Special Conditions; ASPEN Avionics Inc. Model EFD 1000; Electronic Flight Instrument System (EFIS); Protection of Systems for High Intensity Radiated Fields (HIRF), 69579-69583 [E7-23835]

Download as PDF Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations Communications Avionics Systems 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 November 30, 2007. Patrick R. Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23852 Filed 12–7–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. CE278, Special Condition 23– 218–SC] Special Conditions; ASPEN Avionics Inc. Model EFD 1000; Electronic Flight Instrument System (EFIS); Protection of Systems for High Intensity Radiated Fields (HIRF) Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. AGENCY: SUMMARY: These special conditions are issued to ASPEN Avionics Inc., for a Supplemental Type Certificate for the models listed under the heading ‘‘Type Certification Basis’’ under the Approved Model List Process. These airplanes will have novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. These novel and unusual design features include the installation of electronic flight instrument system (EFIS) displays Model EFD 1000 manufactured by ASPEN Avionics 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. DATES: The effective date of these special conditions is November 30, 2007. Comments must be received on or before January 9, 2008. ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation Administration, Regional Counsel, ACE–7, Attention: Rules Docket Clerk, Docket No. CE278, Room 506, 901 Locust, Kansas City, Missouri 64106. All comments must be marked: Docket No. CE278. 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: Jim Brady, Aerospace Engineer, Standards Office (ACE–111), Small Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone (816) 329–4132. SUPPLEMENTARY INFORMATION: The FAA has determined that notice and opportunity for prior public comment hereon are impracticable because these procedures would significantly delay issuance of the approval design and thus delivery of the affected aircraft. In addition, the substance of these special conditions has been subject to the public comment process in several prior instances with no substantive comments received. The FAA, therefore, finds that good cause exists for making these special conditions effective upon issuance. Comments Invited Interested persons are invited to submit such written data, views, or arguments as they may desire. Communications should identify the regulatory docket or notice number and be submitted in duplicate to the address 69579 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. 278.’’ The postcard will be date stamped and returned to the commenter. Background On June 26, 2007, ASPEN Avionics Inc., made an application to the FAA for a new Supplemental Type Certificate under the Approved Model List Process for the project airplanes. 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, ASPEN Avionics Inc., must show that the 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 section § 23.1301 of Amendment 23–20; §§ 23.1309, 23.1311, and 23.1321 of Amendment 23–49; and § 23.1322 of Amendment 23–43; exemptions, if any; and the special conditions adopted by this rulemaking action. mstockstill on PROD1PC66 with RULES Aircraft make Aircraft model(s) Type certificate No. Certification basis Aermacchi S.p.A (Siai Marchetti) .. S.205–18/F, S.205–18/R, S.205–20/F, S.205–20/R, S.205–22/R, S.208, S.208A. F.260, F.260B, F.260C, F.260D, F.260E, F.260F ............. 10, 10A, 100, 100A, 100–180 ............................................ A9EU ................ FAR 23 ............. 1 A10EU .............. 1A21 ................. CAR 3 ............... CAR 3 ............... 1 1 Aero Commander (Dynac Aerospace Corp). VerDate Aug<31>2005 16:20 Dec 07, 2007 Jkt 214001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\10DER1.SGM 10DER1 Class 1 or 2 69580 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations Aircraft make Aircraft model(s) Type certificate No. Certification basis Aeronautica Macchi S.p.A (Macchi). Aerostar Aircraft Corp. (Piper Aerostar). American Champion ...................... AL 60, AL 60–B, AL 60–F5, AL 60–C5 ............................. AM–3 .................................................................................. 360, 400 ............................................................................. 7A12 ................. A19EU .............. A11WE ............. CAR 3 ............... FAR 23 ............. FAR 23 ............. 1 1 2 402 ..................................................................................... 8KCAB, 8GCBC ................................................................. A–1, A–1A, A–1B ............................................................... S–1S, S–1T, S–2, S–2A, S–2B, S–2C, S–2S ................... 14–19, 14–19–2, 14–19–3, 14–19–3A,17–30, 17–31, 17– 31TC. 17–30A, 17–31A, 17–31ATC ............................................. 120, 140 ............................................................................. 140A ................................................................................... 150, 150A, 150B, 150C, 150D, 150E, 150F, 150G,150H, 150J, 150K, 150L, 150M, A150K, A150L, A150M, 152, A152. 170, 170A, 170B ................................................................ 172, 172A, 172B, 172C, 172D, 172E, 172F, 172G,172H, 172I, 172K, 172L, 172M, 172N, 172P, 172Q,172R, 172S. 172RG, P172D, R172E, R172F, R172G, R172H, R172J, R172K, 175, 175A, 175B, 175C. 177, 177A, 177B ................................................................ 177RG ................................................................................ 180, 180A,180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, 180K. 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, 182S, 182T, R182, T182, TR182, T182T. 185, 185A, 185B, 185C, 185D, 185E, A185E, A185F ...... 190, 195, 195A, 195B ........................................................ 210, 210A, 210B, 210C, 210D, 210E, 210F, T210F, 210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, T210M, 210N, P210N, T210N, 210R, P210R, T210R, 210–5, 210–5A. 206, P206, P206A, P206B, P206C, P206D, P206E, TP206A, TP206B, TP206C, TP206D, TP206E, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, 206H, T206H. 207, 207A, T207, T207A ................................................... T–303 (Crusader) ............................................................... 310, 310A (USAF U–3A), 310B, 310C, 310D, 310E (USAF U–3B), 310F, 310G, 310H, E310H, 310I, 310J, 310J–1, E310J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R. 320, 320A, 320B, 320C, 320D, 320E, 320F, 320–1, 335, 340, 340A. 336 ..................................................................................... 337, 337A , 337B, T337B, 337C, 337E, T337E, T337C, 337D, T337D, M337B, 337F, T337F, 337G, T337G, 337H, P337H, T337H, T337H–SP. SR20, SR22 ....................................................................... 