Airworthiness directives: E,

[Federal Register: March 28, 2002 (Volume 67, Number 60)]

[Proposed Rules]

[Page 14884-14886]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr28mr02-16]

Proposed Rules Federal Register

This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules.

[[Page 14884]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE175] ; Notice No. 23-02-02-SC

Special Conditions: Installation of Full Authority Digital Engine Control (FADEC) System on The Lancair Company, Model LC40-550FG-E Airplane

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed special conditions.

SUMMARY: This notice proposes special conditions for The Lancair Company, Model LC40-550FG-E Airplane, which will use a FADEC System. This airplane will have a novel or unusual design feature associated with the installation of an engine that uses an electronic engine control system in place of the engine's mechanical system. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These proposed 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: Comments must be received on or before April 29, 2002.

ADDRESSES: Comments on this proposal may be mailed in duplicate to: Federal Aviation Administration, Regional Counsel, ACE-7, Attention: Rules Docket, Docket No. CE175, DOT Building, 901 Locust, Kansas City, Missouri 64106, or delivered in duplicate to the Regional Counsel at the above address. Comments must be marked: Docket No. CE175. Comments may be inspected in the Rules Docket weekdays, except Federal holidays, between 7:30 a.m. and 4:00 p.m.

FOR FURTHER INFORMATION CONTACT: Ervin Dvorak, Aerospace Engineer, Standards Office (ACE-110), Small Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone (816) 329-4123.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to participate in the making of these proposed special conditions by submitting 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 proposals described in this notice 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 filedin the docket. Persons wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must include with those comments a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket No. CE175.'' The postcard will be date stamped and returned to the commenter.

Background

On November 8, 2001, The Lancair Company applied to amend Type Certificate A0003SE for the addition of the Model LC40-550FG-E airplane. The Model LC40-550FG-E is a small, utility category airplane. The airplane is powered by one reciprocating engine equipped with an electronic engine control system with full authority capability in place of the hydromechanical control system.

Type Certification Basis

Under the provisions of 14 CFR 21.101(c), The Lancair Company must show that the Model LC40-550FG-E meets the applicable provisions of the certification basis specified in Amendment 6 to TCDS A00003SE except as follows:

FAR 23.1305 as of Amendment 52.

FAR 23.1359 as of Amendment 49.

Special conditions will be applied to the FADEC installation for protection against high intensity radiated fields (HIRF) and for installed system reliability (FAR 23.1309 applicability).

If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 23) do not contain adequate or appropriate safety standards for the Model LC40-550FG-E because of a novel or unusual design feature, special conditions are prescribed under the provisions of Sec. 21.16.

In addition to the applicable airworthiness regulations and special conditions, the Model LC40-550FG must comply with the fuel vent and exhaust emission requirements of 14 CFR part 34 and the noise certification requirements of 14 CFR part 36, and the FAA must issue a finding of regulatory adequacy pursuant to section 611 of Public Law 92-574, the ``Noise Control Act of 1972.''

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. 21.17(a)(2).

Special conditions are initially applicable to the model for which they are issued. Should the type certificate for that model be amended later to include any other model that incorporates the same novel or unusual design feature, the special conditions would also apply to the other model under the provisions of Sec. 21.101(a)(1).

Novel or Unusual Design Features

The Lancair Company, Model LC40-550FG-E Airplane will incorporate the following novel or unusual design features:

The Lancair Company, Model LC40-550FG-E Airplane will use an engine that includes an electronic control system with full engine authority 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 Lancair Company, Model LC40-550FG-E will perform critical functions, provisions for protection from the effects of HIRF

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fields 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 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, 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 full authority digital engine control 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 Lancair Company, Model LC40-550FG-E 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- 46.

Applicability

As discussed above, these special conditions are applicable to the The Lancair Company, Model LC40-550FG-E Airplane. Should The Lancair Company apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, 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 model, The Lancair Company, Model LC40-550FG-E Airplane. 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.

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 21.17; and 14 CFR 11.38 and 11.19.

The Proposed Special Conditions

Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for The Lancair Company, Model LC40-550FG-E Airplane.

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.

   (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.

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   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 23-46. 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.

   Issued in Kansas City, Missouri on February 5, 2002. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service.

   [FR Doc. 02-7503Filed3-27-02; 8:45 am]

   BILLING CODE 4910-13-P