Special Condition; Avidyne Corporation, Inc.; Various Airplane Models; Protection of Systems for High Intensity Radiated Fields (HIRF), 41104-41108 [E6-11562]

Download as PDF 41104 Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations 10. Operating Limitations and Information—Powerplant Limitations— Fuel Grade or Designation (Compliance With § 23.1521 Requirements) All engine parameters that have limits specified by the engine manufacturer for takeoff or continuous operation must be investigated to ensure they remain within those limits throughout the expected flight and ground envelopes (e.g., maximum and minimum fuel temperatures, ambient temperatures, as applicable, etc.). This is in addition to the existing requirements specified by 14 CFR 23.1521(b) and (c). If any of those limits can be exceeded, there must be continuous indication to the flight crew of the status of that parameter with appropriate limitation markings. Instead of compliance with § 23.1521(d), the applicant must comply with the following: The minimum fuel designation (for diesel engines) must be established so that it is not less than that required for the operation of the engines within the limitations in paragraphs (b) and (c) of § 23.1521. 11. Markings and Placards— Miscellaneous Markings and Placards— Fuel, Oil, and Coolant Filler Openings (Compliance With § 23.1557(c)(1) Requirements) Instead of compliance with § 23.1557(c)(1), the applicant must comply with the following: Fuel filler openings must be marked at or near the filler cover with— For diesel engine-powered airplanes— (a) The words ‘‘Jet Fuel’’; and (b) The permissible fuel designations, or references to the Airplane Flight Manual (AFM) for permissible fuel designations. (c) A warning placard or note that states the following or similar: ‘‘Warning—this airplane equipped with an aircraft diesel engine, service with approved fuels only.’’ The colors of this warning placard should be black and white. wwhite on PROD1PC76 with RULES 12. Powerplant—Fuel System—FuelFreezing If the fuel in the tanks cannot be shown to flow suitably under all possible temperature conditions, then fuel temperature limitations are required. These will be considered as part of the essential operating parameters for the aircraft and must be limitations. A minimum takeoff temperature limitation will be determined by testing to establish the minimum cold-soaked temperature at which the airplane can VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 operate. The minimum operating temperature will be determined by testing to establish the minimum operating temperature acceptable after takeoff from the minimum takeoff temperature. If low temperature limits are not established by testing, then a minimum takeoff and operating fuel temperature limit of 5 °F above the gelling temperature of Jet A will be imposed along with a display in the cockpit of the fuel temperature. Fuel temperature sensors will be located in the coldest part of the tank if applicable. 13. Powerplant Installation—Vibration Levels Vibration levels throughout the engine operating range must be evaluated and: (1) Vibration levels imposed on the airframe must be less than or equivalent to those of the gasoline engine; or (2) Any vibration level that is higher than that imposed on the airframe by the replaced gasoline engine must be considered in the modification and the effects on the technical areas covered by the following paragraphs must be investigated: 14 CFR 23.251; 23.613; 23.627; 23.629 (or CAR 3.159, as applicable to various models); 23.572; 23.573; 23.574 and 23.901. Vibration levels imposed on the airframe can be mitigated to an acceptable level by utilization of isolators, dampers, clutches, and similar provisions, so that unacceptable vibration levels are not imposed on the previously certificated structure. 14. Powerplant Installation—One Cylinder Inoperative It must be shown by test or analysis, or by a combination of methods, that the airframe can withstand the shaking or vibratory forces imposed by the engine if a cylinder becomes inoperative. Diesel engines of conventional design typically have extremely high levels of vibration when a cylinder becomes inoperative. No unsafe condition will exist in the case of an inoperative cylinder before the engine can be shut down. The resistance of the airframe structure, propeller, and engine mount to shaking moment and vibration damage must be investigated. It must be shown by test or analysis, or by a combination of methods, that shaking and vibration damage from the engine with an inoperative cylinder will not cause a catastrophic airframe, propeller, or engine mount failure. 