112, 112TC, 112B, 112TCA, 114, 114A, 114B, 114TC .... CC18–180, CC18–180A .................................................... DHC–2 Mark I, DHC–2 Mark II, DHC–2 Mark III .............. DH.C1, 21, 22, 22A ........................................................... DA 20–A1, DA20–C1 ......................................................... DA 40 ................................................................................. EA300, EA300L, EA300S, EA300/200 .............................. EA–400 .............................................................................. FBA–2C, FBA–2C1 (Bush Hawk), FBA–2C2 (Bush Hawk XP). G44, G44A, SCAN Type 30 .............................................. G115, G115A, G115B, G115C, G115C2, G115D, G115D2, G115EG. G120A ................................................................................ AA–1, AA–1A, AA–1B, AA–1C .......................................... AA–5, AA–5A, AA–5B, AG–5B .......................................... 35–33, 35–A33, 35–B33, 35–C33, 35–C33A, E33, E33A, E33C, F33, F33A, F33C, G33, H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 36, A36, A36TC, B36TC. A3CE ................ A21CE .............. A22NM .............. A8SO ................ 1A3 ................... CAR 3 ............... FAR 23 ............. FAR 23 ............. FAR 23 ............. CAR 3 ............... 2 1 1 1 1 A18CE .............. A–768 ............... 5A2 ................... 3A19 ................. FAR 23 ............. CAR 3 ............... CAR 3 ............... CAR 3, FAR 23 1 1 1 1 A–799 ............... 3A12 ................. CAR 3 ............... CAR 3, FAR 23 1 1 3A17 ................. CAR 3 ............... 1 A13CE .............. A20CE .............. 5A6 ................... FAR 23 ............. FAR 23 ............. CAR 3 ............... 1 1 1 3A13 ................. CAR 3, FAR 23 1 3A24 ................. A–790 ............... 3A21 ................. CAR 3 ............... CAR 3 ............... CAR 3 ............... 1 1 1 A4CE ................ CAR 3 ............... 1 A16CE .............. A34CE .............. 3A10 ................. FAR 23 ............. FAR 23 ............. ...................... 1 2 2 3A25 ................. CAR 3 ............... 2 A2CE ................ A6CE ................ CAR 3 ............... CAR 3, FAR 23 2 2 A00009CH ........ A12SO .............. A00006SE ........ A–806 ............... A44EU .............. TA4CH .............. A47CE .............. A67EU .............. A43CE .............. A7EA ................ FAR 23 ............. CAR 3 ............... FAR 23 ............. CAR 3 ............... FAR 21 ............. FAR 23 ............. FAR 23 ............. FAR 23 ............. FAR 23 ............. CAR 3, FAR 23 1 1 1 1 1 1 1 1 1 1 A–734 ............... A57EU .............. CAR 4a ............. FAR 23 ............. 2 1 A49CE .............. A11EA .............. A16EA .............. 3A15 ................. FAR 23 ............. FAR 23 ............. FAR 23 ............. CAR 3 ............... 1 1 1 1 Aviat (Sky International) ................ Bellanca (Alexandria Aircraft LLC) Cessna .......................................... Cirrus Design Corp ....................... Commander Aircraft Co ................ Cub Crafters .................................. DeHavilland/Bombardier ............... Diamond Aircraft Company ........... Extra (Extra Flugzeugbau GmbH) Found Aircraft Development, Inc .. mstockstill on PROD1PC66 with RULES Gulfstream American Corporation Grob-Werke ................................... Grumman American (Tiger Aircraft LLC). Hawker Beechcraft ........................ VerDate Aug<31>2005 16:20 Dec 07, 2007 Jkt 214001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\10DER1.SGM 10DER1 Class 1 or 2 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations Aircraft model(s) Type certificate No. Certification basis 35, A35, B35, C35, D35, E35, F35, G35, 35R .................. 76 ....................................................................................... 95, B95, B95A, D95A, E95, 95–55, 95–A55, 95–B55, 95–B55A, 95–B55B (T–42A), 95–C55, 95–C55A, D55, D55A, E55, E55A, 56TC, A56TC, 58, 58A. 19A, B19, M19A, 23, A23, A23A, A23–19, A23–24, B23, C23, A24, A24R, B24R, C24R. 50, B50, C50, D50, D50A, D50B, D50C, D50E, D50E– 5990, E50, F50, G50, H50, J50. 45 (YT–34), A45 (T–34A) or (B–45), D45 (T–34B) ........... H–250, H–295, HT–295, H391, H391B, H–395, H–395A, H–700, H–800. HST–550, HST–550A ........................................................ 500 ..................................................................................... Model 44 ............................................................................ 4500–300, 4500–300 Series II .......................................... Colonial C–1, Colonial C–2, Lake LA–4, Lake LA–4A, Lake LA–4P, Lake LA–4–200, Lake Model 250. LC40–550FG, LC41–550FG, LC42–550FG ...................... XL–2 ................................................................................... 402–2 ................................................................................. 11A, 11E ............................................................................ Bee Dee M–4, M–4, M–4C, M–4S, M–4T, M–4–180C, M–4–180S, M–4–180T, M–4–210, M–4–210C, M–4– 210S, M–4–210T, M–4–220, M–4–220C, M–4–220S, M–4–220T, M–5–180C, M–5–200, M–5–210C, M–5– 210TC, M–5–220C, M–5–235C, M–6–180, M–6–235, M–7–235, MX–7–235, MX–7–180, MX–7–420, MXT– 7–180, MT–7–235, M–8–235, MX–7–160, MXT–7–160, MX–7–180A, MXT–7–180A, MX–7–180B, M–7–235B, M–7–235A, M–7–235C, MX–7–180C, M–7–260, MT– 7–260, M–7–260C, M–7–420AC, MX–7–160C, MX–7– 180AC, M–7–420A, MT–7–420. M20, M20A, M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20M, M20R, M20S. M22 .................................................................................... ZLIN 562L .......................................................................... ZLIN Z–242L, Z–143L ........................................................ Navion, Navion A, Navion B, Navion D, Navion E, Navion F, Navion G, Navion H. OMF–100–160 ................................................................... A–777 ............... A29CE .............. 3A16 ................. CAR 3 ............... FAR 23 ............. CAR 3, FAR 23 1 1 2 A1CE ................ CAR 3 ............... 1 5A4 ................... CAR 3 ............... 2 5A3 ................... 1A8 ................... CAR 3 ............... CAR 3 ............... 1 1 A4EA ................ A2EA ................ A2WI ................. A17CE .............. 1A13 ................. CAR 3 ............... CAR 3 ............... FAR 23 ............. FAR 23 ............. CAR 3 ............... 1 2 2 2 1 A00003SE ........ A00008DE ........ 2A11 ................. A–804 ............... 3A23 ................. FAR 23 ............. FAR 23 ............. CAR 3 ............... CAR 3 ............... CAR 3 ............... 1 1 2 1 1 2A3 ................... CAR 3 ............... 1 A6SW ............... A30EU .............. A76EU .............. A–782 ............... CAR 3 ............... FAR 23 ............. FAR 23 ............. CAR 3 ............... 1 1 1 1 A46CE .............. FAR 23 ............. 1 A31EU .............. FAR 23 ............. 2 7A15 ................. CAR 3 ............... 1 A50EU .............. A–780 ............... 1A2 ................... FAR 23 ............. CAR 3 ............... CAR 3 ............... 1 1 1 1A4 ................... CAR 3 ............... 1 1A6 ................... CAR 3 ............... 1 1A10 ................. 1A15 ................. 2A13 ................. CAR 3 ............... CAR 3 ............... CAR 3 ............... 2 1 1 A1EA ................ A3SO ................ CAR 3 ............... CAR 3 ............... 2 1 A7SO ................ CAR 3 ............... 