Federal Aviation Administration (FAA), DOT.
Final special conditions; request for comments.
These special conditions are issued to The Lancair Company, 22550 Nelson Road, Bend, Oregon 97701, for a Type Design Change for the Lancair LC41-550FG and LC42-550FG airplanes. These airplanes 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 Model 700-00006-XXX-( ) manufactured by Avidyne Corporation 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.
The effective date of these special conditions is April 13, 2005. Comments must be received on or Start Printed Page 19255before May 13, 2005 for domestic, August 11, 2005 for foreign.
Comments may be mailed in duplicate to: Federal Aviation Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk, Docket No. CE220, Room 506, 901 Locust, Kansas City, Missouri 64106. All comments must be marked: Docket No. CE220. Comments may be inspected in the Rules Docket weekdays, except Federal holidays, between 7:30 a.m. and 4 p.m.Start Further Info
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.End Further Info End Preamble Start Supplemental Information
The FAA has determined that notice and opportunity for prior public comment hereon are impracticable because these procedures would significantly delay issuance of 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.
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. CE220.” The postcard will be date stamped and returned to the commenter.
In 2001 and 2002, The Lancair Company, 22550 Nelson Road, Bend, Oregon 97701, made applications to the FAA for a Type Design Change for the Lancair LC41-550FG and LC42-550FG airplanes. The modification incorporated an existing Supplemental Type Certificate (STC) into the Type Design as optional equipment on the LC41-550FG and LC42-550FG. These models are currently approved under Type Certificate Data Sheet (TCDS) No. A00003SE. 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, The Lancair Company must show that the LC41-550FG and LC42-550FG aircraft meet the following provisions, or the applicable regulations in effect on the date of application for the change to the two models.
For the LC41-550FG: Part 23 of the Federal Aviation Regulations (FAR) effective February 1, 1965, as amended by 23-1 through 23-46, except for FAR 23.1305 and FAR 23.1359. FAR 23.1305 as amended through 23-52 and FAR 23.1359 as amended through 23-49. FAR 36 as amended on the date of certification. Application for type certificate dated October 24, 2002. Equivalent Level of Safety (ELOS) Findings for Emergency exit requirements of FAR 23.807 in accordance with ELOS No. ACE-99-02, as detailed in FAA memo dated February 2, 1999 (FAA memo reference no. 99-190S-64), and the terms of these Special Conditions.
For the LC42-550FG: Part 23 of the Federal Aviation Regulations (FAR) effective February 1, 1965, as amended by 23-1 through 23-46, except for FAR 23.1305 and FAR 23.1359. FAR 23.1305 as amended through 23-52 and FAR 23.1359 as amended through 23-49. FAR 36 as amended on the date of certification. Applicable Equivalent Level of Safety (ELOS) Findings: Stall and spin requirements of FAR's 23.201, 23.203, and 23.221 in accordance with ELOS No. ACE-98-1, as detailed in the FAA memo dated September 3, 1998 (FAA memo reference no. 98-190S-581) and ELOS No. ACE-98-2 as detailed in the FAA memo dated October 7, 1998 (FAA memo reference no. 98-190S-608). Emergency exit requirements of FAR 23.807 in accordance with ELOS No. ACE-99-02 as detailed in FAA memo dated February 2, 1999 (FAA memo reference no. 99-190S-64), and the terms of these Special Conditions.
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.
Special conditions are initially applicable to the model for which they are issued. Should the applicant apply to modify any other model already included on the same Type Data Sheet 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
The Lancair Company plans to incorporate certain novel and unusual design features into an airplane for which the airworthiness standards do not contain adequate or appropriate safety standards for protection from the effects of HIRF. These features include EFIS, which are susceptible to the HIRF environment, that were not envisaged by the existing regulations for this type of airplane.
Protection of Systems From High Intensity Radiated Fields (HIRF)
Recent advances in technology have given rise to the application in aircraft designs of advanced electrical and electronic systems that perform functions required for continued safe flight and landing. Due to the use of sensitive solid state advanced components in analog and digital electronics circuits, these advanced systems are readily responsive to the transient effects of induced electrical current and voltage caused by the HIRF. The HIRF can degrade electronic systems performance by damaging components or upsetting system functions.
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, Start Printed Page 19256coupling 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:
|Frequency||Field strength (volts per meter)|
|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.|
(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.
As discussed above, these special conditions are applicable to the Lancair Company Model LC41-550FG and LC42-550FG airplanes. Should the Lancair Company apply at a later date for a type design change 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 § 21.101.
This action affects only certain novel or unusual design features being proposed for the model(s) discussed in this special condition. 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.Start List of Subjects
List of Subjects in 14 CFR Part 23End List of Subjects Start Part
PART 23—AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES
CitationEnd Part Start Amendment Part
The authority citation for these special conditions is as follows:End Amendment Part
The Special ConditionsStart Amendment Part
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 Lancair LC41-550FG and LC42-550FG airplanes modified to add an EFIS as optional equipment by the Lancair Company.End Amendment Part
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. Start Printed Page 19257
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.Start Signature
Issued in Kansas City, Missouri on April 1, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 05-7427 Filed 4-12-05; 8:45 am]
BILLING CODE 4910-13-P