15. Powerplant Installation—High Energy Engine Fragments It may be possible for diesel engine cylinders (or portions thereof) to fail PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 and physically separate from the engine at high velocity (due to the high internal pressures). This failure mode will be considered possible in engine designs with removable cylinders or other nonintegral block designs. The following is required: (1) It must be shown by the design of the engine that engine cylinders, other engine components or portions thereof (fragments) cannot be shed or blown off of the engine in the event of a catastrophic engine failure; or (2) It must be shown that all possible liberated engine parts or components do not have adequate energy to penetrate engine cowlings; or (3) Assuming infinite fragment energy, and analyzing the trajectory of the probable fragments and components, any hazard due to liberated engine parts or components will be minimized and the possibility of crew injury eliminated. Minimization must be considered during initial design and not presented as an analysis after design completion. Issued in Kansas City, Missouri, on July 11, 2006. Steve W. Thompson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–11474 Filed 7–19–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. CE244, Special Condition 23– 184A–SC] Special Condition; Avidyne Corporation, Inc.; Various Airplane Models; Protection of Systems for High Intensity Radiated Fields (HIRF) Federal Aviation Administration (FAA), DOT. ACTION: Amended final special conditions; request for comments. AGENCY: SUMMARY: These amended special conditions are issued to Avidyne Corporation, 55 Old Bedford Road, Lincoln, MA 01773. This is an amendment to special condition 23– 184–SC, which was published on May 23, 2006 (71 FR 29574), for installation of an EFIS manufactured by Avidyne on various models. The original issue left off the Cirrus Design Corporation SR22, which was the first model to be certified under the STC. The airplanes listed under this multimodel approval will have novel and unusual design features when compared E:\FR\FM\20JYR1.SGM 20JYR1 Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations to the state of technology envisaged in the applicable airworthiness standards. These novel and unusual design features include the installation of the Entegra II Avionics System, consisting of: (2) Model 700–0003–( ) Integrated Flight Displays (IFD), (2) Model 700– 00011–( ) Magnetometer/OAT sensors, and (1) Model 700–00085–000 Keyboard/Controller. These components are all manufactured by Avidyne Corporation, Inc. 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 May 10, 2006. Comments must be received on or before August 21, 2006. ADDRESSES: Comments on these special conditions may be mailed in duplicate to: Federal Aviation Administration, Regional Counsel, ACE–7, Attention: Rules Docket Clerk, Docket No. CE244, Room 506, 901 Locust, Kansas City, Missouri 64106. All comments must be marked: Docket No. CE244. 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: Wes Ryan, Aerospace Engineer, Standards Office (ACE–110), Small Airplane Directorate, Aircraft Certification Service, Federal Aviation 41105 Administration, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone (816) 329–4123. be date stamped and returned to the commenter. The FAA has determined that notice and opportunity for prior public comment hereon are impracticable because 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. In early 2006, the Avidyne Corporation, 55 Old Bedford Road, Lincoln, MA 01773, made an application to the FAA for a new Supplemental Type Certificate for airplane models listed under the type certification basis. The models are currently approved under the type certification basis listed in the paragraph headed ‘‘Type Certification Basis.’’ The proposed modification incorporates a novel or unusual design feature, such as a digital avionics system, that may be vulnerable to HIRF external to the airplane. Background SUPPLEMENTARY INFORMATION: 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. CE244.’’ The postcard will Type Certification Basis Under the provisions of 14 CFR part 21, § 21.101, Avidyne 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 §§ 23.1301, 23.1309, 23.1311, and 23.1321, 23.1322 of Amendment 23–49; exemptions, if any; and the terms of this special condition adopted by this rulemaking action. FINAL SPECIAL CONDITIONS [Approved model list—Part 23 Class I & II (AC 23.1309–1C] Aircraft make Aircraft model(s) Type certificate No. Aerostar Aircraft Corporation PA–60–600 (Aerostar 600), PA–60–601 (Aerostar 601), PA–60–601P (Aerostar 601P), PA–60–602P (Aerostar 602P). 172R, 172S ........................................................................ 182S, 182T, T182T ............................................................ 206H, T206H ...................................................................... T303 ................................................................................... 310, 310A (USAF U–3A), 310B, 310C, 310D, 310E (USAF U–3B), 310F, 310G, 310H, 310I, 310J, 310J–1, 310K, 310L, 310N, 310P, E310H, E310J, T310P, 310Q, T310Q, 310R, T310R. 320, 320–1, 320A, 320B, 320C, 320D, 320E, 320F 340, 340A, 335, 340, 340A. 336 ..................................................................................... 337, 337A (USAF O2B), 337B, 337C, 337D, 337E, 337F, 337G, 337H, M337B (USAF O2A), P337H, T337B, T337C, T337D, T337E, T337F, T337G, T337H, T337H–SP. SR20, SR22 ....................................................................... LC40–550FG, LC42–550FG .............................................. A17WE ...................... 14 CFR Part 23. 3A12 .......................... 3A1314 CFR Part 23. A4CE ......................... A34CE ....................... 3A10 .......................... 14 CFR Part 23. 14 CFR Part 23. 14 CFR Part 23. CAR 3. 