2 Aircraft make Helio (Alliance LLC). Aircraft Group, King’s Engineering Fellowship (The). Lake/Revo (Global Amphibians LLC). Lancair (Columbia Aircraft) ........... Liberty Aerospace Incorporated .... Lockheed Aircraft Corporation ...... Luscombe Aircraft Corporation ..... Maule ............................................. Mooney Aircraft Corp .................... Moravan (Moravan a.s.) ................ Navion Aircraft Company, Ltd. (Navion). OMF (Ostmeck. Flugzeugbau GmbH). Partenavia (Vulcanair S.p.A.) ........ Pilatus Aircraft Limited .................. mstockstill on PROD1PC66 with RULES Piper (New Piper) .......................... VerDate Aug<31>2005 69581 16:20 Dec 07, 2007 P68, P68B, P68C, P68C–TC, P68 ‘‘Observer,’’ P68 ‘‘Observer 2,’’ P68 TC ‘‘Observer’’, AP68TP 300 ‘‘Spartacus’’, AP68TP 600 ‘‘Viator’’, VA300. 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. PC–7 .................................................................................. PA–12, PA–12S ................................................................. PA–18, PA–18S, PA–18–105, PA–18S–105, PA–18A, PA–18–125, PA–18S–125, PA–18AS–125, PA–18– 135, PA–18A–135, PA–18S–135, PA–18AS–135, PA– 18–150, PA–18A–150, PA–18S–150, PA–18AS–150, PA–19, PA19S. PA–20, PA–20S, PA–20–115, PA–20S–115, PA–20–135, PA–20S–135. PA–22, PA–22–108, PA–22–135, PA–22S–135, PA–22– 150, PA–22S–150, PA–22–160, PA–22S–160. PA–23, PA–23–160, PA–23–235, PA–23–250 ................. PA–24, PA–24–250 PA–24–260, PA–24–400 .................. PA–28–140, PA–28–150, PA–28–151, PA–28–160, PA– 28–161, PA–28–180, PA–28–235, PA–28S–160, PA– 28–161, PA–28–181, PA–28–235, PA–28S–160, PA– 28R–201, PA–28R–201T, PA–28RT–201, PA–28RT– 201T, PA–28–201T, PA–28–236. PA–30, PA–39, PA–40 ...................................................... PA–32–260, PA–32–300, PA–32S–300, PA–32R–300, PA–32RT–300, PA–32RT–300T, PA–32R–301(SP), PA–32R–301(HP), PA–32R–301T, PA–32–301, PA– 32–301T, PA–32–301FT, PA32–301XTC. PA–34–200, PA–34–200T, PA–34–220T .......................... Jkt 214001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\10DER1.SGM 10DER1 Class 1 or 2 69582 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations Aircraft model(s) Type certificate No. Certification basis PA–44–180, PA–44–180T ................................................. PA–46–310P, PA–46–350P, PA–46–500TP ..................... 200, 200A, 200B, 200C, 200D, 400 .................................. PZL–104 WILGA 80, PZL–104M WILGA 2000, PZL– WARSZAWA. PZL–KOLIBER 150A, PZL–KOLIBER 160A, .................... PZL M20 03 ....................................................................... PZL M26 01 ....................................................................... T67M260, T67M260–T3A .................................................. TB9, TB10, TB20, TB21, TB200 ....................................... 100S, 150ST, 150T, 235E, 235C MS880B, MS885, MS894A, MS893A, MS892A–150, MS892E–150, MS893E, MS894E. GA–7 (Cougar) ................................................................... A19SO .............. A25SO .............. 3A18 ................. A55EU .............. A69EU .............. FAR 23 ............. FAR 23 ............. CAR 3 ............... FAR 23 ............. FAR 23 ............. 1 1 1 1 1 A68EU .............. A44CE .............. A73EU .............. A51EU .............. 7A14 ................. FAR 23 ............. FAR 23 ............. FAR 23 ............. FAR 23 ............. CAR 3 ............... 2 1 1 1 1 A17SO .............. FAR 23 ............. 2 108, 108–1, 108–2, 108–3, 108–5 .................................... A–767 ............... CAR 3 ............... 1 500, 500–A, 500–B, 500–U, 500–S, 520, 560, 560–A, 560–E. WACO YMF ....................................................................... CH2000 .............................................................................. ATC 542 ........... CAR 3 ............... 1 ATC 542 ........... TA5CH .............. Aero 7A ............ FAR 23 ............. 1 1 Aircraft make Prop-Jets, Inc ................................ PZL (Panstwowe Zaklady Lotnicze). PZL (PZL Mielec) .......................... Slingsby Aviation Ltd ..................... SOCATA (SOCATA Groupe Aerospatiale). SOCATA (SOCATA Groupe Aerospatiale). Stinson (Univair Aircraft Corporation). Twin Commander Aircraft Corporation. WACO Aircraft Company .............. Zenair Ltd ...................................... 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). 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. mstockstill on PROD1PC66 with RULES Novel or Unusual Design Features ASPEN Avionics Inc., 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. VerDate Aug<31>2005 16:20 Dec 07, 2007 Jkt 214001 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 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Class 1 or 2 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 ........... 50 50 50 100 50 50 100 100 700 700 2000 3000 3000 1000 3000 2000 600 Average 50 50 50 100 50 50 100 100 50 100 200 200 200 200 300 200 200 The field strengths are expressed in terms of peak root-mean-square (rms) values. or, E:\FR\FM\10DER1.SGM 10DER1 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations (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. Applicability As discussed above, these special conditions are applicable to one modification to the aircraft models listed under the heading ‘‘Type Certification Basis.’’ Should ASPEN Avionics Inc., apply at a later date to extend this modification to include additional airplane models, the special conditions would apply to that model as well under the provisions of § 21.101. mstockstill on PROD1PC66 with RULES Conclusion This action affects only certain novel or unusual design features on one modification to the aircraft models listed under the heading ‘‘Type Certification Basis.’’ 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. VerDate Aug<31>2005 16:20 Dec 07, 2007 Jkt 214001 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. List of Subjects in 14 CFR Part 23 Aircraft, Aviation safety, Signs and symbols. Citation The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 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 the EFD 1000 EFIS manufactured by ASPEN Avionics Inc. 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 November 30, 2007. Patrick R. Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23835 Filed 12–7–07; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 69583 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28943; Directorate Identifier 2007–NM–011–AD; Amendment 39–15295; AD 2007–25–13] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767–300F Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767–300F series airplanes. This AD requires replacing the rotomolded duct(s) of the mix manifold system with new duct(s). This AD results from a report of failures of the duct joint seal of the mix manifold system. We are issuing this AD to prevent air conditioning leakage into the mix manifold bay. Such leakage could decrease the air flow to the flight compartment and main cabin or could allow smoke into the flight compartment in the event of a fire in the main cabin or forward cargo compartment. This AD becomes effective January 14, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 14, 2008. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. DATES: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Jeffrey S. Palmer, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, E:\FR\FM\10DER1.SGM 10DER1

