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CFR Citation: 14 CFR Part 25

Docket ID: [Docket No. NM280; Special Conditions No. 25-264-SC]

NOTICE: RULES

ACTION: Airworthiness standards:

DOCUMENT ACTION: Final special conditions; request for comments.

SUBJECT CATEGORY: Special Conditions: Raytheon Aircraft MU-300 Airplanes; High Intensity Radiated Fields (HIRF)

DATES: The effective date of these special conditions is June 3, 2004. Comments must be received on or before July 14, 2004.

DOCUMENT SUMMARY: These special conditions are issued for Raytheon Aircraft Company Model MU300 airplanes modified by Elliott Aviation Technical Products Development, Inc. These airplanes will have novel and unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. The modification incorporates the installation of a Honeywell AZ252 Advanced Air Data Computer and optional BA250 and AM250 Altimeters. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for the protection of these systems from the effects of highintensityradiated fields (HIRF). 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.

SUMMARY: Raytheon Aircraft Co. Model MU-300 airplanes,

SUPPLEMENTAL INFORMATION

The FAA has determined that notice and opportunity for prior public comment hereon is unnecessary as 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; however, we invite interested persons to participate in this rulemaking by submitting written comments, data, or views. The most helpful comments reference a specific portion of the special conditions, explain the reason for any recommended change, and include supporting data. We ask that you send us two copies of written comments.

We will file in the docket all comments we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning these special conditions. The docket is available for public inspection before and after the comment closing date. If you wish to review the docket in person, go to the address in the ADDRESSES section of this preamble between 7:30 a.m. and 4:00 p.m. Monday through Friday, except Federal holidays.

We will consider all comments we receive on or before the closing date for comments. We will consider comments filed late if it is possible to do so without incurring expense or delay. We may change these special conditions in light of the comments received.

If you want the FAA to acknowledge receipt of your comments on these special conditions, include with your comments a preaddressed, stamped postcard on which the docket number appears. We will stamp the date on the postcard and mail it back to you.

Background

On March 22, 2004, Elliott Aviation Technical Products Development, Inc., Quad City Airport, P.O. Box 100, Moline, Illinois 612660100, applied for a supplemental type certificate (STC) to modify Raytheon Aircraft Company Models MU300 (Diamond I and IA) airplanes. The Raytheon MU300 airplanes are small transport category airplanes powered by two turbojet engines, with maximum takeoff weights of up to 14,630 pounds. These airplanes operate with a 2pilot crew and can seat up to 9 passengers. The proposed modification incorporates the installation of a Honeywell AZ252 Advanced Air Data Computer with optional pilot's BA250 Altimeter and Copilot's AM250 Altimeter. The information this equipment presents is flight critical. The avionics/ electronics and electrical systems to be installed on these airplanes have the potential to be vulnerable to highintensity radiated fields (HIRF) external to the airplane.

Type Certification Basis

Under the provisions of 14 CFR 21.101, Elliott Aviation must show that the Raytheon Aircraft Company Model MU300 airplanes, as changed, continue to meet the applicable provisions of the regulations incorporated by reference in Type Certificate No. A14SW, 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.''

The regulations incorporated by reference in Type Certificate No. A14SW include 14 CFR part 25, as amended by Amendments 251 through 25 40; Sec. Sec. 25.1351(d), 25.1353(c)(5), and 25.1450, as amended by Amendment 2541; Sec. Sec. 25.1353(c)(6), and 25.255, as amended by Amendment 2542; Sec. 25.361(b) as amended by Amendment 2546; and 14 CFR part 36 as amended by Amendment 361 through 3612.

If the Administrator finds that the applicable airworthiness regulations (i.e., part 25, as amended) do not contain adequate or appropriate safety standards for modified Model MU300 airplanes, 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 Raytheon Model MU300 airplanes 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.

Special conditions, as defined in 14 CFR 11.19, are issued in accordance with Sec. 11.38, and become part of the type certification basis in accordance with Sec. 21.101.

