2138; facsimile (425) 227-1149. SUPPLEMENTARY INFORMATION: Comments Invited The FAA has determined that notice and opportunity for prior public comment is impracticable because these procedures would significantly delay certification of the airplane and thus delivery of the affected aircraft. In addition, the substance of these special conditions has been subject to the public comment process in several prior instances with no substantive comments received. The FAA therefore finds that good cause exists for making these special conditions effective upon issuance; however, the FAA invites interested persons to participate in this rulemaking by submitting written comments, data, or views. The most helpful comments reference a specific portion of the special conditions, explain the reason for any recommended change, and include supporting data. We ask that you send us two copies of written comments. We will file in the docket all comments we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning these special conditions. The docket is available for public inspection before and after the comment closing date. If you wish to review the docket in person, go to the address in the ADDRESSES section of this preamble between 7:30 a.m. and 4 p.m., Monday through Friday, except Federal holidays. We will consider all comments we receive on or before the closing date for comments. We will consider comments filed late if it is possible to do so without incurring expense or delay. We may change these special conditions based on the comments we receive. If you want the FAA to acknowledge receipt of your comments on these special conditions, include with your comments a pre-addressed, stamped postcard on which the docket number appears. We will stamp the date on the postcard and mail it back to you. Background On July 25, 2002, Elliott Aviation Technical Products Development, Inc., Quad City Airport, Moline, Illinois 61266-0100, applied for a supplemental type certificate (STC) to modify Raytheon Aircraft Company Model HS.125 Series 700A airplanes approved under Type Certificate No. A3EU. The HS.125 Series 700A airplanes are executive type transports that have two aft mounted turbine engines, a maximum passenger load of 15 passengers, and a maximum operating speed of 280 to 320 KTS depending on the fuel loading configuration. The modification incorporates the installation of the Rockwell Collins FDS 2000 Electronic Flight Instrument System (EFIS). This system uses flat information display panels for display of critical flight parameters (heading and attitude) to the crew. These displays can be susceptible to disruption to both command and response signals as a result of electrical and magnetic interference caused by high-intensity radiated fields (HIRF) external to the airplane. This disruption of signals could result in the loss of all critical flight information displays and annunciations or present misleading information to the pilot. Type Certification Basis Under the provisions of 14 CFR 21.101, Elliott Aviation Technical Products Development, Inc., must show that the Raytheon Aircraft Company Model HS.125 Series 700A airplanes, as changed, continue to meet the applicable provisions of the regulations incorporated by reference in Type Certificate No. A3EU, or the applicable regulations in effect on the date of application for the change. The regulations incorporated by reference in the type certificate are commonly referred to as the ``original type certification basis.'' The certification basis for the modified Raytheon Aircraft Company Model HS.125 Series 700A airplanes include 14 CFR part 25 effective February 1, 1965, as amended [[Page 256]] by Amendments 25-2 and 25-20, as described in Type Certificate Data Sheet A3EU. If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 25, as amended) do not contain adequate or appropriate safety standards for the Raytheon Aircraft Company Model HS.125 Series 700A airplanes because of novel or unusual design features, special conditions are prescribed under the provisions of Sec. 21.16. In addition to the applicable airworthiness regulations and special conditions, the Raytheon Aircraft Company Model HS.125 Series 700A airplanes must comply with the fuel vent and exhaust emission requirement of 14 CFR part 34 and the noise certification requirement of part 36. Special conditions, as defined in Sec. 11.19, are issued in accordance with Sec. 11.38 and become part of the type certification basis in accordance with Sec. 21.101(b)(2), Amendment 21-69, effective September 16, 1991. Special conditions are initially applicable to the model for which they are issued. Should Elliott Aviation Technical Products Development, Inc., apply at a later date for a supplemental type certificate to modify any other model included Type Certificate No. A3EU 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(a)(1), Amendment 21-69, effective September 16, 1991. Novel or Unusual Design Features As noted earlier, the modified Raytheon Aircraft Company Model HS.125 Series 700A airplanes will incorporate the Rockwell Collins FDS 2000 Electronic Flight Instrument System (EFIS). Because these advanced systems use electronics to a far greater extent than the original flight and navigation systems, they may be more susceptible to electrical and magnetic interference caused by high-intensity radiated fields (HIRF) external to the airplane. The current airworthiness standards of