Agencies

[Federal Register Volume 72, Number 236 (Monday, December 10, 2007)]
[Rules and Regulations]
[Pages 69579-69583]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23835]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE278, Special Condition 23-218-SC]


Special Conditions; ASPEN Avionics Inc. Model EFD 1000; 
Electronic Flight Instrument System (EFIS); Protection of Systems for 
High Intensity Radiated Fields (HIRF)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued to ASPEN Avionics Inc., 
for a Supplemental Type Certificate for the models listed under the 
heading ``Type Certification Basis'' under the Approved Model List 
Process. These airplanes will have novel and unusual design features 
when compared to the state of technology envisaged in the applicable 
airworthiness standards. These novel and unusual design features 
include the installation of electronic flight instrument system (EFIS) 
displays Model EFD 1000 manufactured by ASPEN Avionics 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.

DATES: The effective date of these special conditions is November 30, 
2007. Comments must be received on or before January 9, 2008.

ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation 
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk, 
Docket No. CE278, Room 506, 901 Locust, Kansas City, Missouri 64106. 
All comments must be marked: Docket No. CE278. 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: Jim Brady, Aerospace Engineer, 
Standards Office (ACE-111), Small Airplane Directorate, Aircraft 
Certification Service, Federal Aviation Administration, 901 Locust, 
Room 301, Kansas City, Missouri 64106; telephone (816) 329-4132.

