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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

CFR Citation: 14 CFR Part 23

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

NOTICE: RULES

ACTION: Airworthiness standards:

DOCUMENT ACTION: Final special conditions; request for comments.

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

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

DOCUMENT 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.

SUMMARY: Special conditions—; ASPEN Avionics Inc. Model EFD 1000,

SUPPLEMENTAL INFORMATION

The FAA has determined that notice and opportunity for prior public comment hereon are impracticable because these procedures would significantly delay issuance of 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 2320; Sec. Sec. 23.1309, 23.1311, and 23.1321 of Amendment 2349; and Sec. 23.1322 of Amendment 2343; 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.20518/F, S.20518/ A9EU.................. FAR 23............... 1 Marchetti). R, S.20520/F, S.205
20/R, S.20522/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). 100180.
[[Page 69580]]
Aeronautica Macchi S.p.A AL 60, AL 60B, AL 60 7A12.................. CAR 3................ 1 (Macchi). F5, AL 60C5. A19EU................. FAR 23............... 1 AM3..................
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)..... A1, A1A, A1B....... A22NM................. FAR 23............... 1 S1S, S1T, S2, S2A, A8SO.................. FAR 23............... 1 S2B, S2C, S2S.
Bellanca (Alexandria Aircraft 1419, 14192, 1419 1A3................... CAR 3................ 1 LLC). 3, 14193A,1730, 17
31, 1731TC.
1730A, 1731A, 17 A18CE................. FAR 23............... 1 31ATC.
Cessna........................ 120, 140.............. A768................. 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....... A799................. 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.. A790................. 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, 2105, 2105A.
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 T303 (Crusader)...... A34CE................. FAR 23............... 2 310, 310A (USAF U3A), 3A10.................. ..................... 2 310B, 310C, 310D,
310E (USAF U3B),
310F, 310G, 310H,
E310H, 310I, 310J,
310J1, 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,
T337HSP.
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.................. CC18180, CC18180A... A00006SE.............. FAR 23............... 1 DeHavilland/Bombardier........ DHC2 Mark I, DHC2 A806................. CAR 3................ 1 Mark II, DHC2 Mark
III.
DH.C1, 21, 22, 22A.... A44EU................. FAR 21............... 1 Diamond Aircraft Company...... DA 20A1, DA20C1..... 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 EA400................
Found Aircraft Development, FBA2C, FBA2C1 (Bush A7EA.................. CAR 3, FAR 23........ 1 Inc. Hawk), FBA2C2 (Bush
Hawk XP).
Gulfstream American G44, G44A, SCAN Type A734................. CAR 4a............... 2 Corporation. 30.
GrobWerke.................... G115, G115A, G115B, A57EU................. FAR 23............... 1 G115C, G115C2, G115D,
G115D2, G115EG.
G120A................. A49CE................. FAR 23............... 1 Grumman American (Tiger AA1, AA1A, AA1B, AA A11EA................. FAR 23............... 1 Aircraft LLC). 1C. A16EA................. FAR 23............... 1 AA5, AA5A, AA5B, AG
5B.
Hawker Beechcraft............. 3533, 35A33, 35B33, 3A15.................. CAR 3................ 1 35C33, 35C33A, 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, A777................. CAR 3................ 1 D35, E35, F35, G35,
35R.
76.................... A29CE................. FAR 23............... 1 95, B95, B95A, D95A, 3A16.................. CAR 3, FAR 23........ 2 E95, 9555, 95A55,
95B55, 95B55A, 95
B55B (T42A), 95C55,
95C55A, D55, D55A,
E55, E55A, 56TC,
A56TC, 58, 58A.
19A, B19, M19A, 23, A1CE.................. CAR 3................ 1 A23, A23A, A2319,
A2324, B23, C23,
A24, A24R, B24R, C24R.
50, B50, C50, D50, 5A4................... CAR 3................ 2 D50A, D50B, D50C,
D50E, D50E5990, E50,
F50, G50, H50, J50.
45 (YT34), A45 (T 5A3................... CAR 3................ 1 34A) or (B45), D45
(T34B).
Helio (Alliance Aircraft H250, H295, HT295, 1A8................... CAR 3................ 1 Group, LLC). H391, H391B, H395, H
395A, H700, H800.
HST550, HST550A..... A4EA.................. CAR 3................ 1 500................... A2EA.................. CAR 3................ 2 King's Engineering Fellowship Model 44.............. A2WI.................. FAR 23............... 2 (The). 4500300, 4500300 A17CE................. FAR 23............... 2 Series II.
Lake/Revo (Global Amphibians Colonial C1, Colonial 1A13.................. CAR 3................ 1 LLC). C2, Lake LA4, Lake
LA4A, Lake LA4P,
Lake LA4200, Lake
Model 250.
Lancair (Columbia Aircraft)... LC40550FG, LC41 A00003SE.............. FAR 23............... 1 550FG, LC42550FG.
