40638 Federal Register / Vol. 63, No. 146 /Thursday, July 30, 1998 /Rules and Regulations

accordance with section E of Appendix

A of this part, a statement that interest

cannot remain on deposit and that

payout of interest is mandatory.

* * * * *

3. Section 230.8 is amended by

revising paragraph (c)(6)(iii) to read as

follows:

§ 230.8 Advertising.

* * * * *

(c) * * *

(6) * * *

(iii) Required interest payouts. For

noncompounding time accounts with a

stated maturity greater than one year

that do not compound interest on an

annual or more frequent basis, that

require interest payouts at least

annually, and that disclose an APY

determined in accordance with section

E of Appendix A of this part, a

statement that interest cannot remain on

deposit and that payout of interest is

mandatory.

* * * * *

4. In Part 230, Appendix A is

amended by revising section E of Part I

to read as follows:

Appendix A To Part 230—Annual

Percentage Yield Calculation

* * * * *

E. Time Accounts with a Stated Maturity

Greater than One Year that Pay Interest At

Least Annually

1. For time accounts with a stated maturity

greater than one year that do not compound

interest on an annual or more frequent basis,

and that require the consumer to withdraw

interest at least annually, the annual

percentage yield may be disclosed as equal

to the interest rate.

Example

(1) If an institution offers a $1,000 two-year

certificate of deposit that does not compound

and that pays out interest semi-annually by

check or transfer at a 6.00% interest rate, the

annual percentage yield may be disclosed as

6.00%.

(2) For time accounts covered by this

paragraph that are also stepped-rate accounts,

the annual percentage yield may be disclosed

as equal to the composite interest rate.

Example

(1) If an institution offers a $1,000 threeyear certificate of deposit that does not

compound and that pays out interest

annually by check or transfer at a 5.00%

interest rate for the first year, 6.00% interest

rate for the second year, and 7.00% interest

rate for the third year, the institution may

compute the composite interest rate and APY

as follows:

(a) Multiply each interest rate by the

number of days it will be in effect;

(b) Add these figures together; and

(c) Divide by the total number of days in

the term.

(2) Applied to the example, the products of

the interest rates and days the rates are in

effect are (5.00%×365 days) 1825,

(6.00%×365 days) 2190, and (7.00%×365

days) 2555, respectively. The sum of these

products, 6570, is divided by 1095, the total

number of days in the term. The composite

interest rate and APY are both 6.00%.

* * * * *

By order of the Board of Governors of the

Federal Reserve System, July 24, 1998.

Jennifer J. Johnson,

Secretary of the Board.

[FR Doc. 98–20268 Filed 7–29–98; 8:45 am]

BILLING CODE 6210–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE146, Special Condition 23–

98–02–SC]

Special Conditions; Raytheon Aircraft

Company, Beech Model 3000 Airplane:

Protection of Systems From 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 Raytheon Aircraft Company,

9709 East Central, Wichita, Kansas

67201–0085 for a Type Certificate on the

Beech Model 3000 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 displays 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

that provided by the existing

airworthiness standards.

DATES: The effective date of these

special conditions is July 14, 1998.

Comments must be received on or

before August 31, 1998 for domestic,

November 27, 1998 for foreign.

ADDRESSES: Comments may be mailed

in duplicate to: Federal Aviation

Administration, Office of the Assistant

Chief Counsel, ACE–7, Attention: Rules

Docket Clerk, Docket No. CE146, Room

1558, 601 East 12th Street, Kansas City,

Missouri 64106. All comments must be

marked: Docket No. CE146. 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:

Ervin Dvorak, Aerospace Engineer,

Standards Office (ACE–110), Small

Airplane Directorate, Aircraft

Certification Service, Federal Aviation

Administration, 601 East 12th Street,

Kansas City, Missouri 64106; telephone

(816) 426–6941.

SUPPLEMENTARY INFORMATION: The FAA

has determined that notice and

opportunity for prior public comment

hereon are impracticable because these

procedures would significantly delay

issuance of the approval design and

thus delivery of the affected aircraft. In

addition, the substance of these special

conditions has been subject to the

public comment process in several prior

instances with no substantive comments

received. The FAA therefore finds that

good cause exists for making these

special conditions effective upon

issuance.

Comments Invited

Interested persons are invited to

submit such written data, views, or

arguments as they may desire.

Communications should identify the

regulatory docket or notice number and

be submitted in duplicate to the address

specified above. All communications

received on or before the closing date

for comments will be considered by the

Administrator. The special conditions

may be changed in light of the

comments received. All comments

received will be available in the Rules

Docket for examination by interested

persons, both before and after the

closing date for comments. A report

summarizing each substantive public

contact with FAA personnel concerning

this rulemaking will be filed in the

docket. Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must include a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

CE146.’’ The postcard will be date

stamped and returned to the

commenter.

Background

Beech Aircraft Corporation made

application for a new type certification

(TC) for the Beech Model 3000 airplane

on August 31, 1992, for the purpose of

entering the competition with several

other manufacturers for the contract to

build the Joint Primary Aircraft Training

System (JPATS) trainer aircraft. This

application was allowed to expire after

three years when it was determined that
Federal Register / Vol. 63, No. 146 /Thursday, July 30, 1998 /Rules and Regulations 40639

Beech Aircraft Corporation did not need

a TC in their name to be in the

competition. The Swiss TC for the

original Pilatus PC–9 airframe was

adequate for that purpose.

Beech made a new application for a

TC on January 15, 1996, when they were

awarded the contract. This is the

application that is still in force. On

April 15, 1996, Beech Aircraft

Corporation became Raytheon Aircraft

Company.

