63196 Federal Register / Vol. 65, No. 205 / Monday, October 23, 2000 / Rules and Regulations

made in order to provide better service

to borrowers.

We are also correcting a date in the

list of contract forms.

RUS received no comments to the

proposed regulation published in the

Federal Register on April 24, 2000, at

65 FR 21671.

List of Subjects in 7 CFR Part 1724

Electric power, Loan programs—

energy, Reporting and recordkeeping

requirements, Rural areas.

For the reasons set forth in the

preamble, RUS amends 7 CFR chapter

XVII by amending part 1724 as follows:

PART 1724—ELECTRIC

ENGINEERING, ARCHITECTURAL

SERVICES AND DESIGN POLICIES

AND PROCEDURES

1. The authority citation for part 1724

continues to read as follows:

Authority: 7 U.S.C. 901 et seq., 1921 et

seq., 6941 et seq.

2. Section 1724.54(f)(2) is revised to

read as follows:

§ 1724.54 Requirements for RUS approval

of plans and specifications.

* * * * *

(f) * * *

(2) Unless RUS approval is required

by paragraph (a) of this section, plans

and specifications for headquarters

buildings do not require RUS approval.

The borrower shall submit two copies of

RUS Form 740g, Application for

Headquarters Facilities. This form is

available from Program Development

and Regulatory Analysis, Rural Utilities

Service, United States Department of

Agriculture, Stop 1522, 1400

Independence Ave., SW., Washington,

DC 20250–1522. The application must

show floor area and estimated cost

breakdown between office building

space and space for equipment

warehousing and service facilities, and

include a one line drawing (floor plan

and elevation view), to scale, of the

proposed building with overall

dimensions shown. The information

concerning the planned building may be

included in the borrower’s construction

work plan in lieu of submitting it with

the application. (See 7 CFR part 1710,

subpart F.) Prior to issuing the plans

and specifications for bid, the borrower

shall also submit to RUS a statement,

signed by the architect or engineer, that

the building design meets the Uniform

Federal Accessibility Standards (See

§ 1724.51(e)(1)(i)).

* * * * *

3. Section 1724.74(d)(7) is revised to

read as follows:

§ 1724.70 List of electric program standard

contract forms.

* * * * *

(d) * * *

(7) RUS Form 284, Rev. 4–72, Final

Statement of Cost for Architectural

Service. This form is used for the

closeout of architectural services

contracts.

* * * * *

Dated: October 5, 2000.

Jill Long Thompson,

Under Secretary, Rural Development.

[FR Doc. 00–27155 Filed 10–20–00; 8:45 am]

BILLING CODE 3410–15–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. NM177; Special Conditions No.

25–163–SC]

Special Conditions: Canadair Model

CL–600–2B19 Series Airplanes; HighIntensity Radiated Fields (HIRF).

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final special conditions; request

for comments.

SUMMARY: These special conditions are

issued for Canadair Model CL–600–

2B19 series airplanes modified by

Rockwell Collins Flight Dynamics.

These modified airplanes will have a

novel or unusual design feature when

compared to the state of technology

envisioned in the airworthiness

standards for transport category

airplanes. The modification

incorporates the installation of a new

Head-Up Guidance System (HGS). The

HGS will utilize electrical and

electronic systems that perform critical

functions. The applicable airworthiness

regulations do not contain adequate or

appropriate safety standards for the

protection of this system 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 that established by the

existing airworthiness standards.

DATES: The effective date of these

special conditions is October 17, 2000.

Comments must be received on or

before November 22, 2000.

ADDRESSES: Comments on these special

conditions may be mailed in duplicate

to: Federal Aviation Administration,

Transport Airplane Directorate,

Attention: Rules Docket (ANM–114),

Docket No. NM177, 1601 Lind Avenue

SW., Renton, Washington 98055–4056;

or delivered in duplicate to the

Transport Airplane Directorate at the

above address. All comments must be

marked: Docket No. NM177. Comments

may be inspected in the Rules Docket

weekdays, except Federal holidays,

between 7:30 a.m. and 4:00 p.m.

