Special Conditions: West Pacific Air LLC; Raytheon Beech Model B-36TC; Protection of Electronic Flight Instrument Systems From the Effects of High Intensity Radiated Fields (HIRF), 51457-51459 [E6-14457]

Download as PDF Federal Register / Vol. 71, No. 168 / Wednesday, August 30, 2006 / Rules and Regulations Supplement I to Part 205—Official Staff Interpretations * 3. Disclosure of dollar amount of fee at POS. The notice provided to the consumer at POS under § 205.3(b)(3)(ii) must state the amount of the fee for insufficient or uncollected funds if the dollar amount of the fee can be calculated at the time of the transaction. For example, if a state sets a maximum fee that may be collected due to insufficient or uncollected funds in a consumer’s account based on the amount of the underlying transaction (such as where the amount of the fee is expressed as a percentage of the underlying transaction), the person collecting the fee must provide the actual dollar amount of the fee on the notice provided to the consumer. Alternatively, in a state where the amount of the insufficient funds fee a person may collect cannot be calculated at the time of the transaction (for example, where the amount of the fee will depend on the number of days a debt continues to be owed), the person collecting the fee may provide a description of how the fee will be determined on both the posted notice as well as on the notice provided to the consumer. * A–8 Model Clause for Electronic Collection of Insufficient Funds Fees (§ 205.3(b)(3)) If your payment is returned due to insufficient funds in your account, you authorize us to make a one-time electronic fund transfer from your account to collect a fee of $ll . [If your payment is returned due to insufficient funds in your account, you authorize us to make a one-time electronic fund transfer from your account to collect a fee. The fee will be determined [by]/[as follows]: llll.] 4. In Supplement I to Part 205, under Section 205.3—Coverage, the heading ‘‘Paragraph 3(b)(3)—Collection of Service Fees via Electronic Fund Transfer’’ is revised as ‘‘Paragraph 3(b)(3)—Collection of Insufficient Funds Fees via Electronic Fund Transfer’’, paragraph 1. is revised, and paragraphs 2. and 3. are added. I * * * * Section 205.3—Coverage * * * * * 3(b) Electronic Fund Transfer jlentini on PROD1PC65 with RULES * * * * * Paragraph 3(b)(3)—Collection of Insufficient Funds Fees via Electronic Fund Transfer 1. Fees imposed by account-holding institution. The requirement to obtain a consumer’s authorization to collect a fee via EFT for the return of an EFT or check unpaid due to insufficient or uncollected funds in the consumer’s account applies only to the person to whom the EFT or check was returned and that intends to collect the service fee by means of an EFT from the consumer’s account. The authorization requirement does not apply to any fees assessed by the consumer’s account-holding financial institution when it returns the unpaid underlying EFT or check or pays the amount of the overdraft. 2. Accounts receivable transactions. In an accounts receivable (ARC) transaction where a consumer sends in a payment for amounts owed, a person seeking to electronically collect a fee for returned items due to insufficient or uncollected funds in a consumer’s account must obtain the consumer’s authorization to collect the fee. A consumer authorizes a person to electronically collect an insufficient funds fee when the consumer receives notice, typically on an invoice or statement, that the person may collect the fee through an EFT to the consumer’s account, and the consumer goes forward with the underlying transaction by sending payment. The notice must also state the dollar amount of the fee. However, an explanation of how that fee will be determined may be provided in place of the dollar amount of the fee if the fee may vary due to the amount of the transaction or due to other factors. For example, if a state law permits a maximum fee of $30 or 10% of the underlying transaction, whichever is greater, a payee may explain how the fee is determined, rather than state a specific dollar amount for the fee. VerDate Aug<31>2005 16:32 Aug 29, 2006 Jkt 208001 51457 AGENCY: 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 August 23, 2006. Comments must be received on or before September 29, 2006. ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation Administration, Regional Counsel, ACE–7, Attention: Rules Docket Clerk, Docket No. CE257, Room 506, 901 Locust, Kansas City, Missouri 64106. All comments must be marked: Docket No. CE257. 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: Mr. Ervin Dvorak, 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) 329–4123. 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. SUMMARY: These special conditions are issued to West Pacific Air LLC, 6427 E. Rutter Road, Spokane, WA 99212, for a Supplemental Type Certificate for the Raytheon Beech Model B–36TC airplane. This airplane 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 ICDS–10 manufactured by SAGEM Avionics, Inc. for which the 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 * * * * By order of the Board of Governors of the Federal Reserve System. Dated: August 24, 2006. Jennifer J. Johnson, Secretary of the Board. [FR Doc. E6–14342 Filed 8–29–06; 8:45 am] BILLING CODE 6210–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. CE257, Special Condition 23– 197–SC] Special Conditions: West Pacific Air LLC; Raytheon Beech Model B–36TC; Protection of Electronic Flight Instrument Systems From the Effects of High Intensity Radiated Fields (HIRF) Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 E:\FR\FM\30AUR1.SGM 30AUR1 51458 Federal Register / Vol. 71, No. 168 / Wednesday, August 30, 2006 / Rules and Regulations 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. CE257.’’ The postcard will be date stamped and returned to the commenter. Background On May 25, 2005, West Pacific Air LLC, 6427 E. Rutter Road, Spokane, WA 99212, applied for a new Supplemental Type Certificate for the Raytheon Beech Model B–36TC airplane. The Raytheon Beech Model B–36TC is currently approved under TC No. 3A15 and modified to TurbineAir configuration under STC SA01156SE. 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. jlentini on PROD1PC65 with RULES Type Certification Basis Under the provisions of 14 CFR part 21.101, West Pacific Air LLC must show that the Raytheon Beech Model B–36TC aircraft, as changed, continues to meet the following provisions, or the applicable regulations in effect on the date of application for the change to the Raytheon Beech Model B–36TC. The regulations incorporated by reference in the type certificate are commonly referred to as the ‘‘original type certification basis.’’ The regulations incorporated by reference in TC No. 3A15 are as follows: CAR 3 effective May 15, 1956, through Amendment 3– 8, effective December 18, 1962; Federal Aviation Regulations (14 CFR, part 23) § 23.1301, Amendment 23–20; § 23.1309, Amendment 23–49; § 23.1311, Amendment 23–49; § 23.1321, Amendment 23–49; § 23.1322, Amendment 23–43; § 23.1331, Amendment 23–43; 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 for an airplane because of a novel or unusual design feature, 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. VerDate Aug<31>2005 16:32 Aug 29, 2006 Jkt 208001 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 West Pacific Air LLC plans to incorporate certain novel and unusual design features into the Raytheon Beech Model B–36TC 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 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 PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 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 ........... 50 50 50 100 50 50 100 100 700 700 2000 3000 3000 1000 3000 2000 600 Average 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 ‘‘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 E:\FR\FM\30AUR1.SGM 30AUR1 Federal Register / Vol. 71, No. 168 / Wednesday, August 30, 2006 / Rules and Regulations 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 Raytheon Beech Model B–36TC airplane. Should West Pacific Air LLC 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. jlentini on PROD1PC65 with RULES 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. VerDate Aug<31>2005 16:32 Aug 29, 2006 Jkt 208001 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 Raytheon Beech Model B–36TC airplane modified by West Pacific Air LLC to add an EFIS. 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 August 23, 2006. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–14457 Filed 8–29–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2001–NE–30-AD; Amendment 39–14728; AD 2006–17–07] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, –17AR, –209, –217, –217A, –217C, and –219 Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D–209, –217, PO 00000 Frm 00039 Fmt 4700 Sfmt 4700 51459 –217A, –217C, and –219 turbofan engines. That AD currently requires initial and repetitive visual inspections for fretting and fluorescent magnetic particle inspections (FMPI) for cracking in the area of the tierod holes on 8th stage high pressure compressor (HPC) front hubs (from here on, referred to as HPC front hubs) that have operated at any time with PWA 110–21 coating. This AD requires either replacing HPC front hubs and HPC disks that have operated at any time with PWA 110–21 coating and that operated in certain engine models, or, visually inspecting and FMPI for cracking of those parts and re-plating them if they pass inspection. This AD also requires adding JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, and –17AR engines to the applicability. This AD results from an investigation by PW, which concluded that any HPC front hub or HPC disk coated with PWA 110– 21 that ever operated on JT8D–15, –15A, –17, –17A, –17R, –17AR, –209, –217, –217A, –217C, and –219 turbofan engines, could crack before reaching their published life limit. We are issuing this AD to prevent a rupture of an HPC front hub or an HPC disk that could result in an uncontained engine failure and damage to the airplane. DATES: This AD becomes effective October 4, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of October 4, 2006. ADDRESSES: You can get the service information identified in this AD from Pratt & Whitney, 400 Main St., East Hartford, CT 06108, telephone (860) 565–7700; fax (860) 565–1605. You may examine the AD docket at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. You may examine the service information, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. FOR FURTHER INFORMATION CONTACT: Keith Lardie, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7189; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 with a proposed AD. The proposed AD applies to PW JT8D–209, –217, –217A, –217C, and –219 turbofan engines. We published the proposed AD in the Federal Register on December 30, 2005 (70 FR 77342). That action proposed to require either replacing HPC front hubs E:\FR\FM\30AUR1.SGM 30AUR1