SUPPLEMENTARY INFORMATION: The FAA has determined that notice and 
opportunity for prior public comment hereon are impracticable because 
these procedures would significantly delay issuance of the approval 
design and thus delivery of the affected aircraft. In addition, the 
substance of these special conditions has been subject to the public 
comment process in several prior instances with no substantive comments 
received. The FAA, therefore, finds that good cause exists for making 
these special conditions effective upon issuance.

Comments Invited

    Interested persons are invited to submit such written data, views, 
or arguments as they may desire. Communications should identify the 
regulatory docket or notice number and be submitted in duplicate to the 
address specified above. All communications received on or before the 
closing date for comments will be considered by the Administrator. The 
special conditions may be changed in light of the comments received. 
All comments received will be available in the Rules Docket for 
examination by interested persons, both before and after the closing 
date for comments. A report summarizing each substantive public contact 
with FAA personnel concerning this rulemaking will be filed in the 
docket. Commenters wishing the FAA to acknowledge receipt of their 
comments submitted in response to this notice must include a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 278.'' The postcard will be date stamped and 
returned to the commenter.

Background

    On June 26, 2007, ASPEN Avionics Inc., made an application to the 
FAA for a new Supplemental Type Certificate under the Approved Model 
List Process for the project airplanes. The proposed modification 
incorporates a novel or unusual design feature, such as digital 
avionics consisting of an EFIS that is vulnerable to HIRF external to 
the airplane.

Type Certification Basis

    Under the provisions of 14 CFR part 21, Sec.  21.101, ASPEN 
Avionics Inc., must show that the 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 section Sec.  23.1301 
of Amendment 23-20; Sec. Sec.  23.1309, 23.1311, and 23.1321 of 
Amendment 23-49; and Sec.  23.1322 of Amendment 23-43; exemptions, if 
any; and the special conditions adopted by this rulemaking action.

----------------------------------------------------------------------------------------------------------------
                                                                                                        Class 1
         Aircraft make             Aircraft model(s)     Type certificate No.    Certification basis      or 2
----------------------------------------------------------------------------------------------------------------
Aermacchi S.p.A (Siai           S.205-18/F, S.205-18/   A9EU..................  FAR 23...............          1
 Marchetti).                     R, S.205-20/F, S.205-
                                 20/R, S.205-22/R,
                                 S.208, S.208A.
                                F.260, F.260B, F.260C,  A10EU.................  CAR 3................          1
                                 F.260D, F.260E,
                                 F.260F.
Aero Commander (Dynac           10, 10A, 100, 100A,     1A21..................  CAR 3................          1
 Aerospace Corp).                100-180.

[[Page 69580]]