3A25 .......................... CAR 3. A2CE ......................... A6CE ......................... CAR 3. CAR 3, 14 CFR Part 23. A00009CH ................. A00003SE ................. 14 CFR Part 23. 14 CFR Part 23. wwhite on PROD1PC76 with RULES Cessna Aircraft Company ..... Cirrus Design Corporation .... Columbia Aircraft Manufacturing. VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\20JYR1.SGM 20JYR1 Certification basis (see note 1) 41106 Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations FINAL SPECIAL CONDITIONS—Continued [Approved model list—Part 23 Class I & II (AC 23.1309–1C] Aircraft make Aircraft model(s) Type certificate No. Commander Aircraft .............. de Havilland Inc .................... Diamond Aircraft Industries .. 112, 114, 112TC, 112B, 112TCA, 114A, 114B, 114TC .... DHC–2 Mk. I, DHC–2 Mk. II, DHC–2 Mk. III ..................... DA 20–A1, DA20–C1 ......................................................... A40 ..................................................................................... A12SO ....................... A–806 ........................ TA4CH ....................... A47CE ....................... A42 ..................................................................................... A57CE ....................... Bee Dee M–4, M–5–180C, MXT–7–160, M–4, M–5–200, MX–7–180A, M–4C, M–5–210C, MXT–7–180, M–4S, M–5–210TC, MX–7–180B, M–4T, M–5–220C, MXT–7– 420, M–4–180C, M–5–235C, M–7–235B, M–4–180S, M–6–180, M–7–235A, M–4–180T, M–6–235, M–7– 235C M–4–210 M–7–235 MX–7–180C, M–4–210C, MX–7–235, M–7–260, M–4–210S MX–7–180 MT–7– 260, M–4–210T, MX–7–420, M–7–260C,M–4–220, MXT–7–180, M–7–420AC, M–4–220C, MT–7–235, MX–7–160C, M–4–220S, M–8–235, MX–7–180AC, M– 4–220T, MX–7–160. M20, M20A, M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20M, M20R, M20S. M22 .................................................................................... P 68, P 68B, P 68C, P 68C–TC, P 68 ‘‘OBSERVER’’, AP68 TP series 300, P68TC ‘‘OBSERVER’’, AP68TP 600, P68 ‘‘OBSERVER 2’’. PA–28–160, PA–28–150, PA–28–180, PA–28S–160, PA–28S–180, PA–28–235, PA–28–140 2 PCLM, PA– 28–140 4 PCLM, PA–28R–180, PA–28R–200, PA– 28R–200, PA–28–180, PA–28–235, PA–28–151, PA– 28–181, PA–28–181, PA–28–161, PA–28–161, PA– 28–161, PA–28R–201, PA–28R–201T, PA–28–236, PA–28RT–201, PA–28RT–201, PA–28RT–201T, PA– 28–201T. A–32–260, PA–32–300, PA–32S–300, PA–32R–300, PA–32RT–300, PA–32RT–300T, PA–32R–301, PA– 32R–301, PA–32R–301T, PA–32–301, PA–32–301T, PA–32R–301T. PA–30, PA–39, PA–40 ...................................................... PA–34–200, PA–34–200T, PA–34–220T, PA–34–220T, PA–34–220T. PA–44–180, PA–44–180, PA–44–180T ............................ PA–46–310P, PA–46–350P, PA–46–500TP ..................... A36, B36TC, G36 .............................................................. 58 and 58A ........................................................................ 58P and 58PA, 58TC and 58TCA ..................................... Lake LA–4, LA–4A, LA–4P, Lake LA–4–200, Lake 250 ... TB 20, TB 10, TB 21, TB9, TB 200 ................................... 3A23 .......................... CAR 3. CAR 3. 14 CFR Part 23. 14 CFR Part 21, 14 CFR Part 23. 14 CFR Part 21, 14 CFR Part 23. CAR 3. 2A3 ............................ CAR 3. A6SW ........................ A31EU ....................... CAR 3. 14 CFR Part 23. A3SO ......................... CAR 3. A1EA ......................... A7SO ......................... CAR 3. CAR 3. A19SO ....................... A25SO ....................... 3A15 .......................... 3A16 .......................... A23CE ....................... 1A13 .......................... A51EU ....................... 14 CFR Part 23. 14 CFR Part 23. CAR 3. CAR 3. 14 CFR Part 23. CAR 3, 14 CFR Part 23. 14 CFR Part 23. 6A1 ............................ CAR 3. Maule Aerospace Technology, Inc. Mooney Aircraft Corp ............ Partenavia Costruzioni Aeronauticas S.p.A. The New Piper Aircraft, Inc .. Raytheon Aircraft Company .. REVO, Incorporated .............. SOCATA—Groupe AEROSPATIALE. Twin Commander .................. 500, 520, 560, 560–A ........................................................ Certification basis (see note 1) FINAL SPECIAL CONDITIONS [Approved model list—Part 23 class III] Aircraft model(s) Type certificate No. Aerostar Aircraft Corporation Cessna Aircraft Company ..... wwhite on PROD1PC76 with RULES Aircraft make PA–60–700P (Aerostar 700P) ........................................... 208, 208A, 208B ................................................................ 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425. 404, 406 ............................................................................. 441 ..................................................................................... (Twin Otter) DHC–6–1, DHC–6–100, DHC–6–200, DHC– 6–300. SA26–T, SA26–AT, SA226–T, SA226–AT, SA226–T(B), SA227–AT, SA227–TT. MU–2B, MU–2B–10, MU–2B–20, MU–2B–15, MU–2B– 30, MU–2B–35, MU–2B–25, MU–2B–36, MU–2B–26. A17WE ...................... A37CE ....................... A7CE ......................... 14 CFR Part 23. 14 CFR Part 23. CAR 3. A25CE ....................... A28CE ....................... A9EA ......................... 14 CFR Part 23. 14 CFR Part 23. CAR 3. A5SW ........................ CAR 3. A2PC ......................... CAR 3. de Havilland Inc .................... Fairchild ................................ Mitsubishi Heavy Industries, Ltd. VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\20JYR1.SGM 20JYR1 Certification basis (see note 1) Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations 41107 FINAL SPECIAL CONDITIONS—Continued [Approved model list—Part 23 class III] Aircraft model(s) Type certificate No. MU–2B–25, MU–2B–35, MU–2B–26, MU–2B–36, MU– 2B–26A, MU–2B–36A, MU–2B–40, MU–2B–60. ‘‘SPARTACUS’’, AP68TP 600 ‘‘VIATOR’’, VA300 ............ A10SW ...................... CAR 3. A31EU ....................... 14 CFR Part 23. A59EU ....................... A78EU ....................... 7A15 .......................... 14 CFR Part 23. 14 CFR Part 23. CAR 3. A20SO ....................... A8EA ......................... CAR 3. CAR 3. A23SO ....................... A14CE ....................... A31CE ....................... 5A4 ............................ 14 CFR Part 23. 14 CFR Part 23. 14 CFR Part 23. CAR 3. A12CE ....................... 3A20 .......................... 14 CFR Part 23. CAR3, 14 CFR Part 23. A60EU ....................... 14 CFR Part 23. 2A4 ............................ CAR 3. 6A1 ............................ A12SW ...................... CAR 3. 14 CFR Part 23. Aircraft make Partenavia Costruzioni Aeronauticas S.p.A. Piaggio Aero Industries S.p.A Pilatus Aircraft Limited .......... The New Piper Aircraft, Inc .. Raytheon Aircraft Company .. SOCATA—Groupe AEROSPATIALE. Twin Commander .................. P–180 ................................................................................. PC–12, PC–12/45 .............................................................. PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC–6/350–H2, PC–6/A, PC–6/A–H1, PC–6/A–H2, PC– 6/B–H2, PC–6/B1–H2, PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2, PC–6/C1–H2. PA–31, PA–31–300, PA–31–325, PA–31–350 ................. PA–31P, PA–31T, PA–31T1, PA–31T2, PA–31T3, PA– 31P–350. PA–42, PA–42–720, PA–42–720R, PA–42–1000 ............. A100 (U–21F), A100A, A100C, B100 ................................ F90 ..................................................................................... E50 (L–23D, RL–23D), C50, F50, D50 (L–23E), G50, D50A H50, D50B, J50, D50C, D50E, D50E–5990. 60, A60, B60 ...................................................................... 65, 65–A90–1, A65, 65–A90–2, A65–8200, 65–A90–3, 65–80, 65–A90–4, 65–A80, 65–A80–8800, 65–B80, 65–88, 65–90, 65–A90, 70, B90, C90, C90A, E90, H90. TBM 700 ............................................................................ 560–F, 681, 680, 690, 680E, 685, 680F, 690A, 720, 690B, 680FL, 690C, 680FL(P), 690D, 680T, 695, 680V, 695A, 680W, 695B. 500–A, 500–B, 500–U, 560–E, 500–S .............................. 700 ..................................................................................... Note 1: The Certification Basis listing refers to the Certification Basis listed on the Type Certificate Data Sheet for each model. The modified aircraft will be compliant with the latest amendment of the regulations applicable to the modification. In particular, the revised Certification Basis will incorporate §§ 23.1301, 23.1309, 23.1311, 23.1321, 23.1322, 23.1353 at amendment 49, and the terms of this Special Condition. Also, each model will be added to the Approved Model List (AML) using a prototyping approach, where the model is only added to the Supplemental Type Certificate as installations are accomplished and evaluated on each model. This combined special condition is being issued simply to avoid having to re-issue a repeated Special Condition document for each model listed on this multi-model approval. wwhite on PROD1PC76 with RULES 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) of Amendment 21–69. VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 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 Avidyne 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 Electronic Flight Instrument Systems (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 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 Certification basis (see note 1) 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 E:\FR\FM\20JYR1.SGM 20JYR1 41108 Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations 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) 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 wwhite on PROD1PC76 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’’ refers to functions, whose VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 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 one modification to the airplane models listed under the heading ‘‘Type Certification Basis.’’ Should Avidyne 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 § 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 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 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: I 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 airplane models listed under the ‘‘Type Certification Basis’’ heading modified by Avidyne 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. I Issued in Kansas City, Missouri on July 14, 2006. Patrick R. Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–11562 Filed 7–19–06; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\20JYR1.SGM 20JYR1