Liberty Aerospace Incorporated XL2.................. A00008DE.............. FAR 23............... 1 Lockheed Aircraft Corporation. 4022................. 2A11.................. CAR 3................ 2 Luscombe Aircraft Corporation. 11A, 11E.............. A804................. CAR 3................ 1 Maule......................... Bee Dee M4, M4, M 3A23.................. CAR 3................ 1 4C, M4S, M4T, M4
180C, M4180S, M4
180T, M4210, M4
210C, M4210S, M4
210T, M4220, M4
220C, M4220S, M4
220T, M5180C, M5
200, M5210C, M5
210TC, M5220C, M5
235C, M6180, M6
235, M7235, MX7
235, MX7180, MX7
420, MXT7180, MT7
235, M8235, MX7
160, MXT7160, MX7
180A, MXT7180A, MX
7180B, M7235B, M7
235A, M7235C, MX7
180C, M7260, MT7
260, M7260C, M7
420AC, MX7160C, MX
7180AC, M7420A, MT
7420.
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 Z242L, Z143L... A76EU................. FAR 23............... 1 Navion Aircraft Company, Ltd. Navion, Navion A, A782................. CAR 3................ 1 (Navion). Navion B, Navion D,
Navion E, Navion F,
Navion G, Navion H.
OMF (Ostmeck. Flugzeugbau OMF100160........... 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...... PC6, PC6H1, PC6 7A15.................. CAR 3................ 1 H2, PC6/350, PC6/
350H1, PC6/350H2,
PC6/A, PC6/AH1, PC
6/AH2, PC6/BH2, PC
6/B1H2, PC6/B2H2,
PC6/B2H4, PC6/C
H2, PC6/C1H2.
PC7.................. A50EU................. FAR 23............... 1 Piper (New Piper)............. PA12, PA12S......... A780................. CAR 3................ 1 PA18, PA18S, PA18 1A2................... CAR 3................ 1 105, PA18S105, PA
18A, PA18125, PA
18S125, PA18AS125,
PA18135, PA18A
135, PA18S135, PA
18AS135, PA18150,
PA18A150, PA18S
150, PA18AS150, PA
19, PA19S.
PA20, PA20S, PA20 1A4................... CAR 3................ 1 115, PA20S115, PA
20135, PA20S135.
PA22, PA22108, PA 1A6................... CAR 3................ 1 22135, PA22S135,
PA22150, PA22S
150, PA22160, PA
22S160.
PA23, PA23160, PA 1A10.................. CAR 3................ 2 23235, PA23250.
PA24, PA24250 PA24 1A15.................. CAR 3................ 1 260, PA24400.
PA28140, PA28150, 2A13.................. CAR 3................ 1 PA28151, PA28160,
PA28161, PA28180,
PA28235, PA28S
160, PA28161, PA28
181, PA28235, PA
28S160, PA28R201,
PA28R201T, PA28RT
201, PA28RT201T, PA
28201T, PA28236.
PA30, PA39, PA40... A1EA.................. CAR 3................ 2 PA32260, PA32300, A3SO.................. CAR 3................ 1 PA32S300, PA32R
300, PA32RT300, PA
32RT300T, PA32R
301(SP), PA32R
301(HP), PA32R301T,
PA32301, PA32
301T, PA32301FT,
PA32301XTC.
PA34200, PA34200T, A7SO.................. CAR 3................ 2 PA34220T.
[[Page 69582]]
PA44180, PA44180T. A19SO................. FAR 23............... 1 PA46310P, PA46 A25SO................. FAR 23............... 1 350P, PA46500TP.
PropJets, Inc................ 200, 200A, 200B, 200C, 3A18.................. CAR 3................ 1 200D, 400.
PZL (Panstwowe Zaklady PZL104 WILGA 80, PZL A55EU................. FAR 23............... 1 Lotnicze). 104M WILGA 2000, PZL A69EU................. FAR 23............... 1 WARSZAWA.
PZLKOLIBER 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, T67M260T3A.. 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, MS892A150,
MS892E150, MS893E,
MS894E.
SOCATA (SOCATA Groupe GA7 (Cougar)......... A17SO................. FAR 23............... 2 Aerospatiale).
Stinson (Univair Aircraft 108, 1081, 1082, 108 A767................. CAR 3................ 1 Corporation). 3, 1085.
Twin Commander Aircraft 500, 500A, 500B, 500 ATC 542............... CAR 3................ 1 Corporation. U, 500S, 520, 560,
560A, 560E.
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 cockpitinstalled 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 kHz100 kHz...................................... 50 50 100 kHz500 kHz..................................... 50 50 500 kHz2 MHz....................................... 50 50 2 MHz30 MHz........................................ 100 100 30 MHz70 MHz....................................... 50 50 70 MHz100 MHz...................................... 50 50 100 MHz200 MHz..................................... 100 100 200 MHz400 MHz..................................... 100 100 400 MHz700 MHz..................................... 700 50 700 MHz1 GHz....................................... 700 100 1 GHz2 GHz......................................... 2000 200 2 GHz4 GHz......................................... 3000 200 4 GHz6 GHz......................................... 3000 200 6 GHz8 GHz......................................... 1000 200 8 GHz12 GHz........................................ 3000 300 12 GHz18 GHz....................................... 2000 200 18 GHz40 GHz....................................... 600 200 The field strengths are expressed in terms of peak rootmeansquare (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 noncritical 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. E723835 Filed 12707; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Jim Brady, Aerospace Engineer, Standards Office (ACE111), Small Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone (816) 3294132.