Special Conditions: Societe de Motorisation Aeronautiques (SMA) Engines, Cessna Models 182Q and 182R: Installation of Model SR305-230 Aircraft Diesel Engine for Full Authority Digital Engine Control (FADEC) System and the Protection of the System From the Effects of High Intensity Radiated Fields (HIRF), 34517-34519 [E6-9241]

Download as PDF Federal Register / Vol. 71, No. 115 / Thursday, June 15, 2006 / Rules and Regulations employer or the recruiter or referrer, must attest to the required information in Form I–9. The system used to capture the electronic signature should include a method to acknowledge that the attestation to be signed has been read by the signatory. Any person or entity who has failed to comply with the criteria established by this regulation for electronic signatures, if used, and at the time of inspection does not present a properly completed Form I–9 for the employee, is in violation of section 274A(a)(1)(B) of the Act and 8 CFR 274a.2(b)(2). Dated: June 8, 2006. Michael Chertoff, Secretary. [FR Doc. E6–9283 Filed 6–14–06; 8:45 am] DEPARTMENT OF AGRICULTURE Animal and Plant Health Inspection Service [Docket No. APHIS–2006–0020] States Approved To Receive Stallions and Mares From CEM-Affected Regions; Indiana Animal and Plant Health Inspection Service, USDA. ACTION: Direct final rule; confirmation of effective date. AGENCY: cprice-sewell on PROD1PC66 with RULES DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. CE249; Special Conditions No. 23–189–SC] Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. AGENCY: 9 CFR Part 93 SUMMARY: On April 27, 2006, the Animal and Plant Health Inspection Service published a direct final rule. (See 71 FR 24806–24808.) The direct final rule notified the public of our intention to amend the animal importation regulations by adding Indiana to the lists of States approved to receive certain stallions and mares imported into the United States from regions affected with contagious equine metritis. We did not receive any written adverse comments regarding the addition of Indiana to those lists or written notice of intent to submit adverse comments in response to the direct final rule. DATES: Effective Date: The effective date of the direct final rule is confirmed as June 26, 2006. FOR FURTHER INFORMATION CONTACT: Dr. Freeda E. Isaac, Senior Staff Veterinarian, National Center for Import and Export, VS, APHIS, 4700 River Road Unit 39, Riverdale, MD 20737– 1231; (301) 734–8364. Authority: 7 U.S.C. 1622 and 8301–8317; 21 U.S.C. 136 and 136a; 31 U.S.C. 9701; 7 CFR 2.22, 2.80, and 371.4. 14:45 Jun 14, 2006 BILLING CODE 3410–34–P Special Conditions: Societe de Motorisation Aeronautiques (SMA) Engines, Cessna Models 182Q and 182R: Installation of Model SR305–230 Aircraft Diesel Engine for Full Authority Digital Engine Control (FADEC) System and the Protection of the System From the Effects of High Intensity Radiated Fields (HIRF) BILLING CODE 4410–10–P VerDate Aug<31>2005 Done in Washington, DC, this 9th day of June 2006. Kevin Shea, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. E6–9350 Filed 6–14–06; 8:45 am] Jkt 208001 SUMMARY: This proposes special conditions for the Cessna Models 182Q and 182R airplanes with a Societe de Motorisation Aeronautiques (SMA) Model SR305–230 aircraft diesel engine (ADE). The supplemental type certificate for these airplanes will have a novel or unusual design feature associated with the installation of an aircraft diesel engine that uses an electronic engine control system instead of a mechanical control system. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. DATES: The effective date of these special conditions is June 7, 2006. Comments must be received on or before July 17, 2006. ADDRESSES: Comments on the special conditions may be mailed in duplicate to: Federal Aviation Administration (FAA), Regional Counsel, ACE–7, Attention: Rules Docket, Docket No. CE249, 901 Locust, Room 506, Kansas City, Missouri 64106, or delivered in duplicate to the Regional Counsel at the above address. Comments must be marked: Docket No. CE249. Comments may be inspected in the Rules Docket PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 34517 weekdays, except Federal holidays, between 7:30 a.m. and 4 p.m. FOR FURTHER INFORMATION CONTACT: Peter L. Rouse, Federal Aviation Administration, Aircraft Certification Service, Small Airplane Directorate, ACE–111, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: 816–329–4135, fax: 816–329–4090. The FAA has determined that notice and opportunity for prior public comment hereon are impracticable because these procedures would significantly delay issuance of the design approval and thus delivery of the affected aircraft. In addition, the substance of these special conditions has been subject to the public comment process in several prior instances with no substantive comments received. The FAA, therefore, finds that good cause exists for making these special conditions effective upon issuance. SUPPLEMENTARY INFORMATION: Comments Invited Interested persons are invited to submit such written data, views, or arguments as they may desire. Communications should identify the regulatory docket or special condition 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. CE249.’’ The postcard will be date stamped and returned to the commenter. Background On March 19, 2004, the Societe de Motorisation Aeronautiques Engines, Inc. applied for Supplemental Type Certification of Cessna Models 182Q and 182R airplanes for the installation of an SMA Model SR305–230. The airplane is powered by a SMA Model SR305–230 that is equipped with an electronic engine control system with full authority capability in these airplanes. E:\FR\FM\15JNR1.SGM 15JNR1 34518 Federal Register / Vol. 71, No. 115 / Thursday, June 15, 2006 / Rules and Regulations Type Certification Basis Under the provisions of 14 CFR 21.101, SMA Engines, Inc., must show that the Cessna Models 182Q and 182R airplanes, with the installation of an SMA Model SR305–230, meets the applicable provisions of part 14 CFR part 23, as amended by Amendments 23–1 through 23–51 and Civil Air Regulations (CAR) 3 thereto. If the Administrator finds that the applicable airworthiness regulations (i.e., CAR 3; 14 CFR, part 23) do not contain adequate or appropriate safety standards for the Cessna Models 182Q and 182R airplanes because of a novel or unusual design feature, 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, and become part of the certification basis for the supplemental type certification basis in accordance with § 21.101. Special conditions are initially applicable to the model for which they are issued. Should the applicant apply for a supplemental type certificate to modify any other models that are listed on the same type certificate to incorporate the same novel or unusual design features, the special conditions would also apply under the provisions of § 21.101. cprice-sewell on PROD1PC66 with RULES Novel or Unusual Design Features The SMA Engines, Inc. modified Cessna Models 182Q and 182R airplanes will incorporate a novel or unusual design feature, an engine that includes an electronic control system with Full Authority Digital Engine control (FADEC) capability. Many advanced electronic systems are prone to either upsets or damage, or both, at energy levels lower than analog systems. The increasing use of high power radio frequency emitters mandates requirements for improved High Intensity Radiated Fields (HIRF) protection for electrical and electronic equipment. Since the electronic engine control system used on the SMA Engines, Inc., modified Cessna Models 182Q and 182R airplanes will perform critical functions, provisions for protection from the effects of HIRF should be considered and, if necessary, incorporated into the airplane design data. The FAA policy contained in Notice 8110.71, dated April 2, 1998, establishes the HIRF energy levels that airplanes will be exposed to in service. The guidelines set forth in this notice are the result of an Aircraft Certification Service review of existing policy on HIRF, in light of the ongoing work of the Aviation Rulemaking Advisory VerDate Aug<31>2005 14:45 Jun 14, 2006 Jkt 208001 Committee (ARAC) Electromagnetic Effects Harmonization Working Group (EEHWG). The EEHWG adopted a set of HIRF environment levels in November 1997 that were agreed upon by the FAA, the Joint Aviation Authorities (JAA), and industry participants. As a result, the HIRF environments in this notice reflect the environment levels recommended by this working group. This notice states that a FADEC is an example of a system that should address the HIRF environments. Even though the control system will be certificated as part of the engine, the installation of an engine with an electronic control system requires evaluation due to the possible effects on or by other airplane systems (e.g., radio interference with other airplane electronic systems, shared engine and airplane power sources). The regulatory requirements in 14 CFR part 23 for evaluating the installation of complex systems, including electronic systems, are contained in § 23.1309. However, when § 23.1309 was developed, the use of electronic control systems for engines was not envisioned; therefore, the § 23.1309 requirements were not applicable to systems certificated as part of the engine (reference § 23.1309(f)(1)). Also, electronic control systems often require inputs from airplane data and power sources and outputs to other airplane systems (e.g., automated cockpit powerplant controls such as mixture setting). Although the parts of the system that are not certificated with the engine could be evaluated using the criteria of § 23.1309, the integral nature of systems such as these makes it unfeasible to evaluate the airplane portion of the system without including the engine portion of the system. However, § 23.1309(f)(1) again prevents complete evaluation of the installed airplane system since evaluation of the engine system’s effects is not required. Therefore, special conditions are proposed for the SMA Engines, Inc., modified Cessna Models 182Q and 182R airplanes to provide HIRF protection and to evaluate the installation of the electronic engine control system for compliance with the requirements of § 23.1309(a) through (e) at Amendment 23–49. Applicability As discussed above, these special conditions are applicable to the SMA Engines, Inc., modified Cessna Models 182Q and 182R airplanes. Should SMA Engines, Inc., apply at a later date for a supplemental type certificate to modify any other model included on the same type certificate as the SMA Engines, Inc., modified Cessna Models 182Q and PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 182R airplanes to incorporate the same novel or unusual design features, the special conditions would apply to that model as well under the provisions of § 21.101. Conclusion This action affects only certain novel or unusual design features on SMA Engines, Inc., modified Cessna Models 182Q and 182R airplanes. It is not a rule of general applicability, and it affects only the applicant who applied to the FAA for approval of these features on the airplane. Under standard practice, the effective date of final special conditions would be 30 days after the date of publication in the Federal Register. However, as the certification date for the SMA Engines, Inc., modified Cessna Models 182Q and 182R is imminent, the FAA finds that good cause exists to make these special conditions effective upon issuance. 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 supplemental type certification basis for SMA Engines, Inc., modified Cessna Models 182Q and 182R airplanes. 