Agencies

[Federal Register Volume 71, Number 168 (Wednesday, August 30, 2006)]
[Rules and Regulations]
[Pages 51457-51459]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-14457]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE257, Special Condition 23-197-SC]


Special Conditions: West Pacific Air LLC; Raytheon Beech Model B-
36TC; Protection of Electronic Flight Instrument Systems From the 
Effects of 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 West Pacific Air LLC, 
6427 E. Rutter Road, Spokane, WA 99212, for a Supplemental Type 
Certificate for the Raytheon Beech Model B-36TC airplane. This airplane 
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 ICDS-10 
manufactured by SAGEM Avionics, 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 August 23, 
2006. Comments must be received on or before September 29, 2006.

ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation 
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk, 
Docket No. CE257, Room 506, 901 Locust, Kansas City, Missouri 64106. 
All comments must be marked: Docket No. CE257. 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: Mr. Ervin Dvorak, 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) 329-4123.

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

[[Page 51458]]

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. CE257.'' The postcard will be date stamped and 
returned to the commenter.

Background

    On May 25, 2005, West Pacific Air LLC, 6427 E. Rutter Road, 
Spokane, WA 99212, applied for a new Supplemental Type Certificate for 
the Raytheon Beech Model B-36TC airplane. The Raytheon Beech Model B-
36TC is currently approved under TC No. 3A15 and modified to TurbineAir 
configuration under STC SA01156SE. 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 21.101, West Pacific Air LLC 
must show that the Raytheon Beech Model B-36TC aircraft, as changed, 
continues to meet the following provisions, or the applicable 
regulations in effect on the date of application for the change to the 
Raytheon Beech Model B-36TC. The regulations incorporated by reference 
in the type certificate are commonly referred to as the ``original type 
certification basis.'' The regulations incorporated by reference in TC 
No. 3A15 are as follows: CAR 3 effective May 15, 1956, through 
Amendment 3-8, effective December 18, 1962; Federal Aviation 
Regulations (14 CFR, part 23) Sec.  23.1301, Amendment 23-20; Sec.  
23.1309, Amendment 23-49; Sec.  23.1311, Amendment 23-49; Sec.  
23.1321, Amendment 23-49; Sec.  23.1322, Amendment 23-43; Sec.  
23.1331, Amendment 23-43; 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 for 
an airplane because of a novel or unusual design feature, 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 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

    West Pacific Air LLC plans to incorporate certain novel and unusual 
design features into the Raytheon Beech Model B-36TC 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 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:

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

[[Page 51459]]

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 
Raytheon Beech Model B-36TC airplane. Should West Pacific Air LLC 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

    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 Raytheon Beech Model B-36TC 
airplane modified by West Pacific Air LLC to add an EFIS.
    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 August 23, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-14457 Filed 8-29-06; 8:45 am]
BILLING CODE 4910-13-P

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