FOR FURTHER INFORMATION CONTACT:

Gerald Lakin, FAA, Standardization

Branch, ANM–113, Transport Airplane

Directorate, Aircraft Certification

Service, 1601 Lind Avenue SW.,

Renton, Washington 98055–4056;

telephone (425) 227–1187; facsimile

(425) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA has determined that good

cause exists 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 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 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 these special

conditions must include a selfaddressed, stamped postcard on which

the following statement is made:

‘‘Comments to Docket No. NM177.’’ The

postcard will be date stamped and

returned to the commenter.

Background

On June 26, 2000, Rockwell Collins

Flight Dynamics, 16600 S.W. 72nd

Avenue, Portland, OR 97224, applied

for a Supplemental Type Certificate

(STC) for Canadair Model CL–600–2B19

series airplanes. The Model CL–600–

2B19 is a Model Regional Jet Series 100

passsenger airplane with two AVCO

Lycoming ALF–502L or ALF–502L–2

engines. These airplanes will

incorporate a Head-Up Guidance

System (HGS), manufactured by

Rockwell Collins Flight Dynamics,

which displays attitude and heading

information.

Federal Register / Vol. 65, No. 205 / Monday, October 23, 2000 / Rules and Regulations 63197

The HGS performs critical functions

associated with the display of attitude

and heading information to the pilot.

These functions can be susceptible to

disruption of both command and

response signals as a result of electrical

and magnetic interference caused by

high-intensity radiated fields (HIRF)

external to the airplane. This disruption

of signals could result in loss of critical

flight displays and annunciations, or

could present misleading information to

the pilot.

Type Certification Basis

Under the provisions of 14 CFR

21.101, Rockwell Collins Flight

Dynamics must show that the Model

CL–600–2B19 series airplanes, as

changed, continue to meet the

applicable provisions of the regulations

incorporated by reference in Type

Certificate No. A21EA, or the applicable

regulations in effect on the date of

application for the change. The

regulations incorporated by reference in

the type certificate are commonly

referred to as the ‘‘original type

certification basis.’’ The regulations

included in the certification basis for

the Model CL–600–2B19 series

airplanes include Title 14, Code of

Federal Regulations (14 CFR) part 25, as

amended by Amendments 25–1 through

25–62, plus additional requirements

listed in the type certificate data sheet

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 Model CL–600–2B19

series airplanes because of a novel or

unusual design feature, special

conditions are prescribed under the

provisions of § 21.16.

In addition to the applicable

airworthiness regulations and special

conditions, the Model CL–600–2B19

series airplanes must comply with the

fuel vent and exhaust emission

requirements of part 34 and the noise

certification requirements of part 36.

Special conditions, as appropriate, are

issued in accordance with § 11.49, as

required by §§ 11.28 and 11.29, and

become part of the airplane’s 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 included on the

same type certificate to incorporate the

same novel or unusual design features,

these special conditions would also

apply to the other model under the

provisions of § 21.101(a)(1).

Novel or Unusual Design Features

As stated earlier, the Model CL–600–

2B19 series airplanes modified by

Rockwell Collins Flight Dynamics will

incorporate a HGS system, which

performs critical functions. The HGS

system contains electronic equipment

for which the current airworthiness

standards of part 25 do not contain

adequate or appropriate safety standards

for the protection of this equipment

from the adverse effects of HIRF. This

system may be vulnerable to HIRF

external to the airplane. Accordingly,

this system is considered to be a novel

or unusual design feature.

Discussion

There is no specific regulation that

addresses the requirements for

protection of 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 that is equivalent to that

intended by the regulations

incorporated by reference, special

conditions are needed for the Model

CL–600–2B19 airplanes modified to

include the Rockwell Collins Flight

Dynamics HGS system. These special

conditions will require that this system,

which performs critical functions, 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 (HIRF)

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

electromagnetic energy to cockpitinstalled 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 rms

per meter 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. Both peak

and average field strength components

from the Table are to be demonstrated.