1. High Intensity Radiated Fields (HIRF) Protection. In showing compliance with 14 CFR part 21 and the airworthiness requirements of 14 CFR part 23, protection against hazards caused by exposure to HIRF fields for the full authority digital engine control system, which performs critical functions, must be considered. To prevent this occurrence, the electronic engine control system must be designed and installed to ensure that the operation and operational capabilities of this critical system are not adversely affected when the airplane is exposed to high energy radio fields. At this time, the FAA and other airworthiness authorities are unable to precisely define or control the HIRF energy level to which the airplane will be exposed in service; therefore, the FAA hereby defines two acceptable interim methods for complying with the requirement for protection of systems that perform critical functions. E:\FR\FM\15JNR1.SGM 15JNR1 Federal Register / Vol. 71, No. 115 / Thursday, June 15, 2006 / Rules and Regulations (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 external HIRF threat environment defined in the following table: 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 50 100 200 200 200 200 300 200 200 cprice-sewell on PROD1PC66 with RULES The field strengths are expressed in terms of peak root-mean-square (rms) values. or, (2) The applicant may demonstrate by a system test and analysis that the electrical and electronic systems that perform critical functions can withstand a minimum threat of 100 volts per meter peak electrical strength, without the benefit of airplane structural shielding, in the frequency range of 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. Data used for engine certification may be used, when appropriate, for airplane certification. 2. Electronic Engine Control System. The installation of the electronic engine control system must comply with the requirements of § 23.1309(a) through (e) at Amendment 23–49. The intent of this requirement is not to re-evaluate the inherent hardware reliability of the control itself, but rather determine the effects, including environmental effects addressed in § 23.1309(e), on the airplane systems and engine control system when installing the control on the airplane. When appropriate, engine certification data may be used when showing compliance with this requirement. With respect to compliance with § 23.1309(e), the levels required for compliance shall be at the levels for catastrophic failure conditions. VerDate Aug<31>2005 14:45 Jun 14, 2006 Jkt 208001 BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES Average 50 50 50 100 50 50 100 100 700 700 2000 3000 3000 1000 3000 2000 600 Issued in Kansas City, Missouri on June 7, 2006. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–9241 Filed 6–14–06; 8:45 am] Food and Drug Administration 34519 per ton’’ column, in the entry for use of lasalocid at 30 to 600 grams per ton in combination with chlortetracycline at 500 to 4000 grams per ton, by removing the second paragraph designation ‘‘(xxiii)’’ and by adding in its place the paragraph designation ‘‘(xxviii)’’. Dated: June 1, 2006. Stephen F. Sundlof, Director, Center for Veterinary Medicine. [FR Doc. E6–9321 Filed 6–14–06; 8:45 am] BILLING CODE 4160–01–S 21 CFR Part 558 New Animal Drugs for Use in Animal Feeds; Lasalocid; Correction AGENCY: HHS. [Public Notice 5362] Final rule; correcting amendments. SUMMARY: The Food and Drug Administration (FDA) is correcting a document amending the animal drug regulations to reflect approval of an original new animal drug application (NADA) that appeared in the Federal Register of April 27, 2006 (71 FR 24814). FDA is correcting a paragraph designation in the table for lasalocid cattle feeds which was drafted in error. This correction is being made to improve the accuracy of the animal drug regulations. DATES: This rule is effective June 15, 2006. FOR FURTHER INFORMATION CONTACT: George K. Haibel, Center for Veterinary Medicine (HFV–6), Food and Drug Administration, 7519 Standish Pl., Rockville, MD 20855, 240–276–9019, email: george.haibel@fda.hhs.gov. SUPPLEMENTARY INFORMATION: For the reasons set forth in the preamble, FDA is correcting 21 CFR part 558 to read as follows: List of Subjects in 21 CFR Part 558 Animal drugs, Animal feeds. I Therefore, under the Federal Food, Drug, and Cosmetic Act and under authority delegated to the Commissioner of Food and Drugs and redelegated to the Center for Veterinary Medicine, 21 CFR part 558 is amended as follows: PART 558—NEW ANIMAL DRUGS FOR USE IN ANIMAL FEEDS 1. The authority citation for 21 CFR part 558 continues to read as follows: I Authority: 21 U.S.C. 360b, 371. [Amended] 2. Section 558.311 is corrected in the table in the ‘‘Lasalocid sodium in grams I PO 00000 22 CFR Parts 40, 41, and 42 Food and Drug Administration, ACTION: § 558.311 DEPARTMENT OF STATE Frm 00013 Fmt 4700 Sfmt 4700 Nomenclature Changes Reflecting Creation of Department of Homeland Security State Department. Final rule. AGENCY: ACTION: SUMMARY: This rule makes technical nomenclature changes to Title 22 Code of Federal Regulations (CFR) parts 40, 41, and 42 to properly reflect the creation of the Department of Homeland Security (DHS) and its assumption of the functions of the former Immigration and Naturalization Service (INS). This rule also reflects changes to form numbers on various visa-related forms. Because the amendments are entirely technical, the State Department is not providing an opportunity for public comment under the Administrative Procedure Act ‘‘good cause’’ exemption. DATES: Effective Date: This rule is effective June 15, 2006. Persons with access to the internet may view this notice by going to the regulations.gov Web site at: http:// www.regulations.gov/index.cfm. FOR FURTHER INFORMATION CONTACT: Barbara J. Kennedy, Legislation and Regulations Division, Visa Services, U.S. Department of State, 2401 E Street, NW., Room L–603, Washington, DC 20520–0106; telephone 202–663–1206 or e-mail KennedyBJ@state.gov. SUPPLEMENTARY INFORMATION: Why is the Department Promulgating This Rule? On March 1, 2003, the INS’s functions were transferred to the newly created Department of Homeland Security (DHS). The reorganization was required by the Homeland Security Act of 2002, Public Law No. 107–296 section 1502. This final rule includes the changes that reflect the transfer. E:\FR\FM\15JNR1.SGM 15JNR1

