Special Conditions; New Piper Aircraft, Inc.; PA-34; Protection of Systems for High Intensity Radiated Fields (HIRF), 72070-72072 [05-23524]

Download as PDF 72070 Federal Register / Vol. 70, No. 230 / Thursday, December 1, 2005 / Rules and Regulations 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: Frequency Field strength (volts per meter) Peak 10 kHz–100 kHz ....... 100 kHz–500 kHz ..... 500 kHz–2 MHz ........ 2 MHz–30 MHz ......... 30 MHz–70 MHz ....... 70 MHz—100 MHz ... 100 MHz–200 MHz ... 200 MHz–400 MHz ... 400 MHz–700 MHz ... 700 MHz–1 GHz ....... 1 GHz–2 GHz ........... 2 GHz–4 GHz ........... 4 GHz–6 GHz ........... 6 GHz–8 GHz ........... 8 GHz–12 GHz ......... 12 GHz–18 GHz ....... 18 GHz–40 GHz ....... Average 50 50 50 100 50 50 100 100 700 700 2000 3000 3000 1000 3000 2000 600 50 50 50 100 50 50 100 100 50 100 200 200 200 200 300 200 200 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 VerDate Aug<31>2005 14:18 Nov 30, 2005 Jkt 208001 ‘‘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 § 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 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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: I 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 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. I 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 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. CE235, Special Condition 23– 175–SC] Special Conditions; New Piper Aircraft, Inc.; PA–34; Protection of Systems for High Intensity Radiated Fields (HIRF) Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. AGENCY: SUMMARY: These special conditions are issued to the New Piper Aircraft, Inc., Vero Beach, Florida, for a type design E:\FR\FM\01DER1.SGM 01DER1 Federal Register / Vol. 70, No. 230 / Thursday, December 1, 2005 / Rules and Regulations change for the PA–34 model airplanes. These airplanes will have novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. These novel and unusual design features include the installation of electronic flight instrument system (EFIS) displays Model 700–00006– XXX(), manufactured by Avidyne Corporation, Inc. for which 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 the airworthiness standards applicable to these airplanes. 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. CE235, Room 506, 901 Locust, Kansas City, Missouri 64106. All comments must be marked: Docket No. CE235. 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 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 VerDate Aug<31>2005 14:18 Nov 30, 2005 Jkt 208001 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. CE235.’’ The postcard will be date stamped and returned to the commenter. Background The New Piper Aircraft, Inc., Vero Beach, Florida, has made application to revise the type design of the PA–34 model airplanes. The model is currently approved under the type certification basis listed on Type Certificate Data Sheet (TCDS) A7SO. The proposed modification incorporates a novel or unusual design feature, such as digital avionics consisting of an EFIS that is vulnerable to HIRF external to the airplane. Type Certification Basis Under the provisions of 14 CFR part 21, § 21.101, New Piper Aircraft, Inc, must show that affected airplane models, as changed, continue to meet the applicable provisions of the regulations identified on the appropriate TCDS. In addition, the type certification basis of the airplanes embodying this modification will include the additional certification basis for installation of the Avidyne Entegra EFIS: 14 CFR part 23 regulations FAR 23.301, 23.337, 23.341, 23.473, 23.561, 23.607, 23.611, as amended by Amdt. 23–48; FAR 23.305, 23.613, 23.773, 23.1525, 23.1549 as amended by Amdt. 23–45; FAR 23.777, 23.1191, 23.1337 as amended by Amdt. 23–51; FAR 23.867, 23.1303, 23.1307, 23.1309, 23.1311, 23.1321, 23.1323, 23.1329, 23.1351, 23.1353, 23.1359, 23.1361, 23.1365, 23.1431 as amended by Amdt. 23–49; FAR 23.1305 as amended by Amdt. 23–52; FAR 23.1322, 23.1331, 23.1357 as amended by Amdt. 23–43; FAR 23.1325, 23.1543, 23.1545, 23.1555, 23.1563, 23.1581, 23.1583, 23.1585 as amended by Amdt. 23–50; FAR 23.1523 as amended by Amdt. 23– 34; FAR 23.1529 as amended by Amdt. 23–26; and the special conditions adopted by this rulemaking action. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 72071 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 § 21.16. Special conditions, as appropriate, as defined in § 11.19, are issued in accordance with § 11.38 after public notice and become part of the type certification basis in accordance with § 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 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 § 21.101. Novel or Unusual Design Features The New Piper Aircraft, Inc 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 EFIS, which are 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 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 E:\FR\FM\01DER1.SGM 01DER1 72072 Federal Register / Vol. 70, No. 230 / Thursday, December 1, 2005 / Rules and Regulations 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 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: Frequency Field strength (volts per meter) Peak 10 kHz–100 kHz ....... 100 kHz–500 kHz ..... 500 kHz–2 MHz ........ 2 MHz–30 MHz ......... 30 MHz–70 MHz ....... 70 MHz–100 MHz ..... 100 MHz–200 MHz ... 200 MHz–400 MHz ... 400 MHz–700 MHz ... 700 MHz–1 GHz ....... 1 GHz–2 GHz ........... 2 GHz–4 GHz ........... 4 GHz–6 GHz ........... 6 GHz–8 GHz ........... 8 GHz–12 GHz ......... 12 GHz–18 GHz ....... 18 GHz–40 GHz ....... Average 50 50 50 100 50 50 100 100 700 700 2000 3000 3000 1000 3000 2000 600 50 50 50 100 50 50 100 100 50 100 200 200 200 200 300 200 200 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 VerDate Aug<31>2005 14:18 Nov 30, 2005 Jkt 208001 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 New Piper PA–34 model airplanes. 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 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 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: I 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 New Piper PA–34 model airplanes modified by installation of the factory optional Avidyne Entegra EFIS system. 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. I Issued in Kansas City, Missouri on November 17, 2005. David R. Showers, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–23524 Filed 11–30–05; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\01DER1.SGM 01DER1

