Source: https://www.federalregister.gov/documents/2005/11/18/05-22917/special-conditions-garmin-at-inc-efis-on-the-raytheon-a36-protection-of-systems-for-high-intensity
Timestamp: 2017-09-25 01:05:07
Document Index: 151079555

Matched Legal Cases: ['art 21', '§\u200921', '§\u200921', '§\u200911', '§\u200911', '§\u200921', '§\u200921', '§\u200921']

Federal Register :: Special Conditions; Garmin AT, Inc.; EFIS on the Raytheon A36; Protection of Systems for High Intensity Radiated Fields (HIRF)
Special Conditions; Garmin AT, Inc.; EFIS on the Raytheon A36; Protection of Systems for High Intensity Radiated Fields (HIRF)
A Rule by the Federal Aviation Administration on 11/18/2005
The effective date of these special conditions is November 7, 2005. Comments must be received on or before December 19, 2005.
70 FR 69891
69891-69893 (3 pages)
Docket No. CE232, Special Condition 23-172-SC
05-22917
https://www.federalregister.gov/d/05-22917 https://www.federalregister.gov/d/05-22917
Start Preamble Start Printed Page 69891
These special conditions are issued to Garmin AT, Inc., 2345 Turner Rd. SE, Salem, OR 97302, for a Supplemental Type Certificate for the Raytheon A36. The 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 an electronic flight instrument system (EFIS) display, Model G-1000, manufactured by Garmin International Inc., for which the applicable regulations do not contain adequate or appropriate airworthiness standards for the protection of these systems from the effects of high intensity radiated fields (HIRF). These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to the airworthiness standards applicable to these airplanes.
Comments may be mailed in duplicate to: Federal Aviation Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk, Docket No. CE232, Room 506, 901 Locust, Kansas City, Missouri 64106. All comments must be marked: Docket No. CE232. Comments may be inspected in the Rules Docket weekdays, except Federal holidays, between 7:30 a.m. and 4 p.m.
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.
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.
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. CE232.” The postcard will be date stamped and returned to the commenter.
On March 8, 2004, Garmin AT, Inc., 2345 Turner Rd. SE, Salem, OR 97302, made an application to the FAA for a new Supplemental Type Certificate for the Raytheon A36. The Raytheon A36 is currently approved under TC No. 3A15. 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.
Under the provisions of 14 CFR part 21, § 21.101, Garmin AT, Inc. must show that the Raytheon A36 meets its original certification basis, as listed on Type Data Sheet 3A15, the additional certification requirements added for the G1000 system, exemptions, if any; and the special conditions adopted by this rulemaking action. The additional certification requirements for the G1000 system include 23.1301, 23.1309, 23.1311, 23.1322, 23.1353 and other rules at the amendment appropriate for the date of application. Further details of the certification basis for the installation of the G1000 EFIS are available on request.
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 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.
Garmin AT, Inc. plans to incorporate certain novel and unusual design features into the Raytheon A36 for which the airworthiness standards do Start Printed Page 69892not 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, 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:
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 Raytheon A36. Should Garmin AT, Inc. 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 § 21.101.
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.
Accordingly, pursuant to the authority delegated to me by the Administrator, the following special Start Printed Page 69893conditions are issued as part of the type certification basis for the Raytheon A36 airplane modified by Garmin AT, Inc. to add the G1000 EFIS system.
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.
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 November 7, 2005.
[FR Doc. 05-22917 Filed 11-17-05; 8:45 am]