Agencies

[Federal Register Volume 71, Number 115 (Thursday, June 15, 2006)]
[Rules and Regulations]
[Pages 34517-34519]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-9241]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE249; Special Conditions No. 23-189-SC]


Special Conditions: Societe de Motorisation Aeronautiques (SMA) 
Engines, Cessna Models 182Q and 182R: Installation of Model SR305-230 
Aircraft Diesel Engine for Full Authority Digital Engine Control 
(FADEC) System and the Protection of the System From the Effects of 
High Intensity Radiated Fields (HIRF)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

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

SUMMARY: This proposes special conditions for the Cessna Models 182Q 
and 182R airplanes with a Societe de Motorisation Aeronautiques (SMA) 
Model SR305-230 aircraft diesel engine (ADE). The supplemental type 
certificate for these airplanes will have a novel or unusual design 
feature associated with the installation of an aircraft diesel engine 
that uses an electronic engine control system instead of a mechanical 
control system. The applicable airworthiness regulations do not contain 
adequate or appropriate safety standards for this design feature. These 
special conditions contain the additional safety standards that the 
Administrator considers necessary to establish a level of safety 
equivalent to that established by the existing airworthiness standards.

DATES: The effective date of these special conditions is June 7, 2006. 
Comments must be received on or before July 17, 2006.

ADDRESSES: Comments on the special conditions may be mailed in 
duplicate to: Federal Aviation Administration (FAA), Regional Counsel, 
ACE-7, Attention: Rules Docket, Docket No. CE249, 901 Locust, Room 506, 
Kansas City, Missouri 64106, or delivered in duplicate to the Regional 
Counsel at the above address. Comments must be marked: Docket No. 
CE249. 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: Peter L. Rouse, Federal Aviation 
Administration, Aircraft Certification Service, Small Airplane 
Directorate, ACE-111, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: 816-329-4135, fax: 816-329-4090.

