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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

CFR Citation: 14 CFR Part 23

Docket ID: [Docket No. CE251, Special Condition 23-191-SC]

NOTICE: RULES

ACTION: Airworthiness standards:

DOCUMENT ACTION: Final special conditions; request for comments.

SUBJECT CATEGORY: Special Conditions; Rickenbacker Avionics, EFS-50 EFIS Installation in Rockwell Twin Commander Model 690B; Protection of Systems From High Intensity Radiated Fields (HIRF)

DATES: The effective date of these special conditions is June 12, 2006. Comments must be received on or before July 21, 2006.

DOCUMENT SUMMARY: These special conditions are issued to Rickenbacker Avionics, 2820 Bobmeyer Road, Hangar C6, Hamilton, OH 45015, for a Supplemental Type Certificate for the Rockwell Twin Commander Model 690B airplane. This airplane will have novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. This novel and unusual design feature will include the installation of a twotube Bendix/King EFS50 Electronic Flight Instrument System (EFIS). The installation also includes components associated with this display system. 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 that established by the existing the [[Page 35501]]
airworthiness standards applicable to these airplanes.

SUMMARY: Special conditions—; Rickenbacker Avionics; Rockwell Twin Commander Model 690B airplanes,

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. CE251.'' The postcard will be date stamped and returned to the commenter.

Background

In early October 2005, Rickenbacker Avionics made an application to the FAA for a new Supplemental Type Certificate for the Rockwell Twin Commander 690B, which is currently approved under Type Certificate No. 2A4. The proposed modification incorporates novel or unusual design features that are vulnerable to HIRF external to the airplane. Type Certification Basis

Under the provisions of 14 CFR, part 21, Sec. 21.101, Rickenbacker Avionics must show that the Twin Commander 690B aircraft continues to meet the applicable provisions of the regulations incorporated by reference in the original type certification basis for each model, as listed on the Type Data Sheet 2A4, or the applicable regulations and the additional provisions in effect on the date of application for this Supplemental Type 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 and the additional systems related provisions that cover the EFIS installation include: Sec. Sec. 23.1301, 23.1309, 23.1311, 23.1321, 23.1322, 23.1323, 23.1331, 23.1353, and 23.1357 at the amendment level appropriate for the application date; exemptions, if any; and the special conditions adopted by this rulemaking action. Additional information regarding the certification basis for this STC is available from the applicant.

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 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 the applicant apply for a supplemental type certificate to modify any other model 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

Rickenbacker Avionics 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 EFS50 EFIS and associated components, potentially 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 solidstate 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 [[Page 35502]]
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 0 500 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,
(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'' refers to 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 the Rockwell Twin Commander Model 690B airplanes. Should Rickenbacker Avionics apply at a later date for a supplemental type certificate to modify any other model on the same type certificate, Type Certificate No. 2A4, to incorporate 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 of airplane. 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 Rockwell Twin Commander Model 690B airplanes modified by Rickenbacker Avionics to add EFS50 EFIS installation.

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 June 12, 2006. James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E69818 Filed 62006; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Wes Ryan, Aerospace Engineer, Standards Office (ACE114), Small Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone (816) 3294123.