 
Aeronautica Macchi S.p.A        AL 60, AL 60-B, AL 60-  7A12..................  CAR 3................          1
 (Macchi).                       F5, AL 60-C5.          A19EU.................  FAR 23...............          1
                                AM-3..................
Aerostar Aircraft Corp. (Piper  360, 400..............  A11WE.................  FAR 23...............          2
 Aerostar).
American Champion.............  402...................  A3CE..................  CAR 3................          2
                                8KCAB, 8GCBC..........  A21CE.................  FAR 23...............          1
Aviat (Sky International).....  A-1, A-1A, A-1B.......  A22NM.................  FAR 23...............          1
                                S-1S, S-1T, S-2, S-2A,  A8SO..................  FAR 23...............          1
                                 S-2B, S-2C, S-2S.
Bellanca (Alexandria Aircraft   14-19, 14-19-2, 14-19-  1A3...................  CAR 3................          1
 LLC).                           3, 14-19-3A,17-30, 17-
                                 31, 17-31TC.
                                17-30A, 17-31A, 17-     A18CE.................  FAR 23...............          1
                                 31ATC.
Cessna........................  120, 140..............  A-768.................  CAR 3................          1
                                140A..................  5A2...................  CAR 3................          1
                                150, 150A, 150B, 150C,  3A19..................  CAR 3, FAR 23........          1
                                 150D, 150E, 150F,
                                 150G,150H, 150J,
                                 150K, 150L, 150M,
                                 A150K, A150L, A150M,
                                 152, A152.
                                170, 170A, 170B.......  A-799.................  CAR 3................          1
                                172, 172A, 172B, 172C,  3A12..................  CAR 3, FAR 23........          1
                                 172D, 172E, 172F,
                                 172G,172H, 172I,
                                 172K, 172L, 172M,
                                 172N, 172P,
                                 172Q,172R, 172S.
                                172RG, P172D, R172E,    3A17..................  CAR 3................          1
                                 R172F, R172G, R172H,
                                 R172J, R172K, 175,
                                 175A, 175B, 175C.
                                177, 177A, 177B.......  A13CE.................  FAR 23...............          1
                                177RG.................  A20CE.................  FAR 23...............          1
                                180, 180A,180B, 180C,   5A6...................  CAR 3................          1
                                 180D, 180E, 180F,
                                 180G, 180H, 180J,
                                 180K.
                                182, 182A, 182B, 182C,  3A13..................  CAR 3, FAR 23........          1
                                 182D, 182E, 182F,
                                 182G, 182H, 182J,
                                 182K, 182L, 182M,
                                 182N, 182P, 182Q,
                                 182R, 182S, 182T,
                                 R182, T182, TR182,
                                 T182T.
                                185, 185A, 185B, 185C,  3A24..................  CAR 3................          1
                                 185D, 185E, A185E,
                                 A185F.
                                190, 195, 195A, 195B..  A-790.................  CAR 3................          1
                                210, 210A, 210B, 210C,  3A21..................  CAR 3................          1
                                 210D, 210E, 210F,
                                 T210F, 210G, T210G,
                                 210H, T210H, 210J,
                                 T210J, 210K, T210K,
                                 210L, T210L, 210M,
                                 T210M, 210N, P210N,
                                 T210N, 210R, P210R,
                                 T210R, 210-5, 210-5A.
                                206, P206, P206A,       A4CE..................  CAR 3................          1
                                 P206B, P206C, P206D,
                                 P206E, TP206A,
                                 TP206B, TP206C,
                                 TP206D, TP206E, U206,
                                 U206A, U206B, U206C,
                                 U206D, U206E, U206F,
                                 U206G, TU206A,
                                 TU206B, TU206C,
                                 TU206D, TU206E,
                                 TU206F, TU206G, 206H,
                                 T206H.
                                207, 207A, T207, T207A  A16CE.................  FAR 23...............          1
                                T-303 (Crusader)......  A34CE.................  FAR 23...............          2
                                310, 310A (USAF U-3A),  3A10..................  .....................          2
                                 310B, 310C, 310D,
                                 310E (USAF U-3B),
                                 310F, 310G, 310H,
                                 E310H, 310I, 310J,
                                 310J-1, E310J, 310K,
                                 310L, 310N, 310P,
                                 T310P, 310Q, T310Q,
                                 310R, T310R.
                                320, 320A, 320B, 320C,  3A25..................  CAR 3................          2
                                 320D, 320E, 320F, 320-
                                 1, 335, 340, 340A.
                                336...................  A2CE..................  CAR 3................          2
                                337, 337A , 337B,       A6CE..................  CAR 3, FAR 23........          2
                                 T337B, 337C, 337E,
                                 T337E, T337C, 337D,
                                 T337D, M337B, 337F,
                                 T337F, 337G, T337G,
                                 337H, P337H, T337H,
                                 T337H-SP.
Cirrus Design Corp............  SR20, SR22............  A00009CH..............  FAR 23...............          1
Commander Aircraft Co.........  112, 112TC, 112B,       A12SO.................  CAR 3................          1
                                 112TCA, 114, 114A,
                                 114B, 114TC.
Cub Crafters..................  CC18-180, CC18-180A...  A00006SE..............  FAR 23...............          1
DeHavilland/Bombardier........  DHC-2 Mark I, DHC-2     A-806.................  CAR 3................          1
                                 Mark II, DHC-2 Mark
                                 III.
                                DH.C1, 21, 22, 22A....  A44EU.................  FAR 21...............          1
Diamond Aircraft Company......  DA 20-A1, DA20-C1.....  TA4CH.................  FAR 23...............          1
                                DA 40.................  A47CE.................  FAR 23...............          1
Extra (Extra Flugzeugbau GmbH)  EA300, EA300L, EA300S,  A67EU.................  FAR 23...............          1
                                 EA300/200.             A43CE.................  FAR 23...............          1
                                EA-400................
Found Aircraft Development,     FBA-2C, FBA-2C1 (Bush   A7EA..................  CAR 3, FAR 23........          1
 Inc.                            Hawk), FBA-2C2 (Bush
                                 Hawk XP).
Gulfstream American             G44, G44A, SCAN Type    A-734.................  CAR 4a...............          2
 Corporation.                    30.
Grob-Werke....................  G115, G115A, G115B,     A57EU.................  FAR 23...............          1
                                 G115C, G115C2, G115D,
                                 G115D2, G115EG.
                                G120A.................  A49CE.................  FAR 23...............          1
Grumman American (Tiger         AA-1, AA-1A, AA-1B, AA- A11EA.................  FAR 23...............          1
 Aircraft LLC).                  1C.                    A16EA.................  FAR 23...............          1
                                AA-5, AA-5A, AA-5B, AG-
                                 5B.
Hawker Beechcraft.............  35-33, 35-A33, 35-B33,  3A15..................  CAR 3................          1
                                 35-C33, 35-C33A, E33,
                                 E33A, E33C, F33,
                                 F33A, F33C, G33, H35,
                                 J35, K35, M35, N35,
                                 P35, S35, V35, V35A,
                                 V35B, 36, A36, A36TC,
                                 B36TC.

[[Page 69581]]