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 design 
approval and thus delivery of the affected aircraft. In addition, the 
substance of these special conditions has been subject to the public 
comment process in several prior instances with no substantive comments 
received. The FAA, therefore, finds that good cause exists for making 
these special conditions effective upon issuance.

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 special condition 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. CE249.'' The postcard will be date stamped and 
returned to the commenter.

Background

    On March 19, 2004, the Societe de Motorisation Aeronautiques 
Engines, Inc. applied for Supplemental Type Certification of Cessna 
Models 182Q and 182R airplanes for the installation of an SMA Model 
SR305-230. The airplane is powered by a SMA Model SR305-230 that is 
equipped with an electronic engine control system with full authority 
capability in these airplanes.

[[Page 34518]]

Type Certification Basis

    Under the provisions of 14 CFR 21.101, SMA Engines, Inc., must show 
that the Cessna Models 182Q and 182R airplanes, with the installation 
of an SMA Model SR305-230, meets the applicable provisions of part 14 
CFR part 23, as amended by Amendments 23-1 through 23-51 and Civil Air 
Regulations (CAR) 3 thereto.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., CAR 3; 14 CFR, part 23) do not contain adequate or 
appropriate safety standards for the Cessna Models 182Q and 182R 
airplanes because of a novel or unusual design feature, 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, and become part of the 
certification basis for the supplemental type certification basis in 
accordance with Sec.  21.101. Special conditions are initially 
applicable to the model for which they are issued. Should the applicant 
apply for a supplemental type certificate to modify any other models 
that are listed on the same type certificate to incorporate the same 
novel or unusual design features, the special conditions would also 
apply under the provisions of Sec.  21.101.

Novel or Unusual Design Features

    The SMA Engines, Inc. modified Cessna Models 182Q and 182R 
airplanes will incorporate a novel or unusual design feature, an engine 
that includes an electronic control system with Full Authority Digital 
Engine control (FADEC) capability.
    Many advanced electronic systems are prone to either upsets or 
damage, or both, at energy levels lower than analog systems. The 
increasing use of high power radio frequency emitters mandates 
requirements for improved High Intensity Radiated Fields (HIRF) 
protection for electrical and electronic equipment. Since the 
electronic engine control system used on the SMA Engines, Inc., 
modified Cessna Models 182Q and 182R airplanes will perform critical 
functions, provisions for protection from the effects of HIRF should be 
considered and, if necessary, incorporated into the airplane design 
data. The FAA policy contained in Notice 8110.71, dated April 2, 1998, 
establishes the HIRF energy levels that airplanes will be exposed to in 
service. The guidelines set forth in this notice are the result of an 
Aircraft Certification Service review of existing policy on HIRF, in 
light of the ongoing work of the Aviation Rulemaking Advisory Committee 
(ARAC) Electromagnetic Effects Harmonization Working Group (EEHWG). The 
EEHWG adopted a set of HIRF environment levels in November 1997 that 
were agreed upon by the FAA, the Joint Aviation Authorities (JAA), and 
industry participants. As a result, the HIRF environments in this 
notice reflect the environment levels recommended by this working 
group. This notice states that a FADEC is an example of a system that 
should address the HIRF environments.
    Even though the control system will be certificated as part of the 
engine, the installation of an engine with an electronic control system 
requires evaluation due to the possible effects on or by other airplane 
systems (e.g., radio interference with other airplane electronic 
systems, shared engine and airplane power sources). The regulatory 
requirements in 14 CFR part 23 for evaluating the installation of 
complex systems, including electronic systems, are contained in Sec.  
23.1309. However, when Sec.  23.1309 was developed, the use of 
electronic control systems for engines was not envisioned; therefore, 
the Sec.  23.1309 requirements were not applicable to systems 
certificated as part of the engine (reference Sec.  23.1309(f)(1)). 
Also, electronic control systems often require inputs from airplane 
data and power sources and outputs to other airplane systems (e.g., 
automated cockpit powerplant controls such as mixture setting). 
Although the parts of the system that are not certificated with the 
engine could be evaluated using the criteria of Sec.  23.1309, the 
integral nature of systems such as these makes it unfeasible to 
evaluate the airplane portion of the system without including the 
engine portion of the system. However, Sec.  23.1309(f)(1) again 
prevents complete evaluation of the installed airplane system since 
evaluation of the engine system's effects is not required.
    Therefore, special conditions are proposed for the SMA Engines, 
Inc., modified Cessna Models 182Q and 182R airplanes to provide HIRF 
protection and to evaluate the installation of the electronic engine 
control system for compliance with the requirements of Sec.  23.1309(a) 
through (e) at Amendment 23-49.