Agencies

[Federal Register Volume 71, Number 139 (Thursday, July 20, 2006)]
[Rules and Regulations]
[Pages 41104-41108]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-11562]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE244, Special Condition 23-184A-SC]

Special Condition; Avidyne Corporation, Inc.; Various Airplane
Models; Protection of Systems for High Intensity Radiated Fields (HIRF)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Amended final special conditions; request for comments.

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SUMMARY: These amended special conditions are issued to Avidyne
Corporation, 55 Old Bedford Road, Lincoln, MA 01773. This is an
amendment to special condition 23-184-SC, which was published on May
23, 2006 (71 FR 29574), for installation of an EFIS manufactured by
Avidyne on various models. The original issue left off the Cirrus
Design Corporation SR22, which was the first model to be certified
under the STC.
The airplanes listed under this multi-model approval will have
novel and unusual design features when compared

[[Page 41105]]

to the state of technology envisaged in the applicable airworthiness
standards. These novel and unusual design features include the
installation of the Entegra II Avionics System, consisting of: (2)
Model 700-0003-( ) Integrated Flight Displays (IFD), (2) Model 700-
00011-( ) Magnetometer/OAT sensors, and (1) Model 700-00085-000
Keyboard/Controller. These components are all manufactured by Avidyne
Corporation, Inc. 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 May 10, 2006.
Comments must be received on or before August 21, 2006.

ADDRESSES: Comments on these special conditions may be mailed in
duplicate to: Federal Aviation Administration, Regional Counsel, ACE-7,
Attention: Rules Docket Clerk, Docket No. CE244, Room 506, 901 Locust,
Kansas City, Missouri 64106. All comments must be marked: Docket No.
CE244. 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: 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) 329-4123.