The proposed configuration

incorporates a novel or unusual design

feature, such as digital avionics

consisting of an electronic flight

instrument system (EFIS), that is

vulnerable to HIRF external to the

airplane.

Type Certification Basis

Under the provisions of 14 CFR part

21, 21.17, Raytheon Aircraft Company

must show that the Beech Model 3000

meets the applicable provisions of the

following:

The type certification basis for the

Beech Model 3000 airplane is given by

the following:

Federal Aviation Regulations part 23

effective February 1, 1965, as amended

by Amendments 23–1 through 23–47;

Federal Aviation Regulations §§ 23.201,

23.203 and 23.207 as amended by

Amendment 23–50; Federal Aviation

Regulations part 34 effective September

10, 1990, as amended by the

amendment in effect on the date of

certification; Federal Aviation

Regulations part 36 effective December

1, 1969, as amended by amendment 36–

1 through the amendment in effect on

the day of certification; The Noise

Control Act of 1972; and Special

Conditions for such items as Protection

from High Intensity Radiated Fields

(HIRF), Digital Electronic Engine

Control (DEEC) and the Section Defuel

System.

If the Administrator finds that the

applicable airworthiness regulations, 14

CFR part 23, do not contain adequate or

appropriate safety standards for the

Beech Model 3000 because of a novel or

unusual design feature, special

conditions are prescribed under the

provisions of § 21.16.

Special conditions, as appropriate, are

issued in accordance with § 11.49, as

required by §§ 11.28 and 11.29(b), and

become part of the type certification

basis in accordance with § 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 § 21.101(a)(1).

Novel or Unusual Design Features

The Beech Model 3000 will

incorporate the following novel or

unusual design features: Installation of

electronic equipment and displays for

which the airworthiness standards do

not contain adequate or appropriate

safety standards for protection from the

effects of HIRF.

Discussion

The FAA may issue and amend

special conditions, as necessary, as part

of the type certification basis if the

Administrator finds that the

airworthiness standards, designated

according to § 21.101(b), do not contain

adequate or appropriate safety standards

because of novel or unusual design

features of an airplane. Special

conditions are prescribed under the

provisions of § 21.16 to establish a level

of safety equivalent to that established

in the regulations. Special conditions

are normally issued according to

§ 11.49, after public notice, as required

by §§ 11.28 and 11.29(b), effective

October 14, 1980, and become a part of

the type certification basis in

accordance with § 21.101(b)(2).

Raytheon Aircraft Company plans to

incorporate certain novel and unusual

design features into an airplane for

which the airworthiness standards do

not contain adequate or appropriate

safety standards for protection from the

effects of HIRF. These features include

electronic systems, 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 previously 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 as follows:

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

12 GHz—18 GHz 2000 200

18 GHz—40 GHz 600 200
40640 Federal Register / Vol. 63, No. 146 /Thursday, July 30, 1998 /Rules and Regulations

Frequency

Field strength (volts

per meter)

peak average

The field strengths

are expressed in

terms of peak rootmean-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, peak 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

electrical and/or electronic systems that

perform critical functions. The term

‘‘critical’’ means those functions whose

failure would contribute to, or cause, a

failure condition that would prevent the

continued safe flight and landing of the

airplane. The systems identified by the

hazard analysis that perform critical

functions are candidates for the

application of HIRF requirements. A

system may perform both critical and

non-critical functions. Primary

electronic flight display systems, and

their associated components, perform

critical functions such as attitude,

altitude, and airspeed indication. The

HIRF requirements apply only to critical

functions.

Compliance with HIRF requirements

may be demonstrated by tests, analysis,

models, similarity with existing

systems, or any combination of these.

Service experience alone is not

acceptable since normal flight

operations may not include an exposure

to the HIRF environment. Reliance on a

system with similar design features for

redundancy as a means of protection

against the effects of external HIRF is

generally insufficient since all elements

of a redundant system are likely to be

exposed to the fields concurrently.

Applicability

As discussed above, these special

conditions are applicable to the Beech

Model 3000. Should Raytheon Aircraft

Company apply at a later date for a

supplemental type certificate or

amended type certificate to modify any

other model that may be included on

this Type Certificate incorporating, the

same novel or unusual design feature,

the 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 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

symbol

Citation

The authority citation for these

special conditions is as follows:

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

44701; 14 CFR part 21, §§ 21.16 and 21.17;

and 14 CFR part 11, §§ 11.28 and 11.49.

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

Aircraft Company, Beech Model 3000

airplane.

1. Protection of Electrical and

Electronic Systems from High Intensity

Radiated Fields (HIRF). Each system

that performs critical functions must be

designed and installed to ensure that the

operations, and operational capabilities

of these systems to perform critical

functions, are not adversely affected

when the airplane is exposed to 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 July 14,

1998.

Marvin Nuss,

Assistant Manager, Small Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20345 Filed 7–29–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–212–AD; Amendment

39–10676; AD 98–16–01]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain McDonnell

Douglas Model MD–11 series airplanes.

This action requires repetitive

inspections to measure for free play

(wear on nut assembly) of the horizontal

stabilizer actuator assembly, and

corrective actions, if necessary. This

amendment is prompted by reports of

wear of the horizontal stabilizer actuator

assembly due to a jackscrew surface

finish that was manufactured

incorrectly. The actions specified in this

AD are intended to prevent excessive

free play and wear of the horizontal

stabilizer actuator assembly, which

could result in a free-floating horizontal

stabilizer, and consequent loss of

aircraft pitch control.

DATES: Effective August 14, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 14,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

September 28, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

212–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from The

Boeing Company, Douglas Products