Special conditions are initially applicable to the model for which they are issued. Should Elliott Aviation apply at a later date for supplemental type certificate to modify any other model included on the same type certificate to incorporate the same novel or unusual design feature, these special conditions would also apply to the other model under the provisions of Sec. 21.101.

Novel or Unusual Design Features

The modified Model MU300 airplanes will incorporate avionics/ electrical systems that will perform critical functions. These systems may be vulnerable to HIRF external to the airplane.

Discussion

There is no specific regulation that addresses protection requirements for electrical and electronic systems from HIRF. Increased power levels from groundbased radio transmitters and the growing use of sensitive avionics/electrical and electronic systems to command and control airplanes have made it necessary to provide adequate protection.

To ensure that a level of safety is achieved equivalent to that intended by the regulations incorporated by reference, special conditions are needed for the Model MU300 airplanes. These special conditions require that new avionics/electronics and electrical systems that perform critical functions be designed and installed to preclude component damage and interruption of function due to both the direct and indirect effects of HIRF.

HighIntensity Radiated Fields (HIRF)

With the trend toward increased power levels from groundbased transmitters, plus the advent of space and satellite communications, coupled with electronic command and control of the airplane, the immunity of critical digital avionics/electronics and electrical systems to HIRF must be established.

It is not possible to precisely define the HIRF to which the airplane will be exposed in service. There is also uncertainty concerning the effectiveness of airframe shielding for HIRF. Furthermore, coupling of electromagnetic energy to cockpitinstalled equipment through the cockpit window apertures is undefined. Based on surveys and analysis of existing HIRF emitters, an adequate level of protection exists when compliance is shown with either HIRF protection special condition paragraph 1 or 2 below:

1. A minimum threat of 100 volts rms (rootmeansquare) per meter electric field strength from 10 KHz to 18 GHz.

a. The threat must be applied to the system elements and their associated wiring harnesses without the benefit of airframe shielding. [[Page 32851]]

b. Demonstration of this level of protection is established through system tests and analysis.

2. A threat external to the airframe of the field strengths indicated in the following table for the frequency ranges indicated. Both peak and average field strength components from the table are to be demonstrated.
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 of the rootmean square (rms) over the complete modulation period.

The threat levels identified above are the result of an FAA review of existing studies on the subject of HIRF, in light of the ongoing work of the Electromagnetic Effects Harmonization Working Group of the Aviation Rulemaking Advisory Committee.

Applicability

As discussed above, these special conditions are applicable to the Raytheon Aircraft Company Model MU300 airplanes. Should Elliott Aviation Technical Products Development, Inc. apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, these special conditions would apply to that model as well under the provisions of 14 CFR 21.101.

Conclusion

This action affects only certain novel or unusual design features on the Raytheon Aircraft Company Model MU300 airplanes. It is not a rule of general applicability and affects only the applicant who applied to the FAA for approval of these features on the airplanes.

The substance of the special conditions for these airplanes has been subjected to the notice and comment procedure in several prior instances and has been derived without substantive change from those previously issued. 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 immediately. 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 25

Aircraft, Aviation safety, Reporting and recordkeeping requirements.
The authority citation for these special conditions is as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. 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 Raytheon Aircraft Company Model MU300 airplanes modified by Elliott Aviation Technical Products Development, Inc.

1. Protection from Unwanted Effects of HighIntensity Radiated Fields (HIRF). Each electrical and electronic system that performs critical functions must be designed and installed to ensure that the operation and operational capability of these systems to perform critical functions are not adversely affected when the airplane is exposed to high intensity radiated fields.

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 Renton, Washington, on June 3, 2004.
Franklin Tiangsing,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 0413306 Filed 61004; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Greg Dunn, FAA, Airplane and Flight Crew
[[Page 32850]]
Interface Branch, ANM111, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington, 98055 4056; telephone (425) 2272799; facsimile (425) 2271149.