SUPPLEMENTARY INFORMATION: The FAA has determined that notice and
opportunity for prior public comment hereon are impracticable because
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. CE244.'' The postcard will be date stamped and
returned to the commenter.

Background

In early 2006, the Avidyne Corporation, 55 Old Bedford Road,
Lincoln, MA 01773, made an application to the FAA for a new
Supplemental Type Certificate for airplane models listed under the type
certification basis. The models are currently approved under the type
certification basis listed in the paragraph headed ``Type Certification
Basis.'' The proposed modification incorporates a novel or unusual
design feature, such as a digital avionics system, that may be
vulnerable to HIRF external to the airplane.

Type Certification Basis

Under the provisions of 14 CFR part 21, Sec. 21.101, Avidyne
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. Sec. 23.1301,
23.1309, 23.1311, and 23.1321, 23.1322 of Amendment 23-49; exemptions,
if any; and the terms of this special condition adopted by this
rulemaking action.

Final Special Conditions
[Approved model list--Part 23 Class I & II (AC 23.1309-1C]
----------------------------------------------------------------------------------------------------------------
Certification basis
Aircraft make Aircraft model(s) Type certificate No. (see note 1)
----------------------------------------------------------------------------------------------------------------
Aerostar Aircraft Corporation.... PA-60-600 (Aerostar A17WE......................... 14 CFR Part 23.
600), PA-60-601
(Aerostar 601), PA-60-
601P (Aerostar 601P),
PA-60-602P (Aerostar
602P).
Cessna Aircraft Company.......... 172R, 172S.............. 3A12.......................... ...................
182S, 182T, T182T....... 3A1314 CFR Part 23............ 14 CFR Part 23.
206H, T206H............. A4CE.......................... 14 CFR Part 23.
T303.................... A34CE......................... 14 CFR Part 23.
310, 310A (USAF U-3A), 3A10.......................... CAR 3.
310B, 310C, 310D, 310E
(USAF U-3B), 310F,
310G, 310H, 310I, 310J,
310J-1, 310K, 310L,
310N, 310P, E310H,
E310J, T310P, 310Q,
T310Q, 310R, T310R.
320, 320-1, 320A, 320B, 3A25.......................... CAR 3.
320C, 320D, 320E, 320F
340, 340A, 335, 340,
340A.
336..................... A2CE.......................... CAR 3.
337, 337A (USAF O2B), A6CE.......................... CAR 3, 14 CFR Part
337B, 337C, 337D, 337E, 23.
337F, 337G, 337H, M337B
(USAF O2A), P337H,
T337B, T337C, T337D,
T337E, T337F, T337G,
T337H, T337H-SP.
Cirrus Design Corporation........ SR20, SR22.............. A00009CH...................... 14 CFR Part 23.
Columbia Aircraft Manufacturing.. LC40-550FG, LC42-550FG.. A00003SE...................... 14 CFR Part 23.

[[Page 41106]]

