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 Department of Transportation Federal Aviation Administration 14 CFR Part 25
[Docket No. NM190, Special Conditions No. 25-178-SC]
 AGENCY: Federal Aviation Administration, DOT.
 ACTION: Final special conditions; request for comments.
 SUMMARY: These special conditions are issued for Bombardier Inc. Model CL-600-1A11 airplanes modified by Duncan Aviation, Inc. These modified airplanes will have novel and unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. The modification incorporates the installation of dual Attitude Heading Reference Systems (AHRS) as well as a new Electronic Flight Information System (EFIS) that displays critical flight parameters to the flightcrew. The applicable airworthiness standards do not contain adequate or appropriate safety standards for the protection of these systems from the effects of high-intensity radiated fields. The 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 April 25, 2001. Comments must be received on or before June 4, 2001.
 ADDRESSES: Comments on these special conditions may be mailed in duplicate to: Federal Aviation Administration, Transport Airplane Directorate, Attn: Rules Docket (ANM-114), Docket No. NM190, 1601 Lind Avenue SW., Renton, Washington, 98055-4056; or delivered in duplicate to the Transport Airplane Directorate at the above address. Comments must be marked: Docket No. NM190. 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: Mark Quam, FAA, Standardization Branch, ANM-113, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington, 98055-4056; telephone (425) 227-2145; facsimile (425) 227-1149.
                        ( print page 22427)


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 rules docket or special conditions 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. These 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 these special conditions must include a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket No. NM190.” The postcard will be date stamped and returned to the commenter. Background On November 28, 2000, Duncan Aviation Inc., P.O. Box 81887, Lincoln, NE 68501, applied for a supplemental type certificate (STC) to modify Bombardier Inc. Model CL-600-1A11 airplane listed on Type Certificate A21EA. The Model CL-600-1A11 is a twin engine transport airplane. It has an executive interior and is capable of carrying two flight crewmembers and up to nineteen passengers. This model is powered by two aft mounted AVCO Lycoming ALF-502L or ALF-502L-2 engines. The modification incorporates the installation of dual Rockwell Collins Attitude Heading Reference Systems (AHRS) as well as a new Electronic Flight Information System (EFIS) that displays critical flight parameters to the flightcrew. These systems can be susceptible to disruption to command and/or response signals as a result of electrical and magnetic interference. This disruption of signals could result in loss of all critical flight displays and annunciations or present misleading information to the pilot. Type Certification Basis Under the provisions of 14 CFR 21.101, Duncan Aviation must show that the Bombardier Inc. Model CL-600-1A11 airplanes, as changed, continue to meet the applicable provisions of the regulations incorporated by reference in Type Certificate No. A21EA, 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 Bombardier Inc. Model CL-600-1A11 airplane includes 14 CFR part 25, dated February 1, 1965, including Amendments 25-1 through 25-37, as listed in the Type Certificate Data Sheet (TCDS) A21EA. If the Administrator finds that the applicable airworthiness regulations (i.e., part 25, as amended) do not contain adequate or appropriate safety standards for the Bombardier Inc. Model CL-600-1A11 airplane because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16. In addition to the applicable airworthiness regulations and special conditions, the Model CL-600-1A11 airplane must comply with the part 25 fuel vent and exhaust emission requirements of 14 CFR part 34 and the part 25 noise certification requirements of 14 CFR part 36. Special conditions, as defined in § 11.19, are issued in accordance with § 11.38 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 Duncan Aviation, Inc. apply 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, these special conditions would also apply to the other model under the provisions of § 21.101(a)(1). Novel or Unusual Design Features The Bombardier Inc. Model CL-600-1A11 airplane will incorporate the following novel or unusual design features: Dual Attitude and Heading Reference Systems (AHRS) as well as a new Electronic Flight Information System (EFIS) that displays critical flight parameters to the flightcrew. These systems can be susceptible to disruption to command and/or response signals as a result of electrical and magnetic interference. This disruption of signals could result in loss of all critical flight displays and annunciations or present misleading information to the pilot. 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 avionic/electronic and electrical 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 Bombardier Inc. Model CL-600-1A11 as modified by Duncan Aviation Inc. These special conditions require that new avionic/electronic and electrical systems, such as the AHRS and EFIS that perform 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 avionics 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 paragraph 2, below: 1. A minimum threat of 100 volts rms 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.
                    ( print page 22428) 2. A threat external to the airframe of the following field strengths for the frequency ranges indicated. Both peak and average field strength components from the Table are to be demonstrated. Frequency
Field strength (volts per meter)Peak
Average10 kHz-100 kHz
50
50100 kHz-500 kHz
50
50500 kHz-2 MHz
50
502 MHz-30 MHz
100
10030 MHz-70 MHz
50
5070 MHz-100 MHz
50
50100 MHz-200 MHz
100
100200 MHz-400 MHz
100
100400 MHz-700 MHz
700
50700 MHz-1 GHz
700
1001 GHz-2 GHz
2000
2002 GHz-4 GHz
3000
2004 GHz-6 GHz
3000
2006 GHz-8 GHz
1000
2008 GHz-12 GHz
3000
30012 GHz-18 GHz
2000
20018 GHz-40 GHz
600
200The 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 Bombardier Inc. Model CL-600-1A11 airplane modified by Duncan Aviation, Inc. Should Duncan 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, these special conditions would apply to that model as well under the provisions of § 21.101(a)(1). Conclusion This action affects only certain novel or unusual design features on Bombardier Inc. Model CL-600-1A11 airplane modified by Duncan Aviation, 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 the airplane. The substance of the special conditions for this airplane 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 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 type certification basis for Bombardier Inc. Model CL-600-1A11 airplanes modified by Duncan. 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 April 25, 2001. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.


[FR Doc. 01-11254 Filed 5-3-01; 8:45 am] BILLING CODE 4910-13-U