[Federal Register Volume 60, Number 216 (Wednesday, November 8, 1995)]
[Rules and Regulations]
[Pages 56223-56224]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-27705]



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 Rules and Regulations
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  Federal Register / Vol. 60, No. 216 / Wednesday, November 8, 1995 / 
Rules and Regulations  

[[Page 56223]]


DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. NM-119, Special Conditions No. 25-ANM-109]


Special Conditions: Bombardier Inc., Canadair Challenger CL-600-
2B16 (CL-604 Variant), High-Intensity Radiated Fields

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final special conditions; request for comments.

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

SUMMARY: These special conditions are issued for the Canadair 
Challenger CL-600-2B16 (CL-604 Variant) airplane. This airplane will 
utilize new avionic/electronic systems that provide critical data to 
the flightcrew. The applicable regulations do not contain adequate or 
appropriate safety standards for the protection of these systems from 
the effects of high-intensity radiated fields. These special conditions 
contain the additional safety standards that the Administrator 
considers necessary to establish a level of safety equivalent to that 
established by the existing airworthiness standards.

DATES: The effective date of these special conditions is October 31, 
1995. Comments must be received on or before December 26, 1995.

ADDRESSES: Comments on these final special conditions, request for 
comments, may be mailed in duplicate to: Federal Aviation 
Administration, Office of the Assistant Chief Counsel, Attn: Rules 
Docket (ANM-7), Docket No. NM-119, 1601 Lind Avenue SW., Renton, 
Washington 98055-4056; or delivered in duplicate to the Office of the 
Assistant Chief Counsel at the above address. Comments must be marked: 
Docket No. NM-119, Comments may be inspected in the Rule Docket 
weekdays, except Federal holidays, between 7:30 a.m. and 4 p.m.

FOR FURTHER INFORMATION CONTACT:
Gregory L. Dunn, FAA, Standardization Branch, ANM-113, Transport 
Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue 
SW., Renton, Washington, 98055-4056, (206) 227-2799.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA has determined that good cause exits for making these 
special conditions effective upon issuance; however, interested persons 
are invited to submit such written data, views, or arguments as they 
may desire. Communications should identify the regulatory docket and 
special conditions 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. These 
special conditions may be changed in light of comments received. All 
comments submitted 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. Persons wishing the FAA to acknowledge receipt of their 
comments submitted in response to this request must be submitted with 
those comments a self-addressed, stamped postcard on which the 
following statement is made: ``Comments to Docket No. NM-119.'' The 
postcard will be date stamped and returned to the commenter.

Background

    On June 14, 1993, Bombardier Inc., Candor, P.O. Box 6087, Station 
Centreville, Montreal, Quebec H3C 3G9, applied to Transport Canada for 
a type design change to their Type Certificate A21EA in the transport 
airplane category for the Model CL-600-2B16 (CL-604 Variant) airplane. 
The CL-604 Variant is a low swept wing, business jet airplane powered 
by two GE CF 34-3B turbofan engines mounted on pylons extending from 
the aft fuselage. The airplane has a seating capacity of up to nineteen 
passengers, and a maximum ramp weight of 48,300 pounds.

Type Certification Basis

    Under the provisions of Sec. 21.101 of the FAR, Canadair must show, 
except as provided in Sec. 25.2, that the Model CL-600-2B16 (CL-604 
Variant) meets the applicable provisions of part 25, effective February 
1, 1965, as amended by Amendments 25-1 through 25-78. In addition, the 
proposed certification basis for the Model CL-600-2B16 (CL-604 Variant) 
includes part 34, effective September 10, 1990, plus any amendments in 
effect at the time of certification; and part 36, effective December 1, 
1969, as amended by Amendment 36-1 through the amendment in effect at 
the time of certification. No exemptions are anticipated. The special 
conditions incorporated herein form an additional part of the type 
certification basis. In addition, the certification basis may include 
other special conditions that are not relevant to these special 
conditions.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., part 25, as amended) do not contain adequate or 
appropriate safety standards for the CL-600-2B16 (CL-604 Variant) 
because of a novel or unusual design feature, special conditions are 
prescribed under the provisions of Sec. 21.16 to establish a level of 
safety equivalent to that established in the regulations.
    Special conditions, as appropriate, are issued in accordance with 
Sec. 11.49 of the FAR after public notice, as required by Secs. 1128 
and 11.29, 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 type certificate for that model be amended 
later to include any other model that incorporates the same novel or 
unusual design feature, or should any other model already included on 
the same type certificate be modified 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(a)(1).

Novel of Unusual Design Features

    The Model CL-600-2B16 incorporates new avionic/electronic 
installations, including a digital Electronic Flight Instrument System 
(EFIS) and a limited Engine Indication and Crew Alerting System 
(EICAS). These systems may be 

[[Page 56224]]
vulnerable to high-intensity radiated fields (HIRF) external to the 
airplane.

