Bureau of Labor Statistics ( BLS). 2004. Table 5. Wages and Salaries ( not seasonally adjusted): Employment Cost Index for wages and salaries, civilian and State and local government workers, by industry and occupational group. Online at http:// www. bls. gov/ news. release/ eci. t05. htm.

Jun 03 Mar 04 Jun 04 Civilian workers.......................... 160.3 163.3 164.3 Excluding sales occupations........... 160.3 163.3 164.2 Industry Goods producing( 1)...................... 157.5 159.9 161 Manufacturing......................... 159 161.3 162.4 Service producing( 2).................... 161.4 164.6 165.5 Services.............................. 162.8 166.5 167.4 Health services..................... 163.2 167.7 168.6 Hospitals......................... 164.4 169 169.9 Educational services................ 160.7 163.6 163.8 Public administration( 3).............. 158 161.1 161.4 Nonmanufacturing........................ 160.5 163.7 164.6 Occupational group White collar............................ 162.9 166.1 167.1 Excluding sales..................... 163.5 166.7 167.6 Professional specialty and technical............................ 160.1 163.8 164.4 Executive, administrative, and managerial........................ 169 171.4 172.4 Administrative support, including clerical.......................... 163.1 166.3 167.5 Blue collar............................. 154.8 157.3 158.4 Service................................. 158.7 161.2 161.9 State and local government................ 159.7 162.5 162.8 Industry Services.............................. 159.8 162.6 162.7 Excluding schools................. 161.8 165.1 165.6 Health services..................... 163.5 167.4 167.8 Hospitals......................... 163.8 167.4 167.9 Educational services................ 159.3 162 162.1 Schools........................... 159.5 162.1 162.3 Elementary and secondary........ 158.5 161.3 161.5 Colleges and universities....... 162.1 164.3 164.4 Public administration( 3).............. 158 161.1 161.4 Occupational group Jun 03 Mar 04 Jun 04 White collar............................ 159.2 162.1 162.4 Professional specialty and technical............................ 159.1 162.1 162.3 Executive, administrative, and managerial........................  161 163.5 163.8 Administrative support, including clerical............................. 157.2 160.4 160.8 Blue collar............................. 156.5 158.9 159.2 Service................................. 163.8 166.7 167 1 Includes mining, construction, and manufacturing. 2 Includes transportation, communication, and public utilities; wholesale and retail trade; finance, insurance, and real estate; service industries; and public administration. 3 Includes executive, legislative, judicial, administrative, and regulatory activities of State and local governments, SICs 91 through 96.


[Federal Register: December 28, 2007 (Volume 72, Number 248)]
[Rules and Regulations]
[Page 73579-73582]
[DOCID:fr28de07-4]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Parts 21 and 27

[Docket No. SW017; Special Condition No. 27-017-SC]

Special Condition: Bell Helicopter Textron Canada Limited Model
429 Helicopters, High Intensity Radiated Fields

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special condition; request for comments.

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

SUMMARY: This special condition is issued for the Bell Helicopter Model
429 helicopters. These helicopters will have novel or unusual design
features associated with installing electrical and electronic systems
that perform critical functions, including an Electronic Flight
Instrument System (EFIS) and a Full Authority Digital Engine Control
(FADEC). The applicable airworthiness regulations do not contain
adequate or appropriate safety standards to protect systems that
perform critical control functions, or provide critical displays, from
the effects of high-intensity radiated fields (HIRF). This special
condition contains the additional safety standards that the
Administrator considers necessary to ensure that critical functions of
systems will be maintained when exposed to HIRF.

DATES: The effective date of this special condition is December 11,
2007. Comments must be received on or before February 11, 2008.

ADDRESSES: Send comments on this special condition in duplicate to:
Federal Aviation Administration, Rotorcraft Directorate, Attention:
Rules Docket (ASW-111) Docket No. SW017, Fort Worth, Texas 76193-0111,
or deliver them in duplicate to the Rotorcraft Directorate at 2601
Meacham Blvd., Fort Worth, Texas 76137. Comments must be marked: Docket
No. SW017. You may inspect comments in the Docket that is maintained in
Room 448 in the Rotorcraft Directorate offices at 2601 Meacham Blvd.,
Fort Worth, Texas, on weekdays, except Federal holidays, between 8:30
a.m. and 4 p.m.