 
                                35, A35, B35, C35,      A-777.................  CAR 3................          1
                                 D35, E35, F35, G35,
                                 35R.
                                76....................  A29CE.................  FAR 23...............          1
                                95, B95, B95A, D95A,    3A16..................  CAR 3, FAR 23........          2
                                 E95, 95-55, 95-A55,
                                 95-B55, 95-B55A, 95-
                                 B55B (T-42A), 95-C55,
                                 95-C55A, D55, D55A,
                                 E55, E55A, 56TC,
                                 A56TC, 58, 58A.
                                19A, B19, M19A, 23,     A1CE..................  CAR 3................          1
                                 A23, A23A, A23-19,
                                 A23-24, B23, C23,
                                 A24, A24R, B24R, C24R.
                                50, B50, C50, D50,      5A4...................  CAR 3................          2
                                 D50A, D50B, D50C,
                                 D50E, D50E-5990, E50,
                                 F50, G50, H50, J50.
                                45 (YT-34), A45 (T-     5A3...................  CAR 3................          1
                                 34A) or (B-45), D45
                                 (T-34B).
Helio (Alliance Aircraft        H-250, H-295, HT-295,   1A8...................  CAR 3................          1
 Group, LLC).                    H391, H391B, H-395, H-
                                 395A, H-700, H-800.
                                HST-550, HST-550A.....  A4EA..................  CAR 3................          1
                                500...................  A2EA..................  CAR 3................          2
King's Engineering Fellowship   Model 44..............  A2WI..................  FAR 23...............          2
 (The).                         4500-300, 4500-300      A17CE.................  FAR 23...............          2
                                 Series II.
Lake/Revo (Global Amphibians    Colonial C-1, Colonial  1A13..................  CAR 3................          1
 LLC).                           C-2, Lake LA-4, Lake
                                 LA-4A, Lake LA-4P,
                                 Lake LA-4-200, Lake
                                 Model 250.
Lancair (Columbia Aircraft)...  LC40-550FG, LC41-       A00003SE..............  FAR 23...............          1
                                 550FG, LC42-550FG.
Liberty Aerospace Incorporated  XL-2..................  A00008DE..............  FAR 23...............          1
Lockheed Aircraft Corporation.  402-2.................  2A11..................  CAR 3................          2
Luscombe Aircraft Corporation.  11A, 11E..............  A-804.................  CAR 3................          1
Maule.........................  Bee Dee M-4, M-4, M-    3A23..................  CAR 3................          1
                                 4C, M-4S, M-4T, M-4-
                                 180C, M-4-180S, M-4-
                                 180T, M-4-210, M-4-
                                 210C, M-4-210S, M-4-
                                 210T, M-4-220, M-4-
                                 220C, M-4-220S, M-4-
                                 220T, M-5-180C, M-5-
                                 200, M-5-210C, M-5-
                                 210TC, M-5-220C, M-5-
                                 235C, M-6-180, M-6-
                                 235, M-7-235, MX-7-
                                 235, MX-7-180, MX-7-
                                 420, MXT-7-180, MT-7-
                                 235, M-8-235, MX-7-
                                 160, MXT-7-160, MX-7-
                                 180A, MXT-7-180A, MX-
                                 7-180B, M-7-235B, M-7-
                                 235A, M-7-235C, MX-7-
                                 180C, M-7-260, MT-7-
                                 260, M-7-260C, M-7-
                                 420AC, MX-7-160C, MX-
                                 7-180AC, M-7-420A, MT-
                                 7-420.
Mooney Aircraft Corp..........  M20, M20A, M20B, M20C,  2A3...................  CAR 3................          1
                                 M20D, M20E, M20F,
                                 M20G, M20J, M20K,
                                 M20L, M20M, M20R,
                                 M20S.
                                M22...................  A6SW..................  CAR 3................          1
Moravan (Moravan a.s.)........  ZLIN 562L.............  A30EU.................  FAR 23...............          1
                                ZLIN Z-242L, Z-143L...  A76EU.................  FAR 23...............          1
Navion Aircraft Company, Ltd.   Navion, Navion A,       A-782.................  CAR 3................          1
 (Navion).                       Navion B, Navion D,
                                 Navion E, Navion F,
                                 Navion G, Navion H.
OMF (Ostmeck. Flugzeugbau       OMF-100-160...........  A46CE.................  FAR 23...............          1
 GmbH).
Partenavia (Vulcanair S.p.A.).  P68, P68B, P68C, P68C-  A31EU.................  FAR 23...............          2
                                 TC, P68 ``Observer,''
                                 P68 ``Observer 2,''
                                 P68 TC ``Observer'',
                                 AP68TP 300
                                 ``Spartacus'', AP68TP
                                 600 ``Viator'', VA300.
Pilatus Aircraft Limited......  PC-6, PC-6-H1, PC-6-    7A15..................  CAR 3................          1
                                 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.
                                PC-7..................  A50EU.................  FAR 23...............          1
Piper (New Piper).............  PA-12, PA-12S.........  A-780.................  CAR 3................          1
                                PA-18, PA-18S, PA-18-   1A2...................  CAR 3................          1
                                 105, PA-18S-105, PA-
                                 18A, PA-18-125, PA-
                                 18S-125, PA-18AS-125,
                                 PA-18-135, PA-18A-
                                 135, PA-18S-135, PA-
                                 18AS-135, PA-18-150,
                                 PA-18A-150, PA-18S-
                                 150, PA-18AS-150, PA-
                                 19, PA19S.
                                PA-20, PA-20S, PA-20-   1A4...................  CAR 3................          1
                                 115, PA-20S-115, PA-
                                 20-135, PA-20S-135.
                                PA-22, PA-22-108, PA-   1A6...................  CAR 3................          1
                                 22-135, PA-22S-135,
                                 PA-22-150, PA-22S-
                                 150, PA-22-160, PA-
                                 22S-160.
                                PA-23, PA-23-160, PA-   1A10..................  CAR 3................          2
                                 23-235, PA-23-250.
                                PA-24, PA-24-250 PA-24- 1A15..................  CAR 3................          1
                                 260, PA-24-400.
                                PA-28-140, PA-28-150,   2A13..................  CAR 3................          1
                                 PA-28-151, PA-28-160,
                                 PA-28-161, PA-28-180,
                                 PA-28-235, PA-28S-
                                 160, PA-28-161, PA-28-
                                 181, PA-28-235, PA-
                                 28S-160, PA-28R-201,
                                 PA-28R-201T, PA-28RT-
                                 201, PA-28RT-201T, PA-
                                 28-201T, PA-28-236.
                                PA-30, PA-39, PA-40...  A1EA..................  CAR 3................          2
                                PA-32-260, PA-32-300,   A3SO..................  CAR 3................          1
                                 PA-32S-300, PA-32R-
                                 300, PA-32RT-300, PA-
                                 32RT-300T, PA-32R-
                                 301(SP), PA-32R-
                                 301(HP), PA-32R-301T,
                                 PA-32-301, PA-32-
                                 301T, PA-32-301FT,
                                 PA32-301XTC.
                                PA-34-200, PA-34-200T,  A7SO..................  CAR 3................          2
                                 PA-34-220T.