Discussion

    There is no specific regulation that addresses protection 
requirements for electrical and electronic systems from HIRF. Increased 
power levels from ground based radio transmitters and the growing use 
of sensitive electrical and electronic systems to command and control 
airplanes have made it necessary to provide adequate protection.
    To ensure that a level of safety is achieved equivalent to that 
intended by the regulations incorporated by reference, special 
conditions are issued for Canadair CL-600-2B16 (CL-604 Variant) which 
require that new technology electrical and electronic systems, such as 
the EFIS and EICAS, be designed and installed to preclude component 
damage and interruption of function due to both the direct and indirect 
effects of HIRF.

High-Intensity Radiated Fields

    With the trend toward increased power levels from ground based 
transmitters, plus the advent of space and satellite communications 
coupled with electronic command and control of the airplane, the 
immunity of critical digital avionics systems to HIRF must be 
established.
    It is not possible to precisely define the HIRF to which the 
airplane will be exposed in service. There is also uncertainty 
concerning the effectiveness of airframe shielding for HIRF. 
Furthermore, coupling of eletromagnetics energy to cockpit-installed 
equipment through the cockpit window apertures is undefined. Based on 
surveys and analysis of existing HIRF emitters, an adequate level of 
protection exists when compliance with the HIRF protection special 
condition is shown with either paragraph 1 or 2 below:
    1. A minimum threat of 100 volts per meter peak electric field 
strength from 10 KHz to 18 GHz.
    a. The threat must be applied to the system elements and their 
associated wiring harnesses without the benefit of airframe shielding.
    b. Demonstration of this level of protection is established through 
system tests and analysis.
    2. A threat external to the airframe of the following field 
strengths for the frequency ranges indicated.

------------------------------------------------------------------------
                                                          Peak   Average
                       Frequency                         (V/M)     (V/M)
------------------------------------------------------------------------
10 KHz-100 KHz........................................       50       50
100 KHz-500 KHz.......................................       60       60
500 KHz-2000 KHz......................................       70       70
2 MHz-30 MHz..........................................      200      200
30 MHz-100 MHz........................................       30       30
100 MHz-200 MHz.......................................      150       33
200 MHz-400 MHz.......................................       70       70
400 MHz-700 MHz.......................................    4,020      935
700 MHz-1000 MHz......................................    1,700      170
1 GHz-2 GHz...........................................    5,000      990
2 GHz-4 GHz...........................................    6,680      840
4 GHz-6 GHz...........................................    6,850      310
6 GHz-8 GHz...........................................    3,600      670
8 GHz-12 GHz..........................................    3,500    1,270
12 GHz-18 GHz.........................................    3,500      360
18 GHz-40 GHz.........................................    2,100      750
------------------------------------------------------------------------

    As discussed above, these special conditions would be applicable 
initially to the Model CL-600-2B16 (CL-604 Variant). Should Canadair 
apply at a later date for a change to the type certificate to include 
another model incorporating the same novel or unusual design feature, 
these special conditions would apply to that model as well, under the 
provisions of Sec. 21.101(a)(1).
    Under standard practice, the effective date of final special 
conditions would be 30 days after the date of publication in the 
Federal Register. However, as the certification date for the Bombardier 
Inc., Canadair Challenger CL-600-2B16 (CL-604 Variant) is imminent, the 
FAA finds that good cause exists for making these special conditions 
effective upon issuance.

Conclusion

    This action affects certain design features only on the Canadair 
CL-600-2B16 (CL-604 Variant) airplane. It is not a rule of general 
applicability and affects only the manufacturer who applied to the FAA 
for approval of these features on the airplane.

List of Subjects in 14 CFR Part 25

    Aircraft, Aviation safety, Federal Aviation Administration, 
Reporting and recordkeeping requirements.

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

    Authority: 49 U.S.C. app. 1344, 1348(c), 1352, 1354(a), 1355, 
1421 through 1431, 1502, 1651(b)(2), 42 U.S.C. 1857f-10, 4321 et 
seq.; E.O. 11514; and 49 U.S.C. 106(g).

The Special Conditions

    Accordingly, the following special conditions are issued as part of 
the type certification basis for the Bombardier Inc., Canadair Model 
CL-600-2B16 (CL-604 Variant) airplanes.
    1. Protection from Unwanted Effects of High-Intensity Radiated 
Fields (HIRF). Each electrical and electronic system that performs 
critical functions must be designed and installed to ensure that the 
operation and operational capability of these systems to perform 
critical functions are not adversely affected when the airplane is 
exposed to high-intensity radiated fields.
    2. For the purpose of this special conditions, the following 
definition applies: Critical Functions. Functions whose failure would 
contribute to or cause a failure condition that would prevent the 
continued safe flight and landing of the airplane.

    Issued in Renton, Washington, on October 31, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service, ANM-100.
[FR Doc. 95-27705 Filed 11-7-95; 8:45 am]
BILLING CODE 4910-13-M