FOR FURTHER INFORMATION CONTACT: Carroll Wright, Electrical Flight
Systems

Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards, 2601
Meacham Blvd., Fort Worth, Texas 76193-0110; telephone<PHONE_NUMBER>,
FAX<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION: We have determined that notice and
opportunity for prior public comment are unnecessary since the
substance of this special condition has been subject to the public
comment process in several prior instances with no substantive comments
received. Therefore, we determined that good cause exists for making
this special condition effective upon issuance.

Comments Invited

    You are invited to submit written data, views, or arguments. Your
communications should include the regulatory docket or special
condition number and be sent in duplicate to the address stated above.
We will consider all communications received on or before the closing
date and may change the special condition in light of the comments
received. Interested persons may examine the Docket. We will file a
report summarizing each substantive public contact with FAA personnel
concerning this special condition in the docket. If you wish us to
acknowledge receipt of your comments, you must include a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket No. SW017.'' We will date stamp the postcard and
mail it to you.

Background

    On September 13, 2004, Bell Helicopter submitted an application for
a Type Certificate for the Model 429 helicopter. The Model 429
helicopter is a new design based on the existing drive train of the
Bell Model 427 helicopter and a new fuselage. The Model 429 is a twin-
engine, 4-bladed main and tail rotor helicopter with a maximum gross
weight of 7,000 pounds, capable of carrying up to nine passengers plus
a pilot. The helicopter will be designed for dual and single pilot
instrument flight rules (IFR) and Category A operations.

Type Certification Basis

    Under the provisions of 14 CFR 21.17, Bell Helicopter must show
that the Model 429 helicopter meets the applicable provisions of the
regulations as listed below:
    14 CFR part 27, Amendment 27-0 through Amendment 27-40 dated May 9,
2001.
    Sections of 14 CFR part 29, Amendment 29-14 dated September 1,
1977, as listed in 14 CFR part 27 Appendix B for instrument flight
rules (IFR).
    Sections of 14 CFR part 29 Amendment 29-0 through Amendment 29-47
dated May 9, 2001, as listed in 14 CFR part 27 Appendix C for Category
A.
    14 CFR part 36 Appendix H, Amendment 36-25, including FAA stage 3
noise limits for helicopters.
    Any special conditions, exemptions, and equivalent safety findings
deemed necessary.
    In addition, the certification basis includes certain special
conditions and equivalent safety findings that are not relevant to this
special condition.
    If the Administrator finds that the applicable airworthiness
regulations do not contain adequate or appropriate safety standards for
these helicopters 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, Bell Helicopter Model 429 helicopters must comply with the
noise certification requirements of 14 CFR part 36; and the FAA must
issue a finding of regulatory adequacy pursuant to Sec.  611 of Public
Law 92-574, the ``Noise Control Act of 1972.''
    Special conditions, as appropriate, are defined in Sec.  11.19, and
issued by following the procedures in Sec.  11.38, and become part of
the type certification basis in accordance with Sec.  21.17(a)(2).
    Special conditions are initially applicable to the model for which
they are issued. Should the type certificate for that model be amended
later to include any other model that incorporates 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 Bell Helicopter Model 429 helicopter will incorporate the
following novel or unusual design features: Electrical, electronic, or
combination of electrical electronic (electrical/electronic) systems
that perform critical control functions or provide critical displays,
such as electronic flight instruments that will be providing displays
critical to the continued safe flight and landing of the helicopter
during operation in Instrument Meteorological Conditions (IMC), and
Full Authority Digital Engine Control (FADEC) that will be performing
engine control functions that are critical to the continued safe flight
and landing of the helicopter during visual flight rules (VFR) and IFR
operations.