Commander Aircraft............... 112, 114, 112TC, 112B, A12SO......................... CAR 3.
112TCA, 114A, 114B,
114TC.
de Havilland Inc................. DHC-2 Mk. I, DHC-2 Mk. A-806......................... CAR 3.
II, DHC-2 Mk. III.
Diamond Aircraft Industries...... DA 20-A1, DA20-C1....... TA4CH......................... 14 CFR Part 23.
A40..................... A47CE......................... 14 CFR Part 21, 14
CFR Part 23.
A42..................... A57CE......................... 14 CFR Part 21, 14
CFR Part 23.
Maule Aerospace Technology, Inc.. Bee Dee M-4, M-5-180C, 3A23.......................... CAR 3.
MXT-7-160, M-4, M-5-
200, MX-7-180A, M-4C, M-
5-210C, MXT-7-180, M-
4S, M-5-210TC, MX-7-
180B, M-4T, M-5-220C,
MXT-7-420, M-4-180C, M-
5-235C, M-7-235B, M-4-
180S, M-6-180, M-7-
235A, M-4-180T, M-6-
235, M-7-235C M-4-210 M-
7-235 MX-7-180C, M-4-
210C, MX-7-235, M-7-
260, M-4-210S MX-7-180
MT-7-260, M-4-210T, MX-
7-420, M-7-260C,M-4-
220, MXT-7-180, M-7-
420AC, M-4-220C, MT-7-
235, MX-7-160C, M-4-
220S, M-8-235, MX-7-
180AC, M-4-220T, MX-7-
160.
Mooney Aircraft Corp............. M20, M20A, M20B, M20C, 2A3........................... CAR 3.
M20D, M20E, M20F, M20G,
M20J, M20K, M20L, M20M,
M20R, M20S.
M22..................... A6SW.......................... CAR 3.
Partenavia Costruzioni P 68, P 68B, P 68C, P A31EU......................... 14 CFR Part 23.
Aeronauticas S.p.A. 68C-TC, P 68
``OBSERVER'', AP68 TP
series 300, P68TC
``OBSERVER'', AP68TP
600, P68 ``OBSERVER 2''.
The New Piper Aircraft, Inc...... PA-28-160, PA-28-150, PA-
28-180, PA-28S-160, PA-
28S-180, PA-28-235, PA-
28-140 2 PCLM, PA-28-
140 4 PCLM, PA-28R-180,
PA-28R-200, PA-28R-200,
PA-28-180, PA-28-235,
PA-28-151, PA-28-181,
PA-28-181, PA-28-161,
PA-28-161, PA-28-161,
PA-28R-201, PA-28R-
201T, PA-28-236, PA-
28RT-201, PA-28RT-201,
PA-28RT-201T, PA-28-
201T.
A-32-260, PA-32-300, PA- A3SO.......................... CAR 3.
32S-300, PA-32R-300, PA-
32RT-300, PA-32RT-300T,
PA-32R-301, PA-32R-301,
PA-32R-301T, PA-32-301,
PA-32-301T, PA-32R-301T.
PA-30, PA-39, PA-40..... A1EA.......................... CAR 3.
PA-34-200, PA-34-200T, A7SO.......................... CAR 3.
PA-34-220T, PA-34-220T,
PA-34-220T.
PA-44-180, PA-44-180, PA- A19SO......................... 14 CFR Part 23.
44-180T.
PA-46-310P, PA-46-350P, A25SO......................... 14 CFR Part 23.
PA-46-500TP.
Raytheon Aircraft Company........ A36, B36TC, G36......... 3A15.......................... CAR 3.
58 and 58A.............. 3A16.......................... CAR 3.
58P and 58PA, 58TC and A23CE......................... 14 CFR Part 23.
58TCA.
REVO, Incorporated............... Lake LA-4, LA-4A, LA-4P, 1A13.......................... CAR 3, 14 CFR Part
Lake LA-4-200, Lake 250. 23.
SOCATA--Groupe AEROSPATIALE...... TB 20, TB 10, TB 21, A51EU......................... 14 CFR Part 23.
TB9, TB 200.
Twin Commander................... 500, 520, 560, 560-A.... 6A1........................... CAR 3.
----------------------------------------------------------------------------------------------------------------

Final Special Conditions
[Approved model list--Part 23 class III]
----------------------------------------------------------------------------------------------------------------
Certification basis
Aircraft make Aircraft model(s) Type certificate No. (see note 1)
----------------------------------------------------------------------------------------------------------------
Aerostar Aircraft Corporation.... PA-60-700P (Aerostar A17WE......................... 14 CFR Part 23.
700P).
Cessna Aircraft Company.......... 208, 208A, 208B......... A37CE......................... 14 CFR Part 23.
401, 401A, 401B, 402, A7CE.......................... CAR 3.
402A, 402B, 402C, 411,
411A, 414, 414A, 421,
421A, 421B, 421C, 425.
404, 406................ A25CE......................... 14 CFR Part 23.
441..................... A28CE......................... 14 CFR Part 23.
de Havilland Inc................. (Twin Otter) DHC-6-1, A9EA.......................... CAR 3.
DHC-6-100, DHC-6-200,
DHC-6-300.
Fairchild........................ SA26-T, SA26-AT, SA226- A5SW.......................... CAR 3.
T, SA226-AT, SA226-
T(B), SA227-AT, SA227-
TT.
Mitsubishi Heavy Industries, Ltd. MU-2B, MU-2B-10, MU-2B- A2PC.......................... CAR 3.
20, MU-2B-15, MU-2B-30,
MU-2B-35, MU-2B-25, MU-
2B-36, MU-2B-26.

