[Federal Register Volume 65, Number 250 (Thursday, December 28, 2000)]
[Rules and Regulations]
[Pages 82257-82259]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-33179]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. NM180; Special Conditions No. 25-170-SC]


Special Conditions: Cessna Model 560, Citation V, Series 
Airplanes; High-Intensity Radiated Fields (HIRF)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

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SUMMARY: These special conditions are issued for Cessna Model 560, 
Citation V, series airplanes modified by Honeywell International Inc. 
These modified airplanes will have a novel and unusual design feature 
when compared to the state of technology envisioned in the 
airworthiness standards for transport category airplanes. The 
modification incorporates the installation of a new integrated 
electronic cockpit display system. The cockpit display system will 
utilize electrical and electronic systems that perform critical 
functions. The applicable airworthiness regulations do not contain 
adequate or appropriate safety standards for the protection of this 
system 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 airworthiness standards.

DATES: The effective date of these special conditions is December 7, 
2000. Comments must be received on or before January 29, 2001.

ADDRESSES: Comments on these special conditions may be mailed in 
duplicate to: Federal Aviation Administration, Transport Airplane 
Directorate, Attention: Rules Docket (ANM-114), Docket No. NM180, 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. NM180. 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: Meghan Gordon, FAA, Standardization 
Branch, ANM-113, Transport Airplane Directorate, Aircraft Certification 
Service, 1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone 
(425) 227-2138; facsimile (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA has determined that good cause exists for making these 
special conditions effective upon issuance; however, interested persons 
are invited to submit such written data, views, or arguments, as they 
may desire. Communications should identify the regulatory docket number 
and be submitted in duplicate to the address specified above. The 
Administrator will consider all communications received on or before 
the closing date for comments. These 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 these special conditions must include a self-addressed, 
stamped postcard on which

[[Page 82258]]

the following statement is made: ``Comments to Docket No. NM180.'' The 
postcard will be date stamped and returned to the commenter.

Background

    On February 25, 2000, Honeywell International Inc., 21111 N. 19th 
Avenue, Phoenix, AZ 85027, applied for a Supplemental Type Certificate 
(STC) to modify the Cessna Model 560, Citation V, airplane approved 
under Type Certificate No. A22CE. The subject Cessna Model 560, 
Citation V, airplane is a straight wing, small transport category 
airplane. These airplanes, serial numbers 560-001 through 560-0259, are 
powered by two Pratt & Whitney JT15D-51 turbofans, with a maximum 
takeoff weight of 15,900 pounds. Serial numbers 560-0260 through 560-
0538 are powered by two Pratt & Whitney JT15D-5D turbofans, with a 
maximum takeoff weight of 16,300 pounds. This series of airplanes 
operates with a 2-pilot crew and can hold up to 11 passengers.
    The Model 560, Citation V, will incorporate integrated electronic 
PRIMUS EPIC Cockpit Display Systems (CDS), manufactured by Honeywell 
International Inc., which display attitude and heading information. The 
PRIMUS EPIC CDS performs a critical function associated with the 
display of attitude and heading information to the pilot, and must be 
designed and installed to ensure that its operation is not adversely 
affected by high intensity radiated fields (HIRF). This critical 
function can be susceptible to disruption of both command and response 
signals as a result of electrical and magnetic interference caused by 
HIRF external to the airplane. This disruption of signals could result 
in loss of critical flight displays and annunciations, or could present 
misleading information to the pilot.

Type Certification Basis

    Under the provisions of 14 CFR 21.101, Honeywell International Inc. 
must show that the Cessna Model 560, Citation V, series airplanes, as 
changed, continue to meet the applicable provisions of the regulations 
incorporated by reference in Type Certificate No. 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 regulations included in the certification 
basis for the Cessna Model 560, Citation V, series airplanes include 
Title 14, Code of Federal Regulations (14 CFR) part 25, as amended by 
Amendments 25-1 through 25-8, plus additional requirements listed in 
the type certificate data sheet that are not relevant to these special 
conditions.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., part 25, as amended) do not contain adequate or 
appropriate safety standards for the Cessna Model 560, Citation V, 
series 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 Cessna Model 560, Citation V, series airplanes must 
comply with the fuel vent and exhaust emission requirements of part 34 
and the noise certification requirements of part 36.
    Special conditions, as appropriate, are issued in accordance with 
Sec. 11.49, as required by Secs. 11.28 and 11.29, and become part of 
the airplane's type certification basis in accordance with 
Sec. 21.101(b)(2).
    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 features, 
these special conditions would also apply to the other model under the 
provisions of Sec. 21.101(a)(1).

Novel or Unusual Design Features

    As stated earlier, the Cessna Model 560, Citation V, series 
airplanes modified by Honeywell International Inc. will incorporate the 
PRIMUS EPIC CDS, which performs critical functions. This system 
contains electronic equipment for which 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. The CDS may be vulnerable to HIRF external to the airplane. 
Accordingly, this system is considered to be a novel or unusual design 
feature.

Discussion

    There is no specific regulation that addresses the requirements for 
protection of 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 that is equivalent to 
that intended by the regulations incorporated by reference, special 
conditions are needed for the Cessna Model 560, Citation V, airplanes 
modified to include the PRIMUS EPIC CDS. These special conditions will 
require that this system, which performs critical functions, 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, plus the advent of space and satellite communications 
coupled with electronic command and control of the airplane, the 
immunity of critical digital avionics 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 with either paragraph 1 OR 2 below:
    1. A minimum threat of 100 volts rms 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 following field 
strengths for the frequency ranges indicated. Both peak and average 
field strength components from the Table are to be demonstrated.

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                                                       Field strength
                                                      (volts per meter)
                     Frequency                     ---------------------
                                                       Peak     Average
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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 HGz-2 GHz.......................................       2000        200
2 HGz-4 GHz.......................................       3000        200
4 GHz-6 GHz.......................................       3000        200
6 GHz-8 GHz.......................................       1000        200
8 GHz-12 GHZ......................................       3000        300

[[Page 82259]]

 
12 GHz-18 GHz.....................................       2000        200
18 GHz-40 GHz.....................................        600       200
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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.

Applicability

    As discussed above, these special conditions are applicable to 
Cessna Model 560, Citation V, series airplanes modified by Honeywell 
International Inc. to include the PRIMUS EPIC CDS. Should Honeywell 
International Inc. apply at a later date for a supplemental type 
certificate to modify any other model included on Type Certificate 
A22CE to incorporate the same novel or unusual design features, these 
special conditions would apply to that model as well under the 
provisions of Sec. 21.101(a)(1).

Conclusion

    This action affects only certain novel or unusual design features 
on the Cessna Model 560, Citation V, series airplanes modified by 
Honeywell Inc. 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 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 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 the Cessna Model 560, 
Citation V, series airplanes modified by Honeywell International 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.

    Issued in Renton, Washington, on December 7, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-33179 Filed 12-27-00; 8:45 am]
BILLING CODE 4910-13-P