Discussion

    The Bell Helicopter Model 429 helicopter, at the time of
application, was identified as incorporating one and possibly more
electrical/electronic systems, such as electronic flight instruments
and FADEC. After the design is finalized, Bell Helicopter will provide
the FAA with a preliminary hazard analysis that will identify any other
critical functions, required for safe flight and landing, that are
performed by the electrical/electronic systems.
    Recent advances in technology have led to the application in
aircraft designs of advanced electrical/electronic systems that perform
critical control functions or provide critical displays. These advanced
systems respond to the transient effects of induced electrical current
and voltage caused by HIRF incident on the external surface of the
helicopter. These induced transient currents and voltages can degrade
the performance of the electrical/electronic systems by damaging the
components or by upsetting the systems' functions.
    Furthermore, the electromagnetic environment has undergone a
transformation not envisioned by the current application of 14 CFR
27.1309(a). Higher energy levels radiate from operational transmitters
currently used for radar, radio, and television. Also, the number of
transmitters has increased significantly.
    Existing aircraft certification requirements are inappropriate in
view of these technological advances. In addition, the FAA has received
reports of some significant safety incidents and accidents involving
military aircraft equipped with advanced electrical/electronic systems
when they were exposed to electromagnetic radiation.
    The combined effects of the technological advances in helicopter
design and the changing environment have resulted in an increased level
of vulnerability of the electrical/electronic systems required for the
continued safe flight and landing of the helicopter. Effective measures
to protect these helicopters against the adverse effects of exposure to
HIRF will be provided by the design and installation of these systems.
The following primary factors contributed to the current conditions:
(1) Increased use of sensitive electronics that perform critical
functions; (2) reduced electromagnetic shielding afforded helicopter
systems by advanced technology airframe materials; (3) adverse service
experience of military aircraft using these technologies; and (4) an
increase in the number and power of radio frequency

emitters and the expected increase in the future.
    On July 30, 2007, we issued a final HIRL rule (72 FR 44016, August
6, 2007). This rule provides standards to protect aircraft electrical
and electronic systems from HIRFs. It was effective September 5, 2007.
However, that rule included provisions that provide relief from the new
testing requirements for equipment previously certificated under HIRF
special conditions issued in accordance with 14 CFR 21.16. To obtain
this relief the applicant must be able to show that--
    (1) The system has previously been shown to comply with special
conditions for HIRF, prescribed under Sec.  21.16, issued before
December 1, 2007;
    (2) The HIRF immunity characteristics of the system have not
changed since compliance with the special conditions was demonstrated;
and
    (3) The data used to demonstrate compliance with the HIRF special
conditions is provided.
    The Bell 429 installations are eligible for this relief provided in
14 CFR 29.1317(d) of the final HIRF rule. However, to meet their HIRF
requirements they must comply with this Special Condition, which is
based on similar, historical HIRF protections requirements.
    Compliance with HIRF requirements will be demonstrated by tests,
analysis, models' similarity with existing systems, or a combination of
these methods. Service experience alone will not be acceptable since
such experience in normal flight operations may not include an exposure
to HIRF. Reliance on a system with similar design features for
redundancy as a means of protection against the effects of external
HIRF is generally insufficient because all elements of a redundant
system are likely to be concurrently exposed to the radiated fields.
    This special condition will require aircraft installed systems that
perform critical control functions or provide critical displays to meet
certain standards based on either a defined HIRF environment or a fixed
value using laboratory tests. Control system failures and malfunctions
can more directly and abruptly contribute to a catastrophic event than
display system failures and malfunctions. Therefore, it is considered
appropriate to require more rigorous HIRF verification methods for
critical control systems than for critical display systems.
    The applicant may demonstrate that the operation and operational
capabilities of the installed electrical/electronic systems that
perform critical functions are not adversely affected when the aircraft
is exposed to the defined HIRF test environment. We have determined
that the test environment defined in Table 1 is acceptable for critical
control functions in helicopters. The test environment defined in Table
2 is acceptable for critical display systems in helicopters.
    The applicant may also demonstrate, by a laboratory test, that the
electrical/electronic systems that perform critical control functions
or provide critical displays can withstand a peak electromagnetic field
strength in a frequency range of 10 kHz to 18 GHz. If a laboratory test
is used to show compliance with the defined HIRF environment, no credit
will be given for signal attenuation due to installation. A level of
100 volts per meter (v/m) is appropriate for critical display systems.
A level of 200 v/m is appropriate for critical control functions.
Laboratory test levels are defined according to RTCA/DO-160D Section 20
Category W (100 v/m and 150 mA) and Category Y (200 v/m and 300 mA). As
defined in DO-160D Section 20, the test levels are defined as the peak
of the root means squared (rms) envelope. As a minimum, the modulations
required for RTCA/DO-160D Section 20 Categories W and Y will be used.
Other modulations should be selected as the signal most likely to
disrupt the operation of the system under test, based on its design
characteristics. For example, flight control systems may be susceptible
to 3 Hz square wave modulation while the video signals for electronic
display systems may be susceptible to 400 Hz sinusoidal modulation. If
the worst-case modulation is unknown or cannot be determined, default
modulations may be used. Suggested default values are a 1 kHz sine wave
with 80 percent depth of modulation in the frequency range from 10 kHz
to 400 MHz, and 1 kHz square wave with greater than 90 percent depth of
modulation from 400 MHz to 18 GHz. For frequencies where the
unmodulated signal would cause deviations from normal operation,
several different modulating signals with various waveforms and
frequencies should be applied.
    Applicants must perform a preliminary hazard analysis to identify
electrical/electronic systems that perform critical functions. The term
``critical'' means those functions whose failure would contribute to or
cause an unsafe condition that would prevent the continued safe flight
and landing of the helicopter. The systems identified by the hazard
analysis as performing critical functions are required to have HIRF
protection. 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 indications. HIRF requirements would apply only
to the systems that perform critical functions, including control and
display.
    Acceptable system performance would be attained by demonstrating
that the critical function components of the system under consideration
continue to perform their intended function during and after exposure
to required electromagnetic fields. Deviations from system
specifications may be acceptable, but must be independently assessed by
the FAA on a case-by-case basis.

