Skip to Content


Special Conditions: Cessna Models 500, 550 and S550 Airplanes; High Intensity Radiated Fields (HIRF)

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble


Federal Aviation Administration (FAA), DOT.


Final special conditions; request for comments.


These special conditions are issued for Cessna Models 500, 550 and S550 airplanes modified by Shadin Company, Inc. These modified 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 the Shadin Company dual ADC-6000 Air Data Computer (ADC) which will allow for the removal of the existing encoding altimeters, air data computer, and pneumatic altimeter. The applicable airworthiness regulations do not contain adequate or appropriate safety 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 provided by the existing airworthiness standards.


The effective date of these special conditions is April 27, 2004. Comments must be received on or before June 4, 2004.


Comments on these special conditions may be mailed in duplicate to: Federal Aviation Administration, Transport Airplane Directorate, Attention: Rules Docket (ANM-113), Docket No. NM277, 1601 Lind Avenue SW., Renton, Washington, 98055-4056; or delivered in duplicate to the Transport Airplane Directorate at the above address. All comments must be marked: Docket No. NM277.

Start Further Info


Greg Dunn, FAA, Airplane and Flight Crew Interface Branch, ANM-111, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington, 98055-4056; telephone (425) 227-2799; facsimile (425) 227-1149.

End Further Info End Preamble Start Supplemental Information


Comments Invited

The FAA has determined that notice and opportunity for prior public comment are impracticable, because these procedures would significantly delay certification of the airplane 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; however, the FAA invites 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 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 based on the comments we receive.

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


On March 1, 2004, Shadin Company, Inc. applied for a supplemental type certificate (STC) to modify Cessna Models 500, 550 and S550 airplanes. Cessna Model 500, 550 and S550 airplanes are currently approved under Type Certificate A22CE. The modification incorporates the installation of the Innovative Solutions & Support (IS & S) Duplex Reduced Vertical Separation Minimum (RVSM) system which will allow for the removal of the existing altitude alerter, encoding altimeters, air data computer, and standby altimeter. This system uses two air data computer ADC-6000s and interfaces to existing BA-141 altimeters. These ADCs can be susceptible to disruption to both command and response signals as a result of electrical and magnetic interference. This disruption of signals could result in the loss of all critical flight information displays and annunciations or the presentation of misleading information to the pilot.

Type Certification Basis

Under the provisions of 14 CFR 21.101, Shadin Company, Inc. must show that Cessna Model 500, 550 and S550 airplanes, as changed, continue to meet the applicable provisions of the regulations incorporated by reference in Type Certificate A22CE 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 certification basis for the modified Cessna Models 500, 550 and S550 airplanes includes 14 CFR 25, effective February 1, 1965 as described in Type Certificate A22CE.

If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR 25, as amended) do not contain adequate or appropriate safety standards for the Cessna Model 500, 550 and S550 airplanes because of novel or unusual design features, special conditions are prescribed under the provisions of § 21.16.

Special conditions, as defined in 14 CFR 11.19, are issued in accordance with § 11.38 and become part of the type Start Printed Page 24937certification basis in accordance with § 21.101.

Special conditions are initially applicable to the models for which they are issued. Should the applicant apply for a supplemental type certificate to modify any other model included on Type Certificate A22CE to incorporate the same novel or unusual design feature, the special conditions would also apply to the other models under the provisions of § 21.101.

Novel or Unusual Design Features

The modified Cessna Model 500, 550 and S550 airplanes will incorporate a new altitude display system, the Shadin Company ADC-6000 system, which will perform critical functions. This system may be vulnerable to high-intensity radiated fields (HIRF) external to the airplane. The current airworthiness standards of part 25 do not contain adequate or appropriate safety standards for the protection of this equipment from the adverse effects of HIRF. Accordingly, this system is considered to be a novel or unusual design feature.


There is no specific regulation that addresses protection requirements for electrical and electronic systems from HIRF. Increased power levels from ground-based radio transmitters and the growing use of sensitive 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 Cessna Models 500, 550 and S550 airplanes modified by the Shadin Company, Inc. These special conditions require that new electrical and electronic systems that perform critical functions, such as the ADC-6000, be designed and installed to preclude component damage and interruption of function due to both the direct and indirect effects of HIRF.

High-Intensity Radiated Fields (HIRF)

With the trend toward increased power levels from ground-based transmitters and the advent of space and satellite communications, coupled with electronic command and control of the airplane, the immunity of critical digital avionic/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 cockpit-installed 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 with the HIRF protection special condition is shown in accordance with either paragraph 1 OR 2 below:

1. A minimum threat of 100 volts rms (root-mean-square) 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.

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 table below for the frequency ranges indicated. Both peak and average field strength components from the table below are to be demonstrated.

FrequencyField strength (volts per meter)
10 kHz-100 kHz5050
100 kHz-500 kHz5050
500 kHz-2 MHz5050
2 MHz-30 MHz100100
30 MHz-70 MHz5050
70 MHz-100 MHz5050
100 MHz-200 MHz100100
200 MHz-400 MHz100100
400 MHz-700 MHz70050
700 MHz-1 GHz700700
1 GHz-2 GHz2000200
2 GHz-4 GHz3000200
4 GHz-6 GHz3000200
6 GHz-8 GHz1000200
8 GHz-12 GHz3000300
12 GHz-18 GHz2000200
18 GHz-40 GHz600200
The field strengths are expressed in terms of peak of the root-mean-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.


As discussed above, these special conditions are applicable Cessna Model 500, 550 and S550 airplanes modified by Shadin Company, Inc. Should Shadin Company, Inc. apply at a later date for design change approval to modify any other model included on the same type certificate to incorporate the same or similar novel or unusual design feature, these special conditions would apply to that model as well under the provisions of § 21.101.


This action affects only certain novel or unusual design features on Cessna Model 500, 550 and S550 airplanes modified by Shadin Company, Inc. It is not a rule of general applicability and affects only the applicant which applied to the FAA for approval of these features on these airplanes.

The substance of the special conditions for this airplane 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 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.

Start List of Subjects

List of Subjects in 14 CFR Part 25

  • Aircraft
  • Aviation safety
  • Reporting and recordkeeping requirements
End List of Subjects

The authority citation for these special conditions is as follows:

Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. 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 Cessna Model 500, 550 and S550 airplanes modified by the Shadin Company, Inc. 1. Protection from Unwanted Effects of High-Intensity 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.

End Authority Start Signature
Start Printed Page 24938

Issued in Renton, Washington, on April 27, 2004.

Michael Kaszycki,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 04-10238 Filed 5-4-04; 8:45 am]