Special Conditions; Cessna Aircraft Company; Protection of Systems for High Intensity Radiated Fields (HIRF), 72068-72070 [05-23523]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 70, Number 230 (Thursday, December 1, 2005)]
[Rules and Regulations]
[Pages 72068-72070]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23523]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE218, Special Condition 23-158-SC]


Special Conditions; Cessna Aircraft Company; Protection of 
Systems for 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 to Cessna Aircraft Co., 
for the Type Certificate of Model 510 Mustang airplane. This airplane 
will have novel and unusual design features when compared to the state 
of technology envisaged in the applicable airworthiness standards. The 
novel and unusual design features include the installation of an 
Electronic Flight Instrumentation System (EFIS), Digital Air Data 
Computer (ADC), and a Full Authority Digital Engine Control (FADEC). 
The applicable regulations do not adequately consider failure of

[[Page 72069]]

electrical and electronic systems performing critical functions from 
the effects of external HIRF. These special conditions contain the 
additional safety standards that the Administrator considers necessary 
to establish a level of safety equivalent to the airworthiness 
standards applicable to this airplane.

DATES: The effective date of these special conditions is November 17, 
2005. Comments must be received on or before January 3, 2006.

ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation 
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk, 
Docket No. CE218, Room 506, 901 Locust, Kansas City, Missouri 64106. 
All comments must be marked: Docket No. CE218. Comments may be 
inspected in the Rules Docket weekdays, except Federal holidays, 
between 7:30 a.m. and 4 p.m.

FOR FURTHER INFORMATION CONTACT: Wes Ryan, 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) 329-4127.

SUPPLEMENTARY 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 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. CE218.'' The postcard will be date stamped and 
returned to the commenter.

Background

    On January 28, 2004, Cessna Aircraft Company; One Cessna Boulevard; 
Post Office Box 7704; Wichita, KS 67277, made an application to the FAA 
for a new Type Certificate for the Cessna Model 510 Mustang. The Cessna 
510 will be approved under a new Type Certificate Data Sheet (TCDS) 
Number when Type Certificate (TC) is issued. The proposed modification 
incorporates a novel or unusual design feature, a digital air data 
computer, which may be vulnerable to HIRF external to the airplane.

Type Certification Basis

    Under the terms of Sec.  21.17, Cessna Aircraft must show that the 
Model 510 Mustang meets the following provisions, the provisions of 
other applicable special conditions, or the applicable regulations in 
effect on the date of application for their type certificate: Federal 
Aviation Regulations (FAR) part 23 effective February 1, 1965 as 
amended by Amendments 23-1 through 23-54; Special Conditions applied to 
Sec.  23.45, Sec.  23.51, Sec.  23.53, Sec.  23.55, Sec.  23.57, Sec.  
23.59, Sec.  23.61, Sec.  23.63, Sec.  23.66, Sec.  23.67, Sec.  23.73, 
Sec.  23.75, Sec.  23.77, Sec.  23.177, Sec.  23.201(e), Sec.  
23.203(c), Sec.  23.251, Sec.  23.253, Sec.  23.735, Sec.  23.1195, 
Sec.  23.1197, Sec.  23.1199, Sec.  23.1201, Sec.  23.1323, Sec.  
23.1505, Sec.  23.1583, Sec.  23.1585, Sec.  23.1587; Equivalent Levels 
of Safety applied to Sec.  23.1305(c)(2), Sec.  23.1305(c)(5), Sec.  
23.1549(a) thru (d), Sec.  23.841(b)(6), Sec.  23.841(a), Sec.  
23.807(e), Sec.  23.1435(a)(2), and Sec.  23.1555(d); an exemption to 
Sec.  23.181(b); FAR part 34 as amended by the Amendment in effect on 
the date of certification; and FAR part 36 as amended by the Amendment 
in effect on the day of application; the certification requirements 
applied to the EFIS, Air Data Computer, and FADEC, and these terms of 
these Special Conditions.

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 after public notice and become 
part of the type certification basis in accordance with Sec.  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 already 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.  21.17.

Novel or Unusual Design Features

    Cessna 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 the addition of an EFIS, 
ADC, and FADEC, which may be 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 solid-state 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 electromagnetic 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 cockpit-installed 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

[[Page 72070]]

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 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 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.

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'' means 
those 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 non-critical 
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 
Cessna Model 510 Mustang airplane. Should Cessna apply at a later date 
for a supplemental type certificate to modify any other model on the 
same type certificate 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

0
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

0
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 Cessna Model 510 Mustang airplane.
    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 
HIRF 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 November 17, 2005.
David R. Showers,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 05-23523 Filed 11-30-05; 8:45 am]
BILLING CODE 4910-13-P