part 25 do not contain adequate or appropriate safety standards for the protection of this equipment from the adverse effects of HIRF. Accordingly, this system is considered to be a novel or unusual design feature. Discussion There is no specific regulation that addresses protection requirements for electrical and electronic systems from HIRF. Increased power levels from ground-based radio transmitters and the growing use of sensitive electrical and electronic systems to command and control airplanes have made it necessary to provide adequate protection. To ensure that a level of safety is achieved equivalent to that intended by the regulations incorporated by reference, special conditions are needed for the Raytheon Aircraft Company Model HS.125 Series 700A airplanes modified by Elliott Aviation Technical Products Development, Inc. These special conditions will require that the new EFIS that performs critical functions be designed and installed to preclude component damage and interruption of function due to both the direct and indirect effects of HIRF. High-Intensity Radiated Fields (HIRF) With the trend toward increased power levels from ground-based transmitters, plus the advent of space and satellite communications, coupled with electronic command and control of the airplane, the immunity of critical digital avionic/electronic and electrical systems to HIRF must be established. It is not possible to precisely define the HIRF to which the airplane will be exposed in service. There is also uncertainty concerning the effectiveness of airframe shielding for HIRF. Furthermore, coupling of electromagnetic energy to cockpit-installed equipment through the cockpit window apertures is undefined. Based on surveys and analysis of existing HIRF emitters, an adequate level of protection exists when compliance with the HIRF protection special condition is shown with either paragraph 1 or 2 below: 1. A minimum threat of 100 volts rms (root-mean-square) per meter electric field strength from 10 KHz to 18 GHz. a. The threat must be applied to the system elements and their associated wiring harnesses without the benefit of airframe shielding. b. Demonstration of this level of protection is established through system tests and analysis. 2. A threat external to the airframe of the field strengths indicated in the table below for the frequency ranges indicated. Both peak and average field strength components from the table below are to be demonstrated. ------------------------------------------------------------------------ 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 of the root-mean- square (rms) over the complete modulation period. The threat levels identified above are the result of an FAA review of existing studies on the subject of HIRF, in light of the ongoing work of the Electromagnetic Effects Harmonization Working Group of the Aviation Rulemaking Advisory Committee. Applicability: As discussed above, these special conditions are applicable to Raytheon Aircraft Company Model HS.125 Series 700A airplanes modified by Elliott Aviation Technical Products Development, Inc. Should Elliott Aviation Technical Products Development, Inc., apply at a later date for a supplemental type certificate to modify any other model included on Type Certificate No. A3EU to incorporate the same novel or unusual design feature, these special conditions would apply to that model as well under the provisions of Sec. 21.101(a)(1), Amendment 21-69, effective September 16, 1991. Conclusion This action affects only certain novel or unusual design features on Raytheon Aircraft Company Model HS.125 Series 700A airplanes modified by Elliott Aviation Technical Products Development, Inc. It is not a rule of general applicability and affects only the applicant who applied to the FAA for approval of these features on this airplane. The substance of the special conditions for this airplane has been subjected to the notice and comment procedure in several prior instances and has been derived without substantive change from those previously issued. Because a delay would significantly affect the certification of the airplane, which is imminent, the FAA has determined that prior public notice and comment are unnecessary and impracticable, and good cause exists for adopting these special conditions upon issuance. The FAA is requesting comments to allow interested persons to submit views that may not have been [[Page 257]] submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the supplemental type certification basis for Raytheon Aircraft Company Model HS.125 Series 700A airplanes modified by Elliott Aviation Technical Products Development, Inc. 1. Protection from Unwanted Effects of High-Intensity Radiated Fields (HIRF). Each electrical and electronic system that performs critical functions must be designed and installed to ensure that the operation and operational capability of these systems to perform critical functions are not adversely affected when the airplane is exposed to high-intensity radiated fields. 2. For the purpose of these special conditions, the following definition applies: Critical Functions. Functions whose failure would contribute to or cause a failure condition that would prevent the continued safe flight and landing of the airplane. Issued in Renton, Washington, on December 23, 2002. Charles Huber, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-63 Filed 1-2-03; 8:45 am] BILLING CODE 4910-13-P