  Table 1.--Rotorcraft Critical Control Functions Field Strength Volts/
                                  Meter
------------------------------------------------------------------------
                   Frequency                        Peak       Average
------------------------------------------------------------------------
10 kHz-100 kHz................................          150          150
100 kHz-500 kHz...............................          200          200
500 kHz-2 MHz.................................          200          200
2 MHz-30 MHz..................................          200          200
30 MHz-70 MHz.................................          200          200
70 MHz-100 MHz................................          200          200
100 MHz-200 MHz...............................          200          200
200 MHz-400 MHz...............................          200          200
400 MHz-700 MHz...............................          730          200
700 MHz-1 GHz.................................         1400          240
1 GHz-2 GHz...................................         5000          250
2 GHz-4 GHz...................................         6000          490
4 GHz-6 GHz...................................         7200          400
6 GHz-8 GHz...................................         1100          170
8 GHz-12 GHz..................................         5000          330
12 GHz-18 GHz.................................         2000          330
18 GHz-40 GHz.................................         1000          420
------------------------------------------------------------------------

  Table 2.--Rotorcraft Critical Display Functions Field Strength Volts/
                                  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
------------------------------------------------------------------------

Applicability

    As previously discussed, this special condition is applicable to
the Bell Helicopter Model 429 helicopter. Should Bell Helicopter apply
at a later date for a change to the type certificate to include another
model incorporating the same novel or unusual design feature, the
special condition 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 series of helicopters. 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 helicopter.
    The substance of this special condition has been subjected to the
notice and comment period previously and is written without substantive
change from those previously issued. It is unlikely that prior public
comment would result in a significant change from the substance
contained in this special condition. For this reason, we have
determined that prior public notice and comment are unnecessary, and
good cause exists for adopting this special condition 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.

List of Subjects in 14 CFR Parts 21 and 27

    Aircraft, Air transportation, Aviation safety, Rotorcraft, Safety.

0
The authority citation for these special conditions is as follows:

    Authority: 42 U.S.C. 7572; 49 U.S.C. 106(g), 40105, 40113,
44701-44702, 44704, 44709, 44711, 44713, 44715, 45303.

The Special Condition

    Accordingly, pursuant to the authority delegated to me by the
Administrator, the following special condition is issued as part of the
type certification basis for Bell Helicopter Model 429 helicopters.

Protection for Electrical and Electronic Systems from High Intensity
Radiated Fields

    1. Each system that performs critical functions must be designed
and installed to ensure that the operation and operational capabilities
of these critical functions are not adversely affected when the
helicopter is exposed to high intensity radiated fields external to the
helicopter.
    2. For the purpose of this special condition, critical functions
are defined as those functions, whose failure would contribute to, or
cause, an unsafe condition that would prevent the continued safe flight
and landing of the aircraft.

    Issued in Fort Worth, Texas, on December 11, 2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
 [FR Doc. E7-25143 Filed 12-27-07; 8:45 am]

BILLING CODE 4910-13-P