Frequency

Field strength (volts per meter)

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

63198 Federal Register / Vol. 65, No. 205 / Monday, October 23, 2000 / Rules and Regulations

Frequency

Field strength (volts per meter)

Peak Average

12 GHz–18 GHz ...................................................................................................................................................... 2000 200

18 GHz–40 GHz ...................................................................................................................................................... 600 200

The field strengths are expressed in terms of peak of the root-mean-square (rms) over the complete modulation period.

The threat levels identified above are

the result of an FAA review of existing

studies on the subject of HIRF, in light

of the ongoing work of the

Electromagnetic Effects Harmonization

Working Group of the Aviation

Rulemaking Advisory Committee.

Applicability

As discussed above, these special

conditions are applicable to Canadair

Model CL–600–2B19 series airplanes

modified by Rockwell Collins Flight

Dynamics to include the Rockwell

Collins Flight Dynamics HGS system.

Should Rockwell Collins Flight

Dynamics apply at a later date for a

supplemental type certificate to modify

any other model included on Type

Certificate A21EA to incorporate the

same novel or unusual design features,

these special conditions would apply to

that model as well under the provisions

of § 21.101(a)(1).

Conclusion

This action affects only certain novel

or unusual design features on Canadair

Model CL–600–2B19 series airplanes

modified by Rockwell Collins Flight

Dynamics. 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

airplanes.

The substance of the 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 25

Aircraft, Aviation safety, Reporting

and recordkeeping requirements.

The authority citation for these

special conditions is as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701,

44702, 44704.

The Special Conditions

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the following special

conditions are issued as part of the

supplemental type certification basis for

Canadair Model CL–600–2B19 series

airplanes modified by Rockwell Collins

Flight Dynamics.

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 highintensity radiated fields.

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 Renton, Washington, on October

17, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–27181 Filed 10–20–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 95

[Docket No. 30209; Amdt. No. 425]

IFR Altitudes; Miscellaneous

Amendments

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts

miscellaneous amendments to the

required IFR (instrument flight rules)

altitudes and changeover points for

certain Federal airways, jet routes, or

direct routes for which a minimum or

maximum en route authorized IFR

altitude is prescribed. This regulatory

action is needed because of changes

occurring in the National Airspace

System. These changes are designed to

provide for the safe and efficient use of

the navigable airspace under instrument

conditions in the affected areas.

EFFECTIVE DATE: 0901 UTC, November

30, 2000.

FOR FURTHER INFORMATION CONTACT:

Donald P. Pate, Flight Procedure

Standards Branch (AMCAFS–420),

Flight Technologies and Programs

Division, Flight Standards Service,

Federal Aviation Administration, Mike

Monroney Aeronautical Center, 6500

South MacArthur Blvd., Oklahoma City,

OK, 73169 (Mail Address: P.O. Box

25082 Oklahoma City, OK 73125)

telephone: (405) 954–4164.

SUPPLEMENTARY INFORMATION: This

amendment to part 95 of the Federal

Aviation Regulations (14 CFR part 95)

amends, suspends, or revokes IFR

altitudes governing the operation of all

aircraft in flight over a specified route

or any portion of that route, as well as

the changeover points (COPs) for

Federal airways, jet routes, or direct

routes as prescribed in part 95.

The Rule

The specified IFR altitudes, when

used in conjunction with the prescribed

changeover points for those routes,

ensure navigation aid coverage that is

adequate for safe flight operations and

free of frequency interference. The

reasons and circumstances that create

the need for this amendment involve

matters of flight safety and operational

efficiency in the National Airspace

System, are related to published

aeronautical charts that are essential to

the user, and provide for the safe and

efficient use of the navigable airspace.

In addition, those various reasons or

circumstances required making this

amendment effective before the next

scheduled charting and publication date

of the flight information to assure its

timely availability to the user. The

effective date of this amendment reflects

those considerations. In view of the