[[Page 69582]]

 
                                PA-44-180, PA-44-180T.  A19SO.................  FAR 23...............          1
                                PA-46-310P, PA-46-      A25SO.................  FAR 23...............          1
                                 350P, PA-46-500TP.
Prop-Jets, Inc................  200, 200A, 200B, 200C,  3A18..................  CAR 3................          1
                                 200D, 400.
PZL (Panstwowe Zaklady          PZL-104 WILGA 80, PZL-  A55EU.................  FAR 23...............          1
 Lotnicze).                      104M WILGA 2000, PZL-  A69EU.................  FAR 23...............          1
                                 WARSZAWA.
                                PZL-KOLIBER 150A, PZL-
                                 KOLIBER 160A,.
PZL (PZL Mielec)..............  PZL M20 03............  A68EU.................  FAR 23...............          2
                                PZL M26 01............  A44CE.................  FAR 23...............          1
Slingsby Aviation Ltd.........  T67M260, T67M260-T3A..  A73EU.................  FAR 23...............          1
SOCATA (SOCATA Groupe           TB9, TB10, TB20, TB21,  A51EU.................  FAR 23...............          1
 Aerospatiale).                  TB200.                 7A14..................  CAR 3................          1
                                100S, 150ST, 150T,
                                 235E, 235C MS880B,
                                 MS885, MS894A,
                                 MS893A, MS892A-150,
                                 MS892E-150, MS893E,
                                 MS894E.
SOCATA (SOCATA Groupe           GA-7 (Cougar).........  A17SO.................  FAR 23...............          2
 Aerospatiale).
Stinson (Univair Aircraft       108, 108-1, 108-2, 108- A-767.................  CAR 3................          1
 Corporation).                   3, 108-5.
Twin Commander Aircraft         500, 500-A, 500-B, 500- ATC 542...............  CAR 3................          1
 Corporation.                    U, 500-S, 520, 560,
                                 560-A, 560-E.
WACO Aircraft Company.........  WACO YMF..............  ATC 542...............  Aero 7A..............          1
Zenair Ltd....................  CH2000................  TA5CH.................  FAR 23...............          1
----------------------------------------------------------------------------------------------------------------

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).
    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

    ASPEN Avionics Inc., 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, coupling to 
cockpit-installed equipment through the cockpit window apertures is 
undefined.
    The combined effect of the technological advances in airplane 
design and the changing environment has resulted in an increased level 
of vulnerability of electrical and electronic systems required for the 
continued safe flight and landing of the airplane. Effective measures 
against the effects of exposure to HIRF must be provided by the design 
and installation of these systems. The accepted maximum energy levels 
in which civilian airplane system installations must be capable of 
operating safely are based on surveys and analysis of existing radio 
frequency emitters. These special conditions require that the airplane 
be evaluated under these energy levels for the protection of the 
electronic system and its associated wiring harness. These external 
threat levels, which are lower than previous required values, are 
believed to represent the worst case to which an airplane would be 
exposed in the operating environment.
    These special conditions require qualification of systems that 
perform critical functions, as installed in aircraft, to the defined 
HIRF environment in paragraph 1 or, as an option to a fixed value using 
laboratory tests, in paragraph 2, as follows:
    (1) The applicant may demonstrate that the operation and 
operational capability of the installed electrical and electronic 
systems that perform critical functions are not adversely affected when 
the aircraft is exposed to the HIRF environment defined below:

------------------------------------------------------------------------
                                                        Field strength
                                                       (volts per meter)
                      Frequency                      -------------------
                                                        Peak     Average
------------------------------------------------------------------------
10 kHz-100 kHz......................................        50        50
100 kHz-500 kHz.....................................        50        50
500 kHz-2 MHz.......................................        50        50
2 MHz-30 MHz........................................       100       100
30 MHz-70 MHz.......................................        50        50
70 MHz-100 MHz......................................        50        50
100 MHz-200 MHz.....................................       100       100
200 MHz-400 MHz.....................................       100       100
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,


[[Page 69583]]


    (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.

Applicability

    As discussed above, these special conditions are applicable to one 
modification to the aircraft models listed under the heading ``Type 
Certification Basis.'' Should ASPEN Avionics Inc., apply at a later 
date to extend this modification to include additional airplane models, 
the special conditions would apply to that model as well under the 
provisions of Sec.  21.101.

Conclusion

    This action affects only certain novel or unusual design features 
on one modification to the aircraft models listed under the heading 
``Type Certification Basis.'' 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.

List of Subjects in 14 CFR Part 23

    Aircraft, Aviation safety, Signs and symbols.

Citation

    The authority citation for these special conditions is as follows:

    Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 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 the EFD 1000 EFIS manufactured by 
ASPEN Avionics Inc.
    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 November 30, 2007.
Patrick R. Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-23835 Filed 12-7-07; 8:45 am]
BILLING CODE 4910-13-P