Applicability

    As discussed above, these special conditions are applicable to the 
SMA Engines, Inc., modified Cessna Models 182Q and 182R airplanes. 
Should SMA Engines, Inc., apply at a later date for a supplemental type 
certificate to modify any other model included on the same type 
certificate as the SMA Engines, Inc., modified Cessna Models 182Q and 
182R airplanes to incorporate the same novel or unusual design 
features, 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 SMA Engines, Inc., modified Cessna Models 182Q and 182R airplanes. 
It is not a rule of general applicability, and it affects only the 
applicant who applied to the FAA for approval of these features on the 
airplane.
    Under standard practice, the effective date of final special 
conditions would be 30 days after the date of publication in the 
Federal Register. However, as the certification date for the SMA 
Engines, Inc., modified Cessna Models 182Q and 182R is imminent, the 
FAA finds that good cause exists to make these special conditions 
effective upon issuance.

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 supplemental type certification basis for SMA Engines, Inc., 
modified Cessna Models 182Q and 182R airplanes.
    1. High Intensity Radiated Fields (HIRF) Protection. In showing 
compliance with 14 CFR part 21 and the airworthiness requirements of 14 
CFR part 23, protection against hazards caused by exposure to HIRF 
fields for the full authority digital engine control system, which 
performs critical functions, must be considered. To prevent this 
occurrence, the electronic engine control system must be designed and 
installed to ensure that the operation and operational capabilities of 
this critical system are not adversely affected when the airplane is 
exposed to high energy radio fields.
    At this time, the FAA and other airworthiness authorities are 
unable to precisely define or control the HIRF energy level to which 
the airplane will be exposed in service; therefore, the FAA hereby 
defines two acceptable interim methods for complying with the 
requirement for protection of systems that perform critical functions.

[[Page 34519]]

    (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 external HIRF threat environment defined 
in the following table:

------------------------------------------------------------------------
                                                       Field strength
                                                      (volts per meter)
                     Frequency                     ---------------------
                                                       Peak     Average
------------------------------------------------------------------------
10 kHz-100 kHz....................................         50         50
100 kHz-500 kHz...................................         50         50
500 kHz-2 MHz.....................................         50         50
2 MHz-30 MHz......................................        100        100
30 MHz-70 MHz.....................................         50         50
70 MHz-100 MHz....................................         50         50
100 MHz-200 MHz...................................        100        100
200 MHz-400 MHz...................................        100        100
400 MHz-700 MHz...................................        700         50
700 MHz-1 GHz.....................................        700        100
1 GHz-2 GHz.......................................       2000        200
2 GHz-4 GHz.......................................       3000        200
4 GHz-6 GHz.......................................       3000        200
6 GHz-8 GHz.......................................       1000        200
8 GHz-12 GHz......................................       3000        300
12 GHz-18 GHz.....................................       2000        200
18 GHz-40 GHz.....................................        600        200
------------------------------------------------------------------------
 The field strengths are expressed in terms of peak root-mean-square
  (rms) values.

or,
    (2) The applicant may demonstrate by a system test and analysis 
that the electrical and electronic systems that perform critical 
functions can withstand a minimum threat of 100 volts per meter peak 
electrical strength, without the benefit of airplane structural 
shielding, in the frequency range of 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. Data used for engine 
certification may be used, when appropriate, for airplane 
certification.
    2. Electronic Engine Control System. The installation of the 
electronic engine control system must comply with the requirements of 
Sec.  23.1309(a) through (e) at Amendment 23-49. The intent of this 
requirement is not to re-evaluate the inherent hardware reliability of 
the control itself, but rather determine the effects, including 
environmental effects addressed in Sec.  23.1309(e), on the airplane 
systems and engine control system when installing the control on the 
airplane. When appropriate, engine certification data may be used when 
showing compliance with this requirement.
    With respect to compliance with Sec.  23.1309(e), the levels 
required for compliance shall be at the levels for catastrophic failure 
conditions.

    Issued in Kansas City, Missouri on June 7, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-9241 Filed 6-14-06; 8:45 am]
BILLING CODE 4910-13-P