[[Page 41107]]

MU-2B-25, MU-2B-35, MU- A10SW......................... CAR 3.
2B-26, MU-2B-36, MU-2B-
26A, MU-2B-36A, MU-2B-
40, MU-2B-60.
Partenavia Costruzioni ``SPARTACUS'', AP68TP A31EU......................... 14 CFR Part 23.
Aeronauticas S.p.A. 600 ``VIATOR'', VA300.
Piaggio Aero Industries S.p.A.... P-180................... A59EU......................... 14 CFR Part 23.
Pilatus Aircraft Limited......... PC-12, PC-12/45......... A78EU......................... 14 CFR Part 23.
PC-6, PC-6-H1, PC-6-H2, 7A15.......................... CAR 3.
PC-6/350, PC-6/350-H1,
PC-6/350-H2, PC-6/A, PC-
6/A-H1, PC-6/A-H2, PC-6/
B-H2, PC-6/B1-H2, PC-6/
B2-H2, PC-6/B2-H4, PC-6/
C-H2, PC-6/C1-H2.
The New Piper Aircraft, Inc...... PA-31, PA-31-300, PA-31- A20SO......................... CAR 3.
325, PA-31-350.
PA-31P, PA-31T, PA-31T1, A8EA.......................... CAR 3.
PA-31T2, PA-31T3, PA-
31P-350.
PA-42, PA-42-720, PA-42- A23SO......................... 14 CFR Part 23.
720R, PA-42-1000.
Raytheon Aircraft Company........ A100 (U-21F), A100A, A14CE......................... 14 CFR Part 23.
A100C, B100.
F90..................... A31CE......................... 14 CFR Part 23.
E50 (L-23D, RL-23D), 5A4........................... CAR 3.
C50, F50, D50 (L-23E),
G50, D50A H50, D50B,
J50, D50C, D50E, D50E-
5990.
60, A60, B60............ A12CE......................... 14 CFR Part 23.
65, 65-A90-1, A65, 65- 3A20.......................... CAR3, 14 CFR Part
A90-2, A65-8200, 65-A90- 23.
3, 65-80, 65-A90-4, 65-
A80, 65-A80-8800, 65-
B80, 65-88, 65-90, 65-
A90, 70, B90, C90,
C90A, E90, H90.
SOCATA--Groupe AEROSPATIALE...... TBM 700................. A60EU......................... 14 CFR Part 23.
Twin Commander................... 560-F, 681, 680, 690, 2A4........................... CAR 3.
680E, 685, 680F, 690A,
720, 690B, 680FL, 690C,
680FL(P), 690D, 680T,
695, 680V, 695A, 680W,
695B.
500-A, 500-B, 500-U, 560- 6A1........................... CAR 3.
E, 500-S.
700..................... A12SW......................... 14 CFR Part 23.
----------------------------------------------------------------------------------------------------------------

Note 1: The Certification Basis listing refers to the
Certification Basis listed on the Type Certificate Data Sheet for
each model. The modified aircraft will be compliant with the latest
amendment of the regulations applicable to the modification. In
particular, the revised Certification Basis will incorporate
Sec. Sec. 23.1301, 23.1309, 23.1311, 23.1321, 23.1322, 23.1353 at
amendment 49, and the terms of this Special Condition. Also, each
model will be added to the Approved Model List (AML) using a
prototyping approach, where the model is only added to the
Supplemental Type Certificate as installations are accomplished and
evaluated on each model. This combined special condition is being
issued simply to avoid having to re-issue a repeated Special
Condition document for each model listed on this multi-model
approval.

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

Avidyne 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 Electronic Flight
Instrument Systems (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

[[Page 41108]]

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
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'' refers
to 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 one
modification to the airplane models listed under the heading ``Type
Certification Basis.'' Should Avidyne 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

0
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

0
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 Avidyne 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 July 14, 2006.
Patrick R. Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-11562 Filed 7-19-06; 8:45 am]
BILLING CODE 4910-13-P

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