Agencies

[Federal Register Volume 70, Number 230 (Thursday, December 1, 2005)]
[Rules and Regulations]
[Pages 72070-72072]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23524]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE235, Special Condition 23-175-SC]


Special Conditions; New Piper Aircraft, Inc.; PA-34; Protection 
of Systems for High Intensity Radiated Fields (HIRF)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued to the New Piper Aircraft, 
Inc., Vero Beach, Florida, for a type design

[[Page 72071]]

change for the PA-34 model airplanes. These airplanes will have novel 
and unusual design features when compared to the state of technology 
envisaged in the applicable airworthiness standards. These novel and 
unusual design features include the installation of electronic flight 
instrument system (EFIS) displays Model 700-00006-XXX(), manufactured 
by Avidyne Corporation, Inc. for which 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 the airworthiness standards applicable to 
these airplanes.

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. CE235, Room 506, 901 Locust, Kansas City, Missouri 64106. 
All comments must be marked: Docket No. CE235. 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 
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. CE235.'' The postcard will be date stamped and 
returned to the commenter.

Background

    The New Piper Aircraft, Inc., Vero Beach, Florida, has made 
application to revise the type design of the PA-34 model airplanes. The 
model is currently approved under the type certification basis listed 
on Type Certificate Data Sheet (TCDS) A7SO. The proposed modification 
incorporates a novel or unusual design feature, such as digital 
avionics consisting of an EFIS that is vulnerable to HIRF external to 
the airplane.

Type Certification Basis

    Under the provisions of 14 CFR part 21, Sec.  21.101, New Piper 
Aircraft, Inc, must show that affected airplane models, as changed, 
continue to meet the applicable provisions of the regulations 
identified on the appropriate TCDS. In addition, the type certification 
basis of the airplanes embodying this modification will include the 
additional certification basis for installation of the Avidyne Entegra 
EFIS: 14 CFR part 23 regulations FAR 23.301, 23.337, 23.341, 23.473, 
23.561, 23.607, 23.611, as amended by Amdt. 23-48; FAR 23.305, 23.613, 
23.773, 23.1525, 23.1549 as amended by Amdt. 23-45; FAR 23.777, 
23.1191, 23.1337 as amended by Amdt. 23-51; FAR 23.867, 23.1303, 
23.1307, 23.1309, 23.1311, 23.1321, 23.1323, 23.1329, 23.1351, 23.1353, 
23.1359, 23.1361, 23.1365, 23.1431 as amended by Amdt. 23-49; FAR 
23.1305 as amended by Amdt. 23-52; FAR 23.1322, 23.1331, 23.1357 as 
amended by Amdt. 23-43; FAR 23.1325, 23.1543, 23.1545, 23.1555, 
23.1563, 23.1581, 23.1583, 23.1585 as amended by Amdt. 23-50; FAR 
23.1523 as amended by Amdt. 23-34; FAR 23.1529 as amended by Amdt. 23-
26; and the special conditions adopted by this rulemaking action.

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(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 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.  21.101.

Novel or Unusual Design Features

    The New Piper Aircraft, Inc 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 EFIS, which 
are 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 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

[[Page 72072]]

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 
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:

------------------------------------------------------------------------
                                                         (volts per meter)
                 Frequency                     Field   --------------------
                                              strength     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 New 
Piper PA-34 model airplanes.

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 New Piper PA-34 model airplanes 
modified by installation of the factory optional Avidyne Entegra EFIS 
system.
    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 November 17, 2005.
David R. Showers,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 05-23524 Filed 11-30-05; 8:45 am]
BILLING CODE 4910-13-P